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| 11:00 | 11:25 | 1.1.1 |
SUSTAINABLE AVIATION TECHNOLOGY PROGRAMMES IN EUROPE A. Krein, Clean Aviation, Germany invited speaker for the Global Sustainable Aviation track | ||||
| 11:25 | 11:50 | 1.1.2 |
UNITED STATES\' AIRCRAFT SUSTAINABILITY RESEARCH & DEVELOPMENT EFFORTS A. Orton, Federal Aviation Administration, United States; R. Guerrero, United States Air Force, United States; R. Wahls, National Aeronautics and Space Administration, United States Invited speaker for the Global Sustainable Aviation track | ||||
| 11:50 | 12:15 | 1.1.3 |
A VIEW LOOKING IN - AVIATION WEEK\'S ASSESSMENT OF SUSTAINABLE AVIATION R&D IN CHINA AND THE ASIA-PACIFIC REGION G. Warwick¹, G. Norris¹; ¹Aviation Week, United States Invited speaker for the Global Sustainable Aviation track | ||||
| 12:15 | 12:40 | 1.1.4 |
Q&A - MINI PANEL Q&A A, Q&A - MINI PANEL | ||||
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| 11:00 | 11:25 | 2.1.1 |
GLOBAL SENSITIVITY ANALYSIS OF LIQUID HYDROGEN STORAGE DESIGN PARAMETERS FOR OVERALL AIRCRAFT DESIGN T. Burschyk¹, B. Fröhler¹, M. Alder¹, T. Zill¹; ¹DLR, Institute for System Architectures in Aeronautics, Germany To systematically address the uncertainties and assumptions for hydrogen-powered aircraft concepts, a global sensitivity analysis is carried out. Recognizing the interdependencies between the overall aircraft design and liquid hydrogen storage through an integrated process, this study aims for the identification of key factors influencing the liquid hydrogen system design. | ||||
| 11:25 | 11:50 | 2.1.2 |
GEOMETRIC OPTIMIZATION OF HYDROGEN AIRCRAFT FUSELAGES IN PRELIMINARY DESIGN M. Engelmann¹, M. Hornung¹; ¹Bauhaus Luftfahrt e.V., Germany This paper introduces a methodology to assess hydrogen aircraft fuselages in preliminary design. Considering the overall tank arrangement, number of passengers, seat abreast and more, the tool derives a variety of fuselage geometries. These concepts are then evaluated on both fuselage and overall aircraft level using key parameters to identify the optimum configurations for the given input. | ||||
| 11:50 | 12:15 | 2.1.3 |
RESULTS FROM THE APPU PROJECT: THE POTENTIAL OF LOW-THRESHOLD HYDROGEN-POWERED BLI PROPULSION A. Heidebrecht¹, M. Hoogreef¹, A.T. Isikveren, SAFRAN S.A., Germany; A. Gangoli Rao¹; ¹TU Delft, Netherlands We investigated replacing the conventional APU of a passenger aircraft with an auxiliary hydrogen-driven, boundary-layer-ingesting engine, as part of a aircraft model upgrade. Although only about 15% of peak thrust are produced from H2, the climate impact can be reduced by over 20%. The concept is geared at very fast entry to market and includes contingencies, e.g. in case no H2 is available. | ||||
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| 11:00 | 11:25 | 3.1.1 |
SET-BASED DESIGN TECHNIQUES FOR EVOLVABILITY EXPLORATION DURING CONCEPTUAL AIRCRAFT DESIGN A.S.J. van Heerden, University of Glasgow, United Kingdom; S. Jimeno Altelarrea¹, A. Riaz¹, X. Chen¹, M.D. Guenov¹, A. Molina-Cristóbal, University of Glasgow Singapore, Singapore; ¹Cranfield University, United Kingdom Presenter: Sergio Jimeno Altelarrea, Cranfield University This paper presents computational techniques for applying set-based design to aircraft evolvability studies during conceptual design. Specifically, it is shown how the set-based design criteria of ‘interval dominance,’ ‘maximality,’ and ‘E-admissibility’ can be extended to enable swift, systematic, and interactive reduction of the evolvability design space. | ||||
| 11:25 | 11:50 | 3.1.2 |
FAST PARAMETRIC STRUCTURE MODELING FOR VARIETY OF AIRCRAFT CONFIGURATIONS Y.-L. Yin¹, K.-S. Zhang¹, H.-L. Qiao¹, A.-L. Che¹, Z.-H. Han¹; ¹School of Aeronautics, Northwestern Polytechnical University, China This work proposed a surface discretization method to attain fast parametric structure modeling for complete aircraft configurations. The geometric model is established in a discretized way at the beginning of parametric modeling process instead of being discretized after finite element (FE) analysis is started. Then FE meshing becomes faster and more likely to succeed, and the design zones can be easily grouped. It’s successfully applied in modeling supersonic transport, tailless fighter and flying-wing bomber. | ||||
| 11:50 | 12:15 | 3.1.3 |
TRANSIENT SIMULATION CALCULATION FOR ELECTRIC THERMAL ANTI-ICING PERFORMANCE OF COMPOSITE WING IN ICING ENVIRONMENT Z. Dong¹, X. Guo¹, W. Dong¹, P. Wang¹; ¹Shanghai Jiaotong University, China This article focuses on the composite material electric anti-icing technology. With the consideration of external water evaporation, the surface ice surface undergoes freezing, semi-melting (dynamic equilibrium of the surface), and melting processes during the electric heating process. In a one-dimensional process, composite materials can be simplified into several interlayers, assuming that the physical properties in the horizontal direction are the same, the characteristic length in the horizontal direction far exceeds that in the vertical direction, and the boundary conditions are the third type of boundary conditions on both sides; For two-dimensional processes, more information is needed, including adiabatic side boundary conditions and different convective parameters in the outer surface flow field. For the heat flux towards the surface and inside during the heating process, one method is that the explict format can be used to assume the initial condition time iteration, and on the other hand, the heat flux condition can be used for iteration. Due to the complexity of the two-dimensional calculation process, we can also calculate theoretical solutions for each layer and use numerical iterations to significantly reduce computational complexity, thereby obtaining data for optimization. Optimization includes material physical properties and heat flow time distribution patterns to achieve the optimal anti-icing effect. | ||||
| 12:15 | 12:40 | 3.1.4 |
TILT-DUCT AIRCRAFT WING AERODYNAMIC DESIGN AND OPTIMIZATION BASED ON ADJOINT METHOD Y.-T. Zhang¹, S.-R. Xu¹, Z.-J. Zheng¹, Y. Zheng¹, Y.-L. Liu¹; ¹Zhejiang University, China Presenter: Shangru Xu, Zhejiang University Tilt-duct aircraft, which combines the advantages of high speed and efficiency of fixed wing aircraft and vertical takeoff and landing and hovering of helicopters, is an important trend in the development of future aircraft. Aerodynamic optimization is an important means to enhance the overall performance of tilt-duct aircraft. Compared to traditional aerodynamic optimization methods using finite difference method for gradient calculation, the adjoint method can obtain the gradient of the objective function by solving the equation in one go, which has higher computational efficiency. For tilt-duct wing aerodynamic design optimization problems containing large-scale design variables, the adjoint method has great advantages. Therefore, we use adjoint-based aerodynamic design optimization of tilt-duct aircraft wing, to achieve higher lift-to-drag ratio at desired flight conditions. | ||||
| additional information (interactive) | 3.1.R |
APPLICATION OF LAMBDA FRAMEWORK FOR AIRCRAFT MULTIDISCIPLINARY DESIGN, ANALYSIS AND OPTIMIZATION S. Hosseini¹, M.A. Vaziry Zanjany¹, H.R. Ovesy¹, E. Lekzian, Semnan University, Iran; ¹Amirkabir University of Technology, Iran | |||||
| additional information (interactive) | 3.1.R |
AICRAFT-0 SAT D1 FOR GREENER, SAFER AND AFFORDABLE MORE ELECTRIC (MEA) AND FLY-BY-WIRE (FBW) SMALL AIR TRANSPORT (SAT) M. Alberti¹, G. Apuleo¹, A. Calia¹, D. Cirio¹, A. Cozzolino¹, F. Gravano¹, M. Mancini¹, F. Nunciato¹, A. Terrile¹; ¹Piaggio Aerospace, Italy | |||||
| additional information (interactive) | 3.1.R |
THE INFLUENCE OF DIFFERENT WING MOTIONS ON THE LIFT IN BIO-INSPIRED AERIAL VEHICLES B.T.V. Carnielo¹, D.D. Bueno¹; ¹São Paulo State University, Brazil | |||||
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| 11:00 | 11:25 | 4.1.1 |
AIRCRAFT SYSTEM DESIGN: A MODEL-BASED AND COLLABORATIVE APPROACH V. Voth¹, O. Bertram¹; ¹German Aerospace Center (DLR), Germany This paper investigates challenges in decentralized aviation system development. With globalized teams, traditional document-centric methods become cumbersome. Model-Based Systems Engineering (MBSE) is explored as a solution, reducing document reliance, improving collaboration and providing a centralized system model for consistency. The paper aims to integrate aircraft design and MBSE for more efficient and cohesive development in the aerospace industry. The research introduces a model-based multidisciplinary method, demonstrated through a use case. | ||||
| 11:25 | 11:50 | 4.1.2 |
TECHMAPS – TECHNOLOGY MANAGEMENT FOR THE ARCHITECTING PROCESS OF AIRCRAFT ON-BOARD SYSTEMS N. Kuelper¹, V. Kriewall¹, K. Beschorner¹, F. Thielecke¹; ¹Hamburg University of Technology, Germany For low emission aviation, existing and novel technologies are investigated. However, navigating technology knowledge is challenging, requiring support to explore technologies during conceptual design. Thus, the Technology Management for Architecting Process of on-board Systems (TechMAPS) method is developed, enabling conservation of standardized knowledge, while considering intellectual property. | ||||
| 11:50 | 12:15 | 4.1.3 |
MODEL-BASED APPROACH FOR HYDROGEN PRELIMINARY AIRCRAFT DESIGN CONSIDERING SAFETY AND OPERABILITY A. Sarr¹, J. Jézégou¹, P. de Saqui-Sannes¹; ¹ISAE-SUPAERO, France This paper proposes a model based approach for system modelling and safety assessment for a tube-and-wing liquid hydrogen fuelled aircraft considering operability. System Engineering and Safety Assessment tools and methods are applied during the process. Initial analyses show that new functions need to be considered at aircraft and system levels since they would impact the preliminary design. | ||||
| 12:15 | 12:40 | 4.1.4 |
SAFETY ANALYSIS (CCA) OF THE AIR SUPPLY SYSTEM OF A FUEL CELL-POWERED AERO ENGINE FOR ELECTRIC REGIONAL AIRCRAFT S. Kazula, DLR - Electrified Aero Engines, Germany By means of a Common Cause Analysis (CCA), potential safety challenges of the air supply system for polymer electrolyte membrane fuel cell systems (PEMFCSs) as the primary energy provider in electric aero engines are identified and mitigated. The design of an exemplary hydrogen-fuelled PEMFCS-powered aero engine is described, focusing on the air supply system. The safety assessment method CCA, consisting of a Zonal Safety Analysis (ZSA), a Particular Risk Analysis (PRA) and a Common Mode Analysis (CMA), is described and conducted on the PEMFCS aero engine’s air supply system. Failure modes and external events, which can have safety effects are identified, and potential design adaptations for mitigation are presented. | ||||
| additional information (interactive) | 4.1.R |
RESEARCH ON TECHNOLOGICAL INNOVATION CAPABILITY EVALUATION INDEX FOR AVIATION INDUSTRIES W. CHENG¹, R. FAN, Aviation Industry Corporation of China, Ltd (AVIC), China; J. XU¹, H. ZHANG¹, Z. WANG¹; ¹Aviation Industry Development Research Center of China (ADR), China | |||||
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| 11:00 | 11:25 | 5.1.1 |
EFFECTIVENESS OF CFD FOR AIRCRAFT DESIGN: STATUS AND PROSPECTS P. Raj, Virginia Tech, United States Presenter: Pradeep Raj, Virginia Tech A fully effective CFD that delivers credible aerodynamic data on time and on budget is crucial to developing quality affordable aircraft. From five decades of experience, author asserts that RANS cannot produce credible data due to turbulence [and transition] modeling deficiencies anytime soon--if ever. Long-term (DNS), mid-term (LES), and near-term (TicTac) options are discussed in the paper. | ||||
| 11:25 | 11:50 | 5.1.2 |
EFFECTIVENESS OF CFD FOR AIRCRAFT DESIGN: STATUS AND PROSPECTS PART 2 P. Raj, United States A fully effective CFD that delivers credible aerodynamic data on time and on budget is crucial to developing quality affordable aircraft. From five decades of experience, author asserts that RANS cannot produce credible data due to turbulence [and transition] modeling deficiencies anytime soon--if ever. Long-term (DNS), mid-term (LES), and near-term (TicTac) options are discussed in the paper. | ||||
| 11:50 | 12:15 | 5.1.3 |
COMPUTATIONAL ANALYSIS ON THE EFFECTS OF LEADING EDGE TUBERCLES ON THE PERFORMANCE OF ROTATING PROPELLER D. Di Pasquale¹, T. Tarun, Indian Institute of Technology(BHU) , India; S. Shubham¹, S.A. Prince¹, A. Proenca¹; ¹Cranfield University, United Kingdom This research paper focuses on investigating the effect of leading edge tubercles on the performance of rotating propeller. The primary objective of this study is to assess if bio-mimic passive flow control techniques such as tubercles could be employed to suppress flow separation on propeller blades, and thereby delay the onset of transition that leads to recirculation vortices caused by the stimulus of flow breakdown. The study involved the assessment of various leading edge tubercles of various sizes and extent on a three blade propeller. Preliminary RANS CFD investigations have shown that these tubercles can have a positive effect in term of thrust produced. These results will further be validated against other two different numerical solver. An unsteady solver based on a vorticity panel code and another solver based on a Lattice Boltzmann Method (LBM). The three aerodynamic methods will be discussed and compared in term of numerical results, stability, robustness, and numerical efficiency. Additionally, experimental test will be performed for further validation using a new propeller rig already designed and manufactured at Cranfield University and capable of measuring propeller thrust. The primary focus is the validation of tools and methods that can be used to design and analysing of the next generation of rotorcraft. | ||||
| 12:15 | 12:40 | 5.1.4 |
INITIAL DEVELOPMENT OF A CFD ICING TOOL J.R. Teixeira Da Silva¹, M.E.M.C. Lopes¹, A.P.R. Preguica¹, C.F. Rafael¹, P.C. Souza Villela¹, G.A. Lima da Silva, Aerothermal Solutions and Software Distributor LLC, United States; H. Jasak, Cambridge University, United Kingdom; ¹ATS Aerothermal Solutions, Brazil This paper introduces iceAccretionRimeFoam, a 3D ice accretion tool in Foam-extend 5.0 CFD suite. It simulates rime ice growth on NACA0012 airfoil using Eulerian droplet trajectories and evaluates solver accuracy. It considers parameters like droplet size, liquid content, airspeed, temperature, ice density, and droplet distribution. | ||||
| additional information (interactive) | 5.1.R |
CONJUGATED HEAT TRANSFER SIMULATION OF BUOYANCY-INDUCED FLOW AND HEAT TRANSFER MECHANISMS IN A COMPRESSOR CAVITY M. Jian¹, Y. Xiao¹, X. Cheng¹, W. Dong¹; ¹Shanghai Jiao Tong University, China | |||||
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| 11:00 | 11:25 | 6.1.1 |
A CFD STUDY OF THE ACTIVE FLOW CONTROL SYSTEM BEHAVIOUR ON A VERTICAL TAIL SECTION OF AN AIRPLANE, WITH THE AID OF AI C. Cordoni¹, A. Saporiti¹, M. Boffadossi¹; ¹DAER, Politecnico di Milano, Via La Masa 34, 20156 Milano, Italy, Italy CFD study of an active flow control (AFC) system on a full-scale vertical tail section of an airplane. The rudder is subjected to fluidic oscillators (FOs) action, which are introduced as boundary conditions. Results are used with Artificial Intelligence (AI) to obtain a control-law for the AFC system so to gain optimal aerodynamics performances. | ||||
| 11:25 | 11:50 | 6.1.2 |
GENETIC ALGORITHM OPTIMIZATION OF AN OPPOSITION CONTROL STRATEGY IN A FULLY TURBULENT CHANNEL FLOW E. Saccaggi¹, G.M. Di Cicca¹; ¹Politecnico di Torino, Italy Presenter: Enrico Saccaggi, Politecnico di Torino The proposed study investigates a real-time opposition control strategy to reduce the skin friction drag driven by a genetic algorithm optimization. The experiments are conducted in a fully turbulent channel flow having the friction Reynolds number Re? = 270. Opposition control of sweep events is carried out using a wall-normal jet. Changes to the turbulence structure in the region closer to the wall are examined using hot-wire anemometry. By using a genetic algorithm, amplitude, frequency, and phase are optimized to minimize the skin friction drag. | ||||
| 11:50 | 12:15 | 6.1.3 |
FAULT DIAGNOSIS AND TOLERANCE SYSTEM OF FLIGHT STATE PERCEPTION MODEL BASED ON MACHINE LEARNING FOR CO-FLOW JET AIRFOIL Y.-R. Zhao, China; B.-G. Mi, China; H. Zhan, China; H.-Y. Xu, China A flight state perception model for CFJ airfoil has been developed using DNNs. To enhance robustness, a fault diagnosis method using random forest classification algorithm is proposed. A fault diagnosis and tolerance system for CFJ airfoil’s flight state perception model is constructed, ensuring accurate prediction even with pressure measurement point malfunctions. | ||||
| 12:15 | 12:40 | 6.1.4 |
NUMERICAL INVESTIGATION OF THE FLOW FEATURES ON THE TURRET WITH DIFFERENT CYLINDER HEIGHT IN THE TRANSONIC FLOW X.-T. Tan¹, H.-Y. Xu¹, Z. Pei¹; ¹Northwest Polytechnic University, China IDDES is performed to investigate the effect of varying heights of cylinder on the turret at transonic Mach number Ma=0.7. Five levels of height are discussed, ranging from 0 to R. Mean and statistical results are used to compare the effect of the cylinder height. POD and DMD are performed on flow data to further investigate the spatial and temporal characteristics of dominant unsteady modes. | ||||
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| 11:00 | 11:25 | 7.1.1 |
ADVANCING URBAN AIR MOBILITY: COLLABORATIVE EXCELLENCE AND INFRASTRUCTURE INITIATIVES BY DLR O. Bertram¹, B. Schuchardt¹, A. König¹, K. Wendt¹, P. Shiva Prakasha¹; ¹DLR, Germany This paper showcases the HorizonUAM project's pioneering advancements in eVTOL development and the planned establishment of regulatory sandboxes at airports. Emphasizing MBSE, it delves into the collaborative approach and interdisciplinary cooperation within DLR’s HorizonUAM project. The integration of disciplines, strategic utilization of DLR resources, and the implementation of regulatory sandboxes for testing are discussed. The paper underscores ongoing collaboration, innovation, and the HorizonUAM project's significance in shaping AAM. | ||||
| 11:25 | 11:50 | 7.1.2 |
NASA’S ADVANCED AIR MOBILITY RESEARCH P.H. Kopardekar, United States The research work will provide a comprehensive view of the advanced air mobility related eco-system wide research considerations. These considerations will cover aircraft, airspace, and infrastructure. On aircraft side, fundamental considerations such as design safety, aircraft noise, handling quality issues will be discussed. On airspace side, information, technologies and procedures needed to accommodate electric and/or autonomous aircraft in the airspace system will be examined. Regarding infrastructure, considerations such as ability persistent communications, navigation, surveillance will be discussed. Additionally, near-term and long-term transformative impact of Advanced Air Mobility will be discussed in this presentation. | ||||
| 11:50 | 12:15 | 7.1.3 |
IFAR-X: COLLABORATIVE ENGINEERING FRAMEWORK FOR NEXT GENERATION OF AEROSPACE ENGINEERS WORKING ON AIRCRAFT DESIGN S. Garg¹, A.M.P. Silva², P.F. Albuquerque², E. Nguyen Van, The French Aerospace Lab (Onera), France; K. Kimura³, Y. Sugioka³, M. Jacinto¹, P. Shiva Prakasha¹, B. Nagel¹; ¹German Aerospace Center (DLR), Germany ;²Centre of Engineering and Product Development (CEiiA), Portugal ;³Japan Aerospace Exploration Agency (JAXA), Japan IFAR-ECN 2023 conference brought 18 IFAR member together, to introduce the next generation of engineers to the Collaborative Engineering Framework (CEF). This paper presents the framework and guidelines, using a high aspect ratio wing (HAW) aircraft design to showcase the collaborative efforts across multiple institutes, establishing a reference aircraft for future IFAR-ECN events. | ||||
| 12:15 | 12:40 | 7.1.4 |
AIRCRAFT WING STRUCTURAL SIZING COMPUTATIONAL TOOL TAILORED FOR A COLLABORATIVE MULTIDISCIPLINARY DESIGN FRAMEWORK P.F. Albuquerque¹, A.M.P. Silva¹, A. Pereira¹; ¹CEiiA, Portugal Presenter: Ana Silva, CEiiA This article presents two innovative tools, WinG3N and WingSizer, designed to streamline the traditional process of hand-made model development for aircraft wings. WinG3N enables the automatic generation of a wing finite element model within seconds. The WingSizer automates the sizing process for static and buckling analyses. It enables benchmark studies between metallic and composite structures. | ||||
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| 11:00 | 11:25 | 8.1.1 |
EXPERIMENTAL AND NUMERICAL INVESTIGATION OF A STRUCTURAL-DYNAMICALLY SCALED DELTA WING WITH TRAINING EDGE FLAPS K. Bantscheff¹, F. Santelli¹, C. Breitsamter¹; ¹Technische Universität München / Lehrstuhl für Aerodynamik, Germany Presenter: Konstantin Bantscheff, Technische Universität München / Lehrstuhl für Aerodynamik The main objective of this work focuses on the conduction of experimental investigations of a newly developed aeroelastically scaled delta wing featuring deflectable trailing edge flaps. The model at hand is used to study the effects of different flap angles on the occurring flow phenomena for low Mach numbers and stationary inflow conditions considering dynamic deformations. | ||||
| 11:25 | 11:50 | 8.1.2 |
EVALUATION OF WIND TUNNEL TEST RESULTS OF TAXIDERMY BLACK-TAILED GULL (LARUS CRASSIROSTRIS) N. Kishimoto, Kwansei Gakuin University, Japan; D. Wada¹, M. Tamayama¹, Y. Iwami², N. Tomita², T. Ikeda³, Y. Tanahashi³, K. Katagiri, Hiroshima University, Japan; ¹JAXA, Japan ;²Yamashina Institute of Ornithology, Japan ;³Chubu University, Japan In this paper, we reported the aerodynamic results of a wind tunnel experiment on taxidermy black-tailed gulls, a 3D printed model and a 2D aluminum plate based on scan data of taxidermy specimen. Due to manufacturing method issues, we improved the taxidermy specimen by creating a 3D-printed body based on the X-ray CT data of the black-tailed gull. In these experiments, we also measured deformation using stereo viewing and experimented with varying the yaw angle. | ||||
| additional information (interactive) | 8.1.R |
EXPLORING WINGTIP COLUMNAR VORTEX GENERATORS FOR UAV PERFORMANCE ENHANCEMENT R. Bardera¹, A.A. Rodríguez-Sevillano², J.C. Matías¹, E. Barroso¹, M. Ojeda², J. Fernández²; ¹Instituto Nacional de Técnica Aeroespacial (INTA)., Spain ;²Escuela Técnica Superior de ingeniería Aeronáutica y del Espacio, Spain | |||||
| additional information (interactive) | 8.1.R |
INFLUENCE OF REINFORCED TRAILING EDGE ON FLAPPING WING AERODYNAMIC FORCE AND DEFORMATION Y.-F. Wang¹, B.-F. Song¹, Y. Luo¹, X.-Y. Lang¹, W. Wang¹; ¹Northwestern Polytechnical University, China | |||||
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| 11:00 | 11:25 | 9.1.1 |
EFFICIENT THERMOMECHANICAL SIMULATION FOR METALLIC LATTICE STRUCTURES FABRICATED BY ADDITIVE MANUFACTURING N. Tsushima, Japan Aerospace Exploration Agency, Japan; M. Kita¹, I. Matsubara¹, M. Ohishi, Ryoyu Systems Co., Ltd., Japan; R. Higuchi, 2The University of Tokyo, Japan; K. Yamamoto¹; ¹3Cybernet Systems Co., Ltd., Japan In this study, the efficiency and accuracy of different heat source models and numerical configurations in thermomechanical simulations are investigated. We focus on the powder bed fusion (PBF) process, which is one of the popular processes offering compatibility with metal alloys for practical stiffness and strength properties. Structural characteristics of lattice structures with geometrical predictions of fabricated lattice structures with various thermomechanical simulations are also investigated to evaluate the feasibilities of each simulation model in terms of computational efficiency and accuracy. The study provides a better understanding of the fabrication process and resulting geometrical deviation of lattice structures by the AM. | ||||
| 11:25 | 11:50 | 9.1.2 |
USE OF GRAPHENE MATERIAL IN AIRCRAFT STRUCTURE FOR LIGHTNING STRIKE PROTECTION P. Jha¹, V.M. Sharma¹, V. Samanyusree¹, A. Sharma¹, S. Maheshwari¹; ¹R. V. College of Engineering, India Lightning strikes can cause structural damage to an aircraft.there is a need to upgrade the existing lightning strike protection technology. Graphene, a carbon derivative, is a possible solution to enhance lightning protection, owing to its superior electrical, heat conductivities and mechanical strength. | ||||
| 11:50 | 12:15 | 9.1.3 |
EFFECT OF LASER PRINTING MODE ON SURFACE TOPOGRAPHY, MICROSTRUCTURE AND CORROSION PROPERTY OF ADDITIVE-MANUFACTURED NITI Xin Liu¹, Dngdong Gu¹; ¹Nanjing University of Aeronautics and Astronautics, China Considering the unique characterizations of LPBF process, the position and sequence of laser irradiation are different under different laser scanning modes, which will affect the properties of as-built samples, especially for heat-sensitive intelligent NiTi SMAs with high Ni content. Hence, based on the designed chessboard partitions, NiTi SMAs with high performance were successfully fabricated. | ||||
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| 11:00 | 11:25 | 10.1.1 |
TOWARDS EFFICIENT ANALYSIS OF POSTBUCKLING IN AIRCRAFT STIFFENED STRUCTURES M.H. Elalfy¹, R. de Breuker¹, S.G.P. Castro¹; ¹TU Delft, Netherlands This paper introduces a new computationally efficient tool to predict postbuckling behavior in thin-walled aircraft structures, particularly stiffened plates. Focusing on the critical transition where local buckling alters load distribution but retains the structure’s load-carrying capacity. The proposed postbuckling analysis tool employs a semi-analytical approach based on the Rayleigh-Ritz method and the perturbation approach. By assuming a displacement field through Ritz Method and utilizing hierarchical polynomials, this tool seeks to overcome limitations in existing methodologies. The integration of hierarchical polynomials aims to enhance versatility and computational efficiency, enabling its application across a wide range of structural configurations and boundary conditions. The enhancement in computational efficiency, additionally, provides substantial benefits to the design and optimization processes. | ||||
| 11:25 | 11:50 | 10.1.2 |
CONCEPTUAL DESIGN AND TOPOLOGY OPTIMIZATION OF A COMPLIANT MORPHING FLAP FOR NEXT GENERATION HYBRID-ELECTRIC REGIONAL AIRCRAFT M.C. Noviello¹, I. Dimino¹, S. Ameduri¹, A. Concilio¹; ¹The Italian Aerospace Research Centre (CIRA), Italy Presenter: Maria Chiara Noviello, The Italian Aerospace Research Centre (CIRA) CONCEPTUAL DESIGN AND TOPOLOGY OPTIMIZATION OF A COMPLIANT MORPHING FLAP FOR NEXT GENERATION HYBRID-ELECTRIC REGIONAL AIRCRAFT | ||||
| 11:50 | 12:15 | 10.1.3 |
HIGH-VELOCITY DROPLET IMPACT STUDIES ON C/SIC AND C/C COMPOSITES Yifan YUE¹, Renxi ZHAO¹, Bo WANG¹, Yulong LI, Shaanxi Key Laboratory of Impact Dynamics and Engineering Applic, China; ¹School of Aeronautics, Northwestern Polytechnical University, China Rain erosion is a potential hazard for supersonic vehicles, with severe damage to materials that may be impacted by raindrops. C/SiC composite materials and C/C composite materials are widely employed in high-speed aircraft due to their excellent high-temperature and mechanical performance. The rain erosion issues associated with these two materials hold significant research significance. In this paper, a series of impact tests of 260–572 m/s are carried out on a 3 mm-thick 2D C/SiC composite specimen and 3 mm-thick 3D C/C composite specimen using a single impact waterjet apparatus. The typical morphology of C/SiC specimen and C/C specimen are obtained by single jet impact test. Observations using optical microscopy, SEM, and X-CT revealed that damage to both materials included matrix cracking and loss, delamination, and fiber fracture. The study found that with an increase in droplet impact velocity and diameter, the extent of damage significantly increased. When the droplet impact velocity reached 570 m/s, a change in the damage pattern occurred. Stress waves generated reflected tensile waves on the specimen's backside, resulting in noticeable fiber fracture and matrix loss in both materials. Three-point bending tests on the post-impact C/C composite materials showed a significant drop in bending resistance after impact at 570 m/s, indicating that backside damage affected the material's mechanical performance. Under the multi-droplet impact, the stress wave interaction is enhanced, and the internal damage of the specimen is severe, showing a funnel-shaped damage. The study found that the multi-drop impact process for both materials is a process of cumulative damage expansion. Moreover, the C/SiC specimen is penetrated after 5 drops of impact. Quasi-static tensile tests were employed to quantify the post-impact strength of the specimen, during which the digital image correlation (DIC) method was used t | ||||
| 12:15 | 12:40 | 10.1.4 |
WEIGHT OPTIMIZATION AND STRENGTH ANALYSIS OF AIRBORNE POD BASED ON T300/QY9611 CARBON FIBER COMPOSITE Z.-C. Dong¹, X.-M. Li, AVIC·Leihua Electronic Technology Research Institute, China; H.-Y. Huang¹; ¹Northwestern Polytechnical University, China This study investigates the use of T300/QY9611 carbon fiber composite for airborne pod weight reduction. Replacing traditional aluminum alloys, the composite material is analyzed through structural design and finite element software. Results indicate a significant 45.89% weight reduction while maintaining required strength, showcasing potential in lightweight aircraft design. | ||||
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| 11:00 | 11:25 | 11.1.1 |
POTENTIAL LIMITS OF LOAD ALLEVIATION IN REDUCING THE STRUCTURAL MASS OF A LONG-RANGE TRANSPORT CONFIGURATION V. Handojo¹, S. Puelm¹; ¹DLR German Aerospace Center, Germany In recent years, numerous publications have dealt with load alleviation to reduce the structural mass of transport aircraft. With more and more aggressive load alleviation functions however, aspects such as fatigue, loads during failure cases as well as high-lift loads might become sizing relevant. This work addresses to what extent the mentioned points pose potential limits of load alleviation. | ||||
| 11:25 | 11:50 | 11.1.2 |
CLOSED-LOOP GUST LOADS ANALYSIS OF A SUPERSONIC FIGHTER AIRCRAFT A. Voß¹, J. Baier¹; ¹DLR Institute of Aeroelasticity, Germany Military supersonic fighter configurations, due to their high maneuverability requirements, are usually sized by maneuver loads. This work investigates if gusts can exert higher loads on the primary structure in terms of section loads and structural dynamic accelerations. | ||||
| 11:50 | 12:15 | 11.1.3 |
DYNAMIC DROP SIMULATION OF THE MAIN LANDING GEAR OF A GENERAL AVIATION AIRCRAFT N. Li¹, H. Wang¹, Z.Q. Li¹, Z.H. Wang¹; ¹Taiyuan University of Technology, China The kinematic model of the rigid-flexible coupling for the main landing gear was established, the dynamic simulations under extreme working conditions were conducted, and the strength& stiffness models were obtained, so that the performance was reflected more accurately, and the optimization strategies and structural design suggestions were put forward. | ||||
| 12:15 | 12:40 | 11.1.4 |
TRADE OFF STUDIES ON WING MANEUVER LOAD ALLEVIATION STRATEGIES BASED ON AILERONS AND WINGLETS MOVABLE SURFACES R. Pecora, University of Naples Federico II, Italy Wing load alleviation is a crucial aspect in aircraft design for improved structural efficiency. Typically, movable surfaces are employed to lessen aerodynamic stresses during maneuvers, thereby reducing structural weight. This study evaluates aileron- and winglet-based strategies on a civil transportation aircraft, focusing on allowable reductions in wing bending moment/shear while adhering to structural stiffness constraints to prevent aeroelastic instability within the certification flight envelope. Analyzing different geometrical settings for the involved alleviators, trends in elastic aircraft behavior have been identified, offering insights into the benefits and drawbacks of each investigated alleviation strategy. | ||||
| additional information (interactive) | 11.1.R |
FLIGHT LOADS RESEARCH OF TWIN VERTICAL TAIL FOR BLENDED WING-BODY AIRCRAFT BASED ON STRAIN GAUGE CAILBRATION Z. Guo¹, A. Tang¹, Q. Jing¹; ¹Chinese Flight Test Estsblishment, China | |||||
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| 11:00 | 11:25 | 12.1.1 |
EFFECTS OF SHOCK IMPINGEMENT LOCATION ON PANEL AEROELASTIC STABILITY IN MACH REFLECTION Y. He¹, A. Shi¹; ¹Northwestern Polytechnical University, China The aeroelastic stability and chaotic motions of a two-dimensional heated panel in Mach reflection are investigated through theoretical analysis, which reveals the impact of shock impingement location on the stability boundary and discloses the stability region of post-divergence flutter, providing insight into the aeroelastic behavior of heated panels in Mach reflection. | ||||
| 11:25 | 11:50 | 12.1.2 |
PARAMETERISATION OF NONLINEAR AEROELASTIC REDUCED ORDER MODELS WITH AERODYNAMIC AND STRUCTURAL NONLINEARITY M. Candon¹, E. Hale¹, M. Balajewicz, Independent Researcher, United States; A. Delgado-Gutierrez¹, V. Muscarello¹, P. Marzocca¹; ¹RMIT University, Australia Presenter: Pier Marzocca, RMIT University It is shown that, through Orthogonal Matching Pursuit, sparse higher-order functional series based ROMs can now be efficiently applied to complex 3D aeroelastic systems. Furthermore, an interpolation scheme for a nonlinear ROM library demonstrates excellent precision and robustness in modelling high amplitude limit cycles for a stabilator with freeplay and transonic aerodynamic nonlinearity. | ||||
| 11:50 | 12:15 | 12.1.3 |
EFFICIENT MULTI-FIDELITY REDUCED-ORDER MODELING FOR FLUTTER PREDICTIONS ACROSS MULTIPLE MACH NUMBERS X. Wang¹, X. Peng¹, H. Liu¹, J. Kou¹, W. Zhang¹; ¹Northwestern Polytechnical University, China A method for constructing a multi-fidelity reduced order model has been proposed, which can effectively improve modeling efficiency and reduce the cost of flutter analysis. The generalization of Mach number and angle of attack shows that this model has good generalization capability and can be applied to flutter simulation of aircraft. | ||||
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| 11:00 | 11:25 | 13.1.1 |
FAST PREDICTION METHOD FOR RADIAL GROWTH OF LABYRINTH SEAL CLEARANCE BASED ON TRANSIENT THERMAL-FLUID COUPLING NETWORK Z. Li¹, C. Liu¹, P. Liu¹, Y. Wang¹, X. Jin¹, S. Ding¹; ¹Research Institute of Aero-Engine, Beihang University, China NA | ||||
| 11:25 | 11:50 | 13.1.2 |
BASE FLOW CHARACTERISTICS FOR A SUB-SCALE HIGH-SPEED EXHAUST AT OVER-EXPANDED MODE S. Tsentis¹, I. Goulos¹, S. Prince¹, V. Pachidis¹, V. Zmijanovic, Reaction Engines Ltd, United Kingdom; ¹Cranfield University, United Kingdom The flow of a high-speed exhaust at overexpansion mounted on the tunnel wall through a wing is presented. DDES computations are performed to analyse the flow. Results show that the mean and fluctuating pressure is significantly reduced behind the pylon. This is also confirmed through the application of POD. This flow asymmetry can increase base drag and cause side loads on wingtip-mounted engines | ||||
| 11:50 | 12:15 | 13.1.3 |
EXPERIMENTAL AND NUMERICAL INVESTIGATIONS OF A SWIRL-STABILIZED JET ENGINE COMBUSTOR B.O. Cakir¹, D. Sanned¹, P. Vauquelin¹, M. Prakash¹, J.-P. Hannappel¹, A. Subash¹, M. Richter¹, X.-S. Bai¹, C. Fureby¹; ¹Lund University, Sweden Achieving lower global emission levels in aviation demands alternative fuels to be developed. This necessitates the characterization of thermochemical properties and combustion characteristics. Accordingly, The Triple Annular Research Swirler burner, which simulates aeroengines combustors, is employed for experimental and numerical investigations of non-reactive and reactive flows dynamics. | ||||
| 12:15 | 12:40 | 13.1.4 |
PERFORMANCE ASSESSMENT OF AN ENGINE-INTEGRATED CLOSED-AIR COOLING THERMAL MANAGEMENT SYSTEM IN A NEXT GENERATION FIGHTER CONFIGURATION T. Matuschek¹, J. Häßy¹, M. Schmelcher¹, A. Görtz¹; ¹German Aerospace Center (DLR), Germany The potential of an engine-integrated TMS in a next-generation fighter configuration is analyzed. The cooling cycle is a closed-air reverse Brayton cycle, in which heat is transfered from the internal cooling system to the engine bypass stream. The aim is to quantify and evaluate the dependencies between cooling capacity and engine performance as well as installation space and required TMS mass. | ||||
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| 11:00 | 11:25 | 14.1.1 |
RESEARCH RESULTS AND PERSPECTIVES ON NON-COOPERATIVE SENSING FOR SAFE UAM OPERATIONS F. Vitiello¹, F. Causa¹, R. Opromolla¹, G. Fasano¹; ¹University of Naples Federico II, Italy The paper describes recent results and research paths followed at the University of Naples “Federico II” regarding non cooperative sensing for low altitude airspace surveillance. In particular, the focus is set on architecture and algorithms for detection and tracking based on radars, optical sensors, and data fusion. Near term research perspectives are also discussed. | ||||
| 11:25 | 11:50 | 14.1.2 |
SENSOR UNCERTAINTY MITIGATION FOR DETECT AND AVOID SYSTEMS E. Theunissen, Netherlands Defence Academy, Netherlands The impact of position- and velocity uncertainty is illustrated in the TCPA-DCPA domain. Following this, Sensor Uncertainty Management (SUM) strategies are presented. To illustrate the performance of a prototype SUM function, baseline alerting performance statistics are provided for two alerting algorithms without SUM that use the bounds of the available trade-space of a DO-365B DAA function | ||||
| 11:50 | 12:15 | 14.1.3 |
PRELIMINARY APPLICATION OF FORMAL VERIFICATION TO AN AUTONOMY ARCHITECTURE FOR UNMANNED AIRCRAFT L.R. Humphrey¹, C.A. Muñoz¹; ¹NASA, United States In this paper, formal methods are used to verify that modules in ICAROUS, an architecture for building safety-centric autonomous unmanned aircraft applications, interact correctly. Specifically, this paper shows how to use the Spin model checker to specify requirements and model parts of the system, then verify whether the model satisfies the requirements and find and fix errors when it does not. | ||||
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| 11:00 | 11:25 | 15.1.1 |
A TIERED CONTINUOUS CULTIVATING SYSTEM FOR AVIATION TECHNOLOGY TALENTS THAT INTEGRATES STEM AND POPULAR SCIENCE EDUCATION J. Li¹, Y. He, Sichuan Technical Exchange Center, China; X.H. Tang, School of Public Administration, Sichuan University, China; Y.M. Zhou¹, W.F. Huo², J. Zhang², K. Lin², Y. Luo, Mao County Innovation Institute of Intelligent Aircraft Engineer, China; M. Ling, Chenghang Innovation Institute of Intelligent Aerocraft, Chengdu, China; ¹School of Aeronautic Science and Engineering, Beihang University, China ;²Chengdu Xueshang Technology Co., Ltd, China Presenter: Ji Li, Beihang University/School of Aeronautic Science and Engineering This article analyzes the student growth patterns and curriculum in the basic education stage, designs a continuous advanced aviation science and technology innovation curriculum system that matches student abilities, systematically develops teaching aids, textbooks, resources, and forms a complete aviation characteristic STEM course. | ||||
| 11:25 | 11:50 | 15.1.2 |
DESIGN BUILD AND FLY: A STUDENT APPROACH TO THE CREATION OF AN RC DRONE FOR UNIVERSITY COMPETITION E. Gaspari¹, E. Bianchini¹, L. Pezzullo¹, A. Giorgi¹, M. Giannetti¹, D.M. Macchini¹, L. Ferrarini¹, F. Bondanese¹, S. Celli¹, T. Strafforello¹, U. Mignemi¹, A. Arnaldi¹, M. Ferrazzani¹, M. Sanna¹, D. Geraci¹, M.R. Chiarelli¹, A.A. Quarta¹, G. Palaia¹, L. Boni¹; ¹University of Pisa, Department of Civil and Industrial Engineeri, Italy This document summarizes the activities of a group of students from the University of Pisa, preparing for the 2024 Air Cargo Challenge. Their goal is to design and build a RC model aircraft compliant with the competition regulations. In this first phase the team has determined all the main features of the aircraft, aiming to finish the construction within May 2024 to compete in the ACC in July. | ||||
| 11:50 | 12:15 | 15.1.3 |
MICKEY MOUSE AND A GIANT: COMPARISON OF AERONAUTICS EDUCATION IN FINLAND AND CHINA M. Kanerva¹, Y. Zhang, Tsinghua University, China; R. Yondo Mine¹, L. Qiu, Beihang University, China; M. Wang, BIT, China; ¹Tampere University, Finland Presenter: Raoul Yondo Mine, Tampere University This study focuses on comparing the size and structure of aeronautics education in two different universities and nations: Tampere University in Finland and Tsinghua University in China. Parametric data is collected and analysed. | ||||
| 12:15 | 12:40 | 15.1.4 |
DESIGN AND VISUALIZATION OF A KNOWLEDGE-BASED AIRCRAFT CABIN IN VIRTUAL REALITY F. Prokic¹, C. Eriksson¹, R.C. Munjuluru¹; ¹Linköping University, Sweden Presenter: Fredrik Prokic By constructing and using a knowledge-based aircraft cabin and a VR game engine, the designed cabin can be visually inspected in the VR environment to help further the design and better understand building processes or the user experience. This paper will explain the process of creating geometrical models and how to transfer the model into the VR environment and Airport Terminal operations. | ||||
| additional information (interactive) | 15.1.R |
DESIGNING A FRAMEWORK FOR FLIGHT SIMULATOR TRAINING SCENARIOS. AN EVIDENCE BASED TRAINING APPROACH. G. Kontos¹, O. Lehmann¹; ¹Abu Dhabi University, United Arab Emirates | |||||
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| 11:00 | 11:25 | 16.1.1 |
COMPARATIVE ANALYSIS OF MACHINE LEARNING ALGORITHMS FOR HEAT EXCHANGERS DIAGNOSIS IN ELECTRIFIED AIRCRAFT D. F. Migliore¹, G. D'Alessio², S. Caggese², A. De Martin², F. Acerra¹, M. Sorli², M. Fioriti²; ¹Leonardo S.p.A., Italy ;²Politecnico di Torino, Italy This paper presents a comparative analysis of ML algorithms to assess the severity of fouling in heat exchangers as an enabler for Condition-Based Maintenance. A high-fidelity model of the Thermal Management System is employed to generate the required data for data-driven algorithms, simulating both healthy and degraded conditions. | ||||
| 11:25 | 11:50 | 16.1.2 |
APPLICATION OF NATURAL LANGUAGE PROCESSING FOR AIRCRAFT DEFECT TRACKING IN MAINTENANCE OPERATIONS M.J. Scott¹, O. Kirkpatrick¹, W. Verhagen¹, V. Kekoc, Defence Science and Technology Group, Australia; B. Teunisse, Capability Acquisition and Sustainment Group, Australia; J. Zhang¹, H. Fayek¹, P. Marzocca¹; ¹RMIT University, Australia Current maintenance reports necessitate manual scrutiny to identify recurring defects across an aircraft fleet. Natural Language Processing (NLP) methods present an automated means to harness the potential of under-utilised maintenance reports. This paper applies NLP to two-year's worth of maintenance reports, and through in-depth analysis, unveils lead indicators for defects. | ||||
| 11:50 | 12:15 | 16.1.3 |
TOWARDS TRUSTWORTHY DATA-DRIVEN GAS TURBINE PROGNOSTICS A. Apostolidis¹, S. Le Dantec, SIGMA Clermont, France; K.P. Stamoulis¹; ¹Amsterdam University of Applied Sciences, Netherlands This paper discusses the evolution of aircraft data recording, focusing on Aircraft Operational Data for prognostics. The importance of trustworthiness for data-driven prognostics is pivotal. This work uses real-world engine data for Exhaust Gas Temperature prediction, addressing challenges like missing data points, and explores solutions like KNN-imputation and Generalized Additive Model. | ||||
| 12:15 | 12:40 | 16.1.4 |
FASTVIBE SW TOOL FOR RIDE-ALONG VIBRATION SURVEY ANALYSIS S. Bianchi¹, F. Negroni¹, M. Riganti¹; ¹Leonardo Aircraft Division, Italy With the aim of simplifying the aircraft vibration survey analysis, an automated tool is created with the use of Machine Learning technique. Starting from experimental flight data it allows for much faster times in aircraft experimental vibration analysis by making the process self-learning in identifying the origin of vibration environment, helping the interpretation of occurred exceedances. | ||||
| additional information (interactive) | 16.1.R |
LIFE CYCLE ASSESSMENT OF ALTERNATIVE LAUNCH METHODS S. Wildermuth¹, W. Veraburenon¹, T. Bellier¹, C. Bil¹; ¹RMIT University, Australia | |||||
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| 11:00 | 11:25 | 17.1.1 |
MODEL-BASED DESIGN OF ACTIVE/ACTIVE ELECTRO-HYDROSTATIC ACTUATION FOR HELICOPTER FLIGHT CONTROLS M.-W. Sun¹, J. Fu¹, D.-C. Lyu¹, J.-C. Mare, ICA, INSA-Toulouse, France; ¹Beihang University, China The EHA design involves 2 channels arranged in a tandem force-summing configuration, which needs a detailed study of the redundant EHA in the active/active mode, as well as in the passive mode. Thus, the research addresses the characteristics difference between the dissimilar power modules. A cooperative control method is proposed to manage the force equalization and the pressure transients. | ||||
| 11:25 | 11:50 | 17.1.2 |
DEVELOPMENT OF AN ELECTRO-HYDROSTATIC NOSE LANDING GEAR ACTUATION AND STEERING SYSTEM M.N. Duval¹, T. Lammering¹; ¹Liebherr-Aerospace Lindenberg GmbH, Germany A self-sufficient, electro-hydrostatic based solution is proposed for to perform all functions of the nose landing gear of an aircraft. The system works solely on electric power, and thus is an important brick towards the electrification of future aircraft. The development process from concept selection to functional demonstrator in a representative environment is described. | ||||
| additional information (interactive) | 17.1.R |
RESEARCH ON MODELING THE TEMPERATURE FIELD OF A NEW AEROSPACE SERVO ELECTRO-HYDROSTATIC MODULE BASED ON THERMO-MAGNETIC BIDIRECTIONAL COUPLING ANALYSIS X. Hu¹, Y. Fu¹, Dingchong Lyu¹, M. Sun¹, S. Zhao, Beijing Institute of Precision Mechatronics and Controls, Labora, China; J. Fu¹, J. Zhao¹; ¹School of Mechanical Engineering and Automation, Beihang Univers, China Presenter: Mingwei SUN, Beihang University | |||||
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| 14:30 | 14:55 | 1.2.1 |
JETZERO: RESHAPING AVIATION WITH THE BLENDED WING SS Savian, JetZero, United States invited speaker for the Global Sustainable Aviation track | ||||
| 14:55 | 15:20 | 1.2.2 |
X-66: ACCELERATED LEARNING THROUGH FULL SCALE PROTOTYPING B. Cobleigh, NASA (AFRC), United States; E. Kaduce, Boeing, United States invited speaker for the Global Sustainable Aviation track | ||||
| 15:20 | 15:45 | 1.2.3 |
BOMBARDIER ECOJET RESEARCH PROJECT; THE QUEST FOR SUSTAINABLE AVIATION S. McCullough, Bombardier, Canada Invited Speaker for the Global Sustainable Aviation track | ||||
| 15:45 | 16:10 | 1.2.4 |
Q&A - MINI PANEL Q&A A, Q&A - MINI PANEL | ||||
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| 14:30 | 14:55 | 2.2.1 |
IMPACT OF HYDROGEN FUEL ON OVERALL DESIGN OF TRANSPORT AIRCRAFT E. Nguyen Van¹, J. Gauvrit-Ledogar¹, C. Julien², B. Paluch², J.L. Ruan, ONERA/DMPE, France; F. Moens, ONERA/DAAA, France; ¹ONERA/DTIS, France ;²ONERA/DMAS, France This paper presents the ONERA research effort made to enable hydrogen aircraft, understand the impact of hydrogen on the overall design of aircraft and characterise the performance of a hydrogen fuelled transport aircraft. The study focuses on Small to Medium Range Aircraft and on two aircraft configurations; a traditional Tube and Wing aircraft and a more advanced Blended Wing body concept. | ||||
| 14:55 | 15:20 | 2.2.2 |
A PERFORMANCE COMPARISON OF HYDROGEN AIRCRAFT CONCEPTS N. Wood¹, S. Taylor¹, M. Hales¹, M. Joynt¹, S. Chandran¹, D. Sanjeevekumar¹; ¹GKN AEROSPACE, United Kingdom GKN Aerospace is committed to sustainable aviation. This paper will present data showing the benefits of a cryogenic fuel cell powertrain for regional aircraft when compared to non-cryogenic and combustion platforms. It will also present a future view on the scale potential for hydrogen fuelled aircraft. | ||||
| 15:20 | 15:45 | 2.2.3 |
PRELIMINARY SIZING OF HYDROGEN-BURNING JETLINER FOR DIRECT OPERATING COST OPTIMIZATION H. Mohammadi¹, G. Sirtori¹, L. Trainelli¹; ¹DAER, Politecnico di Milano, Italy Presenter: Gabriele Sirtori, DAER, Politecnico di Milano This study aims to conduct a design study on the use of liquid hydrogen (LH2) as a direct burning fuel in passenger aircraft. The goal is to minimize direct operating costs associated with LH2 fuel usage and adapt the current tube and wing configuration to accommodate LH2. Additionally, the objective is to find optimal solutions for narrowbody and widebody aircraft that meet market demands. | ||||
| 15:45 | 16:10 | 2.2.4 |
INVESTIGATING THE FLEXIBLE HYDROGEN AIRCRAFT SYSTEM INTERFACE DESIGN USING THE XR CO-DESIGN APPROACH F. Reimer¹, M. Fuchs¹, J. Herzig¹, S. Cornelje¹, J. Biedermann¹, B. Nagel¹; ¹DLR, Germany In an era of ongoing global climate change, there is a trend towards a more sustainable and climate-neutral aviation, which necessitates a multitude of new key technologies. Particularly, the exploration of alternative propulsion systems such as hydrogen propulsion exhibits significant potential to substantially reduce the emissions of future aircraft. However, the integration of novel propulsion systems notably impacts the aircraft cabin and its system architecture. As a safety-critical subsystem of the overall aircraft, critical system interfaces and the complex interactions of individual subsystems must be understood and considered during integration into retrofit and novel aircraft architectures. Utilizing digital methods, it is possible to integrate these complex and innovative system components including the relevant system and subsystem interfaces based on rules, 3D models and digital twins of conventional aircraft architectures, vividly depicting them in virtual reality. | ||||
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| 14:30 | 14:55 | 3.2.1 |
A MORPHOLOGICAL ANALYSIS OF METHODS FOR CONCEPTUAL AIRCRAFT DESIGN UNDER UNCERTAINTIES V.T. Todorov¹, D. Rakov, Blagonravov Institute of Engineering Science, Russia; A. Bardenhagen¹; ¹Technical University of Berlin, Germany Disruptive technologies should be achieved by assuring their reliable operation while accelerating their entry into service. Hence, the need for novel methods for conceptual aircraft design under uncertainties is additionally stressed. These are outlined and analyzed by using the Advanced Morphological Approach. The work serves as an aid for future aircraft designers for the selection or development of conceptual design methods. | ||||
| 14:55 | 15:20 | 3.2.2 |
NUMERICAL AND THEORETICAL INVESTIGATION OF HELICOPTER DITCHING WITH VARIOUS INITIAL VELOCITY AND PITCHING ANGLE L. Zheng¹, M. Wang², Y. Lu², H. Qiao¹, T. Xiao¹, S. Deng¹; ¹Nanjing University of Aeronautics and Astronautics, China ;²Chinese Aeronautical Establishment, China Results demonstrate the effects of initial downward velocity and pitching angle on the helicopter ditching process in detail. A shape factor and an average deadrise angle are introduced to extend the theoretical model for predicting the kinematic parameters during ditching. | ||||
| 15:20 | 15:45 | 3.2.3 |
MAXIMUM SPEED OF BATTERY-POWERED TILT-ROTOR AIRCRAFT N. Roh¹, M. Park¹; ¹Hanwha systems, South Korea This key aim of the current paper is to derive exact analytical expression for the maximum speed of an electric powered tilt-rotor aircraft. To achieve it, properly sized aircraft with determined maximum power and torque is considered. Two operational methods are proposed, and the feasibility of applying simplified formulas is evaluated. Subsequently, a formula is derived to calculate the maximum flight speed while adhering to constraints on both maximum power and maximum torque. | ||||
| 15:45 | 16:10 | 3.2.4 |
EFFICIENT MULTI-OBJECTIVE DESIGN OPTIMIZATION OF ROTOR AIRFOILS FOR IMPROVING DYNAMIC STALL CHARACTERISTICS Z. Lu¹, Z.-H. Han¹, W.-P. Song¹, K.-S. Zhang¹, K.-Y. Zhou¹; ¹School of Aeronautics, Northwestern Polytechnical University, China This paper conducted a multi-objective design optimization of rotor airfoils for improving dynamic stall characteristics, through employing an efficient surrogate-based algorithm. Furthermore, a multi-objective design optimization considering both dynamic stall and static aerodynamic characteristics have been made, since they are equally important. | ||||
| Reserve Paper | 3.2.R |
AN UNCERTAINTY MULTIDISCIPLINARY PROPAGATION ANALYSIS METHOD FOR CORRELATED HIGH-DIMENSIONAL DATA IN AIRCRAFT DESIGN S. Du, China; C. Li, China; Y. Liu, China Presenter: Siyi Du | |||||
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| 14:30 | 14:55 | 4.2.1 |
COLOSSUS EU PROJECT – COLLABORATIVE SOS EXPLORATION OF AVIATION PRODUCTS, SERVICES AND BUSINESS MODELS: OVERVIEW AND APPROACH P. Shiva Prakasha¹, N. Naeem¹, K. Amadori, SAAB Aeronautics, Sweden; G. Donelli¹, J. Akbari¹, F. Nicolosi, UNINA, Italy; L. Knöös Franzen, Linkoping University, Sweden; M. Ruocco, Smartup Engineering, Italy; T. Lefebvre, The French Aerospace Lab, France; B. Nagel¹; ¹German Aerospace Center - DLR, Germany COLOSSUS EU Project will develop a system-of-systems design framework and methodology which for the first time will enable the combined optimization of aircraft, fleet, operations and business models. To develop a robust framework two contrasting use cases are considered 1) Sustainable Intermodal Mobility (ADAM) and 2) Aerial Wildfire-Fighting (EVE) In addition, developed methods and tools will be openly published in order to foster exploitation for SOS research and industry. This collaborative research paper by several Research Organizations, Industry Partners, SMEs and Universities in Europe will highlight the Framework development, Initial results and the insights of such coupled framework for bringing together Aviation Products – Operations – Digitalization and Business Models. The two-use cases pose diverse and unique requirements on the framework and thereby aim to rekindle the research approach. The paper will show the first coupling results and sensitivity between Subsytems (Technology tradeoff) , Constituent Systems (Aircraft), System of Systems (Fleet and ConOps), and Business Models. The Agent-Based Simulation of System of Systems developed for both Use Cases will also be delivered in future along with paper for community use. | ||||
| 14:55 | 15:20 | 4.2.2 |
A SYSTEM OF SYSTEMS AIRCRAFT DESIGN FRAMEWORK: DEMONSTRATION USING A SEAPLANE TRANSPORT NETWORK IN THE GREEK ISLANDS V. Nugnes¹, C. Varriale, TU Delft, Italy; P. Ratei¹, P. Shiva Prakasha¹, B. Nagel¹; ¹DLR, Italy This paper aims to contribute to the field of aircraft design with a novel approach, adopting a System of Systems Engineering (SoSE) perspective. For this purpose, conventional design disciplines are coupled with Agent-Based Modeling and Simulation (ABMS) defining a unique optimization problem. We want to show the impact of including ABMS in the design workflow on aircraft design parameters. | ||||
| 15:20 | 15:45 | 4.2.3 |
CONCEPT OF OPERATIONS IN AN AGENT-BASED SIMULATION: A SYSTEM-OF-SYSTEMS APPROACH F. Villas¹, L. Knöös Franzén¹, C. Jouannet², K. Amadori², I. Staack, TU Braunschweig, Germany; ¹Linköping University, Sweden ;²Saab Aeronautics, Sweden Presenter: Ludvig Knöös Franzén, Linköping University The paper presents an approach for analyzing and generating Concepts of Operations using the Unified Architecture Framework to prioritize operational aspects of aircraft agents, aligning with stakeholders' needs while maintaining cooperative behavior within the System of Systems. An example of the approach is applied for forest firefighting scenario. | ||||
| 15:45 | 16:10 | 4.2.4 |
SYSTEM OF SYSTEMS ANALYSIS OF AUTONOMOUS AIRCRAFT OPERATIONS IN AIR CARGO FEEDER NETWORKS P.W. Jansen¹, R.E. Perez¹, J.C.-H. Wang, Ribbit Inc, Canada; ¹Royal Military College of Canada, Canada Air cargo networks provide an important logistical support to large cities and remote communities alike. This research presents a Systems-of-Systems analysis of the operational changes that autonomous vehicles can bring within existing regional air cargo feeder networks. The analysis shows the potential of autonomy to reduce operating costs, enhance and expand cargo feeder networks operations. | ||||
| Reserve Paper | 4.2.R |
TECHNICAL RISK MANAGEMENT OF SYSTEM OF SYSTEMS BASED ON TECHNOLOGY READINESS ASSESSMENT H. Cao¹, W. Cheng¹, C. Xing, Chinese Aeronautics Establishment (CAE), China; G. Song¹; ¹ Aviation Industry Development Research Center of China (ADR) , China | |||||
| additional information (interactive) | 4.2.R |
RESEARCH ON ROUTE PLANNING METHOD FOR UAV SWARM AREA COVERAGE MISSIONS BASED ON COMPLEX NETWORKS X. Li¹, L. Deng¹, Y. Ge¹, Y. Pei¹, Y. Gu², L. Cao², A. Shi¹; ¹NORTHWESTERN POLYTECHNICAL UNIVERSITY, China ;²Shanghai Electro-Mechanical Engineering Institute, China | |||||
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| 14:30 | 14:55 | 5.2.1 |
GRID EFFECT ON M823 BOMB AT TRANSONIC REGIME J. Jiménez-Varona¹, G. Liaño¹; ¹INTA, Spain The flow field past an axisymmetric body configuration at high angles of attack is asymmetric, and unsteady. Projectiles, missiles and bombs are composed of an axisymmetric body with a fins set and/or strakes. At subsonic and transonic regimes, the flow may be asymmetric at certain angles of attack, due to instabilities at the tip nose region, amplified by the leeside vortex interaction with the rear fins. The role of grids in such cases is very decisive when numerical calculations are performed. Excessive irregularities in the tip nose region, due to a coarse and/or inaccurate definition of the tip, may lead to important differences of the calculated forces and moments when compared to experimental data. The grid role in terms of resultant forces and moments may be large at high angles of attack, where there are nonlinear effects, some of them due to spurious numerical effects. This effect may also be significant in rolling motion and on the derived Magnus forces and moments at high angles of attack. In this paper, the grid role is studied by using different grids resembling the configuration M823 Bomb at transonic regime and moderate angles of attack. These grids differ on the amount of numerical roughness, which is a way of measurement of the geometrical irregularities regarding the ideal configuration. At the larger values of angle of attack, important differences of the calculated side and normal force and pitching moments are present, due to large irregularities of one of the grids. There are smooth and rough configurations in terms of numerical calculations. The numerical effect in terms of an increment of the side force at larger angles of attack has also been verified in wind tunnel testing with either smooth or rough models. Therefore, for subsonic and transonic regime and at high angles of attack conditions, care must be taken in the numerical calculations, due to the grid is absolutely determinant on the accuracy of the solutions. Exper | ||||
| 14:55 | 15:20 | 5.2.2 |
LOW SPEED AERODYNAMICS OF SIX OPTIMISED UNCONVENTIONAL RE-ENTRY VEHICLE AEROSHAPES S.M. Giannino¹, G. Pezzella¹, A. Viviani¹; ¹Università della Campania Luigi Vanvitelli, Italy Presenter: Spartaco Giannino, Università della Campania "Luigi Vanvitelli" This paper deals with the CFD analysis of six different lifting body aeroshapes developed for the optimal design of a Return Vehicle for Low Earth orbit. The flowfield past those aeroshapes at subsonic flow conditions, close to landing conditions, is investigated for different angles of attack and sideslip. Aeroshapes longitudinal and lateral-directional stabilities are discussed in detail | ||||
| 15:20 | 15:45 | 5.2.3 |
SCALE EFFECT ON WATER LANDING PERFORMANCE OF AMPHIBIOUS AIRCRAFT H. Zhang¹, J. Chen², F. Wang¹, G. Zhang¹, Z. Shen, Aircraft Strength Research Institute of China, China; Q. Zhu, China Special Vehicle Research Institute, China; G. Wu, Commercial Aircraft Corporation of China Ltd, China; M. Tong²; ¹Jinling Institute of Technology, China ;²Nanjing University of Aeronautics and Astronautics, China NA | ||||
| 15:45 | 16:10 | 5.2.4 |
ANALYSIS OF SUCTION FORCE EFFECT ON DIFFERENT FUSELAGE SHAPE DURING THE WATER DITCHING J.-Y. Li¹, X.-Y. Wang, Shanghai Electro-Mechanical Engineering Institute, China; J.-C. Chen¹, J. Jiao, China Special Vehicle Research Institute, China; M.-B. Tong¹, C.-L. Yan, Beijing University Of Aeronautics And Astronautics, China; ¹Nanjing University Of Aeronautics And Astronautics, China Based on computational fluid dynamics methods and LES turbulence model, simulations were conducted on aircraft calm water ditching at different pitch angles and different flight speeds. The tail suction effect and splashing situation were analyzed. | ||||
| additional information (interactive) | 5.2.R |
APPLICATION OF ARTIFICIAL NEURAL NETWORK (ANN) FOR PREDICTION OF DRAG COEFFICIENT OF AXISYMMETRIC BOATTAIL MODELS Q. Nguyen Dinh¹, H. Tran The¹, G. Sharma², J. Tanimoto²; ¹Le Quy Don Technical University, Vietnam ;²Kyushu University, Japan Presenter: Gopal Sharma | |||||
| additional information (interactive) | 5.2.R |
SEPARATION SAFETY ANALYSIS IN VARIABLE LAUNCH CONDITION OF SMALL AIR-LAUNCHED UAVS BASED ON NUMERICAL SIMULATION AND FLIGHT TEST B. Guo¹, Y.F. Lu¹, B. Wang, Chinese Academy of Military Science, China; Z. Guo¹, G.W. Jia¹, D.N. Liu¹; ¹National University of Defense Technology, China | |||||
| additional information (interactive) | 5.2.R |
RESEARCH ON AERODYNAMIC PERFORMANCE OF OVERSIZE MODULAR PARAFOIL IN RANDOM WIND FIELD F. Duan¹, J.-Y. Li¹, Z.-D. Li, Aerospace Life-support Industries Ltd, China; M.-B. Tong¹; ¹Nanjing University of Aeronautics and Astronautics, China | |||||
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| 14:30 | 14:55 | 6.2.1 |
PASSIVE FLOW CONTROL DEVICES ON LOW-REYNOLDS DU89-134 AIRFOIL C. Brunelli¹, M. Avirovic¹, B. Janssens¹, B.G. Marinus¹, M. Runacres, Vrije Universiteit Brussel, Belgium; G. May, Von Karman Institute for Fluid Dynamics, Belgium; A. Ecorce², A. Dalbera²; ¹Royal Military Academy, Belgium ;²National Polytechnic Institute of Toulouse , France The usage of standard passive flow control on Low-Reynolds airfoil – for High-Altitude Pseudo-Satellites (HAPS) vehicles - to increase lift-to-drag ratio using a numeric and experimental approach shows that geometry and position of the device are crucial for increasing efficiency. | ||||
| 14:55 | 15:20 | 6.2.2 |
RESEARCH ON UNSTEADY AERODYNAMIC MODELING METHOD OF PREPOSITIVE WING - MAIN WING COMPOSITE SYSTEM AT HIGH ATTACK ANGLE X. Bai, China; B. Mi, China; J. Zhang, China Based on the prepositive elliptic wing - main wing composite flow control configuration, the state space modeling method for unsteady aerodynamics of a multi-body composite system in high angle of attack maneuvers is studied, which overcomes the limitations of existing high angle of attack aerodynamic modeling techniques in terms of applicability to complex systems. | ||||
| 15:20 | 15:45 | 6.2.3 |
MITIGATING DYNAMIC STALL WITH A MOVABLE LEADING-EDGE: THE NACA0012-IK30 WING E.A.R. Camacho¹, A.R.R. Silva¹, F.D. Marques, Universidade de São Paulo, Brazil; ¹Universidade da Beira Interior, Portugal Presenter: Emanuel Camacho, Universidade da Beira Interior One major problem that affects rotor blade aerodynamics is dynamic stall, characterized by a series of events where transient vortex shedding negatively affects drag and lift, leading to abrupt changes in the wing’s pitching moment. The present work focuses on the mitigation of such effects by using a modified NACA0012 airfoil: the NACA0012-IK30 airfoil, used previously for thrust enhancement in flapping propulsion. Hence, an experimental rig is designed and built to study the advantages of a time-varying pitching leading edge on a plunging wing, more specifically its influence on the aerodynamic coefficients over time. Results indicate that when the wing is not experiencing significant stall, the movable leading edge does not hold considerable influence on drag or lift. However, it can reduce the pitching moment intensity by indirectly shifting the pressure center. Contrarily, when the wing is under proper dynamic stall, the movable leading edge truly improves the aerodynamic characteristics while operating at smaller effective angles of attack. This study contributes to the long-standing discussion on how to mitigate the adverse effects of dynamic stall by providing an innovative yet simple solution. | ||||
| 15:45 | 16:10 | 6.2.4 |
NUMERICAL STUDY ON ACTIVE FLOW CONTROL SOLUTIONS FOR HIGH LIFT P. Scavella¹, G. Paolillo¹, T. Astarita¹, G. Cardone¹, C.S. Greco¹; ¹University of Study of Naples Federico II, Italy Exploring Active Flow Control (AFC) with a focus on the CoFlow Jet (CFJ) airfoil shows potential lift improvement, drag reduction, and increased stall margin through strategic slot placement. This study examines combining AFC solutions like CFJ with circulation control devices like the Coanda jet for enhanced efficiency. LES and RANS simulations quantify various AFC solutions, suggesting integrated configurations for potential application in finite wing designs. | ||||
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| 14:30 | 14:55 | 7.2.1 |
AERODYNAMIC NUMERICAL/EXPERIMENTAL COMPARISON OF A HYPERSONIC TEST VEHICLE IN MORE&LESS PROGRAM P. Roncioni¹, Marco Marini¹, R. Fusaro², N. Viola², D. Pepelea, INCAS, Romania; B. Cakir, VKI, Belgium; M. Clay, REL, United Kingdom; ¹CIRA, Italy ;²POLITO, Italy This paper deals with a numerical and experimental activity for the development and integration of the aerodynamic database of hypersonic test vehicle in the framework of the H2020 More&Less project. At this purpose, a dedicated methodology has been developed and applied to several supersonic/hypersonic vehicles. This methodology foresees the development of aerodynamic aerodatabases by means of incremental steps starting from simplified methods up to very reliable data based on high fidelity CFD simulations and experimental measurements with associated confidence levels. In particular in this paper a direct comparison between CFD results and experimental measurements is reported being this a fundamental step for the building of the final aerodynamic database of the Mach 5 flying experimental vehicle (flying test bed). | ||||
| 14:55 | 15:20 | 7.2.2 |
ANALYSIS ON COMPLEX HYPERSONIC FLOW DURING THE REENTRY OF EXPIRED SPACECRAFT Z. Han¹, Z.-H. Li, National Laboratory for Computational Fluid Dynamics, China; S.-Y. Chu¹, W.-Y. Cheng¹, C.-S. Wang¹; ¹Aviation Industry Development Research Center of China, China This study aims at the accurate numerical simulation of hypersonic flow created by multiple disintegration of expired spacecraft re-entering into near space. Taking the Tiangong-1 spacecraft as an example, we conducted flow simulation calculations for the compartment. We also conducted numerical simulations for the multi-body flow around the debris of the Tiangong-1. | ||||
| 15:20 | 15:45 | 7.2.3 |
ASSESSMENT OF A MACROSCOPIC MODEL FOR THE AEROTHERMODYNAMICS CHARACTERIZATION OF ICE GIANTS ATMOSPHERIC ENTRY D. Ninni¹, F. Bonelli¹, A. Laricchiuta², G. Colonna², G. Pascazio¹; ¹Politecnico di Bari, Italy ;²CNR ISTP Bari, Italy This work provides the assessment of an hybrid macroscopic/state-to-state approach for the numerical simulation of Ice Giants atmospheric entry flows. A GPU-equipped solver is presented with the goal of simulating hypersonic flows past bluff bodies. A comparison between macroscopic and state-to-state results is provided. | ||||
| 15:45 | 16:10 | 7.2.4 |
KINETIC MONTE CARLO BASED CATALYTIC VISCOUS WALL BOUNDARY MODELING IN CFD SIMULATION OF HIGH-ENTHALPY NON-EQUILIBRIUM FLOW Q. Li¹, X. Yang², W. Dong¹, Y. Du²; ¹Shanghai Jiao Tong University, China ;²China Aerodynamics Research and Development Center, China A KMC based catalytic model simulating heterogeneous catalysis was constructed and coupled into CFD method as viscous wall boundary by interpolation. The results showed that simulation of high-enthalpy flow with current method could drive a deterministic heat transfer rate on surface of high-speed aircrafts, thus improve reliability of aerodynamic heating prediction on thermal protection material. | ||||
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| 14:30 | 14:55 | 8.2.1 |
EVALUATING INSTALLATION EFFECTS IN SEMI-SPAN WIND TUNNEL EXPERIMENTS USING CARTESIAN-GRID-BASED FLOW SOLVER UTCART Y. Tamaki¹, Y. Yokoyama¹, T. Imamura¹; ¹The University of Tokyo, Japan The model installation effects in the semi-span wind tunnel experiment stall characteristic of the CRM-HL configuration are investigated based on RANS-based CFD analyses using the Cartesian-grid-based flow solver UTCart. The results show that both the floor boundary layer and peniche (standoff) affect the flow separation at the inboard sections. | ||||
| 14:55 | 15:20 | 8.2.2 |
CHARACTERIZATION OF EXTERNAL LIQUID HYDROGEN TANK INTERFERENCE DRAG C. Graham¹, R.E. Perez¹; ¹Royal Military College of Canada, Canada As the aviation industry moves to reduce greenhouse gas emissions liquid hydrogen fuel has been suggested as a solution. One major hurdle to the adoption of hydrogen aircraft is storing adequate fuel for long flights. This paper investigates the size and positional effects of wing-mounted external hydrogen fuel tanks. | ||||
| 15:20 | 15:45 | 8.2.3 |
WIND TUNNEL ANALYSIS OF A SPACE RE-ENTRY VEHICLE AT LOW-SPEED CONDITIONS N. Montella, University of Campania/ CIRA, Italy; G.A. Vio, The University of Sydney, Australia; L. Iuspa¹, A. Aprovitola¹, G. Pezzella, University of Campania , Italy; A. Viviani¹; ¹University of Campania, Italy Presenter: Nicolina Montella, Università degli Studi della Campania "L. Vanvitelli" / CIRA This paper deals with the low-speed wind tunnel analysis of six Crew Return Vehicle aeroshapes for Low Earth Orbit support services, compatible to landing conditions. Multi-disciplinary Optimization methodologies are used to design the optimal architecture. In particular, the proprietary Skeleton-based Integral Soft Object methodology is exploited to built the different vehicle aeroshapes. | ||||
