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| 10:30 | 11:00 | 1.1.1 |
FLYZERO: THE UK VISION FOR ZERO-CARBON EMISSION AIR TRAVEL (invited) S. Pendry, ATI, United Kingdom FlyZero is an independent UK study to investigate the options for zero-carbon emission commercial flight. It assessed the sustainability impact, design challenges, operational requirements and market opportunities. It concluded that research into liquid hydrogen aviation should be accelerated in parallel to sustainable aviation fuel research. This paper will outline the findings. | ||||
| 11:00 | 11:30 | 1.1.2 |
IMPACT OF NASCENT TECHNOLOGIES ON THE SUSTAINABILITY ATTRIBUTES OF AN EVOLUTIONARY SINGLE-AISLE AIRCRAFT N.J. Allen, Aerospace Technology Institute, United Kingdom; M.R. Schofield, Ellondee Ltd, United Kingdom The Single-Aisle Future Aircraft Model (SAFAM) demonstrates the performance benefits achievable through incorporating evolutionary technology improvements on an aircraft with intended EIS of 2035. Although zero emissions aircraft will be crucial to meet environmental goals, ultra-efficient aircraft like SAFAM will also be essential to achieving emissions reduction, combined with the use of SAF. | ||||
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| 10:30 | 11:00 | 2.1.1 |
LARGE-SCALE MULTIFIDELITY AEROSTRUCTURAL OPTIMIZATION OF A TRANSPORT AIRCRAFT N. Wu¹, C.A. Mader¹, J.R.R.A. Martins¹; ¹University of Michigan, United States Presenter: Neil Wu, University of Michigan Aided by the adjoint method, high-fidelity aerostructural aircraft optimizations have become more widespread in recent years. However, they are still computationally expensive and suffer from optimization convergence issues. In this work, we address some practical issues with large-scale aerostructural optimizations using a multifidelity approach together with a different geometric parameterization. We perform an optimization of a notional transport aircraft analyzed over ten flight conditions, including close to 1000 design variables and 1000 constraints. We compare the result against a reference single-fidelity optimization, and show simultaneous computational cost reduction and an improved level of optimization convergence. | ||||
| 11:00 | 11:30 | 2.1.2 |
REGIONAL JET RETROFITTING DESIGN: FROM STAKEHOLDERS’ NEEDS AND SYSTEM’S REQUIREMENTS TO MDAO WORKFLOW FORMULATION M. Mandorino¹, P. Della Vecchia¹, F. Nicolosi¹, S. Corcione¹, V. Trifari¹, G. Cerino, Leonardo Aircraft Division, Italy; M. Fioriti², C. Cabailero², T. Lefebvre, ONERA/DTIS, Université de Toulouse, France; ¹University of Naples Federico II, Italy ;²Politecnico di Torino, Italy In this paper, a process useful for the verification of economic, environmental and performance requirements related to the retrofit of a 90 passengers regional jet aircraft is described. Requirements are defined according to scenarios and stakeholders’ needs. The overall process is implemented in the framework of the AGILE 4.0 research project, leading to a thorough MBSE problem definition. | ||||
| 11:30 | 12:00 | 2.1.3 |
COAST - A SIMULATION AND CONTROL FRAMEWORK TO SUPPORT MULTIDISCIPLINARY OPTIMIZATION AND AIRCRAFT DESIGN WITH CPACS D. Kiehn¹, J. Autenrieb¹, N. Fezans¹; ¹German Aerospace Center (DLR), Germany This paper presents COAST (CPACS-Oriented Aircraft Simulation Tool), a fixed-wing aircraft simulation software specifically tailored for MDO aircraft design with the CPACS format. Due to its interface with the DLR full flight simulator AVES and a built-in generic flight control system, it offers the potential to use virtual flight testing in MDO toolchains and in early stages of aircraft design. | ||||
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| 10:30 | 11:00 | 3.1.1 |
HIGH-SPEED COMPOUND HELICOPTER RESEARCH AT JAXA M. Sugiura¹, Y. Tanabe¹, N. Kobiki¹, H. Sugawara¹, K. Kimura¹; ¹JAXA, Japan An overview on the research of a high-speed compound helicopter carried out in JAXA is presented. A distinctive configuration of a compound helicopter was proposed by JAXA. The main rotor is combined with a fixed wing to generate lift. The torque caused by the main rotor is canceled out by a couple of motor-driven propellers installed on the fixed-wing tips with differential thrusts between them. | ||||
| 11:00 | 11:30 | 3.1.2 |
DESIGN OF A FLYING V SUBSONIC TRANSPORT J. Benad¹, R. Vos¹; ¹Delft University of Technology, Netherlands This work intends to chronical the technical development of the Flying V aircraft concept. Development began in 2013 at Airbus Future Projects and has been continued at Delft University of Technology with Airbus and KLM. Various studies on the design are currently ongoing in fields such as aerodynamics, structures, manufacturing, flight dynamics, environmental impact, integration and operation. | ||||
| 11:30 | 12:00 | 3.1.3 |
DESIGN AND WIND TUNNEL TESTING OF A GENERAL AVIATION BLENDED WING BODY AIRCRAFT F. Staub¹, T. Tsuchiya¹; ¹The University of Tokyo, Japan Research over the last 3 decades has repeatedly suggested that a BWB aircraft will burn about 20-30% less fuel than a tube-and-wing aircraft for the same payload and range. Despite this, we still do not see BWBs in service today. This study proposes a way we can realize larger BWB aircraft in the future. while also providing immediate benefits in fuel efficiency to the general aviation market. | ||||
| Reserve Paper | 3.1.R |
EXPERIMENTAL INVESTIGATION OF A NEXT-GENERATION AIRLINER WITH BOUNDARY LAYER INGESTION P.D. Bravo-Mosquera¹, J.P. Eguea¹, H.D. Cerón-Muñoz¹, F.M. Catalano¹; ¹University of São Paulo, Brazil | |||||
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| 10:30 | 11:00 | 4.1.1 |
UNSTEADY TURBULENT FLOW SIMULATION OF ROTOR BLADES ON MOVING CARTESIAN GRIDS USING RECURSIVE FITTING APPROACH K. Sugaya¹, T. Imamura¹; ¹The University of Tokyo, Japan Presenter: Keisuke Sugaya, The University of Tokyo To simulate turbulent flow around moving bodies, we propose a new method capable of automatic grid generation and accurate turbulent flow simulation. The automatically generated body-fitted Cartesian grid moves with the bodies. To examine the capability of the proposed method, two- and three-dimensional unsteady flow are simulated. | ||||
| 11:00 | 11:30 | 4.1.2 |
COMPUTATIONAL ANALYSIS OF SUPERSONIC FLOW AROUND A WEDGE AND A CYLINDER USING BUILDING-CUBE METHOD K. Abe¹, S. Miyazaki¹, D. Sasaki¹, S. Takahashi², G. Yamada²; ¹Kanazawa Institute of Technology, Japan ;²Tokai University, Japan The Cartesian mesh CFD has received renewed attention in recent years due to its ease of mesh generation and small computational cost. Cartesian mesh CFD is conducted to solve supersonic flow to predict shock waves and heat flux. The computational targets are a cylinder and a wedge, and bow shock and oblique shock are precisely. In addition, shock wave interference between a wedge and a cylinder are computed. | ||||
| 11:30 | 12:00 | 4.1.3 |
ON THE INFLUENCE OF GRADIENT RECONSTRUCTION PROCEDURES OVER THE ACCURACY OF FINITE VOLUME BASED SCHEMES F.B. Oliveira, Instituto Tecnológico de Aeronáutica, Brazil; J.L.F. Azevedo, Instituto de Aeronáutica e Espaço, Brazil The present work analyzes three different gradient reconstruction procedures, using three different simulation test cases, namely the zero-gradient flat plate, the ONERA M6 wing and the wing-body common research model. Overall increase in algorithm robustness is observed when the gradient-calculation scheme that brings into the formulation the information from the discontinuous solution is used. | ||||
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| 10:30 | 11:00 | 5.1.1 |
GARTEUR: NEARLY HALF A CENTURY OF EUROPEAN COLLABORATION IN AERONAUTICS P. Renzoni, Centro Italiano Ricerche Aerospaziali, Italy This contribution will give an overview of the role played by the Group for Aeronautical Research and Technology in EURope (GARTEUR) over nearly half a century in the European collaboration in aeronautics research. The mission of GARTEUR, its organisation and principles, and its vision, as well as its fields of activities are presented. Conclusions and perspectives for future cooperation are addressed, addressing the challenges Europe has identified both in the civil and military domains. | ||||
| 11:00 | 11:30 | 5.1.2 |
THE GROUP OF RESPONSABLES \"AERODYNAMICS (GOR AD)\" AN OVERVIEW OF ACTIVITIES AND SUCCESS STORIES G. Mingione, CIRA, Italy; P. Coustols, ONERA, France; F. Monge, INTA, Spain; H. van der Ven, NLR, Netherlands; K. Richter, DLR, Germany; M. Tormalm, FOI, Sweden; L.R. Calavera¹, B. Stefes¹, D. Pagan, MBDA, France; P. Eliasson, SAAB, Sweden; M. Mallet, DASSAULT, France; R. Gemma, LEONARDO, Italy; ¹AIRUBS, Spain The GoR AD is active in initiating and organising basic and applied research in aerodynamics and aerothermodynamics. Aerothermodynamics is closely related to space operations and flight through the earth’s atmosphere at very high speeds. This contribution will give an overview about GoR AD research activities, will highlight some very successful highlights and give an outlook on future activities. | ||||
| 11:30 | 12:00 | 5.1.3 |
THE GROUP OF RESPONSABLES \"STRUCTURES AND MATERIALS (GOR SM)\": AN OVERVIEW OF ACTIVITIES AND SUCCESS STORIES H.G.S.J. Thuis, NLR, Netherlands The Garteur SM is active in initiating and organizing aeronautics oriented research on structures, structural dynamics and materials in general. Materials oriented research is related to material systems primarily for the airframe; it includes specific aspects of polymers, metals and various composite systems. Structural research is devoted to computational mechanics, loads and design methodology. Research on structural dynamics involves more especially response to shock and impact loading. The group is active in theoretical and experimental fields of structures and materials to strengthen development and improvement of methods and procedures. Of great importance is the mutual simulation of the diverse scientific approaches. Experiments give new insights into the mechanisms of structural behavior that can be included in improved theoretical models. Finally, the theoretical results must be verified and validated by comparison with results from suitable experiments or trials. Although the specific topics vary over the years, the scientific basis remains largely unchanged. The work is looked upon as an upstream research intended to discover valuable areas of future activity; Activities within the Exploratory and Action Groups cover several aspects of improved conventional and new technologies, new structural concepts and new design and verification criteria. Recent, current and upcoming work is devoted to: • Fatigue and damage tolerance assessment of hybrid structures • Damage repair with composites in composite and metallic structures • Characterization and modelling of Composites with Ceramic Matrix submitted to severe thermo-mechanical loading • Characterization of composites with polymer matrix at high temperatures • Characterization and optimization of shock absorbers for civil aircraft fuselages • Additive Layer Manufacturing • Structural health monitoring for hydrogen airc | ||||
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| 10:30 | 11:00 | 6.1.1 |
EXPERIMENTAL INVESTIGATION OF THE EFFECT OF THE YAW ANGLE ON THE DRAG REDUCTION RATE FOR TRAPEZOIDAL RIBLETS A. Inasawa¹, R. Taniguchi¹, M. Asai¹, M. Sasamori², M. Kurita²; ¹Tokyo Metropolitan University, Japan ;²JAXA, Japan The effects of yaw angle of riblets on the drag reducing effect was examined experimentally for riblets having trapezoidal valleys in turbulent wind channel. The drag reduction effect was weakened when the yaw angle exceeded 10 deg and thus was more sensitive to the yaw angle than for saw-tooth riblets. | ||||
| 11:00 | 11:30 | 6.1.2 |
STABILTY AND TRANSITION OF A LAMINAR SEPARATION BUBBLE SUBJECTED TO FREESTREAM TURBULENCE T. Jaroslawski¹, O. Vermeersch¹, J.-M. Moschetta², M. Forte¹, E. Gowree²; ¹ONERA, France ;²ISAE-SUPAERO, France Experiments are conducted on a two-dimensional laminar separation bubble subjected to a large range of free stream turbulence levels (0.18% < Tu < 6.26%) and integral length scales (8.31mm < Lu < 17.18mm). Spectral analysis of the unsteady velocity measurements and wall-normal disturbance pro les revealed the co-existence of two modes in the bubble: a modal instability attributed to a convective instability and a non-modal instability linked to streaks. The streamwise growth of the energy disturbances is exponential for the lowest levels of freestream turbulence and gradually becomes algebraic as the level of freestream turbulence increases. In occurrence with previous studies, an increase in the level of freestream turbulence, advances the transition position, decreasing the size of the bubble, with its eventual elimination at the highest levels. Finally, for a relatively fixed level of Tu, the variation of Lu has modest effects, however a slight advancement of transition with the decrease in Lu is observed. | ||||
| 11:30 | 12:00 | 6.1.3 |
UNIFORM MOMENTUM ZONES IN A TURBULENT BOUNDARY LAYER OVER PERFORATED WALLS F. Scarano¹, M.C. Jacob, Université de Lyon, France; X. Carbonneau¹, E.R. Gowree¹; ¹ISAE - SUPAERO, France The physics of a boundary layer developing over perforated plates at a moderate Reynolds number is gained from a combined experimental and numerical investigation. The experiments are conducted combining hot wire anemometry and steresocopic PIV. The findings are consistent with literature as to the possibility of reducing drag with circular perforations. | ||||
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| 10:30 | 11:00 | 7.1.1 |
METHODOLOGIES AND EXAMPLE OF CONCEPTUAL DESIGN FOR A FOOT-LAUNCHABLE SPORT SAILPLANE L.M.F. Barbosa, Heart Aerospace, Sweden This work presents a design approach for foot-launchable sport aircraft. The aim is to partially fill a gap in terms of "low-speed, manned aircraft" design, since sometimes these aircraft are not effectively defined using 'classical' approaches; and some foot-launchable aircraft are seem to be result of a ‘intuition-trial-and-error’ process, with support of some theoretical concepts. | ||||
| 11:00 | 11:30 | 7.1.2 |
AIRFOIL DESIGN BY MULTI-ADDITIONAL SAMPLING MULTI-FIDELITY EFFICIENT GLOBAL OPTIMIZATION K. Khankwa¹, T. Phiboon¹, A. Ariyarit¹, R. Kasemsri¹, M. Kanazaki, Tokyo Metropolitan University, Japan; ¹Suranaree University of Technology, Thailand An Efficient global optimization (EGO), with multi-additional sampling multi-fidelity optimization, is applied for NACA 4-digit airfoil design with a single objective to maximize the proportion between lift coefficient (Cl) to drag coefficient (Cd). The application of this research is able to be used in the aircraft design industry to improve the design process. | ||||
| 11:30 | 12:00 | 7.1.3 |
STRUCTURAL DESIGN AND FLUTTER ANALYSIS OF SWEPT BAFFLED INFLATABLE WING N. Ma¹, F.-M. Meng¹, J.-H. Meng¹, L. Liu¹; ¹Beijing Institute of Technology, China Based on the combination of traditional structure and aeroelastic tailoring design, a design method of a new inflatable wing with swept arranged inflatable beams named swept baffled inflatable wing is proposed to realize the improving of aerodynamic and aeroelastic performance. Results show that the swept baffled structure can improve the lift drag ratio and delay the classical flutter. | ||||
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| 10:30 | 11:00 | 8.1.1 |
A REDUCED ORDER MODEL FOR FULL-SCALE DRONE COLLISIONS F. Franke¹, U. Burger¹, C. Hühne, German Aerospace Center, Germany; ¹Technische Hochschule Ingolstadt, Germany In parallel to bird strikes and hailstorms, drone strikes also pose a threat to manned aviation. This paper presents a novel model to calculate the impact force during mid-air collisions of drones with manned aircraft. This model can be used to determine the force-time curve and use the results for a preliminary design of endangered structures. | ||||
| 11:00 | 11:30 | 8.1.2 |
HIGH FIDELITY AIRWORTHINESS BIRD AND DRONE STRIKE ANALYSIS OF ON-DEMAND AIR MOBILITY SERVICE AIRCRAFT P. Vaghela¹, H. Raza¹, E. Stumpf, Institute for Aerospace Systems, RWTH Aachen University, Germany; J. Bayandor¹; ¹CRASH Lab, University at Buffalo - The State Univ. of New York, United States Direct and oblique impacts from bird and drone are modeled on canopy, wings, structure and engine of a modern short take-off and landing aircraft for On-Demand Air Mobility using highly representative finite element analysis. Post-impact behaviors of the structures are investigated to establish new analysis strategies as well as airworthiness criteria. | ||||
| 11:30 | 12:00 | 8.1.3 |
XRF1 HIGH LIFT LOAD ANALYSIS OF WING AND HIGH LIFT SYSTEM S. Pülm¹, V. Handojo¹, R.B. Seidler¹; ¹German Aerospace Center (DLR) e.V., Germany Presenter: Sven Pülm, German Aerospace Center (DLR) To investigate the potential of wing load alleviation in cruise flight, the repercussions on take-off, approach and landing are of interest. CFD analysis of XRF1 high lift load cases deliver aerodynamic loads on wing and high lift devices. Using a condensed structural model, the loads are superposed with inertial loads. | ||||
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| 10:30 | 11:00 | 9.1.1 |
SERIES-HYBRID RETROFIT OF AN XV-15 TILTROTOR AND EMERGENCY PROCEDURE ENERGETIC ANALYSIS G. Avanzini, University of Salento, Italy; G. Bernardini¹, S. Moretti¹, J. Serafini¹; ¹Roma Tre University, Italy This work reports the retrofit of the propulsion system of a XV-15 tiltrotor aicraft into a series-hybrid one. The performance and the environmental impact are reported, considering current technology and future trends. Moreover,an emergency landing procedure suited for this kind of aircraft is defined and its performance is assessed. | ||||
| 11:00 | 11:30 | 9.1.2 |
DEVELOPMENT OF A CONTROLS APPROACH FOR FUEL CELL-POWERED ALL-ELECTRIC AERO ENGINES BASED ON AN FHA S. de Graaf¹, S. Kazula¹; ¹DLR e.V., Germany This work sheds light on the challenges imposed on powertrain controls by the fuel cell technology of today, in general, and the LT-PEM fuel cell, in particular. Controls tasks specific to fuel cell-powered aero engines were derived and strategies developed to comply with the demanding performance and safety requirements of aviation and enable the introduction of sustainable electrified aero engines. | ||||
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| 10:30 | 11:00 | 10.1.1 |
USING ACTIVE FLOW CONTROL TO IMPROVE THE AERODYNAMIC PERFORMANCE OF THE NEXT GENERATION CIVIL TILT ROTOR AIRCRAFT J.B. Vos¹, A. Gehri¹, H. Truong², A. Marouf², Y. Hoarau²; ¹CFS Engineering, Switzerland ;²University of Strasbourg, ICUBE Research Institute, France This paper discusses the use of so called Zero Net Mass Flux (ZNMF) actuators for active flow control on the Next Generation Civil Tilt Rotor Technical Demonstrator (NGCTR-TD) aircraft. The Next Generation Civil Tilt Rotor (NGCTR-TD) is a a novel concept that combines the benefits of a helicopter with the speed and the capabilities of a fixed wing aircraft. The European Funded CleanSky2 project AFC4TR will investigate the use of ZNMF devices to increase the aerodynamic efficiency. In the first phase of the | ||||
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| 10:30 | 11:00 | 11.1.1 |
A SEMANTIC KNOWLEDGE BASED ENGINEERING FRAMEWORK FOR THE RAPID GENERATION OF NOVEL AIR VEHICLE CONFIGURATIONS J. Zamboni¹, A. Zamfir¹, E. Moerland¹, B. Nagel¹; ¹German Aerospace Center (DLR), Germany This paper presents a recently developed, novel knowledge-based engineering framework, which allows for the transparent digitization of conceptual design knowledge and its interconnection using semantic-web technologies. It focuses on describing an effective structure for capturing and storing the expert’s knowledge and on the procedures required to solve and analyze the resulting complex system. | ||||
| 11:00 | 11:30 | 11.1.2 |
RULE-BASED VERIFICATION OF A GEOMETRIC DESIGN USING THE CODEX FRAMEWORK B. Boden¹, Y. Cabac¹, T. Burschyk¹, B. Nagel¹; ¹DLR, Germany This paper presents the codex-geometry module for geometry modelling using semantic web technologies within the Codex KBE framework. We use rules to express geometric requirements and analysis functions, which are automatically evaluated in order to verify a geometric design. We show our approach by the example use case of a conventional fuel system model, including pipe systems and fuel pumps. | ||||
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| 10:30 | 11:00 | 12.1.1 |
REAL-TIME CALCULATION AND ADAPTION OF CONFLICT-FREE AIRCRAFT GROUND TRAJECTORIES L. Nöhren¹, M. Schaper¹, L. Tyburzy¹, K. Muth¹; ¹German Aerospace Center (DLR), Germany In this paper an algorithm is presented, which enables calculation and adaption of aircraft surface traffic trajectories in real-time. It is a combination of an A* algorithm and a genetic algorithm and uses a configurable target function to reach specific optimization goals. The paper closes with test results from a simulation of a complex traffic scenario. | ||||
| 11:00 | 11:30 | 12.1.2 |
DEVELOPING A DEPARTURE QUEUE MODEL FOR INTEGRATED ARRIVAL AND DEPARTURE OPERATION OF RUNWAYS E. Itoh, The University of Tokyo/ENRI, Japan; D. Iwata, The University of Tokyo, Japan; M. Schultz, Bundeswehr University Munich, Germany Presenter: Daiki Iwata, The University of Tokyo This study designs a methodology to develop an aircraft departure queue model at a runway using a time-varying fluid queue, which allows us to input actual time-varying takeoff and landing rates at the runway. The proposed model enables us to design an optimal control approach dealing with an integrated arrival and departure air traffic management. | ||||
| 11:30 | 12:00 | 12.1.3 |
ASSESSMENT AND CONTROL OF ARRIVAL FLOW AND WAITING TIME APPLYING GT/GI/ST+GI TIME-VARYING QUEUING MODEL K. Higasa, The University of Tokyo, Japan; E. Itoh, Electronic Navigation Research Institute, Japan To propose operational strategies to control arrival traffic efficiently, the Gt/GI/st+GI time-varying queueing model, which enables detailed analysis of time-dependent factors, is applied to the actual arrival flow in Japan. The waiting time of entering aircraft in different arrival scenarios is calculated, focusing on the time-varying capacity of airspace and the flight time distribution. | ||||
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| 10:30 | 11:00 | 13.1.1 |
LONG TOUCHDOWN THROUGH A SAFETY-II PERSPECTIVE C. Reiser, Embraer, Brazil; E. Villani¹, M. Machado Cardoso Junior¹; ¹ITA, Brazil Presenter: Moacyr Machado Cardoso Junior, ITA Safety-II assumes that individuals and organizations habitually adjust their performance to match current demands, resources, and constraints to compensate the incompleteness of procedures. It suggests that everything happens basically in the same way, despite of the outcome. This paper shows the analysis of aircraft touchdown routine by this perspective, using a customized and quantitative FRAM. | ||||
| 11:00 | 11:30 | 13.1.2 |
DECISION LADDER APPLICATION ANALYZING A HELICOPTER EMERGENCY B.R. Teixeira¹, L.G.L. de Paula¹, A.C.S. Freitas¹, R.G. Cortes², M.Y.D. Ribeiro², M.M.C. Júnior², E. Vilani²; ¹Brazilian Air Force Flight Test and Research Institute, Brazil ;²Instituto Tecnológico de Aeronáutica , Brazil Presenter: Moacyr Machado Cardoso-Júnior, Aeronautical Institute of Technology This article aimed to analyze how the decision ladder can be used to evaluate emergency situations in aircraft, assist in identifying relevant information, and even improve existing procedures. A case study was conducted based on a real occurrence of an emergency light indicating the presence of metallic particles in a Black Hawk helicopter transmission oil flying in the Amazonian scenario. Based on the decision ladder methodology, it was verified that the occurrence analyzed was not correctly addressed in the flight manual and there would be a need for the inclusion of a new emergency procedure in the flight manual, which would allow the crew to separate a situation of major risk from one of minor risk. | ||||
| 11:30 | 12:00 | 13.1.3 |
SYSTEM SAFETY-BASED SUSTAINABLE AVIATION FUEL SAFETY ASSESSMENT METHOD AND AIRWORTHINESS CERTIFICATION S. Ding, Civil Aviation University of China, China; C. Gan¹, T. Qiu¹, P. Liu¹, Q. Ma¹; ¹Beihang University, China In this paper, we propose a system safety-based SAF safety assessment method. With the system safety as the top-level objective, this method upgrades the similarity check in the certification process from the fuel level to the engine level. The certification process we proposed can effectively improve certification efficiency and unlock fuel potential while maintaining system safety levels. | ||||
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| 10:30 | 11:00 | 14.1.1 |
OPERATIONAL FEASIBILITY STUDY OF AIR TAXI SERVICE USING EVTOL H. Takizawa¹, Z. Lei¹; ¹Suwa University of Science, Japan The purpose of this study is to investigate the demand with consideration of flight performance of the eVTOL, and discuss the operational feasibility of the eVTOL-based air taxi. The eVTOL station for takeoff and landing, and a business model for operation will be studied by comprehensively taking into account some constraints. | ||||
| 11:00 | 11:30 | 14.1.2 |