| 15:45 | 16:10 | 8.2.4 |
DESIGN OF A HIGHLY EFFICIENT TRANSPORT NLF AIRCRAFT WITH A BACKWARD SWEPT WING AND A LONG SINGLE-AISLE FUSELAGE T. Streit¹, J. Ruberte Bailo¹, A. Büscher, Airbus Operations GmbH, Germany; A. Seitz¹; ¹DLR (GERMAN AEROSPACE CENTER), Germany Results obtained in the German LuFo project ULTIMATE for the numerical aerodynamic design and analysis of a highly efficient transport aircraft with a backward swept wing and a long single-aisle fuselage are presented. Large efficiency due to large aspect ratio wings and using natural laminar flow. The final designed geometry defines the shape for a windtunnel model for a ETW windtunnel test | ||||
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| 14:30 | 14:55 | 9.2.1 |
WHAT-IF SCENARIO ANALYSIS OF REGIONAL AIR MOBILITY OPERATIONS IN SOUTH KOREA J.C. Lee¹, S.K. Kim, Georgia Institute of Technology, South Korea; S.M. Ahn¹, J.H. Kim, Sejong University, South Korea; ¹Handong Global University, South Korea This research starts by formulating a research question "What are market dynamics associated with the adoption of RAM services in South Korea?" To answer the question, this research proposes a methodology that leverages a data-driven approach incorporating four modules. Utilizing the modules, this research conducts what-if analysis on five transportation scenarios across potential O-D pairs. | ||||
| 14:55 | 15:20 | 9.2.2 |
DEVELOPMENT OF LOW ALTITUDE 4-DIMENSIONAL OPERATIONS MANAGEMENT SYSTEM FOR ADVANCED AIR-MOBILITY T. Iijima¹, N. Matayoshi¹, N. Yokoyama¹, H. Yoshida¹, A. Oosedo¹, S. Kikkawa¹, M. Yawata², S. Nakada², T. Yahata²; ¹JAXA, Japan ;²NEC, Japan There is a growing momentum towards realizing Advanced Air Mobility (AAM) operations, including unmanned aircraft systems. We propose four-dimensional (4D) operations, in which flight plans are defined in both space and time, to avoid conflicts in the air and at vertiports at the flight planning stage. This paper describes the development of the low altitude 4D operations management system for AAM. | ||||
| 15:20 | 15:45 | 9.2.3 |
EXPLORING RIDESHARING IN PASSENGER URBAN AIR MOBILITY: A COMPARATIVE ANALYSIS A. Edsel¹, S.D. Biswas¹, M. Kilbourne¹, R. Gadre¹, S. Vashi¹, K. Mall¹, W.A. Crossley¹, D.A. DeLaurentis¹, M.D. Patterson², B.E. Sells²; ¹Purdue University, United States ;²NASA Langley Research Center, United States Presenter: Daniel DeLaurentis, Purdue University The concept of air-based ridesharing, although not subject to extensive study as of yet, shows promise for future passenger-carrying UAM operations. Our study demonstrates the potential for UAM-based ridesharing in expanding accessibility and increasing UAM affordability for the general public, as opposed to an alternative scenario of purely single-passenger UAM trips. | ||||
| 15:45 | 16:10 | 9.2.4 |
CLASSIFICATION OF EXTENDED REALITY BASED HUMAN MACHINE INTERFACES SCENARIOS FOR URBAN AIR MOBILITY M. Gomes Araujo¹, C. Conte², F. De Crescenzio¹, D. Accardo²; ¹University of Bologna, Italy ;²University of Naples Federico II, Italy Presenter: Millene Gomes Araujo, University of Bologna Urban Air Mobility uses vertical take-off and landing vehicles for efficient urban transportation. Addressing challenges like public acceptance and operational visualization is crucial. Extended Reality (XR) technologies offer immersive interfaces aiding in early stages. This paper outlines collaborative research in PNRR and MOST projects, exploring XR-based scenarios for UAM integration and traffic management. | ||||
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| 14:30 | 14:55 | 10.2.1 |
DEMOCRATIZATION OF FATIGUE EVALUATION FOR REALISTIC RIVETING CONFIGURATIONS USING STATE-OF-THE-ART SIMULATIONS I. Rivero¹, A. Palomar¹, M. Rebollo¹, J. Domingo¹, M. Lozano¹, Z. Mujika¹, D. Garijo¹, G. Lara¹, A. Capitan¹, J. Gomez-Escalonilla¹; ¹Airbus, Spain Presenter: Alejandro Palomar, Airbus Defence and Space To democratize the deployment of advanced simulation technologies for the development of the new generation of Military Aircraft Programs in Airbus, new integrated software tools are developed at Airbus. One of these tools, called INFERNAL, is able to generate high-fidelity simulations for aircraft riveted joints to predict fatigue cracking for realistic complex scenarios . | ||||
| 14:55 | 15:20 | 10.2.2 |
THE FATIGUE LIFE PREDICTION OF THIN-WALLED WELDED JOINTS M. Sladky¹, M. Machac², J. Papuga², I. Jebacek¹; ¹Faculty of Mechanical Engineering, Brno University of Technology, Czech Republic ;²Faculty of Mechanical Engineering, Czech Technical University, Czech Republic This contribution addresses the fatigue life prediction of thin-walled welded joints in aerospace applications. It evaluates three approaches: nominal, structural, and notch stress based predictions. A comparative study is conducted on a several types of specimens representing critical aircraft structural locations, offering insights for enhanced reliability in these predictions. | ||||
| 15:20 | 15:45 | 10.2.3 |
SURFACE QUALITY CHALLENGE FOR TI-6AL-4V ADDITIVE MANUFACTURED TOPOLOGIC OPTIMIZED LIGHTWEIGHT STRUCTURE C. Matias¹, A. Diskin¹, O. Golan, Afeka- Tel-Aviv Academic College of Engineering, Israel; A. Garkun², E. Strokin²; ¹Israel Aerospace Industries, Israel ;²Technion Research & Development Foundation, Israel AM technology topologic optimization, create hidden surfaces that cannot be adequately treated for produced rough and defective surfaces. This study presents an experimental evaluation procedure to examine state-of-the-art surface treatments, showing that they do not yet meet that challenge. Additional treatments are being suggested to be further evaluated by the procedure presented in this study. | ||||
| 15:45 | 16:10 | 10.2.4 |
INTEGRATIVE ANALYSIS OF LOW-CYCLE FATIGUE AND CRACK PROPAGATION IN TURBINE BLADES N.M. Hoang¹, M.D. Ha¹, T.Q. Nguyen¹, P.M. Nguyen¹; ¹Viettel Aerospace Institute, Vietnam Advancing turbine reliability: Our study integrates low-cycle fatigue and crack propagation analyses, aligning numerical simulations with practical insights. This work aims to enhance turbine durability, offering valuable contributions to design and maintenance strategies. | ||||
| additional information (interactive) | 10.2.R |
STUDY ON FATIGUE PROPERTIES OF TITANIUM ALLOY BASE MATERIAL AND WELDED STRUCTURE IN THERMAL COMBINED ENVIRONMENT H. Peng¹, B. Wang¹, Y. Zhang¹, L. Ji¹, S. Li¹; ¹AVIC the First Aircraft Institute, China | |||||
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| 14:30 | 14:55 | 11.2.1 |
NUMERICAL METHOD TO DETERMINE STRUCTURAL ELEMENT REDUCED STIFFNESS FOR DESIRED COMPOSITE WING STRUCTURES CONFIGURATIONS S. Stammel¹, C. Bisagni¹; ¹Politecnico di Milano, Italy This study aims to introduce a novel and simplified design method for morphing composites wing structures. Morphing composite structures will lead to an increase in efficiency and a decrease of structural weight and therefore in a reduction of the environmental impact of future aeronautical and space vehicles. | ||||
| 14:55 | 15:20 | 11.2.2 |
SEMI-ANALYTICAL SENSITIVITY METHODS FOR AEROELASTIC SHAPE OPTIMIZATION G.M. Gagliardi¹, M.D. Kulkarni, Embry-Riddle Aeronautical University, United States; F. Marulo¹; ¹University of Naples Federico II, Italy Novel semi-analytical methods for flutter eigenvalues sensitivity analysis with respect to the shape has been developed. The derivative of all the structural matrices has been calculated analytically with an element-agnostic approach, while aerodynamic matrices have been differentiated using finite differences. The methods allow for a more accurate and efficient aeroelastic shape sensitivity analysis. | ||||
| 15:20 | 15:45 | 11.2.3 |
ABSOLUTE NODAL COORDINATE FORMULATION FOR NONLINEAR MULTIBODY MODELING OF FLARED HINGED WINGS K. Otsuka, Tohoku University, Japan; C.W. Cheng¹, R. Palacios¹; ¹Imperial College London, United Kingdom The wings of transport jets are becoming high aspect ratio to reduce induced drag. To alleviate excessive large deformation under gust conditions, flared hinged wings have been developed. In this study, multibody simulation considering geometrical nonlinearity based on absolute nodal coordinate formulation is developed for designing the flared hinged wings. | ||||
| 15:45 | 16:10 | 11.2.4 |
OPTIMIZATION DESIGN OF MULTI-SCALE ACTIVE COOLING STRUCTURE FOR AIRCRAFT P. Xu¹, Q.-X. Mu¹, W.-N. Zhang¹; ¹AVIC Shenyang Aircraft Design and Research Institute, China To improve the resistance to extreme environments of ultra-high temperature and pressure loads for the aircraft leading edge structure, this work proposes a novel structural form combining microlattice and flow channels, and a corresponding design method for such structures is developed. Results show that the optimized leading edge structure exhibits excellent mechanical and thermal performances. | ||||
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| 14:30 | 14:55 | 12.2.1 |
COMPUTATIONAL/EXPERIMENTAL AEROELASTIC STUDY FOR AN ALL-MOVABLE HORIZONTAL TAIL WITH TORSION FREE-PLAY X.-Y. Ai, China; X.-Y. Chen, China; W.-J. Wang, China; J. Liu, China; X.-J. Ran, China; W. Qian, China Segmented optimization describing function method is proposed to study the dynamic response induce by free-play. By the method, piecewise expressions for the time history and phase portrait of limit cycle are derived, and the high-order harmonic is predicted. A 3D all-movable horizontal tail with free-play was produced, and the effectiveness of the method was verified by wind tunnel test. | ||||
| 14:55 | 15:20 | 12.2.2 |
NUMERICAL AND EXPERIMENTAL RESEARCH ON AEROELASTICITY OF HIGH-ASPECT-RATIO WINGS J. Liu¹, W. Qian¹, X. Hu¹, X. Ai¹, X. Ran¹; ¹Dalian University of Technology, China An unusual aeroelastic phenomenon was discovered in early wind tunnel test, where deformation of the high-aspect-ratio wing model used in the test suddenly decreases before flutter. In order to figure out the reason of the phenomenon, a new simulation frame is established and a series of high-aspect-ratio wings are designed. The wind tunnel tests are planned to be conducted. | ||||
| 15:20 | 15:45 | 12.2.3 |
W-WING AEROELASTIC DEMONSTRATOR DESIGN MODIFICATION AND UPGRADE J. Cecrdle¹, O. Vich¹, J. Starek¹, J. Vlach¹, M. Kolar¹, M. Smid¹; ¹Czech Aerospace Research Centre (VZLU), Czech Republic W-WING is whirl flutter aeroelastic demonstrator representing a half-wing with the nacelle, engine, and propeller. Two experimental campaigns were accomplished in past. Currently, it is intended for further experiments. For this purpose, the modification and upgrades were proposed. The paper describes the activities including the design, instrumentation, and aerodynamic and structural analyses. | ||||
| 15:45 | 16:10 | 12.2.4 |
MEASUREMENT OF WING BENDING IN-FLIGHT FROM A T67 SLINGSBY FIREFLY LIGHT AIRCRAFT N.J. Lawson, The University of Sydney, Australia; G. Zhao¹, S.C. Place¹, R.A. Harrison¹; ¹Cranfield University, United Kingdom This paper presents in-flight wing bending data, taken using the image pattern correlation technique (IPCT) from a Slingsby T67 Firefly aircraft, during wind-up turns. Data were recorded up to a normal g-load of 3.5g and the wing bending displacement data was compared to a simple cantilever model and inertial data. | ||||
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| 14:30 | 14:55 | 13.2.1 |
SUSTAINABLE FUELS SAFETY BOUNDARIES DEMARCATION METHOD T. Qiu¹, S. Bao¹, S. Ding, Civil Aviation University of China, China; Q. Ma¹, X. Wang¹, C. Gan¹; ¹Beihang University, China Presenter: Shengyu Bao, Beihang University As global warming continues to increase, countries around the world are developing new energy sources to reduce carbon dioxide emissions. However, most new energy sources are less compatible with existing industrial systems. Especially in the field of aviation, it is difficult to rapidly apply emerging new energy technologies due to the lack of validation. The new aviation fuel is a new energy source similar to the traditional aviation fuel. On the one hand, it can reduce carbon dioxide emissions, and on the other hand, it has good compatibility with existing aviation equipment. Therefore, it has a greater potential for rapid popularization. The existing validation method of new aviation fuels is mainly based on the standard system of the American Society for Testing and Materials (ASTM), and the core is based on the operational experience of traditional aviation fuels to constrain the physicochemical properties of new aviation fuels, which can give a clear range of physicochemical properties before validation. Recently, some scholars believe that it is possible to improve the adequacy of the safety assessment of new aviation fuels from the perspective of safety analysis of aviation engines, but it is difficult to give a clear range of physicochemical properties before the assessment in this way, which is not conducive to the reference of research and development organizations. In this paper, we propose a method to obtain the safety boundaries of new aviation fuels by inverse mapping through Monte Carlo method using a standard engine model with fuel resolution. It not only provides support for the range of physicochemical properties of the ASTM standard, but also improves the reference of the new safety assessment method. | ||||
| 14:55 | 15:20 | 13.2.2 |
EFFECTS OF SHAPE AND STREAMWISE SPACING OF PIN-FINS ARRAYS ON FLOW AND HEAT TRANSFER L.W. Li¹, T.L. Dong¹, W.T. Ji¹, J.M. Wu¹; ¹Xi'an Jiaotong University, China Results show that pin-fin shapes and the spacing between rows greatly affect the flow and heat transfer characteristics with pin-fin arrays. Results also show higher heat transfer than the short pin-fins in previous studies. With the increase of heat load, the heat transfer capacity of the channel decreases and the friction factor increases with the same Reynolds number. | ||||
| 15:20 | 15:45 | 13.2.3 |
MULTI-DIMENTIONAL DESIGN AND THERMAL PROTECTION CAPABILITY OF A REGENERATIVE COOLED RBCC VARIABLE-GEOMETRY COMBUSTOR L. Zhang, China; T.-T. Jing, China; X. Sun, China; T. Gao, China; Z. Xu, China; F. Qin, China The study conducted a multidimensional approach to design the regenerative cooling structure of the RBCC variable-geometry combustor. The investigation aimed to determine the effect of different cooling equivalent ratios on the cooling effect. | ||||
| 15:45 | 16:10 | 13.2.4 |
NUMERICAL SIMULATION OF HEAT TRANSFER IN MINIATURE RADIALLY ROTATING SODIUM/POTASSIUM HEAT PIPES G. Li, Tianmushan Laboratory, China; Y. Zhang¹, G. Zhang, Beihang University Research Institute of Aero-Engine, China; S. Huang¹, S. Ding, Civil Aviation University of China, China; ¹Beihang UniversitySchool of Energy and Power Engineering, China To study a new thermal management technology that combines radially rotating heat pipes (RRHP) with turbine disks or compressor disks in aero-engines. the numerical simulations of miniature sodium/potassium RRHP were conducted to predict the heat transfer performance. The equivalent thermal conductivity of the sodium and potassium heat pipe can reach 9176 W/m·K and 8966 W/m·K, respectively. | ||||
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| 14:30 | 14:55 | 14.2.1 |
VALIDATING ASSUMPTIONS ABOUT PILOT RECOGNITION: A PCM-BASED APPROACH FOR AIRCRAFT CERTIFICATION SAFETY ASSESSMENT PROCESS D.M.C. de Lima¹, D.C. Fernandes¹, M.M. Cardoso Junior¹; ¹Aeronautical Institute of Technology, Brazil Aircraft accident investigations have indicated the necessity of a deeper evaluation of the role of the pilot during failure conditions. The current guidance for safety assessment does not provide a structured methodology to perform such evaluation. This paper proposes to use the PCM structure to establish a framework for the evaluation of pilot recognition and response to failure conditions. | ||||
| 14:55 | 15:20 | 14.2.2 |
THE IMPACT OF PIEZOELECTRIC STACK HEATING ON AIRCRAFT DEICING L. Yuan¹, B. Miao¹, K. Yan¹, C.L. Zhu¹; ¹Nanjing University of Aeronautics and Astronautics, China The phenomenon of aircraft icing poses a significant threat to flight safety. There is considerable potential for piezoelectric actuators based on deicing techniques. The focus of this paper is to examine the correlation between vibrational frequency and heating properties of piezoelectric stack, as well as the effect of the piezoelectric stack heating on deicing. The findings indicate that the heating rate of the piezoelectric stack is significantly affected by its vibrational frequency. Short-term and low frequency (below 1000Hz) vibration of the piezoelectric stack at -16°C of environment have slight impact on deicing. | ||||
| 15:20 | 15:45 | 14.2.3 |
HANDLING QUALITIES RATING SCALE: THE IMPACT OF THE PILOT SUBJECTIVITY IN WORKLOAD EVALUATION M.D. Turazza¹, J.P.C.A Macedo ¹, J.H. Bidinotto¹; ¹EESC/USP, Brazil This work evaluates the impact of the pilot subjectivity in the workload. Emergency maneuvers were performed by test pilots, the tasks were classified using the Cooper-Harper Scale. Results showed a strong variation in ratings for different pilots performing the same tasks, highlighting the importance of the development of a tool to become this evaluation without the subjectivity caused by the pilots’ opinion. | ||||
| 15:45 | 16:10 | 14.2.4 |
CLASSIFICATION OF COGNITIVE LOAD BASED ON THE PILOT’ VISUAL SCAN PATTERNS J. Yao, China; Y. Lu, China; Z. Zhong, China; S. Fu, China This study focuses on the differences between the pilots’ visual scan patterns. Three eye movement features were examined and a variety of classification algorithms were used to test the classification ability of different features. The results showed that the eye movement features can distinguish scan patterns of different pilot tasks, especially with the combination of multiple features. | ||||
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| 14:30 | 14:55 | 15.2.1 |
LINEAR QUADRATIC PURSUIT AND EVASION DIFFERENTIAL GAME GUIDANCE STRATEGY WITH OBSTACLE AVOIDANCE X. Wang¹, M. Yang¹, P. Ma¹, T. Chao¹; ¹Harbin Institute of Technology, China In this paper, a class of linear quadratic differential game guidance scheme is presented to study the pursuit and evasion conflict scenario that an evader establishes a static obstacle and performs the evasion maneuver to avoid a pursuer. First of all, the engagement kinematic model among the obstacle, the pursuer, and the evader is linearized according to the assumption. The issue of the pursuit and evasion game is transformed into a linear quadratic differential game through the dead zone and the cost functions. Furthermore, the linear quadratic differential game approach is utilized to obtain the guidance strategy with obstacle avoidance. Numerical simulation results are employed to validate the performance of the guidance policy. | ||||
| 14:55 | 15:20 | 15.2.2 |
LEARNING-BASED FULL-ENVELOPE AUTOPILOT DESIGN BASED ON THE KOOPMAN OPERATOR THEORY Y. Lee¹, J. Kim¹, Y. Kim¹; ¹Seoul National University, South Korea A data-driven approach to designing an autopilot for missile is proposed based on the Koopman operator theory. The proposed approach employs neural networks to approximate the Koopman embedding function. A linear quadratic integral controller is designed for the embedded system, yielding an optimal controller capable of addressing a broad operational spectrum with only a few gain tunings. | ||||
| 15:20 | 15:45 | 15.2.3 |
INTEGRATING POST-OPTIMAL SENSITIVITIES INTO SUPERVISED TRAINING OF NEURAL NETWORKS J. Diepolder¹, J.Z. Ben-Asher¹; ¹Technion, Israel In this paper, we present an advancement for learning quantities derived from solutions to optimal control problems. The proposed approach leverages sensitivity information obtained at optimal solutions to enhance the supervised training of neural networks. | ||||
| 15:45 | 16:10 | 15.2.4 |
PREDICTIVE CONTROL DRIVEN TACTICAL MANEUVERING J. Novák ¹, J. Hanák¹, P. Chudý¹; ¹BUT, Czech Republic Presenter: Jiří Novák, Brno University of Technology This paper presents a Adaptive Flight Control System (AFCS) capable of controlling a jet fighter aircraft during high speed, agile, i.e. tactical, maneuvering. The aircraft model is part of a large simulation framework, developed at the Faculty of Information technology, Brno University of Technology, which serves as a research platform for tactical pilot training. The simulation framework enables an option to practice tactical aerial maneuvers against multiple agent-controlled opponents. | ||||
| additional information (interactive) | 15.2.R |
PURSUIT-BASED LONG-RANGE AIR-TO-AIR MISSILE MIDCOURSE GUIDANCE ROBUST TO CHANGES IN THE PREDICTED IMPACT POINT M. Shin¹, M.-J. Tahk¹, B. Kim¹, C.-H. Lee¹; ¹Korea Advanced Institute of Science and Technology, South Korea | |||||
| additional information (interactive) | 15.2.R |
CONTROL ALLOCATION FOR A DISTRIBUTED ELECTRIC PROPULSION AIRCRAFT USING DIFFERENTIAL THRUST C. Döll¹, S. Waitman¹; ¹ONERA, France | |||||
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| 14:30 | 14:55 | 16.2.1 |
HYBRID MODELING APPROACH FOR OPTIMIZATION BASED CONTROL OF MULTIROTOR UNMANNED AERIAL VEHICLES J. Novák ¹, J. Hanák¹, P. Chudý¹; ¹BUT, Czech Republic Optimization based techniques such as Model Predictive Control (MPC) often rely on simplified governing equations of the system omitting complex interactions which are difficult to accurately model. This paper investigates a hybrid modeling approach based on Sparse Identification of Nonlinear Dynamics (SINDy) for local model improvement within the MPC framework. | ||||
| 14:55 | 15:20 | 16.2.2 |
MEDIAL AXIS TRANSFORMATION-BASED CONVEX MODEL PREDICTIVE CONTROL FOR MULTIROTOR INDOOR AUTONOMOUS FLIGHT WITH FIXED ALTITUDE H.J. Ahn¹, H.C. Bang¹; ¹KAIST, South Korea This paper introduces an advanced strategy for Medial Axis Transformation(MAT)-based Convex MPC(CMPC) for multirotor indoor autonomous flight. The main idea of this suggested framework is the collaboration of MAT-based collision free graph(CFG) generation with the set of circles, piecewisely defined safe flight corridor(SFC), and CMPC including SFC, multirotor dynamics, and other constraints. | ||||
| 15:20 | 15:45 | 16.2.3 |
AERODYNAMIC MODEL IDENTIFICATION OF A VTOL TAILSITTER UAV USING SPARSE IDENTIFICATION OF NONLINEAR DYNAMICS H.-S. Lee¹, D.-W. Lee¹, H.-C. Bang¹; ¹KAIST, South Korea As a data-driven approach, a sparse identification of nonlinear dynamics (SINDy) is implemented for an aerodynamic model identification of the tailsitter UAV. The candidate functions are chosen to reveal the nonlinear relations between aerodynamic terms and system states. The tailsitter dynamics are fully derived and it is verified through simulation and flight tests. | ||||
| 15:45 | 16:10 | 16.2.4 |
ROBUST SLIDING MODE CONTROL FOR UAV FORMATION WITH EXTERNAL DISTURBANCES UNDER EVENT-TRIGGERED STRATEGY L.H. Wang¹, A.J. Li¹, Ch.Q. Wang¹, Z. Yury, Samara National Research University, Russia; ¹Northwestern Polytechnical University, China A robust sliding mode formation control method based on event-triggered strategy is investigated for UAV formation flight trajectory tracking affected by external interference and limited communication. Under this scheme, the discontinuous communication is realized in the discrete update state of the sliding mode surface. Stability proofs and simulations are completed. | ||||
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| 14:30 | 14:55 | 17.2.1 |
SMART ELECTRIC POWER MANAGEMENT ONBOARD FUTURE AIRCRAFT F. Cuomo¹, C. Musto¹, S. Bozhko, University of Nottingham, United Kingdom; B. Guida, Aeromechs srl, Italy; ¹Leonardo Aircraft, Italy Presenter: Beniamino Guida, Aeromechs srl Smart Electric Power Management (SEPM) refers to the sophisticated innovative control of aircraft electrical generation, distribution, and utilization, facilitating the efficient operation of onboard electrical systems, aiming for enhanced safety, reliability, and the overall performance of aircraft operations. SEPM goes beyond the limitations of legacy EPM by making onboard Electrical Power Systems (EPS) flexible and adaptable, adding new functions through real-time power management, as discussed further in this document. The expected benefits of the SEPM approach are: - Increased availability: by using SEPM, the overall aircraft electrical network becomes dynamic and reconfigurable, with benefits in terms of availability when failures occur; - Improved efficiency: focusing on a/c electric power train, SEPM steers the operations of converters, generators and motors towards their towards optimal operation points, having efficiency maximization for whole power train as target - Efficient hybridization: SEPM enables the usage of secondary hi-power energy sources (e.g. batteries, fuel cells) to achieve hybridization by realizing power paths from sources to electrical propellers | ||||
| 14:55 | 15:20 | 17.2.2 |
DESIGNING A HARDWARE-IN-THE-LOOP SIMULATION TEST BED FOR AIRCRAFT ENERGY MANAGEMENT APPLICATIONS A. Dell’Amico, Linköping University, Sweden This paper presents the design of a Hardware-in-the-loop simulation test bed for aircraft energy management applications. It requires interaction of several hardware and software systems and is able to simulate a complete flight mission of a fighter aircraft with flight controls, electric and hydraulic power and distribution. This allows different energy management strategies to be evaluated. | ||||
| 15:20 | 15:45 | 17.2.3 |
DUAL STAGE BATTERY SIZING AND PERFORMANCE ASSESSMENT ON-BOARD HYBRID ELECTRIC AIRCRAFT A. Wise¹, S. Bozhko¹, S. Yeoh¹, S. Sumsurooah¹, C. Manrique, Leonardo S.p.A, Italy; ¹University of Nottingham, United Kingdom This paper presents analytical modelling to produce a battery, split between sizing and performance. This allows for the battery to be sized for maximum conditions while the performance aspect can have multiple mission profiles applied for one size. The design follows industrial modelling requirements, sized for power and energy, to allow the model to be implemented within an aircraft design. | ||||
| 15:45 | 16:10 | 17.2.4 |
PRELIMINARY ASSESSMENT FOR STRUCTURAL BATTERY COMPONENTS G. di Mauro¹, M. Guida¹, G. Olivares², L.M. Gomez², R. Turco¹, R. Tesser¹, S. Mallardo¹, G. Santagata¹, P. Russo¹; ¹Università degli Studi di Napoli Federico II, Italy ;²Jerry Moran Center for Advanced Virtual Engineering & Testing (A, United States Presenter: Michele Guida, Università degli Studi di Napoli Federico II In the context of a project promoted by the Leonardo company and in light of information gathered from the literature State of the Art, a model of Structural Battery was produced by hot compaction and preliminarily tested from a mechanical point of view. | ||||
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| 16:30 | 17:00 | 1.3.1 |
CLEAN AVIATION SHORT MEDIUM RANGE AIRCRAFT CONCEPT K. Mokaddem, AIRBUS, France Invited speaker for the Global Sustainable Aviation Track | ||||
| 17:00 | 17:30 | 1.3.2 |
TOWARDS ZERO CLIMATE IMPACT AVIATION G. Llewellyn, Airbus, United Kingdom An inside view on how Airbus is preparing the path towards zero climate impact flight. | ||||
| 17:30 | 18:00 | 1.3.3 |
ACCELERATING THE CLEAN FUTURE OF FLIGHT G Teofili, ZeroAvia, United Kingdom invited speaker for the Global Sustainable Aviation track | ||||
| 18:00 | 18:30 | 1.3.4 |
PANEL DISCUSSION PD D, PANEL DISCUSSION | ||||
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| 16:30 | 17:00 | 2.3.1 |
CONCEPTUAL AIRCRAFT DESIGN OF A RESEARCH BASELINE WITH DIRECT LIQUID HYDROGEN COMBUSTION M. Kotzem¹, S. Wöhler¹, T. Burschyk¹, C. Hesse¹, S. Hellbrück¹, T. Zill¹; ¹German Aerospace Center (DLR), Germany This study addresses the conceptual aircraft design of a short-medium range research baseline with direct liquid hydrogen combustion and an assumed technology in 2035. The final aircraft design is based on the results of aircraft design and sensitivity studies focusing on the integration of the LH2 tanks and systems, and can be used as a reference point for future research efforts. | ||||
| 17:00 | 17:30 | 2.3.2 |
DESIGN OPTIMISATION OF A BOUNDARY LAYER INGESTION PROPULSOR FOR A MULTI-FUEL HYDROGEN AIRCRAFT A. Battiston¹, A. Magrini¹, R. Ponza¹, E. Benini¹, B. Türkyilmaz², A. Seitz², A. Heidebrecht, TU Delft, Netherlands; ¹hit09, Italy ;²Bauhaus Luftfahrt, Germany Presenter: Andrea Battiston, hit09 The paper presents a design optimization framework for a multi-fuel singel-aisle passenger aircraft with boundary layer ingestion propulsion, combining highly efficient ultra-high bypass ratio turbofan burning sustainable aviation fuels or H2, with a hydrogen fuel cell auxiliary propulsion and power unit driving a tail BLI fan, in order to minimize the pollutant emissions over the entire mission. | ||||
| 17:30 | 18:00 | 2.3.3 |
MODELLING HYDROGEN FUEL CELL AIRCRAFT IN SUAVE C. Svensson¹, P. Miltén¹, T. Grönstedt¹; ¹Chalmers University of Technology, Sweden The open-source conceptual aircraft design tool SUAVE has been extended with methods for designing and simulating regional hydrogen fuel cell aircraft. This includes sizing methods for the airframe, LH2 storage and fuel cell stacks. Dynamic models for H2 boil-off and fuel cell power draw are integrated in the mission solver. This tool enables operators to understand future hydrogen flight. | ||||
| 18:00 | 18:30 | 2.3.4 |
PRELIMINARY DESIGN OF A FULL ELECTRIC GENERAL AVIATION AIRCRAFT POWERED WITH FUEL CELL: A CASE STUDY. G. Cafiero¹, P.J. Comunian¹, A. Lerro¹, F. Ponti², A.N. Damiani Ferretti²; ¹Politecnico di Torino, Italy ;²Università di Bologna, Italy In this work we perform a preliminary analysis of a full electric general aviation aircraft based on fuel cells and we compare the performance of this solution with those obtained with the same aircraft when powered with solid state batteries. For the considered class of aircraft, the results show that the fuel cell-based system can achieve a much greater range with respect to the battery powered system, when constraining the maximum take-off weight (MTOW). In particular, the fuel cell-based solution can achieve values of the range as large as 700nm, with a mass penalty with respect to the internal combustion engine (ICE) of about 30%, whilst the battery powered solution can only attain values of the range equal to 230nm | ||||
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| 16:30 | 17:00 | 3.3.1 |
LARGE LANGUAGE MODEL-DRIVEN SIMULATIONS FOR SYSTEM OF SYSTEMS ANALYSIS IN FIREFIGHTING AIRCRAFT CONCEPTUAL DESIGN J.L. Lovaco¹, R.C. Munjulury¹, I. Staack, Technische Universität Braunschweig, Germany; P. Krus, Linköping University, Sweden; ¹Saab Aeronautics & Linköping University, Sweden Aircraft designed for specific roles, such as firefighting, require a holistic consideration of systems and components. System of Systems analyses aim to achieve this by also considering collaborative emergent behaviours. The present approach integrates a Large Language Model into the decision-making process of Agent-Based Simulations within a wildfire study case. | ||||
| 17:00 | 17:30 | 3.3.2 |
DATA-DRIVEN MULTI-RANGE MISSION-BASED OVERALL AIRCRAFT CONCEPTUAL DESIGN OPTIMIZATION L.J. Liu¹, D. Kim, Ecole Nationale de l’Aviation Civile, France; C. Reyner¹, R.P. Liem¹; ¹The Hong Kong University of Science and Technology, Hong Kong SAR of China This study presents an overall aircraft design framework for aircraft sizing purposes. Multi-range missions are considered in the process for overall fuel economy optimization. The flight simulation process combines different-fidelity models for efficient mission analysis. The utility is demonstrated through fuel economy comparisons between single and multi-range mission-based designs. | ||||
| 17:30 | 18:00 | 3.3.3 |
ADVANCING ENGINEERING SOLUTIONS THROUGH LARGE LANGUAGE MODELS: A CASE STUDY E.A. Moura¹, P. Krus, Linköping University, Sweden; R.G.A. Silva.¹, L.C.S. Goes¹, A.A. Paula¹; ¹Instituto Tecnológico de Aeronáutica, Brazil Presenter: Petter Krus, Fluid and Mechatronic Systems/Linköping University This case study explores Large Language Models (LLMs) as an aid in various stages of aircraft design. LLMs can be adopted to assist in the conceptualization and development of advanced projects, by searching, synthesizing, comparing and generating code for the simulation of stages and systems. Thus, the study evaluates the role of LLMs in engineering, highlighting capabilities and limitations. | ||||
| 18:00 | 18:30 | 3.3.4 |
A DISTRIBUTED UMDO ARCHITECTURE BASED ON SURROGATE MODELS FOR LAUNCH VEHICLE DESIGN Y. Liu¹, C.N. Li¹, C.L. Gong¹; ¹Northwestern Polytechnical University, China This paper proposes a distributed UMDO architecture based on surrogate models to enable the UMDO problems to be solved. The architecture decouples uncertainty analysis and optimization, and surrogate models can quickly evaluate discipline performance and uncertainties. The liquid launch vehicle case is performing to validate the proposed architecture. | ||||
| additional information (interactive) | 3.3.R |
AIRFOIL PRESSURE PREDICTION BASED ON PHYSICS-INFORMED DEEP LEARNING APPROACH J.Z. Li¹, Y.J. Yang¹, Y.F. Zhang¹; ¹School of Aerospace Engineering, Tsinghua University, China | |||||
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| 16:30 | 17:00 | 4.3.1 |
NAVIGATING COMPLEXITY: ADAPTING AEROSPACE DEVELOPMENT IN A DYNAMIC WORLD C. Jouannet, Saab Aeronautics, Sweden The aerospace industry is confronting numerous challenges, from the imperative for more sustainable aviation to the integration of collaborative systems in defense, in a constantly changing world. This presentation will explore challenges and opportunities associated with leveraging Systems-of-Systems engineering in this context. | ||||
| 17:00 | 17:30 | 4.3.2 |
MODELING CARGO DEMAND FOR REGIONAL AIR TRANSPORT NETWORKS IN CANADA AND THE UNITED STATES M.M. Alexiev¹, R.E. Perez¹, P.W. Jansen¹, J.C.-H. Wang, Ribbit Inc., Canada; ¹Royal Military College of Canada, Canada By 2030, most of North America's regional aircraft cargo fleet is expected to be phased out. This research adapts a methodology for passenger demand prediction and extends it to model regional air cargo networks in both Canada and the United States. | ||||
| 17:30 | 18:00 | 4.3.3 |
RESEARCH ON UNMANNED CLUSTER RECONNECTION DECISION-MAKING METHOD CONSIDERING RESOURCE SUPPLEMENTATION M. Yao¹, X. Wang¹, L. Kong, Chinese Aeronautical Establishment, China; G. Fu¹, X. Wang¹, J. Yao¹; ¹School of Reliability and Systems Engineering, Beihang Universit, China Presenter: Mengfei Yao, School of Reliability and Systems Engineering, Beihang Universit For the reconnection problem of unmanned clusters under resource replenishment, performance and potential cognition is carried out, and the number of replenishment decision is made by integrating the performance enhancement and the cost, and based on this, the connection decision is made by preference connection and particle swarm optimization. | ||||
| 18:00 | 18:30 | 4.3.4 |
FROM ONTOLOGY TO SYSTEM ARCHITECTURE: AN MBSE APPROACH TOWARD THE REALIZATION OF URBAN AIR MOBILITY S. Sinha Roy¹, Y. Huang¹, D. Bekdache¹, T.-Y. Fung¹, B. Beck¹, C. Guariniello¹, D. DeLaurentis¹; ¹Purdue University, United States Presenter: Daniel DeLaurentis, Purdue University Various stakeholders related to Urban Air Mobility have been using a different concepts and terminologies in its developmental phase. To avoid future difficulties, we propose the combined use of ontology and system models for developing a common baseline architecture which can be customized for each city. This will ensure consistency, modularity, and interoperability upon the realization of UAM. | ||||
| additional information (interactive) | 4.3.R |
EFFECTIVENESS EVALUATION METHOD FOR AVIATION EMERGENCY RESCUE SYSTEM OF SYSTEMS BASED ON EFFECT CHAIN Y.-Z. Wang¹, B.-L. Shang¹, P.-F. Li¹, W.-Z. Liu¹, R.-X. Lin¹, K.-A. Xing¹, Y.-T. Deng¹; ¹School of Aeronautics, Northwestern Polytechnical University, China | |||||
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| 16:30 | 17:00 | 5.3.1 |
IDENTIFICATION METHOD OF LONGITUDINAL COEFFICIENTS BASED ON THE NUMERICAL STUDY OF THE FLOW TOPOLOGY AROUND THE SACCON GEOMETRY B. Isnard¹, G. Tanguy¹, D. Farcy¹, E. Garnier¹, J.-M. Foucault, LMFL, France; ¹ONERA, France This paper presents a new model for representing the aerodynamic torsor based on the flow topology on the upper surface of the SACCON geometry. In particular, it takes into account the evolution of flow dynamics as the angle of attack increases or decreases. Among other things, this model provides an improved representation of aerodynamic coefficients at high angles of attack. | ||||
| 17:00 | 17:30 | 5.3.2 |
AERODYNAMIC CHARACTERISTICS RESEARCH OF A DISTRIBUTED PROPULSION AIRCRAFT S. Chen¹, Z. Guo¹, G. Jia¹, D. Liu¹; ¹National University of Defense Technology, China The manuscript focuses on the distributed propulsion system of Unmanned Aerial Vehicles. The essential three-dimensional layout parameters of the distributed propulsion system are designed to be dimensionless, which intended to obtain the optimal layout law during takeoff and landing stages. Based on the experimental verification of numerical simulation methods, the Multi-Reference Frame (MRF) method and the sliding grid method were used to perform high-fidelity quasi-/unsteady RANS simulations of the aerodynamic characteristics of multiple propeller-wing-flap coupling configurations. The manuscript reveals the flow mechanism which caused by the aerodynamic interference of multiple propellers-wing-flap in a distributed propulsion system at low Reynolds numbers and high angles of attack; We focused on the three-dimensional spanwise and chord flow characteristics of the wing surface, and the optimal aerodynamic lift enhancement law of the distributed propulsion system is obtained. Finally, the results of Vortex Lattice Method calculation and RANS simulation at high angle of attack were compared, laying the foundation for the subsequent establishment of a rapid optimization process for the three-dimensional layout of distributed propulsion systems. | ||||
| 17:30 | 18:00 | 5.3.3 |
HYDRODYNAMIC ANALYSIS OF STATIC WATER IMPACT ON WEDGE-SHAPED HULL WATERTIGHT TEST SPECIMEN THROUGH NUMERICAL ANALYSIS M. Niu, Northwestern Polytechnical University, China; F. Sun, Xi'an Modern Control Technology Research Institute, China; C. Du, AVIC XAC COMMERCIAL AIRCRAFT CO., LTD., China; H. Huang, Northwestern Polytechnical University/Aircraft Strength Reserch , China Analyzing the static water impact of amphibious aircraft is essential. In this study, the computational fluid dynamics (CFD) software FLUENT is employed to numerically simulate the water response of a wedge-shaped hull in static water. This approach facilitates a detailed analysis of the hull's behavior under water landing conditions. | ||||
| 18:00 | 18:30 | 5.3.4 |
ON THE AERODYNAMIC CHARACTERISTICS OF CRESCENT WING D.F. Kurtulus¹, B. Anilir¹, D. Raymer, Conceptual Research Corporation, United States; ¹METU, Turkey This paper unveils a numerical simulation of the aerodynamic characteristics of crescent wings across a range of Reynolds numbers varying from 5×106 to 5×107. The study also explores the influence of the crescent wing's zero sweep line on its aerodynamic performance. The turbulent flow is resolved by k-? SST turbulence model. The methodology involves a validation process, aligning numerical simulations with wind tunnel experiments documented in existing literature. | ||||
| additional information (interactive) | 5.3.R |
A NUMERICAL VIRTUAL FLIGHT PLATFORM DEVELOPMENT AND ITS APPLICATION ON HIGH MANEUVERABILITY FLIGHT VEHICLES H. Qiao¹, F. Qin¹, S. Deng¹; ¹Nanjing University of Aeronautics and Astronautics, China | |||||
| additional information (interactive) | 5.3.R |
APPLICATION OF CONVOLUTIONAL NEURAL NETWORKS IN DETERMINING THE VELOCITY AND PRESSURE FIELDS AROUND AIRFOIL MODELS G. Sharma¹, T.H. Tran, Le Quy Don Technical University, Vietnam; J. Tanimoto¹; ¹Kyushu University, Japan | |||||
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| 16:30 | 17:00 | 6.3.1 |
VALIDATION OF MULTIPHASE FLOW SIMULATIONS BY EXPERIMENTAL MEASUREMENTS IN A CHANNEL FLOW M. Khaled¹, B. Faraji-Tajrishi¹, A. Herrgen, MTU Aero Engines AG, Germany; B. Weigand¹; ¹Institute of Aerospace Thermodynamics, University of Stuttgart, Germany Water separation from an exhaust gas flow is of great importance for the Water-Enhanced Turbofan concept (WET). Experiments and numerical simulations are performed in a rectangular channel to separate water from a gas flow. In this study a numerical model is developed and validated against measurements. To achieve this, Euler-Lagrange simulations combined with a Fluid Film model are conducted. | ||||
| 17:00 | 17:30 | 6.3.2 |
STUDY OF THE SCAVENGE PUMP PERFORMANCE FOR TWO-PHASE FLOW IN AN AIRCRAFT ENGINE LUBRICATION SYSTEM N. Wu¹, J.-P. Hu¹, Y.-G. Lyu¹, J. Wang¹, Y. Tan¹, Z.-X. Liu¹; ¹Northwestern Polytechnical University, China The lubrication system of aircraft engines supplies lubricating oil to the bearings and gears for lubrication, which mixes with the sealed air in the cavity to form an oil-air mixture in the bearing cavity and accessory gearbox. The oil return pump suctions the oil-air mixture for transport to components such as the oil-gas separator for the recovery of lubricating oil, and ultimately returns to the sliding oil tank for cyclic use. For the problem of poor oil return effect of the oil return pump, this paper focuses on studying the scavenge pump and conducts experimental research on the flow rate performance under negative pressure at high altitude based on ground tests. The high-altitude state takes the local atmospheric pressure at different flight altitudes of the aircraft as a reference, adjusts the inlet pressure of the pumps at all levels to the reference value, and measures the flow rate after reaching stability; the ground state obtains the flow rate characteristics of the pumps at different outlet pressures by adjusting the pressure after the pumps. This article obtains the effect of inlet pressure, outlet pressure, and rotational speed on the flow characteristics and volumetric efficiency of the oil return pump under high-altitude pressures in the pure oil state. | ||||
| 17:30 | 18:00 | 6.3.3 |
STUDY OF DROPLET MOTION AND WATER FILM FLOW CHARACTERISTICS ON SUPERHYDROPHOBIC SURFACES UNDER AIRFLOW SHEARING H. Zhao¹, D. Zhu¹, S. Wang², S. Chang², L. Yu¹, Y. Wu¹; ¹AVIC Aerodynamics Research Institute, China ;²Beihang University, China NA | ||||
| 18:00 | 18:30 | 6.3.4 |
EXPERIMENTAL SETUP FOR THE INVESTIGATION OF WATER SEPARATION IN ANNULAR FLOW WITHIN A CIRCULAR CHANNEL R. Haidl¹, B. Weigand¹; ¹Institute of Aerospace Thermodynamics, University of Stuttgart, Germany An experimental investigation of different separation lip designs is carried out to better understand the process of water separation from a supersaturated flow in a circular, horizontal channel. The experiments are conducted at Reynolds numbers between Re ? 70,000?230,000 and for different levels of supersaturation. The water recovery factor and the pressure loss denote the two key parameters. | ||||
| additional information (interactive) | 6.3.R |
EXPERIMENTAL STUDY ON MULTI-ATTITUDE OIL SUPPLY STRUCTURE Y. Xu¹, Y.-G. lLyu¹, J.-P. Hu¹, Z. Liu¹; ¹Northwestern Polytechnical University, China | |||||
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| 16:30 | 17:00 | 7.3.1 |
ENHANCING PUBLIC GOOD MISSIONS AND DISASTER RESPONSE WITH ADVANCED AERIAL TECHNOLOGY: OPPORTUNITIES AND CHALLENGES A. Andreeva-Mori, Japan Aerospace Exploration Agency (JAXA), Japan; D. Sziroczák, Budapest University of Technology and Economics (BME), Hungary; G. Schwoch, German Aerospace Center (DLR), Germany; M.C.R. Murça, Aeronautics Institute of Technology (ITA), Brazil; B. Dziugiel, Lukasiewicz Research Network – Institute of Aviation (ILOT), Poland; J. Homola, National Aeronautics and Space Administration (NASA), United States; V. Kramar, VTT Technical Research Centre of Finland, Finland IFAR researchers have identified many commonalities in original advanced air mobility (AAM) applications, i.e., public good missions. This presentation will identify commonalities and differences in the disaster-response research conducted by various IFAR members and discuss lessons learned and remaining gaps. Most common use cases and types of disasters are shown and analyzed. | ||||
| 17:00 | 17:30 | 7.3.2 |
NASA RESEARCH TO EXPAND UAS OPERATIONS FOR DISASTER RESPONSE K. Ellis¹, M. Johnson¹, N. Neogi¹, J. Homola¹; ¹NASA, United States Natural disasters can result in the loss of life and cost governments and private industry billions to recover each year. Over the past decade the rate and severity of natural disasters such as wildfires and hurricanes have resulted in increasingly negative impacts to communities, public health, natural ecosystems, and the economy. To help reduce these impacts, NASA’s Aeronautics Research Mission Directorate is working to advance technologies and enable the safe and efficient inclusion of novel aviation applications to better assist in disaster response. To execute on these efforts, NASA’s Advanced Capabilities for Emergency Response Operations (ACERO) and System-Wide Safety (SWS) projects have developed coordinated strategic research plans focused on aviation operations for disaster response. The ACERO project will be a multi-year effort that focuses on enabling the use of uncrewed aircraft systems (UAS) to improve firefighter safety and efficiency and enable the use of UAS to conduct new missions such as logistics and aerial suppression. The ACERO project will demonstrate technologies that support the Second Shift concept, enabling UAS and ground technologies to support aerial suppression in degraded visual conditions (e.g., heavy smoke, nighttime). The SWS project will be a multi-year effort that focuses on addressing the key safety barriers that are preventing the authorization of UAS operations in a variety of increasingly complex disaster response applications: post-hurricane response, medical courier, and urban disaster response. The SWS project will demonstrate an In-Time Aviation Safety Management System (IASMS) designed to effectively monitor, assess, and mitigate safety risks associated with hazards to UAS operations for disaster response. This paper will provide a deeper insight into NASA’s research and development plans and discuss how solutions developed in partnership with industry stakeholders and federal agencies will improve disaster response acros | ||||
| 17:30 | 18:00 | 7.3.3 |
ON-GOING WILDLAND FIRE WORK AT THE NATIONAL RESEARCH COUNCIL OF CANADA WITH A FOCUS ON THE USE OF COTS RPAS FOR REDUCTION OF NON-FIRE PILOT WORKLOAD G. Leblanc¹, G. Ifimov¹, M. Kalacska², O. Lucanus², J.P. Arroyo-Mora¹, J. Gorman¹, M. Wheatley, Ontario Ministry of Natural Resources and Forestry, Canada; C. McFayden, Natural Resources Canada, Canada; ¹National Research Council of Canada (NRC), Canada ;²Applied Remote Sensing Laboratory, McGill University, Canada The effective use of aircraft crew duty day is a major consideration for airborne asset operators including during disaster relief efforts. During wildfire operations, crew duty day is impacted by non-fire suppression activities, such as reconnaissance and intelligence gathering of the active fire and burned regions. The National Research Council of Canada and supporting partners, the Applied Remote Sensing Laboratory (McGill University), the Ontario Ministry of Natural Resources and Forestry, and the Canadian Forest Service, have on-going collaborative activities to provide assessments of the utility of Commercial off-the-shelf (COTS) Remotely Piloted Aircraft Systems (RPAS) for general non-fire suppression support to the wildfire management team. These areas of support include assessing active fire and smouldering detection distances and accuracies, nighttime RPAS visible and thermal IR-based intelligence gathering operations, general situational overview of the fire front and determining practical limitations with COTS RPAS in these environments. Here we present the on-going work, over the last 2 years of a multi-year effort to assess these fires using controlled fire experiments under various conditions, including under snow. Thermal imaging has been the primary tool for our work to date, however, we also include the use of 4K video, VisNIR (visible to near-infrared)_hyperspectral imaging and LiDAR pre/post burn assessments. To date, there have been effective detection distances of up to 9 km from a number of relatively small (~40 m x 10 m being the largest ) slash pile burns, as well as a high degree of active fire detection with a hyperspectral imager detecting a potassium emission feature in the radiance spectra – indicating high energies enough to allow for fire-induced emission to occur. Ground validation of fire intensity and temperatures were achieved by the simultaneous use of a FLIR thermal imager and in-situ temperature probes. The u | ||||
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| 16:30 | 17:00 | 8.3.1 |
MORPHING LEADING-EDGE TUBERCLES ON CESSNA 172 WING G. Abate¹, H.P. Monner¹; ¹German Aerospace Center (DLR), Germany Sinusoidal modifications of the leading-edge also called “tubercles” are applied to the Cessna 172 wing in order to study their aerodynamic effect especially at post-stall conditions. Originally, tubercles characterize the Humpback whale flippers, and they help these giant animals to increase their speed and maneuverability into the water by acting like flow control devices. Studies showed that tubercles are similar to vortex generators and wing fences: they re-energize the leading-edge flow by generating vortices that can block most of the spanwise flow leading to a delay in flow separation and stall. It has been shown that they can successfully be applied to fans and wind turbine blades, but not many works highlight their positive effects on wing applications. Therefore, the present study wants to conduct an aerodynamic analysis of tubercles applied to the leading-edge of the Cessna 172 wing. A particular attention will be given to three design parameters: amplitude, wavelength, and wingspan location. These variables characterize every single tubercle configuration, and their combination results in different aerodynamic flow effects. The aim of this analysis is to give some insights on tubercle parameterization and their geometric characteristics in order to achieve stall delay and relevant aerodynamic improvements in off-design regimes. Moreover, as mentioned before, since the positive effect of tubercles is relevant only at some flow conditions or regimes, the present work wants to consider the possibility of designing tubercles as morphing structures that are deployed only when needed by changing the shape of the leading-edge wing thanks to smart materials and actuators. | ||||
| 17:00 | 17:30 | 8.3.2 |
ON THE CHALLENGES OF SURROGATE-BASED AERODYNAMIC SHAPE OPTIMISATION J. Rasines¹, D. Verstraete¹; ¹The University of Sydney, Australia Simulation failures are a critical challenge in surrogate-based aerodynamic shape optimisation. Understanding its effect on algorithm convergence and trends between low- and high- fidelity simulation is essential to inform efficient algorithm design. This works investigates this through evaluation of a low Reynolds number airfoil design problem. | ||||
| 17:30 | 18:00 | 8.3.3 |
AERODYNAMIC ANALYSIS OF CAMBER MORPHING AIRFOILS USING PARTICLE IMAGE VELOCIMETRY AND COMPUTATIONAL FLUID DYNAMICS METHODS M. Marciniuk¹, L. Kiszkowiak², P. Piskur, Polish Naval Academy of the Heroes of Westerplatte, Poland; L. Malicki¹, K. Strzelecka¹, K. Sibilski², S. Kachel²; ¹Wroclaw University of Science and Technology, Poland ;²Military University of Techology, Poland The paper presents aerodynamic analysis results of camber morphing airfoils using Particle Image Velocimetry and Computational Fluid Dynamics methods. Velocity distribution from the PIV experiment was used to validate the numerical model. Morphing airfoils could provide better aerodynamic performance due to a smooth transition between the leading and trailing edges. | ||||
| 18:00 | 18:30 | 8.3.4 |
ENGINEERING-BASED TOOL FOR THREE-DIMENSIONAL ESTIMATIONS OF RE-ENTRY VEHICLES AEROTHERMODYNAMICS P.E. Di Nuzzo, Italy; M. Maione¹, G. Pezzella¹, A. Viviani¹; ¹University of Campania, Italy Presenter: Maria Maione, Department fo Engineering, University fo Campania "L. Vanvitell The paper deals with the development, implementation, validation, and application of an engineering-based tool able to determine the aerothermodynamic loading environment the assigned re-entry vehicle must withstand during the hypersonic flight. The tool, based on predictive models that are faster than other more reliable simulation approaches (e.g., Computational Fluid Dynamics, CFD), is particularly suitable to feed Multidisciplinary Design Optimization (MDO) procedures to develop next generation re-entry vehicles | ||||
| additional information (interactive) | 8.3.R |
MODELLING ASTEROID TRAJECTORY IN EARTH’S ATMOSPHERE R.H. Morais¹, L.F. Ferreira Marques, ISEC, Portugal; A. Resende Rodrigues da Silva¹, R. Melicio, LAETA-IDMEC, Instituto Superior Técnico, Universidade de Lisboa, Portugal; ¹LAETA-AEROG, Universidade da Beira Interior, Portugal | |||||
| additional information (interactive) | 8.3.R |
AERO-KINEMATIC OPTIMIZATION OF HIGH-LIFT DEVICES WITH DOWNWARD DEFLECTION OF SPOILER C. Wei¹, C. Rao¹, L. Yang¹, T. Zhang¹; ¹Aerodynamics Research Institute, China | |||||
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| 16:30 | 17:00 | 9.3.1 |
ADVANCED HUMAN MACHINE INTERFACES FOR DRONE MONITORING: ASSESSMENT OF THE TECHNOLOGICAL FRAMEWORK FOR THE DESIGN OF AN AUGMENTED REALITY INTERFACE S. Bagassi¹, T. Fadda¹, M. Corsi¹; ¹University of Bologna, Italy As UASs are constantly growing in number and intended tasks over the years, risks for safety and security, including incursion in restricted areas or collision with other air vehicles, are also increasing. Exploiting recent solutions for airport towers and UAS piloting, this work assesses a novel framework for the design and implementation of an A/MR interface for UAS surveillance and monitoring | ||||
| 17:00 | 17:30 | 9.3.2 |
CORUS-XUAM: TACKLING URBAN AIR MOBILITY AIRSPACE INTEGRATION CHALLENGES G. Riccardi¹, L. Brucculeri¹, E. Fornaciari, d-flight, Italy; M. D'Onofrio, Techno Sky, Italy; A. Zilli², D. Leanza², G. Ferrara, Eurocontrol, France; M. Molinario³, G. Esposito³, A. Favier, Pipistrel, Italy; ¹ENAV S.P.A, Italy ;²DTA, Italy ;³NAIS, Italy Presenter: Giancarlo Ferrara, EUROCONTROL The paper is focused on demonstrations in the context of CORUS XUAM SESAR Project. The activity was focused on Urban Air Mobility cargo operations between civil airport and logistics centers. Flight tests, with involvement of a large fixed wing aircraft and other drones took place in south of Italy with involvement of Air Traffic Management component and U-space services. The demo addressed: safety, access and equity, cyber security and human performance. | ||||
| 17:30 | 18:00 | 9.3.3 |
AI-ASSISTED DESIGN OF UAV DOCKING STATION NETWORK FOR DUAL USE PURPOSES A. Avi¹, G. Quaranta¹, A. Valentini, Fondazione Bruno Kessler, Italy; ¹Politecnico di Milano, Italy In this paper we propose a method to design a network of unmanned aerial vehicle docking station in order to perform dual-use activities. In particular, we aim to develop a method, based on European AI On-Demand (AI4EU) platform, that could select best locations where docking station should be located. | ||||
| 18:00 | 18:30 | 9.3.4 |
LOW-ALTITUDE INTEGRATED AIRSPACE OPERATIONS OF AIRCRAFT FLYING UNDER VISUAL FLIGHT RULES: THE VERTICAL DIMENSION A. Andreeva-Mori¹, K. Ohga¹, K. Kobayashi¹; ¹Japan Aerospace Exploration Agency (JAXA), Japan Helicopters, small drones and eVTOLs are going to share low altitude airspace, and are most likely to be separated vertically. This research uses mission information to model altitude profiles based on actual flight data and pilot interviews. | ||||
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| 16:30 | 17:00 | 10.3.1 |
NUMERICAL SIMULATION STUDY ON THE INFLUENCE OF WING SPACING OF DRAGONFLY-INSPIRED FLAPPING WINGS Y. Luo, China; L. Wang, China; J. Wang, China; X. Lang, China; X. Yang, China Dragonflies are widely concerned for their flying skills. In this paper, aiming at the dragonfly-inspired tandem wings, the effect of wing spacing is analyzed using Computational Fluid Dynamics (CFD). The results indicate that the change of the distance between the tandem wings may affect the peak of the force coefficient. This may lead to a large gap in the aerodynamic efficiency of tandem wings. | ||||
| 17:00 | 17:30 | 10.3.2 |
COMPUTATIONAL FLUID DYNAMICS ANALYSIS OF A DIRECT AIR CAPTURE FILTER SYSTEM M. Panagopoulos¹, N.J. Lawson¹, D.M. D’Alessandro¹, E. Kearns¹; ¹University of Syndey, Australia CFD simulations were used to predict the static pressure drop across the filter system of a Direct Air Capture (DAC) device. CFD predictions were in agreement with experimental validation. Pressure losses within the filter were found to be resultant of high pressure regions forming, inducing turbulence. The computational model is hence able to be used in the optimisation of the DAC device. | ||||
| 17:30 | 18:00 | 10.3.3 |
DESIGN OF DUAL-FUSELAGE FLIGHT PLATFORM FOR JET CONTROL FUNCTION VERIFICATION C.P. Li, China; G. Zhang, China; N. Liu, China; Y. Zhang, China; L. Xu, China; M. Wang, China At present, the numerical simulation and wind tunnel test methods used in the study of jet control mechanism are relatively mature, but the means for systematic verification are generally lacking. For this purpose, this paper proposes a low-cost flight platform which can verify the autonomous jet control function in the air. | ||||
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| 16:30 | 17:00 | 11.3.1 |
AEROELASTIC ISSUES IN THE DESIGN OF HIGH ASPECT RATIO STRUT-BRACED WING AIRCRAFT E. Roncolini¹, F. Toffol ¹, S. Ricci¹; ¹Politecnico di Milano, Italy Carbon-based fuels released CO2 is identified as the main responsible for climate change. Several initiatives have been proposed in EU to limit the usage of these fuels, such as the Clean Sky 2 U-HARWARD project. One of the tasks was to study a promising unconventional configuration: the Strut-Braced Wing (SBW). Particular attention must be posed on its design. | ||||
| 17:00 | 17:30 | 11.3.2 |
DYNAMIC BUCKLING ANALYSIS OF THIN-SHELL COMPOSITE STRUCTURES BASED ON ISOGEOMETRIC ANALYSIS H. Qiu¹, Y. Guo¹, Z. Guan¹, H. Zhu¹, Y. Pan¹; ¹Nanjing University of Aeronautics and Astronautics, China A comprehensive framework for the dynamic buckling analysis of composite shell structures has been proposed based on isogeometric analysis. The influences of cut-outs, the amplitude and duration of step pulse load are studied. In particular, the geometric imperfections can be reconstructed and naturally incorporated into the IGA framework due to the unified NURBS basis adopted. | ||||
| 17:30 | 18:00 | 11.3.3 |
EFFICIENT AEROSTRUCTURAL DESIGN OPTIMIZATION COMBINING GRADIENT-ENHANCED KRIGING WITH COUPLED ADJOINT METHOD H.-J. Guo, China; Z.-H. Han, China; C.-Z. Xu, China; K.-S. Zhang, China; W.-P. Song, China; J.-Q. Luo, China An aerostructural analysis code including the coupled adjoint analysis module is developed, then the efficiency and global performance of aerostructural design optimization are improved by combining GEK model with the coupled adjoint method. | ||||
| 18:00 | 18:30 | 11.3.4 |
BIRD AND DRONE IMPACT DAMAGE PROGNOSIS OF ON-DEMAND AIR MOBILITY SERVICE AIRCRAFT ENGINE H. Raza¹, P. Vaghela¹, E. Stumpf, RWTH Aachen, Germany; J. Bayandor¹; ¹University at Buffalo, United States Direct and oblique impacts from bird and drone are modelled on the engine of a modern short take-off and landing aircraft for On-Demand Air Mobility using high fidelity user defined modeling and analysis. Results from the impacts are analyzed and compared to investigate the damage and vibration instability of the aircraft engine to establish new analysis strategies and airworthiness criteria. | ||||
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| 16:30 | 17:00 | 12.3.1 |
DESIGN OF MEASUREMENT SETUP FOR HIGH-ALTITUDE IN-FLIGHT EXPERIMENTS ON DU89-134/14 AIRFOIL AT LOW REYNOLDS NUMBER M. Avirovic¹, C. Brunelli¹, K. Wykes², C. Mengdehl², B.G. Marinus¹, J. Degroote, University of Ghent, Belgium; J. Van Beeck, Von Karman Institute for Fluid Dynamics, Belgium; ¹Royal Military Academy, Belgium ;²Stemme Belgium, Belgium The goal of this research is to design a measurement setup for high-altitude in-flight experiments and to investigate the aerodynamic impact of the test airfoil configuration on the HAPS flight demonstrator, which will be used as the unmanned test aircraft. The design of the test airfoil, pressure measurement, infrared thermography, and temperature sensitive paint setups will be presented. | ||||
| 17:00 | 17:30 | 12.3.2 |
UPGRADE OF THE VTI T-38 BLOWDOWN TRISONIC TEST FACILITY: WIND TUNNEL CONTROL SYSTEM B. Ilic¹, G. Ocokoljic¹, M. Samardžic¹, J. Isakovic, Academy of Applied Technical Studies, Serbia; ¹Military Technical Institute, Serbia The paper addresses a recent major facility upgrade of the VTI T-38 wind tunnel. More than 30 years after the wind tunnel commissioning, a novel solution for test automation developed by VTI brings more than an order of magnitude improved testing accuracy, higher versatility of information obtained from the tests, as well as significantly reduced wind-on time and energy consumption, confirming the VTI T-38 ability to perform tests with the uniform quality from low subsonic speeds via transonic conditions and up to high supersonic speeds. | ||||
| 17:30 | 18:00 | 12.3.3 |
SURFACE VISUALISATION OF TIME AVERAGED FLOW BEHAVIOUR AROUND RIGID AND FLEXIBLE HEMISPHERES UTILISING UV SENSITIVE OIL N. Menakath¹, N.J. Lawson¹, G.A. Vio, Defence Science and Technology Group, Australia; ¹The University of Sydney, Australia Testing has been conducted to provide a comparison between the surface flow characteristics around a thin walled, flexible hemisphere and a rigid hemisphere immersed in a turbulent boundary layer, to observe the variance due to fluid-structure interactions. This work is applicable to design of use morphing structures externally on the fuselage of aircraft, such as for usage as a sensor shroud. | ||||
| 18:00 | 18:30 | 12.3.4 |
HOT-WIRE ANEMOMETRY OF THE BOUNDARY LAYER PRIOR TO A CAVITY IN RESPONSE TO VARIED UPSTREAM GEOMETRY C.O.L. Hamilton Smith¹, N.J. Lawson¹; ¹The University of Sydney, Australia Wind tunnel tests were conducted with hot-wire anemometry to map the boundary-layer prior to an open cavity of L/D = L/W = 3, at U = 10-20m/s. Changes in geometry up-stream were used to alter the boundary-layer profile, separation, acceleration and turbulence intensity, to see how the up-stream boundary-layer impacted cavity response. A number of complex geometry changes using fuselage and nose curvature controlled the boundary-layer . Results align with literature, where a thin boundary-layer returns more energetic excitation. In contrast, a thick boundary-layer was found to filter out detrimental acoustic phenomena. This data is part of a larger study, to see how BL data can be used to predict cavity spectral response and cavity feedback, to harvest energy inside the cavity. | ||||
| additional information (interactive) | 12.3.R |
REVITALIZATION OF A FLOW-CELL DEVICE FOR AIR INTAKE TESTING AND ITS INTEGRATION WITH WIND TUNNEL SYSTEMS D. Damljanovic¹, D. Vukovic¹, L. Petrovic¹; ¹Military Technical Institute, Serbia | |||||
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| 16:30 | 17:00 | 13.3.1 |
EXPERIMENTAL AND NUMERICAL INVESTIGATION OF NOISE GENERATION IN HYDROGEN AND METHANE-HYDROGEN LAMINAR FLAMES F.G. Schiavone¹, M. Durand², M. Torresi¹, S.M. Camporeale¹, T. Schuller², D. Laera¹; ¹Polytechnic University of Bari, Italy ;²Institut de Mécanique des Fluides de Toulouse, France Understanding combustion noise generation is crucial to implement noise reduction strategies in aircraft propulsion systems. Noise generation is here investigated in hydrogen and methane-hydrogen laminar flames, stabilized over a bluff-body burner. Numerical simulations are performed adopting detailed reaction schemes and a fully resolved approach and compared with experimental recordings. | ||||
| 17:00 | 17:30 | 13.3.2 |
AN EXPERIMENTAL SIMULATION ON THE INFLUENCE OF DIFFERENT FILM COOLING HOLE SHAPES ON PARTICLE DEPOSITION ON TURBINE VANE Z. Liu¹, R. Ruan¹, L. Cheng¹, Y. Zhang¹, Z. Liu¹, D. Wu¹; ¹Northwestern Polytechnical University, China When aircrafts fly in environments with high concentrations of sand, dust, and other particles, the engines will inhale a large number of these particles. After entering the aero engine, these particles undergo heating in the combustion chamber and then interact with the turbine vanes in a molten or solid-state, depositing on the surface of the turbine vanes. This affects the aerodynamic and heat transfer characteristics of the turbine vanes and may even block the film cooling holes, leading to the erosion of the turbine vanes and accordingly a flight accidents. Currently, film cooling is used on most high-performance turbine vanes to protect the vanes from heat. However, the presence of film cooling causes interference between the mainstream and cooling flows, which seriously affects the deposition characteristics of particles on the vane surface. Changes in the film cooling hole shape not only affect the cooling efficiency of the vane but also the flow field structure behind the film cooling hole, which in turn affects the movement and heat transfer of particles in the flow field, leading to changes in the amount and distribution of particle deposition on the vane surface. This paper conducts experimental studies on the deposition of particles on flat surfaces with different film cooling hole shapes near ambient temperature conditions, and explores the influence of different film cooling hole shapes on the particles deposition, providing reference for the design of film cooling holes for turbine vane to reduce the deposition. The experimental system applied by Liu et al and consists of the wind tunnel, the wax spray system and the cooling air system, however, the last of which is revised. Atomized wax is used for simulating the particles in harsh environments, and the film-cooled flat plate serves as the test model. The wax deposition on the flat plate surface simulates the deposition of particles on the actual turbine blade surface. The airflow in the w | ||||
| 17:30 | 18:00 | 13.3.3 |
FUEL CONSUMPTION MONITORING OF TURBOPROP ENGINE J. Juracka¹, Z. Hubnerova¹; ¹Brno University of Technology, Czech Republic Article describes a statistical approach to the diagnosis of the change in consumption of turboprop engine. The method of two-parametric regression analysis was choosed and applied on the real flight data. Next, the influence of the ambient temperature on the engine characteristics was analyzed. The results of the analyzes show a real benefit showing changes in engine consumption. | ||||
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| 16:30 | 17:00 | 14.3.1 |
ASSESSING THE TECHNICAL VIABILITY OF ALL-ELECTRIC HYDROGEN-POWERED AIRCRAFTS P. Marocco¹, M.C. Massaro¹, A.H.A. Monteverde¹, M. Santarelli¹; ¹Politecnico di Torino, Italy A comprehensive overview of the most promising solutions for all-electric hydrogen-based aircraft in current and future scenarios is conducted, both from a technical and environmental perspective. A detailed electrochemical model of the fuel cell section is also implemented for an accurate design of the propulsion system. | ||||
| 17:00 | 17:30 | 14.3.2 |
MODELLING A HYDROGEN FUELLED COMPOSITE CYCLE AEROENGINE A. Johansson¹, P. Miltén¹, A. Lundbladh, GKN Aerospace, Sweden; C. Xisto¹; ¹Chalmers University of Technology, Sweden A composite cycle engine (CCE) is an air-breathing jet engine that combines the power density of turbomachinery with the thermal efficiency of a piston engine. The present work investigates the synergies of combining the CCE with hydrogen fuel. A system level model is presented and used to estimate the performance of a short-medium range aircraft engine, focusing on fuel burn and emissions. | ||||
| 17:30 | 18:00 | 14.3.3 |
CFD-BASED SCOUTING FOR THE DESIGN OF A MULTI-FUEL KEROSENE/HYDROGEN ATMOSPHERIC BURNER L. Palanti¹, L. Mazzei¹, C. Bianchini¹, S. Link², K. Dave², F. De Domenico², A.G. Rao²; ¹Ergon Research, Italy ;²TU Delft, Netherlands Within the HOPE project, this study focuses on the multi-fuel concept for aircraft propulsion. Considering a laboratory-scale combustor hosted at TU Delft and originally fueled with pure hydrogen, reactive CFD simulations are used to explore different spray injection configurations and assess the impact of kerosene on the overall performance of the rig. | ||||
| 18:00 | 18:30 | 14.3.4 |
MODELLING AND INITIAL ASSESSMENT OF A FUEL CELL AUXILIARY PROPULSION AND POWER UNIT M.G. Kolb¹, A. Seitz¹, B. Türkyilmaz¹, Y. Ma¹, M. Hornung¹; ¹Bauhaus Luftfahrt e.V., Germany This paper carries out an initial assessment of a novel Fuel Cell Auxiliary Propulsion and Power Unit (FC-APPU) for a short-to-medium range passenger aircraft with an entry-into-service of 2035. Integration implications of a FC-APPU system in terms of mass, drag and hydrogen consumption for different technology scenarios are presented and compared against a Fuel Cell Auxiliary Power Unit (FC-APU). | ||||
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| 16:30 | 17:00 | 15.3.1 |
DOWNRANGE CONTROL GUIDANCE FOR REENTRY BURN OF REUSABLE LAUNCH VEHICLE K.-W. Jung¹, C.-H. Lee¹; ¹KAIST, South Korea This study addresses trajectory correction for Reusable Launch Vehicles using a new guidance law. It focuses on reentry burn phase, utilizing prediction of aero-ballistic trajectories by partial-closed form solution . Simulations confirm its effectiveness and computational efficiency, improving robustness of the RLV operations. | ||||
| 17:00 | 17:30 | 15.3.2 |
EXPLICIT MODEL FOLLOWING TRAJECTORY CONTROL SYSTEM FOR MULTIPLE VERTICAL TAKEOFF AND LANDING CONFIGURATIONS A. Comer¹, I. Chakraborty¹; ¹Auburn University, United States This paper demonstrates a flight control system architecture suitable for Simplified Vehicle Operations and applicable to three dissimilar vehicle configurations. It utilizes a novel Trajectory Control System for controlling longitudinal dynamics coupled to explicit model following inner-loop control. This is demonstrated through representative maneuver simulations. | ||||
| 17:30 | 18:00 | 15.3.3 |
CONVEX PROGRAMMING APPROACH OF ROBUST POWERED DESCENT GUIDANCE THROUGH DYNAMIC TUBE MPC J.-I. Jang¹, C.-H. Lee¹, S. He, BIT, China; ¹KAIST, South Korea Robust powered descent guidance algorithm is presented based on dynamic tube MPC. The modeling error and disturbances are explicitly considered in the MPC problem and tube geometry is simultaneously optimized along with the original powered descent guidance states. Furthermore, the proposed robust PDG problem is transformed into convex optimization for real-time application. | ||||
| 18:00 | 18:30 | 15.3.4 |
SYSTEM ARCHITECTURE AND EVALUATION METHOD OF HUMAN-MACHINE COLLABORATION IN FLIGHT CONTROL SYSTEM J. Che¹, X. Chen¹, S. Che, Northwestern Polytechnical University, China; J. Li¹, Z. Sun¹; ¹Flight Automatic Control Research Institute, AVIC, China We presented a human-machine collaboration system architecture based on cognitive model. Using mixed evaluation method combing scale and operation performance, the performance of the system is evaluated. Different scenarios are tested with different level of assistance.Our method is more conducive to the evaluating the performance of artificial intelligence algorithm. | ||||
| additional information (interactive) | 15.3.R |
PILOT INDUCED OSCILLATIONS AND FLIGHT PHASES IDENTIFICATION OF THE SPACE SHUTTLE AND TRANSPORT AIRPLANES S. Kolb, CREA, France | |||||
| additional information (interactive) | 15.3.R |
A NOLINEAR MODEL PREDICTIVE CONTROL METHOD FOR AIRBREATHING HYPERSONIC VEHICLE BASED ON KOOPMAN OPERATOR C.R. Li¹, W.Q. Li¹, Y. Li¹, S. Tang¹; ¹Northwestern Polytechnical University, China | |||||
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| 16:30 | 17:00 | 16.3.1 |
HARDWARE-IN-THE-LOOP SIMULATION FRAMEWORK FOR THE EVALUATION OF AUTONOMOUS FLIGHT FUNCTIONS D. Pla Guerrero¹, A. Hegde¹, J. Wan, Flanders Make, Belgium; E. Allegaert¹, Y. Lemmens¹; ¹Siemens Digital Industries Software, Belgium Presenter: Elias Allegaert, Siemens Digital Industries Software This paper presents a hardware-in-the-loop simulation framework for autonomous aerial vehicles to validate the performance of the flight controllers in realistic flight conditions. The framework makes use of the Siemens Simcenter software and was evaluated with a Pixhawk flight controller together with a visual simultaneous localization and mapping algorithm on a flight computer | ||||
| 17:00 | 17:30 | 16.3.2 |
FLIGHT CONTROL SYSTEM KNOWLEDGE GRAPH CONSTRUCTION BASED ON AERONAUTICAL DOMAIN KNOWLEDGE AUGMENTED LARGE LANGUAGE MODEL Y. Fan, China; Y. Sun, China; B. Mi, China Continuous intelligent safety assurance of the flight control system (FCS) determines the possibility of mission execution of the aerospace vehicle, and the system state monitoring and assurance of massive data is a task that relies heavily on the empirical knowledge of experts. Therefore, this paper develops a set of FCS knowledge graph construction and application process based on the domain knowledge augmented large language model (LLM) for the problem of difficult knowledge discovery and organization of FCS. By integrating the aeronautics domain knowledge base, to form the FCS ontology, combining the entity relationship types defined in the ontology, adopting the retrieval augmented generation (RAG) e.g. Langchain method on the basis of the basic LLM e.g. ChatGPT, injecting the information in the domain knowledge base, and designing the simple content-type and sentence-type prompt information templates for different FCS knowledge extraction tasks, we can realize the FCS knowledge graph construction and application process. The proposed method can realize the zero-shot or one-shot intelligent extraction FCS knowledge, and display the FCS knowledge in the form of visual graph, which can be applied to FCS data and knowledge value mining and state monitoring. | ||||
| 17:30 | 18:00 | 16.3.3 |
AN UAV MANEUVERING DECISION-MAKING ALGORITHM BASED ON DEEP TRANSFER REINFORCEMENT LEARNING K. Li¹, K. Zhang¹, H. Liu², Y. Li², Q. Wang¹; ¹Northwestern Polytechnical University, China ;²Shenyang Aircraft Design and Research Institute, China Aiming at UAV guidance and aiming problem, we proposed a UAV Maneuvering Decision-Making Algorithm Based on Deep Transfer Reinforcement Learning. We refined the long-distance guidance task and the near-end aiming task and designed the UAV maneuvering decision-making model based on MDPs. And we presented a novel reward function based on expert experience and trained policy by curriculum learning. | ||||
| additional information (interactive) | 16.3.R |
AUTONOMOUS LANDING OF A QUADROTOR ON A MOVING TARGET WITH OCCLUSION AVOIDANCE MANEUVER D. Kim¹, H.J. Kim¹; ¹Seoul National University, South Korea | |||||
| additional information (interactive) | 16.3.R |
ULTRA-LOW-ALTITUDE PENETRATION PATH PLANNING FOR FIXED-WING AIRCRAFT BASED ON NMP ALGORITHM H.-X. Huang¹, D.-B. Li¹, P.-Y. Qi¹, Y.-X. Shang¹; ¹beihang university, China | |||||
| additional information (interactive) | 16.3.R |
AN OPTICAL FLOW BASED GUIDANCE ALGORITHM FOR A QUADROTOR UAV MOVING INSIDE CIRCULAR CORRIDORS A. Bagherzadeh¹, F. Saghafi¹; ¹Sharif University of Technology, Iran | |||||
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| 16:30 | 17:00 | 17.3.1 |
HYBRID AIR DATA SYSTEM ARCHITECTURE: FROM DESIGN TO FLIGHT TEST VERIFICATION M. Rovelli¹, A. Brandl¹, S. Di Bitonto¹, F. Di Donfrancesco¹, E. Maruccia¹, I. Viglietti¹, D. Marchetti¹; ¹Leonardo, Italy Overview of the design, integration and test of a Hybrid Air Data System architecture that relies on both sensors and synthetic estimator, designed to solve a calibration problem occurring on an already existing architecture. The proposed design is verified and validated in a laboratory environment and through flight testing. | ||||
| 17:00 | 17:30 | 17.3.2 |
DEVELOPMENT AND TESTING OF AN ACTUATION SYSTEM FOR A MORPHING CONTROL SURFACE M. Schäfer¹, R. Keimer¹, O. Bertram¹; ¹German Aerospace Center (DLR), Germany Morphing structures can contribute to reduce the fuel consumption of aircraft. In addition to the structure itself, an actuation system must be developed that meets the requirements for an aircraft control surface. The paper presents the design, test environment, and experimental results of an actuation system for a shape-variable trailing edge. | ||||
| 17:30 | 18:00 | 17.3.3 |
PRELIMINARY ANALYSIS OF TEMPERATURE EFFECTS AND MANEUVER-INDUCED DEFORMATIONS ON FBG OPTIC FIBER INTEGRATED SYSTEMS A. Aimasso¹, M. Bertone¹, C. Ferro¹, M.D.L. Dalla Vedova¹, P. Maggiore¹; ¹Politecnico di Torino, Italy The work is about a FBG sensors network onboard an UAV. It collects local temperature and maneuver-induced deformations to provide health status information. The tests were conducted from on ground analysis to flight. Thanks to data collected, the proposed system presents a promising approach to provide an alternative data source, thereby enhancing the reliability of current navigation systems. | ||||
| 18:00 | 18:30 | 17.3.4 |
NUMERICAL METHOD FOR DESIGNING AND MODELING AN EXHAUST CLUSTER FOR A SMALL TURBOJET ENGINE TEST CELL T.-G. Nguyen¹, Q.-H. Nghiem¹, P.-M. Nguyen¹; ¹Viettel Aerospace Institute, Vietnam This paper describes the process of designing, modeling, and simulating a jet engine test cell’s exhaust cluster including an augmentor tube, a blast bucket, a deflector cone, and a square-cross-section exhaust stack. This system is intended for testing a small and uncooled turbojet engine at sea level condition with exhausted gas temperature (EGT) of around 700°C. The studying method used in this research is Computational Fluid Dynamics (CFD). The design target is to dilute the engine’s hot exhaust gas by induced air via an augmentor tube to the extent that allows installation of supervising camera at the nose of a deflector cone i.e. 150 oC. After that, a deflector cone and a blast basket are used to divert and decelerate the direction of now-cooled exhaust gas into an exhaust stack. By introduction of a dump region design between a deflector cone and a blast bucket, it is discovered to address the shortcomings of published systems so that the high velocity jets are no longer blown against an exhaust stack’s end wall. This design feature promotes mixing between high and low velocity jets inside an exhaust stack, exploiting better exhaust stack’s space to offer more slowed down, more uniform flow field before discharging to ambient environment. | ||||
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| 10:00 | 10:30 | 1.4.1 |
FUEL CELL BASED POWERTRAINS J. Ludvik, Honeywell, United States Fuel Cell (FC) is a promising technology for decarbonization of CS23 and smaller CS25 aircrafts. FCs bring significant benefits: high efficiency, low noise, no NOx or PM emissions. FCs also come with challenges - complexity, novelty, weight. The presentation will outline the progres and future of transition from traditional turbines to FCs in aerospace. | ||||
| 10:30 | 11:00 | 1.4.2 |
CLEAN AVIATION HIGH VOLTAGE NETWORK AND DEMONSTRATION R. Foley, RTX/Collins, United States Invited speaker for the Global Sustainable Aviation track | ||||
| 11:00 | 11:30 | 1.4.3 |
P&W APPROACH TO SUSTAINABILITY J-M Thomassin, Pratt & Whitney Canada, Canada The presentation describes the Pratt&Whitney pragmatic approach to sustainability. Our approach is to first minimize the energy consumption per seat mile. We view electrical components as high power density elements with limited energy and so we use them to optimize the equipment design. We then describe some of the various projects at PW/RTX with a deeper dive into the PWC HEP demonstrator | ||||
| 11:30 | 12:00 | 1.4.4 |
PANEL DISCUSSION: ADDITONAL: SUSAN YING, ERIKA HOLTZ, GABRIELE TEOFILI, DAVID SERCOMBE D. P., Panel Discussion by: Susan Ying, Ampaire Erika Holtz, Harbour Air Ben Loxton, magniX Val Miftakhov, Zero Avío Pratt & Whitney Canada Cedric Justin, GaTech | ||||
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| 10:00 | 10:30 | 2.4.1 |
OBJECTIVES OF THE UNITED STATES FULL SCALE BLENDED WING BODY FLIGHT DEMONSTRATION F. Collier, NASA (LaRC), United States The United States Government has initiated a full-scale flight demonstration of a Blended Wing Body airliner design. This presentation will described the objectives and timeline of the flight demonstration. | ||||
| 10:30 | 11:00 | 2.4.2 |
TECHNICAL APPROACH FOR A BWB AIRLINER TO MEET MARKET DEMANDS M. Page, JetZero, United States This presentation will cover the technical approach for a BWB Airliner to meet market demands | ||||
| 11:00 | 11:30 | 2.4.3 |
TECHNICAL FINDINGS TO DATE TO SUPPORT MARKET DEMANDS OF A BWB AIRLINER M. Page, JetZero, United States This presentation will cover technical findings to date to support market demands of a BWB Airliner | ||||
| 11:30 | 12:00 | 2.4.4 |
GROUND AND SCALED FLIGHT TEST PLANS TO SUPPORT DEVELOPMENT OF A BWB AIRLINER M. Page, JetZero, United States This presentation cover ground and flight test plans to support development of a BWB Airliner | ||||
| 12:00 | 12:30 | 2.4.5 |
PERFORMANCE COMPARISON OF THE BLENDED WING BODY AND TUBE AND WING CONFIGURATIONS J. Ahuja¹, C. Perron¹, R.D.B. Rivera¹, J.C. Tai¹, D.N. Mavris¹; ¹Georgia Tech, United States This presentation will cover detailed system assessments of a BWB airliner with EIS of 2030 | ||||
| Reserve Paper | 2.4.R |
PERFORMANCE COMPARISON OF THE BLENDED WING BODY AND TUBE AND WING CONFIGURATIONS EXTRA J. Tai, Georgia Tech, United States | |||||
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| 10:00 | 10:30 | 3.4.1 |
ROBUST SCHUR-COMPLEMENT SOLVERS AND LARGE-SCALE MULTIDISCIPLINARY DESIGN OPTIMIZATION M.A.S. Abdul-Kaiyoom¹, A. Yildirim¹, J.R.R.A. Martins¹; ¹University of Michigan, United States In this work, we use the newly developed nonlinear and linear Schur complement solvers, appropriate for multidisciplinary models based on computational fluid dynamics (CFD) to solve these saddle-point problems. When compared to conventional optimizations, the SC solver-based optimization proved to be more cost-effective in the benchmark case we provided. | ||||
| 10:30 | 11:00 | 3.4.2 |
PROCESSES, METHODS AND TOOLS SUPPORTING THE DEVELOPMENT OF AERONAUTICAL SYSTEMS L. Boggero¹, J. Bussemaker¹, G. Donelli¹, F. Torrigiani¹, B. Nagel¹; ¹German Aerospace Center (DLR), Germany New processes, methods and tools are needed to efficiently support the development of new aeronautical systems, from the definition of their stakeholders to their design and optimization, considering their whole life-cycle. This paper presents the processes, methods and tools being developed at the German Aerospace Center, demonstrating how they can effectively support the main activities of a system development process. | ||||
| 11:00 | 11:30 | 3.4.3 |
MDAX : ENHANCEMENTS IN A COLLABORATIVE MDAO WORKFLOW FORMULATION TOOL S. Garg¹, J.H. Bussemaker¹, L. Boggero¹, B. Nagel¹; ¹German Aerospace Center (DLR), Germany Collaborative MDAO Workflow Design Accelerator, MDAx, bridges the gap between competence deployment phase and workflow execution phase with help of XDSMs. Industry feedback driven additions like modelling sub-workflows as components, value-based identification of variables, duplication of tools etc. are presented along with a user-friendly interface. | ||||
| 11:30 | 12:00 | 3.4.4 |
SURROGATE-ASSISTED HIERARCHICAL OPTIMIZATION METHOD FOR VARIABLE SWEEP FLIGHT VEHICLE TRAJECTORY N.-H. Ye¹, T. Long¹, B. Fu, Xi’an Modern Control Technology Research Institute, China; R.-H. Shi, Beijing Institute of Technology Chongqing Innovation Center, China; ¹Beijing Institute of Technology, China As the most crucial procedure, the trajectory design generally determines the morphing flight vehicle performance. To sufficiently improve the flight range, a surrogate-assisted hierarchical optimization method is developed for the variable sweep flight vehicle trajectory, which consists of inner and external optimization processes. | ||||
| 12:00 | 12:30 | 3.4.5 |
RAPID DESIGN OF UNCONVENTIONAL AIRCRAFT USING SOFTWARE TOOLS COUPLED IN OPTIMIZATION LOOP – LESSONS LEARNED T. Goetzendorf-Grabowski¹, A. Kwiek¹, J. Mieloszyk, ?ukasiewicz Research Network – Institute of Aviation, Poland; A. Tarnowski¹; ¹Warsaw University of Technology, Poland The paper presents the experience gained while designing aircraft in unconventional configuration using a methodology based on multidisciplinary optimization. An outline of the method involving the inclusion of dynamic stability analysis at an early design stage is presented. Several examples of aircraft designs with unconventional configurations using self-developed software were shown. | ||||
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| 10:00 | 10:30 | 4.4.1 |
REQUIREMENTS UNCERTAINTY PROPAGATION IN CONCEPTUAL DESIGN USING BAYESIAN NETWORKS A. Spinelli¹, A. Sharma, Centre for Aeronautics, Cranfield University, United Kingdom; T. Kipouros¹; ¹Centre for Propulsion and Thermal Power, Cranfield University, United Kingdom This paper presents the application of a Bayesian Network as a tool for propagating the uncertainty between the aircraft-level design and the component-level design. The framework is applied to an example case in UAV design for payload transport. By querying the model, we demonstrate its ability to capture the casual relationships of the design problem and propagating the effects of design decisions on other parameters. | ||||
| 10:30 | 11:00 | 4.4.2 |
APPLICATION OF SYSML IN THE DEVELOPMENT OF AIRCRAFT CABIN HEALTH MANAGEMENT A. Hechelmann¹, T. Mannchen¹; ¹Baden-Wuerttemberg Cooperative State University (DHBW) Ravensbur, Germany Digitalization unlocks new prospects for aircraft cabin maintenance, which have to be developed under consideration of operational aspects and adherence to safety and security regulations. This paper presents the application of a customized model-based systems engineering (MBSE) approach advancing the development of health management for aircraft cabin systems. | ||||
| 11:00 | 11:30 | 4.4.3 |
AUTOMATION OF ENGINEERING INTEROPERABILITY FOR AIRCRAFT SYSTEM DESIGN F. During¹, R.C. Munjulury¹, R. Hällqvist, System Simulation and Concept Development, Saab Aeronautics, Sweden; ¹FLUMES, Linköping University, Sweden The work showed that an automated framework can estimate the pressure loss coefficient for an internal flow system with good accuracy as well as merge the CAD model with other topological simulation models. By automatically updating the pressure loss coefficients when re-designing a flow system, a simulation can be run whit pre-packaged parameters reducing the risk for errors. | ||||
| 11:30 | 12:00 | 4.4.4 |
AUTOMATIC SYSTEM REQUIREMENTS VERIFICATION FOR THE MBSE-ORIENTED AIRCRAFT DESIGN PROCESS A. Dagna¹, S. Centomo², E. Brusa¹, C. Delprete¹, R. Gentile²; ¹Politecnico di Torino, Italy ;²Leonardo LABS, Leonardo S.p.A., Italy The present work introduces a new approach to robustly write requirements and easily integrate them into physical models which simulate the systems to be designed. The final goal is to provide the designer with a tool-agnostic workflow, enabling an automatised requirements verification process since the very early steps of systems design. | ||||
| 12:00 | 12:30 | 4.4.5 |
AN MBSE ENABLED MDAO APPROACH FOR THE CONCEPTUAL DEVELOPMENT OF COMPLEX SYSTEMS M. Fouda¹, L. Willrodt¹, H. Almeida¹, J. Cortez¹, O. Hussein¹, F. Castaneda¹, H. Dhouib¹, C. Dahik¹, V. Drouet¹, R. Brook¹; ¹Capgemini Engineering, Germany Presenter: Mahmoud Fouda, Capgemini Engineering This paper explores the integration of MBSE and MDAO to enhance the development process of complex aerospace systems. It introduces a novel approach in which the MBSE model is connected to an enabling process model, allowing for the automatic extraction of the MDAO problem specifications. This ensures digital continuity and consistent information flow among stakeholders. The approach improves traceability of requirements changes and their impact on design iterations, demonstrating agility. This method is also applicable to other engineering projects aiming to harmonize MBSE and MDAO. | ||||
| additional information (interactive) | 4.4.R |
A MODEL BASED SYSTEM ENGINEERING APPROACH TOWARDS AIRCRAFT DIGITAL CERTIFICATION C. Mirabella¹, M. Tuccillo¹, P. Della Vecchia¹; ¹Università degli Studi Federico II, Italy | |||||
| additional information (interactive) | 4.4.R |
A SEMANTIC MODEL-BASED SYSTEMS ENGINEERING APPROACH FOR SUPERSONIC BUSINESS JET CONCEPTUAL DESIGN Z. Cui¹, M. Luo¹, J. Lu¹, J. Wang¹; ¹Beihang University, China | |||||
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| 10:00 | 10:30 | 5.4.1 |
BREAKING THE SOUND BARRIER: ACHIEVING QUIET SUPERSONIC FLIGHT OVER LAND P. Coen, United States The time saving benefits of supersonic civil aviation remain one of the great unfulfilled promises of the modern air transportation system. As part of its charter to develop technology that will transform the future of air transportation, NASA participates with the international community to develop solutions that will make supersonic air travel sustainable and available to a broad segment of the population. NASA is leading efforts to overcome one of the most challenging barriers to this vision: supersonic overland flight restrictions put in place to protect the public from exposure to unacceptably loud sonic boom noise. Inspired by a breakthrough in the understanding of airframe design techniques that can reduce the sonic boom to a soft thump, NASA has embarked on the Quesst mission. Quesst will use the X-59 research aircraft as the centerpiece of a multi-year project to collect data on how populations respond to the sonic thump. Quest will provide this data to Committee on Aviation Environmental Protection of the International Civil Aviation Organization to support their efforts to define a standard for acceptable sound levels from supersonic flight. The presentation will review the history of the development of the quiet supersonic design methodology, provide details of the X-59 aircraft and describe the elements of the Quesst mission. Opportunities for international collaboration related to the mission will be presented | ||||
| 10:30 | 11:00 | 5.4.2 |
DUAL-STREAM JET NOISE TEST WITH INTERNAL MIXER DESIGN VARIATIONS FOR LTO NOISE OF SUPERSONIC AIRCRAFT R. Habing¹, M.-J. Van der Meulen¹, M. Huet, ONERA / DAAA, France; R. Jaron, DLR, Germany; F. Petrosino², M. Barbarino², O. Zaporozhets, Institute of Aviation, Poland; ¹NLR, Netherlands ;²CIRA, Italy One of the challenges of designing future commercial supersonic aircraft is accurate prediction and reduction of landing and takeoff (LTO) noise. It is expected that jet noise is a dominant noise source during LTO. In the present study a small-scale acoustic jet noise test has been designed and performed. The model contains a dual-stream nozzle including an external plug and has a modular design to vary nozzle length and internal mixers designs. An acoustic test in an anechoic environment with a sideline microphone array has been performed for a range of nozzle pressure ratios. The effect of mixer and lobes and nozzle length on the jet noise characteristics has been evaluated. | ||||
| 11:00 | 11:30 | 5.4.3 |
THE FUTURE OF CIVIL SUPERSONIC TRANSPORT IN EUROPE: THE SENECA AND MORE&LESS PROJECTS R. Jaron, DLR, Germany; N. Viola, Politecnico di Torino, Italy The request for faster and greener civil aviation is urging the worldwide scientific community and aerospace industry to develop a new generation of supersonic aircraft. To pursue this purpose, SENECA and MORE&LESS, answering to EC call “Towards global environmental regulation of supersonic aviation”, aim to support Europe to shape global environmental regulations for future supersonic aviation. | ||||
| 11:30 | 12:00 | 5.4.4 |
POTENTIAL OF THE RANGE EXTENSION OF SUPERSONIC TRANSPORT Z. Lei, SUWA UNIVERSITY OF SCIENCE, Japan The supersonic transport consumes a large amount of fuel in supersonic cruise, which accounts for about 50% of their takeoff weight. In order to increase the range, the supersonic transport commonly becomes larger, thus results in higher manufacturing costs and fuel consumption. The objective of this study is to investigate the range extension by adopting transonic cruise of flight segments in addition to supersonic cruise within the allowable cruising time. The effects of the combination of supersonic and transonic cruise on the range extension and cruising time were estimated using flight theories. Based on the results, the advantages in flight performance and operational economy were discussed. Even if transonic cruising is adopted in a part region, the left supersonic cruising have still significantly shortened flight time as compared to the competing subsonic transport. The time savings and lower fares make supersonic transports highly competitive. This is of great interest to airlines, and could open up a new market for business class passengers. | ||||
| 12:00 | 12:30 | 5.4.5 |
ESATTO: THE HOLISTIC FRAMEWORK TO SUPPORT THE DESIGN OF SUSTAINABLE SUPERSONIC AVIATION R. Fusaro¹, G. Piccirillo¹, D. Ferretto¹, G. Saccone, Italian Aerospace Research Center, Italy; D. Bodmer², J. Jäschke², M. Cremaschi, ENVISA, Italy; N. Viola¹; ¹Politecnico di Torino, Italy ;²Hamburg University of Technology, Germany This paper aims to summarise the status of the development of the ESATTO Framework, an integrated multi-disciplinary framework developed in the framework of the H2020 MORE&LESS project. ESATTO combines validated and accepted tools to holistically assess the environmental impact of supersonic airplanes on the future global air navigation system. | ||||
| Reserve Paper | 5.4.R |
AERODYNAMIC DESIGN OF A SUPERSONIC TRANSPORT CONFIGURATION CONSIDERING AVERAGE LOUDNESS IN THE WHOLE BOOM CARPET Q. Chen¹, Z.-H. Han¹, J.-L. Qiao¹, Y.-L. Ding¹, K.-S. Zhang¹, W.-P. Song¹; ¹Northwestern Polytechnical University, China Presenter: Qing Chen, Northwestern Polytechnical University | |||||
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| 10:00 | 10:30 | 6.4.1 |
TRANSITION MODELING IN SUPPORT OF CFD VISION 2030 - HIGHLIGHTS OF RECENT EFFORTS AT THE NASA LANGLEY RESEARCH CENTER M. Choudhari¹, E. Beyak¹, N. Hildebrand¹, F. Li¹, E. Vogel¹, P. Paredes, National Institute of Aerospace, United States; V. Srivastava², B. Venkatachari²; ¹NASA Langley Research Center, United States ;²Analytical Mechanics Associates, United States According to CFD Vision 2030, the most critical area in CFD simulation capability that will remain a pacing item is the ability to adequately predict viscous turbulent flows with possible transition and flow separation. Established methodology for transition prediction correlates the onset of transition with the linear amplification of instability waves, but automated calculations of the amplification factors pose a major challenge for routine CFD analyses, especially in the presence of strong viscous-inviscid interaction. The more recent approach based on the recasting of empirical transition correlations in the form of auxiliary transport equations is computationally robust, but cannot be easily generalized to capture the physical complexity of the transition process across the speed regime. This paper provides an overview of the recent advancements in CFD-integrated transition modeling at the NASA Langley Research Center. The dual-pronged strategy is aimed at simultaneous improvements in the robustness of automated stability computations coupled with RANS flow solvers along with the accuracy and the physical basis of transport-equations-based transition models. The paper outlines the lessons learned from the implementation and assessment of both approaches in NASA flow solvers, including their assessment in the context of various canonical configurations, encompassing both 2D and 3D boundary layers with a variety of pressure gradients, edge Mach numbers, and multiple instability mechanisms that may lead to transition either in isolation and/or in concert with one another. Furthermore, the development of machine-learning-based stability models as an effective surrogate for the direct computation of instability characteristics will be outlined. Several shortcomings of popular transport-equations-based transition models have also been identified in the course of this work. These include the lack of adequate physics to capture the cumulative history of disturbance | ||||
| 10:30 | 11:00 | 6.4.2 |
EVALUATION OF CFD TRANSITION MODELING FOR TRANSONIC, NATURAL-LAMINAR-FLOW DESIGN J.G. Coder, Pennsylvania State University, United States The predictive capability of leading CFD-based laminar-turbulent transition models will be evaluated in the context of aerodynamic design in the transonic regime. The absolute location of boundary-layer transition will be validated against experimental data, as weill the ability of leading tools to capture the design-limiting movement of the upper-surface transition location. | ||||
| 11:00 | 11:30 | 6.4.3 |
ON THE CHOICE OF TURBULENCE MODEL FOR THE SIMULATION OF AIRFOILS AT REYNOLDS NUMBER BELOW 200,000 S. Shahjahan¹, B. Emmerson¹, D. Verstraete¹; ¹The University of Sydney, Australia CFD is increasingly used in the design and optimisation of wings of small UAVs. Airfoils of these small vehicles operate at Reynolds numbers where laminar-turbulent transition has a pronounced effect on performance. This paper presents a validation of four transition models using a steady RANS solver for three different airfoils at Reynolds numbers between 60,000 and 200,000. | ||||
| 11:30 | 12:00 | 6.4.4 |
FLUIDODYNAMIC ANALYSIS OF LOW REYNOLDS NUMBER FLOWS N. Verde, Italy; F. Capoluongo, Italy; P. Catalano, CIRA, Italy; G. Pezzella, University of Campania , Italy; A. Viviani, University of Campania, Italy Presenter: Giuseppe Pezzella, Department of Engineering, University of Campania \"L. Vanvit This work deals with the fluid dynamic analysis of subsonic, viscous flows characterized by low Reynolds numbers over various wing sections, utilizing advanced Computational Fluid Dynamics tools, including ANSYS-FLUENT, SU2, and XFoil tools. The primary goal extends beyond a mere exploration of flow characteristics; it aims to undertake a comprehensive investigation into the complex phenomenon of separation and the intricate formation of laminar bubbles. The research delves into the intricate dynamics of airflow around wing surfaces, seeking not only to characterize the separation patterns and laminar boundary layers but also to unravel the underlying mechanisms governing these phenomena. By scrutinizing the interplay of aerodynamic forces and boundary layer dynamics, the study endeavors to contribute valuable insights that can inform design considerations for enhanced performance under conditions of low Reynolds numbers. This holistic approach underscores the importance of a detailed understanding of fluid dynamics in optimizing the aerodynamic efficiency of wing profiles, particularly in the challenging regime of low Reynolds numbers. | ||||
| 12:00 | 12:30 | 6.4.5 |
BOUNDARY-LAYER SUCTION AND AERODYNAMIC SHAPE OPTIMIZATION FOR HYBRID LAMINAR FLOW CONTROL ON A FIN H. Wu¹, W. Song¹, H. Nie¹, Z. Han¹; ¹National Key Laboratory of Aircraft Configuration Design, China Aerodynamic drag reduction is conducive to improving the economy and environmental friendliness of transport aircrafts, and is of great significance to achieving green aviation. Application of hybrid laminar flow control (HLFC) system on fins has been proved of great potentials in drag reduction. To achieve drag reduction, the HLFC system has to attenuate the Tollimien-Schlichting (TS) and crossflow (CF) instabilities inside the boundary layers and delay flow transition, which requires coupled design of suction parameters and aerodynamic shape. For this purpose, a surrogate-based optimization framework is utilized toward the boundary-layer suction and airfoil shapes on a vertical fin. The optimization toolbox is an in-house software SurroOpt. The aerodynamic characteristics of the fin under HLFC are also evaluated by an in-house software PMNS3DR with automatic transition prediction by an eN method. Results show that the CF instabilities are mainly suppressed by boundary layer suction, and the TS instabilities are suppressed by a favorable pressure gradient introduced through shape optimization. Compared to the baseline configuration, the optimized vertical fin reaches a larger laminar flow range of approximately 55% over the fin surface, bringing a drag reduction by 41.7%, which indicates the effectiveness of the coupled design optimization method for HLFC. | ||||
| additional information (interactive) | 6.4.R |
BOUNDARY LAYER TRANSITION AND RE-LAMINARIZATION IN MACH 6 NOZZLE OF A SHOCK TUNNEL–A NUMERICAL STUDY S. Malekipour¹, M. Mohammadi-Amin¹, I. Bahman-Jahromi¹; ¹Aerospace Research Institute, Iran Presenter: Shahed Malekipour, ARI | |||||
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| 10:00 | 10:30 | 8.4.1 |
FINITE-STATE AEROELASTIC MODELLING OF MORPHING WING THROUGH UNSTEADY LIFTING-LINE THEORY R. Giansante¹, G. Bernardini¹, M. Gennaretti¹; ¹Roma Tre University, Italy A state-space aeroelastic formulation for the study of morphing wings is presented. It is based on an Unsteady Lifting-Line theory model for the prediction of the aerodynamic loads, which is coupled with a structural dynamics model to obtain a model suitable for aeroelastic stability analysis and aeroservoelastic applications. | ||||
| 10:30 | 11:00 | 8.4.2 |
DECOUPLING STORE AND PARENT AERODYNAMICS FOR FAST PREDICTION OF SUBSONIC STORE TRAJECTORIES N. Mthembu¹, H. Ndlovu¹, B. Ndebele¹, K. Jamison¹, L. Zwane¹; ¹CSIR, South Africa Presenter: Ndumiso Mthembu, CSIR In this paper, we describe a method for calculating trajectories of stores separating from a subsonic aircraft. The method uses a combination of CFD to calculate the flowfield around the subsonic aircraft (excluding the store); Missile DATCOM to estimate the store aerodynamic characteristics; and a panel code to calculate store trajectories. This method was fast in calculating store trajectories. | ||||
| 11:00 | 11:30 | 8.4.3 |
WIND-TUNNEL TESTS OF INNOVATIVE TAILPLANE CONFIGURATIONS F. Nicolosi¹, P. Della Vecchia¹; ¹University of Naples Federico II, Italy The article deals with an experimental wind-tunnel test campaign developed on a scaled model representative of a commercial jet tailplane. The main goal of aerodynamic tests is the test of an innovative tailplane geometry with forward sweep and with the application of a Leading Edge Extension (LEX) as stall control device. Tests have been performed on different geometries with positive and negative (forward) sweep angle. For the negative swept case several LEX with different shapes have been tested. Many visualization with tufts have been performed in order to highlight the tailplane stall path and the effect of LEX as stall control device. Several tests have been also performed with a boundary layer fence. | ||||
| 11:30 | 12:00 | 8.4.4 |
FAST PREDICTION OF PRESSURE DISTRIBUTION FOR 3D CONFIGURATION BASED ON LARGE LANGRAGE MODEL B.W. Shu, Northwestern Polytechnical University, China; Z.H. Gao, China; J.T. Huang, China; X. Chen, China; W. Zhang, China; H. Zhao, China Presenter: Hua Zhao, Northwestern Polytechnical University A deep learning framework based on large langrage model is proposed for predicting pressure distributions for 3D layouts. Based on our framework, the pressure distribution can be obtained in seconds. Our framework is suitable for arbitrary CFD methods and experimental data, and avoids the dependence of neural networks on computational grids | ||||
| 12:00 | 12:30 | 8.4.5 |
RESEARCH ON AERODYNAMIC DESIGN OF ENGINE NACELLE UNDER THE INFLUENCE OF PROPELLER SLIPSTREAM FOR THE TURBOPROP AIRCRAFT R.-F. Xu¹, W.-P. Song¹, X.-H. Li², R.-Z. Qian², Y.-J. Zhang², J.-H. Xu¹, X.-L. Li¹; ¹Northwestern Polytechnical University, China ;²AVIC The First Aircraft Institute, China Presenter: Xin-Long Li, Northwestern Polytechnical University The design and installation angle optimization of the engine nacelle for the civil turboprop aircraft considering the influence of propeller slipstream is completed. A detailed computational evaluation is conducted, and the interference mechanism between the slipstream flow, the nacelle and wing is analyzed.The results show that the lift to drag ratio of the aircraft can be greatly improved by 2%. | ||||
| additional information (interactive) | 8.4.R |
LONG-WAVE INSTABILITY OF AIRCRAFT WAKE VORTEX UNDER SHEAR CROSSWIND Z. Xu¹, D. Li¹, J. Cai¹, J. Han, N, China; ¹Northwestern Polytechnical University School of Aeronautics, China | |||||
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| 10:00 | 10:30 | 9.4.1 |
EUROPEAN RESEARCH COUNCIL (ERC) - FUNDING OPPORTUNITIES AND REPRESENTATIVE PROJECT HIGHLIGHTS G. Symeonidis, European Research Council Executive Agency (ERCEA), Belgium This presentation provides an outline of the funding opportunities offered by the European Research Council (ERC) under the European Commission's Horizon Europe Framework Programme for Research and Innovation, highlighting some representative funded projects/topics in the field of Aeronautics. | ||||
| 10:30 | 11:00 | 9.4.2 |
TOWARDS A FIRST-PRINCIPLE BASED QUANTITATIVE DESCRIPTION OF TURBULENCE WITHOUT THE NEED FOR ADHOC MODELS T.M. Schneider, EPFL, Switzerland Although the Navier-Stokes equations have been known for more than two centuries, our understanding of fluid turbulence remains incomplete. Consequently, we rely on often adhoc turbulence models with many adjustable parameters. I will discuss how non-chaotic time-periodic exact solution of the flow equations may provide a path towards a first-principle based description of fluid turbulence. | ||||
| 11:00 | 11:30 | 9.4.3 |
METAMATERIALS FOR CONTROL OF FLUID FLOWS M. Kotsonis, Delft University of Technology, Netherlands Achieving extensive laminar flow can reduce aircraft drag by up to 15%, offering breakthrough potential for curbing polluting emissions in aviation and other energy-intensive sectors. To achieve this, wave-like flow instabilities growing in laminar boundary layers need to be controlled and attenuated, to delay transition from laminar to turbulent flow. However, their complex, multi-scale, and broadband nature makes these instabilities extremely challenging to control. In this presentation, we outline a new disruptive concept for flow control, first born in classical wave physics: Metamaterials. These are engineered composite structures, invoking dispersive wave phenomena to gain exotic properties that go beyond what is considered possible in Nature. The main such property we explore is the bandgap, a range in which waves are suppressed when interacting with the Metamaterial. The work aims to uncover the complex dynamic behaviour of flow instabilities under dispersive interaction with Metamaterials and will help us understand and fully exploit bandgap mechanisms in transitional flows. Ultimately we aim to create a new class of Metamaterials for flow control and pave the way to ultra-low drag wings for the next generation of emission-free aviation. | ||||
| 11:30 | 12:00 | 9.4.4 |
THERMOACOUSTIC INSTABILITY IN AERO-ENGINE COMBUSTORS A. Morgans, United Kingdom Thermoacoustic instability is caused by a two-way coupling between acoustic waves and flame unsteadiness, and its resulting large amplitude oscillations can cause catastrophic damage. It can occur in the combustors of aero-engines, power gas turbines, rocket engines, domestic boilers etc. The transition to sustainable fuels may result in increased propensity to thermoacoustic instability, with designing it out being a key enabling technology. This talk will present the background and importance of thermoacoustic instability in aero-engine combustors, followed by research progress made through two European Research Council grants on the topic (ERC Starting Grant ACOULOMODE 2013-18 and ERC Consolidator Grant AFIRMATIVE 2018-23). | ||||
| 12:00 | 12:30 | 9.4.5 |
NABUCCO TAKE-OFF: MULTI-STABLE PANELS FOR AN ADAPTIVE WING C. Bisagni, Politecnico di Milano, Italy The project NABUCCO (New Adaptive and BUCkling-driven COmposite aerospace structures), funded by the European Union through an ERC Advanced Grant, aims to design new adaptive buckling-driven composite structures for next generation of aircraft configurations. The results of the first year of the project will be summarized, showing the potential impact for reducing weight and increasing efficiency needed for future clean aviation. | ||||
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| 10:00 | 10:30 | 10.4.1 |
HIGH TEMPERATURE BALLISTIC IMPACT TEST TECHNOLOGY BASED ON ELECTROMAGNETIC LAUNCH C. Zhang¹, J. Liu¹; ¹NORTHWESTERN POLYTECHNICAL UNIVERSITY, China Considering the high temperature when areo-engine is working, it is necessary to carry out the ballistic impact test of the high temperature projectile penetrating target to study the blade containment at high temperature. This paper puts forward a ballistic impact test based on electromagnetic launch. A theoretical model and a scaled test are established to verify the rationality of the method. | ||||
| 10:30 | 11:00 | 10.4.2 |
IMPACT TOLERANCE OF CERAMIC MATRIX COMPOSITES FOR AEROSPACE APPLICATIONS G. Janszen¹, A.M. Caporale¹, L. Cavalli, Petroceramics S.p.A., Italy; M. De Stefano Fumo, CIRA, Italy; A. Airoldi¹; ¹Politecnico di Milano, Italy Ceramic Matrix Composites have been extensively studied for the development of Thermal Protection Systems in aerospace vehicles and have been proved capable of performing structural roles. This make them interesting candidates for the development of elements with structural roles in high-temperature environments. The study exploits their residual strength after barely visible damage after impact. | ||||
| 11:00 | 11:30 | 10.4.3 |
INFLATABLE SPACE SHIELD STRUCTURE FOR SPACE HABITATION MODULE J.-H. Cha, Chosun Uni., South Korea Traditional spacecraft shields face limitations due to payload constraints. Addressing this, an origami shield structure using UHMWPE/hydrogen-rich benzoxazine composite (UHC) is proposed. Hypervelocity impact tests determine the stand-off distance, revealing improved bulletproof and cosmic radiation shielding performance compared to traditional shields. | ||||
| 11:30 | 12:00 | 10.4.4 |
DAMAGE CHARACTERISTICS AND MECHANISM OF CARBON FIBER REINFORCED COMPOSITES IMPACTED BY HIGH-SPEED WATERJETS Y. Li, School of Aeronautics, Northwestern Polytechnical University, China; N. Hou¹, X. Wang¹; ¹School of Civil Aviation, Northwestern Polytechnical University, China Single and multiple waterjet impact erosion tests were performed and damage characterization were characterized on CFRP laminates to investigate their rain erosion performance. The influences of the impact velocity, impact number, impingement direction, waterjet diameter and other critical factors on the damage characteristics were further studied and damage mechanisms were revealed combined with finite element analysis. | ||||
| 12:00 | 12:30 | 10.4.5 |
DAMAGE AND MECHANICAL REPAIR OF COMPOSITE LAMINATES: EFFECTS OF EMBEDDED DEFECTS AND LOW VELOCITY IMPACTS G. Zhang, China; M. Tong, China; B. Yan, China; F. Wang, China; H. Zhang, China Presenter: Guijia Zhang Both numerical simulations and experimental methods were employed to investigate the compressive strength of laminates with pre-embedded defects and under low velocity impact. The CAI of laminates with embedded defects was also examined. Bolted repairs were implemented around the damaged area to investigate the effectiveness in improving compressive strength for both scenarios. | ||||
| Reserve Paper | 10.4.R |
IMPACT RESPONSES AND FAILURE MECHANISMS OF ALMGB14 UNDER DYNAMIC LOADS Y. Lu¹, W. Wang¹, Y. Zhang, Hangzhou Zhiyuan Research Institute, China; Z. Zhang, Northwest Institute of Mechanical and Electrical Engineering, China; ¹Northwestern Polytechnical University, China Presenter: YANYAN LU, School of Aeronautics, Northwestern Polytechnical University | |||||
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| 10:00 | 10:30 | 11.4.1 |
DETECTION OF DELAMINATIONS IN DAMAGED COMPOSITE PLATES VIA LOCAL DAMAGE RESONANCE APPROACH F. Nicassio¹, A.P. Fontanella², M. Cinefra², G. Scarselli¹; ¹University of Salento, Italy ;²Politecnico of Bari, Italy This study investigates the Nonlinear Elastic Wave Spectroscopy (NEWS) via Local Damage Resonance (LDR) effects in the presence of kissing bonds in composite plates. The agreement between analytical/numerical/ results reveals that a monitoring approach combining NEWS and LDR is an extremely efficient and sensitive tool for ensuring integrity and safety of structural composite elements. | ||||
| 10:30 | 11:00 | 11.4.2 |
FREE VIBRATIONS OF CYLINDRICAL SHELLS WITH CUTOUTS BY A SINGLE-DOMAIN RITZ FORMULATION A. Milazzo, University of Palerrmo, Italy; M. Lo Cascio, University of Palermo, Italy A novel single-domain Ritz approach is presented for the free vibration analysis of cylindrical laminated shells with cut-outs. The characteristic matrices of the resolving algebraic system are computed using a special integration technique based on the implicit description of the cut-out via level set function. Validation results and studies show the potential of the method for aerospace applications. | ||||
| 11:00 | 11:30 | 11.4.3 |
LARGE-SCALE STRUCTURAL DYNAMIC TOPOLOGY OPTIMIZATION DESIGN FOR AIRCRAFT VIBRATION REDUCTION UNDER RANDOM EXCITING RESPONSE S. Xiao¹, L.-Y. Liu¹, H.-M. Xue¹, M.-Q. Wang¹, D.-Y. Chen¹; ¹AVIC Shenyang Aircraft Design and Research Institute, China Presenter: Huimin Xue, AVIC Shenyang Aircraft Design and Research Institute The aircraft is faced with complex and uncertain aerodynamic load environment. In this presentation, a large-scale dynamic topology optimization method considering random exciting response is developed to reduce the vibration of aircraft structures. Several numerical examples including an aircraft wall panel demonstrate the effectiveness of the proposed method. | ||||
| 11:30 | 12:00 | 11.4.4 |
ACTIVE CONTROL DAMPING WITH THE USE OF VOICE COIL ACTUATORS G. Cardellino¹, T. Melz¹, R. Feldmann¹, C. Adams, Technical University of Graz, Austria; F. Franco², G. Petrone², S. De Rosa²; ¹Technical University of Darmstadt, Germany ;²Universitä degli Studi di Napoli Federico II, Italy This paper presents a groundbreaking method using voice coil actuators to actively control damping in plates. By dynamically modifying damping, it streamlines experiments in aerospace and other fields, eliminating the need for repeated trials on different plates. This approach is important for the structural dynamics optimization, enhancing efficiency across various industries. | ||||
| 12:00 | 12:30 | 11.4.5 |
ANALYTICAL STUDY ON HYDROSTATIC RESPONSE CHARACTERISTICS DURING WATER LANDINGS OF AMPHIBIOUS AIRCRAFT F. Sun, Xi'an Modern Control Technology Research Institute, China; Y.-H. Zheng¹, S.-S. Zhu¹; ¹Northwestern Polytechnical University, China In this study, the computational fluid dynamics software FLUENT was used to calculate the landing response of the amphibious aircraft on static water, and the variation law of the maximum center of gravity overload, the pressure-time curves of multiple monitoring points at the bottom of the hull and the pitch angle of the amphibious aircraft during the landing process were given. | ||||
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| 10:00 | 10:30 | 12.4.1 |
TOWARDS SUSTAINABLE AVIATION WITH EFFICIENT AIRSPACE OPERATIONS W.J. Coupe¹, S. Saxena¹; ¹NASA Ames Research Center, United States Presenter: William Coupe An overview of the airspace operations research being conducted by the Digital Information Platform (DIP) project and the contribution towards NASA’s Sustainable Flight National Partnership mission will be presented. The paper will share the sustainability benefits achieved by DIP’s pre-departure re-routing tool along with the flight demo plan of gate-to-gate trajectory management service. | ||||
| 10:30 | 11:00 | 12.4.2 |
COMPARING CONVECTIVE WEATHER IMPACTS ON AIR TRAFFIC MANAGEMENT OPERATIONS IN UNITED STATES, CANADA & EUROPE G. Enea¹, T. Reynolds¹, J. Venuti¹, T. Polishchuk², V. Polishchuk², A. Lemetti², A. Lau³, J. Solzer³, T. Bölle³; ¹MIT Lincoln Laboratory, United States ;²Linköping University, Sweden ;³German Aerospace Center (DLR), Germany Best practices and models to evaluate the impact of convective weather on air traffic in Canada, Europe and United States are compared in this paper. The results are used to highlights differences in weather types and mitigations to present lesson learned to benefit the international community. | ||||
| 11:00 | 11:30 | 12.4.3 |
RELATIONSHIPS BETWEEN AIRCRAFT ROUTES AND TURBULENCE-RELATED WEATHER DATA Y. Nakamura¹, A. Senoguchi¹; ¹Electronic Navigation Research Institute, Japan Presenter: Yoichi Nakamura, Electronic Navigation Research Institute An accurate prediction of turbulence is hard while turbulence is one of the major safety concerns in aviation. This paper aims to establish the objective indices using EDR (Eddy Dissipation Rate) and turbulence-related weather data. Through the comparison between the data, the availability of the data for the future ATM system including a management of severe weather avoidance route was examined. | ||||
| 11:30 | 12:00 | 12.4.4 |
ROUTE PLANNING FOR VOLCANIC ASH AND RADIOACTIVITY IN-SITU DRONE MEASUREMENTS USING A GENETIC ALGORITHM AND KRIGING K.A. Buchtal¹, A. Lau¹, D. Ebert², J. Richters², K. Schneiders²; ¹German Aerospace Center (DLR), Institute of Air Transport, Germany ;²German Weather Service (DWD), Radioactivity Monitoring, Germany The project MEASURE pursues the development and testing of a measurement drone system for in-situ measurement of volcanic ash and radioactivity to maintain aviation safety. This study presents a method for route planning for in-situ measurements of volcanic ash and radioactivity using a genetic algorithm and kriging. This method shows high potential in different propagation scenarios. | ||||
| 12:00 | 12:30 | 12.4.5 |
INTEGRATING ECO-EFFICIENT FLIGHT PLANNING IN AIRCRAFT CONCEPTUAL DESIGN: MINIMAL NOX ROUTES FOR HIGH-SPEED AIRCRAFT USING HYDROGEN F. Borgna¹, V. Borio¹, R. Fusaro¹, N. Viola¹, G. Saccone, Italian Aerospace Research Centre (CIRA), Italy; ¹Politecnico di Torino, Italy This paper reviews strategies for assessing the environmental impact of NOx emissions based on the spatial location of the emission points and investigates route optimization in eco-friendly flight planning. A specialized algorithm is proposed for high-speed hydrogen-fueled aircraft, resulting in the formulation of a route characterized by minimal environmental impact in terms of NOx emissions. | ||||
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| 10:00 | 10:30 | 13.4.1 |
ON THE WATER ENHANCED TURBOFAN CONCEPT: PART B – FLOW PATH AND MASS ASSESSMENT J. Häßy¹, A. Görtz¹, M. Schmelcher¹, J. Schmeink¹, M. El-Soueidan¹; ¹DLR, Germany The Water-Enhanced Turbofan is a promising concept for reducing the climate impact of aviation in terms of CO2 and Non-CO2 effects. However, one challenge is the size and mass of the propulsion system in terms of installation and fuel burn penalties. This work deals with the estimation of the flow path and mass on conceptual level and comapres it to a conventional turbofan architecture. | ||||
| 10:30 | 11:00 | 13.4.2 |
DESIGN AND ANALYSIS OF A SCALED COMPOSITE UHBR FAN BLADE FOR WIND TUNNEL TESTS B.A.T. Noordman¹, W.J. Vankan¹; ¹Royal Netherlands Aerospace Centre, Netherlands Future aircraft have to comply with strict environmental targets like reductions in CO2, NOx and noise emissions. Ultra-High Bypass Ratio (UHBR) turbofan engines with large fan diameters are promising in terms of reduction of fuel consumption and emissions. To investigate the challenging integration of such an UHBR engine in the airframe, an experimental scaled turbofan model is being developed to perform a wind tunnel test campaign. For the fan stage of this turbofan model composite fan blades are designed that shall resist the high centrifugal and aerodynamic loads for different flight conditions. For the design and analyses of the composite fan blade, a detailed finite element method (FEM) modelling approach is developed taking into account accurately the 3D blade geometry including blade foot, composite material properties, fibre directions and composite layup of the blade design. This detailed FEM modelling approach is validated with test results of geometrically simplified composite test elements. Blade hot-to-cold analyses are applied to the Aerodynamic Design Point (ADP-S1) flight condition to retrieve the blades’ cold shape that will be manufactured. With the cold shape of the blade design the hot shapes are calculated for different flight conditions and blade twist angles and blade tip radial displacements are checked. Campbell diagrams for the blade design are generated for the first 3 eigenmodes to assess the blade’s vibrational behaviour under operational conditions. The first three blade eigenfrequencies at zero rotational speed were compared with test blade tap test results, which agreed quite well. | ||||
| 11:00 | 11:30 | 13.4.3 |
ON THE WATER ENHANCED TURBOFAN CONCEPT: PART A - THERMODYNAMICS AND OVERALL ENGINE DESIGN A. Görtz¹, J. Häßy¹, M. Nickl², A. Lessis², M. Schmelcher¹, M. El-Soueidan¹; ¹German Aerospace Center, Germany ;²Bauhaus Luftfahrt e.V., Germany Aviation is responsible for a growing portion of global greenhouse gas emissions contributing to climate change. The Water-Enhanced Turbofan (WET) is a promising concept for reducing the climate impact of aviation in terms of CO2 and Non-CO2 effects. The innovative thermodynamic cycle with a quasi-closed water circuit increases overall efficiency and reduces emissions. However, the Water Enhanced Turbofan offers a new range of design parameters for the propulsion system. The influence of important cycle parameters such as temperature, pressure and water to air ratio is assessed in this work. Furthermore, the impact of varying these parameters on the WET specific components is discussed. Finally, the influence of these changes is evaluated not only at engine level, but also on overall mission fuel burn. | ||||
| 11:30 | 12:00 | 13.4.4 |
UNSTEADY AERODYNAMICS OF A COUPLED COMPACT INTAKE-FAN IN CROSSWIND L. Lobuono¹, D. MacManus¹, R. Christie¹, L. Boscagli¹; ¹Cranfield University, United Kingdom This paper analyses the unsteady intake-fan interactions under crosswind conditions. The effect of unsteady crosswind speed is analysed together with the intake ground plane interaction and coupling between the intake and fan. The overall aim of the research is to identify the flow coherent structures and the unsteady mechanisms involved in the separation. | ||||
| 12:00 | 12:30 | 13.4.5 |
KNOWLEDGE-BASED TURBINE DISK MODELING – A CONCEPTUAL DESIGN PROCESS CALIBRATED TO THE NASA ENERGY EFFICIENT ENGINE P. Wehrel¹, J. Schmeink¹, J. Häßy¹; ¹German Aerospace Center (DLR), Germany Rotating disks are essential components of every turbomachinery. Since the disks account for a significant portion of the total engine weight, turbomachinery disk design is crucial and has to be already considered in the early phase of conceptual design, which is a highly challenging task due to many uncertainties. Especially the tradeoff between disk mass and life time is a critical aspect that has to be handled carefully. In order to facilitate this task for engineers, this paper provides calibrated design parameters for turbine disks which are derived from the NASA Energy Efficient Engine (E3). Performance and geometry models are generated for the high- and low-pressure turbine of the NASA E3 and a conceptual disk design process is calibrated based on these models. The design process itself follows the methodology of knowledge-based geometry and mass estimation. Important results are the generation of suitable reference geometries as well as the determination and quantification of dimensionless parameter sets for disk parametrization. Moreover, blade and disk masses are calculated and a conceptual disk stress analysis is performed in order to provide knowledge-based safety factors. | ||||
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| 10:00 | 10:30 | 14.4.1 |
STUDY OF HYBRIDISATION SCENARIOS FOR TURBOPROP AIRCRAFT IN THE GENERAL AVIATION SEGMENT F. Lutz¹, J. Jézégou¹, M. Budinger², A. Reysset²; ¹ISAE-SUPAERO, France ;²INSA Toulouse, France This paper explores the feasibility of the hybridisation of turboprop aircraft in the General Aviation segment. Because of the long lifetime of CO2 in the atmoshpere, designs using current electric technologies are investigated to assess the reductions in terms of cumulated emissions. Two aircraft and their most common routes are studied to obtain commercially realistic hybridised versions. | ||||
| 10:30 | 11:00 | 14.4.2 |
INSTRUMENTATION OF A SUBESCALE GROUND EFFECT VEHICLE, VOLITAN, TO MEASURE FLIGHT PROPULSION EFFICIENCY C. Fischer, 1Instituto Federal de São Paulo and Aeronautics Institute of Tec, Germany; M.A.R. Diaz¹, L. Souza¹, R.G.A. da Silva¹, L.C.S. Goes¹; ¹Aeronautics Institute of Technology, Brazil Recent advances in electronics and programming have stimulated science and industry to explore aviation projects. These include the ground-effect vehicles for energy-efficient flight near water surfaces. Brazilian startup Aeroriver is developing the Volitan for transportation on the Amazon. In this work, the instrumentation for data acquisition during measurements and flight tests is presented | ||||
| 11:00 | 11:30 | 14.4.3 |
A SENSITIVITY ANALYSIS ON THE ENDURANCE EQUATION FOR HYBRID-ELECTRIC AIRCRAFT A. Batra¹, R. Raute, Dept. Ind. Elec. Eng. University of Malta, Malta; R. Camilleri¹; ¹INSTITUTE OF AEROSPACE TECHNOLOGIES (IAT), UNIVERSITY OF MALTA, Malta Paper carries out sensitivity analysis on the proposed hybrid-electric endurance equation showing effects of coefficient of lift & drag, payload & empty weight, planform area, battery energy density, degree of hybridization, etc on endurance. Effects of these parameters are investigated as some values would improve in the future hence showing feasibility for operating a hybrid electric aircraft. | ||||
| 11:30 | 12:00 | 14.4.4 |
DESIGN APPROACH FOR HYBRID ELECTRIC PROPULSION CONCEPTS OF MID-RANGE AIRCRAFT INCLUDING SUSTAINABLE AVIATION FUELS K. Ziaja¹, D. Lieder², J. Göing², J. Friedrichs², F. di Mare¹; ¹Ruhr University Bochum, Germany ;²Technische Universität Braunschweig, Germany The aviation industry faces an urgent need to address the environmental impact of air traffic. This is underlined by the Flightpath 2050 agenda of policymakers and the aerospace industry, which has the ambitious goals of reducing CO2 emissions by 75 %, NOx emissions by 90 %, and noise emissions by 65% until 2050 compared to typical capabilities of new aircraft in 2000. Various technologies are promising solutions to tackle these goals; for example, efficient propulsion concepts, such as Distributed Hybrid Electric Propulsion (DHEP), allow the reduction or even elimination of pollutant emissions through full-electrical operation at ground levels (< 900 m). Another promising option is the use of Sustainable Aviation Fuel (SAF) to reduce chemical emissions directly at the source. This paper introduces a design approach for powertrains of mid-range aircraft based on the 0D in-house tool ASTOR for the thermodynamic cycle performance calculation of gas turbines. It has been adapted for on-design calculations and extended by a new combustion chamber model to enable the determination of combustion emissions of SAFs by using the tool EBSILON®Professional. The SAF models, based on a comprehensive review of existing SAF surrogate models, are implemented by an efficient tabulation method. The powertrain model represents a two-spool gas turbine unit consisting of compressors and turbines for the low- and high-pressure spool side, as well as the combustion chamber. Appropriate boundary conditions are applied to consider a propeller-based DHEP concepts. Subsequently, a Design of Experiments-based (DoE) design process is performed, which covers conventional Jet-A1 and chosen SAF fuels. The DoE results provide insights into power-specific fuel consumption (PSFC), the thermal efficiency and chemical emission composition (pollutant concentrations), offering a database enabling new assessments of air pollution at ground level or airports, respectively. | ||||
| 12:00 | 12:30 | 14.4.5 |
HYDROGEN-POWERED SOLID OXIDE FUEL CELL - GAS TURBINE SYSTEM FOR AERONAUTICAL APPLICATION D. Kierbel¹, T. Neuland¹, P.-E. Roux¹, P. Nehter¹, J. Hollmann², C.N. Dagli², P. Köhler², S. Kabelac², A.G. Rao³, F. de Domenico³, M. Hoogreef³, L. Van Biert³, F. Yin³, C. Rossignol*, L. Dessemond*, M.C. Steil*, P. Maasº, F. Winterº, C. Warschº, S.S. Ventura, German Aerospace Center, Germany; ¹AIRBUS SAS, Germany ;²Leibniz University Hannover, Germany ;³Technische Universiteit Delft, Netherlands ;*Univ. Grenoble Alpes, Univ. Savoie Mont Blanc, France ;ºBauhaus Luftfahrt e.V., Germany Presenter: Pascal Köhler, Leibniz University of Hanover, Germany HYLENA will investigate, develop and optimize an innovative, highly efficient, hydrogen powered electrical aircraft propulsion concept. This is based on the integration and combination of Solid Oxide Fuel Cells (SOFC) with turbomachinery in order to use both the electric and thermal energy for maximization of propulsive efficiency. This game-changing engine will exploit the synergistic use of: a) an electrical motor: the main driver for propulsion, b) hydrogen fueled SOFC stacks: geometrically optimized for nacelle integration, c) a gas turbine: to thermodynamically integrate the SOFC. This concept will achieve significant climate impact reduction by being completely carbon neutral with radical increase of overall efficiency for short and medium range aircrafts. The HYLENA methodology covers on: - SOFC cell level: experimental investigations on new high-power density cell technologies - SOFC stack level: studies and tests to determine the most light-weight and manufacturable way of stack integration - Thermodynamic level: engine cycle simulations of novel HYLENA concept architectures - Engine design level: exploration, through resilient calculation and simulation, of the best engine design, sizing and overall components integration - Overall engine efficiency level: demonstration that HYLENA concept can reach an outstanding efficiency increase compared to state-of-the-art turbofan engines - Demonstration level: a decision dossier for a potential ground test demonstrator to prove that the concept works in practice during a second phase of the project The HYLENA consortium consists of one aircraft manufacturer (Airbus), 3 universities and 2 research institutes covering the expertise in aircraft design, propulsion system design, SOFC technology, hydrogen combustion and climate impact assessment. This project is fully complementary to Clean-Aviation to investigate a low level TRL concept and bring it to TRL3 in 42 months prior to a demonstrator in phase 2. | ||||
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| 10:00 | 10:30 | 15.4.1 |
REDESIGN OF AN AERONAUTICAL COMPOSITE STIFFENED PANEL WITH THE DOUBLE-DOUBLE DESIGN APPROACH A. Riccio¹, A. Garofano¹, G. Rigliaco¹, M. Boccaccio², F. Acerra²; ¹University of Campania “Luigi Vanvitelli”, Italy ;²Leonardo S.p.A., Italy Double-Doubles introduce an alternative approach to design composite laminate structures with a proper and effective optimization in terms of laminate thickness and plies orientation. A Double-Double design for a composite stiffened panel has been proposed and optimized to meet the material strength requirements, resulting in a total mass reduction up to 26.48% as compared to the starting design. | ||||
| 10:30 | 11:00 | 15.4.2 |
MACRO, MESO AND MICRO SCALE ENERGY EVALUATION IN LAMINATED AND COMPOSITE STRUCTURES USING THE COMPONENT-WISE APPROACH S. Saputo¹, R. Augello¹, E. Carrera, Germany; ¹Department of Aeronautics and Aerospace Engineering, Politecnico, Italy The aim of this investigation is to exhaustively evaluate the strain energy assimilated within a structural system, and establish a correlation between the energy absorption and the structural integrity employing the Carrera Unified Formulation (CUF). The correlation assumes a predominant significance in predicting probable modes of failure. The methodology allows to evaluate the strain energy distribution at the individual component level, which plays a pivotal role in identifying specific regions within the structure that gather elevated levels of strain energy. | ||||
| 11:00 | 11:30 | 15.4.3 |
ELECTROMAGNETIC INDUCTION HEATING OF TP-CFRP LAMINATES: FEM MODELLING AND VALIDATION W.J. Vankan¹, N. van Hoorn¹, A.J. de Wit¹, T.P.A. Koenis¹; ¹NLR, Netherlands The use of advanced 3D finite element modelling is essential for the prediction and understanding of complex local electromagnetic inductive heating phenomena in composite laminates. Such EM simulations can support induction welding processes that can be used in the innovative manufacturing and assembly of thermoplastic carbon composite components. | ||||
| 11:30 | 12:00 | 15.4.4 |
ON AN EFFICIENT GLOBAL/LOCAL STOCHASTIC METHODOLOGY FOR FAILURE PREDICTION OF AIRCRAFT COMPOSITE STRUCTURES P. Minigher, INEGI / University of Porto / University of Girona, Italy; A. Arteiro¹, A. Turon, University of Girona, Spain; J. Fatemi, Airbus NL, Netherlands; S. Guinard, Airbus SAS, France; L. Barrière, Saint Exupéry, France; P.P. Camanho¹; ¹INEGI / University of Porto, Portugal An efficient global/local approach to estimate the uncertainties in specific regions of interest with limited computational effort is proposed. This is achieved by refining only locally the model taking advantage of Refined Structural Theories. The stochastic analysis is dealt with a sensitivity study carried out both in the global and in the local model. | ||||
| 12:00 | 12:30 | 15.4.5 |
FATIGUE CRACK LIFE PREDICTION BASED ON BAYESIAN DYNAMIC UPDATE Y. Zhang, China; Y. Ning, China; B. Wang, China; H. Peng, China Damage monitoring data obtained from sensors are used to construct crack propagation model considering uncertainty by Bayesian dynamic updating method, and the uncertainty is considered by randomizing the relevant parameters of crack growth model. The distribution of crack growth life is obtained by using the distributed parameter sampling and replacing the crack growth model. The prediction provides a higher accuracy than traditional model. | ||||
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| 10:00 | 10:30 | 16.4.1 |
THE JOURNEY TOWARDS CONDITION-BASED MAINTENANCE: A FRAMEWORK FOR THE HORIZONTAL TAIL ACTUATOR OF AN ADVANCED JET TRAINER AIRCRAFT L. Baldo¹, A. De Martin¹, M. Terner, Leonardo S.p.A. Aircraft Division, Italy; M. Sorli¹; ¹DIMEAS, Politecnico di Torino, Italy In this paper, the first steps towards a comprehensive CBM framework for the horizontal tail (HT) actuator of an Advanced Jet Trainer Aircraft are presented. After a thorough analysis of design documents and operational procedures, the most significant data have been identified, leading to the identification of possible PHM strategies for the specific sub-system. The paper will cover the preliminary framework in which the system will be developed. | ||||
| 10:30 | 11:00 | 16.4.2 |
HOLISTIC AND SCALABLE SMART OPTIMIZATION FRAMEWORK FOR PRESCRIPTIVE MAINTENANCE A. Giacotto¹, A.C. Pereira Mesquita¹, H. Costa Marques¹, A. Martinetti, University of Twente, Netherlands; ¹ITA, Brazil This paper presents a Prescriptive Maintenance framework, using IoT and analytics to revolutionize maintenance in complex systems. It overcomes traditional methods' limitations, handling diverse data and uncertainties, and steering systems towards optimal solutions. Uniquely, it extends this framework from aviation to healthcare, illustrating its industry-wide applicability and versatility. | ||||
| 11:00 | 11:30 | 16.4.3 |
HYDROGEN TANKERING: TOOLS FOR ECONOMIC AND ENVIRONMENTAL IMPACT SCENARIO STUDIES G. Sirtori¹, L. Trainelli¹, Z. Lahmam¹; ¹DAER, Politecnico di Milano, Italy Hydrogen-powered aircraft operations will be constrained by the lack of H2 refueling infrastructures across airports. Tankering could enable flights to fields that have no H2 infrastrucutre. The proposed methodology assessed the impact on extra fuel consumption, costs and network coverage, considering aircraft performance and H2 distribution, to eventually modify the aircraft design range. | ||||
| 11:30 | 12:00 | 16.4.4 |
AN EMPIRICAL AND CUSTOMISABLE FLEET RENEWAL MODEL FOR PROSPECTIVE SCENARIOS USING OPEN-ACCESS DATA P. Viry¹, T. Planès¹, S. Delbecq¹, L. Joly, ISAE-SUPAERO, Université de Toulouse, France; A. Salgas¹; ¹Fédération ENAC ISAE-SUPAERO ONERA, Université de Toulouse, France Air transport decarbonisation requires rapid and radical action to be taken. These include reducing operations inefficiency, switching to alternative low-carbon energies and accelerating aircraft efficiency improvement. The latter results from improvements at the aircraft level but also from the renewal of the current fleet by the most recent aircraft types. This paper presents an updated and more accurate fleet renewal model to assess these effects in a prospective scenarios simulator, AeroMAPS. To do so, a fleet database is used alongside an aircraft operating cost model to train the updated fleet model so that it captures the logic behind the renewal decisions of airlines. The model is evaluated and used on an illustrative European network to test the effect of different policies (carbon taxes, blending mandates) on the fleet composition and subsequent CO2 emissions. | ||||
| 12:00 | 12:30 | 16.4.5 |
A NOVEL DEEP MULTIMODAO INFORMATION FUSION MODEL FOR AERO-ENGINE STATE PREDICTION Yufeng Huang¹, Gang Sun¹, Jun Tao¹, Jinzhang Feng¹; ¹Fudan University, China In this paper, a novel deep multimodal information fusion method is proposed, which integrates information from the physical-based model and the data-driven model. Two deep Boltzmann machines are constructed for feature extraction from sensor data and model simulation data, respectively. Whereby the joint information is mapped into a high-dimensional space and forms a joint representation. | ||||
| additional information (interactive) | 16.4.R |
DIGITALISATION AND SUSTAINABILITY IN CABIN DESIGN: SYNERGIES AND DEPENDENCIES M.C. Berschik¹, S. Wehrend¹, F.N. Laukotka¹, D. Krause¹; ¹Hamburg University of Technology, Germany | |||||
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| 10:00 | 10:30 | 17.4.1 |