NEW GENERATION SPACE VEHICLE OPERATIONS IN THE UNITED ARAB EMIRATES – AN AIRSPACE AND RISK ASSESSMENT O. Lehmann¹, R. El-Jabi¹, K. Webster¹, A. Rachdi¹; ¹Abu Dhabi University, United Arab Emirates The purpose of this study is to understand in detail how New Generation Space Vehicle Operations could be integrated into a highly dense airspace when operating from and to a United Arab Emirates spaceport. The results show, that the performance of the glider during the return continues to be a challenge for a safe and efficient operation that does not threaten and obstruct other airspace user. | ||||
| 11:30 | 12:00 | 14.1.3 |
EQUIVALENT CALCULATION METHOD OF FLYOVER NOISE LEVEL OF CUTBACK TAKE-OFF FOR CIVIL JET AIRPLANE AIRWORTHINESS CERTIFICATION Y.-H. Song¹, X.-L. Zhang¹, Q.-H. Liu, Northwestern Polytechnical University, China; Y.-L. Thang¹; ¹Chinese Flight Test Establishment, China A high-precision and widely applicable equivalent method for calculating the flyover noise of engine power cutback take-off is proposed for civil jet airplane airworthiness. Flyover EPNL are calculated by constructed PNLTr history equivalently. A new PNLTr history construction procedure is presented. The method is validated by a civil jet airplane flight test data. | ||||
| Reserve Paper | 14.1.R |
A GLOBAL APPROACH TO ASSESSING THE CLIMATE RESILIENCE OF AIRPORTS M.P.P. Osund-Ireland¹, A.J. Powell¹, C.J. Ireland¹; ¹susteer AB, Sweden | |||||
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| 14:10 | 14:40 | 1.2.1 |
A ROADMAP TOWARDS ENVIRONMENTALLY SUSTAINABLE AVIATION (invited) B. Loxton, United States Different industry players and research organizations have recently joined the challenge towards the emission?free aviation by 2050. Such cooperation is encompassing experiences and advancements in various technological fields, including synthetic fuels, hydrogen in gas turbines and hydrogen fuel cells, revolutionary gas turbine cycles, electric propulsion systems, hybrid?electric, optimized battery systems and climate?friendly routing. The numerous advantages offered by electric propulsion in particular have resulted in a dramatic increase in excitement around this concept. Lower capital cost, lower fuel (or zero fuel) and maintenance costs, decreased noise and air pollution, improved safety, availability and reliability and enabling solutions for unique aircraft design are among the benefits of this revolution; however, the realization of the full potential for the electric aircraft market will require significant advances in motor, inverter and battery technology, with focus on optimizing the various concepts at system level and on realizing higher power densities. magniX, established in 2009 as an electric motor R&D company, has designed, developed, and tested multiple electric motor architectures, topologies, and technologies from superconducting motors to induction motors to axial flux, radial flux, and more, on its mission to lead the commercial aerospace and defense industries by providing high performance, reliable and environmentally friendly electric propulsion solutions (EPU’s). In 2017, the company designed and built its first aerospace prototype motor, the magni5. By leveraging and further developing its technology features, magniX has flight?proven the successor to the magni5, a 560kW propulsion system known as the magni500. The magni500 was designed, built, and tested to be aerospac | ||||
| 14:40 | 15:10 | 1.2.2 |
HYBRID ELECTRIC PROPULSION DEVELOPMENT FOR COMMERCIAL AVIATION C. Andrews¹, A. Simpson¹; ¹GE, United States Presenter: Christine Andrews, GE HYBRID ELECTRIC PROPULSION DEVELOPMENT FOR COMMERCIAL AVIATION | ||||
| 15:10 | 15:40 | 1.2.3 |
TOWARD A COMMUNITY NOISE ASSESSMENT OF SINGLE-AISLE AIRCRAFT WITH HYBRID-ELECTRIC PROPULSION (invited) M.R. Khorrami, United States The speaker will present technical progress toward a high-fidelity assessment of the community noise of a single aisle aircraft seat class aircraft with hybrid electric propulsion. | ||||
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| 14:10 | 14:40 | 2.2.1 |
DESIGN OF AN ADVANCED EMPENNAGE AND REAR FUSELAGE CONCEPT FOR A COMMERCIAL AIRCRAFT R.C. Llamas-Sandin¹, C.D. Handal-Rivera¹; ¹Airbus OSL, Spain Design synthesis and aero-structural optimization of an innovative efficient rear fuselage and empennage concept for a mid-sized commercial aircraft, including experimental validation, numerical studies and overall aircraft integration evaluation. The focus is on improving fuel burn efficiency and manufacturing complexity and evidences are given on the merits of the novel configuration. | ||||
| 14:40 | 15:10 | 2.2.2 |
SYSTEMS ARCHITECTING: A PRACTICAL EXAMPLE OF DESIGN SPACE MODELING AND SAFETY-BASED FILTERING WITHIN THE AGILE 4.0 PROJECT A.K. Jeyaraj¹, J.H. Bussemaker², S. Liscouët-Hanke¹, L. Boggero²; ¹Concordia University, Canada ;²DLR, Germany This paper introduces an approach of filtering a large design space of system architectures using safety heuristics that will enable the exploration of large design spaces consisting of novel aircraft system architectures. These architectures are modelled using a function based modelling approach that can generate large sets of candidate architectures. The system architecting process is made effective | ||||
| 15:10 | 15:40 | 2.2.3 |
AN EFFICIENT SOLUTION FOR AERODYNAMIC SHAPE OPTIMIZATION WITHIN THE MID-RANGE APPROXIMATION FRAMEWORK Y. Zhang¹, F. Qu¹, J.Q. Bai¹, D.S. Jia², E.K. Bontoft², V.V. Toropov²; ¹Northwestern Polytechnical University, China ;²Queen Mary University of London, United Kingdom This paper presented an efficient solution for aerodynamic shape optimization based on the latest developments in the Mid-range Approximation Method (MAM) within a trust-region optimization framework. The proposed method can achieve the design goal successfully for high-fidelity large-scale aerodynamic shape optimization problems with enhanced robustness and efficient performance. | ||||
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| 14:10 | 14:40 | 3.2.1 |
UNMANNED AERIAL VEHICLE – HUMAN PERFORMANCE EVALUTION UNDER CRITICAL OPERATIONAL SCENARIO E.T. da Silva¹, A.G.P. Sarmento¹, T.R. de Paula¹, A.S. Oliveira¹, J. Possamai¹, H.C. Marques¹, M.M. Cardoso¹, E. Villani¹; ¹Aeronautics Institute of Technology, Brazil Presenter: Emilia Villani , Aeronautics Institute of Technology The design of UAS has a paradigm since they are not “flown”, they are commanded by a pilot/operator on a Ground Control Station . At the core of this paradigm there are questions related with Human Machine Interface (HMI). This manuscript discusses the matter and proposes the construction of an HMI prototype that emulate the UAS operation aiming workload and situational awareness optimization | ||||
| 14:40 | 15:10 | 3.2.2 |
RESEARCH ON THE OVERALL DESIGN OF A HIGH-SPEED MORPHING UAV C. Ding, School of Aeronautic Science and Engineering,Beihang University, China; T.-L. Ma, Institute of Unmanned System, Beihang University, China; J.-C. Fu, School of Transportation ScienceandEngineering,BeihangUniversity, China; X.-S. Wang, School of Aeronautic Science and Engineering, Beihang University, China This paper takes the air-launch high-speed aircraft with the morphing wing as the research object, carries out the overall design research according to the proposed task requirements, forms the calculation method of the overall parameters of the variant high-speed aircraft, and proposes a variable outer wing aerodynamic layout form. | ||||
| 15:10 | 15:40 | 3.2.3 |
COOPERATIVE THREAT ENGAGEMENT WITH HETEROGENEOUS DRONE SWARMS L. Giacomossi¹, J.A. Ricardo Jr¹, J.F.B. Brancalion, EMBRAER, Brazil; M.R.O.A. Maximo¹, D.A. Santos¹; ¹ITA, Brazil This research combines modern AI decision-making approaches and state-of-the-art control techniques for a swarm of LW MAVs to coordinate efficient defense actions in a cooperative, autonomous, and decentralized manner. We apply these concepts in a defense scenario, modeled to test and optimize the loyal wingman concept, which we consider an interesting testbed for cooperative decision-making as well as the low-level control techniques. | ||||
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| 14:10 | 14:40 | 4.2.1 |
VALIDATION STUDY OF BLUNTED AND SHARP CONES AT HYPERSONIC SPEED E.K.T. Carias¹, S.A. Prince¹; ¹Cranfield University, United Kingdom The circular cone shaped nose had been the prime interest of study for high speed aerodynamics for quite some time. It is a fundamental shape at which most general pointed bodies are derived from. Besides from its simplicity, the flow field it produces can be easily studied since the flow is conical in nature. This study aims on invistagating blunted and sharp cones in the hypersonic regime. | ||||
| 14:40 | 15:10 | 4.2.2 |
AERODATABASE DEVELOPMENT AND INTEGRATION OF SUPERSONIC/HYPERSONIC CRUISER VEHICLES IN MORE&LESS PROJECT P. Roncioni¹, M. Marini¹, R. Fusaro², N. Viola²; ¹CIRA, Italy ;²POLITO, Italy The European Commission is funding the H2020 MORE&LESS Project (MDO and REgulations for Low boom and Environmentally Sustainable Supersonic aviation), aiming at developing a wide design platform for future supersonic aviation on the base of global environmental regulations. A multi-disciplinary optimization framework to assess the holistic impact of supersonic aviation onto environment is foreseen that can incorporate high-fidelity modelling activities and test campaigns. At first, different disciplines will tackle separate design topics through modelling and tests and then the environmental impact of these aircraft concepts will be evaluated through the holistic framework. To further extend the validity of theories and models, the entire spectrum of supersonic speed regime ranging from Mach 2 to Mach 5 is considered. Moreover, the analysis is not only restricted to aircraft using traditional hydrocarbon fuels, but it moves beyond, addressing aircraft concepts exploiting alternative fuels, such as biofuels and cryogenic fuels. The idea of considering more case-studies with different configurations, performance and fuels fosters the enhancement of the flexibility of the tools, which, starting from the case-studies, are developed based on modelling activities and test campaigns as products that can be flexible enough to be applied to several future vehicle concepts. In order to achieve this aim one important activity is the development of the aerodynamic database. This paper deals with the development and integration of increasing-fidelity aerodynamic modelling approaches in the conceptual design of hypersonic cruisers. This methodology foresees the development of aerodynamic aerodatabases by means of incremental steps starting from simplified methods (panels methods and/or low fidelity CFD simulations) up to very reliable data based on high fidelity CFD simulations and experimental measurements with associated confidence levels. This allows us to follow th | ||||
| 15:10 | 15:40 | 4.2.3 |
TURBULENCE MODELLING STUDIES OF SHOCK-WAVE/BOUNDARY-LAYER INTERACTIONS ON HIFIRE-1 AXISYMMETRIC CONE CYLINDER FLARE IN HYPERSONIC FLOWS R.O. Bura, Republic of Indonesia Defense University, Indonesia; F.A. Maulana, Indonesia In this 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 at Mach 7.16 were analyzed.Validation and analysis of turbulence modeling were compared to the experimental result for HIFiRE-1 ground test studies. | ||||
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| 14:10 | 14:40 | 5.2.1 |
THE GROUP OF RESPONSABLES \"FLIGHT MECHANICS, SYSTEMS AND INTEGRATION (GOR FM)\": AN OVERVIEW OF ACTIVITIES AND SUCCESS STORIES B. Korn, DLR, Germany; M. Hagström, FOI, Sweden The GoR-FM is responsible for all research and development subjects starting from the air vehicles and their flight mechanics until their integration into Air Traffic. It covers embedded sensors, actuators, systems and information technology, cockpits, ground control and human integration issues, with reference to automation for both inhabited and uninhabited aircraft. | ||||
| 14:40 | 15:10 | 5.2.2 |
THE GROUP OF RESPONSABLES \"ROTORCRAFT (RC-GOR)\": AN OVERVIEW OF ACTIVITIES AND SUCCESS STORIES A. Visingardi, CIRA, Italy; R. Heger, Airbus Helicopters, Germany; A. Le Pape, ONERA, France; R. Markiewicz, DSTL, United Kingdom; B. Ohlenforst, NLR, Netherlands; K. Pahlke, DLR, Germany; M. White, University of Liverpool, United Kingdom This paper illustrates the main objectives of the GARTEUR Group of Responsabes "Rotorcraft", formerly Helicopters GoR, since its creation in 1984. | ||||
| 15:10 | 15:40 | 5.2.3 |
AVIATION SECURITY CONCERNS A. Vozella, Italian Aerospace Research Centre, Italy; P. Bieber, ONERA, France Safety and Security represent two challenges (concerns) for aviation which, though have historically followed two different paths and dynamics, are intrinsically interdependent and nowadays there is a common understanding about the need to harmonize them by design. This paper will give an overview of the areas which are of greater interest for future research activities, starting from analyzing for safety and security for aviation: the basic concepts, the traditional approaches, the best practices, the lesson learnt and the state of the art for both concerns. | ||||
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| 14:10 | 14:40 | 6.2.1 |
STRAKE SECTION IMPACT ON HYBRID-DELTA-WING AERODYNAMICS D. Sedlacek¹, C. Breitamter¹; ¹Technical University of Munich, Germany Highly-agility aircraft often consist of a nonslender main wing and a slender strake.Thus, two vortices form and interact with each other. In this study, the influence of the strake-length of a triple-delta and a double-delta wing on the vortex systems is analysed. For this investigation, force and moment measurements, particle image velocimetry and oil-flow visualization were conducted. | ||||
| 14:40 | 15:10 | 6.2.2 |
VOLUMETRIC VELOCITY MEASUREMENTS OF A HELICAL VORTEX PAIR D. Schröder¹, T. Leweke, CNRS, Aix-Marseille Université, Centrale Marseille, France; R. Hörnschemeyer¹, E. Stumpf¹; ¹Institute of Aerospace Systems, RWTH Aachen University, Germany The presented work provides valuable insights from a novel experimental study convcerning mutual interactions and instability phenomena of a closely-spaced helical vortex pair. The superordinate goal of the proposed tip design is to minimize the negative effects of concentrated tip vortices in rotor applications, such as BVI for helicopters and unwanted wake characteristics for wind turbines. | ||||
| 15:10 | 15:40 | 6.2.3 |
NUMERICAL AND EXPERIMENTAL INVESTIGATIONS ON THE DLR-F23 COMBAT AIRCRAFT WIND TUNNEL MODEL J. Zastrow¹, F. Oberdieck¹, U. Henne¹, C. Klein¹; ¹DLR - German Aerospace Center, Germany The combat aircraft wind tunnel model DLR-F23 produces a multi-vortex system that experiences vortex-shock-, vortex-vortex-interactions and vortex breakdown. The flow topologies change throughout the Mach-number and angle of attack regime of the conducted experiments. The unsteadiness of the flow was investigated on, in order to increase the understanding and capabilities in numerical prediction. | ||||
| Reserve Paper (Interactive) | 6.2.R |
INFLUENCE OF TIP DIHEDRAL ON ROTOR AERODYNAMIC PERFORMANCE AND TIP VOTEX M.-H. Kang¹, X. Zhao¹, R. Yao¹, H.-Y. Li¹; ¹Norhwestern Polytechnical University, China Presenter: Hongyan Li, Norhwestern Polytechnical University | |||||
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| 14:10 | 14:40 | 7.2.1 |
APPLICATION OF THE VIRTUAL CRACK CLOSURE TECHNIQUE FOR CRACKS IN BUILT-UP PANELS W.R.P. Mendonca¹, M.R.B. Rodrigues¹; ¹Embraer S.A., Brazil Presenter: Willy Mendonca, Embraer S.A. The objective of this paper is to show the application of Virtual Crack Closure Technique (VCCT) in typical fuselage and wing built-up panels, showing the relevance of contribution of different load components on crack opening. In particular, the study will show through analysis and validation with experiments the influence on the crack propagation results generated by the local bending induced by the failure of a reinforcement. The local bending is even more relevant for thick panels, and this aspect will be addressed in this paper. The use of robust methodologies in structural analysis improves the aircraft structural integrity. | ||||
| 14:40 | 15:10 | 7.2.2 |
NUMERICAL AND EXPERIMENTAL STRUCTURAL CHARACTERIZATION OF COMPOSITE ADVANCED JOINT FOR ULTRA LIGHT AEROSPACE PLATFORMS A. Polla, Politecnico di Torino; Royal Melbourne Institute of Technology, Italy; G. Frulla¹, E. Cestino¹, R. Das², P. Marzocca²; ¹Politecnico di Torino, Italy ;²Royal Melbourne Institute of Technology, Australia Presenter: Enrico Cestino, Politecnico di Torino The proposed research activity has evaluated the elastic and explicit failure behaviour of composite bolted joints subjected to quasi-static and dynamic loading conditions. A High fidelity shell-cohesive progressive damage failure analysis (PDFA) method has been applied to numerically reconstruct the physical performances of selected samples based on two different mechanical configurations. | ||||
| 15:10 | 15:40 | 7.2.3 |
A DAMAGE RECOGNITION METHOD OF COMPOSITE STRUCTURES USING ARTIFICIAL DEFECTIONS Y. Yang¹, S. Lyu¹; ¹Aircraft Strength Research Institute, China Deep learning can help to improve the guided-wave-based damage detection of composite structures, but it needs a large number of damage samples. Based on a great amount of simulated damage samples and a small number of real ones, a domain adaptive damage identification model is designed to realize the migration from simulated damage detection to real damage detection. Firstly, guided-wave signals of faked damage are collected extensively in the form of mass attachment on to the structure surface, and corresponding deep learning model based on convolutional-timing-sequential hybrid neural network is designed to achieve a high accuracy of damage detection. Secondly, a certain amount of guided-wave signals of real damage are collected, and a domain adaptive module is adopted by the model, which approximates the data distribution law of simulated damage and real dam-age in the feature space. With this framework, the model could detect the real damage without the labelling process in advance, and the experimental results demonstrate the detection accuracy of 85.7%, which is ahead of other traditional deep learning models. | ||||
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| 14:10 | 14:40 | 8.2.1 |
WIND TUNNEL EXPERIMENT WITH AN EPP-WING TO INVESTIGATE AEROELASTIC EFFECTS OF NONLINEAR ELASTIC STIFFNESSES K. Bramsiepe¹, M. Braune¹, W. Krüger¹, L. Tichy¹; ¹DLR - Institute of Aeroelasticity, Germany The idea of this concept is to modify the linear properties of wing structures to influence the lift distribution for load alleviation. This work demonstrates the nonlinear elastic characteristics of a wing composed of foam material (EPP) in a wind tunnel test campaign. The degressive nonlinear elastic stiffness reduces the root bending moment of the wing. | ||||
| 14:40 | 15:10 | 8.2.2 |
DESIGN OF AN INNOVATIVE WING TIP FOR AEROELASTIC CONTROL: FROM SCRATCH TO FLIGHT TEST F. Toffol¹, F. Fonte, Leonardo Helicopters, Italy; S. Ricci¹; ¹Politecnico di Milano, Italy The work illustrates the design and test process that led to the manufacturing of an innovative wing tip device in the framework of AIRGREEN2, a Clean Sky 2 platform. The design involved several disciplines (structure, aerodynamics, actuation). Intermediate wind tunnel models and ground demonstrator provided experimental evidence of the utility of the concept. The item will be flight tested in '23 | ||||
| 15:10 | 15:40 | 8.2.3 |
EVALUATION ENVIRONMENT FOR CASCADED AND PARTLY DECENTRALIZED MULTI-RATE LOAD ALLEVIATION CONTROLLERS C. Wallace¹, S. Schulz¹, N. Fezans¹, T. Kier¹, G. Weber, Liebherr-Aerospace, Germany; ¹German Aerospace Center (DLR), Germany A development environment to evaluate a novel control approach for load alleviation is presented. The control structure includes cascaded and partly distributed gust load alleviation functions. The implemented control loops are processed by the central flight control computer as well as by decentralized and fast Remote Electronic Units which are located close to the control surfaces. | ||||
| Reserve Paper | 8.2.R |
SOME EXPERIMENTAL RESULTS ON DYNAMIC AEROELASTICITY OF PLATES AND SHELLS IN SUBSONIC AND SUPERSONIC FLOW. J. Lübker, Germany | |||||
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| 14:10 | 14:40 | 9.2.1 |
ASSESSMENT OF A SERIAL COOLING CONCEPT FOR HTPEM FUEL CELL SYSTEMS FOR AVIATION APPLICATIONS A. Link¹, J. Ludowicy¹, M. Staggat¹; ¹German Aerospace Center (DLR), Germany A serial cooling concept for HTPEMFCs is proposed to reduce system weight for aviation applications by trading liquid coolant mass against fuel cell efficiency and mass. The presented studies across different system parameters of the fuel cell and thermal management system indicate that the proposed concept offers significant weight savings with limited drawbacks in system efficiency. | ||||
| 14:40 | 15:10 | 9.2.2 |
DEMONSTRATION FLIGHTS OF HYBRID ELECTRIC AIRCRAFT P. Bohnert, United Kingdom; S.X. Ying, United States; M. Selier, Netherlands Due to the need of carbon reductions in the aviation sector, Ampaire, an electric aircraft company, demonstrated regional point-to-point flights with a retrofitted hybrid-electric Cessna 337, showing the ability of hybrid-electric aircraft to operate real-life routes in a distributed aviation system and reduce direct emissions by up to 38%. | ||||
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| 14:10 | 14:40 | 10.2.1 |
TRANSONIC NACELLE DESIGN FOR FUTURE MEDIUM RANGE AERO-ENGINES B.D.J. Schreiner¹, D.G. MacManus¹, F. Tejero¹, F. Sanchez-Moreno¹, C. Sheaf, Rolls Royce, United Kingdom; ¹Cranfield University, United Kingdom Presenter: Fernando Tejero, Cranfield University Aerodynamic design and optimisation of non-axisymmetric compact nacelles for medium range applications using CFD-in-the-loop to provide reduced cruise drag relative to conventional architectures. Evaluation of down selected geometries at on- and off-design conditions. Assessment of robustness and sensitivity to operating conditions using steady and unsteady 3D CFD. | ||||
| 14:40 | 15:10 | 10.2.2 |
STUDY OF EFFECTS ON THE WING\'S AERODYNAMIC CHARACTERISTICS DUE TO DISTRIBUTED PROPULSION OVER WINGSPAN G.J. Resende¹, V. Malatesta¹, M.C. Savio², B.M. Castro²; ¹ITA - Aeronautics Institute of Technology, Brazil ;²EMBRAER, Brazil Distributed propulsion (DP) is not a new concept, but recent advances in electric motors and batteries, along with the need for more environmentally friendly products, brought this concept back to the spotlight. This paper addresses two types of DP: wingtip-mounted propellers and distributed propellers along the wingspan. The benchmark of the analysis is the NASA's X-57 "Maxwell" demonstrator. | ||||
| 15:10 | 15:40 | 10.2.3 |
A NOVEL EMBEDDED INLET BASED ON THE INTEGRATED DESIGN CONCEPT OF FUSELAGE AND INLET P. Yan, Shenyang Aircraft Design and Research Institute, China; F. Liu, Shenyang Aircraft Design and Research Institute, Chinese Aeronau, China To improve the performance of submerged inlet, a novel submerged inlet is designed based on the integration design concept of fuselage and inlet. The performance is obtained by numerical simulation and the results indicate that changing the shape curvature of the fuselage can increase the performance of the inlet. | ||||
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| 14:10 | 14:40 | 11.2.1 |
LANDING SIMULATION OF A HIGH-ALTITUDE PLATFORM WITH SKID-TYPE LANDING GEAR – FLIGHT PROCEDURE, CONTROLLER, AND LOADS Y.J. Hasan¹, N. Fezans¹, A. Voß, DLR, Institute of Aeroelasticity, Germany; ¹DLR, Institute of Flight Systems, Germany This paper addresses three issues associated with the landing of high-altitude platforms: first, it presents a manual landing procedure that has a potential of reducing the risk of the landing for such aircraft, second, it describes the positioning process of skids that are used as landing gear and third, it includes the resulting landing loads in the aeroelastic design. | ||||
| 14:40 | 15:10 | 11.2.2 |
ALTITUDE ESTIMATION BY WIDE-FIELD-INTEGRATION OF OPTIC FLOW H. Hiraiwa¹, M. Bando¹, S. Hokamoto¹; ¹Kyushu university, Japan This paper presents an altitude estimation method by using Wide-Field-Integration (WFI) of optic flow. WFI of optic flow is a method for fast estimation of motion variables. The proposed method can additionally estimate the altitude of a flying vehicle by using two patterns of optic flow acquired by two onboard cameras. The proposed method is useful for autonomous flight in GPS denied environment. | ||||
| 15:10 | 15:40 | 11.2.3 |
FIXED-WING UAVS CONTROL WITH MODEL UNCERTAINTIES M.R. Kartal¹, D. Ignatyev¹, A. Zolotas¹; ¹Cranfield University, United Kingdom This paper proposes a comparison of four different control algorithms (LQR, LQRDO, IBS, and IKBS) against model uncertainties of fixed-wing UAVs. Since model uncertainty is a quite frequent problem, this research will be beneficial for every collaborator of UAVs platforms or even the robotics field. | ||||
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| 14:10 | 14:40 | 12.2.1 |
MACHINE LEARNING METHODS ENSURING BOTH PERFORMANCE AND INTERPRETABILITY OF ESTIMATING AIRCRAFT ARRIVAL TIMES N. Morikawa, Faculty of Aerospace Engineering, The University of Tokyo, Japan; E. Itoh, Air Traffic Management Department, Electronic Navigation Researc, Japan To further improve efficiency of runway management, we applied machine learning models to estimate aircraft arrival times using real data in Japan. Various indicators such as SHAP values were introduced to ensure not only the models’ performance, but also interpretability for stakeholders involved in the operation. | ||||
| 14:40 | 15:10 | 12.2.2 |
APPLYING MACHINE LEARNING TO TAXI-TIME PREDICTION ATTOKYO INTERNATIONAL AIRPORT F. Kato¹, E. Itoh¹; ¹The University of Tokyo, Japan This study proposes a methodology to apply Machine Learning (ML) methods as possible alternatives to accurately predict taxi-time of departure aircraft from Tokyo International Airport. The experiment demonstrated that random forest regression was able to predict the taxi time with the mean error of about 80 seconds, which is much more accurate than the result of a previous study. | ||||
| 15:10 | 15:40 | 12.2.3 |
AN AUCTION-BASED MECHANISM FOR A PRIVACY-PRESERVING MARKETPLACE FOR ATFM SLOTS C.G. Schuetz, Johannes Kepler University Linz, Austria; S. Ruiz, EUROCONTROL Innovation Hub, France; E. Gringinger¹, C. Fabianek¹, T. Loruenser, AIT Austrian Institute of Technology, Austria; ¹Frequentis AG, Austria In case of reduced capacity of the European air traffic network, the Network Manager initiates a regulation, which typically causes flight delay. The SlotMachine system will allow airspace users to submit preferences regarding the departure times of individual flights, which are then considered during a privacy-preserving optimization run that aims to find an optimal flight list. | ||||
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| 14:10 | 14:40 | 13.2.1 |
LOCALIZATION OF INTERROGATORS WITH A 1030/1090 MHZ SPECTRUM MONITORING SYSTEM L. Sarperi¹, M. Jäger¹, P. Müller¹, M. Felux¹; ¹ZHAW, Switzerland Presenter: Michael Jäger, ZHAW School of Engineering We present a new method for localizing rotating, directional interrogators based on aircraft interrogator replies, which compared to previous work only requires the reception of aircraft transponders using one receiver on the ground. The data used was obtained with a proof-of-concept implementation of a distributed 1030/1090 MHz Spectrum Monitoring System based on Software-Defined Radios (SDRs). | ||||
| 14:40 | 15:10 | 13.2.2 |
A FEDERATED LEARNING BASED SECURITY FOR CONTROLLER-PILOT DATA LINK COMMUNICATION S. Khan¹, G. Singh Gaba¹, A. Gurtov¹; ¹Linköping University, Sweden Presenter: Suleman Khan, Linköping University As the CPDLC protocol enables communications between air-ground networks, it opens an immense attack vector between the controller and pilot. This paper proposes a federated learning (FL) base security model for communication in aviation networks. Note that the focus of our scheme is to secure CPDLC from various cyber-attacks. | ||||
| 15:10 | 15:40 | 13.2.3 |
TECHNICAL CONCEPTS FOR INSPECTING UAVS FOR DAMAGE J. Eltgen¹, T. Schüppstuhl¹; ¹Hamburg University of Technology, Germany In this work, we analyzed motion and sensor concepts to investigate highly automated pre-flight check methods for vehicles in unmanned urban air mobility. This can be done in two steps. First a holistic scan of the drone with a camera with two ring lights for the illumination. Then a more specific inspection of the parts where failures detected by the camera with white light interferometry. | ||||
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| 14:10 | 14:40 | 14.2.1 |
DATA-DRIVEN APPROACH TO OPTIMAL AIRCRAFT MAINTENANCE O.C. Okoro¹, M. Zaliskyi¹, D. Serhii , National Aviation University , Ukraine; S. Qudus, Tamara Niger Aviation, Niger; ¹National Aviation University, Ukraine The operational phase of an aircraft life cycle generates data which can be used for developing models for cost-effective and efficient aircraft maintenance. The proposed models were developed based on probability theory, reliability theory, and segmented regression. An advantage of these models is their simplicity, making it easy to use by personnel for planning aircraft maintenance activities. | ||||
| 14:40 | 15:10 | 14.2.2 |
OPERABILITY PROJECTION OF MAJOR AIRCRAFT COMPONENTS DURING EARLY AIRCRAFT DESIGN S.S. Manikar, Airbus/ ISAE-SUPAERO, France; J. Jezegou¹, P. de Saqui-Sannes¹, P. Asseman, Airbus, France; E. Benard¹; ¹ISAE-SUPAERO, France Airline profitability depends on many factors; one major factor being the high availability of the aircraft at acceptable cost, which we call ‘operability’. Aircraft operability is one of the most critical criteria for trade-off in early design. This paper proposes a method using Bayesian networks for enabling design trade-off with a high-level definition of the aircraft. | ||||
| 15:10 | 15:40 | 14.2.3 |
DIGITAL TWIN CONCEPT FOR AIRCRAFT COMPONENTS H. Meyer¹, A.-K. Koschlik¹, F. Raddatz¹; ¹German Aerospace Center, Germany Digital twins are one way to develop future intelligent systems. Aviation brings with it very special circumstances, since the majority of the components do not remain in the first aircraft over the life cycle. Many of them are subjected to a maintenance process and then reassembled to another aircraft. In this paper, a digital twin concept is developed for these components. | ||||
| Reserve Paper (Interactive) | 14.2.R |
ESTIMATION OF ROTOR IMBALANCE AND MODEL DISCREPANCY USING A BAYESIAN APPROACH R. Rameshbabu¹, D. Rajaram¹, O.J.P. Fischer¹, D.N. Mavris¹; ¹Georgia Institute of Technology, United States | |||||
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| 16:00 | 16:30 | 1.3.1 |
THE SWEDISH AIR FORCE INTO THE FUTURE – AIMING FOR A HIGHER GROUND AND A SHARPER EDGE (invited) T. Petersson, Sweden The presentation will outline the future plans, going into space, the benefit of a national industry and the urge for research and technology in order to achieve tactical superiority. | ||||
| 16:30 | 17:00 | 1.3.2 |
FUTURE COMBAT AIRCRAFT SYSTEM THE COMPLEXITY OF THE SKILLS EQUATION (invited) S. Hopkins, BAE Systems, United Kingdom; I. Noakes, BAe Systems, United Kingdom Change in the workplace has become part of our daily lives, effecting both what we do and more importantly how we do it. This paper identifies some of the key people challenges we face in the Combat Air sector and how this is impacting the future skills we need to deliver complex next-generation programmes. | ||||
| 17:00 | 17:30 | 1.3.3 |
FUTURE COMBAT AIR SYSTEMS: REQUIREMENTS AND TECHNOLOGIES (invited) G. Girard, France To achieve Air Superiority, Future Combat Air Systems shall integrate cutting edge technologies into several platforms that seamlessly interact to provide the capabilities required by the nations. Dassault views on the main drivers shaping such a system-of-system will be presented. | ||||
| 17:30 | 18:00 | 1.3.4 |
POWER/THERMAL 2030 VISION - AIR PLATFORM ELECTRIFICATION (invited) J.G. Nairus, United States AIR POWER PLANS FOR 2030 | ||||
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| 16:00 | 16:30 | 2.3.1 |
VALIDATION OF SCALED FLIGHT TESTING P. Schmollgruber¹, C. Toussaint¹, A. Lepage¹, F. Bremmers², H. Jentink², L. Timmermans², N. Genito³, A. Rispoli³, D. Meissner, 5Airbus Operations GmbH, Germany; D. Kierbel, Airbus S.A.S., France; ¹ONERA, France ;²NLR, Netherlands ;³CIRA, Italy In the frame of the European programme Clean Sky 2, a specific activity is dedicated to the validation of scaled flight testing as a viable test mean to derisk new technologies or configurations. The work is divided into a theoretical stream to investigate similarity and an experimental one relying on flights with a demonstrator similar to a known reference aircraft. | ||||
| 16:30 | 17:00 | 2.3.2 |
TECHNOLOGY INTEGRATION FOR FUTURE AIRCRAFT CONFIGURATIONS D. Reckzeh, Airbus, Germany The recent ambition towards massive emission reduction on future aircraft triggers a range of technical disruptions. Advanced simulation chains and targeted verification approaches are required to demonstrate viability and allow a synergetic integration on overall product level. | ||||
| 17:00 | 17:30 | 2.3.3 |
MARKET ANALYSIS, TLARS SELECTION AND PRELIMINARY DESIGN INVESTIGATIONS FOR A REGIONAL HYBRID-ELECTRIC AIRCRAFT V. Marciello¹, M. Ruocco, SmartUp Engineering s.r.l., Italy; F. Nicolosi¹, M. Di Stasio¹; ¹University of Naples Federico II, Italy This research work is focused on the description of the workflow implemented to define the Top-Level Aircraft Requirements (TLAR) for a non-conventional 50 pax regional class hybrid/electric aircraft and on the identification of key specifications in terms of on-board energy storage, shaft power level and weight. The work is framed in the context of the CS2 GENESIS Project. | ||||
| 17:30 | 18:00 | 2.3.4 |
UNMANNED AEW/ISR PLATFORM CONCEPTUAL DESIGN AND TECHNOLOGY ASSESSMENT C. Jouannet¹, K. Amadori¹, M. Emeneth, PACE America Inc., United States; A. Papageorgiou, Linköpings University, Sweden; ¹Saab Aeronautics, Sweden This paper presents a case study of a study of an unmanned AEW/ISR platform, where current methods under development at Saab Aeronautics to provide better insight to technology impact and prioritization with respect to a future aircraft programs in aircraft conceptual design . The goal of this work was to test the capabilities and find the boundaries of a new tool for modelling and simulation recently introduced at the Saab. To this end, a typical technology assessment study was crafted as an application case, in which the impact on mission and vehicle performance metrics is assessed when different on-board system architectures and technology clusters are applied. The study was carried out in accordance to the methodology developed at Saab for technology assessment which has been already documented in previous publications | ||||
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| 16:00 | 16:30 | 3.3.1 |
A COMMON FRAMEWORK FOR THE DESIGN OPTIMIZATION OF FIXED-WING, MULTICOPTER AND VTOL UAV CONFIGURATIONS F. Pollet¹, S. Delbecq¹, M. Budinger, ICA, Université de Toulouse, ISAE-SUPAERO, MINES ALBI, UPS, INSA, France; J.-M. Moschetta¹, J. Liscouët, Concordia University, Canada; ¹ISAE-SUPAERO, France This paper focuses on the multidisciplinary design of multicopter, fixed-wing, and quadplane drones. Lightweight models for drone sizing are proposed and integrated with an optimal design approach. The results are validated with commercially available drones, and a comparative study allows to determine the best configuration to perform a mission. | ||||
| 16:30 | 17:00 | 3.3.2 |
DESIGN OF A HALE UAV FOR ATMOSPHERIC IMAGING V. Nan Fernandez-Ayala¹, L. Vimláti¹, A. Matoses Gimenez¹, H. Delmotte¹, M. Ivchenko¹, R. Mariani¹; ¹KTH Royal Institute of Technology, Sweden An electric, fixed-wing HALE UAV is being developed to aid research of high altitude atmospheric phenomena, by carrying imaging equipment above the cloud coverage. This work describes the conceptual design phase of the aircraft, as well as the initial manufacturing and flight testing process of a half-scale prototype. | ||||
| 17:00 | 17:30 | 3.3.3 |
ENHANCING UAS DESIGN PROCESS FOR SPECIFIC CATEGORY OPERATIONS USING SORA R. Kalra¹, P. Flores-Peña, Drone Hopper S.L., Spain; A. Sanchez-Carmona¹, C. Cuerno-Rejado¹; ¹Universidad Politécnica de Madrid, Spain This paper aims to introduce a novel UAS design process from the manufacturer’s perspective by using specific aspects of the SORA to enhance the design process of the UAS by introducing the necessary design and analysis modifications in both the hardware and software of the UAS, as identified by SORA into the preliminary design phases itself. The SORA as originally intended to be a risk assessment procedure to be performed by the operator of the UAS can prove to be an important and useful tool when carefully integrated into the design process by the UAS designer or the manufacturer. This novel approach proposes to use the recommendations and requirements identified at various stages of SORA as a guiding tool in the initial phases of the UAS design process, thus eliminating the need for major design changes at later stages. | ||||
| 17:30 | 18:00 | 3.3.4 |
OPENVSP BASED AERODYNAMIC DESIGN OPTIMIZATION TOOL BUILDING METHOD AND ITS APPLICATION TO TAILLESS UAV J. Kim¹, T. Tsuchiya¹; ¹The University of Tokyo, Japan This paper presents an OpenVSP and Optimization algorithm integrated aerodynamic design optimization tool for aerial vehicles. After an overview of OpenVSP is given, user-friendly integration methods are described. The results of applying the proposed tool to a tailless UAV design are also presented. | ||||
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| 16:00 | 16:30 | 4.3.1 |
A MULTIFIDELITY MULTIDISCIPLINARY APPROACH TO UNCONVENTIONAL AIRCRAFT DEVELOPMENT AND ASSESSMENT WITH APPLICATION TO THE STRUT-BRACED-WING AND HYBRID-WING-BODY CONFIGURATIONS D.W. Zingg¹, T. Chau¹, A.L. Gray¹, T.A. Reist¹; ¹University of Toronto Institute for Aerospace Studies, Canada We present an approach to the investigation and assessment of unconventional aircraft configurations based on multifidelity multidisciplinary optimization, in particular to the problem formulation, including the choice of disciplines, the associated level of fidelity of the analysis, and the operating requirements. Applications to the strut-braced wing and hybrid wing-body aircraft are presented. | ||||
| 16:30 | 17:00 | 4.3.2 |
OVERVIEW OF AERODYNAMIC DESIGN ACTIVITIES PERFORMED AT ONERA TO REDUCE AVIATION\'S CLIMATE IMPACT M. Méheut¹, G. Arnoult¹, O. Atinault¹, Q. Bennehard¹, C. Francois¹; ¹ONERA, France This paper aims at summarizing the most relevant aerodynamic design activities performed at ONERA on the most promising innovative aircraft and engine integration concepts to reduce Aviation's climate impact. Within different projects of the European Programme Clean Sky 2, ONERA decided to explore two specific aircraft configurations for a typical Small Medium Range (SMR) mission: • Aircraft concepts : o The High Aspect Ratio Strut-Braced Wing (HAR SBW) concept in the U-HARWARD project; o The Blended Wing Body (BWB) concept in the NACOR project) and two innovative engine integration solutions. • Engine integration technologies : o The Boundary Layer Ingestion (BLI) technology coupled with the BWB concept in the NACOR project; o The Distributed Propulsion technology in the frame of the ADEC project. | ||||
| 17:00 | 17:30 | 4.3.3 |
MDAO OF A TRANSONIC TRUSS-BRACED WING VISION VEHICLE D.S. Lazzara¹, N.A. Harrison¹; ¹Boeing, United States MDAO of SUGAR TTBW vision vehicle. | ||||
| 17:30 | 18:00 | 4.3.4 |
APPLICATION OF AERODYNAMIC AND AERO-STRUCTURAL OPTIMIZATION FOR ENERGY EFFICIENT AIRCRAFT (invited) O. Brodersen, Germany; T. Wunderlich, Germany; M. Abu-Zurayk, Germany; S. Görtz, Germany; C. Ilic, Germany; L. Reimer, Germany APPLICATION OF AERODYNAMICS AND AERO-STRUCTURAL OPTIMIZATION FÖR ENERGY EFFICIENT AIRCRAFT | ||||
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| 16:00 | 16:30 | 5.3.1 |
MODEL-BASED PERFORMANCE EVALUATION OF AIRCRAFT ACTUATOR TECHNOLOGIES F. Larsson¹, C. Reichenwallner², A. Dell'Amico¹, P. Krus²; ¹Saab AB, Sweden ;²Linköping University, Sweden This paper intends to demonstrate some of the challenges with selection of technology for aircraft actuation system and ease the process through the proposition of a model-based evaluation methodology. This methodology considers comparison of power consumption and cooling needs of electrified- and hydraulic actuators, and is used to study the suitability of the technologies for a fighter jet. | ||||
| 16:30 | 17:00 | 5.3.2 |
A COMPARATIVE ANALYSIS OF INNOVATIVE DIGITAL HYDRAULIC ACTUATORS FOR PRIMARY FLIGHT CONTROL R. Simões Lopes Junior¹, D. Oliveira e Silva¹, M.P. Nostrani¹, A. Dell´Amico, Saab AB, Sweden; P. Krus, Linköping University, Sweden; V.J. De Negri¹; ¹Federal University of Santa Catarina, Brazil This paper presents a fast and flexible method for evaluating new actuators for primary flight control, using the Aero-Data Model In A Research Environment - Admire, demonstrating the modeling integration with three innovative and highly-efficient actuator designs based on digital hydraulics. | ||||
| 17:00 | 17:30 | 5.3.3 |
AN EVALUATION METHOD FOR AIRCRAFT ACTUATION SYSTEMS OPERATIONAL COST C. Reichenwallner, Linköping university, Sweden; F. Larsson¹, A. Dell'Amico¹; ¹Saab AB, Sweden This paper will introduce a method for evaluating operational cost with respect to the aircraft actuation system. The method in the paper considers the weights, volumes, power consumption and cooling needs of components closely related to the actuation system. Trade-studies of the above-mentioned quantities is done in a case study involving a highly maneuverable fighter jet. | ||||
| 17:30 | 18:00 | 5.3.4 |
DEVELOPMENT OF A HIGH EFFICIENT HYDRAULIC POWER PACK L.Z. Lima¹, M.N. Duval¹, T. Zantner¹, D. Metzler¹, T. Lammering¹, F. Thielecke², N. Trochelmann², P.S. Bischof²; ¹Liebherr-Aerospace Lindenberg GmbH, Germany ;²Hamburg University of Technology, Germany Presenter: Leonardo Zanetti de Lima As a first tier supplier, Liebherr-Aerospace faces the ever growing challenge to provide the different airframers with competitive products within a highly competitive and agile business environment. Costs, time-to-market, product maturity, and ramp-up capabilities are certainly driving factors for technology selection, but environmental aspects play a growing role and must be taken into consideration by airframers and suppliers, since they are key criteria for success and customer satisfaction. The electrification of aircraft systems contributes to the goal of greener air transportation, with reduced emissions and decrease in fuel consumption. Several solutions have to be developed at system level to give airframers the elements necessary to turn the “more electric aircraft” into reality. Liebherr proposes a high efficient solution to for decentralized hydraulic power generation, providing the airframes the flexibility to place the hydraulic power pack close to the consumers, eliminating long pipe sections between power generation and consumers. Two size of high efficient power packs were conceived, one for large power demand, typically applied for main landing gear retraction/extension system, and one mid-sized pack for primary flight controls consumers placed in the aircraft tail (rudder and elevators). The system works solely on electric power, and thus is an important brick for the electrification of future aircraft. This paper shows how Liebherr-Aerospace faced the challenge of maturing the solution, bringing our customers a solution with excellent performance while being tailored for high production rates and easy maintenance. | ||||
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| 16:00 | 16:30 | 6.3.1 |
AERODYNAMIC AND AEROACOUSTIC CHARACTERISTICS OF THE NACA 0008 AIRFOIL F.L. dos Santos¹, L. Botero-Bolivar¹, C.H. Venner¹, L.D. de Santana¹; ¹University of Twente, Netherlands This paper discusses the near- and far-field of leading- and trailing-edge noise generated by a NACA0008. Wall-pressure fluctuations are the highest close to the leading edge, suggesting that the leading-edge noise is the dominant noise source for turbulent inflows. This is confirmed by far-field noise measurements. Trailing-edge noise is comparable to the leading-edge noise for high frequencies. | ||||
| 16:30 | 17:00 | 6.3.2 |
EXPERIMENTAL STUDIES ON THE INTERACTION BETWEEN PROPELLERS AND WING G.P.G. Silva¹, M.V.R.J. Silva¹, J.P. Eguea¹, F.M. Catalano¹; ¹Department of Aeronautical Engineering, University of Sao Paulo, Brazil The aerodynamic and aeroacoustic interaction effects between propellers and between propellers and wing are being investigated experimentally in a wind tunnel. The results will bring a better understanding of these interactions, which will allow the elaboration of good practices for distributed electric propulsion conceptual designs, and provide a database for validating computational tools. | ||||
| 17:00 | 17:30 | 6.3.3 |
IDENTIFICATION OF CRITICAL ACOUSTIC MODES FOR AN OPEN BOX CAVITY WITH ADJUSTABLE DEPTH S. Hammer¹, J. Fridh¹, M. Billson, GKN Aerospace Sweden, Sweden; ¹KTH Royal Institute of Technology, Sweden Presenter: Jens Fridh, KTH Royal Institute of Technology Identification of critical operating points in regards to acoustic modes in compressor bleed systems. A clear identification of acoustic resonance and mode shifting in regards to geometric quantities and flow conditions. This will allow for better prediction models in the design chain of low pressure compressors in aero engines. | ||||
| 17:30 | 18:00 | 6.3.4 |
AN OVERVIEW OF AERO-ACOUSTIC EXPERIMENTAL TECHNOLOGY IN AVIC FL-10 WIND TUNNEL Z. Guocheng¹, B. Anyu ¹, C. Bao¹, L. Xiangnan¹; ¹AVIC ARI, China Presenter: BAO Anyu, AVIC ARI This paper introduces the general information and acoustic test environment of FL-10 wind tunnel, and the aero-acoustic experiment and measurement system. The tests of airframe noise, landing gear noise, high-speed railway noise and rotor noise was carried out in FL-10 wind tunnel, and the test results was analyzed in this paper as well. | ||||
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| 16:00 | 16:30 | 7.3.1 |
TOWARDS VIRTUAL FATIGUE TESTING: DEVELOPMENTS AND CHALLENGES FOR METALLIC AND COMPOSITES AEROSTRUCTURES I. Rivero¹, A. Palomar¹, N. Martin¹, M. Lozano¹, J. Romero¹, B. De Nicolas¹, M. Rebollo¹, J. Gomez-Escalonilla¹; ¹Airbus, Spain Presenter: Zuriñe Mujika An overview of the latest developments carried out at Airbus for Military Aircraft programs towards virtual fatigue testing will be presented emphasizing the most relevant specific needs in terms of virtual fatigue testing technology for both metallic and composite structures, and also an identification of the main developments to be addressed for virtual fatigue testing effective implementation. | ||||
| 16:30 | 17:00 | 7.3.2 |
VARIATIONS IN STRUCTURAL PROPERTIES OF LATTICE STRUCTURES DEPENDING ON UNIT CELL SHAPE FOR MORPHING WINGS Y. Nishijima¹, H. Tanaka¹, A. Biron, Special Military School of Saint-Cyr, France; T. Miura¹; ¹National Defense Academy, Japan Lattice structures consisting of five different unit cell types were developed and subjected to tests. The results indicated that some lattices have isotropic characteristics and others have anisotropic characteristics depending on the unit cell. By applying the above anisotropic properties, it is possible to generate arbitrary deformations of the structure in response to inputs from actuators. | ||||
| 17:00 | 17:30 | 7.3.3 |
PROPOSITION OF A NEW QUALIFICATION IMPACT TEST FOR AEROSPACE SMART STRUCTURES G. Gastaldo, France; Y. Rafik, France; M. Budinger, France; V. Pommier-Budinger, France; P. Olivier, France; P. Navarro, France Piezoelectric materials are employed in several aerospace applications. It is thus necessary to ensure their correct functioning for critical events such as impacts. This paper proposes a novel test standard method to measure and qualify the damage resistance of smart PZT structures to a drop-weight impact event through the quantification of electromechanical characteristics. | ||||
| 17:30 | 18:00 | 7.3.4 |
PERIDYNAMIC SIMULATION PLATTFORM TO DETERMINE VIRTUAL ALLOWABLES OF MANUFACTURING DEVIATIONS C. Willberg¹, J.-T. Hesse¹, D. Krause¹; ¹German Aerospace Center, Germany In order to analyze complex and large scale structural mechanical problems, simulation on all levels of the aircraft design process efficient simulation frameworks are required. This can be reached by digitalization. Tools are not understood as one large software tool, but the interaction and communication of several tools. If properly design no additional wrapper are needed between interfaces. The advantages are that specialist could focus in their field and tools can be used more widely. In this talk we want to present Peridynamics based structural mechanics simulation plattform. The framework allows the analysis of fracture mechanical problems and can for example be used to determine simulation based allowables. | ||||
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| 16:00 | 16:30 | 8.3.1 |
AEROELASTIC ANALYSIS OF HIGH ASPECT RATIO AND STRUT-BRACED WINGS Y. Le Lamer¹, J. Morlier, ICA, Université de Toulouse, ISAE-SUPAERO, MINES ALBI, UPS, INSA, France; E. Benard¹, P. He, Iowa State University, United States; ¹ISAE-SUPAERO, Université de Toulouse, France Increasing the aspect ratio of transonic aircraft wings is a promising path to reduce aviation carbon footprint. This paper focuses on the development of high and low fidelity aeroelastic models for high aspect ratio and strut-braced wings. These models are implemented within an aeroelastic analysis framework. Finally, high and low fidelity analysis will be performed and results compared. | ||||
| 16:30 | 17:00 | 8.3.2 |
COMPARING REDUCED ORDER MODEL FORMS FOR NONLINEAR DYNAMICAL SYSTEMS D. Massegur¹, D. Clifford¹, A. Da Ronch¹, S. Symon¹; ¹University of Southampton, United Kingdom This work presents a comparative study between two contrasted ROM approaches: Intrusive against Non-Intrusive techniques. To this aim, a model-based projection method and a machine-learning based system are presented and benchmarked using nonlinear dynamical test cases. Followingly, we perform a thorough performance analysis to highlight the benefits of each approach. | ||||