RESEARCH ON FATIGUE LIFE OF HEAT EXCHANGER BASED ON STRESS SIMULATION L. Hu¹, Y. -L. Han, Nanjing University of Aeronautics and Astronautics, China; F. Meng¹; ¹Nanjing Engineering Institute of Aircraft Systems, China Presenter: Liang Hu, Nanjing Engineering Institute of Aircraft Systems Finite element static analysis and computation have been carried out for some heat exchanger, strain testing has been made to confirm its risky area. Fatigue life has been calculated based on Miner Theory and S-N curves under constant amplitude loading in order to provide the feasible solution to engineering application. | ||||
| 10:30 | 11:00 | 17.4.2 |
HYDROGEN SAFETY: A COMPARATIVE ANALYSIS OF LEAK DETECTION SENSORS O. Petrella¹, A. Martucci¹, P. Caruso¹, L. Travascio¹, A. Vozella¹; ¹CIRA, Italy Presenter: Pasquale Caruso, CIRA Current research worldwide is investigating potentialities, limitations and constraints due to the usage of hydrogen as a energy source. A thorough investigation is needed specially to mitigate risks to the environment and human health related to hydrogen usage. Indeed, hydrogen can be the cause behind various accidents leading to different risk scenarios, due to potential physical and chemical phenomena depending on specific environmental conditions. Some of the main risks can be: asphyxiation, freezing, shock waves from explosions, thermal risks from flame releases and combustion. However, these risks can be reduced by adopting specific mitigations and safety measures which can be identified since the design phase. Careful prevention and a detailed risk assessment, combined with an accurate analysis by monitoring sensors are absolutely necessary for the safe use of hydrogen systems. For this purpose, monitoring sensors can support in managing safety issues of systems dealing with hydrogen usage. This work reports on the analysis carried out on the most suitable sensors for the risk mitigation in particular related to hydrogen leakage. Three kinds of sensors have been analyzed and compared, including new generation sensors such as the Surface Plasmonic Resonance (SPR) and the Surface Acoustic Wave (SAW) sensors. In particular the measurement range, the response time and selectivity are compared. Moreover, the uncertainty measurement will be evaluated and compared by means of simulations (MATLAB environment). The lower the measured uncertainty, evaluated by means of the simulations, the better the sensor will be considered. | ||||
| 11:00 | 11:30 | 17.4.3 |
VIBRATION ANAYLYSIS AND INFLUENCING FACTOR STUTY OF HELICOPTER HYDRAULIC PIPELINNE S. Yang¹, S. Huang¹, Y. Wang¹, Y.-P. Huang¹; ¹CHRDI, China Helicopter hydraulic pipeline system is significant for the hydraulic system. In this paper, the law of helicopter hydraulic pipeline vibration response change with the relative parameters(support, fluid flow rate, pipeline wall thickness, etc.) is studied, And based on which, a typical pipeline located in rear rotor effect zone is optimized. | ||||
| 11:30 | 12:00 | 17.4.4 |
SENS4ICE EU PROJECT HYBRID ICE DETECTION ARCHITECTURES DEMONSTRATION RESULTS C.W. Schwarz¹, C. Deiler¹, J. Lucke¹, T. Jurkat-Witschas¹, A. Orazzo², B. Thillays²; ¹DLR, Germany ;²Safran Aerosystems, France The EU project SENS4ICE (GA no 824253) developed/ matured technologies for detection and discrimination of supercooled large droplets (SLD) icing conditions, including a hybrid approach combining direct sensing (atmospheric conditions/ ice accretion) with indirect aircraft performance-based detection. Icing wind tunnel and flight test results confirm successful technology demonstration. | ||||
| 12:00 | 12:30 | 17.4.5 |
FLIGHT TEST RESULTS FOR PERFORMANCE-BASED ICE DETECTION C. Deiler, DLR, Germany The performance-based (indirect) ice detection methodology is based on the changes of airplane flight characteristics under icing influence and key to a hybrid detection approach as core of the EU funded Horizon 2020 project SENS4ICE. The paper provides an overview on them developed indirect ice detection (IID) algorithm together with some exemplary results from the SENS4ICE flight test campaigns. | ||||
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| 14:30 | 14:55 | 1.5.1 |
APPLICATION OF LAMINAR FLOW CONTROL FOR ENHANCED PERFORMANCE AND REDUCED EMISSIONS J. Crouch, Boeing, United States Invited speaker for the Global Sustainable Aviation track | ||||
| 14:55 | 15:20 | 1.5.2 |
HIGH ASPECT RATION WING CONCEPTS P. Schmollgruber, ONERA, France invited speaker for the Global Sustainable Aviation track | ||||
| 15:20 | 15:45 | 1.5.3 |
RIBLETS IN AVIATION- FIRST EVER INDUSTRIALIZATION WITH AEROSHARK J.U. Müller, Lufthansa, Germany The drag-reducing effect of riblets has been known for decades but has never been really used in aviation industry. BASF and Lufthansa Technik (LHT) developed a material that meets all requirements and LHT then obtained a supplemental type certificate (STC) for a large-area wrap on a Boeing 777. The presentation describes the development, certification, roll-out and the further outlook. | ||||
| 15:45 | 16:10 | 1.5.4 |
Q&A - MINI PANEL QA A, Q&A - MINI PANEL | ||||
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| 14:30 | 14:55 | 2.5.1 |
THE NASA X-57 “MAXWELL” DISTRIBUTED ELECTRIC PROPULSION FLIGHT DEMONSTRATOR PROJECT H. Maliska, NASA, United States THE NASA X-57 “MAXWELL” DISTRIBUTED ELECTRIC PROPULSION FLIGHT DEMONSTRATOR PROJECT | ||||
| 14:55 | 15:20 | 2.5.2 |
X-57 TRACTION POWER AND COMMAND SYSTEMS DEVELOPMENT S. Clarke¹, J. Terry¹, K. Harris¹, D. Avanesian¹; ¹NASA, United States X-57 TRACTION POWER AND COMMAND SYSTEMS DEVELOPMENT | ||||
| 15:20 | 15:45 | 2.5.3 |
FLIGHT PERFORMANCE ESTIMATES FOR THE NASA X-57 DISTRIBUTED ELECTRIC PROPULSION FLIGHT DEMONSTRATOR N. Borer, NASA, United States The X-57 flight demonstrator concept featured four configurations starting with a conventional combustion-powered multiengine airplane and ending with a fully electric configuration with two forms of distributed propulsion and a highly modified wing. These configurations, called Mods, were designed to gain incremental insight into different aircraft propulsion configuration options and their impact on the aircraft performance. The gasoline-powered Mod I configuration consumed 2.6 to 2.9 times more stored energy in cruise than the electric but otherwise conventionally configured Mod II configuration. The highly loaded wing of Mod III led to an increase of 40% in the power-off lift-to-drag ratio as compared to Mod II at the project high-speed cruise target speed and altitude. The power-on lift-to-drag ratio of Mod III was 53% higher than Mod II due to the beneficial aero-propulsive interaction of the wingtip-mounted cruise propellers in Mod III. The high-lift propeller system of Mod IV recovered the low-speed performance of the conventional configuration in Mod II that was otherwise lost with the introduction of the highly loaded Mod III wing. The battery-electric configurations also benefitted from a lack of power lapse in the electric motors with increasing air density as compared to the combustion-powered baseline aircraft. | ||||
| 15:45 | 16:10 | 2.5.4 |
DISTRIBUTED THRUST TAKEOFF FOR THE NASA X-57 MOD IV FLIGHT DEMONSTRATOR N.K. Borer¹, R.D. Wallace², J.R. Reynolds², D.E. Cox¹, C. Sales², T.L. Williams², W.M. Ringelberg²; ¹NASA Langley Research Center, United States ;²NASA Armstrong Flight Research Center, United States The Mod IV configuration of the X-57 flight demonstrator concept featured two forms of distributed electric propulsion—one cruise propulsor at each wingtip for primary propulsion that enabled favorable interaction with the wingtip vortex and six high-lift propulsors distributed along the leading edge of each wing to enhance low-speed flight characteristics. The power system that fed these propulsors was arranged in two independent power buses. This unique arrangement did not lend itself to traditional “one engine inoperative” methods for determining performance after a critical failure in the propulsion system. Several failure scenarios were identified as potential “critical loss of thrust” events, and experiments that included pilot-in-the-loop simulation with the project test pilots were conducted to determine if these events would result in inadequate handling qualities or performance. Prior research showed that a total failure of one of the cruise motors during takeoff or initial climb could result in unacceptable performance for a traditional full-power takeoff. A new technique dubbed Distributed Thrust Takeoff (DiTTo) was developed to reduce the impact of the thrust asymmetry and loss of thrust that could occur in any of the critical loss of thrust scenarios. The results showed that adequate performance and handling qualities could be achieved in each of the critical failure scenarios when using the DiTTo technique. | ||||
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| 14:30 | 14:55 | 3.5.1 |
DATA-DRIVEN AERODYNAMIC SHAPE OPTIMIZATION AND MULTI-FIDELITY DESIGN EXPLORATION USING CONDITIONAL DIFFUSION-BASED GEOMETRY SAMPLING METHOD A. Yang¹, J. Zhang, Shanghai Artificial Intelligence Laboratory, China; J. Li, Institute of High Performance Computing, A*STAR, Singapore; R. Liem¹; ¹Hong Kong University of Science and Technology, Hong Kong SAR of China Presenter: Aobo Yang, Hong Kong University of Science and Technology Aerodynamic shape optimization plays a crucial role in designing efficient and high-performance aircraft. However, the computational cost associated with high-dimensional data often poses a challenge in achieving accurate and efficient optimization. In this study, we propose a multifidelity Bayesian Neural Networks (BNNs) framework tailored for high-dimensional data-driven aerodynamic shape optimization. The framework combines data from multiple fidelity sources to enhance estimation accuracy while reducing computational expenses. The BNNs are used to capture the inherent uncertainties in modeling the relationship between low- and high-fidelity data. They also provide quantified uncertainty measures to optimize shape predictions. We employ variational inference and Monte Carlo sampling techniques to train and estimate posterior distributions of the BNNs. The proposed framework is validated using a high-dimensional dataset, showcasing its capability in accurately optimizing aerodynamic shapes while accounting for uncertainty. The results demonstrate liem{substantial} improvements in both optimization accuracy and computational efficiency compared to traditional approaches. This multifidelity BNNs framework has the potential to further enhance the capability of aerodynamic shape optimization in the aerospace industry, especially in tackling higher-dimensional problems. | ||||
| 14:55 | 15:20 | 3.5.2 |
LATENT SPACE CORRELATION FOR INTERPRETABLE AIRFOIL PARAMETERIZATION USING VARIATIONAL AUTOENCODERS K. Swannet¹, C. Varriale¹, N.A.K. Doan¹; ¹Delft University of Technology, Netherlands This study utilizes Variational Autoencoders (VAEs) to enhance airfoil design by improving latent space interpretability of geometric and aerodynamic features. It develops a comprehensive parameterization model, tackling dataset inconsistencies and broadening property extraction, aiming to offer an efficient, user-friendly solution for diverse engineering applications. | ||||
| 15:20 | 15:45 | 3.5.3 |
RESEARCH ON MULTI-ATTRIBUTE DECISION MAKING AND VERIFICATION METHODS FOR SYSTEMS CONFRONTATION Y. Tong¹, M. Luo¹, Z. Cui¹, Z. Liu¹, Z. Ji¹; ¹Beihang University, China In response to the multi-attribute decision-making issues in aircraft design, a method based on system simulation for verification has been proposed. This method starts from the application dimension, providing reference standards for decision outcomes. Applying this method to the decision-making process of hypersonic aircraft design schemes has validated its effectiveness. | ||||
| 15:45 | 16:10 | 3.5.4 |
EXPLORATION OF EFFICIENT HYPERPARAMETERS ADAPTION OF SUPPORT VECTOR REGRESSION FOR AERODYNAMIC DESIGN K.-S. Zhang¹, H.-L. Qiao¹, P.-H. Wang¹, Y.-Q. Du¹, Z.-H. Han¹; ¹School of Aeronautics, Northwestern Polytechnical University, China This work aims to explore the hyperparameters adaption strategy for efficient support vector regression as it critically affects modeling accuracy and computational cost. The objective of hyperparameter adaption is estimated by cross-validation or leave-one-out bound method with smaller computational cost. The hyperparameters are optimized by a global optimization algorithm, such as Genetic Algorithm, Bayesian Optimization or Covariance Matrix Adaptation Evolution Strategy. The different strategies are compared via series of numerical examples and aerodynamic design cases. | ||||
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| 14:30 | 14:55 | 4.5.1 |
DUCTED HEAT EXCHANGER THERMAL AND AERODYNAMIC SHAPE OPTIMIZATION E.J. Adler¹, A.H.R. Lamkin¹, J.R.R.A. Martins¹; ¹University of Michigan, United States Ducted heat exchangers allow electric and fuel cell aircraft to efficiently reject waste heat. We use numerical optimization to automatically shape the duct and design the heat exchanger. The optimizer can exploit the duct and heat exchanger's coupled interaction to discover improvements that human designers may not find manually. | ||||
| 14:55 | 15:20 | 4.5.2 |
ANALYZING THE IMPACTS OF SUSTAINABLE POWERTRAINS FOR SHORT-HAUL COMMUTER AIRLINES F. Salucci¹, N. Prabhakar¹, D. Karbowski¹; ¹Argonne National Laboratory, United States We retrofitted an AVGAS-fueled 9-pax small commuter aircraft with three powertrains: electric, hybrid-electric, fuel cell hybrid-electric. The retrofitted aircraft will be employed to perform routes currently flown with the conventional version of the aircraft. For each fleet, we will estimate the amount of fuel, electric energy to recharge the batteries, and resulting well-to-wake CO2 emissions. | ||||
| 15:20 | 15:45 | 4.5.3 |
LOCAL AIR QUALITY AND NOISE OPTIMIZATION OF A LARGE ASPECT RATIO WINGS WITH DISTRIBUTED HYBRID ELECTRIC PROPULSION R. Cavallaro¹, P. Norczyk Simon¹, A. Cini¹; ¹Universidad Carlos III de Madrid, Spain Electrification of aircraft to improve the Local Air Quality and Noise is in the agenda of the EU policies to achieve the goals of climate neutrality. An integrated approach, levering on synergies between new powertrain (distributed hybrid-electric propulsion) and airframe (large aspect ratio wings) technologies, in conjunction with new operations, is required to improve LAQN. | ||||
| 15:45 | 16:10 | 4.5.4 |
POWER MANAGEMENT SUPPLY OPTIMIZATION FOR HYBRID-ELECTRIC REGIONAL AIRCRAFT G. Palaia¹, K. Abu Salem¹; ¹Polytechnic of Turin, Italy Presenter: Giuseppe Palaia, Polytechnic of Turin This study deals with the optimisation of the power supply of a parallel hybrid electric powertrain. Specifically, the mission profile is discretised to determine the optimal power split to minimise fuel consumption. This approach serves as a precursor to advanced control techniques in hybrid-electric aircraft. | ||||
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| 14:30 | 14:55 | 5.5.1 |
ESTABLISHING THE DLR-F25 AS A RESEARCH BASELINE AIRCRAFT FOR THE SHORT-MEDIUM RANGE MARKET IN 2035 S. Wöhler¹, J. Häßy¹, V. Kriewall, TUHH, Germany; ¹DLR, Germany Aim of this study is to establish a short-medium range research baseline aircraft with a respective technology scenario in 2035 as part of the LuFo project VirEnfREI for the Clean Aviation programme, research programmes such as the German Luftfahrtforschungsprogramm (LuFo) and Horizon Europe, to compare and benchmark disruptive technologies to a meaningful conventional aircraft configuration. | ||||
| 14:55 | 15:20 | 5.5.2 |
BATTERY PERFORMANCE METRICS FOR LARGE ELECTRIC PASSENGER AIRCRAFT R. de Vries¹, R.E. Wolleswinkel¹, D. Rosen Jacobson¹, M. Bonnema², S. Thiede²; ¹Elysian Aircraft, Netherlands ;²University of Twente, Netherlands Recent studies show that large electric aircraft are feasible with significantly more near-term battery technology than previously thought. In this study we assess the battery performance metrics required for such aircraft and compare them to other electric aircraft and EVs, and investigate the battery production volumes required for different scenarios of market penetration of electric aircraft. | ||||
| 15:20 | 15:45 | 5.5.3 |
CONCEPTUAL DESIGN OF A ZERO-EMISSION REGIONAL AIRCRAFT FOR ENHANCED SHORT-HAUL MOBILITY L. Trainelli¹, C.E.D. Riboldi¹, Y.M. Khan¹, F. Salucci, Argonne National Laboratory, United States; G. Sirtori¹; ¹DAER, Politecnico di Milano, Italy Presenter: Lorenzo Trainelli, DAER, Politecnico di Milano This paper discusses the conceptual design to define a design solution for a disruptive air transport vehicle, characterized by a radically new propulsion system guaranteeing zero emissions at aircraft level and by a unique operational mission: a multi-hop commuter for airport feeding and intercity commuting. The paper details the configuration selection and the preliminary sizing of the vehicle. | ||||
| additional information (interactive) | 5.5.R |
DESIGN OF REMOTE-CONTROLLED GROUND BASED AIRCRAFT TUG I. Kopec¹, D. Matyja¹; ¹Polish Air Force University, Poland | |||||
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| 14:30 | 14:55 | 6.5.1 |
DATA-DRIVEN UNSTEADY AERODYNAMIC MODELS FOR AEROELASTIC STABILITY ANALYSES A.C.N. Carloni, Instituto Tecnológico de Aeronáutica, Brazil; J.L.F. Azevedo, Instituto de Aeronáutica e Espaço, Brazil This work is concerned with systematically investigating different data-driven techniques for identifying CFD-based reduced-order models of the unsteady aerodynamics necessary to formulate the aerodynamic operator for transonic aeroelastic stability analyses. Focus is given to the relative merits and costs of the different methods in predicting the flutter onset. | ||||
| 14:55 | 15:20 | 6.5.2 |
NUMERICAL STUDY OF FLOWS OVER LAUNCH VEHICLES WITH VARIOUS FAIRING BY SECOND-MOMENT CLOSURE DETACHED-EDDY SIMULATION Q. Li¹, G. Wang¹, M. Qin¹, L. Xu¹; ¹Northwestern Polytechnical University, China The influence of fairing geometry on hammerhead launch vehicle buffeting is studied by second-moment closure detached-eddy simulation. The low-frequency domain fluctuation load on the vehicle booster can be reduced by decreasing the fairing boat angle. Increasing the fairing cylinder length can reduce the booster's full-frequency fluctuation load and the shock buffeting on the fairing. | ||||
| 15:20 | 15:45 | 6.5.3 |
NUMERICAL ANALYSIS OF GENERALIZED AERODYNAMIC FORCES CONSIDERING LAMINAR-TURBULENT TRANSITION ON A NLF WING C. Sebastia Saez¹, J. Martin Ferres¹, M. Hornung¹; ¹Technical University of Munich, Germany The wing’s dynamic aeroelastic stability analysis, referred to as flutter analysis, typically involves potential- flow-theory-based methods to model unsteady aerodynamics, which do not consider viscous or non-linear effects. Modern sailplane wings with Natural-Laminar-Flow (NLF) airfoils present significant chordwise runs of laminar boundary layer. Assuming an inviscid or completely turbulent flow over the wing chord would result in completely wrong predictions of the unsteady aerodynamic characteristics of the wing and hence an inaccurate prediction of the dynamic aeroelastic behavior. This study presents a coupled FE beam model of a sailplane with a CFD model to calculate the Generalized Aerodynamic Forces (GAF). The influence of transition on the unsteady aerodynamic response of a modern sailplane’s NLF wing is investigated numerically with the Gamma-Transition Model. The GAF are compared to the results obtained with the fully turbulent Spalart-Allmaras (SA) model. | ||||
| 15:45 | 16:10 | 6.5.4 |
LINEAR SYSTEM TECHNIQUES APPLIED TO NONLINEAR AEROSERVOELASTIC ANALYSES M.V. G. Muniz¹, J.A. A. Lyrio, Aeronautics Institute of Technology, Brazil; J.L. F. Azevedo¹; ¹Institute of Aeronautics and Space, Brazil Identification techniques are used to compute aerodynamic transfer functions on a 3 dof airfoil. The aerodynamic response of the aeroelastic system is obtained from the unsteady Euler equations. Radial Basis Functions are used to execute the mesh motion. A LQR controller is designed to delay the flutter boundaries on the aeroservoelastic system using the identified aerodynamic transfer functions. | ||||
| additional information (interactive) | 6.5.R |
SURROGATE MODELING OF VORTEX SHEDDING TURBINE IN LOW REYNOLDS NUMBER J.L. Kurniawan¹, M. Hu¹; ¹Institut Teknologi Bandung, Indonesia | |||||
| additional information (interactive) | 6.5.R |
PREDICTION OF TRANSIENT DEFORMATION BY COUPLING CFD AND FEM ANALYSIS USING MACHINE LEARNING BASED CORRELATION FUNCTION J. Parez¹, P. Kovar¹, T. Vampola¹; ¹Czech Technical University in Prague, Czech Republic Presenter: Jan Pařez, Czech Technical University in Prague | |||||
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| 14:30 | 14:55 | 7.5.1 |
TRAIN ON SYNTHETIC - TEST ON REAL: DOMAIN ADAPTATION FOR STRAIN-BASED DAMAGE DETECTION ON AN AIRCRAFT WING P. Conen¹, F. Raddatz¹, G. Wende¹; ¹DLR, Germany This paper evaluates the transferability of a machine learning model that is trained with synthetic data. The virtually trained model should predict the existence, location, and geometrical characteristics of cracks in the physical domain. This paper contributes to the fields of structural health monitoring and domain adaptation. | ||||
| 14:55 | 15:20 | 7.5.2 |
MACHINE LEARNING AND NUMERICAL OPTIMIZATION OF BIO-INSPIRED 3D-PRINTABLE SANDWICH CORE CELL B. Omede'¹, A.M. Grande¹; ¹Politecnico di Milano, Italy This article delves into the increasing need for lightweight, energy-absorbing structures, with a focus on additive manufacturing. It integrates Machine Learning (ML) in the crashworthiness optimization of bio-inspired geometries. A circular elytra-inspired design undergoes optimization through ML and genetic algorithms, providing a cost-effective approach to advanced structural engineering solutions. | ||||
| 15:20 | 15:45 | 7.5.3 |
FLUID-STRUCTURE INTERACTION OF TWO-PHASE SCATTERER METAMATERIALS FOR VIBRATION SELF-SUPPRESSION W.H. Yuan¹, Y.J. Chai¹, X.W. Yang¹, F. Ripamonti, Politecnico di Milano, Italy; X. Wang¹, Y.M. Li¹; ¹Xi’an Jiaotong University, China Presenter: Wenhan Yuan, Xi’an Jiaotong University Lower-frequency band gaps are favored by the fluid-structure interaction of two-phase scatterer locally resonant metamaterials. The vibration-damping capacity is enhanced by increasing the solid-liquid contact rate. The obtained results provide a simple passive active control design scheme for resisting the vibration noise of fluid-structure interaction structures in high-end equipment. | ||||
| 15:45 | 16:10 | 7.5.4 |
A PHASE FIELD BASED DEEP LEARNING APPROACH FOR MECHANICAL PROPERTY PREDICTION OF SINTERED SILVER IN POWER ELECTRONICS B.R. Yang¹, B. Wan¹, G.C. Fu¹, X.H. Wang¹, X.H. Wang¹, J. Yao¹; ¹Beihang University, China Sintered silver have promising packaging applications in power electronics because of its superior mechanical properties. However, it contains pore structures induced by sintering process which deeply affect its mechanical properties. Thus, we proposed a deep learning method to predict mechanical properties of porous sinter silver using data generated from phase field simulation. | ||||
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| 14:30 | 14:55 | 8.5.1 |
DATA MINING ANALYSIS ON AERODYNAMIC STEALTH DESIGN PRINCIPLES OF AIRFOIL PROFILES S.-Y. Jin¹, Z.-H. Gao¹, S.-S. Chen¹, Y.-Q. Wang, China Aerodynamics Research and Development Center, China; ¹ Northwestern Polytechnical University, China This paper uses random forest and isometric mapping for data mining to optimize airfoil profiles for aerodynamics and radar cross-section. Leading/trailing edge curvature and chord length significantly impact performance. Data mining establishes optimal design variable ranges for airfoil profiles with superior aerodynamic and stealth performance. | ||||
| 14:55 | 15:20 | 8.5.2 |
INTELLIGENT RECONSTRUCTION METHOD OF AIRFOIL FLOW FIELD BASED ON DEEP ATTENTION NETWORK K. Zuo¹, X. Yuan, China Aerodynamics Research and Development Center, China; W. Zhang¹, Z. Ye¹; ¹Northwestern Polytechnical University, China The computation of aerodynamic parameters using Navier-Stokes (NS) equations is notably time-consuming.To address this, a data-driven Deep Attention Network (DAN) is introduced for rapid reconstruction of steady flow fields over various airfoil shapes. DAN model showcases robust generalization capabilities and high prediction accuracy across a wide array of airfoil flow fields. | ||||
| 15:20 | 15:45 | 8.5.3 |
CORRELATION MODELLING OF SURFACE INVISCID FLOW CHARACTERISTICS AND FRICTION DISTRIBUTION BASED ON MACHINE LEARNING S. Zhao¹, W. Zhang¹; ¹NORTHWESTERN POLYTECHNICAL UNIVERSITY, China This paper proposes a physics guided machine learning modelling approach for skin friction distributions with high generalizability. Compared to end-to-end deep learning modelling of distributed forces, the method achieves high modelling accuracy (drag error of about 2-3%) with a five-fold reduction in sample size, strong interpolation prediction capability and low dispersion of results. | ||||
| 15:45 | 16:10 | 8.5.4 |
DYNAMIC STALL PREDICTION THROUGH COMBINING PHYSICAL MODELS AND MACHINE LEARNING W. Zhang¹, X. Wang¹, J. Kou¹, Z. Liu, The China Aerodynamics Research and Development Center, China; ¹ Northwestern Polytechnical University, China Presenter: Weiwei Zhang We propose new multi-fidelity modeling framework to improve the accuracy and efficiency for dynamic stall prediction. The framework combines the linear dynamic derivative model and machine learning, achieving higher accuracy under sparse experimental states. We validate the framework using wind tunnel data for the pitching motions of NASA Common Research Model (CRM) at high angles of attack. | ||||
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| 14:30 | 14:55 | 9.5.1 |
MULTI SENSOR AND MULTI TASK ALLOCATION BASED ON IMPROVED WHALE OPTIMIZATION ALGORITHM B. Yuan¹, S. Zhang¹, B. Wang, School of Electronic and Information, Northwestern Polytechnica, China; K. Zhang, School of Electronic and Information, Northwestern Polytechnical, China; ¹College of Aerospace Science and Engineering, National Universit, China In response to the collaborative detection problem of UAV formations in cluster operations, this paper constructs an optimization model with detection benefits and detection costs as the objectives based on task priority, and designs an improved whale optimization algorithm to solve the model. Firstly, an elite population initialization based on multiple constraint conditions was proposed, and secondly, an improved method for updating whale individual positions was proposed by combining model characteristics. Subsequently, a local search strategy was designed to enable the algorithm to escape from local optima. Finally, the algorithm provides a set of non dominated solution sets for problem solving, allowing for the selection of more reasonable optimal solutions based on actual needs. On the one hand, the simulation experiment verified the effectiveness of the proposed algorithm in solving task allocation problems, and on the other hand, compared with other intelligent optimization algorithms, the improved whale optimization algorithm obtained a higher quality non dominated solution set, indicating that the algorithm has certain advantages. | ||||
| 14:55 | 15:20 | 9.5.2 |
PRELIMINARY DESIGN OF POWER CONTROL STRATEGIES FOR THE HYBRID-ELECTRIC PROPULSION SYSTEM OF A LIGHTWEIGHT FIXED-WING UAV G. Di Rito¹, A. Suti¹; ¹University of Pisa - Dept. of Civil and Industrial Engineering, Italy Presenter: Gianpietro Di Rito, University of Pisa - Dept. of Civil and Industrial Engineering The design of power control strategies for hybrid electric propulsion system of lightweight fixed-wing UAVs for long-endurance surveillance missions is proposed. The UAV electric generator is temporarily switched into motor operation, up to reduce the power delivered by the ICE and to avoid its temperature rise. The strategies, based on dynamic decoupling techniques, limit the engine temperature during climb and optimize its efficiency during cruise. | ||||
| 15:20 | 15:45 | 9.5.3 |
DEVELOPMENT OF UAVS/DRONES EQUIPPED WITH THERMAL SENSORS FOR THE SEARCH OF INDIVIDUALS LOST UNDER RUBBLE DUE TO EARTHQUAKE COLLAPSES OR ANY EVENTUALITY REQUIRING SUCH CAPABILITIES J.A. Herrera Velasco, National Autonomous University of Mexico (UNAM), Mexico; H.S. Delgado Guevara, UNAM, Mexico In response to the rising frequency of disasters, this abstract explores the development of UAVs with thermal sensors for efficient search and rescue operations in collapsed structures. Emphasizing the importance of thermal sensors, the text discusses challenges, such as dust interference, and proposes solutions. Additionally, it outlines the role of drones in debris removal and supply delivery, emphasizing collaboration with human rescue teams to maximize effectiveness and support survivors in inaccessible areas. | ||||
| 15:45 | 16:10 | 9.5.4 |
MEASURING THE ANGLE OF ATTACK – PRACTICAL CONSIDERATIONS FOR THE DEVELOPMENT OF FAULT DETECTION RESIDUALS C. Raab¹, N. Fezans¹; ¹DLR (German Aerospace Center) - Institute for Flight Systems, Germany Presenter: Christian Raab, DLR - Institute of Flight Systems Angle of attack measurement and current developments in sensor fault detection are the subject of this paper. Different fault residuals are presented. Flight data from the DLR research aircraft A320-ATRA are applied to the residuals. Selected maneuvers and conditions are used to demonstrate the fault detection ability. Recommendations for the practical use of the residuals are given and discussed. | ||||
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| 14:30 | 14:55 | 10.5.1 |
VIBRATION OF COMPOSITE SHELLS OF REVOLUTION USING EQUIVALENT SINGLE LAYER AND LAYER-WISE APPROACHES E. Carrera , Politecnico, Italy; V. Zozulya, iMex, Ukraine Shells of revolution are widely used in aviation. Numerical solutions of these structures are very difficult to obtain due to the complex nature of the differential equations governing their static and dynamic behaviour. An approach to solving problems of vibration of composite multiplayer shells of revolution is proposed. The theory and the resulting equations are based on Carrera unified formulation. The resulting equations can be used for vibration analysis and calculation of the stress-strain state, as well as for modeling thin-walled structures used in science, engineering, and technology. The resented results of calculation can be used as reference examples for finite element analysis of higher order composite laminates plates and shells. Shells of revolution are widely used in aviation. Numerical solutions of these structures are very difficult to obtain due to the complex nature of the differential equations governing their static and dynamic behavior. An approach to solving problems of vibration of composite multilayer shells of revolution is proposed. The theory and the resulting equations are based on Carrera's unified formulation. The resulting equations can be used for vibration analysis and calculation of the stress-strain state, as well as for modeling thin-walled structures used in science, engineering, and technology. The resented results of calculation can be used as reference examples for finite element analysis of higher order composite laminates plates and shells. | ||||
| 14:55 | 15:20 | 10.5.2 |
DAMAGE TOLERANCE OF A CURVED COMPOSITE STIFFENED PANEL FABRICATED BY AN OUT OF AUTOCLAVE – LIQUID RESIN INFUSION PROCESS D. Fanteria¹, L. Boni¹, F. Romano, 2CIRA S.C.p.A., Italian Aerospace Research Centre, Italy; ¹University of Pisa, Italy This paper presents the results of tests conducted on a curved stiffened panel to evaluate its damage tolerance capabilities. The panel was made from dry carbon preforms using Liquid Resin Infusion (LRI) followed by an Out-of-Autoclave curing. Non-linear Finite Element analysis results are also presented and compared to the measurements. Research funded by H2020 Clean Sky 2 JU (GA 807089). | ||||
| 15:20 | 15:45 | 10.5.3 |
NUMERICAL TOOLS FOR SLOW-GROWTH APPROACHES TO DAMAGE TOLERANT COMPOSITE AERONAUTICAL STRUCTURES M. Khella¹, S. Ghiasvand¹, P. Ballarin¹, F. Panzeri¹, S. Piacquadio¹, A. Airoldi¹; ¹Politecnico di Milano, Italy Presenter: Maikel Khella, Politecnico di Milano The activities presented are aimed at integrating in the same numerical approach both the prediction of the residual strength of a composite structural detail in the presence of damage and the evaluation of the crack growing rate under cyclic loading, so to represent a valuable tool for the design of damage tolerant composite aircraft and rotorcraft structures | ||||
| 15:45 | 16:10 | 10.5.4 |
INVESTIGATING THE EFFECT OF DELAMINATION-INDUCED FRICTIONAL CONTACT ON THE DYNAMIC BEHAVIOR OF LAMINATE STRUCTURES S. Kiasat¹, A.S. Nobari, Aeronautics Engineering Department, Imperial College, United Kingdom; M. Filippi¹, E. Carrera¹; ¹POLITECNICO DI TORINO, Italy Presenter: Shabnam Kiasat, Politecnico di Torino The objective of this study is to further investigate the relation between modal damping and interlaminar delamination, aiming to establish modal damping as a reliable and effective damage index for detecting and assessing the presence and severity of delamination in laminated structures. The findings of this research are expected to contribute to the development of improved damage detection techniques, design strategies, and mitigation approaches for enhancing the performance and durability of laminate structures. By gaining insights into the friction-damping mechanism and its impact on the overall dynamic response, this study aims to provide valuable knowledge for engineers and researchers working on non-destructive damage detection methods (especially delamination) in laminated structures. | ||||
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| 14:30 | 14:55 | 11.5.1 |
STUDY OF AEROELASTIC PROBLEM OF RUDDER SYSTEM WITH ELECTRIC ACTUATOR AND STRUCTURAL NONLINEARITIES W. Qian¹, W.-Z. Feng, Dalian University of Technology, China; C.-X. Han¹, X.-Y. Ai¹; ¹Daian University of Technology, China Stiffness of actuator is important for the aeroelastic behavior of rudder system which impacts the design of all-movable control surface of an aircraft. However, the conventional aeroelastic analyzing method took the supporting stiffness of a rudder system as a constant consciously or unconsciously, which led to mistakes in predicting the aeroelastic property of all-movable control surface. In this paper, the aeroelasticity problem for a complete rudder system with actual electric actuator and structural nonlinearities (e.g. free-play and friction) are studied. A Simulink model for a rudder system considering electromechanical part of actuator, elastic part of wing structure as well as free-play and friction nonlinear parts in the drive link is established. Through this model, the aeroelastic property of the all-movable control surface with rudder system can be obtained by time-domain simulation. Meantime, a test model with actual electric actuator is designed and manufactured, nonlinear dynamic test is carried out for estimation of nonlinear parameters including free-play angles and friction coefficients. Finally, the time-domain simulation results and dynamic test results are compared with each other for validating effectiveness of the established model. This paper gives a methodology for studying the aeroelastic property of rudder system supported by practical mechanism. | ||||
| 14:55 | 15:20 | 11.5.2 |
NOVEL TEST RIG TO DEMONSTRATE A MULTI FUNCTIONAL FLAP MECHANISM OFFERING A 2ND DEGREE OF FREEDOM J. Docter¹, H. Pijlman¹, D. de Wit², J. Vervliet², J. Katarzynski¹, R. Postma¹, K.-J. Bisschop¹, J. Vroon¹; ¹NLR, Netherlands ;²Asco Industries, Belgium Presenter: Hermen Hermen, NLR This paper describes test development, demonstration and result correlation of a simplified but representative Multi-Functional Flap Mechanism (MFFM) in a novel test rig at Royal NLR. The objective is to demonstrate that the MFFM can rotate at a speed of 60 degrees per second in retracted, take-off and landing flap positions, considering intact, actuator failure and jamming cases. During the rotation, aero loads will be simulated by mechanical springs and wing bending will be simulated by hydraulic actuation on the station supports. In addition, the effect of flap skew on actuator loading is assessed and compared with analytical results. Furthermore a flexible tube test setup is developed to demonstrate the durability of the flexible hydraulic tube under harsh environmental and loading conditions. The tube should be able to withstand 27000 flight cycles under a pressure of 350bar without rupturing or breaking at temperature conditions of -55°C including combination with hydraulic contamination. | ||||
| 15:20 | 15:45 | 11.5.3 |
GUST LOAD ALLEVIATION IN A SCALED UAV DEMONSTRATOR A. Herwig¹, M. Haupt¹, T. Brack¹, J. Bustamante¹, S. Heimbs¹; ¹Cluster of Excellence SE²A – Techniche Universität Braunschweig, Germany The feasibility of an active and passive gust load alleviation (GLA) approach for flexible wings is assessed in a scaled flight model. The active GLA uses flaps to cancel out eigenmodes. The passive GLA uses a non-linear structural deformation of the wing box forming a flared hinge. The similitude is assessed by static tests and the natural frequencies measured in ground vibration tests. | ||||
| 15:45 | 16:10 | 11.5.4 |
REDUCED ORDER MODELLING OF UNSTEADY AERODYNAMICS FOR GROUND FLUTTER TEST SYSTEM W.-Z. Feng¹, J.-H. Zhang¹, Z.-H. Liang¹, W. Qian¹; ¹Dalian University of Technology, China Presenter: Wei-Zhe Feng, Dalian University of Technology Ground Flutter Test (GFT) technique is a recently developed flutter test technique for carrying out flutter test on full scale aircraft configures based on GVT devices and an efficient Reduce Order Model (ROM) of unsteady aerodynamics. The key techniques of GFT system are the loading of equivalent unsteady aerodynamic force by using electromagnetic shakers and the convergence of continuously distributed aerodynamic force into equivalent concentrated forces. In this paper, an equivalent ROM of unsteady aerodynamic force on several concentrated points are developed based frequency domain unsteady aerodynamic theory and surface spline interpolation technique. The genetic optimization algorithm is used to search the optimized location of concentrated points for the best fits of equivalent unsteady aerodynamic forces. Then, the minimum state method in rational function fitting is used to transform the frequency domain ROM of aerodynamic force into time domain. A real-time simulation of GFT system is carried out based the presented ROM model and Simulink units of other physical devices used in GFT system. Flutter phenomenon appears in flutter test using GFT system. The frequency domain and time domain validation of equivalent unsteady aerodynamics are carried out using equivalent unsteady aerodynamics for flutter calculation. The results show that frequency domain error does not exceed 5% and the time domain error does not exceed 8%. Which validates correctness of the present method. | ||||
| additional information (interactive) | 11.5.R |
EXPERIMENTAL INVESTIGATION AND NUMERICAL ANALYSIS OF THE EFFECT OF TEMPERATURE ON THE MECHANICAL PROPERTIES OF AEROSPACE COMPOSITE-METAL HYBRID JOINTS R. Hou¹, B.T. Wang, Department of Strength Design, The First Aircraft Institute of A, China; Z.X. Zhu¹, W.C. Gao¹; ¹Department of Astronautical Science and Mechanics, HIT, China | |||||
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| 14:30 | 14:55 | 12.5.1 |
ROTOR DYNAMIC LOADS CHARACTERISTIC ANALYSIS WITH BLADE TIP TWIST DISTRIBUTION Z. Yu¹, J. Huang¹, Q. Jiang¹, F. Fan, CHRDI , Germany; S. Huang¹; ¹CHRDI, China This article mainly focuses on the influence of distribution of blade tip twist on rotor vibration loads.The rotor lift and dynamic loads were analyzed in detail with the influence of blade twit distribution, the research results of the paper provide technical support and theoretical basis for the design and optimization of low vibration rotors in helicopter. | ||||
| 14:55 | 15:20 | 12.5.2 |
INVESTIGATING AN OPTIMAL AEROELASTIC DESIGN FOR AIRCRAFT WINGS WITH DISTRIBUTED PROPELLERS MADE OF COMPOSITES M. Abouhamzeh, University of Wolverhampton, United Kingdom; Y. Ma, Bauhaus Aviation Research Institute, Germany Promoting novel technologies to exclude carbon emissions from the civil aviation has initiated research on distributed propulsion. Specifically, features needed for electric aviation can benefit from a distributed propeller wing technology in terms of aero-propulsive efficiency which is crucial regarding the space needed for the battery cells. In order to have a structural design tool in preliminary phases, this paper presents the development of a coupled aeroelastic optimization tool for structural sizing of the wing. The structural modelling implements the geometrically nonlinear response of the composite material. The formulation is based on thin to moderately thick composite wings. Transverse shear deformations and moderate twist angles are taken into account, making it proper for the preliminary design of such structures. Based on the procedure for coupling the aerodynamic and structural fields for optimization, the results are proposed for the final version of this paper. | ||||
| 15:20 | 15:45 | 12.5.3 |
EXPERIMENTAL VALIDATION OF THE DYNAMIC FINITE ELEMENT MODEL OF A 1:8 SCALE SEAPLANE USING A LASER DOPPLER VIBROMETER (LDV) F. Lovero¹, G. Biggi¹, S. Lombardi¹, M.A.C. Costa¹, V. Amore¹, E. Cestino¹; ¹Politecnico di Torino, Italy This text discusses the importance of dynamic analysis in aeronautics, focusing on modal analysis of a 1:8 scale replica of the Savoia Marchetti S55X seaplane. The study employs the Finite Element Method (FEM) with advanced composite materials and Roachell sandwich panels. The goal is to validate the theoretical FEM analysis through static and dynamic testing, comparing results using a Laser Doppler Vibrometer for precise vibration measurements. The study aims to achieve a comprehensive understanding of the seaplane's dynamic behavior under operational conditions. | ||||
| 15:45 | 16:10 | 12.5.4 |
DRIVETRAIN INFLUENCE ON THE LEAD-LAG MOTION OF HELICOPTER ROTORS F. Weiss, DLR, Germany Simulations of helicopter rotor dynamics typically only model the rotor, and assume that the rotational hub speed is undisturbed (baseline model). The presented simulation study drops this assumption. The structural model is extended by the drivetrain to study its influence on the rotor dynamics (rotor-drivetrain system). Comparisons of the rotor-drivetrain system’s mode shapes and eigenfrequencies with those of the baseline model show how the drivetrain modifies the collective lead-lag modes. The effects of the drivetrain inertia and stiffness are identified and distinguished. Aeromechanic simulations of the rotor-drivetrain system reveal considerable changes in the blade passage frequency harmonics of the lead-lag loads compared to the baseline model. Since the modified eigenfrequency of the second collective lead-lag mode is near the blade passage frequency, this mode is responsible for the drivetrain’s influence on the lead-lag loads in steady flight. It is investigated whether reduced drivetrain models are suitable for predicting this influence. Finally, it is shown that the inclusion of the drivetrain in the structural model improves the agreement between simulated lead-lag loads and measurements from a wind tunnel test. | ||||
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| 14:30 | 14:55 | 13.5.1 |
A MOMENTUM-INTEGRAL METHOD TO CALCULATE WINDAGE LOSSES ON A ROTATING DRUM WITH SUPERPOSED FLOW H. Tuo¹, P. Liu¹, S. Ding¹, T. Qiu¹, C. Liu¹, R. Cheng, AECC Shenyang Engine Research Institute, China; ¹Research Institute of Aero-Engine, Beihang University, China In order to evaluate the windage losses of the rotating drum in aero-engines, a Von Karman-type momentum-integral method is presented. A 1/7th power law for the velocity profile is assumed. Comparison results showed that the moment coefficient’s discrepancy between the theoretical solution and the CFD method is less than 10% for Rossby numbers ranging from 0.1 to 1. | ||||
| 14:55 | 15:20 | 13.5.2 |
AERODYNAMIC OPTIMIZATION OF HIGH-ALTITUDE PROPELLER COMBINED WITH MACHINE LEARNING METHOD D. Li¹, Z. Ge¹, R. Cui¹, L. Yang¹, C. Wei¹, W. Song, Northwestern Polytechnical University, China; ¹AVIC Aerodynamics Research Institute, China This paper presents an optimization combined with machine learning methods at high subsonic and low Reynolds number condition, in order to improve the aerodynamic efficiency of an E387-based HALE UAV propeller at design point. The machine learning methods are coupled into the propeller analysis and optimization process to keep a good balance between efficiency and accuracy. | ||||
| 15:20 | 15:45 | 13.5.3 |
AERODYNAMIC PERFORMANCE OF BLADELESS DUCTED FAN BASED ON EJECTION EFFECT WITH DIFFERENT DESIGN VARIABLES K. Han, China; S. Yu, China; J. Huang, China; J. Bai, China; Y. Qiu, China this study employs numerical simulation methodologies to scrutinize the aerodynamic performance and flow mechanisms of bladeless ducted fan based on ejection effect. The investigation assess the bladeless ducted fan thrust characteristics and the ensuing alterations in wing aerodynamic performance following the integration of the bladeless ducted fan. | ||||
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| 14:30 | 14:55 | 14.5.1 |
TRANSFORMATIVE PEDAGOGY: CO-TEACHING COURSE CLUSTERS THROUGH COMPETITIVE TEAM DESIGNS FOR INNOVATIVE TALENT DEVELOPMENT IN AEROSPACE EDUCATION M. Luo¹, H. Liu¹, X. Zhang¹, Z. Cui¹; ¹Beihang University, China Presenter: ZHIYANG CUI, Beihang University This study emphasizes improving students' systematic learning and practical perspectives through co-teaching course clusters and competitive team design. It aims to tackle time wastage resulting from similarities across courses, ensuring efficient teaching hour utilization and a seamless connection between the phases of "learning" and "application". | ||||
| 14:55 | 15:20 | 14.5.2 |
LESSONS LEARNED FROM PROJECT BASED TEACHING IN AEROSPACE AT CHALMERS I. Jonsson¹, C. Xisto¹, V. Chernoray¹, A. Capitao Patrao¹; ¹Chalmers University Of Technology, Sweden This paper shares experiences from project based learning (PBL) in aerospace engineering courses at Chalmers University. It focuses on a case study where students design, simulate, and test a UAV propeller. The paper discusses student and instructor feedback, the pros and cons of PBL in this context, and offers future improvements and suggestions. | ||||
| 15:20 | 15:45 | 14.5.3 |
INTEGRATING UNMANNED AERIAL SYSTEMS INTO THE INTELLIGENT SYSTEMS ENGINEERING CURRICULUM O.D. Dantsker, Indiana University, United States Recently, two experiential learning courses on unmanned aerial systems enhanced the Intelligent Systems Engineering curriculum. Specifically, “Autonomous Sports” to focus on integrated vehicle design and development of lighter-than-air vehicles and “Unmanned Aerial Systems” to introduce UAS in a lecture-lab format where students develop autopilots and integrate them into unmanned aircraft. | ||||
| 15:45 | 16:10 | 14.5.4 |
DLR DESIGN CHALLENGE 2024: DESIGN OF A COST AND ENERGY EFFICIENT REGIONAL AIRCRAFT C. Ehrich¹, L. Kriebel¹, T. Schulz¹, M. Tekkel¹, L. Wauer¹, L. Wenz¹, L. Kugler², S. Müller², C. Niro²; ¹Technical University of Berlin, Germany ;²German Aerospace Center (DLR), Germany This paper provides an insight into this year’s DLR Design Challenge winning concept. Students are asked to design a future aircraft for operation on European regional routes in 2050. The aircraft are optimized for economical and energy efficiency and an open design space ensures a variety of revolutionary and innovative aircraft concepts. The results will be presented by the winning team. | ||||
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| 14:30 | 14:55 | 15.5.1 |
A COMPARSION OF TRAJECTORY GENERATION ALGORITHMS FOR A TERRAIN FOLLOWING FLIGHT H. Lee¹, S. Lee¹; ¹Korea Aerospace University, South Korea In military aviation, Terrain Following plays a crucial role, offering the capability for aircraft to fly close to the ground to minimize the risk of detection by enemies. In this paper, Terrain Following trajectory generation algorithms are compared in two-dimensional space using simulation data of several flight scenarios. | ||||
| 14:55 | 15:20 | 15.5.2 |
A GENETIC ALGORITHM FOR TRAJECTORY GENERATION IN ENGINE-OUT EMERGENCY LANDING SCENARIOS OF COMMERCIAL AIRCRAFT J. Gauci, University of Malta, Malta; B. Zammit, Malta; M. Galea, Malta This paper proposes a Genetic Algorithm for the trajectory generation of engine-out transport aircraft. The algorithm finds a feasible glide path – between the initial aircraft position and the landing site – which accounts for the aircraft’s turn performance and is capable of absorbing any excess energy to ensure that the aircraft reaches the landing site at the right height and speed. | ||||
| 15:20 | 15:45 | 15.5.3 |
ATTITUDE CONTROL DESIGN FOR A FLYING-CRAWLING INTEGRATED FLAPPING-WING MICRO AIR VEHICLE Z.Y. Yuan¹, W.Y. Yang¹, J.X. Xuan¹; ¹nwpu, China This paper introduce the dynamic modeling and attitude control design of a flying- crawling integrated bionic flapping-wing micro air vehicle, enhancing its overall flight performance. | ||||
| 15:45 | 16:10 | 15.5.4 |
TRAJECTORY OPTIMIZATION FOR LONG-RANGE AIR-LAUNCHED GLIDING VEHICLES USING CONVEX PROGRAMMING C.-G. Jung¹, C.-H. Lee¹, M.-J. Tahk¹; ¹Korea Advanced Institute of Science and Technology(KAIST), South Korea In this paper, trajectory optimization for long-range air-launched gliding vehicles using convex programming is proposed. The dynamics is reformulated to compact form and converted to SOCP problem. Furthermore, the robust convergence is accomplished using the adaptive trust-region method. The proposed method demonstrated rapid and stable convergence of SCP with a crude initial guess. | ||||
| additional information (interactive) | 15.5.R |
OPTIMAL APPROACH AND DEPARTURE TRAJECTORIES WITH ACOUSTIC FOOTPRINT ASSESSMENT FOR AN AIR MOBILITY QUAD-ROTOR C. Varriale¹, F. Yunus¹, M. Snellen¹; ¹Delft University of Technology, Netherlands | |||||
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| 14:30 | 14:55 | 16.5.1 |
INCREMENTAL NONLINEAR DYNAMIC INVERSION CONTROLLER FOR A FLYING WING OPERATED IN AN AIRBORNE WIND ENERGY SYSTEM D.F. Duda¹, H. Fuest¹, J. Müller¹, T. Islam¹, D. Moormann¹; ¹RWTH Aachen Unitversity, Germany Within this paper, a controller for the translational motion of a flying wing based on Incremental Nonlinear Dynamic Inversion is presented. Operated within an Airborne Wind Energy system, this approach allows the necessary multi-axial maneuvers such as the yaw-roll transition from propeller-borne flight to wing-borne flight. | ||||
| 14:55 | 15:20 | 16.5.2 |
ADVANCED SOLUTIONS AND CHALLENGES IN MULTI-DRONE SYSTEMS FOR SEARCH AND RESCUE MISSIONS: TECHNICAL APPROACHES AND UNRESOLVED MATTER E. D'Amato, Università degli Studi di Napoli Parthenope, Italy This paper reviews literature on developing a diverse multi-drone system for search and rescue within the framework of the project "CHeMSys: Cooperative Heterogeneous Multi-drone System for disaster prevention and first response." Emphasis is placed on analyzing recent findings regarding unresolved technical challenges in the field. | ||||
| 15:20 | 15:45 | 16.5.3 |
HAWK-INSPIRED COOPERATIVE ENCIRCLEMENT GUIDANCE OF FIXED-WING UAV SWARM WITH LIMITED COMMUNICATION IN THREAT SCENARIO B.-Y. Qin¹, D. Zhang¹, S. Tang¹; ¹Northwestern Polytechnical University, China This paper draws inspiration from Harris’ Hawks’ coordinated hunting to establish a safety-critical, low-cost and real-time bionic multi-layer guidance framework. It is the first attempt to study the fixed-wing UAV swarm’s bionic safety-critical encirclement guidance under limited communication. Our work costs less time and calculation than the existing ones, and accords with UAV flight better. | ||||
| 15:45 | 16:10 | 16.5.4 |
A SIMULINK APPROACH TO MODELING HETEROGENEOUS DRONE FORMATIONS FOR AGENT-BASED SIMULATION G. Raspaolo, Italy; G. D'Alterio, Italy; I. Notaro, Italy; E. D'Amato, Italy Presenter: Immacolata Notaro Simulations enables testing of algorithms in a risk-free virtual environment before real-world deployment. An effective simulator should possess accuracy, reliability, flexibility, an intuitive interface, realistic environment representation, data tracking, parallelization and thorough documentation. In this paper, the integration of these features in a simulink-based simulator is approached. | ||||
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| 14:30 | 14:55 | 17.5.1 |
ENHANCED AIRCRAFT TAKEOFF/LANDING SAFETY USING DEEP LEARNING MODEL IN RUNWAY ASSISTANCE SYSTEM N.L. Ywet¹, A.A. Maw¹, J.W. Han¹, J. Chung, Toronto Metropolitan University, Canada; J.W. Chang, Korea Aerospace University, South Korea; J.-W. Lee¹; ¹Konkuk University, South Korea This study introduces an innovative Takeoff/Landing Safety Runway Control Assistance System that employs advanced deep learning techniques. The primary objective of this system is to enhance precision and safety during critical flight stages by providing precise guidance through a sophisticated Artificial Intelligence framework. By precisely processing data, the system enhances situational awareness, predicts obstacle trajectories, and facilitates proactive risk avoidance. Leveraging the YOLO and LSTM models further fortifies the safety precautions during takeoff and landing. Moreover, this study emphasizes the importance of building trust in runway control station operations through a thorough review and strategic application of data, optimizing decision-making processes, operational techniques, and overall control center efficiency. The comprehensive system in this study aims to significantly reduce operator stress, ensure safety, enhance service satisfaction, and mitigate risks in hazardous aviation situations. | ||||
| 14:55 | 15:20 | 17.5.2 |
NONLINEAR BEHAVIOR IN AIRCRAFT FUEL GAUGE READINGS: AN EXPLORING ANALYSIS M.A.D. Di Marzo¹, O.A. Gonzatto Junior¹, H.N. Najafabadi, Linköping University – LiU, Sweden; J.H. Bidinotto¹; ¹University of São Paulo - USP, Brazil Fuel level gauge in aircraft is a challenging matter, once the aircraft’s movements affect its measurement. In this context, this study addresses a detailed analysis of simulated results from a computational tool specifically developed to study aircraft fuel systems. The tool simulates fuel sensor readings across various aircraft attitudes and fuel levels. This analysis highlights the high nonlinearity of these signals in different. The objective was to explore the relationship between the sensor readings, aircraft orientation, and fuel volume. The dataset consisted of simulated readings from eight capacitive sensors placed at different locations inside an aircraft fuel tank. Each row in the dataset represented a specific combination of aircraft attitude (yaw, pitch, roll) and a “cut” (or cross-section) of the fuel tank, simulating a particular fuel volume. The sensors’ readings at each cut, correlated with the simulated fuel volume and aircraft attitude, provided valuable insights into the relationship between these variables, revealing a complex nonlinear interaction. Contour plots were generated to visualize each sensor’s readings at different pitches and rolls, and a polynomial regressions surface was fitted to understand the trends in the sensor readings. A detailed statistical analysis was conducted to quantify the coefficients and significance of pitch and roll angles and their interactions, as well as a Normalized Sensitivity Matrix (NSM) was used to analyze the sensitivity of the multiple sensors to changes in attitude angles, providing insights into how sensors respond to the attitude variations and their relative sensitivity. Each sensor responded differently to pitch, roll, and yaw variations, providing essential information for sensor positioning and system design. This analys | ||||
| 15:20 | 15:45 | 17.5.3 |
INTEGRITY MONITORING OF TIGHTLY INTEGRATED BDS/SINS USING MULTI-HYPOTHESIS SOLUTION SEPARATION (MHSS) ALGORITHM S. Sun¹, H. Wang¹, R. Liu¹, S. Kuang¹, W. Chen¹; ¹Civil Aviation University of China, China Tightly integrated BDS/SINS (BeiDou Navigation Satellite System/Strap-down Inertial Navigation System) navigation system provides higher accuracy performance with the continuously calibration of IMU sensors’ errors using satellite measurements and better continuity performance profited from SINS aiding under poor satellites coverage, which is appreciated in aircraft performance based navigation (PBN) operation. But tightly integration also means that the system can propagate the established position even if the satellite signals are lost or unexpected satellite failure occurs, which will cause integrity risk because of the mis-calibration due to the undetected failure. This paper explores the MHSS (multi-hypothesis solution separation) algorithm in tightly integrated BDS/SINS system for integrity monitoring, multiple Kalman filters provide a non-transient detection capability to enhance its integrity monitoring function based on inertial redundancy information retained from previously processed measurements. BDS satellites information from BDS ground station and simulated aircraft flight trajectory are used to verify the integrity monitoring algorithm by intentionally added errors to the satellites pseudo-range. Monte Carlo simulation techniques is introduced to verify its FDE (fault detection and exclusion) performance, calculated horizontal protection level (HPL) is compared with system horizontal error. The simulation results show that the BDS/SINS tightly integrated navigation system based on multi-hypothesis solution separation algorithm can detect and identify the faulted satellite effectively, and the calculated horizontal protection level (HPL) is in line with expectations. | ||||
| 15:45 | 16:10 | 17.5.4 |
DEVELOPMENT OF THRUST CONTROL SYSTEM FOR SPACECRAFT’S DOCKING MANEUVER H. Lee¹, H. Lee¹, S. Lee¹; ¹Korea Aerospace University, South Korea The rendezvous/docking technology between spacecraft is a crucial aspect of performing orbital servicing missions. This paper proposes the design process for the thrust control system, followed by the simulation of the docking control system. The thrust control system could be applied to various space missions such as satellite repair, fuel replenishment, space debris removal, and space tourism. | ||||
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| 16:30 | 17:00 | 1.6.1 |
NASA HI-RATE COMPOSITE AIRCRAFT MANUFACTURING (HICAM) PROJECT OVERVIEW R. Young, NASA (LaRC), United States Presenter: Tom Reynolds Invited speaker for the Global Sustainable Aviation track | ||||
| 17:00 | 17:30 | 1.6.2 |
SUSTAINABLE HIGH RATE COMPOSITE MANUFACTURE P C Crothers, Boeing Aerostructures Australia, Australia Boeing is actively leading within commercial aviation industry ambition of net-zero carbon emissions by 2050, framed by four pillars: People and Presence, Products and Services, Efficient Operations, and Communities and Industry. This presentation will speak on Boeing Sustainability Goals and relate them to contemporary air vehicle production systems in the local and global context. | ||||
| 17:30 | 18:00 | 1.6.3 |
FUSELAGE, CABIN & CARGO AND EMPENNAGE OF TOMORROW @ AIRBUS COMMERCIAL - NEW FUSELAGE DESIGN & MATERIALS Y. C. Roth, Airbus, Germany invited speaker for the Global Sustainable Aviation track | ||||
| 18:00 | 18:30 | 1.6.4 |
WING OF TOMORROW - LONGER, LEANER, LIGHTER M. Cantrell, Airbus, United Kingdom AFC Flight-Demonstrator Panel-3 Invited Session | ||||
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| 16:30 | 17:00 | 2.6.1 |
AFC FLIGHT-DEMONSTRATOR X-65 PROGRAM OVERVIEW M.L. Post, DARPA/TTO, United States AFC Flight-Demonstrator Panel-3 Invited Session | ||||
| 17:00 | 17:30 | 2.6.2 |
INTEGRATING ACTIVE FLOW CONTROL ON AIRCRAFT J. F. Langford, Aurora Flight Sciences, A Boeing Company, United States AFC Flight-Demonstrator Panel-3 Invited Session | ||||
| 17:30 | 18:00 | 2.6.3 |
THE PATH TO TRANSITION ACTIVE FLOW CONTROL TECHNOLOGY R. Woszidlo, The Boeing Company, United States AFC Flight-Demonstrator Panel-3 Invited Session | ||||
| 18:00 | 18:30 | 2.6.4 |
PERSPECTIVES ON FLOW CONTROL APPLICATIONS FOR LARGE TRANSPORT AIRCRAFT D. Reckzeh, Airbus, Germany AFC Flight-Demonstrator Panel-3 Invited Session | ||||
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| 16:30 | 17:00 | 3.6.1 |
EU IMPACT MONITOR PROJECT - OVERVIEW AND APPROACH Prajwal Shiva Prakasha¹, Patrick Ratei¹, Michel Van Eenige¹, Thierry Lefebvre, The French Aerospace Lab, France; Marko Alder¹, Utkarsh Gupta, Cranfield University , United Kingdom; Mario Antonio Solazzo, CIRA, Italy; Bjoern Nagel¹; ¹German Aerospace Center - DLR, Germany EU Impact Monitor Project deliver a coherent and holistic framework and toolbox that aim to become the reference choice for technology and policy assessment of the environmental-, economic- and societal-impact of European aviation R&I. Bolstered by its profound knowledge and multidisciplinary expertise, a consortium consisting of 10 research establishments and academic institutes develop this framework and toolbox by advancing credible and successfully-applied approaches beyond state of the art. The paper shares the results and approach of EU Impact Monitor Project: The collaborative framework (analysis tools/models coming from different organizations) and assessment results will be demonstrated for 3 use cases. Each demonstration the multilevel assessment capability considering, one or multiple levels - Aircraft, Airport/ATM and Air Transportation System level Use Case 1 (UC1): Advanced Propulsion System; Long- and Short-Range Aircraft with Aircraft level evaluation Use Case 2 (UC2): Continuous Descent Operations; Aircraft and Airport (1 day) level assessment Use Case 3 (UC3): Sustainable Aviation Fuel; Airport, Airport and Airt Transport System Level assessment The sensitivity, tradeoff is demonstrated via a user-friendly Dashboard. | ||||
| 17:00 | 17:30 | 3.6.2 |
EVALUATION OF ASWING FOR OVERALL AIRCRAFT DESIGN OF UNCONVENTIONAL CONFIGURATIONS. APPLICATION TO JOINED WINGS WITH FOLDING WINGTIPS R. Jan¹, S. Delbecq¹, E. Benard¹; ¹ISAE-Supaero, France This article compares the performance of a short-haul aircraft in two different configurations: a conventional configuration, such as the ATR72, and an innovative architecture involving distributed propulsion. Both configurations involve complex aerodynamic and aeroelastic phenomena that must be considered in the design process. To this end, ASWING, an aeroelastic analysis software package, has been coupled with FASTOAD, an aircraft design and optimization tool. This paper presents the methodology for experimentally validating the various tools and their use on the two architectures to determine which is the most promising. | ||||
| 17:30 | 18:00 | 3.6.3 |
IDENTIFICATION OF THE IMPACT OF BLOWING ON THE AERODYNAMIC MODEL OF AN AIRPLANE WITH DISTRIBUTED ELECTRIC PROPULSION S. Cacciola¹, L. Bottà¹, C.E.D. Riboldi¹, L. Trainelli¹; ¹Politecnico di Milano, Italy This work deals with the identification of the aerodynamic properties of the SwitchMaster, a scaled Distributed Electric Propulsion demonstrator (DEP) aircraft with the final aim of modeling the impact of propeller blowing on the stability and control derivatives of the entire airplane. The demonstrator was designed and built at Politecnico di Milano to demonstrate the possible combination of distributed electric propulsion (DEP) configuration and different propulsive control logics that allow replicating in-flight behavior of a single-engine or a twin-engine airplane. | ||||
| 18:00 | 18:30 | 3.6.4 |
MULTIDISCIPLINARY PRELIMINARY DESIGN PROCESS OF HYBRID-ELECTRIC SEAPLANE M. Tuccillo¹, P. Della Vecchia¹; ¹University of Naples Federico II, Italy The sensitivity towards environmental aspects in aviation drove the application of novel powertrain configurations to reduce the fuel consumption and emissions. The paper present a multidisciplinary design process to evaluate the reduction of burnt fuel and emissions of a future hybrid-electric seaplane concept for two time horizons with increasing technological levels. | ||||
| additional information (interactive) | 3.6.R |
TRANSLATING THE CONCEPT OF SUSTAINABILITY FOR THE DETERMINATION OF REQUIREMENTS FOR THE DESIGN OF FUTURE AIRCRAFT L. Paletti¹, L. Boggero¹, G. Wende¹, B. Nagel¹; ¹German Aerospace Center (DLR), Germany Presenter: Ligeia Paletti, German Aerospace Center (DLR) | |||||
| additional information (interactive) | 3.6.R |
PERFORMANCE ENHANCEMENTS BETWEEN DIFFERENT APPLICATIONS OF ALTERNATIVE FUELS AND NOVEL AIRCRAFT CONFIGURATIONS J.L.C. Chan¹, Y. Sun¹, H. Smith, Cranfield University , United Kingdom; ¹Cranfield University, United Kingdom | |||||
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| 16:30 | 17:00 | 4.6.1 |
EXPLORATION AND EVALUATION OF KNOWLEDGE-BASED ENGINEERING APPROACH FOR LIQUID HYDROGEN TANK INTEGRATION IN EXISTING FUSELAGE N. Bhargav¹, V. Elangovan¹, R.C. Munjulury, Linköping University, Sweden; C. Hesse², P. Satwan²; ¹Linköping University/DLR, Germany ;²Institute for System Architectures in Aeronautics, DLR, Germany This paper introduces an initial analysis conducted on an aft-type liquid hydrogen tank setup, exploring different cabin definitions and tank configurations. Additionally, it delves into an investigation of the utilization of a web application to depict a Knowledge-Based Engineering (KBE) application that was developed. As aviation technology advances towards a more sustainable future, there is a growing desire for innovative concepts toachieve zero emissions and sustainability goals. In pursuit of this goal, a preliminary study is conducted that encompasses the assessment of stability factors such as the center of gravity and static margin, along with an exploration of the range achievable when utilizing liquid hydrogen as a fuel source. For the analysis, a virtual cabin design tool used, known as Fuselage Geometry Assembler (FUGA) provides a digital model of the cabin of both single and twin-aisle configurations of commercial aircraft. The information on aircraft characteristics is provided to FUGA using Common Parametric Aircraft Configuration Schema (CPACS). CPACS coupled with FUGA provides the user with a consistent model of aircraft and cabin design. For ease of usage and better visualization of information from FUGA, a web-based application through Flask is hosted for FUGA. This enables the user to access the FUGA tool without the need to install the tool on their devices. | ||||
| 17:00 | 17:30 | 4.6.2 |
INCREMENTAL TRADE-OFF STUDY OF A HYDROGEN FUEL CELL-BASED PROPULSION SYSTEM USING MDAO TECHNIQUES R. di Giuseppe, ISAE-Supaero, SafranTech, France; S. Delbecq¹, V. Pauvert, SafranTech, France; V. Pommier-Budinger¹; ¹ISAE-SUPAERO, France A fuel cell based propulsion system is a possible solution to reduce the carbon footprint of the aviation sector. The study proposes an incremental trade-off design approach to minimize the mass of a system composed of a fuel cell stack, an air compressor, a heat exchanger, and an electric motor. The methodology involves identifying the design variables, the couplings, and formulating a multipoint optimization problem. | ||||
| 17:30 | 18:00 | 4.6.3 |
METHODOLOGIES FOR THE PRELIMINARY SIZING OF HYDROGEN-POWERED AIRCRAFT AND SUPPORTING AIRPORT INFRASTRUCTURES L. Trainelli¹, C.E.D. Riboldi¹, G. Sirtori¹; ¹DAER, Politecnico di Milano, Italy This paper illustrates two methodologies that assess the feasibility, cost and performance of a future commercial aviation system based on hydrogen as energy source. The first concerns the preliminary sizing of a hydrogen-powered aircraft based on mission and certification requirements. The second performs the optimization of the preliminary sizing of airport hydrogen refueling infrastructure. | ||||
| 18:00 | 18:30 | 4.6.4 |
CFD STUDY OF AIR SUPPLY SYSTEM FOR COOLING OF A HYDROGEN POWERED UNMANNED SEAPLANE AND REDUCTION OF THE RESULTING DRAG A. Marsano¹, F. Bustos Ortega¹, G. Santarella¹, S.G. Soundararajan¹, F. Giargia¹; ¹Politecnico di Torino, Italy The purpose of the paper is to determine the best design for an air supply system of a hydrogen powered long-range seaplane "S55 HERA" using the CFD solver Star-CCM+ and the desired result is to obtain the configuration that produces the least possible aerodynamic drag, so different design configurations will be compared in terms of airflow. | ||||
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| 16:30 | 17:00 | 5.6.1 |
INTEGRATED SIZING OF AN ELECTRIFIED TILT-WING AIRCRAFT FOR VERTICAL AND CONVENTIONAL TAKEOFF AND LANDING A.A. Mishra¹, B. Kunwar¹, I. Chakraborty¹; ¹Auburn University, United States This paper presents an integrated methodology for sizing a tilt-wing aircraft with all-electric, hybrid-electric, and turbo-electric propulsion system architectures which is capable of both vertical and conventional takeoff and landing. The workflow includes explicit evaluation of both stability and controllability constraints to ensure acceptable dynamic stability and adequate control authority. | ||||
| 17:00 | 17:30 | 5.6.2 |
IMPACT OF WELL-TO-TANK EFFICIENCY AND EMISSIONS ON HYBRID AIRCRAFT DESIGN OPTIMIZATION M. Blandino¹, M.M. Molinari¹, J. Liberatori¹, P.P. Ciottoli¹, R. Malpica Galassi¹; ¹Sapienza Università di Roma, Italy We present a general framework for the design of sustainable hybrid aircraft which pursues minimal renewable energy consumption and CO2 emissions, taking into account the complete well-to-wake energy route. The design methodology is applied on a hybrid SAF/electric regional aircraft. Polynomial Chaos Expansion is employed to efficiently build stochastic optimal designs. | ||||
| 17:30 | 18:00 | 5.6.3 |
MASS AND POWER ESTIMATIONS IN PRELIMINARY FLIGHT CONTROL SYSTEM DESIGN S.M. Lübbe¹, M. Schäfer¹, O. Bertram¹; ¹German Aerospace Center (DLR), Germany Statistics based estimation methods for preliminary system sizing are limited in covering multifunctional flight control systems (FCS) with load alleviation function. We demonstrate and examine improved system analysis methods for FCS of future aircraft, that enable evaluation of mass and power implications caused by increased functional extent on the example of the DLR-internal project oLAF. | ||||
| 18:00 | 18:30 | 5.6.4 |
ON THE TECHNOLOGIES FOR THE GREENING OF ALL CLASSES OF AIR TRANSPORT L.M.B.C. Campos¹, J.M.G. Marques, Escola de Ciências e Tecnologias, Universidade de Évora, Portugal; P.A. Serrão¹; ¹IDMEC/CCTAE - IST, Portugal Presenter: Pedro Serão The path towards the greening of aviation includes the following steps: (i) development and maturity of new technologies, including electric propulsion and sustainable fuels; (ii) where feasible utilization in the current aircraft fleet to maximize shorter-term benefits: EU Fit 55; (iii) otherwise, incorporation in novel aircraft designs, hopefully, is available in the next generation: 2035. | ||||
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| 16:30 | 17:00 | 6.6.1 |
ENHANCING EFFICIENCY FOR UNSTEADY CFD COMPUTATIONS IN AERONAUTICS M. Carlsson¹, P. Eliasson¹, P. Weinerfelt¹; ¹Saab, Sweden Presenter: Magnus Carlsson, SAAB AB SSAAB has developed a fully implicit approach for aeronautical CFD applications. We present further developments to reduce the computing time for unsteady problems by enhancing the implicit scheme to 1) speed up the rate of convergence and 2) to avoid unsteady calculations e.g. for dynamic derivatives by solving a linear system of equations. Basic and realistic applicaitons are presented. | ||||
| 17:00 | 17:30 | 6.6.2 |
ANALYSIS OF THE R FAMILY OF LIMITERS APPLIED TO HIGH-ORDER FR/CPR SCHEMES FOR THE SIMULATION OF SUPERSONIC FLOWS F.B. Oliveira, Instituto Tecnologico de Aeronautica, Brazil; J.L.F. Azevedo, Instituto de Aeronautica e Espaco, Brazil; Z.J. Wang, University of Kansas, United States The present investigation assesses the feasibility of a novel family of flux limiter formulations to be used with high-order FR/CPR schemes to simulate supersonic air flows typical of aerospace applications, compared to other well-established formulations currently available in the literature. | ||||
| 17:30 | 18:00 | 6.6.3 |
A HIGH-PRECESION PSEUDO ARC-LENGTH METHOD WITH POSITIVE VALUE PRESERVATION PROPERTIES BASED ON TV SPLITTING C. Wang¹, P. Li¹, L. He¹, G. Li¹, H. Dai¹; ¹Chinese Aeronautical Establishment, China This paper aims to construct a flux scheme with high-resolution and robust numerical stability. The main work includes: (1) proposed a TV splitting scheme based on the complex arc-length coordinate systems. By decomposing the flux vector into convective flux and pressure flux, the TV splitting is extended from the fixed grid to the complex coordinate system; (2) Mapping non-physical space to arc-length space through coordinate transformation facilitates the construction of high-precision numerical scheme; (3) The calculation results show that the solver constructed in this paper not only has higher accuracy but also effectively overcomes numerical instability in strong shock wave simulation. The application of the numerical format constructed in this paper to complex flow problems such as compressible turbulence, as well as the development of solvers on three-dimensional spatial and unstructured grids, it is worth further research in the future. | ||||
| 18:00 | 18:30 | 6.6.4 |
A BOUNDARY INTEGRAL EQUATION FORMULATION FOR POTENTIAL COMPRESSIBLE FLOWS AROUND DEFORMABLE BODIES E. Levati¹, C. Pasquali¹, G. Bernardini¹, M. Gennaretti¹; ¹Roma Tre University, Italy This work deals with the derivation of a novel boundary integral formulation for potential flows useful for the aerodynamic and aeroacoustic analysis of deformable bodies in compressible flows. Current developments in aviation design and the increased demand for innovative aircraft, with unconventional geometry, require more reliable and efficient tools for aerodynamic and aeroacoustic analyses. | ||||
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| 16:30 | 17:00 | 7.6.1 |
EXPERIMENTAL INVESTIGATION OF THE DLR-F23 CONFIGURATION AT TRANSONIC SPEEDS USING FAST-RESPONSE PRESSURE-SENSITIVE PAINT P. Hartl¹, M. Ritschel¹, M. Braune¹, H. Mai¹; ¹German Aerospace Center (DLR), Germany High agility aircraft configurations are designed to cover a wide range of flight maneuvers, from supersonic performance to high maneuverability at subsonic speeds. The DLR-F23 configuration, consisting of a low aspect-ratio triple-delta-wing planform, was investigated with a focus on vortical flow physics. Fast-response pressure sensitive paint was applied to investigate unsteady flow phenomena. | ||||
| 17:00 | 17:30 | 7.6.2 |
ASSESSING THE SONIC BOOM OF A FULL-SIZE AIRCRAFT FROM FREE FLIGHT TESTS ON A SUB-SCALE MODEL G. Fasulo¹, L. Federico¹; ¹Italian Aerospace Research Centre (CIRA), Italy Since the cost of conducting flight tests is proportional to the size and weight of the aircraft, the use of sub-scale models to characterize the sonic boom of the full-scale aircraft is a more desirable option. For this purpose, considerable effort has been devoted to defining a hybrid scaling concept for the sonic boom, combining Whitham's theory, free-flight tests, and a propagation model. | ||||
| 17:30 | 18:00 | 7.6.3 |
EFFECT OF FREESTREAM DISTURBANCES ON BOUNDARY LAYER TRANSITION IN HYPERSONIC WIND TUNNEL J. Yuan¹, S. Yu¹, Z. Qian¹; ¹AVIC Aerodynamics Research Institute, China The effect of freestream disturbances on hypersonic boundary layer transition is studied based on two hypersonic wind tunnels in AVIC Aerodynamics Research Institute | ||||
| 18:00 | 18:30 | 7.6.4 |
ELECTRIC FIELD MEASUREMENT IN GLOW DISCHARGE PLASMA INTERACTING WITH SHOCK WAVE IN HYPERSONIC FLOW N. Cao Van¹, H. Itoh¹, M. Mizoguchi¹, A. Uenaka¹; ¹National Defense Academy of Japan, Japan We investigated the impact of a probe on a glow plasma in a floating probe method used in a hypersonic flow. Considering the change in the cross-sectional area of the positive column suggests that the electron density in front of and behind the shock wave appear to be the same, which leads to the uniform reduced electric field along the positive column whose cross-sectional area is uniform. | ||||
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| 16:30 | 17:00 | 8.6.1 |
SIMULATION OF AN INSTALLED PROPELLER BY MEANS OF STEADY AND UNSTEADY BODY-FORCE MODELING H. Pantel¹, F. Falissard¹, G. Dufour, ISAE-SUPAERO, France; ¹ONERA, France Assessment of the actuator line body force method for a propeller. The results are compared to URANS blade-resolved computations, lifting line computations, and steady body force computations. The simulations include an isolated propeller case and and installed case on a wing. | ||||
| 17:00 | 17:30 | 8.6.2 |
EXPERIMENTAL MEASUREMENTS OF SLIPSTREAM DEFORMATION FOR AN INSTALLED DISTRIBUTED PROPELLER CONFIGURATION. R.R. Duivenvoorden¹, F. do Nascimento Monteiro¹, T. Sinnige¹; ¹Delft University of Technology, Netherlands In this paper, we show experimental measurements of total pressure behind a distributed propulsion wing, thereby visualising the deformation of the slipstreams. We compare with similar experiments with only a single propeller installed. Furthermore, we analyse the effects of relative blade phase angle between propellers in the distributed configuration. | ||||
| 17:30 | 18:00 | 8.6.3 |
AERODYNAMIC PERFORMANCE AND INTERACTION EFFECTS OF AN OVER-THE-WING DISTRIBUTED-PROPELLER SYSTEM IN CRUISE CONDITIONS R. de Vries¹, T. Sinnige¹, L.L.M. Veldhuis¹; ¹Delft University of Technology, Netherlands This study investigates the aero-propulsive performance of an over-the-wing distributed propulsion (OTWDP) system, and assesses how it depends on various operating conditions. A combined experimental/numerical approach is taken. The lower-order numerical model matches experimental results for cruise-like conditions, and is used to assess different lift, thrust, and blade-pitch settings. | ||||
| 18:00 | 18:30 | 8.6.4 |
ON THE INFLUENCE OF PROPELLER MODELLING STRATEGY FOR INTERACTIONAL AERODYNAMICS Z. Li¹, V. Maltsev¹, A.H. Aval¹, A. Da Ronch¹; ¹University of Southampton, United Kingdom The main objective of the current work is to develop guidelines for propeller modelling in rapidly predicting interactional aerodynamic effects that dominates the propeller wing system and accelerate/simplify the workflow. The final conference manuscript and the conference presentation will contain an appreciation of the modeling challenges for test cases of increasing complexity and interactional aerodynamics, and a comparative study quantifying the trade-off between computing costs and prediction fidelity for several aerodynamic methods. | ||||
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| 16:30 | 17:00 | 9.6.1 |
COMPARING THE CAPACITY OF DIFFERENT VERTIPORT TOPOLOGIES USING DISCRETE EVENT SIMULATION E. Wille, RWTH Aachen University, Germany Presenter: Eva Wille Vertiports are considered to be a major barrier to UAM adoption. Vertiport capacity depends on the size and topology of the vertiport as well as on the operational conditions. This work presents a discrete event simulation framework to analyze the vertiport capacity for different infrastructure and operational scenarios. | ||||
| 17:00 | 17:30 | 9.6.2 |
DEMAND CAPACITY BALANCING FOR URBAN AIR MOBILITY USING MULTIAGENT SIMULATION G. Sato, Electronic Navigation Research Institute, Japan This study proposes the new concept of demand capacity balancing (DCB) based on the multi-agent system for urban air mobility. It is assumed the future distributed urban air traffic management. We develop the multi-agent DCB and simulate various situations by varying some parameters. The simulation results show the effectiveness of the multi-agent DCB and provide a benchmark for DCB development. | ||||
| 17:30 | 18:00 | 9.6.3 |
DESIGN OF A UAM GROUND INFRASTRUCTURE NETWORK WITH RESPECT TO MAINTENANCE CAPACITY REQUIREMENTS M. Swaid, German Aerospace Center (DLR), Germany; S. Papakonstantinou¹, D. Kloock-Schreiber¹, V. Gollnick¹; ¹Hamburg University of Technology (TUHH), Germany Previous research established a method for calculating vertiport capacity requirements, emphasizing efficient fleet generation and operational optimization. This study builds upon that work by incorporating maintenance cycles for each fleet vehicle. Its primary goal is to identify necessary maintenance capacity and its distribution across a UAM vertiport network, based in Hamburg City, Germany. | ||||
| 18:00 | 18:30 | 9.6.4 |
AIRPORT INFRASTRUCTURE SIZING FOR A REGIONAL ELECTRIC AVIATION NETWORK F. Vehlhaber¹, M. Salazar¹; ¹Eindhoven University of Technology, Netherlands This work introduces a framework for the sizing of a system for on-site energy generation and storage in support of electric flight operations for a regional aviation network. Specifically, it shows how the properties of the flight network can be leveraged for strategic sizing, highlighting airport specific requirements that arise from considering the air transport and energy system as a whole. | ||||
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| 16:30 | 17:00 | 10.6.1 |
STIMULATED THERMOGRAPHY AS NON-DESTRUCTIVE TESTING TO ASSESS THE STRUCTURAL INTEGRITY OF AERONAUTICAL COMPONENT IN CFRP G. Masciopinto¹, E. D'Accardi¹, D. Palumbo¹, U. Galietti¹; ¹Polytechnic University of Bari, Italy Presenter: Umberto Galietti, Polytechnic University of Bari Composite materials are widely used in aeronautical structures. During manufacturing and service conditions, these materials need to be inspected to characterize the presence of defects. In this work, an experimental study was carried out to assess the capability of different stimulated thermographic techniques in detecting delamination and resin pocket in aeronautical components made in CFRP. | ||||
| 17:00 | 17:30 | 10.6.2 |
NUMERICAL ANALYSIS OF PROCESS-INDUCED DEFORMATIONS AND STRESSES IN AERONAUTICAL COMPOSITE COMPONENTS R. Masia¹, M. Petrolo¹, E. Zappino¹, N. Zobeiry, University of Washingthon, United States; E. Carrera¹; ¹Politecnico di Torino, Italy This work investigates process-induced residual deformations in spars, examining factors such as spring-in angles, deformations, and the distribution of 3D stresses throughout the thickness of these components. The research utilizes one-dimensional, higher-order, layer-wise theories derived from the Carrera Unified Formulation (CUF) to overcome time-consuming simulations for such structures. | ||||
| 17:30 | 18:00 | 10.6.3 |
CONCURRENT TOPOLOGY OPTIMIZATION OF CROSS-SECTION TOPOLOGY AND FIBER ORIENTATION FOR ROTATING COMPOSITE BEAMS Y.-F. Luo¹, M.-L. Hao¹, X. Li¹, Q.-H. Li¹; ¹Shandong University, China Due to coriolis and centrifugal forces, dynamic of the rotating aircraft structure is changed. In this paper, a new topology optimization method for simultaneously optimizing the cross-section topology and fiber orientation for the rotating composite beams is developed. The application in helicopter rotor is shown to illustrate the validity and effectiveness of the proposed method. | ||||
| 18:00 | 18:30 | 10.6.4 |
ELASTIC/PLASTIC SEMI-ANALYTICAL METHOD FOR ARBITRARY CURVED SURFACES OF SCARF REPAIRED COMPOSITES Y. Liu¹, B. Liu¹; ¹Northwestern Polytechnical University, China The stress distribution calculating and optimizing method for arbitrary shape adhesive layer of scarf repaired composites proposed in this paper is more accurate than previous semi-analytical methods. And the optimization algorithm could significantly improve the carrying capability of scarf repaired composite laminates, which provides an efficient way to evaluate and aid design of scarf repair. | ||||
| additional information (interactive) | 10.6.R |
A METHOD FOR OPTIMISING THE ARRANGEMENT OF INTERNAL CHANNELS IN AIRCRAFT HYDRAULIC MANIFOLDS MANUFACTURED BY ADDITIVE MANUFACTURING D.-B. Li, China; H.-X. Huang, China; X.-C. Liu, China; P.-Y. Hou, China; H.-H. Liao, China | |||||
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| 16:30 | 17:00 | 11.6.1 |
MULTI-OBJECTIVE DESIGN OPTIMIZATION OF A MORPHING AILERON FOR A HYBRID ELECTRIC REGIONAL AIRCRAFT A. De Gaspari¹, V. Cavalieri¹, M. Corti¹, S. Ricci¹; ¹Politecnico di Milano, Italy This paper presents the design optimization of a morphing aileron demonstrating that these types of devices can exploit their multiple design degrees of freedom to simultaneously achieve several design objectives. The developed morphing aileron has proven to provide better performance than its traditional hinged counterpart both from the aerodynamic point of view and the required actuation force. | ||||
| 17:00 | 17:30 | 11.6.2 |
ADAPTIVE WING FLUTTER SUPPRESSION BY MEANS OF MULTIPLE TRAILING EDGE CONTROL SURFACES - A COMPARATIVE STUDY C.R. Vindigni¹, G. Mantegna¹, A. Esposito¹, C. Orlando¹, A. Alaimo¹; ¹Kore University of Enna, Italy This work explores the possibility of using multiple ailerons-like control surfaces to suppress wing flutter vibrations by means of adaptive control systems. A comparison between single and double ailerons configuration is discussed from both the control system and structural behavior point of view. | ||||
| 17:30 | 18:00 | 11.6.3 |
DESIGN OF A BODY FREEDOM FLUTTER FLIGHT MODEL WITH CONVENTIONAL CONFIGURATION X. Tian¹, Y. Gu¹, Z. Yang¹; ¹Northwestern Polytechnical University, China When the short-period modal frequency of an aircraft is close to the elastic modal frequency of a flexible wing structure, it is prone to cause rigid-elastic coupling, leading to a special kind of flutter - body freedom flutter. Body freedom flutter is commonly found in large aspect ratio tailless or forward-swept wing configuration, and this paper investigates the design of a body freedom flutter flight model for conventional configuration with short fuselage. For the designed configuration, the influences of the wing sweepback angle and inertia parameters (with varied mass and position of the payload) on its flutter characteristics (flutter speed and flutter frequency) are analyzed. The calculation results show that the sweptback wing layout is more prone to body freedom flutter than the straight wing configuration, and the flutter speed and flutter frequency decrease with the increase of the wing sweepback angle. When the sweepback angle is large enough, the flight model will exhibit body freedom flutter. The flutter speed is decreasing as the mass of payload increasing. Interestingly, the futter speed first decreases and then increases as the mass center of the payload moving forwardly, and the flutter frequency monotonically keeps increasing. Correspondingly, the flutter branch shifts from pitch mode to wing bending mode, and the coupling between the pitch mode and the bending mode gets stronger. However, the flutter phenomenon disappears when the mass of payload is moved forward to a certain position. A prototype vehicle has been built and the theoretical model is validated against the modal test results. The ongoing wind tunnel and flight flutter test are expected to provide further validation of the present results. This study provides a new perspective in understanding the body freedom flutter phenomenon for air vehicles of conventional configuration. | ||||
| 18:00 | 18:30 | 11.6.4 |
DESIGN AND TEST OF A MORPHING LEADING EDGE FOR A LARGE-SCALE CIVIL AIRCRAFT Z. Wang, China; X. Sun, China; Y. Yang, China; J. Zhou, China; C. Li, China; J. Xue, China; J. Xiang, China; D. Li, China The climate change has asked the aviation industry to decrease its emissions of greenhouse gases. With the aerodynamic shape adaptability, morphing leading edges have great potential in the application of laminar flow wing and is beneficial to green aviation. As most of the current morphing leading edge is still focus on laboratory demonstration, this paper developed a three-dimensional full-scale morphing leading edge physical prototype for a large-scale civil aircraft. The final test results show that the developed morphing leading edge can be morphed into its target shape smoothly and precisely and validate the effectiveness of the design approach. | ||||
| additional information (interactive) | 11.6.R |
MODELING AND VALIDATION OF MORPHING WING TRAILING EDGE BASED ON ZERO POISSON\\\\\\\'S RATIO HONEYCOMB S.-Y. Sun¹, H.-Z. Wang¹, R. Yang¹, W. Qian¹; ¹Dalian University of Technology, China | |||||
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| 16:30 | 17:00 | 12.6.1 |
ADVANCED MULTIDISCIPLINARY DESIGN OF NEXT-GENERATION GREEN AIRCRAFT L. Pustina¹, R.M. Galassi¹, M. Blandino¹, F. Mastroddi¹; ¹Sapienza University of Rome, Italy In the design of innovative green aircraft, considering the interplay among various disciplines is crucial. In this work an innovative approach, employing asymmetric subspace optimization, integrates structural dynamics, aerodynamics, innovative propulsion system analysis, and flight dynamics. Numerical results on a regional aircraft validate the proposed methodology. | ||||
| 17:00 | 17:30 | 12.6.2 |
OPTIMIZATION OF COMPOSITE WING STRUCTURE FOR TILT-DUCT AIRCRAFT CONSIDERING DISCRETE AND CONTINUOUS DESIGN VARIABLES S.-R. Xu, China; Y.-T. Zhang, China; J.-F. Zhang, China; Y. Zheng, China; Y.-L. Liu, China This paper focuses on designing and optimizing a composite wing structure for tilt-duct aircraft, involving discrete and continuous design variables. The study is based on a reference aircraft with four tilt-ducts. The optimization process has two phases?The primary goal is to select a structural layout during forward flight and VTOL, minimizing mass while meeting design constraints. | ||||
| 17:30 | 18:00 | 12.6.3 |
A PRELIMINARY METHODOLOGY TO ASSESS GUST SPECTRA VIA SATELLITE DATA E. Carrera¹, A. Pagani¹, M. Valente¹, G. Palaia¹; ¹Politecnico di Torino, Italy Presenter: Erasmo Carrera, Politecnico di Torino This study investigates the effects of rising turbulence intensity driven by climate change on gust spectra and related consequences on aircraft design and aviation. Utilizing data collected from the Aeolus ESA satellite, the authors compare effective gust profiles with established wind models, including those by von Kármán and Dryden. | ||||
| 18:00 | 18:30 | 12.6.4 |
AEROELASTIC DIVERGENCE AND FLUTTER ANALYSIS OF A WING WITH ALL MOVING WING TIP W. Wang¹, W. Qian¹, X. Ai¹; ¹Dalian University of Technology, China This paper makes a first pass at simulating and analyzing aeroelastic characteristics for a wing with all moving wing tip (AMT) that uses fluid structural interaction methods for different flight conditions. The AMT is a promising control surface that fits in the control effector for tailless aircraft because it can increase the drag, decrease the maximum lift-to-drag ratio, reduce radar reflection area, and provide yawing moment. Aeroelastic divergence depends on the torsional stiffness of wings and flutter relied on the structural dynamic of wings are concern in the design of flights. The computational fluid dynamic method offers an approach for calculating unsteady aerodynamic force, the Newmark method is applied to solve the aeroelastic equation, the Delaunay method is used for dynamic mesh, and the Rational Base Function is adopted to interpolate the load and displacement. A novel configuration, which is a wing with all moving tip, were present for the study of the aeroelastic of all moving tip. A structural dynamic model based on the finite element method and an aerodynamic model based on the finite volume method were developed in this study to investigate the aeroelastic divergence and flutter of the wing with AMT. The natural frequencies and mode shapes are gained by the Lancozs method and the mode matrix is sent to solve the aeroelastic equation. The first bending mode of wing and the second rotation mode of AMT were calculated by the Lancozs method. The generalized displacement time history of the two modes were computed by the fluid structural interaction method. According to the results, the divergence dynamic pressure is approximately 220 KPa at the subsonic condition in which the Mach number is less than or equal to 0.8. The flutter dynamic pressure is between 111 KPa with 135 Kpa at the transonic condition which the Mach numbers are 0.9, 0.95, 1.05, 1.1, 1.2, and 1.3. Different flight conditions can compute different generalized displacement time hist | ||||
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| 16:30 | 17:00 | 13.6.1 |
GRADIENT-BASED OPTIMIZATION OF AN AXIAL COMPRESSOR UNDER INLET DISTORTION USING BODY-FORCE MODELING C. Dosne¹, R. Barrier¹, S. Bourasseau¹, M. Carini¹, A. Dumont¹, J. Peter¹; ¹ONERA, France An assessment of the body-force capabilities for axial compressor design under inlet distortion is proposed, using the novel adjoint body force tool recently implemented. Then, several optimizations - first under radial then under a full annulus BLI alike distortion - are conducted to demonstrate those capabilities, and to evaluate the adjoint body-force limitations. | ||||
| 17:00 | 17:30 | 13.6.2 |
EFFECT OF POPULAR ADDITIVE MANUFACTURING TECHNOLOGIES ON THE PERFORMANCE AND ACOUSTICS OF UAV PROPELLERS J. García-Tíscar¹, P. Quintero¹, F.N. Ramírez¹, A. Cremades, KTH Royal Institute of Technology, Sweden; ¹Universitat Politècnica de València, Spain UAV noise is a major showstopper. Also, performing field replacement of propellers using additive manufacturing (AM) is of increased interest. In this work, we analyze experimentally the noise and performance of the same propeller manufactured through popular AM techniques, and also perform numerical experiments to isolate the effect of different parameters related to AM. | ||||
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| 16:30 | 17:00 | 14.6.1 |
SAFETY-DRIVEN BASELINING OF HYBRID ELECTRIC AIRCRAFT ELECTRICAL POWER SYSTEM ARCHITECTURES K. Fong¹, P. Norman¹, C.E. Jones¹; ¹University of Strathclyde, United Kingdom Existing approaches to electrical power system (EPS) design for electrical propulsion aircraft assume a starting point with a comprehensive set of baseline requirements. This paper presents a safety-driven methodology to capture baseline requirements for a new concept aircraft with minimal initial design criteria, and translation of these requirements into a resilient EPS architecture solution. | ||||
| 17:00 | 17:30 | 14.6.2 |
EVALUATION AND SIMULATION OF PARALLEL HYBRID ELECTRIC PROPULSION WITH REAL FLIGHT DATA H. Murphy¹, C. Gallagher¹, C. Stuart¹, S. Spence¹, S. Fitzgerald, Ryanair DAC, Ireland; ¹Dept. of Mechanical Engineering, Trinity College Dublin, Ireland The research explores the feasibility and potential fuel savings of parallel hybrid (PH) electric aircraft for short-haul commercial aviation using real flight data, aiming to reduce carbon emissions / / alleviate supply pressures on SAF. Validated PH propulsion models incl. current state of the art (SoA) and 2035 projected levels are simulated and investigated. Findings indicate limitations for current SoA but potential benefits of up to 12.7% fuel burn savings in the middle-range (~500nmi) using 2023 projected technology. | ||||
| 17:30 | 18:00 | 14.6.3 |
PROJECTION OF KEY POWERTRAIN COMPONENT FIGURES OF MERIT FOR OVERALL ASSESSMENT OF ELECTRIC FLIGHT SCENARIOS A. Link¹, S. de Graaf¹; ¹German Aerospace Center (DLR), Germany This study connects projections for component development with aircraft range predictions. It highlights the increasing potential of electrified propulsion from 2025 to 2070 under two different development scenarios. It identifies key contributors, such as fuel cells and TMS, whose improvements in key component performance figures of merit significantly enhance predicted aircraft ranges. | ||||
| 18:00 | 18:30 | 14.6.4 |
AIRPORT CHARGING SYSTEM DESIGNS AND POWER MANAGEMENT FOR MEGAWATT-LEVEL CHARGING OF BATTERY-ELECTRIC AIRCRAFT J. Hellgren¹, M. Persson¹, H. Alfredsson¹; ¹RISE Research Institutes of Sweden, Sweden Presenter: Jonas Hellgren, RISE Research Institutes of Sweden Introducing commercially viable air traffic using battery-electric aircraft (EA) necessitates the creation of high-power charging solutions and robust airport infrastructure. This study assesses megawatt-level charging system designs and power management strategies, as a foundation for future implementation. These essential measures prevent airport infrastructure from impeding the adoption of EA. | ||||
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| 16:30 | 17:00 | 15.6.1 |
STUDY ON CONFIGURATIONS OF AIRBORNE LAUNCH SYSTEM FOR DELIVERY OF SMALL PAYLOAD TO LOW EARTH ORBIT T. Goetzendorf-Grabowski¹, L. Kiszkowiak², A. Kwiek¹, P. Zalewski², K. Chudy², M. Figat¹; ¹Warsaw University of Technology, Poland ;²Military University of Technology, Poland The paper presents a feasibility study of airborne launch systems enabling the delivery of a small payload into low Earth orbit. The concept of a disposable rocket launched from a fighter aircraft is being analyzed. As alternatives, the paper investigates a reusable rocket plane carried by a mother plane and a three-stage system with a rocket. | ||||
| 17:00 | 17:30 | 15.6.2 |
ASSISTED AND AUTOMATED AERIAL REFUELLING – OVERVIEW OF THE CONDUCTED RESEARCH AT THE GERMAN AEROSPACE CENTER (DLR) T. Jann¹, N. Fezans¹, A. Koloschin¹, S.-O. Schmidt¹, P. Link¹, J. Ament¹, S. Krause¹; ¹German Aerospace Center (DLR), Institute of Flight Systems, Germany The German Aerospace Centre (DLR) has developed different methods for the automated aerial refueling of different aircraft systems, like fighter, helicopter, transport aircraft and UAVs, and evaluated their qualities in experiments and simulator tests with pilots. The paper gives an overview about the developments and results achieved within the correspondig project. | ||||
| 17:30 | 18:00 | 15.6.3 |
ON THE EXTRAPOLATION OF STABILITY DERIVATIVES FOR DIFFERENT AIRSPEEDS AND ANGLES-OF-ATTACK AND SIDESLIP L.M.B.C. Campos¹, J.M.G. Marques, Escola de Ciências e Tecnologias, Universidade de Évora, Portugal; P.A. Serrão¹; ¹IDMEC/CCTAE - IST, Portugal Analytic extrapolation factors are obtained for all 12 longitudinal plus 12 lateral stability derivatives of linear decoupled motion. The extrapolation formulas were validated by comparison with results of CFD using RANS equations. The comparison concerns the extrapolated full longitudinal–lateral stability matrix from one landing and one takeoff condition of a V-tailed aircraft. | ||||
| 18:00 | 18:30 | 15.6.4 |
INFLUENCE OF CONTROL POWER RATE ON HIGH-ALPHA ROLL MANOEUVRABILITY P. Månsson, Saab AB, Sweden Highly manoeuvrable platforms, such as fighter aircraft, can have complex aerodynamic characteristics and dynamic sizing cases for control design. Traditional sizing methods for control power seldom include the aspects of control power rate for flying and handling qualities (FQ/HQ). Ensuring excellent FQ/HQ necessitates a sizing approach that allows sufficiently rapid manoeuvre onset, precision tracking and attitude control. This paper exemplies the impact of control power rate on high angle of attack roll performance as well as aspects of integrating thrust vectoring control (TVC). | ||||
| additional information (interactive) | 15.6.R |
STRUCTURED H-INFINITY DESIGN OF PREDICTORS FOR THE MONITORING OF AN AIRCRAFT IN ITS FLIGHT ENVELOPE K.H. Kienitz, Instituto Tecnologico de Aeronautica, Brazil; A. Gonzalez Sorribes¹, R. Sanz Diaz¹, C. Braga de Mendonça, Boeing Brasil, Brazil; P.J. Garcia¹; ¹Universitat Politecnica de Valencia, Spain | |||||
| additional information (interactive) | 15.6.R |
DYNAMICS ANALYSIS AND CONTROL OF A LARGE WINGSPAN FLAPPING-WING VEHICLE C. Zhai¹, B. Song¹, Q. Fu¹, J. Xuan¹, J. Li¹; ¹NORTHWESTERN POLYTECHNICAL UNIVERSITY, China | |||||
| additional information (interactive) | 15.6.R |
DATA-DRIVEN MODEL DISCOVERY AND CONTROL OF HIGH-PERFORMANCE TRAINER AIRCRAFT VIA SPARSE IDENTIFICATION OF NONLINEAR DYNAMICS M.-W. Kang¹, D.-W. Lee², S.-H. Yun¹, H.-C. Bang²; ¹ADD, South Korea ;²KAIST, South Korea | |||||
| additional information (interactive) | 15.6.R |
GROUND EFFECT ON A SLENDER 65º DELTA WING WITH SIDESLIP, IMAGE METHOD, USING EULER R.K. Nangia¹, T. Nangia¹; ¹Nangia, United Kingdom | |||||
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| 16:30 | 17:00 | 16.6.1 |
REDESIGN AND MACHINING OF LEADING EDGE OF TRANSONIC COMPRESSOR BLADE IN ROBOTIC GRINDING OPERATION H. Li¹, L. Zou¹, W. Wang¹, L. Gui¹; ¹Chongqing University, China Presenter: Lai Zou, Chongqing University Refined design and machining of the blade, especially the leading edge (LE) are two key steps in determining its aerodynamic performance. However, design and processing in past studies lacked sufficient correlation and feedback. In this work, for the enhancement of performance and size accuracy, the LE profile of a transonic compressor blade is redesigned and machined in robotic blade grinding operation. The LE profile is designed based on clamped B-spline curve to achieve curvature continuous. The redesigned and baseline LE shapes are then evaluated in terms of curvature distribution and aerodynamic performance. From the perspective of robotic grinding, the number of grinding paths affecting the machining efficiency is analyzed for various LE profiles based on toolpath planning algorithms. Secondly, the machining accuracy is predicted based on the dwell time control method. | ||||
| 17:00 | 17:30 | 16.6.2 |
DESIGN OF A SUSTAINABLE FLEXFORMING PROCEDURE FOR AERO ENGINE COMPONENTS IS ALLOY 718 P. Ottosson¹, E.-L. Westman¹, I. Nygren, Quintus Technologies, Sweden; T. Pettersson, Permanova LaserTool in Blekinge, Sweden; F. Niklasson², L.-E. Brattström²; ¹RISE Research Institutes of Sweden, Sweden ;²GKN Aerospace Engine Systems Sweden, Sweden The aero engine industry in Sweden continuously strive to develop abilities, processes and products for lightweight solutions that in a fast pace contribute to a sustainable society. GKN Aerospace Engine Systems Sweden and sub-suppliers explore and demonstrate new variants of manufacturing process chains for products that will power fossil free transportation in Sweden and abroad. In this study, a manufacturing procedure for a load carrying aero engine component in alloy 718 was evaluated, including Flexforming and mechanical cutting. The project had a target to considerably reduce material, time and energy consumption by at least 50% each. The virtual die and process design for the Flexforming procedure involved FE-modeling, anisotropic material model calibration and parameter studies to identify best choice in blank design and process parameters with respect to minimal spring back. Predicted responses were compared with measured results from Flexforming tests. Existing multi-step manufacturing procedures are to a high extent based on a forging processes following machining to reach final geometry. This implies high levels of energy, material, and time consumption to a relatively high cost. The Flexforming process is a low-cost sheet metal hydroform technology, ideally suited for low volume production. Flexform use only one single rigid tool half and a flexible rubber diaphragm, backed up by high-pressure hydraulic oil. In this project the Flexforming method is applied to form a geometry used to apply minimal machining to directly obtain the final part tolerances for production. A finite element (FE) model of the Flexform process was developed. Material properties for the 718 alloy of which the part is formed needs to be included in the FE model. The anisotropic material model YLD2000-2D in the software Ls-Dyna was applied. The study shows promising agreement between predicted and measured responses such as material thinning and shape deviation. Al | ||||
| 17:30 | 18:00 | 16.6.3 |
PRESERVING HUMAN EXPERTISE: EXPLORING MIXED REALITY TRAJECTORY PLANNING FOR ROBOTIC BELT GRINDING W.-X. Wang¹, H.-L. He¹, T.-Y. Zhou, Cardiff University, United Kingdom; L. Wan¹; ¹Chongqing University, China Presenter: Wenxi WANG, Chongqing University This paper is dedicated to learning the experience of manual work and proposes a new method for robot grinding and polishing trajectory planning based on mixed reality and pose measurement. The method will capture the movements of a skilled operator when surface polishing a blade part, and generate the path and direction of robot polishing based on this manual polishing trajectory. | ||||
| 18:00 | 18:30 | 16.6.4 |
A DIGITAL METHOD FOR THE COMPENSATED MOLD DESIGN OF COMPOSITE PARTS E. Delsol¹, I. Taouil¹, W. Azoti², B. Castanie², P. Olivier², L. Ratsifandrihana, Segula, France; ¹Segula - ICA, France ;²ICA, France Designing a mold that compensates the residual deformations after curing of a composite part is today an expensive trial and error procedure. A numerical method, based on a in-house curing simulation tool, is proposed. The optimization problem is presented, the convergence, performance and limitation of the method are analyzed. | ||||
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| 16:30 | 17:00 | 17.6.1 |
ANGLE AND DISTANCE EFFECT ON PHOSPHOR THERMOMETRY Q. Yin¹, Y. Quan¹, L. Ma¹, J. Liu¹, J. Chai¹, J. Liu¹, L. Zhang¹; ¹Beihang University, China Phosphor thermometry is a non-contact technology that holds promise for measuring gas turbine temperatures. This paper investigated the effects of angle and distance on phosphor thermometry of four samples. We found that different samples responded differently to angles and distances, with a maximum effect of 3% and 12.8% on the thermometry results for YSZ: Dy and YSZ: Sm powders, respectively. | ||||
| 17:00 | 17:30 | 17.6.2 |
VOID FRACTION CALCULATION MODEL BASED ON TWO-PHASE FLOW PATTERNS IN THE SCAVENGE PIPE J.-W. Xie¹, P.-F. Zhu¹, J.-P. Hu¹, Y.-G. Lyv¹, Z.-X. Liu¹; ¹Northwestern Polytechnical University, China This paper employs a “virtual binocular method” to capture images of the oil-air two-phase flow within the scavenge pipe from two perspectives. Through three-dimensional reconstruction techniques, a stereoscopic representation is established to obtain the void fraction values. Subsequently, a void fraction calculation model is developed based on flow patterns. | ||||
| 17:30 | 18:00 | 17.6.3 |
A STUDY ON THE AIRLOCK MECHANISM OF THE OIL SUPPLY PUMP IN AERO-ENGINE LUBRICATING OIL SYSTEM S. Zhang, China; P.-F. Zhu, China; H. Fan, China; Z.-X. Liu, China The external gear pump is the core component of the oil supply part in the aero-engine lubricating oil system. This study uses numerical simulation and experimental methods to analyze the airlock phenomenon that occurs in the pump during the starting process. An analytical method for the airlock is established. The influencing factors and formation mechanism of the airlock are obtained. The results have guiding significance for the design of lubricating oil systems. | ||||
| 18:00 | 18:30 | 17.6.4 |
POTENTIAL APPLICATION OF PHASE CHANGE MATERIALS FOR THERMAL MANAGEMENT SYSTEM OF NEXT GENERATION AIRCRAFT E. Revello¹, M. Boccaccio, Leonardo Labs, Italy; F. Acerra, Leonardo SpA, Italy; A. Monteverde¹; ¹Politecnico di Torino, DISAT, Italy Thermal Management System of next generation aircrafts is crucial. Among the cooling strategies for temperature-sensitive devices, this study analyzes the potential application of Phase Change Materials to absorb thermal transients of a battery pack. To understand the thermal behavior of different PCMs, a preliminary 1-D analytical model has been developed. | ||||
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| 11:00 | 11:25 | 1.7.1 |
BARRIERS TO MW CLASS ELECTRIFIED POWERTRAIN AIRCRAFT PROPULSION SYSTEMS G. Bezos O Connor, NASA (LaRC), United States INVITED SPEAKER FOR THE GLOBAL SUSTAINABLE AVIATION TRACK | ||||
| 11:25 | 11:50 | 1.7.2 |
NASA HYBRID THERMALLY EFFICIENT CORE (HYTEC) PROJECT OVERVIEW A.L. Nerone¹, J.M. Haglage¹, L.M. Nakley¹, R. Tornabene¹; ¹NASA (GRC), United States Invited speaker for the Global Sustainable Aviation track | ||||
| 11:50 | 12:15 | 1.7.3 |
JAXA EN-CORE PROJECT OVERVIEW AND ACHIEVEMENTS T. Yamane, Japan Aerospace Exploration Agency, Japan invited speaker for the Global Sustainable Aviation track | ||||
| 12:15 | 12:40 | 1.7.4 |
Q&A - MINI PANEL QA A, Q&A - MINI PANEL | ||||
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| 11:00 | 11:25 | 2.7.1 |
A CFD VALIDATION ECOSYSTEM TO ADVANCE THE PREDICTION OF LOW-SPEED AERODYNAMICS J.P. Slotnick, Boeing, United States CFD validation efforts to advance the understanding of low-speed (high-lift) flow physics to ultimately enable a robust predictive capability are well underway within the international aerospace community, driven mainly through CFD prediction workshops. With the completion of the geometric definition of the High Lift Common Research Model (CRM-HL) in 2016, an informal consortium of organizations has been formed to create a CRM-HL “Ecosystem” to design, fabricate, and test a baseline set of CRM-HL configurations in several wind tunnels over a wide range of Reynolds numbers. These data will be used to validate existing and emerging CFD technologies. This paper will discuss the original genesis of the Ecosystem concept, the requirements that drove the technical efforts, and a summary of what has been accomplished and what is expected in the future. | ||||
| 11:25 | 11:50 | 2.7.2 |
CHALLENGES IN GEOMETRY DEVELOPMENT FOR THE CRM-HL ECOSYSTEM A.M. Clark¹, D.S. Lacy¹; ¹Boeing Commercial Airplanes, United States In 2016, the High-Lift Common Research model (CRM-HL) was developed by Boeing and made publicly available to support efforts at NASA to develop advanced aerodynamic technologies. Since then, further development has occurred to define configurations of interest, including takeoff, landing, and small perturbations to challenge CFD validation exercises. These development efforts have launched a robust Ecosystem, with its foundations built on several experimental models of different scales developed by various partners around the world. Ensuring that the physical models developed are a faithful representative of the reference CRM-HL configurations presents unique challenges. Additionally, accurate and robust CFD simulation to match the physical experiments also requires specific focus. This paper will discuss the geometric considerations for consistent development and experimental testing of the CRM-HL configurations, as well as highlight requirements for CFD modeling across the CRM-HL Ecosystem. | ||||
| 11:50 | 12:15 | 2.7.3 |
NASA CONTRIBUTIONS TO THE HIGH LIFT COMMON RESEARCH MODEL ECOSYSTEM M. Rivers, United States As part of the High Lift Common Research Model (CRM-HL) ecosystem, NASA has designed and built two CRM-HL models. The first model is a 5.2% scale semispan model that has been tested in the NASA Langley 14- by 22-Foot Subsonic Wind Tunnel (14x22), the low-speed wind tunnel DNW-NWB in Germany and in the National Transonic Facility (NTF) at NASA Langley Research Center. Information on the NASA tests that will include wind tunnel information, model details, test methods and some test data will be presented in the final document. The second model is a 2.7% scale model that will also be tested in the NTF in both full span and semispan configurations. Information on the design and fabrication of this model will be included in the final document. There will be a total of four tests of these two models in the NTF. The first 5.2% semispan test focused on force and moment and surface pressure measurements to compare with other data obtained for the ecosystem and to provide high Reynolds number data. The second 5.2% semispan test will focus on flow field measurements, both on and off surface. The third test will be of the 2.7% full span model that will also focus on force and moment and surface pressure measurements while the fourth test will be of the semispan 2.7% model that will focus on comparisons of full span versus semispan data differences. More information will be provided in the final document. 1 | ||||
| 12:15 | 12:40 | 2.7.4 |
THE CRM-HL ECOSYSTEM - DLR CONTRIBUTIONS R. Rudnik¹, S. Pülm¹, F. Schmidt¹, J. Wild¹, A. Schröder¹, C. Spehr¹, P. Mühlmann¹; ¹DLR, Germany With the aim to collect unique aerodynamic and aero-acoustic data to validate computational fluid dynamics (CFD) methods as well as to improve the understanding of wind tunnel installation effects, DLR carried out experimental investigations of the NASA Common Research Model in high lift configuration (CRM-HL) in the low speed wind tunnel DNW-NWB in Braunschweig. The data are collected and analyzed as part of the DLR project ADaMant (Adaptive Data-driven Physical Modeling towards Border of Envelope Applications). | ||||
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| 11:00 | 11:25 | 3.7.1 |
CLIMATE IMPACT AND ECONOMIC ASSESSMENT OF LIQUID HYDROGEN AND SYNTHETIC KEROSENE LONG-RANGE AIRCRAFT CONCEPTS S. Wöhler¹, K. Buchtal¹, M. Iwanizki¹, J. Häßy¹, K. Dahlmann¹, C. Lois¹, M. Hepperle¹; ¹DLR, Germany Aim of this study is to assess the climate impact and economics of different energy carrier options such as fossil kerosene, sustainable aviation fuel and liquid hydrogen on aircraft design and the long-range market segment. Additionally, flight Mach number and maximum altitude are reduced to further identify climate impact saving potentials with regard to the direct operating costs. | ||||
| 11:25 | 11:50 | 3.7.2 |
SUSTAINABLE AVIATION IN NORDIC COUNTRIES C. Jouanet¹, K. Amadori¹, E. Espinoza Juarez¹; ¹Linköpings University, Sweden The project examines various propulsion technologies like batteries, fuel cells, hydrogen, and Sustainable Aviation Fuels (SAF) to meet the climate-neutral goal for Swedish and Nordic domestic flights by 2045. The study suggests that a combination of technologies, including the interim use of SAF/Biofuel, is necessary. | ||||
| 11:50 | 12:15 | 3.7.3 |
A PROPOSAL TOWARDS A STEP CHANGE FROM ECO-DRIVEN TO SUSTAINABILITY-DRIVEN DESIGN OF AIRCRAFT COMPONENTS A. Filippatos¹, D.N. Markatos¹, A. Theochari¹, S. Malefaki¹, T. Kalampoukas¹, S.G. Pantelakis¹; ¹University of Patras, Greece We propose an approach enabling a step change from eco-driven to sustainability-driven design of aircraft components. To this end, sustainability is integrated as a design driver of the conceptual design and the design phase, broadening the interpretation of sustainability beyond environmental concerns. To show the approach, an in-depth case study will center on analyzing a hat-stiffened panel. | ||||
| 12:15 | 12:40 | 3.7.4 |
ON THE EXISTENCE OF A FAMILY OF IDEAL AIRCRAFT CONFIGURATIONS R.J. Huyssen, CSIR, South Africa; G.R. Spedding, University of Southern California, United States The bulk of aviation fuel is consumed in the domain of fixed-wing subsonic flight. Best flight efficiency can only be attained if an aircraft design is based on its ideal configuration. Here we propose that a family of aircraft configurations exists that is superior to the current dominant configuration. | ||||
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| 11:00 | 11:25 | 4.7.1 |
CRYOGENIC TANK SIZING MODEL FOR THE CONCEPTUAL DESIGN OF HYDROGEN-POWERED AIRCRAFT G. Licheva¹, S. Liscouët-Hanke¹; ¹Concordia University, Canada This paper presents a parametric model for cryogenic hydrogen tanks for aircraft conceptual design in an MDAO context. The model considers hydrogen properties, filling pressure, tank geometry, insulation, and installation constraints. Case studies for various tank installation and configuration scenarios are presented for a notional business aircraft, considering aircraft-level impact. | ||||
| 11:25 | 11:50 | 4.7.2 |
HYDROGEN STORAGE SYSTEM DESIGN: CASE STUDIES FOR AIRBORNE APPLICATION F. Mazzoni¹, G. Accardo², R. Biga², E. Brusa¹, C. Delprete¹, C.A. Manrique-Escobar², V. Vercella²; ¹Politecnico di Torino, Italy ;²Leonardo S.p.A., Italy The preliminary design of the on-board hydrogen storage system is performed through a sizing model. The geometrical, mechanical, and thermal properties are analyzed for both compressed, cryo-compressed, and liquid hydrogen tanks. Then, the model is applied to two case studies, representatives of two aircraft categories, to evaluate the technical feasibility of the hydrogen-powered aircraft. | ||||
| 11:50 | 12:15 | 4.7.3 |
INTEGRATING CRYOGENIC TANKS MODEL IN HYDROGEN AIRCRAFT DESIGN FOR PARAMETRIC PERFORMANCE ANALYSIS R. Parello, ONERA/ISAE-SUPAERO, France; S. Defoort, ONERA, France; E. Benard¹, Y. Gourinat¹; ¹ISAE-SUPAERO, France Hydrogen aircraft present huge challenges due to hydrogen complex storage in pressurized cryogenic tank. This study focuses on the integration of a medium-fidelity hydrogen tank model into an overall aircraft design tool and its exploitation to optimize a hydrogen aircraft. This integration allows the comparison of tank configurations at the aircraft level and the search of the optimum ones. | ||||
| 12:15 | 12:40 | 4.7.4 |
HYDROGEN AIRLINER TANK OPTIMISATION P. De Felipe¹, C. Cumpsty¹, I. Iturriaga¹, H. Dance¹; ¹ZeroAvia, United Kingdom This paper goes over the retrofit design of a Boeing 737-800 with a Hydrogen Electric Propulsion system. It focuses on the trade-offs with liquid hydrogen tank placement and uses a novel optimization technique to quickly find the optimal design. The results are compared in terms of fuel costs against the original airliner and further notes on technology readiness are given. | ||||
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| 11:00 | 11:25 | 5.7.1 |
ARCHITECTURE DESIGN FOR A COMMERCIALLY VIABLE HYDROGEN-ELECTRIC POWERED RETROFITTED REGIONAL AIRCRAFT B. Rietdijk¹, M. Selier¹; ¹Conscious Aerospace, Netherlands A Dash 8-300 is retrofitted to a hydrogen-electric powered regional aircraft. The results of the architecture design, introduction of automotive and cryogenics and certification considerations presented in this paper are relevant to design aircraft flying on hydrogen in general, and for the introduction of certifiable and commercially attractive aircraft in the energy transition. | ||||
| 11:25 | 11:50 | 5.7.2 |
ENVIRONMENTAL IMPLICATIONS OF HYBRID-ELECTRIC REGIONAL AIRCRAFT: EMISSIONS AND CLIMATE CHANGE K. Abu Salem¹, G. Palaia¹; ¹Politecnico di Torino, Italy What is the actual environmental benefit of the transition of regional aircraft to hybrid-electric propulsion? Starting from this question, this paper aims to discuss the methodological limitations, the need for a change in design approach, and the actual overall magnitude of the impact, related to the assessment of the introduction of hybrid-electric regional aircraft in the operating scenario. | ||||
| 11:50 | 12:15 | 5.7.3 |
CLEANSKY2/ CLEAN AVIATION LARGE PASSENGER AIRCRAFT FOR MORE SUSTAINABLE COMMERCIAL FUSELAGE TECHNOLOGIES – MAJOR ACHIEVEMENTS Y.C. Roth¹, R. Herrmann¹, C. Sanchez Santos, Aernnova, Spain; M. Uellendahl, Airbus Aerostructures, Germany; J. Koopman, GKN Fokker Aerospace, Netherlands; A. Henneberg, Diehl Aviation, Germany; J. Kos, Royal Netherlands Aerospace Centre, Netherlands; I.F. Villegas, Delft University of Technology, Netherlands; A. Choudhary, SAMXL, Netherlands; L. Larsen, DLZ Zentrum für Leichtbauproduktionstechnologie, Germany; S. Ferstl, Premium Aerotec, Germany; B. Diehl, Fraunhofer, Germany; F. Emanuelsson, Saab Aerospace Systems, Sweden; J.-B. Sinechal¹, M. Pleth¹, K. Atherton¹; ¹Airbus, Germany In the framework of CleanSky2 (CS2) - Large Passenger Aircraft project, a consortium led by Airbus consisting of universities, research centers and industrial partners across Europe investigated various fuselage system, cabin & airframe technologies for commercial aircraft. The goal has been to strongly contribute to the environmental objectives of 20-30% CO2 reduction whereas at the same time performance increase through weight reduction and improved competitiveness through less recurring cost and industrial ramp up capabilities had to be demonstrated. In total, more than 40 different technologies have been further developed by the European consortium consisting of 14 partners in order to finally deliver an 8m large scale flagship in 2024: the Multifunctional Fuselage Demonstrator. Novel fuselage design and built concepts are demonstrated as well as thermoplastic composite material testing & modelling, elementary parts manufacture and assembly for large scale fuselage structures incl. “zero airframe customization” concepts for cabin installation. Final results and major achievements of this European funded program will be presented and discussed. | ||||
| 12:15 | 12:40 | 5.7.4 |
ANALYSIS OF BATTERY WEIGHT REQUIREMENTS IN THE DESIGN OF HYBRID ELECTRIC POWERED AIRCRAFT D. Liu¹, Z. Chen¹, Z. Guo¹, B. Zhu¹, G. Jia¹, X. Yang¹; ¹National University of Defense Technology, China The battery of the hybrid electric powered aircraft discharges at high power for a relatively long time during climb, consuming much electric energy and resulting in more battery weight requirements than the takeoff phase. The selection of battery discharge power and the configuration of battery released energy for each phase in aircraft design are investigated. | ||||
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| 11:00 | 11:25 | 6.7.1 |
A BRIEF REVIEW OF PANEL AEROELASTICITY WITH SHOCK INTERACTION A. Shi, China; Y. He, China; E.H. Dowell, United States Presenter: Yiwen He Shock wave is inevitably encountered on flexible panel of high-speed vehicle. Severe pressure and thermal loads aggravate aeroelastic effect threatening structural safety. In turn, aeroelastic behaviors influence dynamics of shock. Via reviewing recent studies on panel aeroelasticity with shock from fluid-structure interaction and shock-boundary layer interaction, control strategies are motivated. | ||||
| 11:25 | 11:50 | 6.7.2 |
ACTIVE-PASSIVE HYBRID CONTROL OF SHOCK BUFFET C.Q. Gao, China; K. Ren, China; W.W. Zhang, China An active-passive hybrid control method is proposed to eliminate the shock buffet flow over wings. Passive control uses SCB to suppress spanwise instability modes. The active control takes the lift coefficient as the feedback signal, and adopts the model free adaptive control method to adjust the rotation angle of the trailing edge flap to achieve the control of chordal shock wave oscillation. When using only the wingtip flap for closed-loop control, the amplitude of lift coefficient fluctuation can be reduced. This is due to the cancellation of the impact of shock wave oscillation and trailing edge flap deflection, resulting in a reduction in the amplitude of lift fluctuation. Using SCB and trailing edge flap hybrid control can basically eliminate lift fluctuation. Moreover, due to the effect of SCB, the shock wave moves backward at the wing tip, and the lift coefficient slightly increases. From the pressure RMS contour, it can also be seen that the pressure fluctuation on the wing surface has basically disappeared. | ||||
| 11:50 | 12:15 | 6.7.3 |
WALL TEMPERATURE EFFECTS ON AERODYNAMIC HEATING MECHANISMS IN SHOCK WAVE TURBULENT BOUNDARY LAYER INTERACTION Z.Y. Tang, China; H.N. Xu, China; X.Y. Li, China; J. Ren, China The paper points out that the decrease of wall temperature leads to the decrease of the peak heat flux enhancement and reveals the underlying mechanism that is the near-wall turbulent aerodynamic heat dissipation variation with wall temperatures. The conclusion provides some insight about the difference between ground test and flight data, and can guide flow control methods by wall cooling. | ||||
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| 11:00 | 11:25 | 7.7.1 |
PSYCHOACOUSTICAL ANALYSIS OF SYNTHESIZED MOTOR-PROPELLER ROTOR SYSTEM NOISE J.H. Jeong, Korea Aerospace Research Institute, South Korea; J.W. Ko, Korea Aerospace University, South Korea The rapid growth of the eVTOL market has underscored the significance of social acceptance regarding noise. However, psychoacoustic understanding remains limited. Conventional numerical methods like CFD and VLM have limitations in capturing unique modulation characteristics. The psychoacoustic analysis addressed this gap using the CONA framework via RPM fluctuation modeling and auralization. | ||||
| 11:25 | 11:50 | 7.7.2 |
INFLUENCE OF MOTOR CHARACTERISTICS ON OPTIMAL PROPROTOR DESIGN S. Shahjahan¹, D. Verstraete¹; ¹The University of Sydney, Australia Proprotor designs often overlook the consideration of the vehicle's motor powertrain. Proprotors are optimised for an eVTOL vehicle employing three distinct electric motors with the same power rating but differs in maximum torque and rotational speed. Results indicate that the Pareto-optimal proprotor designs are significantly influenced by the specific powertrain to which they are coupled. | ||||
| 11:50 | 12:15 | 7.7.3 |
NOVEL SOFTWARE-DRIVEN VARIABLE-PITCH AND LEVEL FLIGHT CONTROL SYSTEM: PRINCIPLES AND APPLICATIONS FOR SMALL AIRCRAFT WITH A QUADROTOR CASE STUDY X. Xiong¹, S. Wu¹; ¹International WYNNBEAR Advanced AeroTech Innovation, United States An exploratory study presents the achievement of variable pitch using simple and reliable fixed pitch propellers. By employing multiple sets of propellers with different blade angles and employing clever layout and control strategies, propulsive efficiency can be increased by up to 35%. | ||||
| 12:15 | 12:40 | 7.7.4 |
CHALLENGES OF INTEGRATING PHOTOVOLTAIC CELLS ONTO THE WINGS OF AN UNMANNED SOLAR-POWERED AIRCRAFT R. Lopusiewicz¹, N. Ksiazek¹; ¹AGH University of Krakow, Poland Presenter: Roza Lopusiewicz, AGH University of Krakow The paper focuses on methods of integrating photovoltaic cells onto the wings of the aircraft we are constructing. In this work, we examine the results of electroluminescence tests and the characteristics of the modules generated on the automatic test station to identify the best method of securing the panels. | ||||
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| 11:00 | 11:25 | 8.7.1 |
SONIC BOOM ANALYSIS OF DIFFERENT SUPERSONIC AIRCRAFT A. Glorioso¹, F. Petrosino², M. Barbarino², G. Pezzella¹, A. Viviani¹; ¹University of Campania, Italy ;²CIRA, Italy Presenter: Antimo Glorioso, University of Campania The focus of this work is to evaluate and compare the sonic boom of three different supersonic aircraft concepts, developed in the European project MORE&LESS, through a numerical approach. Aerodynamic simulations were performed using the open-source solver SU2, while noise propagation from the aircraft to the ground was evaluated using an in-house code developed at Hamburg University TUHH. | ||||
| 11:25 | 11:50 | 8.7.2 |
SPARSE POLYNOMIAL CHAOS-BASED SONIC BOOM UNCERTAINTY QUANTIFICATION AND AERODYNAMIC/SONIC BOOM ROBUST DESIGN OPTIMIZATION UNDER MULTI-PARAMETER UNCERTAINTIES S. Wang¹, H. Zhao¹, K. Gan¹, Z. Gong¹, Y. Gan¹; ¹NORTHWESTERN POLYTECHNICAL UNIVERSITY, China This paper uses the AFBS method for aircraft aerodynamic/sonic boom uncertainty quantification. Establishing a multidisciplinary robust optimal design framework that conducts aerodynamic/sonic boom uncertainty quantification can meet the design requirements of the environment-friendly supersonic civil aircraft. | ||||
| 11:50 | 12:15 | 8.7.3 |
NUMERICAL EVALUATION FOR FAN-NOISE SHIELDING EFFECTS ON AFT-FUSELAGE MOUNTED AND EMBEDDED ENGINES T. Ikeda¹, R. Furuya, Ryoyu Systems, Japan; M. Murayama¹; ¹JAXA, Japan The fan-noise shielding effects are numerically compared for JAXA's low-noise aircraft design between the pylon mounted, and the boundary layer ingestion (BLI) engine configurations in a real scale at a take-off condition. Although both the configurations effectively shield fan noise by the airframe, the BLI configuration shows a better shielding capability through visualization. | ||||
| 12:15 | 12:40 | 8.7.4 |
REFINED PREDICTIONS COMPARED WITH THE PROPULSION AIRFRAME AEROACOUSTICS AND AIRCRAFT SYSTEM NOISE FLIGHT RESEARCH TEST DATA R.H. Thomas¹, Y. Guo, NASA Langley Reseach Center, United States; E.H. Nesbitt¹, I.A. Clark¹, J.C. June¹; ¹NASA Langley Research Center, United States To achieve improvements in aircraft noise prediction and understanding, NASA funded an ambitious aeroacoustic flight research effort, the PAA & ASN flight research test. It was formulated in a highly collaborative process between NASA and Boeing teams and conducted with a Boeing 787-10 aircraft. The paper describes some key aspects of the objectives and comparisons of data with the refined predictions with NASA’s ANOPP-Research code. | ||||
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| 11:00 | 11:25 | 9.7.1 |
SPEED GATED INTERCEPT PROCEDURE STUDY FOR INTEGRATION OF INCREASING DIVERSE OPERATIONS (IDO) AT EUROPEAN AIRPORTS T. Welsch¹, M.-M. Temme¹; ¹DLR, Germany Simulations show that Increasing Diverse Operations (IDO) will result in capacity losses at hub airports, as controllers will have to insert larger gaps between approaches with very different speed profiles. With the help of optimized intercept points on the final, a large part of this loss can be compensated. Thus, supporting the transformation towards individually optimized approach speeds. | ||||
| 11:25 | 11:50 | 9.7.2 |
VALIDATING FLOW-BASED EN ROUTE AMAN COUPLING ESCAPE LIGHT WITH AIRTOP SOFTWARE K. Sekine¹, P. Bouchaudon, EUROCONTROL Innovation Hub, France; T. Tatsukawa¹, K. Fujii¹, E. Itoh, The University of Tokyo, Japan; ¹Tokyo University of Science, Japan This study simulates air traffic to Tokyo International Airport (RJTT) to validate the mitigation of delay and operational feasibility of En Route AMAN coupling ESCAPE Light and AirTOp Software. The results show that En Route AMAN reduce not only the number of instructions but also the total flight time of RJTT arrivals. These results constitute an excellent initial step toward implementation. | ||||
| 11:50 | 12:15 | 9.7.3 |
ON THE POSITION ACCURACY NEEDED FOR SAFE SEPARATION OF FLIGHT ALONG CORRIDORS L.M.B.C. Campos¹, J.M.G. Marques, Escola de Ciências e Tecnologias, Universidade de Évora, Portugal; P.A. Serrão¹; ¹IDMEC/CCTAE - IST, Portugal Three probabilities of coincidence are applied to the old standard and new reduced vertical separations of 2000 ft and 1000 ft respectively, for comparison with the ICAO TLS, and also to assess their suitability as safety metrics. The possibility is raised of complementing the ICAO TLS 5E9 per hour, which is suitable for the cumulative probability of collision by two additional safety metrics. | ||||
| 12:15 | 12:40 | 9.7.4 |
FEASIBILITY STUDY ON OPERATIONAL FLIGHT PLANS ADAPTED FOR TRAJECTORY BASED OPERATION A. Harada, Kyushu University, Japan; N. Takeichi, Tokyo Metropolitan University, Japan; T. Masuki¹, H. Nakahata¹, S. Inohata¹, N. Nagata¹, A. Yasuda¹; ¹Japan Airlines Co., Ltd., Japan The original contribution of this research is to propose a fuel-optimal trajectory with sufficient buffers of flight time adjustment to be adaptable to ATC instructions, suitable for the OFPs in the future TBO concept. | ||||
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| 11:00 | 11:25 | 10.7.1 |
LASER SHEAROGRAPGY-PREDICTION AND OPTIMIZING ITS FLAW DETECTION CAPABILITIES USING AN ADVANCED HYBRID APPROACH Y. Elbaz, Technion, I.I.T.., Israel; H. Abramovich, Technion, I.I.T., Israel The present study presents a theoretical, analytical and experimental study of the engineering prediction of shearography fringe pattern. A methodology was developed and implemented as an easy to run simulation that can evaluate LST fringe pattern in advance. It focuses on a circular delamination flaw stimulated by vacuum excitation. It shows a good agreement with the performed experimental results. | ||||
| 11:25 | 11:50 | 10.7.2 |
FATIGUE PROPERTIES OF ADDITIVELY MANUFACTURED TOOL STEEL C.M. Johnston¹, L.C. Tshabalala¹, M. Davids, University of the Witwatersrand, South Africa; ¹CSIR, South Africa Tool-steel is routinely used in South African wind tunnels for wind tunnel model parts and instruments. Additive Manufacturing is useful in this regard however knowledge of the fatigue characteristics of the material is required. Test specimens were manufactured from AM powder, using Selective Laser Melting, and tested. The results are presented. | ||||
| 11:50 | 12:15 | 10.7.3 |
DEVELOPMENT AND ANALYSIS OF THE THEORY OF COMPOSITE EXPANSION RING UNDER ELECTROMAGNETIC LOADING Z.-X. Liu¹, J. Liu¹; ¹NORTHWESTERN POLYTECHNICAL UNIVERSITY, China NA | ||||
| additional information (interactive) | 10.7.R |
DEVELOPMENT OF A MACHINE LEARNING-BASED STRESS SPECTRUM ESTIMATION TECHNIQUE FOR FATIGUE MONITORING E.G. Park, South Korea; S.H. Jeong, South Korea; J.Y. Cho, South Korea; J.H. Kim, South Korea | |||||
| additional information (interactive) | 10.7.R |
FULLY-EMBEDDED PRESSURE SENSOR FOR AERODYNAMICS SURFACES BASED ON FBG TECHNOLOGY P.E. Boffa¹, E. Casciaro¹, P. Bettini¹; ¹Politecnico di Milano, Italy | |||||
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| 11:00 | 11:25 | 11.7.1 |
STOCHASTIC BUCKLING ANALYSES OF LAMINATED COMPOSITE PLATES UNDER HYGROTHERMAL, GEOMETRIC AND MATERIAL UNCERTAINTIES MODELED AS NON-GAUSSIAN RANDOM FIELDS H.E.A.A. Santos, Embraer S.A., Brazil; D.A. Rade, Aeronautics Institute of Technology, Brazil The paper proposes the evaluation of the effect of stochastic space-dependent temperature and moisture variations on the buckling response of laminated composite plates, considering both Gaussian and non-Gaussian random fields. Discussions and conclusions are brought justifying the importance of incorporating environmental uncertainties in the analysis and design of aerospace composite structures. | ||||
| 11:25 | 11:50 | 11.7.2 |
SANDWICH COMPOSITES SKIN PANEL OPTIMIZATION FOR THE COMMON RESEARCH MODEL WING Y.M. Meddaikar¹, J.K.S. Dillinger¹, W.R. Krüger¹, R. De Breuker, Delft University of Technology, Netherlands; G.H. Silva¹, P.H. Cabral², A.P. do Prado²; ¹DLR - Institute of Aeroelasticity, Germany ;²Embraer S.A., Brazil This paper presents an approach for optimizing practical commercial-scale aircraft wings using sandwich composites in a preliminary design stage. The approach uses lamination parameters as design variables in a continuous optimization step. Structural constraints for classic composite laminate design such as material failure and buckling, and for sandwich design such as crimping, wrinkling, dimpling and core shear failure are accounted for using industrial-standard and empirical methods driven by finite element analyses. As an application case, optimization studies are performed at a skin panel level on the open-source Common Research Model (CRM) wing. Optimization trends show areas of the wingbox where sandwich composites offer superior structural performance, as well as potential cost savings by requiring lesser number of stringers. The aim and novelty of this work is to present performance gains that can be achieved using sandwich composites in primary load-carrying aircraft structures when compared with monolithic composite designs and through this, to provide a motivation for further research and development in sandwich composites and their applications. | ||||
| 11:50 | 12:15 | 11.7.3 |
AEROELASTIC TAILORING BASED ON VIRTUALLY-GENERATED ALLOWABLES AND HIGH ORDER FINITE ELEMENTS FOR IMPROVED COMPOSITE WING AEROELASTIC TAILORING BASED ON VIRTUALLY-GENERATED ALLOWABLES AND HIGH ORDER FINITE ELEMENTS FOR IMPROVED COMPOSITE WING DESIGN P.H. Cabral¹, A.P. do Prado¹, E. Carrera², A. Pagani², A. Racionero Sánchez-Majano², M. Enea²; ¹Embraer S.A., Brazil ;²Politecnico di Torino, Italy This work proposes the use of progressive failure analysis to conceive new strain allowable curves to be used in aeroelastic tailoring of composite wing design. The allowable curves are generated by simulating coupons whose layup sequence may not fulfil some of the standard design rules. This allows us to explore different stacking sequences whose experimental testing would be unaffordable. | ||||
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| 11:00 | 11:25 | 12.7.1 |
STRUCTURAL AND AEROELASTIC OPTIMISATION OF A LARGE AIRCRAFT WING WITH A PASSIVE TWIST WINGTIP Y.J. Pan¹, M. Alam¹, A. Spinelli¹, E. Bragado Aldana¹; ¹Cranfield University, United Kingdom A multi-fidelity toolset for structural and aeroelastic analysis is needed for the multi-disciplinary optimisation of an overall aircraft design. This paper presents the use of structural analysis and aeroelastic tailoring tools in designing an optimised composite wing for a large aircraft. The optimisation of the composite wing structure is divided into two stages, adhering to multiple design constraints. The first stage focuses on minimising the wing structural weight subject to static strength and aeroelastic constraints, utilising the in-house Structural Layout Tool (SLoT) and Structural Analysis Tool (SAIT) that relies on skin-stringer panel and wing box elements developed at Cranfield University. Here, the skin-stringer panel sizing, including skin thickness, web thickness, and stringer sizing, are used as design variables. The second stage involves aeroelastic tailoring, where skin and spar laminate layups are modified using a high-fidelity Finite Element (FE) based optimisation program integrating NASTRAN with MATLAB. This aims to maximise the flutter speed for the designated wing design. Furthermore, this study explores the incorporation of a passive twist wingtip (PTWT) in the wing design as an additional module within this toolset. The PTWT design has specific length, shaft, and CG locations, and it replaces the fixed wingtip of the FE model built in the optimisation stages of SLoT and SAIT. This PTWT module chooses torque spring stiffness and mass as design variables, focusing on aeroelastic stability and gust response. Overall, this paper aims at demonstrating that using the design and optimisation of the current multi-fidelity toolset not only achieves weight optimisation but also produces advantageous aeroelastic characteristics, particularly in terms of flutter suppression and gust alleviation for large aircraft. | ||||
| 11:25 | 11:50 | 12.7.2 |
DEVELOPMENT OF A MASS EVALUATION TOOL FOR CLASSICAL AND DISRUPTIVE AIRCRAFT STRUCTURES V. Priasso¹, A. Lannoo¹; ¹DMAS, ONERA, France Presenter: Valentin Priasso, ONERA This presentation deals with a mass evaluation tool of an aircraft structure which uses semi-empirical and numerical models. It aims to be integrated into a Multi-Disciplinary Optimization (MDO) process for innovative aircraft. The optimization method is presented and some examples are detailed on both classical and disruptive aircraft structures. | ||||
| 11:50 | 12:15 | 12.7.3 |
STRUCTURAL DESIGN OF NEXT-GENERATION REGIONAL GREEN AIRCRAFT L. Pustina¹, F. Mastroddi¹, P. Della Vecchia, University of Naples “Federico II”, Italy; G. Cerino, LEONARDO, Aircraft Division, Italy; ¹Sapienza University of Rome, Italy This paper presents a novel approach for designing next-generation green aircraft, focusing on structural optimization. It employs a simplified FEM to minimize structural weight while maintaining structural integrity for several aircraft configurations, including those with unconventional powertrain architectures. | ||||
| 12:15 | 12:40 | 12.7.4 |