| 17:00 | 17:30 | 8.3.3 |
NUMERICAL INVESTIGATION ON THE DOUBLE TRANSONIC DIP OF SUPERCRITICAL AIRFOIL FLUTTER T. Miyake¹, H. Terashima¹; ¹Hokkaido University, Japan The supercritical airfoil uniquely exhibited a double transonic dip on the flutter boundary. The second transonic dip at a high Mach number condition was only observed for the supercritical airfoil. It was indicated that the generation of the second transonic dip was associated with the unsteady behaviors of flow separation and reattachment over the lower surface. | ||||
| 17:30 | 18:00 | 8.3.4 |
ANALYSIS OF THE HAMMERHEAD LAUNCH VEHICLE USING CFD-CAE COUPLED METHOD IN THE TRANSONIC REGION H.-G. Rho, Korea Aerospace Univeristy, South Korea; P.A. Nguyen¹, J.-S. Bae¹, S.-H. Park, Konkuk University, South Korea; K.-H. Byun, Korea Agency for Defense Development, South Korea; ¹Korea Aerospace University, Vietnam An aeroelastic stability analysis of the hammerhead launch vehicle using computational fluid dynamics and computational structural dynamics coupled method in transonic region is performed with time domain and frequency domain to predict the aeroelastic phenomena such as flutter, divergence and buffet. The obtained results shown that divergence could occur in the worst case of the launch vehicle. | ||||
| Reserve Paper (Interactive) | 8.3.R |
A NUMERICAL METHOD FOR STUDY ON THE AERO-ELASTICITY OF AIR-TO-AIR MISSILES IN OVER-THE-SHOULDER LAUNCH K. Lu¹, W.-P. Song¹, K. Ye¹, C.-H. Gao¹, S.-Q. Han, Sichuan University, China; ¹Northwestern Polytechnical University, China | |||||
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| 16:00 | 16:30 | 9.3.1 |
COUPLED AEROPROPULSIVE ANALYSIS AND OPTIMIZATION OF A HIGH BYPASS TURBOFAN ENGINE A.H.R. Lamkin¹, A. Yildirim¹, J.R.R.A. Martins¹; ¹University of Michigan, United States This work builds upon recent efforts in aeropropulsive design optimization to consider a fully coupled high bypass turbofan configuration. We employ a novel coupling strategy to study interactions between the propulsion sub-systems using a mixed-fidelity framework. The results include a fully coupled aeropropulsive analysis, single point, and multi point gradient-based optimization study. | ||||
| 16:30 | 17:00 | 9.3.2 |
A COMPARITIVE ASSESSMENT OF MULTI-OBJECTIVE OPTIMISATION METHODOLOGIES FOR AERO-ENGINE NACELLES A. Swarthout¹, D. MacManus¹, F. Tejero¹, J. Matesanz-Garcia¹, L. Boscagli¹, C. Sheaf, Rolls Royce Plc., United Kingdom; ¹Cranfield University, United Kingdom Compact aero engine nacelles may promise to reduce the drag and weight penalties associated with ultra-high bypass ratio turbofans. These nacelles may be sensitive to off design conditions. This paper tests three methods of optmising compact nacelles with windmilling considerations. It demonstrates how to consider different sets of representative flow physics within complex optimisation problems. | ||||
| 17:00 | 17:30 | 9.3.3 |
KNOWLEDGE-BASED CONCEPTUAL DESIGN METHODS FOR GEOMETRY AND MASS ESTIMATION OF RUBBER AERO ENGINES J. Häßy¹, J. Schmeink¹; ¹DLR, Germany A knowledge-based conceptual design method for estimating engine geometry and mass at part level based on thermodynamic cycle data and an advanced parameterization of turbo components utilizing splines is presented. The procedure is validated for a modern geared turbofan and the applicability in the context of MDAO is shown by means of an engine design study. | ||||
| 17:30 | 18:00 | 9.3.4 |
MULTIDISCIPLINARY OPTIMIZATION OF COMBUSTION CHAMBER FOR SMALL GAS TURBINE ENGINES C.-A. Pham¹, Q.-H. Nguyen¹, T.-A. Vu¹, N.-V. Nguyen¹; ¹Viettel Aerospace Institute, Viettel Group, Vietnam Presenter: Nhu-Van Nguyen, Viettel Aerospace Institute, Viettel Group The comprehensive multidisciplinary optimization of combustion chamber for small gas turbine engines is summarized and presented. The in-house analysis using CFD and post processing methodology is proposed and verified for the NASA low-cost turbine engine of 650 lbf sea-level static thrust with the key parameters such as combustion efficiency, total-pressure loss, exit-temperature profile, reference velocity. The comparison of experiment data with CFD results (1/12, 1/2 and full scale of combustor chamber) is presented for the radial and circumferential exit temperature profile. The analysis results show very good agreements with the experimental data for the 1/2 and full-scale combustion chamber at the sea-level test conditions from the NASA TM X-2857 report. The proposed methodology is implemented for the 1st combustor prototype while satisfying the requirements. The fabrication and test results of 1st prototype are obtained and enhanced for the next design loop. The proposed methodology shows the feasibility and effectivity of the cost saving and low turnaround time while developing the small and low-cost turbojet engines. | ||||
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| 16:00 | 16:30 | 10.3.1 |
FLIGHT DYNAMICS SIMULATION AND FCS AUTO-GENERATION IN THE CONCEPTUAL DESIGN PHASE OF AN UNSTABLE SUPERSONIC AIRCRAFT E. Johansson¹, P. Månsson¹, P. Sjöberg¹; ¹Saab Aeronautics, Sweden The use of a 6-DOF flight mechanics model with automatically generated control laws is applied to achieve faster design iterations and to provide early design feedback. Parametrisation of key design features provides an improved exploration of design trades. | ||||
| 16:30 | 17:00 | 10.3.2 |
VALIDATION OF A HYBRID LOADS OBSERVER FOR A SUBSCALE TEST AIRCRAFT WITH DISTRIBUTED ELECTRIC PROPULSION O. Luderer¹, F. Thielecke¹; ¹Hamburg University of Technology, Germany By taking advantage of potential synergy between the propulsion and the wing, distributed propulsion opens the design space for innovative aircraft configurations. Future aircraft also tend to lighter wings & high aspect ratios, increasing the need of inflight load monitoring. In this paper a model-based hybrid load observer for load estimation is extended for aircraft with distributed propulsion. | ||||
| 17:00 | 17:30 | 10.3.3 |
A BI-LEVEL CO-DESIGN APPROACH FOR MULTICOPTERS J. Mabboux¹, S. Delbecq¹, V. Pommier-Budinger¹, J. Bordeneuve-Guibe¹, A. Truc-Hermel², J.-M. Kai²; ¹ISAE Supaero, France ;²SAFRAN, France In this paper, a co-design approach for the multirotor is presented with the objective of improving the energetic efficiency. The approach optimizes concurrently the design and the control. In contrast to conventional design approaches that sequentially designs each part, the co-design approach leads to a better optimal solution due to the consideration of the couplings between design and control. | ||||
| 17:30 | 18:00 | 10.3.4 |
DEEP REINFORCEMENT LEARNING FOR EVTOL HOVERING CONTROL D.S. Alarcon¹, J.H. Bidinotto¹; ¹University of São Paulo, Brazil This work uses Deep Reinforcement Learning to control the hovering phase of an eVTOL. A 6DoF model of the Airbus Vahana is implemented in OpenAI Gym and the PPO method tested, with different hyperparamters. Then, compared with DDPG, TD3, SAC and a PID controller baseline. The result showed that the PPO was the best method for this task. This work is the first step of full eVTOL control with DRL. | ||||
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| 16:00 | 16:30 | 11.3.1 |
OPTIMAL HOVERING WING KINEMATICS OF FLAPPING-WING MODEL USING REINFORCEMENT LEARNING H.-H. Yang¹, S.-G. Lee¹, Y.-J. Han¹, J.-H. Han¹; ¹Korea Advanced Institute of Science and Technology, South Korea Presenter: Hyeon-Ho Yang, Korea Advanced Institute of Science and Technology The unsteady vortex method is modified to estimate the contribution of leading-edge vortices and was used to simulate the unsteady aerodynamics of the flapping wing model. The reinforcement learning environment to train flapping wing kinematics is established based on a deep neural network. The optimal hovering wing kinematics that leads to maximum lift and lift/drag ratio is found. | ||||
| 16:30 | 17:00 | 11.3.2 |
PREFLIGHT DIAGNOSIS OF MULTICOPTER ACTUATOR FAULT USING SUPERVISED LEARNING WITH DISTURBANCE OBSERVER OUTPUTS T.G. Kim¹, Y.J. Kim¹, S.K. Kim¹; ¹Chungnam National University, South Korea This study proposes a preflight diagnosis method using disturbance observer outputs for health condition monitoring of multicopter actuators faults. While operating multicopters, determining whether it can perform the flight mission or not is essential. For this reason, we use the disturbance observer's output as a feature for diagnose of the fault. | ||||
| 17:00 | 17:30 | 11.3.3 |
USING DEEP REINFORCEMENT LEARNING TO IMPROVE THE ROBUSTNESS OF UAV LATERAL-DIRECTIONAL CONTROL R. Wang¹, Z. Zhou¹, X. Zhu¹, L. Zheng, Delft University of Technology, Netherlands; ¹Northwestern Polytechnical University, China Inspired by PID and LQG control method, this paper presents an improved TD3 deep reinforcement learning Lat-Dir flight control law design method. Flight simulations are carried out in the nominal state and deviation state respectively. The results show that the TD3 controller has the advantages of clear physical meaning, simple structure of policy network and strong performance robustness. | ||||
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| 16:00 | 16:30 | 12.3.1 |
IMPROVED CONFIGURATION MANAGEMENT FOR GREENER APPROACHES – EVALUATION OF A NOVEL PILOT SUPPORT CONCEPT T. Bauer¹, F. Abdelmoula¹, J. Boyer, Thales, France; M. Gerber, Swiss Sklylab Foundation, Switzerland; J. Meister², J.M. Wunderli²; ¹DLR e.V., Germany ;²Empa, Swiss Fed. Laboratories for Materials Science & Technology, Switzerland Speed and configuration management is the key to carrying out an approach that is not only safe, but as environmentally friendly as possible, minimising fuel / noise. A new operational concept and FMS functionality is developed and evaluated in piloted simulator trials to support the flight crew in this task under fluctuating wind and weather conditions while following individual ATC instructions. | ||||
| 16:30 | 17:00 | 12.3.2 |
A COMPARISON OF CLIMATE-OPTIMISED AND FUEL-OPTIMISED INTERMEDIATE STOP OPERATIONS FOR SELECTED CASE STUDIES Z. Zengerling¹, F. Linke¹, C. Weder¹, K. Dahlmann¹; ¹Deutsches Zentrum für Luft- und Raumfahrt, Germany While increased fuel efficiency from Intermediate Stop Operations has been confirmed in previous research, an optimisation of this operational measure with regards to climate impact is performed in this work. Location of intermediate stop airport and cruise flight level influence both optimising options. Results are compared in terms of flight time, detour, fuel burn, and temperature response. | ||||
| 17:00 | 17:30 | 12.3.3 |
IMPLICATIONS OF POTENTIAL NEW REGULATORY MEASURES TO ADDRESS AVIATION EMISSIONS A. Nieto¹, G. Alonso¹, J. Cubas¹; ¹Universidad Politécnica de Madrid, Spain Analysis of the implications of potential new regulatory policies being proposed in the European Union, such as the carbon tax, or the mandatory blending of SAF (on top of the already existing CORSIA or ETS), to address aviation emissions from a technical, operational and economic perspective. | ||||
| 17:30 | 18:00 | 12.3.4 |
AN ENGINELESS TAXI OPERATIONS SYSTEM USING BATTERY-OPERATED AUTONOMOUS TOW TRUCKS S. Zaninotto¹, J. Gauci¹, B. Zammit¹; ¹University of Malta, Malta This paper will detail the design of an algorithm for taxi operations using autonomous tow trucks. The system will be capable to elaborate conflict-free solutions with minimized delays for aircraft and tow trucks and it will be tested for a large number of scenarios characterized by various features. | ||||
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| 16:00 | 16:30 | 13.3.1 |
A NOVEL METHOD FOR DETECTING UAVS USING PARALLEL NEURAL NETWORKS WITH RE-INFERENCE H. Stepien, Saab Aeronautics, Sweden; M. Bilger, Saab Surveillance, Sweden; H. Forsberg¹, B. Lindgren, Saab Dynamics, Sweden; J. Hjorth¹; ¹Mälardalen University, Sweden In this paper, we suggest a method for detecting unmanned aerial vehicles using a parallel architecture consisting of three diverse convolutional neural networks, each with different properties. The system utilizes re-inference to increase detection capability. The results confirm the method works and show major improvements in total accuracy as well as lower mispredictions. | ||||
| 16:30 | 17:00 | 13.3.2 |
URBAN AIR TRAFFIC MANAGEMENT FOR COLLISION AVOIDANCE WITH NON-COOPERATIVE AIRSPACE USERS I. Panchal¹, I.C. Metz, German Aerospace Center, Germany; M. Ribeiro, TU Delft, Netherlands; S.F. Armanini¹; ¹TU Munich, Germany Urban Air Mobility operations are intended to take place at altitudes most frequented by drones and birds. Encounters will be inevitable. This work develops a collision avoidance system for conflict detection and resolution to prevent collisions between Urban Air Mobility vehicles and these uncooperative airspace users. | ||||
| 17:00 | 17:30 | 13.3.3 |
A HUMAN-MACHINE INTERFACE ANALYSIS FOR TELEOPERATION OF UAV OVERTIME DELAY A.G.P. Sarmento¹, T. Rosado de Paula¹, A.S. Oliveira¹, E.T. da Silva¹, J. Possamai¹, H.C. Marques¹, M.M. Cardoso Junior¹, E. Villani¹; ¹Aeronautics Institute of Technology (ITA), Brazil Presenter: Moacyr Machado Cardoso Júnior , Aeronautics Institute of Technology This research seeks to present an experiment that aims to analyze the influence of communication delay on pilot workload when operating a UAV. The development of the project was defined with the survey of factors, the creation of a simulator and the answers to be analyzed. The performance analysis will be based on physiological data and the ISA scale. | ||||
| 17:30 | 18:00 | 13.3.4 |
IMAGE SEGMENTATION BASED EMERGENCY LANDING FOR AUTONOMOUS AND AUTOMATED UNMANNED AERIAL VEHICLES P. Hausmann¹, H. Meeß, Fraunhofer IVI, Germany; G. Elger¹; ¹Technische Hochschule Ingolstadt, Germany The operation of autonomous unmanned aerial vehicles (UAV) entails serious risks and respective regulations. We have developed an emergency landing operation which aims to offer more security by identifying safe landing spots for both the environment, as well as the drone, using image segmentation. | ||||
| Reserve Paper | 13.3.R |
EVALUATION AND QUANTIFICATION OF THE POTENTIAL CONSEQUENCES OF BIRD STRIKES IN URBAN AIR MOBILITY A. Devta¹, I.C. Metz, DLR, Germany; S.F. Armanini¹; ¹Technical University of Munich, Germany Presenter: Aditya Devta, Technical University of Munich | |||||
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| 16:00 | 16:30 | 14.3.1 |
THE ALBATROSS PROJECT – A EUROPEAN INITIATIVE TO REDUCE AVIATION’S CARBON DIOXIDE EMISSIONS IN LARGE SCALE F. Sachs¹, F. Abdelmoula¹, D. Vechtel¹; ¹DLR, Germany Presenter: Dennis Vechtel, DLR The paper presents methodology used and results obtained by the ALBATROSS Project. The focus of the ALBATROSS project is to reduce fuel burn of commercial aviation flights by close collaboration of all stakeholders. ALBATROSS is a very large demonstration (VLD) that is performed for city pairs and gate to gate operations across Europe. | ||||
| 16:30 | 17:00 | 14.3.2 |
ZERO-EMISSION REGIONAL AVIATION IN SWEDEN R.T. Sorrentino¹, R.C. Parello¹, M. Delage¹, C.Y. Justin¹, D.N. Mavris¹, C. Jouannet², K. Amadori²; ¹Georgia Institute of Technology, United States ;²Saab AB/Saab Aeronautics, Sweden Presenter: Robbie Sorrentino, Georgia Institute of Technology A modeling environment is implemented in Scandinavia and allows for an environmental assessment of various scenarios regarding technology advancements, paradigm shifts in powertrain configurations, new transportation policies, and emission offsetting schemes with the aim to inform technologists and decision-makers about viable and sustainable paths for new regional air operations. | ||||
| 17:00 | 17:30 | 14.3.3 |
PERFORMANCE EVALUATION OF THE ARRIVAL OPERATIONS IN TERMINAL AREA H. Hardell¹, A. Lemetti¹, T. Polishchuk¹; ¹Linköping University, Sweden In this work, we split the arriving air traffic into different clusters, for which we analyse the horizontal and vertical flight efficiency and relate it to the additional fuel burn. In addition, we study the impact of different factors, such as weather and traffic intensity. We suggest that such a targeted per-flow analysis helps to understand the sources of fuel inefficiencies within TMA. | ||||
| 17:30 | 18:00 | 14.3.4 |
AERODYNAMIC INVESTIGATION OF VERY CLOSELY FLYING FIGHTERS TO DEVELOP NEW FORMATION TYPES S.M. Aydin¹, A.G. Yavuz, Turkish Aerospace Industries, Turkey; M. Kaya¹; ¹Yildirim Beyazit University, Turkey Aerodynamic analysis targeted for the development of a new close flight formation with the minimum distance between the 4th Generation Fighters that will turn the opponents' target distribution problem of radar systems against close flight formation into an advantage against new generation fighters increase the Survivability and Lethality factors in BVR engagement at operational environment. | ||||
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| 10:30 | 11:00 | 1.4.1 |
CERTIFICATION BY ANALYSIS - SOME THOUGHTS (invited) U. Kerlin, Airbus, Germany Following the General Lecture by Robert Gregg III, a panel will further explore the progress to date and next steps recommended on a path towards increased certification by analysis for flight characteristics. A similar panel was held at AIAA Aviation in 2017 that helped coalesce ideas on the topic and bring the community together. | ||||
| 11:00 | 11:30 | 1.4.2 |
NEXT STEPS TOWARDS CERTIFICATION BY ANALYSIS - A DIGITAL THREAD PERSPECTIVE (invited) O. Pinon Fischer, United States; D. Mavris, United States Since that time, progress has been made around the world on multiple fronts. One such example is the recommended practices document created under the auspices of the AIAA by and international group resulting in “Recommended Practice: When Flight Modelling is Used to Reduce Flight Testing Supporting Aircraft Certification (AIAA R-154-2021) https://arc.aiaa.org/doi/10.2514/4.106231.001. Another example is the formation of an international ecosystem revolving around the use of common research model geometries to facilitated the sharing of information and learning in the advancement of modeling and simulation tools. | ||||
| 11:30 | 12:00 | 1.4.3 |
TOWARDS CERTIFICATION BY ANALYSIS FOR FLIGHT CHARACTERISTICS (invited) R. Gregg, Boeing, United States Panelists will include senior leaders and experts from around the world representing a diverse organizations who will bring their perspectives to the discussion. It is hoped that several key next steps will emerge that resonate with the global community and can help sharpen focus and collaboration going forward. | ||||
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| 10:30 | 11:00 | 2.4.1 |
DEEP LEARNING TECHNIQUES FOR HIGH-DIMENSIONAL SURROGATE-BASED AERODYNAMIC DESIGN M.A. Hariansyah¹, K. Shimoyama¹; ¹Institute of Fluid Science, Tohoku University, Japan A large-scale wing shape optimization is characterized by its high dimensionality, making gradient-free population-based methods such as genetic algorithm (GA) unpopular in the field. We address this issue by incorporating deep learning techniques to assist a GA called NSGA-II and demonstrate the method by solving lift-constrained drag minimizations of the Common Research Model wing. | ||||
| 11:00 | 11:30 | 2.4.2 |
SUCCESSIVE KNOWLEDGE BUILDUP AND TRANSFER DURING THE ANALYSIS OF SCALED UAV WINGS BY MEANS OF MACHINE LEARNING T. Klaproth¹, M. Hornung¹; ¹Technical University of Munich, Germany We provide formulas for scaling factors to estimate higher-fidelity results from low-fidelity methods. We demonstrate succesful correction of semi-empiric formulas that are intended for other aircraft classes. We explore the potential for knowledge buildup and transfer within an automated design optimization loop. We show an approach that avoids unquestioned imitation of higher-fidelity aero data. | ||||
| 11:30 | 12:00 | 2.4.3 |
AIRCRAFT DESIGN PARAMETER ESTIMATION USING DATA-DRIVEN MACHINE LEARNING MODELS S. Shin¹, S. Lee¹, C. Son, Cheongju University, South Korea; K. Yee, Seoul National University, South Korea; ¹Korea Institute of Industrial Technology, South Korea This research presented the validity of applying a data-driven approach to the aircraft initial sizing problem. The limitations of the existing methods are overcome by using machine learning techniques. K-nearest neighbors algorithm and Variational autoencoder were used in this study for the imputation of the incomplete aircraft data. Both of the models have successfully estimated target values. | ||||
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| 10:30 | 11:00 | 3.4.1 |
EXPLORATION OF BOX-WING AIRCRAFT CONCEPT USING HIGH-FIDELITY AERODYNAMIC SHAPE OPTIMIZATION P.D. Bravo-Mosquera¹, T. Chau², F.M. Catalano¹, D.W. Zingg²; ¹University of São Paulo, Brazil ;²University of Toronto, Canada This paper discusses the application of aerodynamic shape optimization of a box-wing concept based on RANS equations. A lift-constrained drag optimization problem is presented. The results demonstrate the potential of the box-wing concept, and the importance of high-fidelity tools towards the design of novel configurations that can lead to reduced fuel burn and carbon emissions | ||||
| 11:00 | 11:30 | 3.4.2 |
CONCEPTUAL STUDY OF HYBRID-ELECTRIC BOX-WING AIRCRAFT TOWARDS THE REDUCTION OF AVIATION EFFECTS ON LOCAL AIR QUALITY AND CLIMATE CHANGE K. Abu Salem¹, V. Cipolla¹, G. Palaia¹, V. Binante², D. Zanetti²; ¹University of Pisa, Italy ;²SkyBox Engineering, Italy Presenter: Karim Abu Salem, University of Pisa, Dep. of Civil and Industrial Engineering The development of hybrid-electric aircraft with box-wing airframe aims to mitigate the impact of aviation on both local air quality and climate change. This research describes the environmental benefits of integrating hybrid-electric propulsion, which provides reductions in fuel consumption, with the greater aerodynamic efficiency of a box-wing lifting system. | ||||
| 11:30 | 12:00 | 3.4.3 |
MULTIDISCIPLINARY DESIGN ANALYSIS AND OPTIMIZATION PROCESS DEDICATED TO BLENDED WING BODY CONFIGURATIONS J. Gauvrit-Ledogar¹, A. Tremolet¹, F. Moens¹, M. Méheut¹, S. Defoort¹, R. Liaboeuf¹, F. Morel¹, B. Paluch¹; ¹ONERA, France Since 2015, ONERA develops a dedicated multidisciplinary design analysis and optimization process to explore in depth the potential benefits of the Blended Wing Body configuration. The results obtained confirm the good performance expected for such new aircraft configuration, mainly through the reduction of the required fuel weight. | ||||
| Reserve Paper | 3.4.R |
RESEARCH ON THE SELECTION METHOD OF TYPICAL RCS BENCHMARK BASED ON AHP Y.-L. Huang¹, D.-Q. Huang¹, W. Du¹, J. Liu, Beihang University, China; ¹AVIC CHENGDU AIRCRAFT INDUSTRIAL(GROUP) CO.LTD, China | |||||
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| 10:30 | 11:00 | 4.4.1 |
WING BUFFET PRESSURE LOAD PREDICTION BASED ON A HYBRID DEEP LEARNING MODEL R. Zahn¹, A. Weiner, Technical University of Braunschweig, Germany; C. Breitsamter¹; ¹Technical University of Munich (TUM), Germany A hybrid deep learning model based on a convolutional autoencoder and a long short-term memory neural network is applied for the prediction of transonic wing buffet pressure loads on the Airbus XRF-1 configuration. For training the hybrid model, experimental data is used. The model is applied for the prediction of varying buffet conditions, aiming to reduce expensive experimental investigations. | ||||
| 11:00 | 11:30 | 4.4.2 |
AN ASSESSMENT OF REDUCED-ORDER AND MACHINE LEARNING MODELS FOR STEADY TRANSONIC FLOW PREDICTION ON WINGS R. Castellanos¹, J. Bowen Varela¹, A. Gorgues¹, E. Andrés¹; ¹INTA, Spain Presenter: Rodrigo Castellanos, INTA In this paper, the potential of machine learning techniques for the aerodynamics prediction of industrial-relevant aircraft configurations has been assessed. This is relevant for the aeronautic industry since CFD solvers are computationally expensive and machine learning methods can be very useful in certain situations, for instance inside an optimization process. | ||||
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| 10:30 | 11:00 | 5.4.1 |
ASSESSMENT OF THE SUSTAINABILITY OF THE IMPLEMENTATION OF CIRCULAR ECONOMY PRINCIPLES IN PRODUCING AIRCRAFT STRUCTURES D.N. Markatos¹, S.G. Pantelakis¹; ¹University of Patras, Greece Presenter: Dionysios Markatos The current work aims to contribute to the assessment of the implementation of circularity principles in the production of aircraft structures. To this end, a decision support tool will be implemented to aid decision makers and stakeholders identify and select a recycled material, among alternative ones, that best fit to their preferences and needs. | ||||
| 11:00 | 11:30 | 5.4.2 |
INVESTIGATION ON INTEGRATING RECYCLABILITY AS A FUNCTION AT THE DESIGN PHASE OF COMPLEX-LOADED STRUCTURAL COMPONENTS A. Filippatos¹, K. Abhyankar, Institute of Lightweight Engineering and Polymer Technology, Tec, Germany; G. Tzortzinis¹; ¹Dresden Center for Intelligent Materials (DCIM), Technische Univ, Germany We consider recycling as a complex, non-mechanical function during the design phase, and its impact on the main structural function of a component by applying the novel spiral development method. The integration of the function is defined and included at the requirements and the design phase. Here, the recycling-as-a-function approach aims to design by meeting the recycling criteria. | ||||
| 11:30 | 12:00 | 5.4.3 |
SIGMOIDAL SENSING DEVICES FOR MONITORING TO IMPROVE MAINTENANCE OPERATIONS IN AERONAUTICS H. Pfeiffer¹, H. Sekler, Deutsche Lufthansa AG, Germany; M. Wevers¹; ¹KU Leuven, Belgium This paper presents and intents to stimulate the implementation of “sigmoidal responding sensing devices” for the health monitoring of structures and systems in diverse aircraft segments to essentially avoid problems arising from a too weak “contrast” between actual damage signals and interfering background variations. | ||||
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| 10:30 | 11:00 | 6.4.1 |
ANALYSIS OF THE EFFECT OF FLOW TRANSITION OVER THE WINGS OF THE BLADE DEMONSTRATOR R. Larsson, Saab Aeronautics, Sweden This paper describes the Saab flow transition analysis of a BLADE flight-test. It shows the methods and results based on geometries and transition lines given by AIRBUS and DLR. The Saab wing concept has a potential to reduce the total drag with about 9 % for typical A320 like aircraft. | ||||
| 11:00 | 11:30 | 6.4.2 |
TO CFD OR NOT TO CFD? COMPARING RANS AND VISCOUS PANEL METHODS FOR AIRFOIL SHAPE OPTIMIZATION E.J. Adler¹, A.C. Gray¹, J.R.R.A. Martins¹; ¹University of Michigan, United States Using RANS CFD and a viscous panel method, we show the effect of aerodynamic analysis method selection on optimized aerodynamic shapes and the consequences of choosing one that does not capture the relevant flow physics. Our results provide aerodynamicists with the data and intuition to make informed decisions when selecting analysis methods for optimization. | ||||
| 11:30 | 12:00 | 6.4.3 |
PUSHER PROPELLER INFLUENCE ON A LAMINAR WING TRANSITION LOCATION USING INFRARED THERMOGRAPHY J.P. Eguea¹, G.P.G. Silva¹, F.M. Catalano¹; ¹USP, Brazil The impact of a pusher propeller on a laminar wing boundary layer transition position are being investigated experimentally in a wind tunnel. The results will bring a better understanding of this interaction, enabling a discussion on the concept impact on aircraft performance and contribution for making a greener aviation. | ||||
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| 10:30 | 11:00 | 7.4.1 |
EFFECT OF NITRIDING ON MICROSTRUCTURE AND MECHANICAL PROPERTIES ON A TI64 ALLOY FOR AEROSPACE APPLICATIONS S. Stekovic¹, R. Romero-Ramirez¹, L. Selegård, Saab Aeronautics, Sweden; ¹Linköping University, Sweden Presenter: Rodger Romero-Ramirez, Linköping University Titanium is very strong in relation to its low weight making it very interesting for lightweight applications. However, use of titanium in certain aircraft components is limited as it is a relatively soft metal that quickly deteriorates when mechanically stressed. A nitriding heat treatment was developed for Ti64 with aim to improve wear properties without negative effect on fatigue and strength. | ||||
| 11:00 | 11:30 | 7.4.2 |
MECHANICAL CHARACTERIZATION OF A COMPOSITE STRUCTURAL BATTERY LAMINATE G. Di Mauro¹, P. Russo, Institute for Polymers, Composites and Biomaterials, C.N.R., Italy; M. Guida¹; ¹University of Naples Federico II – Department of Industrial Eng., Italy Recently, ambitious targets have been set out in various branches of transportation sector to restrict pollutant emissions and to combat climate change and environmental degradation. In this frame, with specific reference to the aeronautic field, new designs including electric or hybrid-electric powertrains propulsion systems penalize battery characteristics, especially in terms of limited energy and power density performances, in turn imposing an increase of the machine weight. Structural batteries (SB) constitute an interesting technology, with the potential to alleviate such problems. In the literature, structural batteries can be classified into different categories depending on their degree of structural integration. Starting from a side-by-side combination of a structural element and a conventional battery (zero degree of integration) in a fully integrated system, in which the structural element also acts as an energy accumulator, a common classification of structural batteries is based on the integration parameter structural. The class including the integrated thin-film energy storages is not fully considered, as this approach is not expected to yield high enough energy densities for a meaningful contribution to the overall energy needs of an aeronautical vehicle. Furthermore, structural batteries are further divided into two categories: multifunctional structures (or decoupled systems) and multifunctional materials (or coupled systems). In the first case different materials within the structural battery perform a single function (either energy storage or load bearing), however the overall composite is multifunctional, whereas in the latter all materials adopt multiple functions (i.e. energy storage and load bearing). Multifunctional structures are best known as type-I and type-II, whereas multifunctional materials are usually named type-III and type-IV structural batteries. Although higher mass savings are predicted for high | ||||
| 11:30 | 12:00 | 7.4.3 |
DOPAMINE-COATED UHMWPE/HYDROGEN-RICH BENZOXAZINE COMPOSITES FOR SPACE RADIATION SHIELDING J.-H. Cha¹, C.-G. Kim¹; ¹KAIST, South Korea Recently, COTS(commercial off-the-shelf) is being used as an electronic device for high performance and low cost of satellites. However, COTS is vulnerable to cosmic radiation. UHMWPE/hydrogen-rich benzoxazine composite(UHC) has excellent cosmic radiation shielding performance. A study was conducted to improve the mechanical properties of UHC and prove that it can be used as a satellite material. | ||||
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| 10:30 | 11:00 | 8.4.1 |
DEVELOPMENT OF INNOVATIVE AND ECO-FRIENDLY AIRFRAME TECHNOLOGIES TO IMPROVE AIRCRAFT LIFE CYCLE ENVIRONMENTAL FOOTPRINT – LIFE CYCLE ASSESSMENT ACTIVITIES AT ECOTECH / CLEANSKY 2 L.A.S.A Prado¹, T.S.G. Das¹, S. Coskun¹, A. Kötter¹; ¹Capgemini Engineering / Altran Deutschland und SAS KG, Germany Presenter: Luis Antonio Sanchez de Almeida Prado, Capgemini Engineering / Altran Deutschland und SAS KG The activities of ALTRAN as partner in ecoTECH, on the data collection at the flagship demonstration level developed during the consortium are addressed: • Metallic Fuselage • Thermoplastic Fuselage Panel • Thermoset wing/fuselage • Cabin Interior (Magnesium and Biomaterials) The data collection process is explained and an example for the achieved results is presented. The activities of ALTRAN as partner in ecoTECH, on the data collection at the flagship demonstration level developed during the consortium are addressed: • Metallic Fuselage • Thermoplastic Fuselage Panel • Thermoset wing/fuselage • Cabin Interior (Magnesium and Biomaterials) The data collection process is explained and an example for the achieved results is presented. The activities of ALTRAN as partner in ecoTECH, on the data collection at the flagship demonstration level developed during the consortium are addressed: • Metallic Fuselage • Thermoplastic Fuselage Panel | ||||
| 11:00 | 11:30 | 8.4.2 |
NUMERICAL MODELING OF FLUID-STRUCTURE INTERACTION OF A 3D WEDGE DURING WATER IMPACT WITH VARIATION OF VELOCITY AND PITCH ANGLE F. Valpiani¹, P. Cicolini¹, D. Esposto¹, A. Galletti¹, D. Guagliardo¹; ¹Politecnico di Torino, Italy Dynamic interactions related to structures impacting in water are a very complex problem to simulate numerically due to the multi-physics interaction between fluid and structure. Seaplanes, racing boats, re-entry module, and transport aircraft ditching are some examples of the areas that could benefit from Fluid-Structure Interaction (FSI) analyses. The aim of the present work is to extend the previously analysed scenarios of the three-dimensional structure (Fig. 1) by investigating the effects of water impacts with different initial conditions. In detail, it has been investigated the influence of horizontal velocity and pitch angle on the pressures developed in seaplane hulls during typical water landing conditions. The nominal reference conditions have been achieved from the work of the Flight Mechanics section of teams55. These landing conditions are then manipulated to generate a full impact case study useful to the investigation of possible structural failure criteria. The results of this kind of investigation would provide a better understanding of the impact phenomenon and enhance the structural design of the components in contact with water and subject to the impact generated stresses. | ||||
| 11:30 | 12:00 | 8.4.3 |
EFFICIENT SURROGATE-BASED MULTI-OBJECTIVE OPTIMIZATION ALGORITHM WITH A NEW ADAPTIVE WEIGHT VECTOR GENERATION Z. Lu¹, Z.-H. Han¹, Z. Zhou, Science and Technology on Scramjet Laboratory,CARDC, China; W.-P. Song¹, Y. Zhang¹; ¹Northwestern Polytechnical University, China This paper proposes an efficient surrogate-based multi-objective optimization algorithm with a new adaptive weight vectors generation. The experience study on numerical cases shows it is efficient, robust and has good capability of constraint handling to expensive multi-objective optimization. And it is applied to aerodynamic design optimization of hypersonic aircraft. | ||||
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| 10:30 | 11:00 | 9.4.1 |
DEVELOPMENT OF A CONCEPTUAL DESIGN TOOL TO PREDICT PERFORMANCE OF HYDROGEN FUELLED PRECOOLED AIRBREATHING ROCKET ENGINES G. Grimaldi, Politecnico di Torino, Italy For new propulsive architectures, such as precooled air-breathing rocket engines, no propulsive prediction models for a conceptual design phase are available. In this work, different models of increasing complexity are developed and validated based on SABRE by Reaction Engines Limited, showing good agreement with the available data published by the company. | ||||
| 11:00 | 11:30 | 9.4.2 |
LARGE EDDY SIMULATION OF RAMJET TO SCRAMJET TRANSITION T. Nilsson¹, C. Fureby¹; ¹Lund University, Sweden To develop airbreathing hypersonic flight systems knowledge about the reacting flow physics in the transition regime between ramjet and scramjet modes is needed. Reacting Large Eddy Simulations (LES) of the direct-connect ram-scramjet experiment by Fotia & Driscoll [J. Prop. Power, 28, 83] will here be described. The LES results and the experimental data will here be compared and jointly analyzed. | ||||
| 11:30 | 12:00 | 9.4.3 |
AEROPROPULSIVE CHARACTERIZATION OF THE HYPERSONIC CRUISER VEHICLE IN STRATOFLY PROJECT P. Roncioni¹, L. Cutrone¹, M. Marini¹; ¹CIRA, Italy The H2020 STRATOFLY Project is a highly-multidisciplinary project co-funded by the European Commission that combines technological and operative issues for hypersonic civil aircrafts and aims to study the feasibility of high-speed passenger stratospheric flight. The main objectives were to refine the design and the concept of operations of the former LAPCAT-II MR2.4 vehicle, and to reach the ambitious goal of TRL=6 by 2035 for the concept, considering that the crucial technologies of STRATOFLY MR3 vehicle may represent a step forward to reach the goal of future reusable space transportation systems, drastically reducing transfer time (i.e. antipodal flights in less than two to four hours), emissions and noise, and guaranteeing the required safety levels. STRATOFLY MR3 vehicle presents a highly integrated structure which is characterized by a complex waverider configuration with dorsal mounted propulsive subsystem. Aerodynamic forces and propulsive thrust are strictly interdependent and need to be calculated with complete simulations that consider both external and internal flow path and in addition the detailed combustion process and the pollutants emission. In this framework an aeropropulsive characterization of the MR3 hypersonic cruiser configuration was conducted in order to mainly compute and verify the amount of thrust required at cruise conditions (Mach=8). In order to do this both engineering tools (SPREAD) and detailed CFD computations have been conducted and several configurations of the combustion chamber have been analyzed. In particular, the aim of the present activity has been the aerodynamic characterization of the isolator part of STRATOFLY combustion chamber for what concerns its effect on the combustion process and, in particular, the possible back interaction with the air flow capturing operated by means of the intake part and, in general, to verify the correct capturing of air flow. This has been characterized by simulating a configurati | ||||
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| 10:30 | 11:00 | 10.4.1 |
ENVIRONMENTAL ASSESSMENT OF NOISE ABATEMENT APPROACH TRAJECTORIES E.M. Thoma¹, T. Grönstedt¹, E. Otero Sola, KTH, Royal Institute of Technology, Sweden; X. Zhao¹; ¹Chalmers University of Technology, Sweden The study focuses on the evaluation of noise abatement approach operations and their environmental impact. The assessment starts from some standard trajectories, namely the Continuous Descent Approach and the Low-Drag-Low-Power and the aim is to look into more advanced procedures, such as the Steep Approach and optimized trajectories. The procedures are designed for an A321neo and compared and evaluated for noise and emissions, using empirical and semi-empirical correlations. It is indicated that multidisciplinary design and adaptation to specific conditions are required for the assessment of these interdependencies for flight procedures. It will, furthermore, be demonstrated that trajectory optimization can result in significant improvement when aiming to minimize emissions and noise for specific areas, e.g. communities around the airport. | ||||
| 11:00 | 11:30 | 10.4.2 |
DESIGN OF A TYPICAL MANEUVERING PROCESS SIMULATION TEST CONTROL SYSTEM WITH CONTROLLABLE RUDDER SURFACE J.-F. Wang, China; H. Tan, China; H. Chen, China; S. Feng, China; M.-H. Wang, China In the real-time system, the single-axis high-precision control and multi-axis synchronous control are realized through PID combined with fuzzy control theory, and the design of typical maneuvering course simulation test system with controllable rudder surface is completed? | ||||
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| 10:30 | 11:00 | 11.4.1 |
A PREPARATORY RESEARCH FOR UAM COLLISION AVOIDACE USING ADSB S. Ahn¹, H. Choi¹, S. Kim¹, J. Kim¹, H. Ryu¹; ¹Korea Aerospace Research Institute, South Korea In order for UAVs to share airspace with pilot-on-board aircraft, it is necessary to accommodate the flight rules including collision avoidance. A five-year project has been completed as preparatory research for UAM. A two-seat airplane has been modified to a UAV. The flight test results show that a UAV system with collision avoidance capability based on ADSB has been successfully developed. | ||||
| 11:00 | 11:30 | 11.4.2 |
SAFE REINFORCEMENT LEARNING BASED MULTI-ROTOR COLLISION AVOIDANCE WITH UNEXPECTED OBSTACLES H.J. Ahn¹, C.S. Lim¹, D.W. Lee¹, H.C. Bang¹; ¹Korea Advanced Institute of Science and Technology(KAIST), South Korea This paper suggest the safe RL for a quadrotor collision avoidance. The main contribution of this paper are 1) introducing the convex safety filter to guarantee the non-collision flight with RL framework, and 2) using simplified depth image to make easier application of the RL framework generated through the simulation to the real world, and to reduce the calculation time. | ||||
| 11:30 | 12:00 | 11.4.3 |
INVESTIGATION OF SIMULATION FRAMEWORKS FOR THE EVALUATION OF AUTOMATED FLIGHT FUNCTIONS FOR EVTOL AIRCRAFT Y. Lemmens¹, C. Teirlink¹, A. Hegde¹, D. Pla Guerrero¹, G. Olivares², H. Shah²; ¹Siemens Digital Industries Software, Belgium ;²National Institute for Aviation Research, United States This study investigated and demonstrated a simulation framework that can be used to evaluate automated flight functions. The framework coupled Siemens Simcenter® software with the ROS-framework and hence can interact with its toolboxes. Multiple scenarios with the PX4-Avoidance algorithm were simulated in order to evaluate the functioning of the framework. | ||||
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| 10:30 | 11:00 | 12.4.1 |
SMART SKIN FOR AEW AIRCRAFT P. Khanal, Chalmers University of Technology, Sweden; P. Hallander¹, R. Luo¹; ¹Saab AB, Sweden A multifunctional fuselage structure has been developed. It provides the structural integrity necessary for smaller aircraft and permits the transmission of high-power microwave radiation characteristics for long-range surveillance radars. In particular, the solution permits a straightforward integration and allows for a curvature that improves buckling performance. | ||||
| 11:00 | 11:30 | 12.4.2 |
CERTIFICATION ASPECTS OF AN EARTH OBSERVATION PAYLOAD INSTALLED ON COMMERCIAL TRANSPORT AIRCRAFT R. Lopez Pereira, Safran Engineering Services GmbH, Germany; L. Rammos, Skyflox Sarl, Luxembourg The use of commercial transport aircraft as platform for carrying Earth Observation equipment is an innovative use of the existing aviation infrastructure. The challenges of developing a system with as little operational interference as possible to regular operation – have made the development and certification process of the ORCA project one of a kind. | ||||
| 11:30 | 12:00 | 12.4.3 |
DESIGN OF ELECTRONICALLY PHASE-TUNING REFLECTARRAY ANTENNA FOR AIRBORNE RADAR APPLICATION G. Kong, China; P. Cui, China; W. Du, China; R. Chen, China A electronically phase-tuning airborne radar reflectarray antenna is proposed in this paper. The antenna is based on variable capacitor, which can improve the beam-scanning speed of airborne radar antennas. The electronically phase-tuning airborne radar reflectarray antenna is designed in a sandwich form with faster phase-tuning speed. The antenna will be an good candidate for airborne radar. | ||||
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| 10:30 | 11:00 | 13.4.1 |
EXPECTED TEAMWORK ATTRIBUTES BETWEEN HUMAN OPERATOR AND AUTOMATION IN AIR TRAFFIC CONTROL Å. Svensson, LFV, Sweden; N. Rönnberg, Linköping University, Sweden In air traffic control, teamwork between controllers and automation is a key component to safely direct the aircraft. However, the willingness to accept automation relates to the purpose of the automation. Thus, this study presents how controllers want to work with an automated tool in the future and what qualities the automation should have. | ||||
| 11:00 | 11:30 | 13.4.2 |
PILOT’S ATTENTION DISTRIBUTION MODELING USING HIDDEN MARKOV MODELS J. Hanak¹, J. Vlk¹, P. Chudy¹; ¹Brno University of Technology, Czech Republic Presenter: Jiri Hanak This work is focused on fusion of the eye-tracking data with the flight variables acquired during simulated flight experiments. The flight data itself were collected in a series of experimental flight tasks performed by real pilots with a different level of experience. | ||||
| Reserve Paper | 13.4.R |
STRESSING SAFETY ASSESSMENT METHODS BY HIGHER LEVELS OF AUTOMATION L. Meyer¹, C. Bjursten Carlsson¹, Å. Svensson¹, M. Peukert¹, L. Danielson, SDATS, Sweden; B. Josefsson¹; ¹LFV, Sweden | |||||
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| 10:30 | 11:00 | 14.4.1 |
AERODYNAMIC DEVELOPMENT OF SAAB FCAS UNMANNED SUPERSONIC COMBAT AIRCRAFT M. Hackström¹, F. Kållberg¹, P. Nordström¹; ¹Saab Aeronautics, Sweden Presenter: Fredrik Kållberg, Saab AB The aerodynamic development in early stages of design of a supersonic design is performed. Various levels of Computational Fluid Dynamics tools and wind tunnel testing using extensive additive manufacturing techniques, is used. Benchmarking between methodologies is done. | ||||
| Reserve Paper (Interactive) | 14.4.R |
NUMERICAL SIMULATION OF MISSILE AIR-LAUNCHED DYNAMIC PROCESS UNDER DOWNWASH FLOW OF HELICOPTER ROTOR W.-Y. Zhou¹, G.-Q. Yang¹, X. Gao¹, X.-Y. Zhu¹, B.-X. Zhou¹; ¹AVIC Xi’an Flight Automatic Control Research Institute, China | |||||
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| 14:00 | 14:30 | 1.5.1 |
ICAS DIGITAL PIONEERING INITIATIVE AND SYSTEM OF SYSTEM CHALLENGES N. Nagel, Germany; C. Jouannet, Sweden The ICAS Digital Pioneering Initiative is set to establish new digital modes of sharing knowledge beyond written text and oral speech in the frame of ICAS. During the first Digital Pioneering Workshop, September 2-3, 2022, 50 participants discussed challenges of digital collaboration and worked out proposals for activities aiming at unfolding synergies within the community. This talk will explain the concept of the ICAS initiative and present the findings in the field of System-of-Systems. | ||||
| 14:30 | 15:00 | 1.5.2 |
CHALLENGES OF MULTIDISCIPLINARY DESIGN OPTIMIZATION FOR GREEN AVIATION P. Schmollgruber, France; I. Staack, Sweden The ICAS Digital Pioneering Initiative is set to establish new digital modes of sharing knowledge beyond written text and oral speech in the frame of ICAS. During the first Digital Pioneering Workshop, September 2-3-, 2022, 50 participants discussed challenges of digital collaboration and worked out proposals for activities aiming at unfolding synergies within the community. This talk will present the findings in the field of System-of-Systems Multidisciplinary Design Optimization and of Green Aviation. | ||||
| 15:00 | 15:30 | 1.5.3 |
POTENTIAL OF EXTENDED REALITY IN ENGINEERING AND CHALLENGES OF UNCONVENTIONAL VEHICLE DESIGN S. Bagassi, Italy; L. Boggero, Germany The ICAS Digital Pioneering Initiative is set to establish new digital modes of sharing knowledge beyond written text and oral speech in the frame of ICAS. During the first Digital Pioneering Workshop, September 2-3, 2022, 50 participants discussed challenges of digital collaboration and worked out proposals for activities aiming at unfolding synergies within the community. This talk will present the findings in the field of Extended Reality in Engineering and of the Design of Unconventional Vehicles. | ||||
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| 14:00 | 14:30 | 2.5.1 |
MORE ELECTRIC AIRCRAFT (MEA) SCALING ASPECTS AND WEIGHT IMPACT E. Holmgren¹, D. Haldar¹, L. Bertling Tjernberg, School of Electrical Engineering and Computer Science, KTH Royal, Sweden; A. Johansson, SAAB, Sweden; ¹KTH Royal Institute of Technology, Sweden This paper is about investigating the fuel consumption of passenger aircraft with conventional bleed-air driven Environmental Control System (ECS) and aircraft with equivalent electrical systems. A framework has been developed in MATLAB to run simulations under various conditions to study the passenger-scaling effect and impact of subsystem weight. | ||||
| 14:30 | 15:00 | 2.5.2 |
SIZING AND OPTIMIZATION OF A MORE ELECTRIC AIRCRAFT INTEGRATING SHORT-TERM INCREMENTAL TECHNOLOGIES T. Planès¹, S. Delbecq¹, V. Pommier-Budinger¹, V. Palanque¹, E. Bénard¹; ¹ISAE-SUPAERO, France This paper focuses on the sizing and optimization of a short-medium range aircraft architecture incorporating technological improvements available by 2030. FAST-OAD, an open source framework for overall aircraft design is used to size the architecture. Different optimizations are achieved and a life cycle assessment module is used to analyze the environmental performance of the aircraft. | ||||
| 15:00 | 15:30 | 2.5.3 |
IMPLEMENTATION OF WING ICE PROTECTION SYSTEM IN MORE ELECTRIC AIRCRAFT TECHNOLOGIES D. Haldar¹, E. Holmgren¹, A. Johansson¹; ¹KTH Royal Institute of Technology, Sweden More Electric Aircraft (MEA) technologies aim at reducing greenhouse gas emissions to make local and global air transport easier. This paper discusses the development of a tool to evaluate the Wing Ice Protection System (WIPS) power and fuel consumption of MEA airliners of any size and flight configuration. | ||||
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| 14:00 | 14:30 | 3.5.1 |
AEROSHAPE AND TRAJECTORY DESIGN OF NEXT GENERATION RE-ENTRY VEHICLES N. Montella¹, A. Aprovitola¹, L. Iuspa¹, G. Pezzella¹; ¹University of Campania , Italy The paper deals with the multidisciplinary design optimization (MDO) of a next generation re-entry vehicle. Several MDO techniques are considered to determine the optimal aeroshape able to perform a re-entry flight characterized by prescribed levels of convective heat flux. Optimization is formulated minimizing the total integrated thermal load, with an assigned maximum peak heating. The optimal aeroshape is provided and its aerodynamic performance are detailed. | ||||
| 14:30 | 15:00 | 3.5.2 |
A RAPID DESIGN METHOD FOR QUIET SPIKE OF SUPERSONIC TRANSPORT AIRCRAFT L.-W. Zhang¹, Z.-H. Han¹, J.-L. Qiao¹, Y.-L. Ding¹, Q. Chen¹, W.-P. Song¹; ¹Northwestern Polytechnical University, China Aiming at reducing severe sonic boom raised by supersonic aircraft, this paper proposes a new design method of quiet spike. Compared with the traditional method, one can obtain a quiet spike shape rapidly by using this method, and it can be applied to engineering. | ||||
| 15:00 | 15:30 | 3.5.3 |
“CONCORDE-NEO”: A BIOFUEL PROPELLED SUPERSONIC COMMERCIAL AIRCRAFT WITH CONCORDE CONFIGURATION M. Borghi¹, G. Clinca¹, F.A. D'Amico¹, F. Fornaseri¹, E. Versino¹; ¹Politecnico di Torino, Italy Application of the system engineering approach in a conceptual design of a supersonic commercial aircraft with Concorde configuration reducing the environmental impact with the usage of Biofuels. Performance improvements thanks to free flight concept, turbofan architecture, bleedless configuration and more-electric philosophy. Validation of the project with mission simulation (ASTOS). | ||||