MULTIPHYSICS MODELING FOR SAFE BATTERIES USING LS-DYNA G. Di Mauro¹, M. Guida¹, G. Olivares², L.M. Gomez²; ¹University of Naples Federico II, Italy ;²Jerry Moran Center, AVET, NIAR, WSU, United States In this activity the possibility to simulate an abuse load scenario on a conventional battery is investigated throughout the use of the LS-DYNA commercial solver. Attention is dedicated to the adopted methodology, suitable for the analysis of both traditional and structural batteries, along with the parameter set up for the battery model and experimental tests needed to get the required data. | ||||
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| 11:00 | 11:25 | 13.7.1 |
AERO-THERMAL ANALYSIS OF A REUSABLE LAUNCH VEHICLE DURING RE-ENTRY MANOEUVRER A. Assonitis¹, R. Paciorri ¹, V. Orlandini¹, A. Neri, ESA ESRIN, Italy; ¹University of Rome La Sapienza , Italy Presenter: Valerio Orlandini, University of Rome La Sapienza This work focuses on the evaluation of thermal loads during the descent of a single stage reusable launcher, which decelerates via retro-propulsion: in detail, numerical computations of the thermo-fluid dynamic field will be carried out using the CFD++ software of METACOMP, that applies a conjugate heat transfer approach (CHT) to couple the fluid-dynamic thermal field with the solid thermal one. | ||||
| 11:25 | 11:50 | 13.7.2 |
RESEARCH ON AIRSPEED CORRECTION TECHNOLOGY OF EJECTION SEAT BASED ON CFD L. Jin¹, G. Feng¹, L. Wu¹; ¹Overall Technology R&D Department, AVIC Aerospace Life-support I, China This paper presents a method and technique to correct the total, static pressure and velocity of ejection seat in the ejection process by combining CFD simulation and successive iterative approximation algorithm. The correction error is less than 5%, which can meet the needs of engineering applications. | ||||
| 11:50 | 12:15 | 13.7.3 |
AEROACOUSTIC CAVITY FLOW ENERGY HARVESTING J.M. Kirkness-Duncombe¹, N.J. Lawson¹, G.A. Vio², S.D. Moss², D.J. Munk²; ¹The University of Sydney, Department of Aeronautical Engineering, Australia ;²Defence Science and Technology Group, Aerospace Division, Australia This paper explores the use of high-energy cavity environments as a power source for structural health mon- itoring systems. It focuses on harnessing the aeroacoustic energy in a rectangular cavity setting through the development and deployment of a relaxor-ferroelectric single-crystal energy harvester device. | ||||
| 12:15 | 12:40 | 13.7.4 |
NUMERICAL INVESTIGATION OF THE INTERACTION OF OPPOSING JETS AND SUPERSONIC FREE FLOWS Z.K. Liu¹, Y.L. Liu¹, Q.Z. Li¹, G. Wang¹; ¹Northwestern Polytechnical University, China A numerical study focuses on the interaction between shock waves and shear layers on the flow physics of an opposing jet by solving RANS. The results successfully replicate two distinct interaction modes, namely LPM and SPM. In addition, it’s find that DMD can enables the identification of the unstable modal structures and relevant temporal frequencies in analyzing the unsteady oscillatory in LPM | ||||
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| 11:00 | 11:25 | 14.7.1 |
FROM THA TO REAL-TIME MONITORING: INTEGRATING NEW VIEW OF SAFETY INTO FLIGHT TEST PROGRAMS T.F. Macedo¹, M.M. Cardoso Junior¹; ¹Technological Institute of Aeronautics, Brazil Presenter: MOACYR Cardoso-Junior, Technological Institute of Aeronautics This research proposes a novel approach that integrates newer safety philosophies based on continuous monitoring and control of system performance variability. Inspired by Hollnagel’s theory of resilient systems, we enhance THAs with indicators and limits to actively track how hazards manifest during flight tests. | ||||
| 11:25 | 11:50 | 14.7.2 |
REMOTE OBSERVATION EXPERIMENT OF VOLCANIC ASH USING POLARIZATION LIDAR H. Inokuchi¹, H. Oikawa¹, G. Morimoto, Metro Weather Co., Ltd, Japan; S. Inaka¹; ¹JAXA, Japan We are in development of an airborne volcanic ash detection lidar to remotely detect volcanic ash and to determine its degree of danger. Prior to observation flights, we conducted a ground observation experiment. The results indicated the correlation between the lidar reception intensity and the mass concentration of volcanic ash. | ||||
| 11:50 | 12:15 | 14.7.3 |
COMPARATIVE ANALYSIS OF EVTOL, DRONE AND GROUND TRANSPORTATION SYSTEMS FOR EMERGENCY DELIVERY OF BLOOD-DERIVED MEDICATION D. Angelini¹, E. Cestino¹, D. Cestino², F. Cattel²; ¹Politecnico di Torino, Italy ;²A.O.U. Città della Salute e della Scienza di Torino, Italy This study compares eVTOL aircraft and drones to traditional ground transport to deliver blood-derived medicines in emergency scenario. It uses risk maps, demographic data, and optimal path algorithm to find efficient routes. Using a figure of merit eVTOLs excel in urgent deliveries, while cars are better for routine tasks. The study investigates also hub placements to improve the delivery sistems | ||||
| 12:15 | 12:40 | 14.7.4 |
ENABLING AIRWORTHINESS SECURITY BY A HOLISTIC SECURITY ENGINEERING PROCESS AT VARIOUS AIRCRAFT DESIGN LEVELS M. Blecken¹, H. Hintze¹, R. God¹; ¹Hamburg University of Technology, Germany This paper introduces a holistic security engineering methodology that enables airworthiness security in accordance with the certification specification CS-25.1319. By applying model-based methods and by connecting various aircraft design levels a continuous flow of security information is enabled. Thus, consistency and traceability is ensured which finally facilitates aircraft certification. | ||||
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| 11:00 | 11:25 | 15.7.1 |
DYNAMICS OF THE MECHANISM FOR VENTILATION ACROSS FEATHERS IN FLAPPING WING UAV R.C. Silva¹, D.D. Bueno¹; ¹UNESP, Brazil The work is focused into understanding the dynamics of feathered flapping-flight. The problem under investigation is the dynamic formation of ventilation channels between flexible feathers in a flapping wing model. The understanding of the physics from this ventilation mechanism is relevant for increasing efficiency of the flapping flight from bio-inspired unmanned aerial vehicles. | ||||
| 11:25 | 11:50 | 15.7.2 |
TRAJECTORY OPTIMIZATION OF EVTOL VEHICLES FOR URBAN AIR MOBILITY USING INDIRECT METHODS K. Mall¹, R. Gadre¹, J. Gerardus¹, D.A. DeLaurentis¹; ¹Purdue University, United States This paper is first instance of using advanced indirect methods of optimization for finding optimal cruise, descent, and landing phases of eVTOL vehicles for UAM missions. Such optimization has not been studied much and would be needed to make UAM more profitable and feasible. Government agencies, companies, and university researchers in the UAM domain will benefit from this study. | ||||
| 11:50 | 12:15 | 15.7.3 |
IN-FLIGHT VIBRATION SIGNAL BASED DETECTION AND LOCALIZATION FOR UAV PROPELLER ANOMALIES UNDER UNCERTAINTY VIA MACHINE LEARNING TYPE METHODS I.A. Iliopoulos¹, J.S. Korolis¹, S.D. Fassois¹, J.S. Sakellariou¹; ¹University of Patras, Greece In this study, an unsupervised machine learning method for in-flight vibration-based anomaly detection in UAV propellers is presented. Effective detection of single and multiple rotor faults in various configurations may be accomplished using vibration signals, even from a single sensor, ensuring the safety and reliability of UAV operations. | ||||
| additional information (interactive) | 15.7.R |
DESIGN OF ATTITUDE CONTROL SYSTEM FOR DRAGONFLY-INSPIRED FLAPPING WING AERIAL VEHICLE L. Wang¹, X. Yang¹, Y. Luo¹, H. Chen¹, J. Li¹; ¹NORTHWESTERN POLYTECHNICAL UNIVERSITY, China | |||||
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| 11:00 | 11:25 | 16.7.1 |
AN ONTOLOGY-BASED APPROACH FOR THE CO-DEVELOPMENT AND OPTIMIZATION OF AIRCRAFT CABIN DESIGN AND ASSEMBLY ARCHITECTURES Y. Ghanjaoui¹, J.H. Bussemaker¹, J. Biedermann¹, B. Nagel¹; ¹DLR, Germany To address the challenges faced by the aeronautical industry concerning sustainability and the growing demand for aircraft, it is crucial to evaluate innovative technologies at early design stages. This should include their impact on the overall architecture in terms of design and assembly. This work introduces an ontology-based approach for co-development and optimization in the aircraft domain. | ||||
| 11:25 | 11:50 | 16.7.2 |
FRICTION RIVETING OF THERMOPLASTIC COMPOSITE WITH A CNC MACHINE: EXPERIMENTAL WORK I. Tan¹, G. Cohen¹, A.-C. Araujo¹, A. Daidié¹; ¹Institut Clément Ader, France Friction riveting is an innovative joining technique which presents a good alternative to assemble thermoplastic composite. This work studies the feasability of a riveting process in two phases: implantation and closing of the rivet head by friction. Experiments are performed using a CNC machine with internal and external sensors in order to understand the impact of process parameters on the joint | ||||
| 11:50 | 12:15 | 16.7.3 |
PRELIMINARY RESULTS FOR AN INSTRUCTION DESIGN PROCEDURE IN AERONAUTICAL MANUFACTURING M. Bartolomei¹, F. Barravecchia¹, L. Mastrogiacomo¹, F. Franceschini¹, F. Acerra², D.M. Gatta², D. Cannizzaro²; ¹Politecnico di Torino, Italy ;²Leonardo S.p.A, Italy This study introduces a systematic approach to enhance assembly instruction design protocols in aerospace manufacturing. It incorporates a detailed taxonomy of assembly-related information to assist designers in formulating instruction content, and subsequently applies dual evaluation criteria to determine the most effective and comprehensive format for delivering instructions. | ||||
| 12:15 | 12:40 | 16.7.4 |
SURFACE MORPHOLOGY AND MICROSTRUCTURAL FEATURES OF ELECTRON BEAM SURFI-SCULPTED TI-6AL-4V ALLOY K. Li¹, P. Fu¹, Z. Tang¹, B. Zhang¹, Y. Ma, Chongqing University of Technology, China; ¹AVIC Manufacturing Technology Institute, China A Ti64 alloy was employed for electron beam processing to produce surface textures efficient for fluid-drag reduction. The as-resulted surface was characterized by parallel ridges and grooves. The near-surface was occupied by fusion zone, heat-affected zone and base metal. Processed wing models exhibits a reducing efficiency over 15%. | ||||
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| 11:00 | 11:25 | 17.7.1 |
MIXED REALITY FOR AIRCRAFT STRUCTURAL DENT AND BUCKLE NON-DESTRUCTIVE EVALUATION A.-K. Koschlik¹, M.J. Scott², T. Keser¹, F. Rauscher¹, H. Meyer¹, W. Verhagen², P. Marzocca², F. Raddatz¹, G. Wende¹; ¹DLR, Germany ;²RMIT, Australia new integrative process for the evaluation of dent and buckels of an airplane including integration into digital twin for future automation and AR assessment for mechanics for advanced decision making | ||||
| 11:25 | 11:50 | 17.7.2 |
CINNABAR PROJECT - AUGMENTED REALITY WORKFLOW FOR AIRCRAFT DENT & BUCKLE INSPECTION T. Keser¹, R. Schmied-Kowarzik¹, A.-K. Koschlik¹, L. Kaschub², M.J. Scott, RMIT University, Australia; R. Rodeck², G. Wende²; ¹German Aerospace Center (DRL), Germany ;²German Aerospace Center (DLR), Germany Conventional aircraft Dent & Buckle inspection is a time-intensive task. The CINNABAR project introduces an Augmented Reality (AR) supported workflow. This paper approaches object tracking on HoloLens using infrared-reflective markers to detect the aircraft pose and align visualizations. The preliminary assessment results show high potential and usefulness for the introduced AR system. | ||||
| 11:50 | 12:15 | 17.7.3 |
CINNABAR PROJECT: EXAMINING REQUIREMENTS FOR USER ACCEPTANCE OF AIRCRAFT STRUCTURE INSPECTION IN AUGMENTED REALITY R. Schmied-Kowarzik¹, T. Keser¹, L. Kaschub¹, A.-K. Koschlik¹, R. Rodeck¹, G. Wende¹; ¹German Aerospace Center (DLR), Germany This paper examines whether an Augmented Reality approach is applicable to help overcome challenges in aircraft structure inspection through a user study. The focus lies on the methodology and conduction of the user study to ensure that the implementation is acceptable, usable, and functions correctly. | ||||
| 12:15 | 12:40 | 17.7.4 |
CINNABAR PROJECT – COST-BENEFIT ANALYSIS OF DIGITAL PROCESSES FOR NON-DESTRUCTIVE INSPECTIONS OF AIRCRAFT STRUCTURES J. Aigner¹, A.-K. Koschlik¹, H. Meyer¹, F. Raddatz¹, G. Wende¹; ¹German Aerospace Center (DLR), Germany The study focuses on the cost-benefit analysis of implementing digital processes for aircraft inspection using state-of-the-art laser-scanning technology, augmented reality, and digital twins. The findings offer valuable insights for aircraft maintenance companies and decision-makers regarding the feasibility and potential benefits of adopting digital processes for structural aircraft inspection. | ||||
| additional information (interactive) | 17.7.R |
DIGITAL TWIN OF AN AIRCRAFT LANDING GEAR TO ENHANCE FAILURE ANALYSIS AND MANAGE PREDICTIVE MAINTENANCE D.Y. Sabag¹, O. Yakimenko, Naval Postgraduate School, United States; H. Alian¹; ¹Israeli Air Force, Israel | |||||
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| 14:30 | 14:55 | 1.8.1 |
SAFRAN PROPULSION STRATEGY AND ROADMAP FOR FUTURE SUSTAINABLE AVIATION D Dijoud, France Safran is advancing pioneering integrated systems and technologies as part of its sustainability roadmap. The CFM RISE program is now concrete, with more than 250 tests completed moving forward to module-level tests. Additionally to ultra-efficient propulsive systems, Safran has been actively working to unlock the potential of electric/hybrid propulsion through promising demonstrators. | ||||
| 14:55 | 15:20 | 1.8.2 |
MTU’S ROADMAP TOWARDS SUSTAINABLE PROPULSION F. Donus, MTU, Germany invited speaker for the Global Sustainable Aviation track | ||||
| 15:20 | 15:45 | 1.8.3 |
DELIVERING THE ROLLS-ROYCE NET ZERO ROADMAP T Newby, Rolls-Royce plc, United Kingdom Invited speaker for the Global Sustainability Aviation Track | ||||
| 15:45 | 16:10 | 1.8.4 |
Q&A - MINI PANEL QA A, Q&A - MINI PANEL | ||||
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| 14:30 | 14:55 | 2.8.1 |
BOEING CONTRIBUTIONS TO THE CRM-HL ECOSYSTEM K. Hood, United States Boeing contributions to the High Lift Common Research Model Ecosystem include a 6% scale model of the CRM-HL as well as, in partnership with NASA, a roadmap for the incorporation of icing impacts on high-lift aerodynamics through experimental testing within the CRM-HL Ecosystem. The Boeing 6% scale CRM-HL model has been designed to be as modular as possible and capable of testing at a variety of dry air wind tunnel facilities. Artificial ice testing using a range of representative shapes at a range of flight conditions and configurations is needed to inform computational improvements. We will present an overview of key 6% Boeing CRM-HL Model features, model capabilities, and a summary of clean and iced results from the first entry at the QinetiQ 5-Metre Low-Speed Wind Tunnel. | ||||
| 14:55 | 15:20 | 2.8.2 |
TEST SUMMARY OF THE FULL-SPAN HIGH-LIFT COMMON RESEARCH MODEL AT KHI AERO-ACOUSTIC LOW-SPEED WIND TUNNEL T. Hashioka¹, Y. Murahashi¹, H. Yasuda¹, Y. Sawaki¹, S. Onda¹, Y. Tsuchimoto¹, Y. Nishizaki¹, W. Suzuki¹, T. Kawamura¹; ¹Kawasaki Heavy Industries, Ltd., Japan Kawasaki Heavy Industries, Ltd. (KHI) introduced 3.23% CRM-HL model as a check model for the Kawasaki Low speed aero-acoustic Wind Tunnel (KLWT) has 3 * 3m test section in 2022. In this paper, test results in Jan.2023 are summarized with related CFD results after some introduction about KLWT and its CRM-HL model. | ||||
| 15:20 | 15:45 | 2.8.3 |
ACTIVITY PLANS USING CRM-HL AT JAXA M. Kohzai, Japan JAXA plans to fabricate an 8% CRM-HL half-span model to obtain validation data for our CFD based stall prediction tool and to demonstrate airframe noise reduction effect with a common high-lift configuration. Specifications of our model under fabrication, purpose of wind tunnel tests, and initial test plans are introduced. | ||||
| 15:45 | 16:10 | 2.8.4 |
PANEL DISCUSSION P D, United States PANEL DISCUSSION | ||||
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| 14:30 | 14:55 | 3.8.1 |
LARGE LANGUAGE MODEL IN AIRCRAFT SYSTEM DESIGN P. Krus, Linköping University, Sweden The objective in this paper is to demonstrate how large language models models such as ChatGPT-4 can revolutionize the automation of the engineering design process. In this paper the configuration of aircraft hybrid propulsion systems is studied. It is shown how a system configuration can be generated and presented in the form of UML component diagrams and how it can be simulated. | ||||
| 14:55 | 15:20 | 3.8.2 |
APPLYING MODEL-BASED SYSTEM ENGINEERING AND DEVOPS ON THE IMPLEMENTATION OF AN AI-BASED COLLISION AVOIDANCE SYSTEM T. Stefani¹, J.M. Christensen¹, E. Hoemann¹, A. Anilkumar Girija¹, F. Köster, DRL, Germany; T. Krüger¹, S. Hallerbach¹; ¹DLR, Germany The work is demonstrating an efficient way of an agile DevOps approach for implementing and testing an AI-based collision avoidance system, while complying to the W-model published by EASA. From high-level requirements to verification and validation, the engineering process is executed by Model-based System Engineering using SysML. | ||||
| 15:20 | 15:45 | 3.8.3 |
A HUMAN-CENTERED SYSTEMS ENGINEERING APPROACH FOR INTEGRATING ARTIFICIAL INTELLIGENCE IN AVIATION: A REVIEW OF AI SYSTEMS L.D.O. Morais¹, P. Krus, Linköping University, Sweden; L. Pereira¹; ¹UFABC, Brazil The introduction of AI Systems in the design of aeronautical products inserts new layers of complexity into Systems Engineering methods, impacting also human factors aspects. The clarity of information for pilots is a great concern for the aviation industry. This paper aims to provide a review of AI Systems applications in aviation and their relationship with human factors and systems engineering. | ||||
| 15:45 | 16:10 | 3.8.4 |
AN AUTONOMOUS SYSTEM FOR DOCKING AND BATTERY SWAPPING IN UAVS I. Kute¹, J. Dagli¹, E. Khot¹, R. Verma¹, P. Gupta¹, D. Shukla¹, R. Pant¹; ¹Indian Institute of Technology Bombay, India, India This study covers a robotic docking and battery swapping system for UAVs. As UAVs are utilized for a wide range of applications, from surveillance to package deliveries, the demand for UAVs with enhanced functionality and autonomy is on the rise. To achieve optimal performance and autonomy, the battery life of an UAV is a crucial factor. However, limited battery life necessitates the development of new technologies to increase the in-air time of UAVs. Many UAVs lose significant energy during take-off and landing thus leading to more reasons for adopting battery swapping systems. Unfortunately, existing battery-swapping systems are often complex and expensive to manufacture. Our mission is to showcase a simple yet effective robotic docking and battery swapping system made from readily available materials that can execute at altitudes of 500 feet or higher. To accomplish this, we will employ a custom, stable aerostat to launch the robotic system into the air. Ultimately, we envision creating a hub where various UAVs can land, dock, swap batteries, and continue their operations with renewed energy while their old batteries are being charged. | ||||
| additional information (interactive) | 3.8.R |
AUTOMATING THE VERIFICATION OF GEOMETRIC REQUIREMENTS FOR AIRCRAFT FUEL SYSTEMS USING KNOWLEDGE-BASED ENGINEERING B. Boden¹, M. Padilha¹, T. Burschyk¹, C. Cabaleiro de la Hoz¹, E. Moerland¹, M. Fioriti, Politecnico di Torino, Germany; ¹DLR, Germany | |||||
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| 14:30 | 14:55 | 4.8.1 |
A DESIGN APPROACH FOR A MODEL-SCALE VTOL POWERED BY TWO PIVOTING KEROSENE TURBINES T. Müller¹, V. Gollnick¹; ¹Institute of Air Transportation Systems, Germany The Institute of Air Transportation Systems is developing an innovative VTOL model with kerosene turbines for research and student projects. It is designed for various missions such as disaster monitoring and vehicle jettisoning. The paper outlines the design process, two main concepts, calculations and future steps to realise this aircraft. | ||||
| 14:55 | 15:20 | 4.8.2 |
ENERGY AND EMISSION ANALYSIS OF AN AIR-TAXI SERVICE USING DYNAMIC EVTOL SYSTEM MODELS N. Prabhakar¹, F. Salucci¹, D. Karbowski¹; ¹Argonne National Laboratory, United States Electric Vertical Take-off and Landing (eVTOL) Vehicles, given their size and power requirements can serve as the perfect test-beds to study the feasibility of sustainable powerplants. At Argonne National Laboratory, we have been developing a 6-degrees of freedom eVTOL model, using Aeronomie to understand, predict, and eventually optimize the impact these aircraft will have on our current energy, emissions, and mobility infrastructure. This model can simulate the aircraft and powerplant dynamics for a thrust-vectoring eVTOL aircraft. In this paper we will analyze a hypothetical air-taxi service during the LA 2028 Olympics. Vertiports will be located at major stadiums around the city, which will be connected through eVTOL air-taxis. The final paper will discuss total energy use and emissions for different fleet sizes and estimate charging-turnaround time relationships for such a service. | ||||
| 15:20 | 15:45 | 4.8.3 |
SCALED FLIGHT TESTING FOR EVALUATING DISTRIBUTED ELECTRIC PROPULSION H. Jentink, Royal Netherlands Aerospace Centre NLR, Netherlands; C. Döll, ONERA, France; P. Iannelli, CIRA, Italy; M. Hoogreef, TU Delft, Netherlands; D. Kierbel, Airbus, France The scaled flight testing methodology is applied, first on a known aircraft configuration with jet engines and on an aircraft configuration with distributed electric propulsion through six electrically driven propellers. Especially the dynamics and control of the aircraft is studied. Results from wind tunnel tests, taxi tests and flight tests are presented. | ||||
| 15:45 | 16:10 | 4.8.4 |
DETERMINISTIC HYBRID POWER RATIOS CONSIDERING VARIOUS FAILURE CASES FOR QUAD TILTROTOR AIRCRAFT M. Park¹, N. Roh¹; ¹Hanwha systems, South Korea Presenter: Minjun Park, Hanwha Systems This paper proposes deterministic hybrid power ratios for a light series hybrid electric propulsion system in a generic quad tiltrotor aircraft, guided by five sizing rules. It compares four failure scenarios against three, with a focus on reducing aircraft weight. The paper also suggests the best configuration of the hybrid power sources, specifically tailored to the current battery technology. | ||||
| Reserve Paper | 4.8.R |
RETROFITTING A JET DRIVEN UAV TO FORM A MULTI-PURPOSE TEST PLATFORM D. Teubl¹, T.B. Sissing¹, M. Hornung¹; ¹Chair of Aircraft Design, Technical University of Munich, Germany | |||||
| Reserve Paper | 4.8.R |
A STUDY ON BATTERY SEPARATION DRONES TO EXTEND ENDURANCE H. Kim¹, T. Kim, Seoul Digital University, South Korea; C. Son¹; ¹Cheongju University, South Korea | |||||
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| 14:30 | 14:55 | 5.8.1 |
LAUNCH SYSTEM ASSESSMENT OF AN EXPERIMENTAL HYPERSONIC SCRAMJET VEHICLE F. Cascone¹, P. Roncioni¹, O. Russo¹, M. Marini¹, S. Di Benedetto¹, M. Albano², R. Bertacin², G. Ranuzzi²; ¹CIRA, Italy ;²ASI, Italy Presenter: Pietro Roncioni, CIRA This paper explores the aerodynamic analysis of a Hypersonic Scramjet System in a national research project co-funded by CIRA and ASI. The system includes a winged rocket-based launch vehicle and a Scramjet Hypersonic Experimental Vehicle (SHEV) designed for leveled hypersonic flight. The study aims to validate key technologies for hypersonic flight, focusing on aerodynamic balance and efficiency. | ||||
| 14:55 | 15:20 | 5.8.2 |
STABILITY CHARACTERISTICS OF CROSSFLOW MODES IN HYPERSONIC BOUNDARY LAYER WITH EXPANSION CORNER P. Lu¹, Y. Xi¹, J. Sun¹, S. Fu¹; ¹Tsinghua University, China The expansion corner is a common feature on hypersonic vehicles, which has a significant impact on transition. This study investigates how the expansion corner affects instabilities of Mach 6 swept wing boundary layer flows. Results show that the expansion corner increases the growth rate of the most unstable stationary crossflow mode in this case. | ||||
| 15:20 | 15:45 | 5.8.3 |
NUMERICAL INVESTIGATION OF HYPERSONIC FLOWS C.-S. Dikmen¹, M.-N. Yüksel¹, M. Yumusak¹; ¹Roketsan, Turkey The aerothermodynamic effects of high-enthalpy hypersonic flows are considered as vital for hypersonic flow studies. The change between perfect gas flow and chemically reacting flow at hypersonic Mach numbers may be detrimental; therefore, analysts and designers should carefully investigate these changes starting from the basic test geometries. A series of CFD runs are executed using a cylindrical geometry and a double-cone geometry. The results do not only demonstrate the effect of thermochemical changes on the flow field but also how two commercial flow solvers such as ANSYS Fluent and METACOMP CFD++ perform under similar numerical conditions. It is clear that ignoring mentioned effects at critical locations may not be acceptable and flow properties just around the surface of the object and surface loadings may be missed. | ||||
| 15:45 | 16:10 | 5.8.4 |
DETACHED EDDY SIMULATION OF HYPERSONIC SHOCK-WAVE/BOUNDARY-LAYER INTERACTIONS ON HIFIRE-1 AXISYMMETRIC CONE-CYLINDER-FLARE R.O. Bura, Republic Indonesia Defense University, Indonesia; A. Riyadl, National Research and Innovation Agency, Indonesia Presenter: Romie Bura, Republic of Indonesia Defense University In the present work, the turbulent Shock-Wave/Boundary-Layer Interactions (SWBLIs) over a geometry model of HIFiRE-1 Axisymmetric Cone-Cylinder-Flare with a ramp angle of 7 and 33 degrees were analyzed. Detached Eddy Simulation (DES) and k-? turbulence models were used and the simulation results were compared to the experimental result of HIFiRE-1 ground test studies. | ||||
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| 14:30 | 14:55 | 6.8.1 |
NUMERICAL SIMULATION OF FLOWS AROUND AN AIRFOIL DURING ACCELERATED AND DECELERATED FLIGHT R. Yamashita, The University of Tokyo, Japan Numerical simulations are performed to analyse flows around a NACA64A006 airfoil during accelerated and decelerated flight. Computational results show that flow behaviours differ according to the flight phase. The rear shock wave during the decelerated flight persists even in subsonic regions. This leads to hysteresis phenomenon of aerodynamic forces between the accelerated and decelerated phases. | ||||
| 14:55 | 15:20 | 6.8.2 |
NUMERICAL INVESTIGATION ON AERODYNAMIC PERFORMANCE OF HOVERING ROTOR IN GROUND EFFECT X.-L. Li¹, J.-H. Xu¹, W.-P. Song¹, S.-Q. Han, Sichuan University, China; Z.-H. Han¹; ¹ Northwestern Polytechnical University, China The flow and aerodynamic characteristics of S-76 rotor in hover are investigated, for both out-of-ground-effect (OGE) and in-ground-effect (IGE). For IGE, the thrust coefficients inside the blade are larger, which is also confirmed by pressure distribution. In addition, large press bumps and flow separations are observed near the tip under OGE, but there is no phenomenon these under IGE. | ||||
| 15:20 | 15:45 | 6.8.3 |
NONLINEAR DROPLET DYNAMICS IN IDEALIZED TRAILING VORTICES O. Avni¹, Y. Dagan¹; ¹Technion - Israel Institute of Technology, Israel We explore droplet-vortex interactions in trailing vortices, in which transport phenomena such as evaporation, condensation, and mass transport are significant. Our preliminary results illuminate the complex interactions between carrier flow, droplet dynamics, and environmental conditions, uncovering underlying physical mechanisms. | ||||
| 15:45 | 16:10 | 6.8.4 |
FLYING WING CIRCULATION DISTRIBUTIONS, AERODYNAMIC PERFORMANCE AND WAKE ROLL-UP H.W.M. Hoeijmakers¹, M.P.J Sanders¹, L.H. Groot Koerkamp¹, A. van Garrel¹, C.H. Venner¹; ¹University of Twente, Netherlands Prandtl’s Lifting-Line theory is used to predict aerodynamic characteristics of wings with various distributions of circulation, including bell-shape distributions. Expressions for induced upwash distribution, lift, drag, bending moment, yawing moment and center-of vorticity are derived for numerically-computed or prescribed distributions of the circulation. Analysis includes computation of vortex wake roll-up. | ||||
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| 14:30 | 14:55 | 7.8.1 |
ANALYSIS OF AN ELECTRICAL-POWERED-DUCTED-THRUST VECTORING-FLAP V. Gollnick¹, J. Luehrmann¹, F. Danquah¹, A. Semke¹, T. Mueller¹, J. Thoeben¹; ¹Hamburg University of Technology, Germany The Lilium-Jet is fascinating aviation community. However only a few technical information is available, the research question is about a better understanding of the design concept. An experimental study about the behaviour of the Ducted Fan Flap wing concept is presented. The experimental approach and achieved results are presented. A summary and perspective of the next steps is given. | ||||
| 14:55 | 15:20 | 7.8.2 |
AERODYNAMIC INTERACTION EFFECTS OF TILTROTOR EVTOL AIRCRAFT C. Moreira¹, C. Breitsamter¹; ¹Technical University of Munich, Germany A wind tunnel model was specifically designed for investigating wing-propeller aerodynamic interactions of eVTOL aircraft including vectored thrust mechanisms. This work describes the model and offers time-resolved load and pressure data, as well as PIV images of the wake, for wing-propeller configurations considering various propeller tilt angles between 0 and 90 degrees. | ||||
| 15:20 | 15:45 | 7.8.3 |
PIV AND AERODYNAMIC FORCES ANALYSIS OF A HELICOPTER OPERATING AROUND A BUILDING BY WIND-TUNNEL EXPERIMENTS R. Bardera¹, J.C. Matias¹, E. Barroso¹; ¹Instituto Nacional de Técnica Aeroespacial, Spain This study analyses the aerodynamic interaction between a cube-shaped building and helicopter. The results are provided by a 1:100 scaled models tested in wind-tunnel and include measurements of aerodynamic mean forces, moments, fluctuations and flow visualizations with Particle Image Velocimetry when the helicopter is hovering in multiple positions close to the building. | ||||
| 15:45 | 16:10 | 7.8.4 |
EXPERIMENTAL AND NUMERICAL INVESTIGATION ON AERODYNAMIC PERFORMANCE OF A MARS ROTOR SYSTEM Y. Liu¹, J. Xiao¹, N.A. Benai-dara¹, Z. Chen¹, N. Qin, University of Sheffield, United Kingdom; ¹NUAA, China Due to the recent advancements in electric propulsion drives and their application on the Mars helicopters, contrarotating propulsion systems have emerged as a promising solution. These systems offer aerodynamic advantages by efficiently recovering a significant portion of the slipstream rotational energy that would otherwise be lost when using conventional screw propeller systems; therefore, it is necessary to determine the most optimal combination of possible propulsion system components for a given mission profile. This paper presents an investigation on the aerodynamic performance of a contra-rotor system at high altitudes through both experimental and numerical methods. All experimental research was conducted at the NanJing University of Aeronautics and Astronautics (NUAA) High-Altitude Research Facility. The High-Altitude Simulator has an inner diameter and height of 800mm and 2000mm, respectively. It can simulate atmospheric density and pressure at an altitude of 30-50 kilometers. Computational research was conducted using a steady RANS CFD code with multiple meshes to investigate the sensitivity of computational modeling to contra-rotors. Based on the experimental results, the collective pitch angle effects and Reynolds number effects on the lift-drag characteristics and efficiency of the single/contra-rotor system are investigated during the hovering process with Reynolds number ranging from 15,000 to 50,000 (using the chord and speed at 75% of the blade radius) and tip speed ranging from 35m/s to 75m/s. The aerodynamic measurement results of coaxial rotor show that the thrust reduction of lower blade under the influence of upper blade is up to 40%. | ||||
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| 14:30 | 14:55 | 8.8.1 |
A HYBRID APPROACH FOR RECONSTRUCTION OF TRANSONIC BUFFET AERODYNAMIC NOISE: INTEGRATING RANDOM FOREST AND COMPRESSIVE SENSING ALGORITHM Q. Zhang, Northwestern Polytechnical University, China; W. Zhang, Northwestern Polytec, China In response to the difficulty in obtaining high-precision aerodynamic noise data, this paper establishes a comprehensive standardization process for predicting the transonic buffet aerodynamic noise of RAE2822 airfoil. Firstly, a prior criterion is proposed based on flow correlation and the prediction accuracy of the Power Spectral Density (PSD) using the Random Forest (RF) algorithm. Subsequently, we determine whether the RF algorithm can be employed to directly obtain high-precision PSD results using this criterion. Successful PSD prediction is specifically determined when monitoring points simultaneously satisfy RMSE_corr<0.05 and RMSE_adj<0.05, the RMSE_corr represents the Root Mean Square Error (RMSE) of the auto-correlation and the cross-correlation coefficients, and the RMSE_adj indicates the RMSE of the PSD for the adjacent monitoring points. If not, we introduce an innovative approach by embedding the RF model into the Compressed Sensing algorithm reconstruction process (RF_CS). This method efficiently achieves high-precision Overall Sound Pressure Level (OASPL) and PSD reconstruction based on sparse sensor positions, demonstrating good robustness and generalization capabilities. Compared to the CS algorithm based on Proper Orthogonal Decomposition (POD_CS), this method achieves high-precision PSD (OASPL) reconstruction, with the RMSE has been reduced by a factor of 2 to 50 using 22 (9) sensor positions and 15 (12) basis functions, and the method does not exhibit phenomena such as high-frequency distortion or inflection point distortion. | ||||
| 14:55 | 15:20 | 8.8.2 |
AEROACOUSTICS INVESTIGATION OF PROPELLER LEADING EDGE TUBERCLES APPLIED TO ADVANCED AIR MOBILITY D. Skrna, Austria; M. de Rosa Jacinto, Brazil; M. Berens, Germany Presenter: Dominik Skrna, Technische Universität Wien This paper evaluates the potential of applying leading-edge tubercles to propellers to be used in advanced air mobility vehicles in order to reduce their noise emission. The geometry is parameterized and multiple designs are assessed aerodynamically and acoustically via simulations. The influence of each parameter and the effectiveness of such modifications to reduce propeller noise are discussed. | ||||
| 15:20 | 15:45 | 8.8.3 |
OPERATIONAL LIMITS ASSESSMENT FOR HIGH-ALTITUDE LONG-ENDURANCE UAVS CONSIDERING PROPELLER ICING EFFECT Y.H. Kim, South Korea; J.-H. Shin, South Korea; C.J. Woo, South Korea; C.K. Son, South Korea; K.J. Yee, South Korea This study evaluates the operational limitations of a HALE UAVs by simulating the entire airframe, including the propeller, in an icing environment. Two-dimensional (BEMT) and three-dimensional (MRF) analyses are performed to predict propeller icing and analyze its aerodynamic effects. The conclusions highlight the impact of propeller icing on the operational limits of HALE UAVs. | ||||
| 15:45 | 16:10 | 8.8.4 |
NUMERICAL SIMULATION OF THE RESPONSE CHARACTERISTICS OF THE WING STRUCTURE OF A SEAPLANE PLANING IN WAVE Z.-W. Lu¹, Y.-H. Li¹, J.-C. Chen¹, M.-B. Tong¹, B. Wu¹; ¹Nanjing University of Aeronautics and Astronautics, China Research on the wing structure response characteristics during the wave of seaplanes is limited, and conducting relevant experiments is challenging. Therefore, in the study utilizes numerical simulation methods to study and analyze the motion response and wing structure response characteristics of large seaplanes during hydroplaning process. | ||||
| additional information (interactive) | 8.8.R |
NUMERICAL-THEORETICAL EVALUATION OF THE DITCHING OF A HULL WITH DIHEDRAL ANGLES BETWEEN -5 AND 20 DEGREES D. Guagliardo¹, E. Cestino¹, A. Virdis¹, A. Alfero¹, V. Sapienza¹; ¹Politecnico of Turin, Italy | |||||
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| 14:30 | 14:55 | 9.8.1 |
OVERVIEW OF FACTORS RELATED TO AIRCRAFT OPERATION ASSOCIATED WITH A NEGATIVE IMPACT ON THE ENVIRONMENT D. Kacik, Warsaw University of Technology, Poland This paper presents the overview of the state of the science regarding factors related to aircraft operation that are associated with a negative impact on the environment as of early 2024. It lists the current status of science and remaining uncertainties as well as measures that have been lately undertaken to overcome aviation’s unfavourable effect on our planet. | ||||
| 14:55 | 15:20 | 9.8.2 |
A COMPREHENSIVE METHODOLOGY FOR PERFORMING PROSPECTIVE LIFE CYCLE ASSESSMENTS OF FUTURE AIR TRANSPORT SCENARIOS F. Pollet¹, T. Planès¹, S. Delbecq¹; ¹Fédération ENAC ISAE-SUPAERO ONERA, Université de Toulouse, France This paper aims to develop and implement a prospective life cycle assessment module in the open-source framework AeroMAPS, which enables the evaluation of prospective scenarios for the aviation sector. To this end, several tools such as premise and Brightway are integrated into the framework. The relevance of the proposed methodology is illustrated through case studies. | ||||
| 15:20 | 15:45 | 9.8.3 |
MITIGATING THE CLIMATE IMPACT OF AVIATION BY OPERATIONAL MEANS - A COMPARATIVE STUDY FOR DIFFERENT WEATHER SITUATIONS Z.L. Zengerling¹, M. Mendiguchia Meuser¹, A. Lau¹, V. Gollnick, Hamburg University of Technology (TUHH), Germany; ¹German Aerospace Center (DLR), Germany Aviation’s non-CO2 climate effects can efficiently be reduced by operational measures, such as temporal, vertical, or lateral adjustments to the individual flight trajectories. We investigate suitability of these measures under different meteorological boundary conditions combining trajectory and climate impact assessment with a newly defelvoped data set of climate sensitivity grids. | ||||
| 15:45 | 16:10 | 9.8.4 |
CHARACTERISING THE ROLE OF FLEET RENEWAL ON THE PATHWAY TO 2050: A EUROPEAN AIRLINE CASE STUDY N. Barry¹, C. Gallagher¹, S. Fitzgerald, Ryanair, Ireland; C. Stuart¹; ¹Trinity College Dublin, Ireland This work creates a simulation tool that incorporates both aircraft parameters and airline operations into a combined optimisation algorithm to schedule aircraft from a defined fleet to meet the passenger demand of a given network of airports in the most economically and environmentally sustainable way. An holistic design space is characterised to aid in the research of sustainable aviation. | ||||
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| 14:30 | 14:55 | 10.8.1 |
CONVOLUTIONAL NEURAL NETWORKS ALGORITHMS FOR STRUCTURAL HEALTH MONITORING OF AIRCRAFTS COMPOSITES PANELS E. Monaco¹, F. Ricci¹; ¹Università di Napoli , Italy Composite materials replaced metals even in aircrafts primary structures but they can be affected by hidden damages hardly detectable. An SHM system based on sensorised structures and deep neural networks signal analysis methodologies is presented in this paper with the scope of detect and localise delaminations into composites plates. | ||||
| 14:55 | 15:20 | 10.8.2 |
IMPROVING SHAPE SENSING OF AERONAUTICAL STRUCTURES WITH STRAIN PRE-EXTRAPOLATION AND SENSOR PLACEMENT OPTIMIZATION E. Del Priore¹, L. Lampani¹; ¹Sapienza University of Rome, Italy This study addresses shape sensing of aeronautical stiffened panels using the inverse finite element method (iFEM). The effectiveness of the iFEM is improved by integrating it with strain pre-extrapolation and sensor optimization via a multi-objective genetic algorithm that accounts for multiple loading conditions. | ||||
| 15:20 | 15:45 | 10.8.3 |
STRUCTURAL HEALTH MONITORING OF CFRP DURING FATIGUE LOAD VIA THE ASSESSMENT OF CRACK DENSITY BY MEANS OF THERMOGRAPHY R. De Finis, Università del Salento, Italy; D. Palumbo¹, U. Galietti¹; ¹Politecnico di Bari, Italy In the present work, a new procedure is presented to measure the crack density via thermography in quasi-isotropic CFRP made by an innovative industrial process: Automated Fiber Placement. The measured crack densities during constant amplitude fatigue tests were compared with the Ogin analytical model. The thermal parameter adopted was the second amplitude harmonic of the temperature signal. | ||||
| 15:45 | 16:10 | 10.8.4 |
EMBEDDED SENSORS FOR AIRCRAFT PREDICTIVE MAINTENANCE: SHM SYSTEM INTEGRATION & TRADE-OFF ANALYSIS V.M. Sharma¹, P. Jha¹, V. Samanyusree¹, A. Sharma¹, S. Maheshwari¹, G.S. Mamatha¹; ¹RV College of Engineering, India Integrating NDT with SHM, this research automates inspections in aging aircraft using Ultrasonic Inspection, Vibration-Based Methods, Acoustic Emission, Strain Sensors, and Fiber Optic Sensors. Focused on Airbus A380, it compares sensor accuracy for enhanced safety, efficiency, and cost-effectiveness. Study includes trade-off analysis aligning with aerospace industry needs and testing guidelines. | ||||
| additional information (interactive) | 10.8.R |
THERMAL HISTORY PAINT UNDER HIGH SUBSONIC FLOW W. Stryczniewicz¹, T. Kwiatkowski¹, I. Kaminska², M. Chojnacki², K. Fronc²; ¹?ukasiewicz Research Network - Institute of Aviation, Poland ;²Institute of Physics Polish Academy of Sciences, Poland | |||||
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| 14:30 | 14:55 | 11.8.1 |
FAST TRANSONIC CORRECTIONS FOR PANEL METHODS USING VISCOUS-INVISCID INTERACTION A. Crovato¹, P. Dechamps¹, A.P. Prado², P.H. Cabral², V.E. Terrapon¹, G. Dimitriadis¹; ¹University of Liège, Belgium ;²Embraer S.A., Brazil This work presents a methodology for computing unsteady aerodynamic loads in the transonic regime within the context of preliminary aircraft design. The unsteady pressure loads are obtained using a Source and Doublet Panel Method and are corrected by means of Viscous-Inviscid Interaction, whereby a steady transonic full potential solver is coupled with the integral boundary layer equations. | ||||
| 14:55 | 15:20 | 11.8.2 |
EXPLORING MULTI-FIDELITY AEROELASTIC TAILORING: PROSPECT AND MODEL ASSESSMENT H.F. Maathuis¹, S.G.P. Castro¹, R. De Breuker¹; ¹Delft University of Technology, Netherlands In the pursuit of a more sustainable aviation industry, the development of high-performance and eco-friendly aircraft is crucial. However, the push for lighter, more slender wings brings forth challenges in structural integrity and aeroelasticity, especially with the increasing use of composite materials. This paper addresses these challenges through a Multi-Disciplinary Optimisation (MDO) framework, focusing on aeroelastic tailoring while optimising lamination parameters and thicknesses of structural parts. While employing the Classical Laminate Theory (CLT), this study formulates a weight minimization problem while ensuring feasibility through multiple constraints, incorporating diverse disciplines such as structural integrity and dynamic aeroelastic stability. The complexity of this high-dimensional problem often necessitates a sequential optimisation approach across design phases, limiting the exploration of superior designs. To overcome this limitation, the paper proposes a concurrent optimisation strategy utilizing models of varying fidelity — ranging from low-fidelity beam models to high-fidelity shell models — employing multi-fidelity approaches. The work aims to bridge the gap between design stages, allowing for the exchange of crucial information while maintaining computational efficiency. The envisioned design cycle, contrasting past practices with future strategies, highlights the shift from empirical knowledge reliance to physics-based insights, particularly crucial for novel aircraft configurations. By integrating high-fidelity information early in the design process, this work strives to expand design freedom and foster more optimal and structurally feasible aircraft designs. | ||||
| 15:20 | 15:45 | 11.8.3 |
A-BASIS AND B-BASIS BUCKLING ALLOWABLES FOR AN AIRCRAFT COMPOSITE WING R.A.S. Cardoso¹, M.S. Reis¹, L.P.S. Ferreira, FEMTO-ST, France; M.P. Alves¹, S.K. Ha, Hanyang University, South Korea; C.A. Cimini Jr.¹; ¹Federal University of Minas Gerais, Brazil This paper aims to establish an approach to determine A-Basis and B-Basis buckling allowables for an aircraft composites wing. A CNN (Convolutional Neural Network) is trained using data from Monte Carlo simulations of a Finite Element model. A surrogate statistical model is then generated to define the A-Basis and B-Basis allowable bending/torsion buckling strength of the composites wing. | ||||
| 15:45 | 16:10 | 11.8.4 |
ENHANCING THE PERFORMANCE OF SLENDER STRUCTURES WITH GEOMETRIC CONSTRAINTS: A CASE STUDY WITH THE ROORDA FRAME L. Zhu¹, J. Shen, University of Exeter, United Kingdom; R.M.J. Groh¹, M. Schenk¹, A. Pirrera¹; ¹University of Bristol, United Kingdom This work aims to increase a slender structure's load-carrying capacity above its buckling point by introducing small imperfections, informed by post-buckling analysis of the unperturbed structure, known as 'modal nudging'. Specifically, we focus on structures with constrained geometry, such as wing panels, exemplified through a case study on Roorda frames. | ||||
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| 14:30 | 14:55 | 12.8.1 |
ENERGY DISSIPATION BEHAVIOR AND LIFE PREDICTION OF CARBON FIBER REINFORCED COMPOSITE MATERIALS SUBJECTED TO FATIGUE LOAD Jia Huang, China; Qijia Yun, China; Aijia Li, China The energy dissipation behavior of composite materials subjected to fatigue loading is analyzed. It is found that the total entropy increase caused by damage-related energy dissipation is independent of stress amplitude. Based on damage-related energy dissipation information, the fatigue performance of various composite materials is predicted and verified with traditional fatigue experiments. | ||||
| 14:55 | 15:20 | 12.8.2 |
A MESO-SCALED SIMULATION ON THE THICKNESS EFFECT OF TWO-DIMENSIONAL TRIAXIALLY BRAIDED COMPOSITES UNDER TENSILE LOADS Y. Bai¹, P. Liu¹, Z.-Q. Zhao¹, C. Zhang¹; ¹Northwesterm Polytechnical University, China Presenter: Zhenqiang Zhao, Northwestern Polytechnical University The mechanical behaviors of 3D woven composite exhibits obvious size effect and slight strain rate effect. The size dependency of 3D woven composite differs from the unidirection composite. This work provides valuable insights into the determination of dynamic properties for 3D woven composites, and the designing and interpretation of dynamic test. | ||||
| 15:20 | 15:45 | 12.8.3 |
MULTIAXIAL TESTING OF AERONAUTIC COMPOSITE STRUCTURES AT INTERMEDIATE SCALE B. Castanié¹, J.-C. Passieux¹, J.-N. Périé¹, C. Bouvet¹, J.-E. Dufour¹, J. Serra¹; ¹Institut Clément Ader, France Achievements of a multiaxial test bench called “VERTEX” are presented. It allows to load a specimen of 500 x 500 mm2 under shear, tension or compression and internal pressure. Tests were conducted on aeronautic composite panels to study large notches, combined loading after impact, wrinkling and buckling of sandwich panels. | ||||
| 15:45 | 16:10 | 12.8.4 |
DYNAMIC AND STABILITY ANALYSES OF ROTATING THIN-WALLED FILAMENT WOUND GLASS FIBRE COMPOSITE CYLINDERS WITH METAL LINER R. Hu, China; Z. Yuan, China; C. Zhang, China Presenter: Ruiqi Hu The dynamic and stability analyses of cylindrical filament wound composite overwrapped shells with metal liner was carried out to facilitate the lightweight design and improve the structure safety. The FE analysis considered the rotational centrifugal force in ABAQUS, and the reinforcement effect was realized by using the equivalent temperature drop method and the element birth and death technology. | ||||
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| 14:30 | 14:55 | 13.8.1 |
DESIGN SPACE EXPLORATION OF NEXT-GENERATION SUPERSONIC BUSINESS JET ENGINE WITH A FOCUS ON LANDING AND TAKE-OFF (LTO) NOISE D. Del Gatto¹, S. Adamidis¹, C. Mourouzidis¹, S. Brown¹, V. Pachidis¹; ¹Cranfield University, United Kingdom Presenter: Dario Del Gatto, Cranfield University This work illustrates the design space exploration of a mixed-flow turbofan engine for supersonic business jet following an integrated intake/engine approach. It shows the LTO cycle noise constraint impact on the engine design and suggests an alternative engine architecture, providing an overall picture in terms of aircraft performance, and gaseous and noise emissions at airport level. | ||||
| 14:55 | 15:20 | 13.8.2 |
RAMJET/SCRAMJET TEST BENCH WITH CAVITY INJECTION OF HYDROGEN F. Strauss¹, T. Nilsson, Lund University, Sweden; K. Manassis¹; ¹German Aerospace Center DLR, Germany Presenter: Thommie Nilsson, Lund University In this work we study a small ramjet combustor with cavity injection of hydrogen. The work is embedded within the MDO and Regulations for Low-boom and Environmentally Sustainable Supersonic Aviation (More&Less) project (workpackage WP4) and compares two example cases of experimental combustion data for gaseous hydrogen with CFD simulated data for those cases. Includes an outlook on further data. | ||||
| 15:20 | 15:45 | 13.8.3 |
PROPULSIVE CFD ANALYSIS OF THE SCRAMJET HYPERSONIC EXPERIMENTAL VEHICLE O. Russo¹, P. Roncioni¹, M. Marini¹, S. Di Benedetto¹, G. Ranuzzi², S. Pizzurro², M. Albano²; ¹Italian Aerospace Research Centre (CIRA), Italy ;²Italian Space Agency (ASI), Italy The paper examines the propulsive and combustion performances of a hypersonic scramjet engine along with emission indexes for different species in the combustion process. Comprehensive Computational Fluid Dynamics (CFD) analyses cover the entire internal flow path (inlet, combustor, and nozzle) in a flight-cruise setup. Both power-off and power-on conditions are assessed using ANSYS FLUENT software with a steady Reynolds-Averaged Navier-Stokes (RANS) model and established chemical schemes from existing literature. The impact of viscosity on engine performance is also assessed. The findings demonstrate a noteworthy enhancement in performance and the attainment of high combustion efficiency by the end of the engine cycle. | ||||
| 15:45 | 16:10 | 13.8.4 |
EXPERIMENTAL AND NUMERICAL INVESTIGATION ON SEPARATION CHARACTERISTICS OF SERPENTINE CONVERGENT-DIVERGENT NOZZLE M.-X. Wang¹, L. Zhou¹, J.-W. Shi¹, W.-J. Deng¹, H. Xiao¹; ¹Northwestern Polytechnical University, China This paper carries out experimental and numerical investigation of a convergent-divergent nozzle. It is shown that the serpentine shape produces a coupling effect with the flow separation in the overexpanded state. The jet produces thrust deflection at low nozzle pressure ratios and its separation is three-dimensional. | ||||
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| 14:30 | 14:55 | 14.8.1 |
IDENTIFICATION OF FACTORS CONTRIBUTING TO UNFAVORABLE LANDINGS R. Mori, Kobe University, Japan Using more than 3000 data of visual approaches, a decision tree model is used to estimate unfavorable landing events, i.e., overspeed approaches and hard landings. By analyzing the obtained model, the related feature affecting such unfavorable landing events are identified. | ||||
| 14:55 | 15:20 | 14.8.2 |
HELICOPTER ACCIDENTS IN BRAZIL: AN ANALYSIS OF MAINTENANCE FROM THE PERSPECTIVE OF HUMAN FACTORS F. de Assis da Silva Junior¹, J.M. Vieira da Fonseca¹, I.N.M. da Silva¹, A.V. Gaspar¹, M.M. Cardoso Junior¹; ¹Technological Institute of Aeronautics, Brazil Presenter: MOACYR cardoso-Junior, Technological Institute of Aeronautics An analysis of helicopter maintenance from the perspective of human factors Where the results were then codified and used to generate tables showing the accident causal factors. It showed interesting results that validates the use of Human Factors Analysis and Classification System-Maintenance Extension HFACS-ME as a tool for the identification and analysis of organizational management problems | ||||
| 15:20 | 15:45 | 14.8.3 |
SENSITIVITY ANALYSIS OF SAFETY FACTORS BASED ON MODEL OF AVIATION RECIPROCATING ENGINE TURBOCHARGING SYSTEM Z. Wang, China; G. Li, China; Y. Teng, China; T. Xu, China; Y. Zhang, China Presenter: ZiLu Wang This paper analyzes the impact of safety impacting factors on the turbocharging system based on the simulation results, in order to adjust the change scopes of factors during the actual flight, so as to reduce the uncertainty of the key factors and to carry out efficient and intuitive safety analysis to improve the safety level of the aviation piston engine turbocharging system. | ||||
| 15:45 | 16:10 | 14.8.4 |
ANALYZING THE STATISTICAL CORRELATION OF PHYSIOLOGICAL PARAMETERS WITH TUC IN PILOTS PRIOR TO HYPOBARIC TRAINING S.-J. Wu, Taiwan, China; C.-T. Kuo, Taiwan, China; N.-S. Chen, Taiwan, China; C.-J. Su, Taiwan, China; K.-K. Jen, Taiwan, China; S.-T. Hsieh, Taiwan, China; C.-Y. Lai, Taiwan, China; C.-L. Kuo, Taiwan, China This study seeks to gather physiological data, including heart rate, HRV, and SpO2, from 40 military aircrews in Taiwan. The aim is to establish correlations between Time of Useful Consciousness (TUC) and these physiological parameters under simulated hypoxic conditions at an altitude of 25,000 feet, using statistical techniques such as the Generalized Linear Model (GLM). | ||||
| Reserve Paper | 14.8.R |
STUDY ON THE BALLISTIC-RESISTANT AIRWORTHINESS STANDARDS FOR COMMERCIAL AIRCRAFT COCKPIT DOOR T. Hu¹, J. Song¹, N. Yue¹, Z. Zhang², Y. Zhang², T. Chen²; ¹Airworthiness Technology Research & Management Center, China ;²Shanghai Aviation Airworthiness Certification Center, China Presenter: Tao Hu, Airworthiness Technology Research & Management Center | |||||
| additional information (interactive) | 14.8.R |
A METHOD FOR AUTOMATIC GENERATING SAFETY ANALYSIS BASED ON AVIATION PISTON ENGINE MODEL G. Li¹, Y.-D. Teng¹, Z.-L. Wang¹, T.-G. Xu¹, S.-T. Ding, Civil Aviation University of China,, China; ¹Beihang University, China | |||||
| additional information (interactive) | 14.8.R |
IMPROVING DISTRIBUTION OF CRASH ENERGY ABSORPTION FOR CIVIL AIRCRAFT BASED ON PROGRESSIVE BENDING FAILURE MECHANISM T.-J. Jiang¹, Z.-P. Luo¹, Z. Kan¹, J.-W. Xiang¹, X.-C. Liu², C.-Y. Bai², X.-L. Xi²; ¹Beihang University, China ;²Aircraft Strength Research Institute, China | |||||
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| 14:30 | 14:55 | 15.8.1 |
IN-FLIGHT MEASUREMENT OF WING SURFACE PRESSURE DISTRIBUTION ON A FIXED-WING UAV AND ITS APPLICATION TO FLIGHT CONTROL Y. Hayashi¹, J.-H. Kim¹, T. Tsuchiya¹; ¹The University of Tokyo, Japan Birds use their feathers covering wings to sense airflow. In contrast, conventional fixed-wing aircraft rely on IMUs for attitude estimation but often lack sensors to measure airflow around their wings. Inspired by the birds' airflow sensors, a pressure sensor array system working as feathers was developed. Research utilizing the measured pressure values for flight control is planned. | ||||
| 14:55 | 15:20 | 15.8.2 |
MODEL PREDICTIVE CONTROL DRIVEN AERIAL GRASPING WITH SOFT OPERATIONAL CONSTRAINTS J. Novák ¹, J. Hanák¹, P. Chudý¹; ¹BUT, Czech Republic Physical interaction of Unmanned Aerial Vehicles (UAVs) with it’s environment has the potential to enable many complex missions in both scientific and industrial domains. This paper deals with coupled Model Predictive Control (MPC) for an UAV with attached robotic manipulator. Adaptive augmentation loop is used in the trajectory tracking scheme to compensate for the manipulator dynamics and increase precision of aerial grasping tasks. Perception constraints ensure that the payload stays within camera field of view. Conducted numerical simulations show effectiveness of the coupled MPC scheme for aerial grasping and its safety enhanced by the imposed constraints. | ||||
| 15:20 | 15:45 | 15.8.3 |
FUZZING ON TARGET DETECTION SYSTEM OF UNMANNED AERIAL VEHICLE H. Dai¹, Z. Wang¹, J. Ding¹, G. Li¹, C. Wang¹, L. He¹, H. Liu, Swinburne University of Technology, Australia; ¹Chinese Aeronautical Establishment, China Existing testing techniques are unable to generate test cases that match the UAV's perspective, which may result in inadequate testing target detection systems of UAV. We proposed a novel testing framework based on fuzzing technique, named FTU, to generate test cases from the UAV’s perspective and automatically verify the test results based on metamorphic relations. | ||||
| 15:45 | 16:10 | 15.8.4 |
FLIGHT PATH RECONSTRUCTION OF A FLEXIBLE WING UAV WITH WING MOUNTED VANES V.P. Fernandes¹, T.R. Paula¹, R.C. Nascimento¹, R.G.A. Silva¹, L.C.S. Góes¹; ¹ITA - Instituto Tecnológico de Aeronáutica, Brazil This work applied an electric flexible wing UAV that underwent flight evaluations to explore flexibility effects and ensure data accuracy. Flight Path Reconstruction (FPR) was used for data compatibility check, showing consistency in recordings but discrepancies for specific states. The study enhances FPR by including structural dynamics, expecting an improvement in the fidelity of results. | ||||
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| 14:30 | 14:55 | 16.8.1 |
LIGHT WEIGHT DESIGN AND LASER ADDITIVE MANUFACTURING OF METAL BIPOLAR PLATES FOR THE APPLICATION OF AIRCRAFT FUEL CELL K.J. LIN, China; Y. XU, China; D.D. GU, China; J.H. SHAN, China; K.Y. SHI, China; W.L. ZHANG, China In order to reduce the weight of metal bipolar plate for the application of aircraft fuel cell. Four light-weight sandwich structures were designed and manufactured by laser additive manufacturing. This study focuses on the formability, bending mechanical properties, and electrical conductivity properties of the LPBF-processed sandwich structure bipolar plates. | ||||
| 14:55 | 15:20 | 16.8.2 |
EFFECTS OF PROCESSING STRATEGIES ON SURFACE QUALITY AND MECHANICAL PROPERTIES IN HYBRID ADDITIVE MANUFACTURING OF IN718 ALLOY T. Wang¹, C. Wang¹, J.-J. Li¹, W.-X. Wang¹; ¹Chongqing University, China Laser metal deposition/grinding hybrid manufacturing process was utilized to produce In718 alloy thin-walled parts. The forming quality, microstructure characterization and mechanical property of the In718 parts were carried out. In addition, the hollow blade was prepared through the optimized process, which verified the feasibility of the hybrid manufacturing system. | ||||
| 15:20 | 15:45 | 16.8.3 |
BUILDING METHODS FOR A COMPOSITE CONSTRUCTED VTOL USING 3D PRINTING TECHNIQUES T. Müller¹, V. Gollnick¹; ¹Institute of Air Transportation Systems, Germany The Institute of Air Transportation Systems is attempting to pioneer UAV prototyping through 3D printing, particularly for VTOL models. Using Fused Deposition Modelling (FDM) and various plastics to construct hybrid composite structures, they provide a guide to independent aircraft prototyping, freeing designers from conventional manufacturing constraints. | ||||
| 15:45 | 16:10 | 16.8.4 |
THE PRODUCTION OF HIGH-PERFORMANCE HEAT EXCHANGERS FOR AEROSPACE APPLICATIONS J. Shipley¹, A. Magnusson¹, J. Gårdstam¹, C. Beamer¹, A. Cassese¹; ¹Quintus Technologies, Sweden Additive manufacturing enables production of thin-walled heat exchangers but there are challenge in heat treatment of many common materials. This presentation will demonstrate ongoing work with respect to combined HIP and heat treatment cycles which avoid many challenges whilst improving product quality and reliability. | ||||
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| 14:30 | 14:55 | 17.8.1 |
CLIMATE RESILIENCE – THE IMPACT OF EXTREME WEATHER EVENTS - A CASE STUDY: HEATHROW AIRPORT M. Osund-Ireland¹, B. Elzen¹, W.A. Ireland¹; ¹Susteer AB, Sweden At ICAS 2022, we introduced our Climate Resilient Assets Assessment Tool and, using a number of representative airports, demonstrated how ICAO guidance could be applied consistently to better inform airport managers. We have further developed the tool and assessed the resilience of a major hub airport to extreme weather events that may increase or decrease in likelihood due to climate change | ||||
| 14:55 | 15:20 | 17.8.2 |
SUSTAINABLE ENGINE MAINTENANCE: EVALUATING THE ECOLOGICAL IMPACT OF LIFE LIMITED PART REPLACEMENT A. Oestreicher¹, A. Rahn¹, J. Ramm¹, J. Städing², C. Keller², K. Wicke¹, G. Wende¹; ¹DLR, Germany ;²MTU Maintenance, Germany This study presents a Life Cycle Assessment (LCA) for engine maintenance Life Limited Part (LLP) replacement. The assessment analyzes both the LLPs and individual maintenance work in terms of their ecological impact. In the long term, the methodology aims to provide a detailed ecological overview of engine maintenance. | ||||
| 15:20 | 15:45 | 17.8.3 |
FACTORS INFLUENCING THE CLIMATE-RELEVANT ENVIRONMENTAL IMPACT OF AIR TRANSPORT COMPARED TO RAIL AND ROAD TRANSPORT J. Roesing, RWTH Aachen University, Germany To identify where the emissions in the transport sector originate and to draw conclusions on how to reduce them, it is necessary to examine the specific source of the emissions. The aim of this paper is to provide an overview of the different causes of emissions in air passenger transport compared to rail and road transport. It also examines how emissions are determined in existing literature. | ||||
| 15:45 | 16:10 | 17.8.4 |
E-KEROSENE POTENTIAL FOR COMMERCIAL AVIATION DECARBONIZATION G. Quaresma¹, L.B. Magalhães, ISEC, ISEC Lisboa, Portugal; A.F. Ferreira, IDMEC-LAETA, Mechanical Engineering Department, IST/UL, Portugal; A. Silva¹; ¹AEROG-LAETA, Aerospace Sciences Department, UBI, Portugal Reducing greenhouse gas emissions from aircraft transport is crucial to achieving climate goals. In this sense, the present study looks into the suitability of e-fuels such as e-kerosene in reducing CO2 emissions. The Fleet System Dynamic Model is employed to examine data and predict future trends in line with the Committee on Aviation Environmental Protection. While the findings suggest that achieving carbon-neutral growth is possible, it might take longer than current forecasts indicate. For instance, considering an e-fuel production rate of 15%, it is possible to cut emissions by half around 2060 concerning 2005 levels. | ||||
| additional information (interactive) | 17.8.R |
ENSURING THE NEXT GENERATION GREEN AIRCRAFT’ SUSTAINABILITY FROM THE DESIGN PHASE VIA A LIFE-CYCLE COST ANALYSIS E. Stefana¹, E. De Paola¹, L. Pustina¹, R. Patriarca¹, F. Mastroddi¹; ¹Sapienza University of Rome, Italy | |||||
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| 16:30 | 17:00 | 1.9.1 |
PRATT & WHITNEY SUSTAINABILITY STRATEGY & DEMONSTRATORS A. J. Murphy, Pratt & Whitney, United States invited speaker for the Global Sustainable Aviation track | ||||
| 17:00 | 17:30 | 1.9.2 |
GE AEROSPACE: RISING TO THE CHALLENGE FOR MORE SUSTAINABLE FLIGHT R. Seele, GE Aerospace, United States Invited speaker for the Global Sustainable Aviation track | ||||
| 17:30 | 18:00 | 1.9.3 |
FUTURE LANDSCAPE OF AVIATION ENERGY – US PERSPECTIVE M. R. Berube, Department of Energy EERE, United States INVITED SPEAKER FOR THE GLOBAL SUSTAINABLE AVIATION TRACK | ||||
| 18:00 | 18:30 | 1.9.4 |
PANEL DISCUSSION PD D, PANEL DISCUSSION | ||||
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| 16:30 | 17:00 | 2.9.1 |
OVERVIEW OF JAPANESE R&D ACTIVITIES ON GREEN TRANSFORMATION AND DIGITAL TRANSFORMATION IN AVIATION S. Watanabe Watanabe, Japn Aerospace Exploration Agency, Japan This lecture will overview the progresses and challenges of R&D in Japan on GX and DX technologies in aviation, illustrating the features of the promising technologies under development and the eco system to facilitate the collaborations across the different technical fields and organizations. | ||||
| 17:00 | 17:30 | 2.9.2 |
DEVELOPMENT OF CORE TECHNOLOGIES FOR HYDROGEN AIRCRAFT M. Kazari, Kawasaki Heavy Industries,Ltd., Japan Discussions about decarbonizing aircraft to prevent global warming are becoming more active, and there is also growing interest in the development of hydrogen aircraft. In this lecture, I will present about the development of hydrogen combustor, hydrogen supply system and liquefied hydrogen tank, etc., which are the core technologies necessary for the realization of hydrogen aircraft. | ||||
| 17:30 | 18:00 | 2.9.3 |
AIRCRAFT DX IN COMMERCIAL AVIATION SYSTEMS Y. Yamaguchi, Mitsubishi Heavy Industries, Ltd./Commercial Aviation Systems, Japan This paper introduces the overview of DX/MBSE challenges in Mitsubishi Heavy Industries, Ltd. The future vision of DX in commercial aircraft, which leads to the improvement of the visibility from all the stakeholders, will be described. In addition, the details of our current DX activities in Design, Production, and Certification will be explained. | ||||
| 18:00 | 18:30 | 2.9.4 |
DEVELOPMENT OF AIRCRAFT SYSTEM ELECTRIFICATION AND HYBRID ELECTRIC PROPULSION N. Seki¹, T. Inoue¹; ¹IHI Corporation, Japan To achieve the decarbonization of air transportation in 2050, IHI has been conducting research and development to improve energy efficiency of aircraft by applying hybrid electric propulsion and aircraft system electrification with the contract of Japanese national funding. In this paper, the development activities will be presented. | ||||
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| 16:30 | 17:00 | 3.9.1 |
STRUT-BRACED WING INDUCED DRAG MODELING FOR REGIONAL TURBOPROP AIRCRAFT DESIGN G. Grazioso, University of Naples Federico II, Italy; A. De Marco, University of Naples, Italy Strut-braced wing (SBW) can contribute to reducing regional aviation's environmental impact. However, trade-offs emerge, with increased parasite drag compensated by lower induced drag and wing weight. The paper proposes a parametric model to consider the induced drag penalties in the preliminary design stage. The potential reduction in mission fuel consumption is estimated for the ATR 72-600. | ||||
| 17:00 | 17:30 | 3.9.2 |
STEADY ANALYSIS OF THREE-SURFACE AIRPLANES: IMPROVING THE AERODYNAMIC PERFORMANCE THROUGH REDUNDANT LONGITUDINAL CONTROL S. Cacciola¹, C.E.D. Riboldi¹, C. Spitale¹; ¹Politecnico di Milano, Italy Improving the fuel efficiency of airplanes does not necessarily require innovative propulsion or highly unusual designs. In this work, we demonstrate with numerical examples that a three-surface configuration with redundant longitudinal control, obtained via two movable surfaces located on both the horizontal tail and canard, can be significantly effective in increasing the lift-to-drag ratio. | ||||
| 17:30 | 18:00 | 3.9.3 |
LONGITUDINAL STABILITY PARAMETERS FOR FLYING BOOM AERIAL REFUELING L.H. Peristy¹, R.E. Perez¹; ¹Royal Military College of Canada, Canada This work introduces a new parameter called Positional Static Margin (PSM), which is used to make predictions about aircraft longitudinal stability during flying boom aerial refueling. A vortex lattice method is used to examine the PSM of different tanker-receiver pairs, with aircraft geometry being demonstrated as an important consideration, independent of flight conditions. | ||||
| 18:00 | 18:30 | 3.9.4 |
ON THE FUTURE OF TRANSONIC FLIGHTS: CURVED PLANFORM WINGS FOR BUFFET-ONSET CONTROL M.R. Chiarelli¹, S. Bonomo¹, G. Cascinelli¹; ¹Department of Civil and Industrial Engineering, Pisa, Italy The results of studies on a curved planform wing are discussed: these studies consist of 3D unsteady CFD analyses. To test the calculation reliability, 2D analyses were carried out on the NACA0012 profile to estimate the buffet boundary. The curved wing configuration allows a notable reduction of the drag and the aeroelastic instability is postponed compared to a conventional swept wing. | ||||
| Reserve Paper | 3.9.R |
INVESTIGATION ON AERODYNAMIC DESIGN OF VTOL AIRCRAFT PROPELLER L.D. Deng¹, W.P. Song¹, J.H. Xu¹; ¹School of Aeronautics, Northwestern Polytechnical University, China | |||||
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| 16:30 | 17:00 | 4.9.1 |
DEVELOPMENT OF A SERVO-DRIVEN FLAPPING-WING AIR VEHICLE WITH FOLDING-WING MECHANISM E.-H. Lee¹, H.-H. Yang¹, S.-G. Lee¹, J.-H. Han¹; ¹KAIST, South Korea This study presents a novel folding-wing mechanism for enhanced lift efficiency in a flapping-wing air vehicle (FWAV). It establishes a flapping-wing flight simulation environment and validates aerodynamic and dynamic models for the FWAV. A prototype is flight-tested, allowing an analysis of control and performance, especially with increased wing movement degrees. | ||||
| 17:00 | 17:30 | 4.9.2 |
PRELIMINARY DESIGN EXPLORATION OF PROSPECTIVE MULTIROTOR AEROBOTS FOR MARS V. Youhanna¹, L. Felicetti¹, D. Ignatyev¹; ¹Cranfield University, United Kingdom This preliminary design exploration assesses rotorcraft configurations for Martian exploration within defined parameters. Analysis includes single, dual, and quad rotorcrafts, focusing on power consumption in hover, climb, and forward flight. Findings highlight quad rotorcrafts' efficiency but underscore practical constraints. The study aids Martian aerobot designers in optimal configuration selection. | ||||
| 17:30 | 18:00 | 4.9.3 |
MISSION-BASED OPTIMAL PROPELLER SELECTION FOR VTOL SUAV CONFIGURATION C. Reyner¹, C. Lee¹, D. Kim, Ecole Nationale de l’Aviation Civile, France; R.P. Liem¹; ¹The Hong Kong University of Science and Technology, Hong Kong SAR of China This paper presents a method for optimal propeller selection in VTOL sUAV, maximizing efficiency for any mission profile. Using unsupervised ML and surrogate models, the approach reduces flight data complexity and predicts performance in various conditions. This offers a rigorous basis for optimal propeller from hundreds of selection and can benefit sUAVs operation in real-world environments. | ||||
| 18:00 | 18:30 | 4.9.4 |
MICRO-SIZE MARS AIRPLANE FOR THE STEPWISE MARS LANDING EXPLORATION PROGRAM Y. Shiratsuchi¹, K. Kaneko, The University of Tokyo, Japan; S. Okada, Tokyo University of Agriculture and Technology, Japan; A. Oyama², K. Yamada², H. Tanaka², M. Sato¹; ¹Kogakuin University, Japan ;²Japan Aerospace Exploration Agency, Japan Mars exploration mission using a micro-size Mars airplane is proposed. We assume the airplane and a deployable aeroshell are stored in 3 units (30 cm x 10 cm x 10 cm) and the weight of the airplane is 1kg. The present feasibility study shows micro-size Mars airplane that flies 25km is possible. | ||||
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| 16:30 | 17:00 | 5.9.1 |