| Reserve Paper | 3.5.R |
CONCEPT DESIGN OF A LOW BOOM SSBJ TO SATISFY SOCIAL ACCEPTANCE S. Horinouchi, SuperSonic Jet Planning Inc., Japan | |||||
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| 14:00 | 14:30 | 4.5.1 |
CAD DEFORMATION FOR THE CONSIDERATION OF AEROELASTIC EFFECTS P. Wegener¹, S. Keye¹; ¹DLR, Germany Wings of real aircraft deform elastically depending on the load and the flight situation. For the aerodynamic post-calculation of wind tunnel tests, an approach is presented as an alternative to mesh deformation, to transfer these deformations directly to the CAD model and to regenerate the mesh for the calculation. | ||||
| 14:30 | 15:00 | 4.5.2 |
AUTOMATIC FREE-FORM DEFORMATION AS GEOMETRIC PARAMETERIZATION FOR AERODYNAMIC DESIGN M.A.L. Matunaga, ITA - Instituto Tecnológico de Aeronáutica, Brazil; J.L.F Azevedo, IAE - Instituto de Aeronáutica e Espaço, Brazil An automatic Free-Form Deformation algorithm is presented in order to parameterize aeronautical configurations of interest. Results for 2-D and 3-D problems, for different aerodynamic parameters, such as, dihedral, span, sweep, twist and wing shape, are presented. The present tools can help engineers understand how FFD methods can be employed for aerodynamic shape optimization studies. | ||||
| 15:00 | 15:30 | 4.5.3 |
HEAT TRANSFER ENHANCEMENT BY SUSPENDED PARTICLES IN A TURBULENT SHEARLESS FLOW H.R. Zandi Pour¹, M. Iovieno¹; ¹Politecnico di Torino, Italy The present work investigates fluid-particle thermal interaction in a shearless turbulent mixing by means of direct numerical simulations. Particles are assumed to have sub-Kolmogorov size so that the point-particle paradigm can be used. We determine the dependence of the Nusselt number from the particle inertia, parametrized the the Stokes and thermal Stokes numbers. | ||||
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| 14:00 | 14:30 | 5.5.1 |
TRANSITIONAL FLOW MODELLING OF A HYBRID LAMINAR FLOW CONTROL AND VARIABLE CAMBER TRANSONIC TRANSPORT AIRCRAFT WING M.M. Jentys¹, C. Breitsamter¹; ¹Technical University of Munich, Germany Computational fluid dynamics (CFD) results and modelling approaches, considering transitional flow around an aircraft wing with a combined hybrid laminar flow control and variable camber system are presented in this contribution. The goal of the combination is an increase in aerodynamic efficiency, which is reflected by the CFD results using correlation based transition turbulence models. | ||||
| 14:30 | 15:00 | 5.5.2 |
REACTIVE CONTROL OF BYPASS TRANSITION IN A WING BOUNDARY LAYER J.M. Faúndez Alarcón¹, K. Sasaki¹, A. Hanifi¹, R. Larsson, Saab Aeronautics, Sweden; D.S. Henningson¹; ¹KTH Royal Institute of Technology, Linné FLOW Centre, Sweden This investigation deals with the numerical implementation of a data-driven method for reactive control in a NACA0008 boundary-layer. The aim of this work is to evaluate the performance of the controller in damping the flow disturbances and the effect that this has on decreasing the skin-friction by maintaining a laminar flow. | ||||
| 15:00 | 15:30 | 5.5.3 |
DIRECT NUMERICAL SIMULATIONS OF A THICK, ROTATING AIRFOIL AT A LOW REYNOLDS NUMBER T. Coelho Leite Fava¹, D. Henningson¹, A. Hanifi¹; ¹KTH, Sweden Direct Numerical Simulations of a rotating airfoil at Re=100,000, several angles of attack, and rotation speeds were performed. Rotation increased the reversal flow during separation and postponed the reattachment and transition. Lift was reduced, and drag was increased by rotation. Higher angles of attack and stronger separation enhanced the rotation effects. | ||||
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| 14:00 | 14:30 | 6.5.1 |
PRELIMINARY AERODYNAMIC WING DESIGN OPTIMISATION FOR WING-IN-GROUND EFFECT AIRCRAFT R. Jesudasan¹, R. Mariani¹, A. Hanifi¹; ¹KTH Royal Institute of Technololgy, Stockholm, Sweden Wing-in-Ground effect aircraft have become an interesting concept in the context of reducing the environmental footprint and increasing the speed of coastal transport. In this work, a shape optimisation framework is proposed using OpenMDAO, combining a parametric shape modeler OpenVSP, a low fidelity solver VSPAERO and NSGA-II to support the preliminary design of wing-in-ground effect aircraft. | ||||
| 14:30 | 15:00 | 6.5.2 |
ON THE APPLICABILITY ASSESSMENT OF VON KARMAN’S MOMENTUM THEORY IN PREDICTING THE WATER-ENTER LOAD OF V-SHAPED BODY Y. Lu, China; A. Del Buono, Italy; T. Xiao, China; A. Iafrati, Italy; J. Xu, China The present study is dedicated to implementing numerical analysis on a two-dimensional symmetric wedge and a three-dimensional cabin section with free fall water entry in order to investigate and build up kinds of relations on parameters, based on the transformation of conservation of momentum theory, such as maximal acceleration and the corresponding velocity. | ||||
| 15:00 | 15:30 | 6.5.3 |
AERODYNAMIC AND AEROTHERMODYNAMIC ASSESSMENT OF A LIFTING-BODY RE-ENTRY VEHICLE A. Aprovitola¹, N. Montella¹, L. Iuspa¹, G. Pezzella¹, A. Viviani¹; ¹University of Campania , Italy Design of future generation reusable re-entry vehicles is unavoidably dictated by the adopted re-entry strategy for thermal barrier, range, and cross-range managements, especially for lifting returns [1]. In this case, in fact, enhanced aerodynamic performances allow for a gentler aerothermal loading environment and with long range and wide cross-range re-entry trajectories. In this framework, the paper provides a detailed aerodynamic and aerothermodynamic analysis of a lifting-body aeroshape obtained by means of a multidisciplinary design optimization (MDO), where vehicle configuration and re-entry strategy are mutually integrated in the spacecraft design. Several Computational Fluid Dynamics (CFD) simulations are carried out to address the aerothermal loading environment (i.e., pressure and convective heat flux loads) the unconventional optimum lifting-body aeroshape must withstand during descent. Reynolds Average Navier-Stokes Simulation (RANS) with both perfect gas and thermo-chemical non-equilibrium air computations are addressed to assess the flowfield that takes place past the vehicle at low-speed (e.g., landing phase) and high-speed (e.g., hypersonic flight) conditions, respectively. Flowfield simulations are carried out on both multiblock structured and hybrid grids. Finally, force and moment coefficients are evaluated to build-up the aerodynamic database of the spacecraft and to address the vehicle static stability in both longitudinal and lateral-directional flight conditions. | ||||
| Reserve Paper (Interactive) | 6.5.R |
EFFICIENT MID-FIDELITY AERODYNAMIC MODELING OF A TILT-WING EVTOL FOR CONTROL APPLICATIONS D. Perdolt¹, D. Milz¹, M. May¹, M. Thiele, Technical University of Munich, Germany; ¹German Aerospace Center, Germany Presenter: Daniel Perdolt, German Aerospace Center Institute of System Dynamics and Control | |||||
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| 14:00 | 14:30 | 7.5.1 |
TI-6AL-4V ADDITIVE MANUFACTURING MEASURE OF QUALITY ACCORDING TO FATIGUE CRACK INITIATION VS. CRACK PROPAGATION C. Matias¹, A. Diskin¹, O. Golan, Afeka- Tel-Aviv Academic College of Engineering, Israel; A. Garkun², E. Strokin²; ¹Israel Aerospace Industries (IAI), Israel ;²The Israel Institute of Metals,, Israel Additive Manufacturing technology is facing implementation challenges for airframe production. This is mainly due to lack of generic economic quality control methods to detect defects that compromise fatigue strength. The study done by an experimental campaign with Micro-CT inspections & SEM/Fractographic failure analyses, presents defect characteristics to be detected, for Ti-6AL-4V PBF via SLM. | ||||
| 14:30 | 15:00 | 7.5.2 |
RVE-BASED HOMOGENIZATION OF ADDITIVELY MANUFACTURED POROUS METALS A. Alaimo¹, G. Mantegna¹, C. Orlando¹, D. Tumino¹, C.R. Vindigni¹; ¹Faculty of Engineering and Architecture Kore University of Enna, Italy The effect of size, number and spatial distribution of micro-voids on the stress-strain behaviour of additive manufactured AlSi10Mg is studied through numerical simulations using the Representative Volume Element approach. An in-house code is used to model a random porosity distribution inside the RVE; comparison with reference case studies are reported. | ||||
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| 14:00 | 14:30 | 8.5.1 |
AMPAIRE AND THE ELECTRIFIED PROPULSION JOURNEY (invited) S. Ying, AMPAIRE, United States AMPAIRE AND THE ELECTRIFIED PROPULSION JOURNEY | ||||
| 14:30 | 15:00 | 8.5.2 |
REALISTIC HYDROGEN-BASED SOLUTIONS FOR SUSTAINABLE AVIATION J.P. Clark, Universal Hydrogen, United States Airlines, aircraft manufacturers and propulsion solution providers are all under significant pressure from consumers, investors, and customers to reduce emissions and provide zero carbon emission flight. There is growing consensus that hydrogen as an energy source will play a key role in transforming aviation into a zero-carbon system over the next few decades. A recent study by McKinsey & Company found that “hydrogen – as a primary energy source for propulsion, either for fuel cells, direct burn in thermal (gas turbine) engines or as a building block for synthetic liquid fuels – could feasibly power aircraft with entry into service by 2035 for short-range aircraft.” In this presentation, I will provide details of a hydrogen fuel cell-electric motor-propeller driven regional aircraft that is currently under development at Universal Hydrogen Co. for introduction into service in 2025 and show how regional aircraft powered by green hydrogen are economically competitive on a cost per available seat-mile (CASM) basis with carbon-based fueled aircraft when the novel UH2 hydrogen storage and distribution system is employed. I will also discuss the fundamental challenges with using fuel cell-electric propulsion on larger aircraft, as well as the aircraft and propulsion system characteristics that ultimately determine the need to transition to direct combustion of hydrogen. | ||||
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| 14:00 | 14:30 | 9.5.1 |
PROPULSION SYSTEM INTEGRATION FOR A FIRST GENERATION HYDROGEN CIVIL AIRLINER? J. Huete¹, D. Nalianda¹, P. Pilidis¹; ¹Cranfield University, United Kingdom Presenter: Jon Huete, Cranfield University PROPULSION SYSTEM INTEGRATION FOR A FIRST GENERATION HYDROGEN CIVIL AIRLINER | ||||
| 14:30 | 15:00 | 9.5.2 |
SAND EROSION MODELING IN GENERIC COMPRESSOR RIG TESTING L.-Y. Jiang¹, X. Wu¹, Q. Yang¹; ¹National Research Council Canada, Canada Based on erosion coupon tests, a sand erosion model for 17-4PH steel was developed. The developed erosion model was validated against the results of compressor erosion tests from a generic rig and from other researchers. A high-fidelity computational fluid dynamics (CFD) model of the test rig was built, a user defined function was developed to implement the erosion model into the ANSYS CFD software, and the turbulent, two-phase flow-field in multiple reference frames was solved. The simulation results are consistent with the test results from the compressor rig and experimental findings from other researchers. Specifically, the sand erosion blunts the leading edge, sharpens the trailing edge, and increases pressure-surface roughness. A quantitative comparison with three other sand erosion models indicates that the developed model has performed adequately. | ||||
| 15:00 | 15:30 | 9.5.3 |
MULTI-PLATFORM APP-EMBEDDED MODEL FOR HYBRID AIR-BREATHING ROCKET-CYCLE ENGINE IN HYPERSONIC ATMOSPHERIC ASCENT S.E. Tsentis, Greece; V.G. Gkoutzamanis, Greece; A.D. Gaitanis, Greece; A.I. Kalfas, Greece Presenter: Spyros Tsentis, Aristotle University of Thessaloniki MULTI-PLATFORM APP-EMBEDDED MODEL FOR HYBRID AIR-BREATHING ROCKET-CYCLE ENGINE IN HYPERSONIC ATMOSPHERIC ASCENT | ||||
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| 14:00 | 14:30 | 10.5.1 |
HANDLING QUALITIES OF A DISTRIBUTED ELECTRIC PROPULSION AIRCRAFT D. Planas, ONERA & ISAE SUPAERO, France; C. Döll, ONERA, France; P. Pastor, ISAE SUPAERO, France The use of DEP creates several aero-propulsive interactions between the wing and the propulsion system which can be leverage for achieving increased performance. Several methods exist for the modelling of these aerodynamic-propulsive interactions that occur between the engines and the wing, however few research has been done regarding how the handling qualities and the controllability of the aircraft can be affected when modifying the placing and sizing of the different engines and actuators, or when undergoing typical situations like engine failures. This problem will be studied in order to propose a multidisciplinary design methodology for the design of the different actuators and engines at the same time as the control laws, for a distributed electrical propelled aircraft. | ||||
| 14:30 | 15:00 | 10.5.2 |
PRELIMINARY STUDY ON A DESIGN OF A RETURN FLIGHT TRAJECTORY OF A SUBORBITAL VEHICLE A. Kwiek¹, M. Figat¹, T. Goetzendorf-Grabowski ¹; ¹Warsaw University of Technology, Poland This paper presents outcomes of the study into return flight trajectory parameters of the tailless rocket plane to suborbital space tourist flights. This study focuses on the efficiency of control surfaces for high altitudes as well as the rocket plane's initial orientation to meet the mission requirements. | ||||
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| 14:00 | 14:30 | 11.5.1 |
UNMANNED AERIAL VEHICLE\\\\\\\'S TRAJECTORY OPTIMIZATION IN CONSTRAINED ENVIRONMENTS J. Novák ¹, P. Chudý¹; ¹Brno University of Technology, Czech Republic The range of multirotor Unmanned Aerial Vehicle (UAV) applications has grown significantly over the last decade. Varying mission requirements with respect to UAVs’ target location, payload capacity, speed or time of flight combined with environment constraints such as no--fly zone avoidance can be hard to satisfy without use of modern trajectory optimization techniques examined by this paper. | ||||
| 14:30 | 15:00 | 11.5.2 |
NUMERICAL MODELLING OF PITCHING WINGS FOR GUST MITIGATION W. Yuan¹, A. Wall¹, X. Zhang², D. Poirel²; ¹National Research Council (NRC) Canada, Canada ;²Royal Military College of Canada (RMC),, Canada Urban environments are aerodynamically challenging for unmanned air vehicles (UAVs) because of complex flow structures and high levels of turbulence encountered around buildings. Therefore, studies have started focusing on the effects that gusting has on UAV aerodynamic performance. This study develops gust modelling capabilities towards understanding the aerodynamic response and more specifically gust mitigation strategies for UAVs operating in gusty urban environments. In particular, a radial basis function is applied to a modified split-velocity method for the numerical modelling of pitching wings for gust mitigation. | ||||
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| 14:00 | 14:30 | 12.5.1 |
VISION-BASED LOCALISATION FOR AUTONOMOUS AERIAL NAVIGATION IN GNSS-DENIED SITUATIONS D. Sabel¹, A. Maki¹, T. Westin², D. Åsvärn²; ¹KTH Royal Institute of Technology, Sweden ;²Spacemetric AB, Sweden GPS-based aerial navigation can fail due to unintentional radio frequency interference, or malicious jamming and spoofing. Spacemetric cooperates with the Royal Institute of Technology (KTH) in Stockholm to tackle this problem using visual navigation. The paper presents results of ongoing research with image-based deep learning methods and an innovative approach to Terrain Referenced Navigation. | ||||
| 14:30 | 15:00 | 12.5.2 |
INNOONBOARD FOR IMPROVED IMAGE HANDLING IN AIRBORNE COASTAL RECONNAISSANCE – A PROJECT PRESENTATION D. Åkerman¹, O. Fästh, ST Airborne Solutions, Sweden; M. Persson, Unibap, Sweden; D. Sabel¹, D. Åsvärn¹; ¹Spacemetric, Sweden Presenter: Daniel Sabel, Spacemetric Air reconnaissance gives huge image data volumes, with data downlinks hard pressed to keep up. A way to solve this is to decrease the amount of data at source, i.e to de-select low-interest data already on board. Another way is to select important data for priority download. INNOONBOARD combines both methods, creating an on-board image data management system for coastal reconnaissance aircraft. | ||||
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| 14:00 | 14:30 | 13.5.1 |
MANUFACTURE OF LARGE-SCALE SPACE EXPLORATION COMPONENTS USING WIRE + ARC ADDITIVE MANUFACTURING C. Diao¹, E. Eimer¹, S. Mancini, Thales Alenia Space, Italy; S. Krishnaswamy¹, F. Schwarz¹, E. Pagone¹, J. Ding¹, S. Williams¹, Z. Pinter², F. Martina²; ¹Cranfield University, United Kingdom ;²WAAM3D, United Kingdom Cranfield University, Thales Alenia Space and WAAM3D believe that WAAM process has great potential and is the go-to process for manufacturing large-scale aerospace space exploration components. With the combination of multi-functional tool, intelligent tool path planning and FEA simulation, the cost and lead time can be significantly reduced and the sustainability can be significantly increased. | ||||
| 14:30 | 15:00 | 13.5.2 |
LATEST DEVELOPMENTS IN HIGH PRESSURE HEAT TREATMENT OF AEROSPACE COMPONENTS J. Shipley¹, A. Magnusson¹, C. Beamer, Quintus Technologyes LLC, United States; ¹Quintus Technologies AB, Sweden in-process heat treatment directly after the densification of materials (High Pressure Heat Treatment) has shown further improvements to material properties such as strength and fatigue resistance, facilitating weight savings and optimal performance. Further improving thermal treatments is a key focus area for aviation and space applications. | ||||
| 15:00 | 15:30 | 13.5.3 |
VIKA - CONCEPT OF A DIGITAL PLATFORM FOR IMPLICIT KNOWLEDGE AND VIRTUAL ASSISTANCE FOR ADDITIVE MANUFACTURED PARTS J. Steffen, HAW Hamburg, Germany The subject of the work is the conceptual elaboration of a virtual application that enables users in aircraft construction in the context of additive manufacturing to make important decisions for the component design process interactively and intuitively. The user can interact with a developed and integrated CMS-system and a virtual AI assistant. | ||||
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| 14:00 | 14:30 | 14.5.1 |
A FRAMEWORK FOR INNOVATION WITHIN AEROSPACE SEGMENT A.G. Slongo¹, C. Jochims Lau¹, G.L. de Oliveirra¹, B.M. Ramos¹, T.B. Volkman¹; ¹AEL Sistemas, Brazil This work presents an innovation framework that was developed in AEL Sistemas in order to motivate and incentivize research groups in the Aerospace and Defense field. The work was developed at AEL Sistemas, an Aerospace and Defense Brazilian company that designs, develops and manufactures products, providing maintenance and logistics supports for its clients. | ||||
| 14:30 | 15:00 | 14.5.2 |
INTEGRATE ONLINE QUERY&DEFENSE INTO PROJECT BASED LEARNING TO PROMPT ENGINEERING AUTHENTIC EXPERIENCES S. Sun, Civil Aviation University of China, China; R. Gong, University of Waterloo, Canada Presenter: shuguang SUN, Civil Aviation University of China As an effective student-centered pedagogical approach in improving students’ academic knowledge, teamwork skills, communication skills and leadership, Project Based Learning (PBL) has been widely adopted in engineering courses delivering during the last decades. However, there is a challenge for both the teachers and the students during the PBL: Most project results are fragile to their operation environment because of the students’ poor understanding of the engineering authentic problems and integrity requirements or even neglect these, while engineering complexity and functional integrity is essential characteristic in aviation and other safety related fields, engineering authenticity and integrity analyzation ability and habit are basic requirements for future aviation engineers. Taking navigation principles and systems course PBL as a case, use online query & defense challenge competition to promote the students to conduct in-depth discussion and analysis on the engineering authenticity and integrity requirements in the early stage of project implementation, so as to improve the students’ project participation and outcomes. Project outcomes are assessed and compared with no query & defense activities integrated ones, data are collected and analyzed, the test results show that the online query & defense pedagogical form can effectively help the students to improve their engineering authenticity and integrity thinking. | ||||
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| 16:00 | 16:30 | 1.6.1 |
NATO AVT-297 DEVELOPMENT OF A FRAMEWORK FOR VALIDATION OF COMPUTATIONAL TOOLS FOR ANALYSIS OF AIR VEHICLES (invited) J. Morrison¹, M. Nikbay, Istanbul Technical University, Turkey; E. Walker¹; ¹NASA Langley Research Center, United States Joseph Morrison NASA Langley Research Center, USA M. Nikbay Istanbul Technical University, TUR E. Walker NASA Langley Research Center, USA | ||||
| 16:30 | 17:00 | 1.6.2 |
CONNECTING SYSTEM DESIGN TO MODELING AND SIMULATION CAPABILITIES (invited) J.M. Luckring, NASA Langley Research Center, United States; S. Shaw, MBDA UK Ltd., United Kingdom; W.L. Oberkampf, WLO Consulting, Inc., United States; R. Graves, Air Force Research Laboratory, United States James M. Luckring NASA Langley Research Center, USA Scott Shaw MBDA UK Ltd., GBR William L. Oberkampf WLO Consulting, Inc., USA Rick Graves Air Force Research Laboratory, USA | ||||
| 17:00 | 17:30 | 1.6.3 |
SYSTEM LEVEL IDENTIFICATION OF CRITICAL UNCERTAINTIES TO ENABLE VALIDATION EXPERIMENTS D.N. Mavris¹, E.Y. Yarbasi¹, B. Bagdatli¹; ¹Georgia Institute of Technology, United States Dimitri Mavris Georgia Institute of Technology, USA Efe Y. Yarbasi & Burak Bagdatli Georgia Institute of Technology, TUR | ||||
| 17:30 | 18:00 | 1.6.4 |
OPEN PANEL DISCUSSION (invited) op panel, United States open panel discussion | ||||
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| 16:00 | 16:30 | 2.6.1 |
BOEING/SAAB CO-DEVELOPMENT PROGRAMME OF T-7A TRAINER - A JOINT DIGITAL JOURNEY (invited) D.C. Yates, Boeing, United States Presenter: Tomas Karlsson, Saab The T-7A program employs digital engineering that went from firm concept to first flight within 36 months while utilizing an advanced and digitized production line. The collaboration between Boeing and Saab has resulted in the design and development of two production representative jets. Contract award from the USAF has led to the ongoing engineering and manufacturing development phase. Series production of the T-7A Red Hawk advanced trainer aircraft system for USAF is next. | ||||
| 16:30 | 17:00 | 2.6.2 |
TOWARDS A SEAMLESS SIMULATION OF THE AIR TRANSPORT SYSTEM E. Moerland¹, A. Mancini¹, B. Nagel¹; ¹German Aerospace Center (DLR), Germany This work presents a framework for the systematic integration of all disciplines within air vehicle design, allowing for the seamless connection of disciplinary knowledge in a highly-scalable distributed multidisciplinary collaboration setting. Based on experiences gained, a roadmap towards simulating the entire design lifecycle of revolutionary air transport systems is provided. | ||||
| 17:00 | 17:30 | 2.6.3 |
CERTIFICATION DRIVEN DESIGN FROM STAKEHOLDERS’ NEEDS TO MDAO FORMULATION WITHIN AGILE 4.0 PROJECT M. Fioriti, Politecnico di Torino, Italy; C. Cabaleiro, DLR, Germany; T. Lefebvre, ONERA, France; P. Della Vecchia¹, M. Mandorino¹, S. Liscouët-Hanke², A. Jeyarai²; ¹Università di Napoli Federico II, Italy ;²Concordia University, Canada Whitin the Horizon 2020 Agile 4.0 research program several studies are performed to integrate certification disciplines in a Multidisciplinary Design Analysis and Optimization environment. Inside this framework, some tools have been developed to formalize and help the integration. The present paper describes the integration of noise, performance, and safety verification within a multidisciplinary design of a small regional aircraft with electrified on-board systems. Starting from the definition of a possible architecture of the virtual certification process for noise, performance and safety, the necessary disciplinary tools are identified together with possible multidisciplinary design problems. The results are then propagated up to the initial requirements as means of future validation. | ||||
| 17:30 | 18:00 | 2.6.4 |
DIGITAL COLLABORATIVE DESIGN: AN INNOVATIVE FRAMEWORK IN AERONAUTICAL EDUCATION Z. Cui¹, M. Luo¹, H. Liu¹, X. Sun¹, Z. Ji¹, Y. Hua, China Academy of Launch Vehicle Technology, China; ¹Beihang University, China A digital collaborative design framework is proposed to integrate design resources based on an enduring and evolutionary Authoritative Source of Truth. The framework can support aeronautical education in three modes. The application of the framework to single-course and multidisciplinary education has shown its effectiveness in providing innovative design practice in aeronautical education. | ||||
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| 16:00 | 16:30 | 3.6.1 |
INNOVATIVE URBAN AIR MOBILITY FROM THE PERSPECTIVE OF THE HAMBURG METROPOLITAN REGION D. Kloock-Schreiber¹, M. Swaid², V. Gollnick¹, A. Fay, HSU, Institute of Automation Technology, Germany; M. Niklaß²; ¹TUHH, Institute of Air Transportation Systems, Germany ;²DLR, Institute of Air Transportation Systems, Germany Several projects bundle a multitude of competences to develop UAM scenarios which are evaluated in terms of time, cost, noise, energy consumption, acceptance and the ease of integration. It considers societal interactions, legal frameworks, demand modeling, concept development, ground-based infrastructure, airspace organization and operation, as well as overall system modeling. | ||||
| 16:30 | 17:00 | 3.6.2 |
ESTIMATION OF EVTOL FLIGHT PERFORMANCE USING ROTORCRAFT THEORY Y. Fukumine¹, Z. Lei¹; ¹Suwa University of Science, Japan The purpose of this study is to investigate performance of the multicopter, and provide technical information for operational feasibility. The theory of helicopter was modified for the multicopter type eVTOL aircraft. Two representatives of the eVTOL aircraft were analyzed by the theory of rotorcraft aerodynamics based on the information available. | ||||
| 17:00 | 17:30 | 3.6.3 |
MIXED INTEGER NONLINEAR PROGRAMMING FOR EVTOL AIRCRAFT DESIGN AND OPTIMIZATION T. Jiang¹, M. Li¹, Y. Liu¹, Y. Zheng¹; ¹School of Aeronautics and Astronautics, Zhejiang University, China Presenter: Tianhong Jiang Due to the advantages in speed, efficiency and carbon emissions as compared to helicopters or ground vehicles, electric vertical take-off and landing (eVTOL) aircraft has great potentials in both military and civil applications. The goal of this paper is to design a four-seat tilt-duct eVTOL aircraft with possibly high energy efficiency. To enhance the overall aircraft level performance of the baseline configuration that is obtained via conceptual design and comprehensive sizing methods, we apply the Mixed Integer Nonlinear Programming (MINLP) to include both continuous design variables such as wing planform parameters and discrete design variables such as the number of ducted fans, the choice of energy system (lithium batteries, fuel cells, etc.), and the choice of tail configuration. In the full-length paper, the detailed design and optimization methods and results will be presented. | ||||
| 17:30 | 18:00 | 3.6.4 |
RESEARCH ON THE DESIGN OF UNMANNED AERIAL VERICLE FOR MINE INSPECTION Z.-K. Li¹, S.-G. Su, Aerospace Times Feihong Technology Co., Ltd. , China; Z.-Y. Li¹, F.-R. Li¹, G. Chao¹; ¹Northwestern Polytechnical University, China Presenter: Zhi-Yu Li, Northwestern Polytechnical University In order to ensure the safe production of mines, mining companies usually use a combination of manual inspection and online monitoring to conduct inspections on the mine tunnel environment and equipment operating status. Manual inspection has low efficiency, high labor intensity, and high degree of danger; online monitoring methods cover a small area, low maintenance efficiency, and high investment costs. Therefore, there is an urgent need for a flexible unmanned equipment that can replace personnel for mine inspections.This paper designs a mine inspection drone, which can complete inspection tasks in mines with complex environments and full of dangers. By combining the actual needs of mine inspections and the general principles of multi-rotor aircraft design, the design indicators for the use of mine inspection drones are proposed, and mine inspections are carried out on this basis. The HyperWorks is used to perform finite element analysis on the body structure and protective structure composed of carbon fiber composite materials. Then use CFD software to analyze the aerodynamic characteristics of the UAV, and obtain its parameters such as lift, drag, and pitching moment in the forward and lateral flow, as well as the flow field distribution in the hovering state.Finally, make a prototype of the test principle of the mine inspection drone. After debugging, the test flight is completed to check whether the principle prototype meets the technical requirements. | ||||
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| 16:00 | 16:30 | 4.6.1 |
EFFECT OF LES LENGTH SCALE AND NUMERICAL SCHEME IN HYBRID RANS-LES OF FREE SHEAR LAYER FLOWS S. Arvidson¹, M. Carlsson, Chalmers University of Technology, Sweden; S. Nilsson¹; ¹Saab Aeronautics, Sweden The effect of LES length scale and numerical scheme in hybrid RANS-LES of free shear layer flows is investigated using an unstructured compressible ?ow solver. It is concluded that the choice of LES length scale is vital for accurate predictions and that the RANS-to-LES grey-area can be much reduced which is very valuable in industrial aeronautical applications. | ||||
| 16:30 | 17:00 | 4.6.2 |
INVESTIGATION OF LEADING-EDGE VORTICES ON A TRIPLE-DELTA-WING CONFIGURATION USING SCALE-ADAPTIVE SIMULATION T. Di Fabbio¹, E. Tangermann¹, M. Klein¹; ¹Universität der Bundeswehr München, Germany Delta wings are used in variety of aerospace vehicles, such as highly swept wings of fighter aircraft and supersonic civil transport. The paper will focus in particular on the prediction of aerodynamic coefficients and on the analysis of the vortex-vortex and shock-vortex interaction to provide an advancement in the understanding of delta wing flow using scale-resolving simulation. | ||||
| 17:00 | 17:30 | 4.6.3 |
NUMERICAL INVESTIGATION OF HYPERSONIC TURBULENT BOUNDARY LAYERS WITH HIGH-TEMPERATURE EFFECTS D. Passiatore¹, L. Sciacovelli, ENSAM Paris, France; P. Cinnela , Sorbonne Université, France; G. Pascazio¹; ¹Politecnico di Bari, Italy In this work, we investigate the influence of high-temperature effects on compressible wall-bounded turbulence, by carrying out a DNS and LESs of a hypersonic turbulent flat-plate boundary layer, thermally and chemically out-of-equilibrium. The analysis aims at assessing the effects of thermochemical activity on turbulence, by means of a detailed investigation of turbulent statistics. | ||||
| 17:30 | 18:00 | 4.6.4 |
HYBRID RANS-LES MODELLING: SOME RECENT DEVELOPMENT AND AERODYNAMIC APPLICATIONS S.-H. Peng, Swedish Defence Research Agency, FOI, Sweden Presenter: Shia-Hui Peng, Swedish Defence Research Agency, FOI Hybrid RANS-LES methods exploit the merits of RANS (Reynolds-Averaged Navier-Stokes) and LES (Large Eddy Simulation) modelling approaches, enabling turbulence-resolving simulations with computing resources less demanding than full LES. Based on a set of involved research activities on hybrid RANS-LES modelling approaches, a comprehensive overview about recent development and applications are reported in this work, with primary focus on aerodynamic analysis industry relevance serving aeronautical applications. Along with a progressive maturation in engineering practice of using existing hybrid RANS-LES modelling approaches, new development has been driven by further enhancement of CFD simulation accuracy and improved modelling feasibility. Among others, the RANS-LES interface, which is regarded as a so-called “grey area”, has attracted particular attention in current studies for Grey-Area Mitigation (GAM) in order to enable reasonable LES-resolving capabilities over the interface in the LES region. Some recent effort made to develop the GAM method will be reported. Aerodynamic applications of hybrid RANS-LES method are exampled with unsteady aerodynamic flow simulations, severing aerodynamic analysis, flow control, aero-optic analysis and aero-acoustic analysis. By means of these demonstrated applications, the advantage and current limitations of hybrid RANS-LES methods in relation to further development are discussed. | ||||
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| 16:00 | 16:30 | 5.6.1 |
STABILITY OF A LAMINAR BOUNDARY LAYER OVER LOCALISED SURFACE INDENTATION E.R. Gowree, ISAE-SUPAERO, France; C.J. Atkin, University of East Anglia, United Kingdom Experimental evidence of the co-existence of both an artificially excited convective mode and a natural mode in a confined laminar separation bubble is presented. The naturally excited mode takes the form of a wave-packet which became clearer when wavelet transform was applied to hot wire measurements. This mode had a characteristic frequency centred at a Strouhal number approximately 1 based on the freestream velocity and length of the bubble. It appeared to grow rapidly both in time and space, where the linear spatial growth is similar to the artificial convective mode, suggesting that the noise introduced in the system by the feedback loop from the bubble oscillation triggers an amplifier dynamics. | ||||
| 16:30 | 17:00 | 5.6.2 |
ANALYSIS OF THE STABILITY OF MULTIPLE HELICAL VORTICES USING COMPLEX-STEP LINEARIZATION V.G. Kleine, ITA, Brazil; A. Hanifi¹, D.S. Henningson¹; ¹KTH, Sweden A system of external and internal vortices is created by some blade devices proposed to destabilize the tip vortices of helicopters. The stability of such systems of multiple helical vortices is studied in this work using a complex-step technique to linearize the equations. This investigation elucidate some of the mechanisms of stability of vortices created by rotors. | ||||
| 17:00 | 17:30 | 5.6.3 |
EXPERIMENTAL EVALUATION OF A PASSIVE FLOW-CONTROL DEVICE FOR A TILTROTOR AIRCRAFT A.R. Proenca¹, S.A. Prince¹, L. Banks-Davies¹, K.P. Garry¹; ¹Cranfield University, United Kingdom This paper presents an experimental investigation into tilt-rotor propeller/nacelle/wing flows, and the flow breakdowns that can lead to the phenomenon of whirl flutter. Preliminary results suggest that leading edge modified blades have the potential to provide a significant increase in performance for the baseline blade design. The final campaign is ongoing. | ||||
| 17:30 | 18:00 | 5.6.4 |
RESEARCH ON PRESSURE LOAD OF AN EMBEDDED JET NOZZLE H. Li¹, X. Wang¹, D. Yu¹, F. Liu¹; ¹Shenyang Aircraft Design and Research Institute, China An embedded nozzle was taken as the research object to study the steady-state and dynamic pressure load at the jet infiltration area. The CFD results show good agreement with the wind tunnel test data. The flow filed information release that the mixing of jet and external flow plays a key role on the dynamic load level. | ||||
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| 16:00 | 16:30 | 6.6.1 |
PREDICTING STEADY LIFT AND DRAG COEFFICIENT OF TANDEM AIRCRAFT USING PRANDTL’S EXTENDED LIFTING-LINE THEORY IMPLEMENTED UNDER ASWING R. Jan¹, J.-M. Moschetta¹, J.-P. Condomines, ENAC, France; ¹ISAE-SUPAERO, France The Steady form of ASWING’s extended non-linear LLT is recalled and benchmarked using both experimental and CFD data. A tandem configuration is used as a strong vortices interaction example with a low aspect ratio to present the benefit of such software to predict lift and drag coefficients of multiple lifting surfaces | ||||
| 16:30 | 17:00 | 6.6.2 |
ROTOR / ROTOR AERODYNAMIC INTERACTIONS - A GARTEUR ACTION GROUP R. Boisard¹, L. Lefevre¹, T. Zhang², G. Barakos², A. Visingardi, CIRA, Italy; F. Lößle³, A. Kostek³, T. Andronikos, NTUA, Greece; M. Keßler*, R. Wickersheim*, A. Colliº, G. Gibertiniº, A. Zanottiº; ¹ONERA, France ;²University Of Glasgow, United Kingdom ;³DLR, Germany ;*University of Stuttgart, Germany ;ºPolitecnico di Milano, Italy The paper presents the objectives of the GARTEUR Action Group HC/AG-25 project on Rotor – Rotor wakes interactions. The outcome of this study will be the experimental databases, and a better understanding of the physics of rotor / rotor interactional aerodynamics. | ||||
| 17:00 | 17:30 | 6.6.3 |
COMPARING POTENTIAL FLOW SOLVERS FOR AERODYNAMIC CHARACTERISTICS ESTIMATION OF THE T-FLEX UAV F. Yu¹, J. Bartasevicius¹, M. Hornung¹; ¹Technical University of Munich, Germany The FliPASED project aims to design an actively-controlled wing with a MDO toolchain to achieve drag reduction, and test the new design on the T-FLEX demonstrator. Accurate and fast predictions of aerodynamic characteristics is vital in this process. This paper discusses the applicability of low order aerodynamic tools to such aircraft while comparing them with a CFD tool and flight test data. | ||||
| 17:30 | 18:00 | 6.6.4 |
INVESTIGATION FLAPPING-FLIGHT AERODYNAMICS OF A ROBOTIC BIRD H.W.M. Hoeijmakers¹, L.H. Groot Koerkamp¹, L.D. de Santana¹, C.H. Venner¹, S. Stramigioli¹, J.L. Mulder¹, A. Brentjes¹, F. Gijsman¹, S.A. Hartman¹; ¹University of Twente, Netherlands The paper describes the analysis of the flow in the wake of the flapping wing of an ornithopter-type of robotic bird mimicking the Peregrine falcon. The aim of the experimental and computational analysis is to determine thrust and lift performance as function of dimensionless (scaling) parameters governing flapping flight. | ||||
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| 16:00 | 16:30 | 7.6.1 |
WING STATIC STRUCTURAL ANALYSIS AND EXPERIMENTAL TESTING OF A COMPOSITE 1:8 S55-X REPLICA G. Nicolosi¹, A. Lunghitano ¹, S. Lombardi ¹, T. Talamucci¹, A. Caivano¹, N. Simone¹, E. Cestino¹, V. Sapienza, Aeronautical Engineering Consultant, Italy; ¹Politecnico di Torino, Italy This work presents the designing process and the results of a Wing Static Test carried out on a scale replica of the seaplane S55-X mostly realized by twill carbon fiber. The aim is to test the aircraft structure strength to a 4G pull-up maneuver and validate the FE model. | ||||
| 16:30 | 17:00 | 7.6.2 |
ASSESSMENT OF FAILURE UNDER LONGITUDINAL COMPRESSION OF UNIDIRECTIONAL COMPOSITES WITH IN-PLANE FIBER MISALIGNMENT A.R. de Faria, ITA, Brazil Presenter: Alfredo Rocha de Faria, ITA This work employs a micromechanical theory, kinematic relationships and an incremental approach to describe the displacement field in individual unidirectional composite plies. The Ramberg-Osgood relations are used to correct degraded mechanical properties of the resin in the nonlinear regime. The Hashin-Rotem failure criterion and experimental data previously obtained validate the technique. | ||||
| 17:00 | 17:30 | 7.6.3 |
DAMAGE QUANTIFICATION ON COMPOSITE STRUCTURES USING NEURAL NETWORKS AND HYBRID DATA L.P.S. Ferreira¹, M.O. Yano², S. Silva², C.A. Cimini¹; ¹UFMG, Brazil ;²UNESP, Brazil This work aims to develop a damage classification model that can be trained with numerical and experimental data. A finite element model is adjusted to experimental data with Bayesian inference and used to simulate damaged conditions. A hybrid approach using experimental and numerical data is proposed to train a neural network and the remaining experimental data is used in the test phase. | ||||
| 17:30 | 18:00 | 7.6.4 |
TRIBOLOGICAL AND STRUCTURAL EVALUATION OF 3D PRINTED EPOXY RESINS G.C. Cristea¹, A. Stefan¹, K. Krawczyk, Joanneum Research, Austria; C.-E. Pelin¹, S. Ilina¹; ¹INCAS, Romania This paper aims to investigate the morpho structural behavior of 3D printed epoxy resin influenced by printing parameters, the periodic geometries of reactive materials, after the preliminary characterization of mechanical properties. The test specimens in this paper were made using reactive inkjet prototyping technology. The samples subjected to tribological tests were prototyped starting from a single layer and reaching a maximum of 6 layers. A batch of 6 samples with different periodic geometries was analyzed, evaluating the behavior of the material from a structural point of view. | ||||
| Reserve Paper (Interactive) | 7.6.R |
STUDY ON MECHANICAL PROPERTIES OF CARBON FIBER RESIN MATRIX COMPOSITE BOLTED JOINT STRUCTURE AT HIGH TEMPERATURE D. Wang, School of Aeronautics, Northwestern Polytechnical University, Xi, China; G.W. Li, School of civil aviation, Northwestern Polytechnical University, China; H.Y. Huang, School of Aeronautics, Northwestern Polytechnical University, China Presenter: Dong Wang, Northwestern Polytechnical University | |||||
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| 16:00 | 16:30 | 8.6.1 |
AEROELASTIC MODELING, LOADS ANALYSIS AND STRUCTURAL DESIGN OF A FIGHTER AIRCRAFT A. Voß¹, T. Klimmek¹; ¹DLR Institute of Aeroelasticity , Germany The DLR Future Fighter Demonstrator is a highly agile, supersonic aircraft. Based on a given conceptual design, this work focuses on the aeroelastic modeling, incl. structures, masses and aerodynamics. With these models, a comprehensive loads analysis is performed. To confirm the results, the aerodynamic panel methods (VLM and Zona51) are compared with higher fidelity results obtained from CFD. | ||||
| 16:30 | 17:00 | 8.6.2 |
LOADS ANALYSIS AND STRUCTURAL OPTIMIZATION OF A LONG-RANGE TRANSPORT CONFIGURATION WITH HYBRID LAMINAR FLOW CONTROL V. Handojo¹, T. Klimmek¹, T. Streit, DLR - Institute of Aerodynamics and Flow Technology, Germany; ¹DLR - Institute of Aeroelasticity, Germany One approach to reduce aerodynamic drag is hybrid laminar flow control. Such designs require different wing geometries compared to its turbulent counterpart, so that the different flight loads and the geometry itself might have an effect on the structural mass. This work focuses on the impact of a HLFC wing design on the flight loads and structural mass of a long-range transport configuration. | ||||
| 17:00 | 17:30 | 8.6.3 |
LATERAL GUST BEHAVIOUR OF AIRCRAFT INCORPORATING FLARED FOLDING WINGTIPS R.C.M. Cheung¹, H. Gu¹, F. Healy¹, D. Rezgui¹, J.E. Cooper¹; ¹University of Bristol, United Kingdom The Semi-Aeroelastic Hinge (SAH) concept enables higher aspect ratio wings without any increase in loads, resulting in more fuel efficient aircraft. This paper will consider two aspects of the SAH: i. transient response of the aircraft following release of the SAH and ii. response to lateral gusts. Numerical studies will investigate these aspects and their effect on aircraft performance. | ||||
| 17:30 | 18:00 | 8.6.4 |
SET-BASED DESIGN COORDINATION BETWEEN COUPLED SYSTEMS: A WING AERO-STRUCTURAL DESIGN PERSPECTIVE X. Chen¹, A. Riaz¹, M.D. Guenov¹; ¹Cranfield University, United Kingdom Presented in this paper is a novel, set-based method for design coordination between coupled systems. The research is motivated by the limitations of current point-based and set-based coordination approaches with regard to enabling collaborative and interactive design. The proposed method employs design space explorations and surrogate models to process each sub-system in parallel. A global design of experiment is then performed in the space of design variables except the coupled ones. For each design point, an optimization process is employed to guarantee system consistency. The result is a set of consistent and feasible solutions which contains the potential global optima. The proposed approach will be evaluated with a realistic wing aero-structural design problem. The result (a feasible set) is expected to be similar to the one produced by the benchmark studies using the traditional all-in-one setup. Compared with the all-in-one approach, the proposed method enables distributed and parallel computation of different disciplines. Compared with the point-based approach, the proposed method promises to be more interactive and flexible by providing multiple promising design solutions. | ||||
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| 16:00 | 16:30 | 9.6.1 |
LATTICE BOLTZMANN METHOD FOR BROADBAND NOISE PREDICTIONS ON A TURBULENCE-CASCADE TEST RIG INCLUDING SERRATED VANES M. Buszyk¹, L. Vienne², T. Le Garrec¹, J.-F. Boussuge², C. Polacsek¹, R. Barrier¹; ¹ONERA, France ;²CERFACS, France In order to reduce rotor-stator interaction noise on future high-bypass engines, silent OGVs have to be designed. This study will focus on noise predictions by means of weakly compressible and compressible lattice Boltzmann simulations, along with aerodynamic assessment. Computations will be performed on a full test rig including a grid generated turbulence interacting with a 7-vanes cascade. | ||||
| 16:30 | 17:00 | 9.6.2 |
OPTIMIZATION OF INSTALLED COMPACT AND ROBUST NACELLES USING SURROGATE MODELS F. Sánchez-Moreno¹, D. MacManus¹, J. Hueso-Rebassa¹, F. Tejero¹, C. Sheaf, Rolls Royce, United Kingdom; ¹Cranfield University, United Kingdom A method for aero-engine compact nacelle optimization in installed configuration is proposed using a single fidelity surrogate modelling approach based on Euler CFD data. Artificial neural networks and Kriging interpolation have been used as machine learning methods to model the design space and guide the optimization. The methodology accounts for design robustness at off-design operating points. | ||||
| 17:00 | 17:30 | 9.6.3 |
AEROACOUSTIC PERFORMANCES OF A LOW-NOISE AIRFOIL CASCADE WITH SERRATED LEADING EDGES: PREDICTIONS AND MEASUREMENTS C. Polacsek¹, M. Buszyk¹, R. Barrier¹, V. Clair², E. Salze²; ¹ONERA, France ;²LMFA, France This paper presents a collaborative work realized in H2020 InnoSTAT project devoted to the study of innovative stators for the reduction of turbofan noise. Leading edge serrations designed by Onera are implemented on the airfoils of rectilinear cascades tested in the KCA rig of ECL. PWL reductions of about 4-5 dB obtained by Onera's prediction methods are compared to the acoustic measurements. | ||||
| 17:30 | 18:00 | 9.6.4 |
EFFECT OF HEAT EXCHANGER INTEGRATION IN AERODYNAMIC OPTIMISATION OF AN AGGRESSIVE S-DUCT I. Jonsson¹, R. Ranman¹, A. Capitao¹, C. Xisto¹; ¹Chalmers Tekniska Hogskola AB, Sweden This work investigates the integration of compact heat exchangers for intercooling of a hydrogen-fuelled midsized commercial aviation engine. Preliminary results from an ongoing aerodynamic optimisation indicate that common penalties of intercooling, such as weight and ducting issues, can largely be avoided when utilising hydrogen as a heat sink. | ||||
| Reserve Paper | 9.6.R |
EFFECT OF TAILCONE SHAPE ON HOT STREAK PHENOMENA AND INFRARED SIGNATURE OF SERPENTINE NOZZLE WITH AFT DECK J.-Z. Fan¹, Q.-Z. Yang¹, X.-B. Du¹, H.-Q. Yang¹, Y.-B. He¹, Y.-Q. Shi¹; ¹Northwestern Polytechnical University, China | |||||
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| 16:00 | 16:30 | 10.6.1 |
AUTOMATIC TAKE-OFF AND LANDING OF A VERY LIGHT ALL ELECTRIC OPTIONALLY PILOTED AIRCRAFT S. Scherer¹, M. Speckmaier¹, D. Gierszewski¹, C. Mishra¹, A. Steinert¹, R. Steffensen¹, S. Wulf¹, F. Holzapfel¹; ¹Technical University of Munich,, Germany The proposed paper describes the development, testing and demonstration of an automatic take-off and landing (ATOL) system for a very light all-electric optionally-piloted aircraft. The system allows to control the aircraft during during approach, flare, ground run and take-off. Simulation results as well as real flight test data is presented. | ||||
| 16:30 | 17:00 | 10.6.2 |
LPV/LFR CONTROL FOR ACTIVE FLUTTER SUPPRESSION OF A SMART AIRFOIL MODEL R.L. Pereira, ITA, Brazil; P.J. González¹, F.J. Silvestre¹; ¹TU Berlin, Germany This paper focuses on a novel gain-scheduling state-feedback control strategy to cope with the active flutter suppression of a smart airfoil model. Unlike other gain-scheduled control approaches in the literature, this one allows combining the polytopic and linear fractional representations into a particular framework to increase the degrees of freedom of a control design. Finally, a smart airfoil model is used to show the effec- tiveness of the proposed control method. | ||||
| 17:00 | 17:30 | 10.6.3 |
LQR BASED DIGITAL AUTOPILOT FOR LIGHT SPORT AIRCRAFT J. Vlk¹, P. Chudy¹, M. Prustomersky¹; ¹Brno University of Technology, Czech Republic The core of this work is aimed at flight control laws synthesis built around the optimal control theory. The researched flight control laws originating from the proposed design process were integrated into an experimental digital Flight Control System.The paper introduces the evaluation of the designed automatic Flight Control System in the real flight experiments. | ||||
| 17:30 | 18:00 | 10.6.4 |
EXTENSION OF THE CAPABILITIES OF AN AUTOMATIC LANDING SYSTEM WITH PROCEDURES MOTIVATED BY VISUAL-FLIGHT-RULES S. Scherer¹, C. Mishra¹, F. Holzapfel¹; ¹Technical University of Munich, Germany The automatic flight capabilities of a CS-23 aircraft are enhanced by automating maneuvers, based on Visual-Flight-Rules (VFR), currently adhered by manned flight. The system presented is capable of guiding the aircraft to a predefined landing trajectory. The system was tested in SiL and HiL. Afterwards, the capabilities were demonstrated on an optionally piloted Diamond DA42 aircraft. | ||||
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| 16:00 | 16:30 | 11.6.1 |
FAULT DIAGNOSIS FOR SENSOR AND ACTUATOR OF HEXACOPTER UAV USING DUAL EXTENDED KALMAN FILTER Y.J. Kim¹, T.G. Kim¹, S.K. Kim¹; ¹Chungnam National University, South Korea This paper performs the fault diagnosis for the hexacopter attitude control system using a dual EKF. Fault detection and diagnosis (FDD) is conducted by using the analytical redundancy of angular rates. Two EKFs are designed for dynamics and kinematics, respectively. FDD of the IMU sensor and actuator is conducted using these EKFs. The performance of the FDD for several scenarios is verified. | ||||
| 16:30 | 17:00 | 11.6.2 |