APPLICATION OF DIFFERENT NUMERICAL TOOLS AND NUMERICAL METHODS FOR PREDICTION OF HEAT EXCHANGER RAMAIR-CONCEPTS FOR HYBRID ELECTRIC PROPULSION AIRCRAFT CONFIGURATIONS A.-R. Hübner¹, J. Kirz¹, K. Weinman¹; ¹German Aerospace Center (DLR), Germany To reduce the overall emissions of aviation hybrid-electric propulsion concepts have a great potential satisfying this challenge. For fuel cell applications heat exchangers are required to dissipate the waste heat produced by the fuel cell. The integration of the heat exchangers has an impact on the aircraft aerodynamics. With a new tool implementation for the simulations of heat exchangers in the DLR-TAU code, a generic application case is calculated and analyzed. | ||||
| 17:00 | 17:30 | 5.9.2 |
TOWARDS REFINED CONTRAIL SIMULATIONS OF FORMATION FLIGHT SCENARIOS J. Pauen¹, S. Unterstrasser¹, A. Stephan¹; ¹DLR, Germany Formation flight is a promising option to reduce aviation's CO2 emissions and even more the contrail climate impact. Contrail LES with RANS-based wake vortex initialisation will be performed to improve our understanding of early contrail processes. Hereby, single aircraft scenarios as well as formation flight configurations are investigated. | ||||
| 17:30 | 18:00 | 5.9.3 |
PERFORMANCE AND ACOUSTIC ANALYSIS OF A DISTRIBUTED ELECTRIC PROPULSION UNMANNED AIRCRAFT R. Navarro¹, L.M. García-Cuevas¹, J. García-Tíscar¹, F.N. Ramírez¹; ¹Universitat Politècnica de València, Spain Aircraft with distributed electric propulsion (DEP) have a strong interaction between the propulsion system and the airframe, which gives rise to interesting optimisation opportunities but significant design challenges. This paper presents a comparison of performance and noise emission calculations of an unmanned aircraft with DEP using different methods with increasing levels of fidelity. | ||||
| 18:00 | 18:30 | 5.9.4 |
HIGH FIDELITY MODELING OF ACOUSTIC LINERS FOR AERONAUTICAL APPLICATIONS L. Pinelli¹, M. Marconcini¹, A. Arnone ¹, D. Bacci, Oxford Thermofluids Institute, University of Oxford, United Kingdom; ¹Department of Industrial Engineering, University of Florence, Italy Aircraft noise is a polluting emission from civil aviation and is the most significant cause of adverse community reaction related to the operation and expansion of airports. Reducing the population affected by significant aircraft noise is therefore a key priority for aircraft-engine designers. Acoustic liners are a well-established technology to abate noise emissions and they have been installed in the engine intake and turbine nozzle from a long time. Such passive devices are usually designed to absorb a target band of the noise spectrum radiated from the aft and rear part of the engine. Liner panes based on single-degree-of-freedom cavities are usually designed by means of semi-analytical methods and verified with experimental campaign in dedicated grazing tube rig. Thanks to the growth in computational capability, high fidelity simulations of such devices are becoming viable and can be used instead of expensive experimental campaigns. This is particularly true when screening non-conventional geometries of the resonator cavity as Triply Periodic Minimal Surface (TPMS). In this context, the paper presents and validates a high-fidelity numerical approach based on the OpenFOAM opensource CFD code to predict the acoustic impedance and absorption of liner panels. LES simulations of a single resonator cell have been performed with and without grazing flow for different Sound Pressure Level (SPL) of the planal acoustic waves to investigate linear and non-linear regimes of the resonator. Liner impedance and absorption coefficients have been derived by mean of the well-know in-situ method. | ||||
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| 16:30 | 17:00 | 6.9.1 |
PRELIMINARY DESIGN OF A FIXED-WING DRONE FOR MARS EXPLORATION ACTIVITIES G. Barbato¹, G. Pezzella¹, A. Viviani¹; ¹Università della Campania Luigi Vanvitelli, Italy Presenter: Gennaro Barbato, Università della Campania \\\"Luigi Vanvitelli\\\" This paper deals with the preliminary design of a fixed-wing drone for Mars surface exploration activities. The design cycle is detailed in the paper and justifications for design requirements and constraints are also provided and discussed. Outcomes of design phase are provided in the paper with several details. Keywords: Mars exploration aircraft, Design Requirements, Design Constraints. | ||||
| 17:00 | 17:30 | 6.9.2 |
PARELLEL UNSTEADY REYNOLDS-AVERAGED NAVIER-STOKES (URANS) STUDEIS OF THE PERFORMANCE OF ONR WATERJET AXWJ-2 S.E. Monroe, Clarkson University, United States The accuracy of SimericsMP+ Unsteady Reynolds-Averaged Navier-Stokes (URANS) is validated by studying turbulent flow past counter rotating propellers (CRPs). Subsequently, URANS is used to study an axial flow in an Office of Naval Research (ONR) waterjet and the pump’s performance. Specifically, experimental data from Miller (1976) as well as LES results from Hu et al (2019) are employed to compare against the current URANS results. Due to the large size of both simulations, parallel computing over 80 cores is involved. For the CRP study, torque and thrust coefficients are plotted against a range of advance ratios, ensuring a Reynolds number of less than 500,000. For the pump, torque and head coefficients are plotted for a range of flow rates. For both studies, two different mesh sizes were utilized. The finer meshes of both studies contained roughly twice the number of cells found in their respective coarse meshes. These refinements lead to minor improvements, showing good convergence. The URANS torque and thrust coefficients were found to be within 10% of that from experimental data across all advance ratios for the CRP set, showing good agreement. The torque and head coefficients for the pump displayed even better agreement, with the greatest error across all flow conditions remaining under 3%. | ||||
| 17:30 | 18:00 | 6.9.3 |
NUMERICAL INVESTIGATION ON THE LIQUID SLOSHING DAMPING INSIDE A TANK WITH A FLEXIBLE ANTI-SLOSHING DEVICE F. Rossetti¹, L. Pirillo¹, M. Cimini, ENEA, Italy; M. Bernardini¹, F. Stella¹; ¹Sapienza University, Italy Presenter: Lorenzo Pirillo, Sapienza University This paper explores the lateral sloshing phenomenon in a tank equipped with Anti-Sloshing Devices (ASD). Initially, the analysis neglects the ASD deformability. Subsequently, two-way Fluid-Structure Interaction (FSI) simulations investigate the benefits of ASD deformability in enhancing the damping ratio of the sloshing phenomenon within the tank. | ||||
| 18:00 | 18:30 | 6.9.4 |
THE EFFECTS OF INITIAL STRESS ON AERODYNAMIC PERFORMANCE OF FLEXIBLE MEMBRANE-SKELETON WINGS WITH FSI SIMULATION Y.-Y. Guo¹, W.-Q. Yang¹, J.-L. Xuan¹, W. Wang¹, D. Xue¹; ¹Northwestern Polytechnical University, China We conduct fluid-structure interaction (FSI) numerical simulations involving flexible wings. This will take into account factors such as the spanwise distance between two wing ribs, the distribution and size of the wing shape supported by the front and rear edges in the chordwise direction, membrane material properties, membrane pre-stress, and other relevant parameters. | ||||
| additional information (interactive) | 6.9.R |
VALIDATION OF CFD-BASED DATA SERVICE FOR DRONE INSPECTION OF WIND FARMS WITH FLIGHT TEST DATA M. Turner¹, J. Sharpe¹, M. Kopacz¹, D. Standingford¹, C. Sequeira², B. Sanby², C. Rider²; ¹Zenotech, United Kingdom ;²Flare Bright, United Kingdom | |||||
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| 16:30 | 17:00 | 7.9.1 |
MECHANISM STUDY ON THE IMPACT OF PULSED JET AT THE BLADE TIP LEADING EDGE ON THE FLOW FIELD IN COMPRESSOR Y. Yang, Civil Aviation Flight University of China, China; H. Zhang¹, W. Lu, Nanjing Tech University, China; C. Zhang¹, C. Xu¹, G. Huang¹; ¹Nanjing University of Aeronautics and Astronautics, China A pulsed jet hole is introduced at leading edge on the casing wall of a simplified model of compressor rotor cascade and LES is conducted. The mechanism of periodic flow control is found to resonate with the tip gap vortex, leading to more organized vortices that wrap around the primary leakage vortex with smaller pitch and radius, thereby reducing the affected area and delaying vortex breakdown. | ||||
| 17:00 | 17:30 | 7.9.2 |
IMPLEMENTATION OF ACTIVE FLOW CONTROL ON A SHORT-INLET UHBR ENGINE NACELLE S. Hayböck¹, C. Breitsamter¹; ¹Technical University of Munich, Germany Innovative nacelle designs and disruptive technologies are required to address drag and weight penalties of high bypass ratio turbofan nacelles. Active Flow Control is a promising technology to improve flow quality for short-inlet nacelle geometries. The formation of counter-rotating vortex pairs is crucial for the effectiveness of the system. | ||||
| 17:30 | 18:00 | 7.9.3 |
NUMERICAL STUDY OF THE FLOWFIELD IN A DIFFERENTIALLY-THROTTLED LINEAR AEROSPIKE J. Hassan ¹, R. Marsilio¹, G.M. Di Cicca¹, M. Ferlauto¹; ¹Dept. of Mech. and Aerospace Engineering, Politecnico di Torino, Italy 2D flowfield of truncated linear aerospike nozzle is investigated. Numerical simulations carried out both without and with differential throttling for thrust vectoring. Results compare well with experimental data. In differential throttling mode, relationship between flow structures and resultant side-force is investigated. Effect of differential throttling on thrust and thrust-angle is analyzed. | ||||
| 18:00 | 18:30 | 7.9.4 |
ON THE OPTIMIZATION OF (GENERALIZED) IMPEDANCE FOR ACOUSTIC LINERS E. De Bono, France; A.D. Fernandes, Italy; G. Petrone, Italy; M. Ouisse, France; R. Teloli, Italy; S. De Rosa, Italy Presenter: Arthur Diniz In this work, we provide a review of optimization criteria for acoustic liner impedance, and the reduction of noise transmission in ducts. The new prospectives provided by metamaterials and active liners, require proper guidelines and physical insight on the mechanisms which lead to optimal noise attenuation. The contribution of this work is to combine analytical and numerical tools for general liner design. | ||||
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| 16:30 | 17:00 | 8.9.1 |
AERODYNAMIC SHAPE OPTIMIZATION OF FILLETED INTERSECTIONS WITH SURFACE MESH DEFORMATION H.M. Hajdik¹, A. Yildirim¹, J.R.R.A. Martins¹; ¹University of Michigan, United States Component intersections are a persistent challenge in aerodynamic design. In this work, we present a method based on inverse distance warping to deform a fillet between two components for the minimum drag design. We show that this is tractable within gradient-based aerodynamic shape optimization and results in lower drag designs than those optimized without changing the intersection region. | ||||
| 17:00 | 17:30 | 8.9.2 |
NOVEL GRADIENT-ENHANCED MULTI-FIDELITY SURROGATE MODEL ASSISTED ROBUST MULTIDISCIPLINARY DESIGN OPTIMIZATION OF TAILLESS FLYING WING H. Zhao¹, K.-K. Wang¹, Z.-Y. Gong¹, K.Y. Gan¹; ¹Northwestern Polytechnical University, China Presenter: Huan Zhao The tailless flying wing design encounters a significant challenge from the lack of longitudinal control. This paper establishes an efficient robust aerodynamic/stealth design optimization method based on the proposed gradient-enhanced multi-fidelity polynomial chaos-Kriging model. This proposed method is validated to significantly improve the aerodynamic/stealth/control performance of a tailless flying wing. | ||||
| 17:30 | 18:00 | 8.9.3 |
DESIGN AND AERODYNAMIC OPTIMIZATION OF A THIN-HAUL AIRCRAFT WITH DISTRIBUTED ELECTRIC PROPULSION: ZETHA G. Beghetto¹, M. Boffadossi¹; ¹Politecnico di Milano, Italy Presenter: Giacomo Beghetto, DAER, Politecnico di Milano The work focuses on the design and aerodynamic analysis of a thin-haul aircraft with DEP. After the aircraft's preliminary design, the aerodynamic improvements achieved through the DEP activation are analyzed. A significant lift enhancement is obtained due to the propellers' slipstream induced on the wing, leading to radical modifications of the aircraft in order to improve efficiency and range. | ||||
| 18:00 | 18:30 | 8.9.4 |
ABOUT MODELLING OF EMPIRICAL CORRELATIONS WITHIN AERODYNAMIC PROFILES USING HIGHER ORDER ARTIFICIAL NEURAL NETWORKS P. Kovar, Center of Advanced Aerospace Technology, Czech Republic; J. Fürst, Department of Technical Mathematics, Faculty of Mechanical Engin, Czech Republic Nowadays, numerical simulations remain time-consuming. Consequently, empirical correlations keep their importance as a valuable tool for compressor design and for estimating flow parameters. This contribution utilizes higher order neural networks to predict flow parameters for new family of airfoils, offering an alternative to time-expensive simulations or inaccurate empirical correlations. | ||||
| additional information (interactive) | 8.9.R |
LOCALIZED AERODYNAMIC SHAPE OPTIMIZATION FOR AUTOMOTIVE APPLICATIONS M. Nayman¹, R.E, Perez¹; ¹Royal Military College of Canada, Canada | |||||
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| 16:30 | 17:00 | 9.9.1 |
WEATHER-AWARE INTEGRATED AIRPORT/AIRSPACE CAPACITY PREDICTION TECHNOLOGIES T. Reynolds¹, K.C. Woodrow¹, H. Iskenderian¹, D. Johnson¹, M. Matthews¹, J. Venuti¹, M. Worris¹, G. Enea¹, B. Crawley, NAV CANADA, Canada; ¹MIT Lincoln Laboratory, United States Presenter: Gabriele Enea, MIT Lincoln Laboratory This paper will describe an integrated suite of technologies being developed to enable more effective weather-aware decision support for Air Traffic Management needs. Technologies tailored to specific needs in terms of weather situational awareness and impact translation at airport, terminal and en route airspace resources are described. | ||||
| 17:00 | 17:30 | 9.9.2 |
PROBING AND MODELING LARGE-SCALE AIRLINE NETWORK DISRUPTIONS: 2022 SOUTHWEST AIRLINES SCHEDULING CRISIS M. Peng¹, A. Kamat¹, V. Tran, Harvard University, United States; C. Dawson², C. Fan², M.Z. Li¹; ¹University of Michigan, United States ;²Massachusetts Institute of Technology, United States Presenter: Max Zhaoyu Li Large-scale airline disruptions result in large financial losses, along with passenger dissatisfaction and environmental impacts. We extract data-driven insights regarding the Southwest Airlines December 2022 disruption, using agent-based modeling and probabilistic programming approaches. Our work will be helpful for airline and air traffic control stakeholders during decision-making processes. | ||||
| 17:30 | 18:00 | 9.9.3 |
TIME-BASED CONTROL TO REDUCE TRAJECTORY COMPLEXITY IN THE FLOW-CENTRIC AIR TRAFFIC CONTROL PARADIGM K. Tominaga¹, N. Inoue¹, M. Schultz, University of the Bundeswehr Munich, Germany; Y. Zeng, Nanyang Technological University Singapore, Singapore; E. Itoh¹; ¹The University of Tokyo, Japan Presenter: Eri Itoh, The University of Tokyo This study examines how planned trajectory complexity in an ASEAN en-route airspace may be reduced using tactical time control alone. Networks of fluid queues are applied at hotspots as well as departures, and the effectiveness is measured in a Fast-Time Simulation experiment. Its findings are anticipated to facilitate evaluation of Flow-Centric Operations, a novel Air Traffic Control paradigm. | ||||
| 18:00 | 18:30 | 9.9.4 |
APPLICATIONS AND CHALLENGES FOR AIRBORNE AD-HOC COMMUNICATION NETWORKS IN ORP AIRSPACES USING THE L-BAND T. Marks¹, A. Hillebrecht¹, M.A. Bellido-Manganell¹; ¹German Aerospace Center, Germany Presenter: Alexander Hillebrecht, German Aerospace Center Data communication is an essential part of today's air traffic operations, enabling more flexible routing of aircraft leading to increased airspace capacity. In our work we analyze applications enabled by AANETs and identify challenges for the design and development of the communication technology with a focus on using the L-Band. | ||||
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| 16:30 | 17:00 | 10.9.1 |
DESIGN OF HYDROGEN STORAGE SYSTEMS IN NEW-GENERATION REGIONAL AIRCRAFT V. Memmolo¹, L.M. Cardone¹, G. Petrone¹, S. De Rosa¹; ¹Università degli Studi di Napoli Federico II, Italy This paper showcases the detailed design of hydrogen storing system for regional aircraft. Starting from TLAR, the hydrogen is sized and then designed in detail considering different solutions both for load bearing and proper liquid containment. A further analysis shows the necessity to account the weight of the system versus its volume/surface ratio as a key parameter for preliminary design of such systems. | ||||
| 17:00 | 17:30 | 10.9.2 |
THERMAL AND MECHANICAL CYCLING OF THIN-PLY COMPOSITES FOR CRYOGENIC APPLICATIONS M.S. Loukil¹, J. Xu¹, E. Marklund², M. Merzkirch², F. Moreau³, F. Ohlsson³; ¹Linköping University, Sweden ;²Research Institutes of Sweden RISE, Sweden ;³Oxeon AB, Sweden During this work, the materials (carbon fiber and matrix) were selected and cross ply [90/0]4s composite laminates were manufactured using filament winding. The laminates were inspected for damage, and samples prepared for testing. Quasi-static, mechanical fatigue and thermal fatigue tests were performed. Only a few matrix cracks were observed at a very high load and high number of cycles. | ||||
| 17:30 | 18:00 | 10.9.3 |
NUMERICAL SOLUTION OF LOX FLOW IN A LIQUID ROCKET ENGINE ADDITIVELY MANUFACTURED COOLING CHANNEL N. Monokrousos¹, L. Könözsy¹, V. Pachidis¹, E. Sozio², F. Rossi²; ¹Cranfield University, United Kingdom ;²Pangea Aerospace, Spain The numerical solution of an LOx flow in an AM cooling channel of an aerospike engine demonstrator is presented. Roughness is generated and modeled through a Gaussian method, instead of being measured. This is of great industrial importance, in terms of cost and time reduction. For the solution of the coolant flow, turbulence models available in commercial CFD packages are employed. | ||||
| 18:00 | 18:30 | 10.9.4 |
OPTIMIZATION OF POST-PROCESSING HEAT TREATMENT FOR LPBF MODIFIED 2024 ALUMINIUM ALLOY M. Bona¹, A.M. Grande¹; ¹Politecnico di Milano, Italy Investigating titanium-modified aluminium 2024 via LPBF through Scheil simulations and SEM analysis to understand the formation of inoculants and classic precipitation. Classic T6 treatment and alternative pathways are explored to improve mechanical properties. Microhardness measurements and as-built vs. post-heat-treatment microstructure analyses enrich understanding of the alloy’s behaviour. | ||||
| additional information (interactive) | 10.9.R |
ANALYSIS OF THE POSSIBILITY OF INCREASING THE THERMAL RESISTANCE OF EPOXY RESIN WITH CWNT AND MMT R. Szczepaniak¹, P. Przybylek¹, D. Szczechula¹, A. Krzyzak¹, A. Komorek¹, G. Woroniak, Bialystok University of Technology, Poland; ¹Polish Air Force University, Poland | |||||
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| 16:30 | 17:00 | 11.9.1 |
THE EFFECTS OF ENGINE MASS AND LOCATION ON THE FLUTTER CHARACTERISTICS OF AIRCRAFT WINGS J.R. Banerjee¹, A. Ananthapuvirajah¹, P.H. Cabral, Embraer S.A., Brazil; ¹City, University of London, United Kingdom The effects of engine mass and its location on the free vibration and flutter behaviour of two representative transport aircraft wings are investigated using an assembly of coupled bending-torsion beams and Theodorsen type unsteady aerodynamics. The aeroelastic computer program CALFUN (CALculation of Flutter speed Using Normal mode method) has been used when computing the results which are discussed and commented on | ||||
| 17:00 | 17:30 | 11.9.2 |
INFLUENCE OF SKIN CURVATURE ON WINGBOX OPTIMIZATION WITH NONLINEAR STRUCTURAL STABILITY CONSTRAINTS F.M.A. Mitrotta¹, A. Pirrera¹, T. Macquart¹, J.E. Cooper¹, A. Pereira do Prado², P.H. Cabral²; ¹University of Bristol, United Kingdom ;²Embraer, Brazil Embraer's Aeroelastic Tailoring Framework pioneers a nonlinear structural stability approach to reduce aircraft emissions. Tests on a simplified version of NASA's CRM wingbox achieved up to 29.6% mass reduction, surpassing linear methods. Using MSC Nastran and OpenAeroStruct, the study explores complex scenarios, promising more efficient and lightweight airframes for sustainable aviation. | ||||
| 17:30 | 18:00 | 11.9.3 |
RANDOM MATRIX MODELLING FOR UNCERTAINTY QUANTIFICATION IN PRESTRESSED STRUCTURES A. Mannoosseril¹, S. Adhikari¹, A.P. Prado², P.H. Cabral²; ¹James Watt School of Engineering, University of Glasgow, United Kingdom ;²Embraer S.A., São José dos Campos, Brazil, Brazil This paper introduces random-matrix-based uncertainty quantification to prestressed complex structures, which is particularly beneficial for large-scale structures such as aircraft. The proposed Wishart Random Matrix model quantifies uncertainty in critical structural components—mass, stiffness, and damping matrices. The approach is implemented using NASTRAN, Monte Carlo Simulations and Python. | ||||
| 18:00 | 18:30 | 11.9.4 |
FLUID-SOLID INTERACTIVE MODELLING OF FABRIC-BASED ATMOSPHERIC ENTRY SIZED AERODYNAMIC DECELARATORS E. Malof¹, J. Bayandor¹; ¹University at Buffalo CRASH Lab, United States In the aeronautical industry, parachutes are the main aerodynamic decelerator used to slow aircraft, cargo and landing vehicles. Numerical solvers allow for multiple parachute designs to be simulated in numerous environments at reduced costs. The work in this paper improves the modelling of multiple parachutes from a packed to fully deployed state, showing the entire parachute inflation process. | ||||
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| 16:30 | 17:00 | 12.9.1 |
PROCESS MODELLING OF COMPOSITES USING A MULTISCALE FRAMEWORK G.M. Odegard, Michigan Technological University, United States; M. Maiaru, Columbia University, United States The goal of this research is to use molecular dynamics (MD) and finite element analysis (FEA) to predict the residual stresses in composite laminates and optimize processing parameters to minimize the residual stress | ||||
| 17:00 | 17:30 | 12.9.2 |
MICROMECHANICAL MODELING OF THE VISCOELASTIC-VISCOPLASTIC RESPONSE OF FIBER-REINFORCED COMPOSITES Tian Nan¹, Gun Jin Yun, Seoul National University, North Korea; Chao Zhang¹; ¹Northwestern Polytechnical University, China This work describes a newly proposed viscoelastic–viscoplastic constitutive model that is used to characterize the effective mechanical behaviors of fiber-reinforced composites based on micromechanical modeling. The proposed micromechanics-based constitutive model has an explicit form, which contributes to the computational efficiency of the multiscale simulations for the composite structures. | ||||
| 17:30 | 18:00 | 12.9.3 |
A DYNAMIC TEST METHODOLOGY FOR DETERMINING THE LONGITUDINAL COMPRESSIVE RESPONSE OF CARBON FIBER COMPOSITE TOWS J. Gu¹, Y. Bai¹, Z. Zhao¹, C. Zhang¹; ¹Northwestern Polytechnical University, China Textile composites have been applied widely in aircraft structure, such as fan blades and cases of aero-engine, since of their excellent impact resistance, great delamination resistance and high damage tolerance [1]. Composite fiber tows, as the main load-bearing component, have a critical influence on the dynamic performance of textile composites and even the whole composite structures [2]. However, determination of the Intrinsic properties of individual composite fiber tow mainly rely on theoretical and numerical predictions. Because of small size and challenges in effective loading of this unidirectional composites [3] in dynamic testing, it strain-rate effects still lacks direct test methodology and experimental results. In this study, a dynamic compression test method for composite fiber tows is proposed based on the Split Hopkinson compressive bar system combined with an ultra-high-speed camera. Firstly, the volume fraction, porosity content and fiber misalignment distribution of composite tows are evaluated characterized to compare the influence of different preparation methods. The comparison of several common specimen designs by quasi-static and dynamic compression test and finite element simulation shows that dumbbell design is a reasonable design. Then, the validity and applicability of the test methodology are verified systematically and comprehensively from stress distribution, data reduction method, dynamic stress balance and failure morphology. The preliminary test results show that the compressive properties of composite fiber tows are significantly dependent on the strain rate, and the compressive strength increases by more than 50% when the strain rate ranges from 0.01 s-1 to 400 s-1. This work will realize the direct and efficient test of composite tows and provide insightful inputs for multiscale analysis of textile composite. | ||||
| 18:00 | 18:30 | 12.9.4 |
INVESTIGATION ON VARIABLE-HEIGHT PROTRUSION ARRANGEMENT OF METAL–COMPOSITE HYBRID JOINTS UNDER A TENSILE LOAD Y. Zhao, China; W. Wang, China; X. Wan, China Metal–composite hybrid joints with variable-height pins reinforced were numerically investigated to analysis its mechanical behavior. Results showed that stress concentration of these joints occurred in different positions, and the reinforcing efficiency of protrusions varied across the overlapping area. These findings provided guidance for optimal protrusion arrangement of hybrid joints. | ||||
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| 16:30 | 17:00 | 13.9.1 |
MODEL-BASED CONCEPTUAL DESIGN AND EVALUATION OF A SOLID-FUEL SCRAMJET VEHICLE M. Bhardwaj¹, S. Rajashankar¹, N. Ananthkrishnan¹, A. Sharma¹, W.-D. Ki², H.-J. Namkoung²; ¹Yanxiki Tech, India ;²Hyundai Rotem, South Korea Presenter: Hyuck-Joon Namkoung, Hyundai Rotem A solid-fuel scramjet (SFSJ) vehicle is conceptually designed. Initially, an integrated model is constructed in MATLAB where each engine component is modeled employing empirical data or analytical relations. Aim is to ensure that the model generates ample thrust. Subsequently, the SFSJ is modeled in Simulink. Comparison of results from MATLAB and Simulink validates the design's integrity. | ||||
| 17:00 | 17:30 | 13.9.2 |
AERODYNAMIC DEFORMATION EXPERIMENT OF SERPENTINE NOZZLE FOR TURBOFAN AND ANALYSIS OF FLUID-STRUCTURE INTERACTION METHOD Q.-L. Li¹, L. Zhou¹, Z.-X. Wang¹, X.-B. Zhang¹, S. Huang¹; ¹Northwestern Polytechnical University, China In this paper, an experimental study on structural deformation of serpentine nozzle for turbofan engine is carried out?and the reliability of one-way/two-way fluid-structure coupled was verified. The deformation is mainly located in the second bend channel, and the two-way fluid-structure coupled method can more accurately simulate the aerodynamic deformation characteristics of the nozzle. | ||||
| 17:30 | 18:00 | 13.9.3 |
DESIGN OF A WIND TUNNEL MODEL FOR A REUSABLE LAUNCH VEHICLE DURING ITS LANDING BURN A.T. Hoang¹, N.J. Lawson¹, T. Bykerk, German Aerospace Center (DLR), Germany; ¹The University of Sydney, Australia Presenter: Nicholas J. Lawson, The University of Sydney This paper presents the design and measurements from a wind tunnel model of a reusable launch vehicle (RLV) during its landing burn. The model of the body and supersonic nozzle will be tested in a low-speed wind tunnel, and aerodynamic data with a freestream Mach number <0.15 will be presented. | ||||
| 18:00 | 18:30 | 13.9.4 |
COMPARISON OF LIFE CYCLE COST FOR MACH 8 AND MACH 5 HYPERSONIC PASSENGERS AIRCRAFT L. Pugliese¹, D. Ferretto¹, R. Fusaro¹, N. Viola¹; ¹Politecnico di Torino, Italy This paper analyses the life cycle cost of two hypersonic long-haul passengers aircraft, characterized by a Mach number in cruise of about 8 and 5 respectively. It aims at promoting a comparison between different architectures and mission concepts in order to understand the impact of vehicle size and operating conditions on final cost breakdown and ticket price for the reference payload. | ||||
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| 16:30 | 17:00 | 14.9.1 |
DECODING AN IN-FLIGHT REFUELING INCIDENT: AVIATION COMPLEXITY THROUGH STAMP/CAST AND ACCIMAP METHODS J.G. Fowler¹, D.C. Fernandes¹, D.M.C. de Lima¹, G.V. da Rocha¹, M.M. Cardoso Júnior¹; ¹Aeronautic Institute of Technology, Brazil Presenter: Daniella Castro Fernandes, Aeronautic Institute of Technology This study examines an accident during an in-flight refueling. Utilizing Rasmussen's Accimap and Leveson's STAMP/CAST methodologies, it identifies contributing factors and control failures. Emphasizing the demanding nature of in-flight refueling and the role of human factors, the study advocates for ongoing research in ergonomics. Methodologies' strengths and limitations are discussed. | ||||
| 17:00 | 17:30 | 14.9.2 |
DYNAMIC RESPONSE MONITORING OF FLIGHT CONTROL WITH INCREMENTAL NONLINEAR DYNAMIC INVERSION H. Hofsäß¹, F. Holzapfel¹; ¹Technical University of Munich, Germany A concept for model-based monitoring of aircraft responses to inputs at the pilot inceptor is proposed. The derived modelling structure adds to the state of the art as it provides robustness towards false alarms due to uncertain inner-loop dynamics and thereby improves failure detection capability with respect to allowable aircraft responses as given in high-level dynamic response requirements. | ||||
| 17:30 | 18:00 | 14.9.3 |
INVESTIGATION OF THE AERODYNAMIC CHARACTERISTICS OF WINGS UNDER ICING CONDITIONS AT VARIOUS SWEEP ANGLES X. Xu¹, Y. Zhang¹, G. Chen¹, X. Ma, Xi'an Jiaotong UniversityXi'an Jiaotong University, China; ¹Xi'an Jiaotong University, China The aerodynamic characteristics of multiple swept wing ice wind tunnel test models are determined by numerically simulating the distribution of velocity and angle of attack. This allows for the calculation of parameters such as lift drag coefficient, which are used to generate initial samples. The polynomial chaotic technique is employed to create a surrogate model for uncertainty analysis. | ||||
| 18:00 | 18:30 | 14.9.4 |
SLEEPINESS IN BRAZILIAN AVIATION: A PROBLEM-SOLVING APPROACH V. Gomes¹, T. Paiva¹, A. Herculano¹, T. Dias¹, M.M. Cardoso-Junior¹, M.C. Belderrain¹; ¹ITA, Brazil Excessive daytime sleepiness can have a negative impact on performance, memory, and attention, increasing the risk of accidents, including air accidents. It is a condition that, when diagnosed and treated, can significantly reduce these risks. By using the Soft Systems Methodology approach, the main relevant systems, the necessary transformations, and the strategic human activity systems were identified to promote culturally viable and desirable changes in the systemic context. As a concrete result, strategic actions were proposed for each identified transformation, which, if implemented, have the potential to minimize the risks of air accidents resulting from Excessive Daytime Sleepiness. Finally, control criteria were established that provide a clear roadmap for the implementation and evaluation of the success of these transformations. The supersystem developed in this work presents a systematic and robust approach to addressing the complex and multifaceted issue of fatigue and sleepiness management in aviation | ||||
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| 16:30 | 17:00 | 15.9.1 |
FLIGHT MECHANICAL ANALYSIS OF A VERY FLEXIBLE HIGH-ALTITUDE PLATFORM UNDER UNCERTAINTY CONSIDERATIONS Y.J. Hasan¹, N. Fezans¹, A. Voß, DLR Institute of Aeroelasticity, Germany; ¹DLR Institute of Flight Systems, Germany This paper deals with a flight mechanical analysis of the high-altitude platform developed by the German Aerospace Center (DLR) respecting uncertainties. For this purpose, various weight and balance parameters of the used flexible flight dynamics model are varied and their influences on the aircraft's flight dynamics are assessed. | ||||
| 17:00 | 17:30 | 15.9.2 |
FLIGHT PERFORMANCE AND DYNAMICS OF AN UNCONVENTIONAL SOLAR POWERED UAS G. Charruaz¹, A. Borgia¹, A. Braghin¹, T. Bussi¹, A. Esposito¹, A. Pescosolido¹; ¹Politecnico di Torino, Italy This paper discusses the performance and flight dynamics analysis of an unconventional, highly efficient solar-powered unmanned aerial system. The design geometry, aerodynamic performance, and mass distribution were analysed to find a solution for a stable and efficient aircraft. The aim of the project is to design and build a sustainable UAS. | ||||
| 17:30 | 18:00 | 15.9.3 |
ON THE DEVELOPMENT OF THE STRUCTURAL DIGITAL TWIN OF AN UNMANNED AERIAL VEHICLE X. Zhou¹, M. Dziendzikowski², K. Dragan², M. Giglio³, L. Dong¹, C. Sbarufatti³; ¹Beihang University, China ;²Instytut Techniczny Wojsk Lotniczych, Poland ;³Politecnico di Milano, Italy This paper addresses the scale differences between overall UAV loading and structural detail damage. The integration of load tracking, multi-level structural analysis, and probabilistic crack growth models into a UAV digital twin offers a comprehensive solution, demonstrating efficiency and accuracy and paving the way for real-time damage prediction using the digital twin methodology. | ||||
| 18:00 | 18:30 | 15.9.4 |
DYNAMIC FREE FLIGHT TESTS WITH A SUB-SCALE AIRPLANE DESIGNED ACCORDING TO THE FROUDE NUMBER C. Fischer, Instituto Federal de São Paulo and Aeronautics Institute of Tec, Brazil; A.S. Davi, Lilium GmbH, Germany; R.G.A. da Silva¹, L.C.S. Goes¹; ¹Aeronautics Institute of Technology, Brazil The use of sub-scales to study flight dynamics is an area that can provide excellent results. With the development of electronics, free flight tests to obtain flight dynamics data on sub-scale aircraft have become increasingly attractive. This paper presents the development of a sub-scale aircraft following the Froude number scaling technique used to achieve representativeness in flight dynamics. | ||||
| additional information (interactive) | 15.9.R |
MANNED AND UNMANNED AERIAL VEHICLES COOPERATIVE COMBAT FRAMEWORK BASED ON LARGE LANGUAGE MODELS H. Shi¹, S. Li, AVIC Chengdu Aircraft Industrial (Group) Co., Ltd., China; Z. Huang¹, s. Li¹, A. Li¹, Y. Zhou¹; ¹BEIHANG UNIVERSITY, China | |||||
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| 16:30 | 17:00 | 16.9.1 |
THERMAL AND GRINDING PERFORMANCE OF 3D PRINTED COMPLIANCE GRINDING TOOLS WITH ROTARY-ENHANCED HEAT TRANSFER STRUCTURE M.C. Li, China; S. Yan, China; K.F. Zhang, China; W. Wang, China; L. Zou, China; Y. Huang, China Presenter: Wenxi Wang Compliance ball-head (BE) grinding tools show promise for precision grinding of complex curved components in narrow areas, represented by integral discs. However, the grinding process generates significant heat in the grinding zone, which can limit the tool's service life and performance. To address this issue, a rotary-enhanced heat transfer (RHET) structure based on turbine blade was designed in this study. Numerical simulations were used to demonstrate the heat transfer mechanism of the tool. The tools were structured using multi jet fusion and their grinding performance was compared to conventional structures through robot-assisted grinding of titanium plates. The results indicated that the REHT improved the heat transfer capability of the BE by introducing high momentum fluids and increasing the pressure at the inner wall. The REHT structure resulted in a reduction of the grinding temperature by over 19.84%, leading to a tool life extension of more than 40%. Furthermore, compliant grinding tools with REHT resulted in a higher cumulative material removal alongside lower and more consistent surface roughness (Ra). | ||||
| 17:00 | 17:30 | 16.9.2 |
CYBER-PHYSICAL SYSTEM IMPLEMENTATION FOR THE AR-ASSISTED AIT OF AEROSPACE COMPONENTS J. Pesce¹, A. Carini¹, M. Marinacci¹, M. Boscia¹, P. Marzioli¹, M. Pasquali¹, M. Eugeni¹, M. Mecella¹, P. Piergentili¹, P. Gaudenzi¹; ¹Sapienza University of Rome, Italy This research explores the integration of cyber-physical systems (CPS) and augmented reality (AR) in aerospace assembly, integration, and testing (AIT) processes. Highlighting CPS's real-time monitoring and control capabilities and AR's visual overlays via the implementation of different case studies, the study showcases their transformative potential in the aerospace sector. | ||||
| 17:30 | 18:00 | 16.9.3 |
DESIGN AND DEVELOPMENT OF THE VISUAL AND AUDITORY LAYER FOR DIFFERENT CABIN/COCKPIT LAYOUT A. Alaimo, Kore Università di Enna, Italy; S. Bagassi¹, E. Carrera, Politecnico di Torino, Italy; T. Fadda¹, M.C. Moruzzi¹; ¹Università di Bologna, Italy This paper aims to develop an extended reality model for the human-centered design of aircraft acoustic comfort. Starting with the vibro-acoustic simulation to evaluate the noise level and the effectiveness of the applied solutions, we move on to the auralization of the acoustic footprint and then to its possible evaluation by different user categories (flight crew and passengers). | ||||
| 18:00 | 18:30 | 16.9.4 |
STUDY ON CONTROL PERFORMANCE OF A NEW TYPE OF TILT-ROTOR AIRCRAFT K. Miyabe¹, M. Bando¹, S. Hokamoto¹; ¹Kyushu Univercity, Japan We propose a new type of tilt-rotor aircraft, whose rotors are tilted by arm-mechanisms. The aircraft can enhance the stability during the transitional mode and independent control for its three attitude motions is possible only by rotor thrusts without control surfaces. | ||||
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| 16:30 | 17:00 | 17.9.1 |
MRO FOR VTOLS IN A FUNCTIONAL SEQUENCES SOLUTION SPACE S. Papakonstantinou¹, D. Kloock-Schreiber¹, M. Ziegler², A.N. Mishra, Hamburg University of Technology, Germany; P.K. Jaisawal¹, U. Wieczorek², V. Gollnick¹; ¹Hamburg University of Technology, ILT, Germany ;²Airbus Protect, Germany Presenter: Stephanos Papakonstantinou, TUHH/ILT The paper reviews current maintenance strategies for VTOLs by classifying them into various categories. The paper also addresses functional design aspects for vertiport using BPMN diagrams. The solution space of BPMN diagrams are extended by integrating damage data generation module. Additionally, security analysis is conducted for drone based visual inspection of vertiport. | ||||
| 17:00 | 17:30 | 17.9.2 |
ASSESSMENT OF A HIGHLY PARAMETERIZED STEADY-STATE MICROSCALE WIND SIMULATOR FOR URBAN AIR MOBILITY APPLICATIONS D.S. Nithya¹, G. Quaranta¹, V. Muscarello², M. Liang²; ¹Politecnico di Milano, Italy ;²RMIT University, Australia This paper is targeted to assess the capability of fast computing Wind models, employed within the Wind Engineering and Atmospheric science domain, to generate low-altitude wind data for Urban Air Mobility applications. Therefore, the proposed approach is to reproduce Wind Tunnel test conditions of flow around a building with sufficient accuracy for the comparitive analysis and assessment. | ||||
| 17:30 | 18:00 | 17.9.3 |
A DESIGN OF VFR APPROACH AND DEPARTURE PROCEDURES OF UAM AT VERTIPORTS ADJACENT TO THE AIRPORT S. Kim¹, O. Park¹, H.-S. Shin¹; ¹Cranfield University, United Kingdom This study focuses on identifying key elements vital for the establishment and operation of urban air mobility (UAM) vertiports adjacent to airports based on the literature survey. On top of that, the approach and departure procedures of UAM to the vertiport adjacent to Incheon International Airport (ICN) were designed. | ||||
| 18:00 | 18:30 | 17.9.4 |
ENVIRONMENTAL AND ECONOMIC ASSESSMENT OF AN EVTOL AIRCRAFT FLEET FOR URBAN AIR MOBILITY M. Fioriti¹, M. Borghi¹, G. Pavan¹; ¹Politecnico di Torino, Italy Presenter: Marco Fioriti, Politecnico di Torino This paper has the aim to investigate the economic and the environmental impact of the UAM vehicles life cycle. Parametric cost and environmental impact estimation models are employed to provide flexible estimation considering different technologies and vehicle performance. The investigation also includes part of the needed infrastructures to enable the operation such as vertiports and logistics. | ||||
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| 10:00 | 10:30 | 1.10.1 |
AIRBUS COMMERCIAL AVIATION SUSTAINABILITY STRATEGY I. Bloy, AIRBUS, France AIRBUS SUSTAINABILITY STRATEGY | ||||
| 10:30 | 11:00 | 1.10.2 |
THE CHALLENGE OF SUSTAINABILITY IN COMMERCIAL AVIATION T. Beezhold, Boeing, United States Invited speaker for the Global Sustainable Aviation track. | ||||
| 11:00 | 11:30 | 1.10.3 |
EMBRAER SUSTAINABILITY STRATEGY CS Silva, Embraer, Brazil invited speaker for the Global Sustainable Aviation track | ||||
| 11:30 | 12:00 | 1.10.4 |
ATR COMMERCIAL AVIATION SUSTAINABILITY STRATEGY D. Cuchet, ATR, France invited speaker for the Sustainable Aviation track | ||||
| 12:00 | 12:30 | 1.10.5 |
PANEL DISCUSSION PD D, PANEL DISCUSSION | ||||
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| 10:00 | 10:30 | 2.10.1 |
HIGH-LIFT PREDICTION WORKSHOPS: RETROSPECTIVE, LESSONS LEARNED, AND FUTURE PROSPECTS C.L. Rumsey, NASA Langley Research Center, United States The AIAA High-Lift Prediction Workshop (HLPW) series has been ongoing since 2010. At these workshops, engineers interested in computationally predicting the flows over high-lift configurations have compared and collab-orated with others in an effort to further the goals of the workshop. These goals include: (1) assessing the numerical prediction capability (meshing, numerics, turbulence modeling, high-performance computing requirements, etc.) of current-generation CFD technology/codes for swept, medium-to-high-aspect ratio wings for landing/take-off (high-lift) configurations; (2) developing practical modeling guidelines for CFD prediction of high-lift flow fields; (3) deter-mining the elements of high-lift flow physics that are critical for modeling to enable the development of more accurate prediction methods and tools; and (4) enhancing CFD prediction capability for practical high-lift aerodynamic design and optimization. By the time of the 34th ICAS Congress, five HLPWs will have been completed, and still more workshops are planned for the future. Significant progress has been made in the workshop process itself, encouraging a more rapid rate of learning and faster dissemination of knowledge and ideas to the high-lift prediction community. This paper will provide a 14-year retrospective on the workshop series, including its trajectory over the years, what has been learned, what still needs to be accomplished, and how integrated validation testing plays a critical role. | ||||
| 10:30 | 11:00 | 2.10.2 |
CFD VALIDATION EXPERIMENTS AT DLR: OVERVIEW AND LESSONS-LEARNED C. Grabe, DLR, Germany Modelling turbulent flows using the Reynolds-Averaged Navier-Stokes (RANS) equations is a key element for highly accurate flow simulations with CFD solvers and a standard tool in the aviation industry. At the design point of today's commercial aircrafts, RANS turbulence models offer a good compromise between efficiency and accuracy. However, the quality of these predictions deteriorates towards the edge of the flight envelope. This is particularly the case if flow separation is involved, e.g., at low speeds (take-off and landing) near maximum lift. In order to increase confidence in CFD, high-quality validation experiments tailored to the flow phenomena occurring at low speeds of an aircraft are necessary. DLR has designed and conducted such experiments for various relevant flow phenomena including turbulent boundary layers under adverse pressure gradient, thin turbulent boundary layer separation bubbles and reattachment as well as turbulent longitudinal vortices. Moreover, complex aircraft testcases like the high-lift CRM are needed to assess the interplay of different flow features and the capability of RANS turbulence models to capture them. The talk provides an overview of these experiments and their results, the conclusions we can draw from them and an outlook on future requirements. | ||||
| 11:00 | 11:30 | 2.10.3 |
THE BEVERLI HILL EXPERIMENTS FOR SMOOTH-BODY TURBULENT FLOW SEPARATION - RETROSPECTIVE, LESSONS LEARNED, AND FUTURE PROSPECTS C.J. Roy¹, K.T. Lowe¹, W.J. Devenport¹, A. Borgoltz¹, A. Gargiulo, University of Virginia, United States; ¹Virginia Tech, United States Virginia Tech, with support from NASA-Langley, has acquired high-quality turbulence model validation data for three-dimensional smooth-body flow separation. The geometry, called the BeVERLI Hill (Benchmark Validation Experiments for RANS and LES Investigations), has been studied at subsonic Reynolds numbers between 250k and 650k based on the hill height. Experimental data have been obtained for the hill at nominal zero, 30, and 45 degree orientations and includes extensive oil flow visualizations, surface pressures, skin friction via oil film interferometry and laser Doppler velocimetry, and mean and fluctuating velocities using particle image velocimetry, laser Doppler velocimetry, and pitot-static rakes. Detailed boundary conditions and oncoming boundary layer data have also been measured. | ||||
| 11:30 | 12:00 | 2.10.4 |
SYSTEMATIC CFD VERIFICATION - RESULTS FROM THE 2024 HIGH FIDELITY CFD VERIFICATION WORKSHOP M. Galbraith, United States A large number of Computational Fluid Dynamics (CFD) workshops have been held over the past decade to both assess and advance the current state of the art. These workshops will generally put forth a suite of test cases and participants from academia, industry, and governments will attempt to compute fluid dynamic solutions to predict integrated quantities such as lift, drag, and moment coeffects, or local quantities such as velocity profiles and surface pressure. Inevitably, when all the results are summarized, there is typically a wide scatter in the data. Some of this scatter can be explained by participants using different model fidelities, such as Lattice-Boltzmann vs. Large Eddy Simulation (LES) vs. Reynolds Averaged Navier-Stokes (RANS), or using vastly different meshes, for example. Other differences are less obvious. Most workshops will have multiple participants supposedly running the exact same model yet obtaining different results. The sources of this discrepancies could stem from lack of non-linear residual convergence, order of accuracy of the discretization, stabilization terms, bugs in the software, or user input errors to name a few. The overarching goal of The High-Fidelity CFD Verification Workshop is to establish requirements to obtain consistent results across a range of discretizations and solution schemes. | ||||
| 12:00 | 12:30 | 2.10.5 |
PANEL DISCUSSION P D, PANEL DISCUSSION | ||||
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| 10:00 | 10:30 | 3.10.1 |
PERFORMANCE AND ECONOMIC ASSESSMENT OF A WING-INTEGRATED HYBRID LAMINAR FLOW CONTROL SYSTEM B.M.H.J. Fröhler¹, A.A. Pohya¹, J. Häßy¹, T. Kilian¹, A.H. Bismark¹, M. Radestock, Germany; D. Cruz Palacios, Aernnova Aerospace, Spain; ¹German Aerospace Center (DLR), Germany This study demonstrates the integration of a HFLC system into a wing in an industrial context. The goal is to evaluate the HLFC system objectively by comparing to a non-HLFC aircraft. The assessment covers a mission performance estimation and a life cycle simulation with three scenarios to determine fuel and cost savings. | ||||
| 10:30 | 11:00 | 3.10.2 |
A COST-EFFICIENT PREDICTIVE METHOD FOR AERODYNAMIC PERFORMANCE DEGRADATION OF HORIZONTAL TAIL UNDER ICING CONDITIONS S. Corcione¹, A. De Marco¹, V. Cusati¹; ¹University of Naples Federico II, Italy This study develops a cost-effective 2.5D aerodynamic method predicting icing effects on swept lifting surfaces, integrating with an aircraft's optimization workflow. Employing 2D inviscid methods and CFD simulations, it assesses planform geometry's influence on ice accretion. Results inform a quick-response prediction method, evaluated against test cases for reliability and accuracy. | ||||
| 11:00 | 11:30 | 3.10.3 |
FUEL-BASED THERMAL MANAGEMENT SYSTEM ARCHITECTURES AND TANK TEMPERATURE EVOLUTION MODELS FOR AVIATION S. Favre¹, F. Di Fede, Leonardo Labs, Leonardo S.p.A., Italy; E. Brusa¹, C. Delprete¹; ¹Politecnico di Torino, Italy Development of a dynamic, system level, model for the evaluation of thermal endurance associated with fuel-based Thermal Management Systems (F-TMS) in the aerospace sector. A hybrid-electric regional transport aircraft is taken as a reference, while TMS performance is investigated over multiple parameters, architectures, and degrees of hybridization. | ||||
| 11:30 | 12:00 | 3.10.4 |
SCOPING OF AN AIR SUPPLY CONFIGURATION FOR ACTIVE FLOW CONTROL ON A COMMERCIAL TRANSPORT AIRPLANE HIGH-LIFT SYSTEM C.P. van Dam, University of California - Davis, United States; S.S. Hosseini¹, S.A. Pandya¹; ¹NASA Ames Research Center, United States A scoping study is being conducted on the air supply for a microjet-based active flow control (AFC) system on a twin-turbofan commercial transport airplane. Microjets provide circulation control using small surface-normal pneumatic jets located near the trailing edge of a lifting surface such as a wing or flap. When located on the pressure side of the lifting surface they increase the lift, and when located on the suction side they decrease lift. In this study, microjets are considered for installation in the flaps of the high-lift version of the Common Research Model (CRM-HL). An air supply system involving bleed air from the airplane’s auxiliary power unit (APU) plus ram air provides the air to the microjets. A model based on the 1D compressible flow equations is applied to analyze the air supply system configuration and predict the microjet flow rate with the resulting airplane performance changes based on Reynolds-averaged Navier-Stokes modeling of microjets on the CRM-HL. The results of this scoping study are encouraging in that APU air can be used to entrain ram air and thereby increase the AFC mass flow rate to achieve effective lift control and airplane performance enhancement during takeoff and landing. | ||||
| 12:00 | 12:30 | 3.10.5 |
OPTIMIZATION PROCEDURE FOR THE WING OF A MARS EXPLORATION DRONE A. Viviani¹, A. Aprovitola¹, L. Iuspa², G. Pezzella²; ¹Università della Campania Luigi Vanvitelli , Italy ;²Università della Campania Luigi Vanvitelli , Italy Presenter: Andrea Aprovitola, Università della Campania The present paper focuses on a multi-step optimization procedure of a wing potentially suitable for a Martian exploration drone. Starting form the determination of the sub-optimal wing section specifically tailored for low-Reynolds conditions, the procedure is able to provide an optimal 3D wing able to allow an aerodynamic high performance exploration flight in the Mars atmosphere. | ||||
| Reserve Paper | 3.10.R |
DESIGN OPTIMIZATION OF A WIG CRAFT’S HIGH LIFT DEVICE CONSIDERING GROUND EFFECT Y.H. Wang¹, W.P. Song¹, H. Nie¹, K.F. Zheng¹, Z.H. Han¹; ¹Northwestern Polytechnical University, China | |||||
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| 10:00 | 10:30 | 4.10.1 |
SONIC BOOM COMPARATIVE STUDY BETWEEN MACH 4.7 OUTDOOR EXPERIMENTAL TESTS AND NUMERICAL SIMULATIONS G. Fasulo¹, L. Federico¹, F. Petrosino¹, S. Graziani², N. Viola², S. Hengy³, B. Martinez³, M. Albisser³; ¹Italian Aerospace Research Centre (CIRA), Italy ;²Politecnico di Torino, Italy ;³French-German research institute of Saint-Louis (ISL), France The following paper will compare the numerical and experimental results of the sonic boom test carried out at ISL’s facility within the MORE&LESS project with the Stratofly model. | ||||
| 10:30 | 11:00 | 4.10.2 |
LANDING AND TAKEOFF NOISE PREDICTION OF CONCEPTUAL SUPERSONIC AIRCRAFT M. Graebert¹, R. Jaron¹, M. Plohr¹, S. Zenkner¹, C. Richter², C. Stöhr², C. Villena Munoz, Cranfield University, United Kingdom; M.-J. van der Meulen³, R. Habing³, M. Huet, ONERA, France; F. Petrosino*, M. Barbarino*, F. Fischer, MTU, Germany; O. Zaporozhets, Institute of Aviation, Poland; ¹DLR, Germany ;²Rolls-Royce Deutschland, Germany ;³NLR, Netherlands ;*CIRA, Italy Presenter: Matti Graebert, DLR The design of commercial supersonic aircraft is challenged by the trade-off between minimising drag during supersonic cruise and reducing noise levels in areas close to the airport. In this study, advanced take-off procedures for two business jets with Ma=1.4 and Ma=1.6 and two airliners with Ma=1.8 and Ma=2.2 are optimised to meet the required noise levels. | ||||
| 11:00 | 11:30 | 4.10.3 |
SENECA’S AIRCRAFT EMISSIONS EVALUATION AND THEIRS ENVIRONMENTAL E. Terrenoire¹, M. Muller¹, E. Ramirez Correra², P. Leyland², K. Synylo³, A. Krupko³, O. Zaporozhets, ILOT, Poland; D. Lee*, B. Owen*, L. Lim*, A. Skowron*, R. Rodriguez DE Leon*, D. Marsh*, S. Matthes, DLR, Germany; P. Madden, RR UK, United Kingdom; S. Bake, RR DE, Germany; C. Mourouzidis, CU, United Kingdom; ¹ONERA, France ;²AEDS, Switzerland ;³NAU, Ukraine ;*MMU, United Kingdom The EU HORIZON 2020 SENECA project is a pre-design project for different supersonic aircraft concepts and associated engines for both passenger airliners or bizjets. This paper covers the studies concerning the aircraft engine pollutant emissions and their environmental impact. | ||||
| 11:30 | 12:00 | 4.10.4 |
DESIGN OF THE SENECA MACH 1.8 SUPERSONIC AIRLINER WITH MULTI-FIDELITY AERODYNAMIC ANALYSIS FOR NOISE-OPTIMISED TAKE-OFF TRAJECTORIES C. Villena Muñoz¹, C. Lawson¹, A. Riaz¹, A. Sharma¹; ¹Cranfield University, United Kingdom SENECA advances multi-disciplinary optimisation for sustainable supersonic aircraft, focusing on noise reduction, emission levels, fuel efficiency, and low drag. The project proposes MDO for a Mach 2.2 supersonic airliner, assessing various configurations with different fidelity levels methods. Trade-off studies contribute to a comprehensive description and analysis, enhancing data reliability. | ||||
| 12:00 | 12:30 | 4.10.5 |
CONCEPTUAL DESIGN METHODOLOGY FOR LOW-SUPERSONIC LH2-POWERED PASSENGERS AIRCRAFT E. Sunzeri¹, D. Ferretto¹, N. Viola¹; ¹Politecnico di Torino, Italy This paper aims at evaluating the possibility of designing a liquid hydrogen-powered aircraft for passengers transportation, flying in low supersonic regime along trans-Atlantic routes. A conceptual design methodology is described and results are discussed to highlight limitations of Concorde-like aircraft layouts, when non drop-in fuels are exploited. | ||||
| Reserve Paper | 4.10.R |
THERMODYNAMIC DESIGN AND EMISSIONS MODEL OF A MACH 1.8 SUPERSONIC AIRLINER ENGINE M. Plohr¹, S. Zenkner¹, S. Bake², D. Zeitz²; ¹DLR Institute of Propulsion Technology, Germany ;²Rolls-Royce Deutschland Ltd & Co KG, Germany | |||||
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| 10:00 | 10:30 | 5.10.1 |
SHAPING SUSTAINABLE AVIATION WITH CFD-BASED DESIGN OPTIMIZATION J.R.R.A. Martins¹, M.A.S. Abdul-Kaiyoom¹, E.J. Adler¹, A.C. Gray¹, H. Hajdik¹, E. Jonsson¹, A.H.R. Lamkin¹, B. Pacini¹, A. Yildirim¹; ¹University of Michigan, United States Air transportation's quest for sustainability requires groundbreaking advancements in aircraft design, particularly in the optimization of aircraft configurations, including aerodynamic shape, structural sizing, and propulsive performance. This talk will examine the latest developments in Computational Fluid Dynamics (CFD)-based design optimization, addressing the critical challenges and innovative solutions in shaping aircraft components for enhanced efficiency and reduced emissions. We will explore the sophisticated integration of CFD with structural mechanics to optimize wing aerodynamics, enhancing lift-to-drag ratios and reducing structural weight. The discussion will extend to the aerodynamic optimization of propellers and turbofans, highlighting how CFD facilitates the design of propulsion systems that integrate optimally with the airframe. By employing multidisciplinary optimization (MDO) approaches, we have advanced the design of these key aircraft components, considering complex interactions and design constraints. We will focus on adjoint methods for efficient gradient computation, which is essential for handling the large number of shape and sizing variables required in aircraft design. We will discuss the integration of these methods with computational geometry that ensures industry-grade smoothness. The talk will present case studies demonstrating the successful application of these methods in optimizing aircraft wings, along with innovative designs of propellers and turbofans, underscoring the role of CFD in driving the future of sustainable air travel. | ||||
| 10:30 | 11:00 | 5.10.2 |
ADJOINT-BASED TRANSONIC WING AERODYNAMIC SHAPE OPTIMIZATION INVESTIGATIONS L.V. Rezende Sanches, Universidade Federal do Paraná, Brazil; G.L. Olichevis Halila¹, F. Issamu Kitadani Odaguil¹, J.L.F. Azevedo, Instituto de Aeronáutica e Espaço, Brazil; ¹Embraer, Brazil Transonic wing design involves challenges related to the complex physical phenomena associated with this flow regime. Adjoint-based shape optimization is the choice to perform aerodynamic shape optimization (ASO) of transonic wings. We investigate solver strategies for both analysis and optimization steps to perform robust transonic wing optimization. | ||||
| 11:00 | 11:30 | 5.10.3 |
INVESTIGATING THE INFLUENCE OF AN INBOARD PROPELLER’S VERTICAL OFFSET ON A TRAILING WING’S LIFT AND DRAG DISTRIBUTIONS S.S. Chauhan¹, G. Padovany da Silva, Universidade Federal do Parana, Brazil; G.L. Olichevis Halila, Embraer, Brazil; J.R.R.A. Martins¹, J.L.F. Azevedo, Instituto de Aeronáutica e Espaço, Brazil; ¹University of Michigan, United States Presenter: Gustavo Luiz Olichevis Halila, Embraer We use a gradient-based approach to investigate wing optimization with propeller-wing interaction for a wing with a large tilt-rotor-sized tip propeller. To the best of our knowledge, there are no published studies for this. Initially, we show optimization results for a simple wing with one and two propellers using the CFD code and gradient-based-optimization tools that we are using for this work. | ||||
| 11:30 | 12:00 | 5.10.4 |
A SEQUENTIAL LOCAL ENUMERATION-BASED IMPROVED LATIN HYPERCUBE SAMPLING METHOD FOR BALLISTIC CONSTRAINT DESIGN SPACE H. Zeng¹, Z.-H. Han¹, C.-Z. Xu¹, Y. Zhang¹; ¹School of Aeronautics, Northwestern Polytechnical University, China This paper presents a sequential local enumeration-based improved Latin hypercube sampling method for ballistic constraint design space. It makes up the defect that the traditional design of experiments method is difficult to apply to the ballistic constraint design space, and provides a better sample scheme. | ||||
| 12:00 | 12:30 | 5.10.5 |
EFFICIENT SHAPE OPTIMIZATION IN AERONAUTICS: INTEGRATING PARAMETRIC CAD AND MESH MORPHING FOR ENHANCED AERODYNAMIC PERFORMANCE A. Lopez¹, G. Magrì², U. Cella¹, G. Urso, RBF Morph srl, Italy; F. Della Barba², M.-E. Biancolini¹; ¹Università di Roma Tor Vergata, Italy ;²Università degli studi di Padova, Italy Shape optimization is a critical aspect in the field of aeronautics, especially considering the increasing electrification and, consequently, the need to reduce consumption and enhance aerodynamic performance to extend the aircraft's autonomy. Another critical aspect is the reduction of computation times, given the lengthy durations of Computational Fluid Dynamics (CFD) simulations and the necessity to run multiple simulations to create a significant dataset for shape optimization. This article proposes an innovative optimization workflow that combines the benefits of key conventional methods: parametric Computer-Aided Design (CAD) and mesh morphing. The concept involves using scriptable CAD editor, specifically ESP (Engineering Sketch Pad) to generate Design Points (DPs). The workflow is highly flexible and can be adapted to other CAD editors as well. Tests have already been conducted using CadQuery (an open-source Python library), JPAD (a startup from the University of Naples Federico II), and AxCent (a commercial software program). By comparing the baseline CAD with updated CAD versions, a cloud of points is created, which can be employed to deform the mesh. This deformation utilizes a mesh morphing technique based on Radial Basis Functions (RBF). The workflow is entirely automated and has been applied to the Open Parametric Aircraft Model (OPAM). The results were highly promising in terms of efficiency improvement. | ||||
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| 10:00 | 10:30 | 6.10.1 |
RESEARCH ON EFFICIENT ACTIVE T-S WAVE GENERATION METHOD IN BOUNDARY LAYER P. Li¹, Z. Cao¹, D. Li¹; ¹Northwestern Polytechnical University, China In this paper, several methods of artificially excited T-S waves by intermittent blow-suction in boundary layer are analyzed for laminar flow control. It’s found that intermittent blow-suction has higher T-S wave excitation efficiency than continuous blow-suction, so the pump drag caused by laminar flow control can be reduced. | ||||
| 10:30 | 11:00 | 6.10.2 |
NUMERICAL STUDY ON ACOUSTIC RECEPTIVITY OF COMPRESSIBLE LAMINAR FLOW OVER A FLAT PLATE WITH MODIFIED SUPER-ELLIPSE LEADING EDGE B.Z. Xu¹, Z.L. Chen¹; ¹Northwestern Polytechnical University, China It can be concluded that the higher disturbance frequency, blunter modified super-ellipse leading edge and larger Mach number lead to stronger receptivity. Meanwhile higher disturbance frequency and larger Mach number can promote the Branch-? location upstream. | ||||
| 11:00 | 11:30 | 6.10.3 |
CROSSFLOW AND GÖRTLER INSTABILITIES IN HYPERSONIC BOUNDARY LAYERS Y. Xi¹, S. Fu¹; ¹School of Aerospace Engineering, Tsinghua University, China In three-dimensional hypersonic boundary layers, the crossflow and Görtler instabilities are of great importance and may trigger transition. Using the numerical simulations, stability theory, and together with some ideas from classical differential geometry, we found the origin of both crossflow and Görtler instabilities over a three-dimensional hypersonic boundary layer are because of the bending of local inviscid streamline. The appearance of which instabilities depends on the ratio between the normal curvature and geodesic curvature. The study suggests that as the crossflow increase, the geodesic curvature of the inviscid streamline would become much larger than the normal curvature, which shows that the crossflow instability is the dominative at larger swept angles. The influences of crossflow and surface curvature on the nonlinear developments and the their secondary instabilities are also discussed. | ||||
| 11:30 | 12:00 | 6.10.4 |
ON THE INFLUENCE OF BASE FLOW CHARACTERISTICS ON CROSSFLOW INSTABILITY IN SWEPT BOUNDARY LAYERS Z.-M. Xu¹, Z.-H. Han¹, H. Nie¹, W.-P. Song¹; ¹Northwestern Polytechnical University, China Crossflow instability (CFI) is a crucial factor in triggering early transition in the three-dimensional boundary layer of a swept wing. This paper aims to investigate the impact of two key characteristics of base-flow velocity profiles on CFI. The findings are utilized to analyze how the sweep angle and pressure gradient influence the development of CFI on a swept wing. | ||||
| 12:00 | 12:30 | 6.10.5 |
ON THE INFLUENCE OF SURFACE ROUGHNESS ON BOUNDARY-LAYER TRANSITION FOR SWEPT WINGS V. Prieto, ONERA and ISAE-SUPAERO, France; M. Forte, ONERA, France; E.R. Gowree, ISAE-SUPAERO, France Presenter: Erwin Ricky Gowree, ISAE-SUPAERO This paper studies the effect of surface roughness on the laminar-turbulent transition of the boundary layer of a swept wing. For this purpose, the results from an experimental campaign carried out in a subsonic closed-return wind tunnel at ONERA are presented | ||||
| additional information (interactive) | 6.10.R |
NUMERICAL INVESTIGATION ON THE EFFECT OF REYNOLDS NUMBER ON TANDEM DROPLET S.-T. Peng¹, F.-Z. Chen¹, H. Yan¹, X.-Q. Sun¹; ¹Northwestern Polytechnical University, China | |||||
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| 10:00 | 10:30 | 7.10.1 |
A CALL TO ACTION TO ENGAGE THE COMMUNITY TO MEET THE CHALLENGES THAT MUST BE TACKLED TO MAKE ELECTRIFIED AIRCRAFT PROPULSION REAL V.P. Schultz, NASA Langley Research Center, United States; H. Schlickenmaier, HS Advanced Concepts LLC, United States; L. Daelemans, European Union Aviation Safety Authority, Germany; C. Genster, Diamond Aircraft, Austria; M. Walz, Federal Aviation Administration,, United States; E. Holtz, Harbour Air, Canada; E. Lovelace, Ampaire, United States More is needed to implement novel electrified aircraft than simply reducing technology risk. These novel EAP companies plan to certify their novel aircraft where no current regulations exist. The NASA Electrified Powertrain Flight Demonstration (EPFD) project has partnered with two companies to build upon their approaches to close these gaps in regulations and standards in their EAP technologies. | ||||
| 10:30 | 11:00 | 7.10.2 |
PANEL DISCUSSION: VINCENT SCHOLTZ, HERBERT SCHLICKENMAIER, LILIAN DAELEMANS, MICHAEL WALTZ, CHRISTOPH GENSTER, EDWARD LOVELACE, ERIKA HOLTZ P. D., Lilian Daelemans (Initial Airworthiness-Rulemaking Officer, European Union Aviation Safety Authority),lilian.daelemans@easa.europa.eu: “The regulatory landscape for electrification in Europe" Michael Waltz (Policy & Innovation Certification, Electric Engine, Electric Energy Storage, Federal Aviation Administration), Michael.Walz@faa.gov: “The regulatory landscape for electrification in the US" Christoph Genster (Chair, ASTM Committee F44 General Aviation, Diamond Aircraft), c.genster@diamondaircraft.com: "The new role of ASTM with Electrification for Part 23 and CS-23" Edward Lovelace (Chair, SAE E-40 Electric Propulsion Committee, Ampaire), ed@ampaire.com: “The new role of SAE with Electrification for all transport airplanes" Erika Holtz (Engineering & Quality Manager, Harbour Air Group), eholtz@harbourair.com: “An Operators’ Perspective Trying to Advance Sustainable Aviation in Uncertain Certification Criteria." | ||||
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| 10:00 | 10:30 | 8.10.1 |
SUMMARY OF DLR RESULTS FROM THE SEVENTH AIAA DRAG PREDICTION WORKSHOP S. Keye¹, O. Brodersen¹, S. Melber-Wilkending¹; ¹German Aerospace Center (DLR), Germany A summary of the German Aerospace Research Center's results from the seventh AIAA CFD Drag Prediction Workshop is presented. DLR has contributed to five out of the six workshop test cases. These include a grid convergence study, angle-of-attack and Reynolds number sweeps, a grid adaptation study, and an aero-structural simulation. | ||||
| 10:30 | 11:00 | 8.10.2 |
MULTI-FIDELITY SURROGATE MODELING BASED ON DATA EXTENSION USING POD AND ANN W. Wang¹, X. Jia¹, C. Gong¹, C. Li¹; ¹Northwestern Polytechnical University, China Presenter: Chunna Li, Northwestern Polytechnical University A multi-fidelity surrogate model based on data extension using POD and ANN is proposed. The model can fuse various-fidelity heterogeneous data through the extension model, and provide accurate predictions of the flow data. The case of airfoil validated the proposed method, and indicates that it can significantly improve modeling efficiency with good precision. | ||||
| 11:00 | 11:30 | 8.10.3 |
FLIGHT TEST AND CFD STUDY OF THE EFFECT OF WING BOUNDARY LAYER TRANSITION ON AILERON BALANCE L. Manfriani¹, X. Liu¹; ¹ZHAW, Switzerland A particular training aircraft exhibited an unusual lateral trim change, with a marked tendency to roll left when entering a cloud or passing through an inversion layer. It was found that this behavior was caused by small paint steps causing an asymmetric transition on the wings and affecting aileron balance. A high fidelity CFD was conducted to provide further insight in this peculiar phenomenon. | ||||
| 11:30 | 12:00 | 8.10.4 |
TRANSFER LEARNING FOR REDUCED-ORDER MODELING OF TRANSONIC FLOWS USING MULTIFIDELITY DATA J. Kou¹, C. Ning¹, W. Zhang¹; ¹Northwestern Polytechnical University, China Combining data from multiple sources to construct accurate reduced-order flow models requires accurately capturing the correlation between multi-fidelity data. Therefore we propose multi-fidelity flow reconstruction framework based on transfer learning, which maintains low computational cost, while significantly improve the prediction accuracy over the traditional method. | ||||
| additional information (interactive) | 8.10.R |
RESEARCH ON MULTI-OBJECTIVE AERODYNAMIC/STRUCTURAL DESIGN OPTIMIZATION METHOD FOR LARGE THICKNESS FLATBACK AIRFOILS K.-Y. Zhou¹, S.-Q. Zhang, Jilin Chongtong Chengfei New Material Co., LTD, China; W.-P. Song¹, J.-H. Xu¹, Z.-H. Han¹; ¹Northwestern Polytechnical University, China | |||||
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| 10:00 | 10:30 | 9.10.1 |
DEVELOPMENT OF A NEW OPERATIONAL FRAMEWORK TO ACCOMMODATE STOCHASTIC AIR TRAFFIC FLOW AT TOKYO INTERNATIONAL AIRPORT D. Iwata, The University of Tokyo, Japan; E. Itoh, The University of Tokyo/Electronic Navigation Research Institute, Japan Departure management is an important congestion mitigation method at airport. This study proposed a new operational framework with 1) machine learning models, 2) departure queuing model using time-varying fluid queue, and 3) reflection of airport-specific characteristics. The validation using the AirTOp simulator showed that the proposed framework reduces departure queues by about 52% on average. | ||||
| 10:30 | 11:00 | 9.10.2 |
ATM CONTROLLER SUPPORT IN CASE OF SPACIOUS SEVERE WEATHER CONSTELLATIONS ILLUSTRATED USING TWO AIRSPACE EXAMPLES L. Nöhren¹, O. Gluchshenko¹, M.-M. Temme¹, K. Muth¹; ¹DLR, Germany An Extended Arrival Manager and a radar display were expanded with procedures and functionalities needed to support approach controllers in severe weather situations. The sequencing and the 4D trajectory calculation processes can start long before the top of descent and consider available weather information and forecasts for more reliable planning. | ||||
| 11:00 | 11:30 | 9.10.3 |
EXTENDED REALITY IN AIRPORT CONTROL TOWERS: FROM CONCEPT DESIGN TO PRELIMINARY ASSESSMENT OF AN INNOVATIVE HUMAN-MACHINE INTERFACE FOR AIR TRAFFIC CONTROL OPERATORS S. Bagassi¹, M. Corsi¹, T. Fadda¹; ¹University of Bologna, Italy In previous projects, the idea of using XR to support ATC operations was explored. Recently, a live platform was tested in a real control tower. The implementation of the solution in the real world confirmed its applicability and usefulness, but it also revealed some challenges, such as data clutter. Ongoing refinement of the system, by exploiting AI for data selection, can address these issues. | ||||
| 11:30 | 12:00 | 9.10.4 |
A ROADMAP FOR TRANSFORMING TRADITIONAL ATCO TEAMS INTO COLLABORATIVE HUMAN-MACHINE TEAMS T. Finck, German Aerospace Center, Germany As tool support improves, the question arises as to whether this could also have an impact on the overall composition of the traditional ATCO team, moving from the executive- planner structure to a human-machine collaboration. The aim of this paper is to provide a roadmap that identifies the necessary obstacles that need to be overcome in this transition and the benefits expected. | ||||
| 12:00 | 12:30 | 9.10.5 |
MODELING TECHNIQUE FOR THE EVALUTAION OF ENVIRONMENTAL EFFECT OF FLIGHT-PATH NEAR AIRPORTS: THE CASE STUDY OF A NEW ROUTE AT NAPLES AIRPORT M. Viscardi, University of Naples, Italy A modeling activity has been related to the Naples Capodichino Airport where a new climbing proce-dure has been studied to limit the environmental effect on the population. Due to specific environmental target, a new take-off path has been explored for the airport with the aim to avoid the overflight of the city center for aircraft directed to north europe routes. The new take-off path has been preliminary explored in terms of airworthiness by the competent institu-tions and once approved has been explored in terms of acoustic footprint and gaseous emissions for a direct comparison with actual situation. The simulation demonstrated a redistribution of noise isophonics leading to a reduction in the popula-tion exposed to noise. | ||||
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| 10:00 | 10:30 | 10.10.1 |
FINITE ELEMENT MODEL UPDATE OF VERY FLEXIBLE AIRCRAFT BASED ON GROUND VIBRATION TESTS C.E.S. Cesnik¹, S. Sharqi¹; ¹University of Michigan, United States This paper presents the computational and experimental techniques associated with ground vibration test of very flexible aircraft (VFA) for nonlinear aeroelastic model development. It accounts for the suspension system and multiple deformed shapes about which modal characterization needs to be performed. The methodology is validated in a prototypical VFA. | ||||
| 10:30 | 11:00 | 10.10.2 |
PRELIMINARY STRUCTURAL DESIGN OF A HIGH ASPECT RATIO RANSPORT AIRCRAFT WITH LAMINAR WING M.R. Ritter¹, M. Schmalz¹, M. Fehrs¹; ¹German Aerospace Center (DLR), Germany This paper presents the design of a jet transport with high aspect ratio (AR 15.6) as well as an innovative laminar airfoil layout with natural laminar flow (NLF) realized by Crossflow Attenuated Natural Laminar Flow (CATNLF). The structural optimization considers CS-25 load cases and imposes aeroelastic constraints to ensure the performance of the laminar wing throughout the flight mission. | ||||
| 11:00 | 11:30 | 10.10.3 |
NUMERICAL INVESTIGATION OF PASSIVE AND ACTIVE ALLEVIATION OF DYNAMIC LOADS ON HIGH-ASPECT-RATIO-WING VEHICLES C.W. Cheng¹, S. Duessler¹, R. Palacios¹, G. Wilson¹; ¹Imperial College London, United Kingdom We present a nonlinear simulation environment for the design and testing of gust load alleviation systems, which consideres 1) passive solutions such as flared folding wing tips, large wing deflections, complex vehicle geometries and advanced control architectures. We exercise this on a representative vehicle derived from the FLEXOP configuration. | ||||
| 11:30 | 12:00 | 10.10.4 |
CONCEPTUAL DESIGN OF HYDROGEN-POWERED AIRCRAFT: HIGH ASPECT RATIO WINGS AND FLOATING WINGTIPS F. Healy¹, H. Gu¹, D. Rezgui¹, J. Cooper¹; ¹University of Bristol, United Kingdom Many proposed liquid hydrogen (LH2) aircraft configurations place the fuel in the fuselage. This is in contrast to conventional designs where fuel is stored in the wings which provides inertial relief, reducing loads and reducing wing mass. This paper uses an aircraft sizing framework to explore alternate LH2 configurations such storing fuel under the wing and the use of floating wingtip devices. | ||||
| 12:00 | 12:30 | 10.10.5 |
GUST LOAD PASSIVE ALLEVIATION BY MEANS ON NONLINEAR, BUCKLING DRIVEN, STRUCTURAL RESPONSE F. Toffol¹, C. Bisagni¹; ¹Politecnico di Milano, Italy In this paper, the buckling driven non-linear response is used to passively alleviate dynamic gust load. A novel aeroelastic framework is used to simulate the non-linear stiffness behaviour through a time-marching simulation that evaluates the dynamic response and the load alleviation achieved. The results show how the buckling can be tailored to alleviate the load and to save structural mass. | ||||
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| 10:00 | 10:30 | 11.10.1 |
HIGHER-ORDER 1D STICK MODELS FOR THE FLUTTER ANALYSIS OF AIRCRAFT STRUCTURES E. Zappino¹, M. Santori¹, M. Petrolo¹, E. Carrera¹; ¹Politecnico di Torino, Italy This paper presents flutter analyses of aircraft structures using an advanced aeroelastic formulation. Three-dimensional problems are reduced to refined 1D structural models based on the Carrera Unified Formulation. Aeroelastic results are obtained by coupling the CUF structural model with the doublet-lattice method. Aeroelastic analyses on thin-wall and multi-component structures are proposed. | ||||
| 10:30 | 11:00 | 11.10.2 |
A FORMULATION FOR WING AEROELASTIC ANALYSIS BASED ON THE UNSTEADY VLM AND STRUCTURAL DISCONTINUOUS GALERKIN TECHNIQUE F. Montano¹, I. Benedetti¹, V. Gulizzi¹; ¹Università degli Studi di Palermo, Italy Presenter: Ivano Benedetti, Università degli Studi di Palermo This work proposes a novel formulation for the aeroelastic analysis of aircraft wings based on the conjoined use of the aerodynamic unsteady vortex lattice method (UVLM) and the structural high-order accurate discontinuous Garlerkin (DG) method. The advantages of the proposed approach, such as the ease of UVLM-DG coupling and the high-order accuracy of the DG method, are discussed in the paper. | ||||
| 11:00 | 11:30 | 11.10.3 |
COUPLED THERMOELASTIC ANALYSIS OF BEAM STRUCTURES USING A REFINED 1D FINITE ELEMENT MODEL M. Filippi¹, R. Azzara¹, M. Santori¹, M. Petrolo¹, E. Carrera¹; ¹Politecnico di Torino, Italy In this paper, static and dynamic problems in the framework of coupled and uncoupled thermoelasticity are analyzed. A refined one-dimensional (1D) model, based on the Carrera Unified Formulation (CUF), is employed to provide accurate predictions for the displacement and temperature change fields within homogeneous isotropic structures under thermal loadings. | ||||
| 11:30 | 12:00 | 11.10.4 |
ANALYSIS AND STUDY ON FLUTTER CHARACTERISTICS OF WINGS UNDER TYPICAL FRAGMENT DAMAGE M. Zhang¹, H. Zhan¹, B. Mi¹, Y. Zhang¹, Y. Liu¹; ¹Northwestern Polytechnical University, China In this paper, based on the experimental data of shooting range, the typical fragment damage forms of the wing with high fidelity are established under the water hammer damage principle of the thin-walled structure, and the flutter boundaries of different damage forms are studied based on the CFD&CSD two-way coupling method, and the survivability of the typical fragments of the wing is evaluated. | ||||
| 12:00 | 12:30 | 11.10.5 |
REVIEW ON NONLINEAR AEROELASTIC ANALYSIS WITH FREEPLAY Y. Sun¹, Z. Han¹, H. Cao¹, W. Cheng¹, Z. Wu², C. Yang²; ¹Aviation Industry Development Research Center of China, China ;²School of Aeronautic Science and Engineering, Beihang University, China Presenter: Zheng Han, Aviation Industry Development Research Center of China This article summarizes the progress and challenges in the field of freeplay nonlinearity in aeroelastic analysis. The impact of structural freeplay on aircraft flight and ground tests are described. The main models and modeling methods of freeplay aeroelastic system are summarized. The theoretical and experimental research of nonlinear aeroelastic analysis with freeplay. | ||||
| additional information (interactive) | 11.10.R |
INVESTIGATION ON INFLUENCE PARAMETER OF AIRCRAFT-MISSILE SEPARATION BY CONSIDERING AEROELASTICITY Y. Zhang¹, H. Zhan¹, B. Mi¹, M. Zhang¹; ¹Northwestern Polytechnical University, China | |||||
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| 10:00 | 10:30 | 12.10.1 |
INSIGHTS INTO HUMAN FATIGUE: STATISTICAL ANALYSIS IN AIRCRAFT MAINTENANCE J.C. Silva, Brazil; A. Barqueira, Portugal; L.B. Magalhães, Portugal; L.F.F.M. Santos, Portugal Study shows 52.90% of aircraft maintenance technicians face significant fatigue, affecting those aged 36-50 and night shift workers. It links fatigue to drowsiness and high workload, impacting quality of life. The findings prompt regulatory bodies to develop specific fatigue management strategies, crucial for aviation safety and relevant to other industries where fatigue is a key safety issue. | ||||
| 10:30 | 11:00 | 12.10.2 |
PILOT FATIGUE DETECTION USING BP NEUTRAL NETWORKS C.-R. Huang¹, H.-L. Shi¹; ¹AVIC Aerospace Life-Support Industries, Ltd., China The purpose is to ensure the safety of pilots. BP neural network extracts data features for fatigue assessment based on physiological parameters.When pilots are under fatigue, the machine will involve more, which can reduce the load on pilots and also promote better human-computer interaction. The paper combines the algorithms of BP neutral network to make the assessment to reach 98% precision. | ||||
| 11:00 | 11:30 | 12.10.3 |
ASSESSING MENTAL WORKLOAD AND INTERFACE USABILITY IN MILITARY PILOTS: AN ADVANCED EYE-TRACKING METHODOLOGY A.C. Russo, Universidade de São Paulo, Brazil; A. Sarmento¹, I. S. Rehder¹, M. M. Cardoso-Junior¹, E Villani¹; ¹Instituto Tecnológico de Aeronáutica, Brazil Presenter: Moacyr Machado Cardoso-Junior, Instituto Tecnológico de Aeronáutica This study delves into the cognitive and ergonomic aspects of military UAV operations, focusing on pilots' mental workload and interface usability through advanced eye-tracking technology. The research encompasses a group of 24 military pilots participating in 30-minute flight simulations, with their eye movements meticulously recorded by Tobii Pro Glasses 2 and analyzed using Tobii Pro Lab software. Alongside this objective data, pilots' subjective perceptions of workload and interface usability are gauged through NASA-TLX and SUS questionnaires. The objective is to establish a correlation between eye-tracking data and pilots' subjective assessments, thereby providing a comprehensive view of the cognitive processes and ergonomic challenges faced in military UAV operations. This study is poised to offer significant contributions to the fields of military aviation training and interface design, underscoring the necessity of integrating technological advancements with human factors to enhance operational safety and efficiency. | ||||
| 11:30 | 12:00 | 12.10.4 |
METAMODELLING OF THE WORKLOAD ASSESSMENT IN SIMULATED FLIGHTS USING THE KRIGING METHOD A. Esposito¹, G. Iacolino¹, C. Orlando¹, A. Alaimo¹; ¹Kore University of Enna, Italy This work focuses on the use of the supervised surrogate Kriging model, based on input data from objective metrics obtained via sensors. The signals are collected during simulated flight tasks, and a workload level classification is performed. the adoption of multidimensional approaches holds promise for a deeper understanding of these phenomena, offering an alternative to traditional sensors. | ||||
| 12:00 | 12:30 | 12.10.5 |
A SYSTEMATIC REVIEW OF HUMAN FACTORS AND AI INFLUENCING OPERATOR PERFORMANCE IN MUM-T ENVIRONMENTS I. de Souza Rehder¹, M.M. Cardoso Júnior¹, E. Villani¹; ¹Aeronautical Institute of Technology, Brazil Presenter: Emilia Villani, Aeronautical Institute of Technology This paper conducts a systematic quantitative literature review exploring the interplay between human factors and artificial intelligence (AI) in Manned-Unmanned Teaming (MUM-T) contexts. With AI’s rapid advancement and its growing role in military operations, especially in UAV management, a deeper understanding of how human cognitive capabilities intersect with AI is crucial. This review meticulously evaluates the existing body of literature, following a methodical process of gathering information, building a database, and generating a thorough analysis. The results of this review are organized into principal thematic areas, including levels of au- tonomy, the dynamics of trust in human-machine interactions, cognitive workload management, experimental practices, and analysis of human factors. The findings underscore the intricacies of integrating AI with human operators in MUM-T scenarios, revealing both challenges and opportunities. This comprehensive literature overview aims not only to synthesize current knowledge but also to guide future research and development in the domain, underlining the need for strategies that effectively marry AI capabilities with human expertise in complex military operations | ||||
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| 10:00 | 10:30 | 13.10.1 |
OPTIMIZING FLEET ASSIGNMENT DECISIONS FOR REGIONAL AIRLINES WITH HYBRID ELECTRIC AIRCRAFT UPTAKE B. Chan, University of Pennsylvania, United States; Y. Deng¹, N. Tran¹, H. Wu¹, M. Ikeda, RTX Research Center, United States; G. Cinar¹, M.Z. Li¹; ¹University of Michigan, United States Presenter: Max Zhaoyu Li Hybrid electric aircraft will play a critical role in mitigating the climate impacts of the aviation sector. We address barriers to airline operations of HEA by developing realistic operating cost estimations for HEA, together with a mathematical fleet assignment optimization model to demonstrate practical HEA usage for regional airlines seeking to incorporate these new aircraft into their fleets. | ||||
| 10:30 | 11:00 | 13.10.2 |
SIZING AND PERFORMANCE ANALYSIS OF A MW-CLASS ELECTRIFIED AIRCRAFT PROPULSION (EAP) SYSTEM FOR A PARALLEL HYBRID TURBOPROP CONCEPT D.D.V. Pham¹, C. Recine¹, R.H. Jansen, NASA Glenn Research Center, United States; ¹NASA Ames Research Center, United States This paper discusses an integrated approach to sizing parallel hybrid, multi-MW Electrified Aircraft Propulsion (EAP) systems while assessing performance sensitivities to variations in component-level metrics like specific power, efficiency, and energy density, and their impacts on range and fuel savings for large turboprop class vehicles. | ||||
| 11:00 | 11:30 | 13.10.3 |
REASSESSMENT OF PARAMETRIC OPTIMIZATION AND PERFORMANCE ANALYSIS METHODOLOGY FOR MILD HYBRID AIRCRAFT PROPULSION SYSTEMS J. Gladin¹, E. Aydin¹, J. Kenny¹, A. Burell¹, J. Decroix¹, T. Zaidi¹, R. Gautier¹, D. Mavris¹; ¹ASDL, United States The refinement of a previously-published novel parametric framework for analyzing and optimizing hybrid electric propulsion systems is presented here. A study is performed using this framework, employing Boeing 737MAX with CFM LEAP-1B vehicle and engine model as the technology reference aircraft, and a mild hybrid turbofan and open rotor engine and mild hybrid open rotor modeled as well. | ||||
| 11:30 | 12:00 | 13.10.4 |
VEHICLE ASSESSMENT AND SYSTEM-WIDE BENEFIT ANALYSES OF HYBRID-ELECTRIC COMMERCIAL AIRCRAFT – ELECTRIFIED POWERTRAIN FLIGHT DEMONSTRATION PROJECT (EPFD) K.D. James¹, A. Meade¹; ¹NASA Ames Research Center, United States NASA is committed to aiding the aviation community to realize revolutionary improvements in environmental per-formance of subsonic transports using alternative propulsion approaches. One such approach to improving 2030-2035 subsonic transport system-level metrics of emissions and conventional fuel consumption is the use of hybrid electric propulsion. Partnering with U.S. industry, the Electrified Powertrain Flight Demonstration (EPFD) project was created to focus on turning megawatt-class hybrid electric powertrain flight into a reality. A goal of EPFD is integrating megawatt-class propulsion to commercial aircraft. This is a multi-disciplinary system integration effort and vehicle assessment, and system-wide benefits analyses is necessary to ensure we can achieve the goal. This pa-per outlines EPFD efforts in parametric sizing of megawatt-class propulsion applied to state-of-the-art single-aisle turbofan and turboprop aircraft using projected 2030-2035 technologies, and their projected system-wide impact on emissions and fuel use. | ||||
| 12:00 | 12:30 | 13.10.5 |
PANEL DISCUSSION P D, United States PANEL DISCUSSION | ||||
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| 10:00 | 10:30 | 14.10.1 |
MOREALIS – A HOLISTIC APPROACH TO ENHANCE SAFETY FOR MICRO-AIRCRAFT OPERATIONS R.O. Kuchar¹, W. Scholz², B. Dörfler, Rödel Aerospace Systems, Germany; P. Herrmann², P. Jamakatel, University of the Bundeswehr Munich , Germany; J. Karger², J.J. Kiam³, J. Klennert*, M. Klennert*, M. Lindlar, German Aerospace Center (DLR-ME), Germany; M.S. May¹, D. Milz¹, N. Mummº, D. Nospes³, L. Peterº, G. Looye¹, A. Schulte³, P. Stütz³; ¹German Aerospace Center (DLR-SR), Germany ;²SFL GmbH., Germany ;³University of the Bundeswehr Munich, Germany ;*STAR Healthcare Management GmbH., Germany ;ºAmazilia Aerospace GmbH., Germany Introduced by various European Union member states in recent years, the very lightweight, single-seat micro-light aircraft category (the German "Leichte Luftsportgeräte"-class), with an empty mass of up to 120 kg gained broad popular interest. This is probably caused due to the fact that this class envisions the basic ideas of recreational flight: simplicity through strict weight limitation and low administrative effort, thus low acquisition and operational costs. Furthermore, "LL" aircraft are not required to undergo annual inspections, whereas pilots of this aircraft category are not obliged to pass annual medical examinations, but remain self-responsible for these matters. Despite massive improvement in safety features for general aviation over the last decades, serious or even fatal accidents remain one of the major concerns and require constant improvement. Taking these conditions into account, the MOREALIS project aims towards increasing safety for "LL" aircraft configurations by means ranging from improved structural concepts of the airframe, aircraft and pilot health monitoring up to fault-tolerant flight control laws and finally a dedicated automatic emergency landing procedure. This paper therefore presents an overview of the employed methods and respective partner contributions. | ||||
| 10:30 | 11:00 | 14.10.2 |
GENERATION AND COMMUNICATION OF STRATEGIC PLANS AT DIFFERENT LEVELS OF ABSTRACTION FOR INTELLIGENT ASSISTANCE SYSTEMS IN GENERAL AVIATION P. Jamakatel¹, J.J. Kiam ¹; ¹University of the Bundeswehr Munich, Germany This paper presents the ongoing work on an adaptive intelligent assistance system developed to generate and communicate instructions on how to perform flight tasks, while adapting to the current mental state of the pilot in a single-seat ultralight (UL) cockpit. Context: Session MOREALIS | ||||
| 11:00 | 11:30 | 14.10.3 |
PILOT SAFETY – SUPPORT BY BIOMEDICAL MONITORING IN PILOTS WITH HEALTH RISKS M. Lindlar¹, J. Klennert, STAR Healthcare Management GmbH, Germany; S. Plath¹; ¹German Aerospace Center, Germany Pilots of microlight aircraft do not undergo flight medical examination when not flying for commercial purpose. Within the MOREALIS research project dan integrated system to protect the pilot in the single-seat-aircraft is developed. A medical monitoring shall detect pilot incapacitation as input to an aircraft intervention management and rescue system. (Intended as part of a MOREALIS session) | ||||
| 11:30 | 12:00 | 14.10.4 |
MIXED FLIGHT CONTROL LAYOUT FOR ULTRALIGHT GENERAL AVIATION AIRCRAFT M. May¹, D. Milz¹, W. Scholz², P. Herrmann², J. Karger², L. Peters³, N. Mumm³, R. Kuchar¹; ¹DLR, Germany ;²SFL GmbH, Germany ;³Amazilia Aerospace GmbH, Germany Ultralight aircraft below 120 kg neither require an airworthiness certificate nor pilot medical examinations. Addressing safety issues like aircraft degradation or pilot incapacitation, we present a mixed flight control layout (where separate automated control surfaces augment mechanical pilot flight controls) and analyze the flight and handling qualities of the resulting aircraft design. | ||||
| 12:00 | 12:30 | 14.10.5 |
SENSOR AND COVERAGE PATH PLANNING FOR THE MONITORING OF AIRCRAFT EMERGENCY LANDING SITES D. Nospes¹, P. Stütz¹; ¹University of the Bundeswehr Munich, Germany This work presents our approach to sensor and coverage path planning for the monitoring of a set of aircraft emergency landing sites with a single onboard camera in the context of the MOREALIS project. Due to ground sample distance requirements of the hazard detection, often only a part of a single landing site can be processed in one view. Therefore, to get an overview of the complete hazard situation, a monitoring sequence for multiple landing sites must be created and combined with an area specific coverage plan. For this, we investigate different combinations of methods on a dataset of landing sites regarding their capabilities of on landing site hazard detection as well as minimization of the time required for a complete scan. | ||||
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| 10:00 | 10:30 | 15.10.1 |
APPLICATION OF UAS TECHNOLOGIES TO CREATE RESILIENT RURAL COMMUNITIES M.J. Logan, NASA, United States APPLICATION OF UAS TECHNOLOGIES TO CREATE RESILIENT RURAL COMMUNITIES | ||||
| 10:30 | 11:00 | 15.10.2 |
ENHANCING QUADCOPTER CONTROL: A MODEL REFERENCE ADAPTIVE CONTROL APPROACH WITH NEURAL NETWORKS S.R. Bassolillo¹, G. Raspaolo², L. Blasi², E. D'Amato¹; ¹Università degli Studi di Napoli Parthenope, Italy ;²Università degli Studi della Campania L. Vanvitelli, Italy Presenter: Egidio D\'Amato, Università degli Studi di Napoli Parthenope In recent decades, multirotor flying vehicles have garnered significant attention due to their diverse configurations and versatility. This paper focuses on the design and testing of a flight control scheme employing Model Reference Adaptive Control with Neural Networks. The effectiveness of the proposed controller is demonstrated through numerical simulations on a detailed nonlinear simulator and experimental results. | ||||
| 11:00 | 11:30 | 15.10.3 |
ONBOARD TRAJECTORY OPTIMIZATION FOR RADIUS TO FIX TURNS D.M. Gierszewski¹, P. Piprek¹, F. Holzapfel, Technische Universität München, Germany; ¹ Technische Universität München, Germany An onboard optimization approach is used to generate trajectories for Radius to Fix (RF) turns within an integrated flight guidance and control system. An Optimal Control Problem is formulated such that it accounts for the geometric constraints of the RF as well as the dynamic and limitations of the closed-loop controlled aircraft. The result of the optimization algorithm is verified online. | ||||
| 11:30 | 12:00 | 15.10.4 |
ADAPTIVE CONTROL AND MISSION PLANNER DESIGN FOR UAV OPERATIONS WITH BATTERY MANAGEMENT A. Boldrini¹, G. Gozzini¹, D. Invernizzi¹; ¹Politecnico di Milano, Italy Presenter: Giovanni Gozzini, Politecnico di Milano The primary objective of this work is to leverage adaptive control techniques to effectively counteract the reduction in thrust caused by the battery discharge in Unmanned Aerial Vehicles (UAVs) enhancing their reliability and autonomy while extending their operational range and mission success rates. In addition to this, the w work aims to devise a mission planner capable of ensuring the safe execution of trajectory tracking tasks, such as those related to monitoring/surveillance missions. One of the main contribution of the work is the augmentation of classic baseline controllers with adaptive control mechanisms to dynamically adjust and optimize the control inputs of the UAV as the battery discharges, continuously monitoring and adapting to the changing thrust capabilities, aiming to maintain the UAV's performance within acceptable parameters throughout the mission. Moreover, regarding the autonomous mission planner, the thrust loss estimate, which can be considered as a key parameter of the battery's status, becomes a crucial parameter also for the decision-making algorithms that assess when it is prudent to terminate the mission, ensuring the UAV's safe return to the charging station without risking a depleted battery during flight. Therefore, the mission management system is completed by breaking down the overall mission into different modes and defining a hybrid automaton that enables the transition from one mode to another and a control input that allows the UAV to perform the task autonomously, including when it necessitates to return to the charging base. Lastly, this control scheme and the mission management real-world effectiveness is assessed through a series of tests under different simulation conditions. | ||||
| 12:00 | 12:30 | 15.10.5 |
PASSIVE FAULT TOLERANT CONTROL OF A DUAL-SYSTEM UAV IN TRANSITION FLIGHT J. Cai¹, M. Lovera¹; ¹Politecnico di Milano, Italy A novel passive fault tolerant control system for the transition flight of a dual-system UAV is proposed in this paper. The developed control system is able to overcome the partial loss of a single propeller as well as modeling uncertainty during transition flight, which effectively improves the safety and reliability of the flight of the dual system UAV. | ||||
| additional information (interactive) | 15.10.R |
A NOVEL APPROACH TO AUTOMATED TRACKING CONTROL OF HYBRID TILTING ROTOR UAVS USING LQG CONTROLLER AND STATE MACHINE J.L. Kurniawan¹, P.B.A. Baylon¹, R.A. Sasongko¹; ¹Institut Teknologi Bandung, Indonesia | |||||
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| 10:00 | 10:30 | 17.10.1 |
APPLICATION OF CLUSTERING TECHNIQUES IN OPTIMISATION-BASED FLIGHT CONTROL SYSTEM CLEARANCE P. Piprek¹, P.M. Dias¹, J. Tonti¹, D. Schwalb¹; ¹Airbus Defence and Space GmbH, Germany This paper presents the connection of clustering in an optimization-based clearance toolchain. The clustering is used to exclude already identified critical envelope areas, thus facilitating the exploration and potential to find further critical scenarios. The applicability in a fighter aircraft clearance is discussed. | ||||
| 10:30 | 11:00 | 17.10.2 |
SELF-DRIVING AND MODEL-BASED EXTREMUM SEEKING CONTROL IN TIGHT FORMATION FLIGHT FOR FUEL SAVING D.B. Rossato, Faculdade de Tecnologia SENAI, Brazil; K.H. Kienitz, Instituto Tecnológico de Aeronáutica, Brazil Presenter: Daniel Rossato, Faculdade de Tecnologia SENAI Advances in Extremum Seeking Control are reviewed, with emphasis on the self-driving and model-based approach and highlighting Economic Model Predictive Control. Application to tight formation flight for fuel saving is discussed and convergence performance analysis is exemplified for a follower flying in the vortex of a leading aircraft. | ||||
| 11:00 | 11:30 | 17.10.3 |
APPLICATION OF A MORE INTEGRATED TOTAL ENERGY CONTROL SYSTEM FOR IMPROVING AIRCRAFT AND ENGINE CONTROL EFFICIENCY T. Giusti Degaspare, Embraer S.A., Brazil; K.H. Kienitz, Instituto Tecnológico de Aeronáutica, Brazil Presenter: Karl Heinz Kienitz, Instituto Tenológico de Aeronáutica This article presents improvements obtained by the integration of flight and engine controllers in terms of control efficiency with the use of the More Integrated Total Energy Control System (MI-TECS) and highlights how an integrated design framework offers advantages for controller design when compared with conventional control approaches. | ||||
| 11:30 | 12:00 | 17.10.4 |
FLYING V DIRECTIONAL FLIGHT CONTROL: AN EXPERIMENTAL INVESTIGATION R. Vos¹, N. Johnson¹, S. Nolet¹; ¹TU Delft, Netherlands The present paper shows how the addition of drag rudders can substantially improve the directional control power of the Flying V, particularly at high angle of attack. This is experimentally demonstrated through wind tunnel tests on a 4.6% scale model. Results show that drag rudders and 'normal' rudders can be used in parallel to satisfy the required control power of the Flying V. | ||||
| 12:00 | 12:30 | 17.10.5 |
REENTRY TRAJECTORY DESIGN FOR DEFORMABLE HYPERSONIC VEHICLES BASED ON NEURAL NETWORKS C.-K. Zhou¹, Z.-F. Luo¹, T. Zhang¹; ¹SUN YAT-SEN UNIVERSITY, China Flexible skin is a future trend in morphing aircraft. This study explores its application to hypersonic lifting bodies. Deformable shapes are modeled using parameterized equations(CST). Aerodynamic parameters are obtained through CFD. Relative optimal reentry trajectories are optimized using Gaussian Pseudo method. Results show advantages in specific mission scenarios. | ||||
| Reserve Paper | 17.10.R |
AILERON-FLAP-INTEGRATED ROLL CONTROL LAW BY OPTIMIZED CONTROL ALLOCATION FOR FLEXIBLE TRANSPORT AIRCRAFT H. Wilke¹, G.C. Silva¹, F.J. Silvestre¹; ¹Technische Universität Berlin, Germany | |||||
| additional information (interactive) | 17.10.R |
A MODEL PREDICTIVE CONTROL ALGORITHM FOR THE FORMATION CONTROL OF NANOSATELLITES IN LEO ORBIT C. Santoro¹, S.R. Bassolillo, University of Naples Parthenope, Italy; A. Ferraro, University of Reggio Calabria Mediterranea, Italy; L. Blasi¹, I. Notaro¹; ¹University of Campania L. Vanvitelli, Italy | |||||
| additional information (interactive) | 17.10.R |
MODELING AND FLIGHT CONTROL LAW DESIGN FOR A SEAPLANE DURING WATER SURFACE TAKEOFF Y. Liu¹, Y.-H. Nong², X. Liu, Shanghai Aircraft Airworthiness Certification Center, China; Z.-H. Cheng², M.-X. Zhang¹; ¹Northwestern Polytechnical University, China ;²AVIC General Huanan Aircraft Industry, China | |||||
| additional information (interactive) | 17.10.R |
TRAJECTORY DESIGN FOR ASTEROID SAMPLE RETURN COMBINING BALLISTIC CAPTURE AND AEROBRAKING Z.-F. Luo¹, Y.-J. Lian, National University of Defense Technology, China; C. Zhang, Chinese Academy of Sciences, China; T. Zhang¹; ¹Sun Yat-sen University, China | |||||
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| 13:30 | 14:00 | 1.11.1 |
NASA SUSTAINABLE FLIGHT NATIONAL PARTNERSHIP OPERATIONS RESEARCH A. Sultan, NASA (ARMD), United States As part of the NASA Aeronautics Research Mission Directorate (ARMD) Sustainable Flight National Partnership in response to the US Aviation Climate Action Plan, NASA is engaged with FAA, airlines, and airports on a series of airspace operations technology development and validation for reduced emissions, noise, and fuel consumption between now and 2032. NASA has developed prototype technologies and is actively conducting benefits assessment operational validation and evaluation flight trials at FAA facilities of Dallas and Houston regions in Texas, Dallas Fort Wort International Airport, Dallas Love Field, Houston George Bush International Airport, American Airlines, Southwest Airlines, United Airlines, and Envoy Air. The current phase is focused on demonstrated validation and data collection for reductions in emissions and fuel for pre-departure re-routing around adverse weather. NASA, FAA, and airlines partners will present the prototype technology, how it is utilized by the various entities within the airspace, and the benefits it provides to each. NASA will also present the objectives and benefits of future planned technology development and operational validation and evaluations with partners for Oceanic Inter-ANSP Flow Management and Trajectory Negotiation, Disruption Management, and Integrated Air-Ground Optimized Trajectory Negotiation. | ||||
| 14:00 | 14:30 | 1.11.2 |
HOW CAN EUROPE BECOME THE MOST EFFICIENT AND ENVIRONMENTALLY-FRIENDLY SKY TO FLY IN THE WORLD? A. Boschen, SESAR Joint Undertaking, Germany | ||||
| 14:30 | 15:00 | 1.11.3 |
RECENT FLIGHT EXPERIMENTS SHOW THE CLIMATE BENEFITS OF SUSTAINABLE AVIATION FUELS (SAF) AND ADVANCED ENGINE TECHNOLOGIES R. Moore, NASA (LaRC), United States; C. Voigt, DLR, Germany “invited speaker for the Global Sustainable Aviation track” | ||||
| 15:00 | 15:30 | 1.11.4 |
AI DRIVEN DECISION SUPPORT IN OPERATIONS STEERING C. Most, Lufthansa, Germany invited speaker for the Global Sustainable Aviation track | ||||
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| 13:30 | 14:00 | 2.11.1 |
STRUT-BRACED DRY WING CONCEPT FOR HYDROGEN-POWERED AIRCRAFT M. Méheut¹, D. Losada Costoso¹, F. Moens¹, O. Atinault¹, C. Julien¹, L. Vertonghen¹, L. Coelho¹, V. Priasso¹, A. Lannoo¹, S. Defoort¹, E. NGuyen Van¹, C. David¹, D. Glenis¹, J. Sodja², S. de Boer², J. Schwingel³, D. Eisenhut³; ¹ONERA, France ;² Delft University of Technology, Netherlands ;³University of Stuttgart, Germany This paper aims at presenting the design of a LH2-powered Strut-Braced Dry Wing configuration (SBDW) done within the Clean Aviation UP Wing project. In this framework, ONERA, Technical University of Delft and University of Stuttgart are setting up a common multidisciplinary design process to explore the design space offered by such a configuration where the wing no longer bears the function of carrying the fuel as the cryogenic LH2-tank are located at the rear of the fuselage. The final paper will detail the overall sizing process as well as the disciplinary modules (Structure, aerodynamic, handling quality and aero-elasticity) and will present the overall performance of the optimized concept. | ||||
| 14:00 | 14:30 | 2.11.2 |
OPTIMAL WING ASPECT RATIO OF HIGHLY EFFICIENT LONG-RANGE AIRCRAFT T.F. Wunderlich, German Aerospace Center (DLR), Germany OPTIMAL WING ASPECT RATIO OF HIGHLY EFFICIENT LONG-RANGE AIRCRAFT | ||||
| 14:30 | 15:00 | 2.11.3 |
NASA TRANSONIC TRUSS-BRACED WING STUDIES D.P. Wells¹, G.M. Gatlin¹, J.C. June¹, T.V. Marien¹; ¹NASA Langley Research Center, United States The focus of this paper is to provide an overview of the NASA-funded and NASA-led truss-braced wing (TBW) research within the context of the integrated TBW vehicle design and analysis. This paper presents NASA-sponsored TBW research that is leading to revolutionary improvements in economics and environmental performance. | ||||
| 15:00 | 15:30 | 2.11.4 |
EXPLORING ROLL MANEUVERABILITY OF FUTURE AIRCRAFT WITH HIGH AR WINGS D Sanghi¹, C.E.S. Cesnik¹, Cristina Riso¹; ¹University of Michigan, United States EXPLORING ROLL MANEUVERABILITY OF FUTURE AIRCRAFT WITH HIGH AR WINGS | ||||
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| 13:30 | 14:00 | 3.11.1 |
CONCEPTUAL DESIGN AND SIZING OF A SOLAR POWERED QUAD-ROTOR FIXED WING HYBRID UAV FOR EXPLORATION OVER MARS A. Kalgutkar¹, P. Gupta¹, P. Priyadarshi, Vikram Sarabhai Space Centre, India, India; R.S. Pant¹; ¹Indian Institute of Technology Bombay, India, India This paper presents a comprehensive conceptual design for a solar-powered hybrid unmanned aerial vehicle (UAV) specifically tailored for Mars exploration. The proposed configuration combines quadcopter vertical take-off and landing capabilities with fixed wings for horizontal propulsion, supported by solar energy harvesting. The study utilizes a design methodology derived from a literature review of a similar UAV configuration on Earth, adapting it to the unique challenges and environmental conditions of Mars. Additionally, simulation parameters are modified to accurately represent Martian conditions, including the incorporation of an illumination model and solar cell methodologies. The design process involves the generation and evaluation of multiple design points based on desired mass, payload capacity, and endurance, offering a range of feasible options for Martian UAV missions. The selected configuration has four motors in a quadcopter configuration for Vertical Take-Off and Landing (VTOL) along with fixed wings and a single motor for horizontal propulsion. Energy is harvested using body-mounted solar cells over the duration of a Martian day to enable high endurance flight. The literature review is conducted to obtain a design methodology for a similar configuration of vehicle for earth, albeit without solar power. This methodology is implemented and the code is validated. The simulation parameters are altered to represent conditions on Mars and an illumination model is added. Design points are generated and evaluated as per the process presented above. The analysis of various feasible design points is also conducted, presenting several options based on the desired mass, payload, and endurance. Simulations are performed for different mission profiles to generate a plot of the battery State of Charge versus time. | ||||
| 14:00 | 14:30 | 3.11.2 |
INNOVATIVE UAVS WITH CONFIGURATION OF LIKING BOTH PLANE AND KITE FOR WIND POWER Z.X. Yao, Shenyang Aircraft Design and Research Institute, China The UAV has a novel configuration of liking both plane and kite for wind power. The fresh wind power UAV comprises two main components of the Kite-plane Integrated Configuration UAV and the Sky-Ground collaborative wind power generation control system, targeting the goal of achieving a 2-kilowatt Airborne Wind Power generation | ||||
| 14:30 | 15:00 | 3.11.3 |
FRAMEWORK DEVELOPMENT FOR CONCEPTUAL DESIGN AND CONFIGURATION ANALYSIS OF EVTOL AIRCRAFT R.Y. Yanev¹, I. Staack¹; ¹Technische Universität Braunschweig, Germany Urban air mobility is emerging as a cost-effective alternative to ground transportation. This study explores the impact of design missions, propulsion arrangements, and technological improvements on the short- and mid-term capabilities of multiple electric vertical take-off and landing (eVTOL) aircraft configurations through an in-house developed tool for sizing and analysis. | ||||
| 15:00 | 15:30 | 3.11.4 |
ANALYSIS OF STEALTH ENHANCEMENT DESIGN PROCESS AND METHODS FOR UNMANNED AERIAL VEHICLE G. Jia, China; D. Hu, China; Z. Guo, China; Y. Lu, China; D. Liu, China This article proposes an method for enhancing radar stealth design of UAV, including structural layout optimization, scattering mechanism analysis of strong scattering points, construction a proxy model to evaluate the aerodynamic and stealth characteristics, and joint aerodynamic and stealth optimization of in subregional aircraft. A flying-wing UAV is taken for example during method validation. | ||||
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| 13:30 | 14:00 | 4.11.1 |
FROM THEORY TO FLIGHT: THE BOX-WING CONFIGURATION IMPLICATIONS FOR THE NEXT-GENERATION AIRCRAFT K. Abu Salem¹, G. Palaia¹, A. Frediani, SkyBox Engineering, Italy; ¹Politecnico di Torino, Italy Through a systematic critical analysis of the literature on the box-wing configuration, the work aims to present a discussion on potential benefits and critical issues of the concept. The performance gains are related with the challenges of introducing macroscopic innovations in aeronautical industrial context, aiming at identifying possible path for the industrial integration of such an aircraft. | ||||
| 14:00 | 14:30 | 4.11.2 |
PRELIMINARY SIZING OF A LOW-ALTITUDE AIRSHIP INCLUDING ION PLASMA THRUSTERS C.E.D. Riboldi¹, M. Belan¹, S. Cacciola¹, R. Terenzi¹, S. Trovato¹, D. Usuelli¹, G. Familiari¹; ¹Dept. of Aerospace Science and Technology, Politecnico di Milano, Italy Presenter: Raffaello Terenzi, DAER - Politecnico di Milano A new preliminary design and sizing technique for low altitude airships coping with the inclusion of ion plasma thrusters on board. Preliminary sizing results will be shown for a demonstrator airship, which will be actually built in project IPROP, showing comparisons with a baseline design with conventional electric motors, and showing trend lines and sensitivities of the design solution. | ||||
| 14:30 | 15:00 | 4.11.3 |
GENERAL DESIGN CONSIDERATIONS FOR SOLAR-ELECTRIC HIGH-ALTITUDE LONG-ENDURANCE AIRCRAFT A. Bierig¹, F. Nikodem¹, D. Rothe¹; ¹DLR, Germany The publication describes fundamental design relationships for solar-electric high-altitude aircraft in the context of currently available technologies. The publication aids potential developers of such aircraft in making a quick assessment regarding the feasibility of their projects. Furthermore, the described relationships provide the necessary tools to evaluate and compare existing platforms. | ||||
| 15:00 | 15:30 | 4.11.4 |
CONTINUING DEVELOPMENT OF A NOVEL CERTIFIABLE AIRLINER “GONDOLA” USING LIQUID HYDROGEN R.K. Nangia, Nangia Aero, United Kingdom; L. Hyde, Consulting, United Kingdom; J.E. Cooper, Bristol University, United Kingdom From certification and safety viewpoints, a LH2 powered aircraft must ensure that LH2 is well separated from the passengers. This has led to a novel twin-fuselage “Gondola” airliner with some asymmetry. We describe continuing development, focusing on the main features including stability and control in symmetric and asymmetric flight. | ||||
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| 13:30 | 14:00 | 5.11.1 |
JET NOISE ABATEMENT VIA SURROGATE MODEL-BASED AEROACOUSTIC OPTIMISATION USING LARGE EDDY SIMULATION G. Yang, University of Bristol, United Kingdom This paper presents a surrogate model-based aeroacoustic optimisation framework that is developed and applied to jet nozzle exit geometries. The optimisation package is wrapped around a LES flow solver that is implemented on GPUs, enabling highly efficient CFD and acoustic solutions and thus shape optimisations. Noise reductions are achieved for isolated chevron nozzle geometries. | ||||
| 14:00 | 14:30 | 5.11.2 |
NUMERICAL STUDIES ON NOISE-SHIELDING EFFECTS OF A BLENDED-WING-BODY AIRCRAFT USING BOUNDARY ELEMENT METHOD H.Y. Wang¹, T.M. Collin¹, Z.L. Chen¹; ¹Northwestern Polytechnical University, China A fast Boundary Element Method (BEM) is adopted to study the shielding effects of monopoles on a BWB civil aircraft without freestream flow.The parameter studies of model fidelity of outer mold line, frequency, nacelle, model scaling and engine position on the noise shielding effects of a Blended-Wing-Body aircraft are performed. And the freestream flow effect on noise shielding is under study. | ||||
| 14:30 | 15:00 | 5.11.3 |
AERODYNAMICS AND AEROACOUSTIC ANALYSIS OF A SUPERSONIC SLENDER-BODY GEOMETRY M. De Rosa¹, A. Glorioso¹, G. Pezzella¹, A. Viviani¹; ¹University of Campania, Italy Presenter: Maria De Rosa, University of Campania "Luigi Vanvitelli" This paper deals with the investigations of the sonic boom phenomenon for a slender-body geometry considering the effect of different shape parameters such as the nose radius-to-diameter ratio r/D in order to investigate its effect on the body Aerodynamics and aeroacoustic in near-field domain and then on the sonic carpet. | ||||
| 15:00 | 15:30 | 5.11.4 |
MEASUREMENTS OF T-S WAVES DUE TO ACOUSTIC DISTURBANCES IN EXPERIMENTS Z. Cao¹, P.F. Li¹, D. Li¹; ¹Northwestern Polytechnical University, China Boundary-layer receptivity to external disturbances is the beginning of transition from laminar to turbulent flow and it still remains unclear especially in experiments mainly because of the difficulty to separate T-S waves from other interference like Stokes layer. This work carried out the full process of a receptivity experiment under two type of acoustic disturbances (the continuous forcing and the pulsed forcing) and successfully extracted the T-S waves from the Stokes, which enrich the development of the experimental measurements on instability and has a reference meaning for others who want to implement a familiar experiment. | ||||
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| 13:30 | 14:00 | 6.11.1 |
UNCERTAINTY ANALYSIS OF THE AERODYNAMIC PERFORMANCE OF EVTOL PROPELLERS VIA REYNOLDS STRESS TENSOR PERTURBATION G. Gori¹, A. Zanotti¹; ¹Department of Aerospace Science and Technology, PoliMI, Italy Computational models are unavoidably affected by epistemic uncertainty. Indeed, specific assumptions define the structure of turbulence closures in the RANS model, limiting the general credibility of the model. We suggest a modification of the Eigenspace Perturbation Method to increase the depth of the uncertainty analysis in investigating the aerodynamic performance of two tandem propellers. | ||||
| 14:00 | 14:30 | 6.11.2 |
ASSESSMENT OF AN ADAPTIVE ONE-EQUATION TURBULENCE MODEL FOR LEADING-EDGE VORTEX FLOWS ON MULTIPLE SWEPT DELTA WINGS M. Zieher¹, D. Sedlacek¹, C. Breitsamter¹; ¹Technical University of Munich, Germany The assessment of an adaptive turbulence model based on the Spalart-Allmaras turbulence model will show improved results for common (U)RANS CFD simulations for leading edge vortex dominated flows. This simple model improvement can cut computational cost, time, and energy during aircraft design phases, since more relatively low-cost simulations at higher levels of accuracy can be conducted. | ||||
| 14:30 | 15:00 | 6.11.3 |
EFFECTS OF GEOMETRY PARAMETERS ON AERODYNAMIC CHARACTERISTICS OF ROTOR AIRFOIL IN REVERSE FLOW C.-P. Liu¹, W.-P. Song¹, S.-Q. Han, Sichuan University, China; Z.-H. Han¹; ¹Northwestern Polytechnical University, China An improved high order WENO scheme and IDDES method are used to study the aerodynamic characteristic of rotor airfoil in reverse flow. OA312 airfoil is chosen and morphed with different design parameters. Aerodynamic coefficients of these airfoils are simulated and compared to analyze the influence of different design parameters, which can be used to guide the design of new rotor airfoil. | ||||
| 15:00 | 15:30 | 6.11.4 |
ASSESSMENT OF EXPLICIT ALGEBRAIC REYNOLDS STRESS MODELS APPLIED TO AERONAUTICAL FLOWS T. Chagas Silva, Instituto Tecnológico de Aeronáutica, Brazil; J.L.F. Azevedo, Instituto de Aeronáutica e Espaço, Brazil This work is part of an ongoing effort to assess the capabilities of nonlinear turbulence models to predict tur- bulent flows around aeronautical configurations. In the design of complex geometries, the simpler turbulence models tend to have a poor representation of the complex physical phenomena present in the flow around these configurations. In these cases, intending to optimize such aerodynamic shapes, it is necessary to resort to higher fidelity turbulence models, which, in general, are capable of represent more accurately the solution of the flow. Nonlinear eddy-viscosity turbulence models are an intermediate class of turbulence models ap- propriate to work with the Reynolds-averaged Navier-Stokes (RANS) equations. The main advantage of the nonlinear turbulence models is the capability to predict the flow more accurately at the same time that to keep a computational cost similar to linear eddy-viscosity turbulence models. Two explicit algebraic Reynolds stress models (EARSM) are employed here, coupled with the 3-D RANS equations. This theoretical formulation is solved by a cell-centered, finite volume method using unstructured meshes. The test cases performed to date include the transonic flow over the OAT15A airfoil and the subsonic flow over the McDonnell Douglas 30P30N high-lift airfoil. Other cases of interest in aeronautical engineering are being studied and they will also be included in the final paper. | ||||
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| 13:30 | 14:00 | 7.11.1 |
PIONEERING THE EXCHANGE OF KNOWLEDGE B Nagel, Germany Pioneering the exchange of knowledge is the objective of the Digital Pioneering Initiative (DPI) of The International Council of the Aeronautical Sciences (ICAS). 50 scientists from all over the world joined the 2nd Digital Pioneering Workshop just in advance of the 34th ICAS congress and worked out solutions how synergies from ICAS contributions can be exploited. This presentation will introduce ICAS DPI and its modes of involvement. The other three presentations in this session will present results from the workshop. | ||||
| 14:00 | 14:30 | 7.11.2 |
DIGITAL COLLABORATION FOR SUSTAINABLE AVIATION A.S.J. van Herden, United Kingdom The term sustainable aviation is widely used but which is actually the formal definition and where do we have to draw the system boundaries? Aspects such as climate impact, energy supply from well to wake, noise and economic feasibility all need to be considered. During the ICAS Digital Pioneering Initiative workshop we discussed how to define the problem to be solved and how we can make use of scientific results which get published at the ICAS congress to collaboratively compose extensive simulation frameworks which potentially cover all relevant effects. | ||||
| 14:30 | 15:00 | 7.11.3 |
HARNESSING THE POWER OF METAVERSE TO REVOLUTIONIZE AIRCRAFT AND MRO RESEARCH K.K. Koschlik, Germany The concept of the metaverse represents a collection of virtual worlds where users interact through avatars, often in immersive 3D environments that emphasize social and economic connections. However, realizing this vision requires a multi-disciplinary approach, integrating expertise from computer science, artificial intelligence, design, social sciences, and beyond. During the ICAS Digital Pioneering Initiative workshop discussions centered around building networks of experts from various fields and developing adaptive systems for filtering and synthesizing accumulated knowledge. These systems are crucial for uncovering hidden patterns and connections between skills, tools, and methods, enabling a more cohesive and accelerated development process. By fostering interdisciplinary cooperation, we aim to address the complex challenges of the metaverse and lay the groundwork for its future evolution. | ||||
| 15:00 | 15:30 | 7.11.4 |
MANAGING DIGITAL COMPLEXITY C. Jouannet, Sweden Several ICAS publications describe digital simulation tools which might potentially be made available for collaborative research activities within the ICAS research community. However, the challenge how to integrate all these software tools and which processes need to be implemented to concurrently apply them are challenges we discussed during the ICAS Digital Pioneering Initiative workshop. The ICAS community might constitute a very valuable environment to experiment digital collaboration techniques such as Model Based Systems Engineering (MBSE) in combination with Multidisciplinary Design Analysis and Optimization (MDAO). | ||||
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| 13:30 | 14:00 | 8.11.1 |
LOW-SUBSONIC AERODYNAMIC ANALYSES OF A NONPLANAR BWB MODEL: AN EXPERIMENTAL AND CFD STUDY M. Nikbay¹, K. Kontis², H. Aleisa², B. Pirlepeli¹; ¹Istanbul Technical University, United Kingdom ;²University of Glasgow, United Kingdom A nonplanar wing concept significantly improves the aerodynamic performance of an aircraft. Hence, adopting nonplanar flow control concepts is essential to achieve an enhanced lift performance and controllability. Likewise, the blended wing body (BWB) concept uses a combined wing and fuselage to create a single lifting surface throughout the entire wingspan. The BWB concept offers various advantages such as reduced operating cost, reduced noise emission and improved aerodynamic efficiency. It was expected that a combination of both nonplanar and BWB model would exhibit better aerodynamic performance. This study investigated the aerodynamic performance of a combined nonplanar and BWB concept model using experimental and computational methods at various pitch and yaw angles. The experimental tests were conducted at the de Havilland low-speed wind tunnel facility at the University of Glasgow, while the numerical simulations were carried out using OpenFOAM 8.0. Additionally, optimization of the wingtip shape was performed to improve the aerodynamic performance further. The aerodynamic characteristics and flowfield analyses of the wing model were presented and explained using the post-processed figures. | ||||
| 14:00 | 14:30 | 8.11.2 |
ASPECT RATIO AND ADVANCE RATIO EFFECTS ON AERODYNAMIC CHARACTERISTICS OF FLEXIBLE FLAPPING WINGS R. Addo-Akoto¹, S.-G. Lee¹, J.-S. Han, Chungnam National University, South Korea; J.-H. Han¹; ¹KAIST, South Korea Presenter: Reynolds A.-A, KAIST In this study, experiments are conducted to examine the aspect ratio AR and advance ratio J effects on the aerodynamic characteristics of flexible flapping wings. Three aspect ratios and five J cases are considered in this study. The study reveals that flexible wings can generate non-negative (? 0) transient lift in the upstroke for higher J cases, which is in contrast to the negative lift reported in literature for rigid wings. An increase in J decreases both the cycle-average aerodynamic lift and power irrespective of AR. Hence, a negative exponential relation is found to exist between the cycle-average lift and J, and cycle-average power and J. The AR = 1.5 and 6.0 wings are found to produce almost the same amount of lift for each change in J. However, the AR = 3.0 wing produced the best aerodynamic performance in terms of maximum lift generation and balance in efficiency. To maximize lift at mid-downstroke, the study reveals the existence of an optimum combination of J and AR. Furthermore, the resultant effect of AR and J on the forward force and pitching moment on the virtual body of the flapping flier is examined. The study reveals the tendency of low AR wings (= 1.5 and 3.0) to restore the body to its neutral position; convergence with increasing J. In addition, the low AR wings produce higher forward force than the high AR (= 6.0) wing, emphasizing the dominance and benefits of adopting a low AR wing in flapping flight applications. | ||||
| 14:30 | 15:00 | 8.11.3 |
NUMERICAL STUDY ON THE FIRST-STAGE RE-ENTRY TRAJECTORY USING AN INFLATABLE BALLUTE V. Orlandini¹, R. Paciorri¹, A. Assonitis¹, A. Bonfiglioli, Università degli Studi della Basilicata, Italy; ¹University of Rome La Sapienza, Italy The work explores using an inflatable ballute for decelerating reusable launch vehicle (RLV) first stages during re-entry. This innovative approach, tested on a rocket with a liquid propellant engine, extends mission time, reduces stress at higher altitudes, and significantly lowers speed near the ground. It aims to assess the feasibility and advantages of this method w.r.t. other devices. | ||||
| 15:00 | 15:30 | 8.11.4 |
AERODYNAMIC ANALYSIS OF A FLAP-BASED DEPLOYABLE RE-ENTRY SYSTEM UNDER RAREFIED CONDITIONS D. Vera Sepúlveda¹, R. Cassineli Palharini¹, E. Gaglio, Scuola Superiore Meridionale, Italy; R. Savino, University of Naples “Federico II”, Italy; ¹Universidad Técnica Federico Santa Marpia, Chile In this paper, a flat-based deployable heat shield for cubeSat reentry and recovery is presented. It is a new way to bring small satellites back to Earth and reuse them for new missions. The altitude effect on the flowfield structure, forces, and surface properties will be presented in detail in the final version of the paper. | ||||
| additional information (interactive) | 8.11.R |
SIMULATION STUDY ON AERODYNAMIC CHARACTERISTICS OF COMBINED LOW ASPECT RATIO UAV Y. Li¹, X. Xu¹, Z. Zhou¹, Y. Bai¹, H. Wang¹, B. Xu¹; ¹Northwestern Polytechnical University, China Presenter: Yunlong Li | |||||
| additional information (interactive) | 8.11.R |
RESEARCH ON OPTIMAL TORSIONAL DEFORMATION OF FLAPPING WING J. Liu¹, D. Xue¹; ¹School of Aeronautics, Northwestern Polytechnical University, China | |||||
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| 13:30 | 14:00 | 9.11.1 |
ESTIMATING THE IMPACT OF NUMERICAL WEATHER PREDICTION DATA MODELS ON SHORT-HAUL MINIMUM COST TRACKS N.K. Wickramasinghe¹, Y. Nakamura¹, A. Senoguchi¹; ¹Electronic Navigation Research Institute, Japan This study investigates the impact of weather forecast error in flight planning and its influence in aircraft operational performance. Minimum Cost Tracks over the Tokyo/Fukuoka flight route from a Dynamic-Programming-based trajectory optimizer based on three weather models are used in the evaluation and the results are compared with a series of flight plan data and Quick Access Recorder data. | ||||
| 14:00 | 14:30 | 9.11.2 |
PAIRWISE SWAPPING SEQUENCE OPTIMIZATION BY METROPOLIS-HASTING ALGORITHM WITH QUANTUM ANNEALING FOR AIR TRAFFIC CONTROL N. Yoshikawa, Mitsubishi Electric Corporation, Japan The sequence optimization method with quantum annealing sampler-based Metropolis-Hasting algorithm is investigated. In this study it is shown that the proposed method can solve the sequencing problem with 100 aircraft and 4 runway assignment problem in 10 sec. | ||||
| 14:30 | 15:00 | 9.11.3 |
AUTOMATED OPERATION OF HIGH-PERFORMANCE FIXED-WING DRONES: A POTENTIAL GAME-CHANGER FOR GREEN AERIAL SERVICES M. Spieck, Thelsys, Germany; J.H. Binnebesel¹, J. Mehnen¹; ¹mb+Partner, Germany The work presents technologies that enable fully automated and remotely controlled drone operations, which will greatly improve efficiency and flexibility of high-performance, high value applications. The operating principle is explained by the application example of persistent monitoring missions for the early detection of wildfires. | ||||
| 15:00 | 15:30 | 9.11.4 |
STRUCTURED ANALYSIS ESTIMATION FOR ELECTRICAL ENERGY DEMAND ON AIRPORT OPERATIONS FOR HYBRID REGIONAL AND ELECTRIC TOWING PARAMETERIZED BY MOVEMENT METRICS CONSIDERING UPCOMING ELECTRIC INTENSIVE TECHNOLOGIES AND EMISSION REDUCTIONS IN THE UPCOMING D T. Oliveira¹, A. Carvalho¹; ¹The Boeing Company, Brazil The goal of this work is to provide a structured analysis estimation for electrical energy demand on airport operations parametrized by influence area gross domestic product (GDP), passenger (PAX), cargo and movement metrics considering upcoming electric intensive technologies with regards to the competitive factors that will influence on these new operations when compared to current state. | ||||
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| 13:30 | 14:00 | 10.11.1 |
PATCHBOND II - CERTIFICATION OF ADHESIVE BONDED REPAIRS FOR PRIMARY AEROSPACE COMPOSITE STRUCTURES J. Jokinen, Tampere University, Finland; T. Thorvaldsen, Norwegian Defence Research Establishment, Norway; P. Nijhuis, Royal Netherlands Aerospace Centre, Netherlands; M. Kadlec¹, R. Ruzek¹, L. Munch, University of Stuttgart, Institute of Aircraft Design, Germany; M. Hoffmann, Airbus Defence and Space GmbH, Germany; T. Viitanen, Technical Research Center of Finland Ltd, Finland; M. Wallin, Patria Aviation, Finland; G. Sagvolden, Light Structures AS, Norway; C. Sbarufatti², L. Martulli², A. Bernasconi²; ¹Czech Aerospace Research Centre, Czech Republic ;²Politecnico di Milano, Department of Mechanical Engineering, Italy The European Defence Agency (EDA) project PATCHBOND II (June 2020 – June 2025) was established for studying adhesively bonded repairs of primary composite structures. This multinational project is based on collaboration between several aerospace companies, governmental institutions, research institutes and universities. The main targets are to study damage tolerance and monitoring of the bonded repairs of primary aircraft structures. The project is divided into four technical work packages, for which motivations and developments are presented. The on-going project work has already provided valuable results in the field of adhesively bonded repairs. | ||||
| 14:00 | 14:30 | 10.11.2 |
HOT-WET CONDITIONING AND THE SENSITIVITY OF MECHANICAL TESTING WITHIN SURFACE TREATMENT QUALIFICATION FOR AIRCRAFT D. Blanco Garde¹, F. Mews¹, J. Jokinen¹, N. Pournoori¹, M. Kanerva¹; ¹Tampere University, Finland Surface treatments are necessary for durable adhesive bonds either within aircraft assembly or repair bonding during service engineering. This study focuses on comparing effects of environment (ambient versus hot-wet) on adhesive bond strength when carbon fibre-reinforced composite surface has been qualified by contact angle measurements. The results indicate that conditioning is beneficial. | ||||
| 14:30 | 15:00 | 10.11.3 |
STABLE LOCALIZED CORROSION IN A 7075-T6 ALUMINUM ALLOY FSW JOINT: MECHANISM AND MITIGATION K. Li¹, Y. Ma, Chongqing University of Technology, China; Y. Han¹; ¹AVIC Manufacturing Technology Institute, China Presenter: Kai Li, AVIC Manufacturing Technology Institute The microstructure and corrosion behavior of a friction stir welded 7075 aluminum alloy joint was investigated. Different zones of the FSW joint showed various corrosion behavior. The intergranular corrosion was ascribed to the galvanic coupling effect between Cu-rich grain boundary precipitates and the precipitates free zones. It is urgent to develop a systematic approach to mitigate such attack. | ||||
| 15:00 | 15:30 | 10.11.4 |
INVESTIGATION ON THE MECHANISM OF THERMAL CYCLING FAILURE IN C/SIC COATING COMPOSITE MATERIALS Y. Ma, China; X. Zha, China; P. Cheng, China; J. Xie, China; L. Li, China; X. Liu, China Presenter: Yanbin Ma, Avic Aircraft Strength Research Institute This paper investigates the mechanical properties and microstructural characteristics of C/SiC materials in a 1500?-oxidizing environment using a self-developed thermo-mechanical-oxygen coupling tensile device and SEM characterization method.Important data regarding the high-temperature tensile strength, fracture morphology, and internal microstructural evolution of C/SiC materials are obtained. | ||||
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| 13:30 | 14:00 | 11.11.1 |
DESIGN OF A HIGH ENTHALPY HYPERSONIC NOZZLE FOR “GHIBLI” PLASMA WIND TUNNEL D. Guida¹, A. Smoraldi¹, A. Schettino, C.I.R.A., Germany; ¹CIRA Italian Aerospace Research Centre, Italy This paper presents a new design methodology for hypersonic nozzles for high-enthalpy wind tunnels. The method consists of an iterative optimization procedure based on the Newton-Raphson method, using a direct design approach in weak coupling with a proprietary CFD solver, for the complete treatment of thermo-chemical non-equilibrium conditions. | ||||
| 14:00 | 14:30 | 11.11.2 |
SPARSE RECONSTRUCTION OF SURFACE LOADS ON AIRCRAFT USING POD AND RBFNN X. Jia¹, C. Gong¹, C. Li¹; ¹Northwestern Polytechnical University, China A sparse reconstruction model using proper orthogonal decomposition and radial basis function neural network is proposed. In the optimization of sensor locations, an enhanced objective function is devised by integrating the surface loads. Results demonstrate accurate estimation of surface pressure coefficients on the aircraft DLR-F6 using 36 sensors. | ||||
| 14:30 | 15:00 | 11.11.3 |
DEVELOPMENT OF UNSTEADY PRESSURE-SENSITIVE PAINT FOR LOW REYNOLDS NUMBER WIND TUNNEL TESTS IN LOW-PRESSURE ENVIRONMENTS S. Takaya¹, K. Shibata¹, D. Numata¹; ¹Tokai University, Japan From the present study, it was found that the number of dye solution coatings does not significantly affect the pressure sensitivity of PSP, it has a significant impact on its time response characteristics if the coating conditions are not strictly controlled. | ||||
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| 13:30 | 14:00 | 12.11.1 |
STUDY ON LOW-VELOCITY IMPACT BEHAVIOR AND RESIDUAL PERFORMANCE PREDICTION OF CFRP T-JOINTS J. Zhou, China; C. Zhang, China Current methods that employ multiple models to assess the mechanical properties of composites exhibit certain limitations. This study develops a combined FE analysis method, based on stress failure criteria and stiffness degradation theory. It transfers element damage states between models, avoiding traditional method inefficiencies and errors in multi-model information transfer. | ||||
| 14:00 | 14:30 | 12.11.2 |
THE RESISTANCE TO THE HIGH-VELOCITY IMPACT OF THE INTRA-LAYER HYBRID PLAIN WEAVE COMPOSITES H. Wu¹, Y. Bai¹, S.-L. Fang¹, Z.-Q. Zhao¹, C. Zhang¹; ¹Northwestern Polytechnical University, China The effects of hybrid proportions and configurations on the impact resistance of Kevlar/Carbon hybrid plain weave composite are clarified, and the results can provide reference and data support for the design of the new generation aero engine casing. | ||||
| 14:30 | 15:00 | 12.11.3 |
MODELING THE TEMPERATURE-RISE BEHAVIOR OF 2D TRIAXIAL BRAIDED COMPOSITES UNDER IMPACT LOADS C. Zhang¹, P. Liu¹, Y.-L. Li¹; ¹Northwestern Polytechnical University, China The damage and failure behavior of braided composites under impact load is a typical high strain rate and thermo-mechanical coupling problem. It can be seen that to reveal the impact failure mechanism of braided composites, it is necessary to consider the local temperature rise effect during impact process and develop an appropriate numerical analysis method. | ||||
| 15:00 | 15:30 | 12.11.4 |
THE EFFECT OF TARGET THICKNESS ON THE BALLISTIC BEHAVIOR OF HYBRID CFRP/KFRP COMPOSITES S. Zhao¹, J. Huang¹, C. Zhang¹; ¹Northwestern Polytechnical University, China The study confirmed a strong relationship between thickness and ballistic impact behavior, which has never been addressed in any previous studies of composite stacking methods.Analyses further suggested KFRP as the back face (THIN) and CFRP as the back face (THICK) demonstrate better impact resistance.This study provides theoretical support for the design and development of aero-engine cases. | ||||
| additional information (interactive) | 12.11.R |
EFFECT OF INFILL STYLE AND DENSITY ON SELECTED MECHANICAL PROPERTIES OF THE CARBON FIBRE REINFORCED ABS MFD FILAMENT M. Mucha¹, D. Sikorski, 41st Training Air Base, Poland; R. Szczepaniak¹, R. Babel¹, A. Krzyzak¹, T. Zahorski¹; ¹Polish Air Force University, Poland | |||||
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| 13:30 | 14:00 | 13.11.1 |
FLOW CHARACTERISTICS OF THE INLET IN TURBOPROP ENGINE WITH THE INFLUENCE OF SANDS B. Mi¹, H. Zhan¹, J. Yu, No. 5715 Factory of PLA, China; ¹Northwestern Polytechnical University, China A numerical simulation based on CFD-DPM model has been constructed to consider the dynamic effect of the sands in the airflow on the total pressure recovery coefficient and distortion rate of the inlet. The propeller slipstream has also been calculated to evaluate the influence on the inlet performance with sands, and the influence law of the parameters of the sands have been further revealed. | ||||
| 14:00 | 14:30 | 13.11.2 |
DEEP LEARNING BASED FAST PREDICTION OF AERODYNAMIC PARAMETERS FOR DUCTED PROPELLERS L. Liu¹, L. Zeng¹, T. Wang¹, Z. Gao¹, X. Shao¹; ¹Zhejiang University, China A deep learning-based aerodynamic prediction surrogate model for ducted propellers is developed, which combines different physical properties to improve prediction precision, and has a certain generalization ability and interpretability, solves the drawbacks of traditional surrogate models, and greatly shortens the global optimization design cycle of the aircraft. | ||||
| 14:30 | 15:00 | 13.11.3 |
LOW-SPEED PROPELLER FOR UAV APPLICATIONS, FROM DESIGN TO EXPERIMENTAL EVALUATION M. Crona¹, S. Dinger¹, P. Samuelsson¹, H. Strömfeldt¹, I. Jonsson¹; ¹Chalmers University of Technology, Sweden The design and evaluation of a low-speed UAV propeller using OPTOPROP, a blade element momentum theory design tool is presented. It includes CFD and wind tunnel tests. The study emphasizes the integration of Xfoil to handle low Reynolds number airfoil data for low-speed applications, improving the match between BLMT and CFD by up to 10% | ||||
| 15:00 | 15:30 | 13.11.4 |
PRELIMINARY COUPLING EFFECTS OF A NOVEL INTEGRATED SELF-SUPERCHARGED PROPULSION SYSTEM X. Xiong¹, S. Wu¹; ¹International WYNNBEAR Advanced AeroTechInnovation, United States A lightweight and efficient refined propulsion system that utilizes integrated diffusers and acceleration fans with self-pressurization, as well as efficient matching and coupling, has demonstrated significant improvements in maximum thrust and efficiency (FG/W) for aircraft, small unmanned aerial vehicles (UAVs), and drones, with a respective increase of 30% and 35%. | ||||
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| 13:30 | 14:00 | 14.11.1 |
ADVANCED RADAR-BASED COUNTER-UAV SOLUTIONS FOR ENHANCED AIRCRAFT SECURITY IN AIRPORT ENVIRONMENTS V. Miliotis, Bianor Services Ltd & MSB Technologies P.C., Bulgaria; T. Punchev, Bianor Services Ltd, Bulgaria; I.D. Gavardinas, Hellenic Air Force & University of Thessaly, Greece; P. Koutidis, Hellenic Air Force, Greece; B. Papaspyros, Hellenic Air Force Engineers Scientific Society, Greece; P. Chatzimisios, International Hellenic University, Greece Presenter: VASILEIOS MILIOTIS, Bianor Services Ltd and MSB Technologies This paper conducts a thorough review of current research and available solutions on counter-UAV technologies, focusing on disruptions of aircraft operations by swarm and mini drones in complex airport environments. It introduces a novel radar and AI-based architecture for enhanced detection and effective neutralization, ensuring robust protection of aircraft operations. | ||||
| 14:00 | 14:30 | 14.11.2 |
A FAST INFORMATION THEORETICALLY SECURE RADIO COMMUNICATION PROTOCOL BASED ON GNSS POSITIONING S. Morioka, Interstellar Technologies Inc., Japan; S. Obana, Hosei University, Japan; M. Yoshida, NICT, Japan We have proposed a radio communication protocol that guarantees the highest security level called information theoretic security. The use of state variables is minimized to improve the resilience against H/W failures. In this paper, we have improved the throughput to 10Mbps by incorporating the use of GNSS positioning. | ||||
| 14:30 | 15:00 | 14.11.3 |
MUTUAL POSITION PLAUSIBILITY CHECKING IN FLYING AD-HOC NETWORKS USING DISTANCE MEASUREMENTS T. Marks, German Aerospace Center, Germany; K. Fuger, Hamburg University of Technology, Germany Position verification of UAV in high density traffic scenarios is an important issue. In our work we present an approach to perform a plausibility check on the positions using distance measurement data obtained by the data link connections. We verify this approach by applying an appropriate algorithm to data traffic generated for UAV package delivery traffic scenarios. | ||||
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| 13:30 | 14:00 | 15.11.1 |
FAILURE HANDLING ON A SPLIT-FLAP ULTRALIGHT GENERAL AVIATION AIRCRAFT WITH HYBRID NONLINEAR DYNAMIC INVERSION D. Milz¹, M. May¹, J. Martins¹, R. Kuchar¹, G. Looye¹; ¹German Aerospace Center (DLR), Germany Within the MOREALIS project, this work presents a semi-electronic flight control concept with split flaps and a hybrid nonlinear dynamic inversion control law to enable aided flight and automatic flight for an ultralight (UL) general aviation aircraft. The system is prepared for fault detection, isolation, and recovery and intends to increase the overall flight safety of UL aircraft. | ||||
| 14:00 | 14:30 | 15.11.2 |
EXPLORING A CATEGORY OF LIMIT CYCLE OSCILLATIONS IN AIRCRAFT HYDRAULIC SYSTEMS S. Yang¹, Y. Long, School of Energy and Power Engineering, Beihang University, China; Z. Hu¹; ¹Institute for Aero Engine, Tsinghua University, China In the aircraft hydraulic system, a typical oscillation pattern has been discovered, referred to as a 3rd-order limit cycle. The cause of and criteria for its occurrence have been clarified and specifie | ||||