CONTROL AUGMENTATION SYSTEM DESIGN FOR THE QUAD TILT-WING UAV VIA H-INFINITY STRUCTURE WITH GWO K.K. Deveerasetty¹, K. Oka¹, A. Harada¹; ¹Kochi University of Technology, Japan In this paper, we analyzed the stability and control of a Quad-Tilt-Wing (QTW) Unmanned Aerial Vehicle, especially on the McART3 developed by the Japan Aerospace Exploration Agency, and it can hover and high-speed cruise performance. Our main aim is to design a robust controller to the Control Augmentation System (CAS) for the QTW Unmanned Aerial Vehicle. To guarantee the stability of the CAS, a feedback controller is introduced based on the sensitivity function in the frequency domain using grey wolf optimization (GWO). The advantage of the controller is that robust and straightforward to design. The applied controller performance is validated using the MATLAB SIMULINK. The results suppress the oscillations compared with the existing control techniques. QTW-UAVs have both capabilities to perform like a helicopter or fixed-wing UAV. The advantage of using QTW-UAV is that it can vertical-take-off -landing (VTOL), high speed at cruise, and can carry large payloads. Like fixed-wing aircraft, it does not require long runways for landing and take-off. The propellers will not interrupt the slipstream during the hovering mode, accordingly producing the required lift. There is no restriction related to the placement of the propellers at the end of the wings. The propellers can be placed at the center of the wings or in suitable positions. However, the aerodynamic characteristics vary significantly by changing the angle of the tilt wing, and it causes difficulty in designing a robust flight controller. The designed flight controller has a conventional structure composed of a stability augmentation system (SAS) that feeds back attitude rates with only proportional and integral gains and a turn coordinator (TC) that produces filtered feedforward rudder deflection in response to input roll attitude commands. In the longitudinal motions, the SAS has two control gains, whereas, in the lateral motions, SAS consists of five gains. Aerodynamic c | ||||
| 17:00 | 17:30 | 11.6.3 |
OPTIMIZATION OF ENERGY CONSUMPTION IN THE TRANSITION STATE OF A QUAD-PLANE T. Goetzendorf-Grabowski¹, D. Kacik¹, K. Pobikrowska, Lukasiewicz Research Network – Institute of Aviation, Poland; J. Mieloszyk¹; ¹Warsaw University of Technology, Poland Presenter: Katarzyna Pobikrowska, ?ukasiewicz Research Network - Institute of Aviation The paper presents the problem of minimizing energy consumption by a UAV designed in the quad-plane configuration. The phase, which consumes a big amount of electric energy is the transition from the vertical to the horizontal flight. Therefore, the optimization of the profile of this phase is crucial to improve the performance characteristics. | ||||
| 17:30 | 18:00 | 11.6.4 |
FLIGHT VERIFICATION OF AUTOMATIC TRANSITION FOR QUAD TILT WING SMALL UAV K. Muraoka¹, M. Sato¹; ¹Japan Aerospace Exploration Agency, Japan This paper deals with the automatic transition methodologies for a QTW(Quad Tilt Wing) small VTOL UAV. Flight test was carried out and stable automatic full transition has been accomplished by the proposed algorithm which changed wing tilt angles and maintained the aircraft within the safe flight envelope coordinating existing auto-flight system. | ||||
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| 16:00 | 16:30 | 12.6.1 |
ELECTRICALLY POWERED LANDING GEAR SYSTEM FOR TRANSPORT AIRCRAFT TAXIING I. Berlowitz, IBAero Engineering, Israel The ACARE 2050 has set forth targets for the aircraft entering service in 2050 to reduce ground emissions, reduce noise pollution and save fuel costs. Aircraft taxiing today is performed through the use of engine thrust. The aviation industry is looking for an onboard e-solution for autonomous taxiing. | ||||
| 16:30 | 17:00 | 12.6.2 |
THE INFLUENCE OF THE MODEL PARAMETERS OF LI-ION BATTERIES ON THE WIRING HARNESS PERFORMANCE OF EVTOL AIRCRAFT S. Oberschwendtner¹, M. Hornung¹; ¹Technical University of Munich, Germany The influence of battery discharge characteristics on the performance of an eVTOL wiring harness are investigated. Based on the simulation framework provided by previous work, the performance of different aircraft configurations are calculated by applying different battery models. An optimal wiring harness is optimized for each case and the influencing parameters are identified and discussed. | ||||
| 17:00 | 17:30 | 12.6.3 |
ANALYSIS AND DEVELOPMENT OF INTEGRATED LOW-PRESSURE SHAFT GENERATOR A. Reinap¹, M. Genrup¹, R. Avellán², H. Mårtensson²; ¹Lund University, Sweden ;²GKN Aerospace, Sweden The work focuses on analysis and development of integrated low-pressure shaft generator in a geared twin-spool turbofan engine. It starts with manufacturing and evaluation of direct cooled hollow conductor coils, and has focus manufacturing, assembling and integration issues essential to machine design. The design is used to assess the features of power transfer between the turbo engine spools. | ||||
| 17:30 | 18:00 | 12.6.4 |
AN INTEGRATED CONTROL SCHEME FOR STARTER/GENERATOR SYSTEM IN MORE ELECTRIC AIRCRAFT H. Li, China; Z. Zhao, China; Z. Wan, China; L. Xu, China; S. Zhao, China; P. Sun, China The concept of the starter/generator systemas a promising approach has been widely accepted in aircraft. An integrated control scheme is proposed to regulate the engine and output voltage of aircraft when starter/generator operates in different modes. Extensive simulation results are provided to confirm the validity and effectiveness of the proposed control scheme for in more electric aircraft. | ||||
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| 16:00 | 16:30 | 13.6.1 |
STUDY OF THE COST EFFICIENCY AND LAMINATE QUALITY USING DIFFERENT MOULD-MAKING TECHNOLOGIES L. Loiodice¹, S. Grendene¹, T. Binetti¹, I. Boni ¹, F. Lovero ¹, R. Piani¹; ¹Politecnico di Torino, Italy The aim of this paper is to compare the different laminate qualities, studying the various mould-making technologies, exploring their building process, efficency and time-cost relationship. The intent is to issue the numerous qualities of those material for a small-medium number production. In particular, we will focus on MDF-milled moulds, AM (using FDM technology) and gelcoat and fiberglass. | ||||
| 16:30 | 17:00 | 13.6.2 |
A VALUE-DRIVEN QUANTITATIVE FRAMEWORK COUPLING AIRCRAFT DESIGN, MANUFACTURING AND SUPPLY CHAIN BY LEVERAGING THE AGILE 4.0 MBSE-MDO FRAMEWORK G. Donelli¹, J.M.G.D. Mello², F.I.K. Odaguil², T. Lefebvre³, N. Bartoli³, T. van der Laan, GKN Fokker, Netherlands; L. Boggero¹, B. Nagel¹; ¹DLR, Germany ;²Embraer, Brazil ;³ONERA, France The research activity proposed in this paper is framed within the context of the concurrent engineering applied to the complex aeronautical system development. The main objective of the paper is the simultaneous coupling of multiple domains, from the manufacturing to the production through the aeronautical supply chain, to achieve more competitive, sustainable and circular aeronautical systems: | ||||
| 17:00 | 17:30 | 13.6.3 |
REAL-TIME IDENTIFICATION OF USER ACTIONS IN COMPUTER-AIDED MANUFACTURING USING MACHINE LEARNING AND COMPUTER VISION B. Peukert¹, J. Vesterberg¹, J. Birberg, Saab AB , Sweden; ¹KTH, Sweden Presenter: Bernd Walter Peukert, KTH Within IntDemo-Flygplan we aim at improving the efficiency of CAM programming. In bigger aircraft projects with thousands of parts, the programming process can be a bottleneck. We introduces the groundwork for an expert agent to improve the knowledge transfer of experienced to new programmers. The envisioned expert agent guides the user through the CAM process by observing and cataloging user interactions with the CAM programming environment, and deriving in-situ suggestions to comply with established CAM workflows. | ||||
| 17:30 | 18:00 | 13.6.4 |
DOMAIN MODEL CONSTRUCTION METHOD OF AVIATION EQUIPMENT MANUFACTURING OPERATION MANAGEMENT L. Chen¹, X. Li¹, Z. Zhang¹, W. Huang¹, R. Wu¹, Y. Li¹; ¹AVIC Chengdu Aircraft Industrial (Group) Co., Ltd., China This paper constructed a domain model of aviation equipment manufacturing operation management, and proposed a reference application architecture of manufacturing operation management platform for aviation equipment manufacturing. Combined with the actual application requirements, the effectiveness and practicability of the proposed model and application architecture ware verified. | ||||
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| 16:00 | 16:30 | 14.6.1 |
OVERVIEW OF JAXA AND NASA COLLABORATION ON MANNED AND UNMANNED AIRCRAFT OPERATION INTEGRATION IN DISASTER RESPONSE A. Andreeva-Mori¹, J. Homola², M. Johnson², K. Kobayashi¹, Y. Okuno¹, P. Kopardekar²; ¹JAXA, Japan ;²NASA, United States Presenter: Marcus Johnson, NASA Since 2016, the Japan Aerospace Exploration Agency (JAXA) and National Aeronautics and Space Administration (NASA) have partnered to investigate and address the challenges related to the safe and efficient integration of UAS in disaster relief operations. The collaborative inter-agency work has focused on the integration of JAXA’s Disaster Relief Aircraft Information Sharing Network (D-NET) and NASA’s UAS Traffic Management (UTM) systems through simulation and testing with results and lessons learned that highlight an example solution with benefits to disaster response and more broadly to civil operations as well. | ||||
| 16:30 | 17:00 | 14.6.2 |
INTEGRATED UAS TRAJECTORY OPTIMIZATION FOR DISASTER RESPONSE RECONNAISSANCE MISSIONS A. Andreeva-Mori¹, J. Homola², M. Johnson², K. Kobayashi¹, Y. Okuno¹, P. Kopardekar²; ¹JAXA, Japan ;²NASA, United States JAXA and NASA have been collaborating on the integration of manned and unmanned aircraft in support of disaster response operations. This work details a UAS trajectory optimization algorithm and joint simulations applied to immediate disaster reconnaissance and their contributions to strategic mission planning, and discusses future applications in broader contexts of Advanced Air Mobility (AAM). | ||||
| 17:00 | 17:30 | 14.6.3 |
DLR DESIGN CHALLENGE 2022: DESIGN OF A NEXT GENERATION VTOL FIREFIGHTING AIRCRAFT (invited) J. Ritter¹, H. Kahlo¹, N. Mandry¹, A.G. Can¹, P. Modi¹, B. Knoblauch¹, J. Schneider¹, A. Stromayer¹, T. Dietl², P. Ratei², P. Shiva Prakasha², B. Nagel²; ¹University of Stuttgart, Germany ;²German Aerospace Center (DLR), Germany The DLR Design Challenge is an annual competition offered to German university students in aeronautical sciences. Facing the increasing threats of wildfires across the globe, this year’s request for proposals asks students to come up with future-oriented air vehicle, fleet and operations concepts for aerial firefighting. In this contribution, the winning team presents their innovative concept. | ||||
| 17:30 | 18:00 | 14.6.4 |
DESIGNING FOR SECURITY: A CYBERSECURITY INTRODUCTION FOR AEROSPACE EDUCATION K. Roush, United States The Aerospace industry is only just now seeing a push to translate and implement existing cybersecurity standards/practices. Many students have little/no exposure to aerospace cybersecurity concepts. This paper serves as a cursory introduction of topics with the purpose of exposing the next generation of aerospace engineers to key areas where cybersecurity concepts will prove essential. | ||||
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| 10:30 | 11:00 | 1.7.1 |
DYNAMIC PAIRWISE WAKE VORTEX SEPARATIONS FOR ARRIVALS USING PREDICTIVE MACHINE LEARNING MODELS L. Frigerio¹, I. De Visscher, Wake Prediction Technologies (WaPT), Belgium; G. Stempfel¹, R. Barragan Montes², C. Chalon Morgan²; ¹Euranova, Belgium ;²EUROCONTROL, Belgium Presenter: Lorenzo Frigerio, Euranova The potential encounter of wake vortices from a preceding flight is at the origin of the wake separation minima between aircraft on the final approach. The Dynamic Pairwise Wake Separation for Arrivals concept has been developed in order to safely reduce, when possible, wake separation minima between consecutive arrivals based on wake risk monitoring through the use of machine learning techniques. | ||||
| 11:00 | 11:30 | 1.7.2 |
FLIGHT SIMULATION TO SUPPORT SAFETY CASE FOR PAIR-WISE WAKE TURBULENCE SEPARATION ON DEPARTURES I. De Visscher, WaPT, Belgium; M. Langer¹, K. Bayram¹, T. Feuerle², P. Hecker², F. Rooseleer³, C. Chalon Morgan³; ¹2CACTUS partners GmbH, Germany ;²TU Braunschweig, Germany ;³EUROCONTROL, Belgium FLIGHT SIMULATION TO SUPPORT SAFETY CASE FOR PAIR-WISE WAKE TURBULENCE SEPARATION ON DEPARTURES | ||||
| 11:30 | 12:00 | 1.7.3 |
FLIGHT SIMULATION TO SUPPORT SAFETY CASE FOR PAIR-WISE WAKE TURBULENCE SEPARATION ON DEPARTURES (invited) M. Langer, Germany FLIGHT SIMULATION TO SUPPORT SAFETY CASE FOR PAIR-WISE WAKE TURBULENCE SEPARATION ON DEPARTURES | ||||
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| 10:30 | 11:00 | 2.7.1 |
ZONAL MODEL BASED AIRCRAFT PASSENGER THERMAL COMFORT COMPARATIVE STUDY S. Tarroc Gil¹, J. Schminder¹, A. Guerrero i Almirall, UptimAI, Czech Republic; J.I. Tarraga Prieto, MAHLE Electronics S.L.U, Slovenia; R. Vaz Linn, Federal University of Rio Grande do Sul, Brazil; ¹Linköping University, Sweden A Fractional Step Zonal Model solver is proposed, as an alternative to conventional CFD strategies, for carrying out aircraft cabin climatization coarse fluid simulations, capable of performing extensive comparative studies assessing the thermal comfort of passengers and crew during early stages of aircraft design. | ||||
| 11:00 | 11:30 | 2.7.2 |
AURALIZATION OF NOISE IN A VIRTUAL REALITY AIRCRAFT CABIN FOR PASSENGER WELL-BEING USING HUMAN-CENTRED APPROACH S. Santhosh¹, M.C. Moruzzi¹, F. De Crescenzio¹, S. Bagassi¹; ¹University of Bologna, Italy The noise contour in a commercial aircraft cabin plays an important role in the comfort of passengers. The aim of this paper is to integrate vibro-acoustic simulation results in the virtual aircraft cabin mock-up developed by importing the pressure and displacements map in the virtual model to visualize the results in a more effective way and auralize the sound as a part of the virtual cabin. | ||||
| 11:30 | 12:00 | 2.7.3 |
TRANSPORT AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM AIR QUALITY IMPROVEMENT I. Berlowitz, IBAero Engineering, Israel The paper objectives are to identify the sources and types of potential cabin air contamination, analyze the detection and filtration methods, design system architectures for a detection and filtering system, and assess the potential solutions in terms of effectiveness, maintainability, reliability, ease of installation, and compliance with existing regulations. | ||||
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| 10:30 | 11:00 | 3.7.1 |
SERIES OR PARALLEL HYBRID-ELECTRIC AIRCRAFT PROPULSION SYSTEMS? CASE STUDIES OF THE ATR42 AND ATR72 A. Batra¹, R. Raute, Dept. Ind. Elec. Power Conv., University of Malta, Malta; R. Camilleri¹; ¹Institute of Aerospace Technologies (IAT), University of Malta , Malta Aviation is expanding at a fast pace and is a major source of greenhouse gases. Flightpath 2050 strategy sets aggressive targets to reduce in flight CO2. Hybrid-Electric Propulsion (HEP) could be effective to reduce emissions in sensitive areas such as takeoff and landing. This paper compares effect that series and parallel HEP have on aircraft design and performance, energy demands and emissions. | ||||
| 11:00 | 11:30 | 3.7.2 |
DEVELOPMENT OF A HYDROGEN-POWERED FUSELAGE-MOUNTED BLI PROPULSOR ADD-ON FOR PASSENGER AIRCRAFT A. Heidebrecht¹, K. Burger¹, M. Hoogreef¹, R. Vos¹, A.T. Isikveren, SAFRAN S.A. c/o Aerospace Embedded Solutions GmbH, Munich, Germany; A. Gangoli Rao¹; ¹TU Delft, Netherlands The concept of a "Auxiliary Power and Propulsion Unit | ||||
| 11:30 | 12:00 | 3.7.3 |
TECHNOLOGY ROADMAP AND CONCEPTUAL DESIGN OF HYBRID AND ELECTRIC CONFIGURATIONS IN THE COMMUTER CLASS F. Nicolosi¹, V. Marciello¹, V. Cusati¹, F. Orefice¹; ¹University of Naples Federico II, Italy Presenter: Fabrizio Nicolosi, University of Naples Federico II The article presents the research work of Clean Sky 2 ELICA project which aims to trace a technological roadmap towards green aviation, using the Commuter A/C category as test bed. Design of two different 19-pax aircraft are presented, an aircraft with batteries, and a second one with H2 fuel cells. The emission reduction, whole energy, the cost and safety issues have been included in our study. | ||||
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| 10:30 | 11:00 | 4.7.1 |
EFFECTS OF TWO WINGLET TIP GEOMETRIES ON THE FLOW AND AERODYNAMIC PERFORMANCE OF A HYDRAULIC AXIAL TURBINE D.S. Tonon¹, J.T. Tomita¹, C. Bringhenti¹, D.F.C. Barbosa¹, L.H.L. Whitacker¹, L.E.N. Almeida, AVIBRAS, Brazil; ¹Aeronautics Institute of Technology , Brazil The use of desensitization techniques has proven to be an excellent strategy for reducing tip leakage. The objective of this work is to verify the effects of two Winglet geometries in a hydraulic axial turbine. The results obtained show that it is possible to improve the turbine efficiency depending on the geometry adopted. The work also presents an analysis regarding the cavitation phenomenon. | ||||
| 11:00 | 11:30 | 4.7.2 |
INVESTIGATION ON CRUISE PERFORMANCE OF A HAND-LAUNCHED SOLAR-POWERED UAV FOR ENVIRONMENTAL MONITORING IN TIBET K.-L. Wang¹, Z. Zhou¹; ¹Northwestern Polytechnical University, China Cruise performance of a solar-powered UAV in flying wing configuration is studied with and without consideration of the tractor propeller induced effects. Besides, two types of propeller (MIL and high-performance) are compared. It indicates that the use of high-performance propeller can improve the lift-to-drag performance of the aircraft to a certain extent when compared with the MIL propeller. | ||||
| 11:30 | 12:00 | 4.7.3 |
INVESTIGATION OF TWO-DIMENSIONAL VORTEX DYNAMICS IN THE V103 CASCADE Y. Zhao¹, Y. Liu¹, S. Zhu¹, H. Xu¹, D. Wang¹; ¹Department of Aeronautics and Astronautics, Fudan University, China The present studies indicate that the liutex can be applied to identify vortices at the strong shear regions and clearly reveal two-dimension complex vortex system structures both on the V103 suction and pressure surfaces. The budget analysis of Rz quantitively describes the generation mechanism of vortices from the shear, rotating and viscous effects. | ||||
| Reserve Paper | 4.7.R |
TWO-PHASE NUMERICAL SIMULATION INVESTIGATION ON THE EFFECTS OF TURBULENCE MODEL AND OPERATING CONDITIONS ON THE CENTRIFUGAL NOZZLE PERFROMANCE D. Mo¹, H. Lin¹, C. Liang¹, S. Shang¹, J. Xia, Aero Engine Academy of China, China; Y. Liu¹; ¹AECC Shenyang Engine Research Institute, China | |||||
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| 10:30 | 11:00 | 5.7.1 |
INTERNATIONAL SCIENTIFIC ASSESSMENT ON URBAN AIR MOBILITY AS A CONTRIBUTION TO FUTURE AVIATION STANDARDS (invited) C. Eschmann, DLR, Germany; D.L. Hackenberg, National Aeronautics and Space Administration (NASA), United States; C. Vidal, National Research Council Canada (NRC), Canada The paper describes the work of the International Forum for Aviation Research (IFAR) in the field of Urban Air Mobility (UAM) and the current development a scientific assessment. More than 80 experts worldwide are jointly developing a harmonized, non-biased international perspective that identifies the challenges to be addressed serving as a basis for regulators and authorities. | ||||
| 11:00 | 11:30 | 5.7.2 |
AN INTERNATIONAL RESEARCH PERSPECTIVE ON AIRSPACE INTEGRATION IN THE FRAMEWORK OF URBAN AIR MOBILITY (invited) A. Andreeva-Mori, JAXA, Japan; S. Sharma¹, S. Verma¹, B. Dziugiel, Lukasiewicz Research Network, Poland; D. Sziroczak, Budapest University of Technology and Economics, Hungary; ¹Ames Research Center, United States Urban and advanced air mobility operations offer both opportunities and challenges. This paper presents initial results from a scientific assessment conducted by IFAR experts on the airspace integration and Safety Management Systems (SMS) topics. Technology area overview and state of the art assessment identify differences and commonalities in different countries. Early and long-term use cases are discussed to provide background for the gap analysis performed. Leveraging existing technologies can help early integration, and it is possible related data and standards based around sUAS and automobiles could be leveraged to SMS for UAM operations. The needs for international standardization of integration with existing airspace users, intent sharing, navigation, surveillance, operation concepts and guiding rules are also discussed. | ||||
| 11:30 | 12:00 | 5.7.3 |
KARI-DLR DIGITAL COLLABORATION TO BUILD A MDAO SYSTEM FOR THE PRELIMINARY DESIGN OF HYBRID EVTOL AIRCRAFT S.-K. Paek, Korea Aerospace Research Institute, South Korea The plan of overall MDAO system development by KARI is explained. As the design tool of the MDAO system, such as the input/output definition of each component and control/data flow, CPACS and MDAx are selected. As CPACS has never been applied to eVTOL aircrafts, KARI-DLR cooperations are being made. MDAx by DLR, as a design tool of MDAO system combined with CPACS, is tested and discussed. | ||||
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| 10:30 | 11:00 | 6.7.1 |
WIND TUNNEL TESTS RESULTS AND PERFORMANCE OF THE MOTHIF BLOWN FLAP P. D'Alesio¹, G. Travostino¹, P. Planquart², G. Glabeke²; ¹Piaggio Aerospace, Italy ;²von Karman Institute, Belgium Piaggio Aerospace, in collaboration with Von Karman Institute and SONACA, thanks to the funding received from the Clean Sky 2 Joint Undertaking (JU), designed and tested an innovative blowing flap high lift device within the frame of the MOTHIF project, in order to increase STOL aircraft capability to take off from runaway shorter than 800m. This paper aims to present comprehensively the results of the blowing high lift device wind tunnel test campaign conducted at VKI during Summer 2021, in comparison with CFD-based design data: the blowing jet and its influencing parameters effects on aerodynamic coefficients is exposed, especially regarding lift augmentation. | ||||
| 11:00 | 11:30 | 6.7.2 |
A STUDY OF HIGH-LIFT DEVICES FOR LOW REYNOLDS NUMBER APPLICATIONS Y. Leng¹, K. Fayez, DELAIR, France; J.-M. Moschetta¹, M. Bronz, ENAC, France; ¹ISAE-SUPAÉRO, France This study was inspired by take-off and landing performance improvement of small unmanned aerial vehicles (sUAV). It focused on little researched low Reynolds nomber range and on simple actuation mechanism. Existing semi-empirical method was used to design a single- and double-slotted flap for a DAE 31 airfoil. Results from low-speed windtunnel test and URANS simulations are presented. | ||||
| 11:30 | 12:00 | 6.7.3 |
MULTI-OBJECTIVE AERODYNAMIC OPTIMIZATION OF 2D HIGH-LIFT DEVICE BASED ON DISTRIBUTED DEEP REINFORCEMENT LEARNING J.-H. Dai¹, P.-Q. Liu¹, L. Li¹; ¹Beihang University, China We propose a method based on distributed reinforcement learning to solve the multi-objective optimization problem of high-lift devices. The new method draws lessons from Pareto ranking rather than merging multiple objectives into a single objective, so that a more uniform Pareto leading edge can be obtained. Combined with transfer learning, this method can improve the optimization efficiency. | ||||
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| 10:30 | 11:00 | 7.7.1 |
A GLOBAL/LOCAL ELEMENT-WISE APPROACH FOR THE BUCKLING AND POST-BUCKLING ANALYSIS OF THIN MULTILAYERED STRUCTURES R. Augello¹, E. Carrera¹, A. Pagani¹, M. Petrolo¹; ¹Politecnico di Torino, Italy This paper presents a global/local approach for the nonlinear analysis of thin-walled composite structures. While the global model is built in NASTRAN, the local model is based on refined structural theories with superior computational efficiency and accuracy. The results prove the convenience of using higher-order models for the local domain to reduce computational overheads. | ||||
| 11:00 | 11:30 | 7.7.2 |
OPTIMAL DESIGN OF STIFFENED PANELS UNDER BUCKLING CONSTRAINTS: A DESIGN METHODOLOGY CONSIDERING CAD-BASED PARAMETERIZATION WITH SIMULTANEOUS LAYOUT AND SIZING OPTIMIZATION H. Rahman¹, R. De Breuker¹, S.G.P. Castro¹; ¹Delft University of Technology, Netherlands Stiffened panel is widely used in aerospace and marine applications owing to its higher stiffness and strength-to-weight ratio. Since these panels are thin walled structures, therefore they are more susceptible to fail under buckling loads. Optimization techniques have been employed to design stiffened panels with minimum weight whilst ensuring their enough resistance against buckling failure. The key factors which influence the optimal weight of a stiffened panel include the choice of material, panel and stiffeners sizing, stiffeners layout and the type of the stiffener. The layout parameters describe the arrangement of the stiffeners on the panel including their location and orientation. There exist various research studies in which the optimal stiffened panel design was achieved through layout optimization. The common trend in all these studies was the use of non-gradient based optimization techniques which are computationally expansive and therefore can allow only a very limited number of design variables. This shrinks the design space which ultimately limits the performance improvement. The probable reasons for using non-gradient based techniques are their easy implementation and to avoid the challenging task of calculating the shape gradients which are required because a change in the stiffener layout will change the shape of the stiffened panel. The motivation of the current research is to use gradient based methods for simultaneous layout and sizing optimization of stiffened panels under buckling constraints. Another challenge which is addressed here is the use of CAD-based geometry parameterization for the stiffened panels. An innovative design strategy for simultaneous layout and sizing optimization has been developed and employed on stiffened panels. The use of gradient based method opens up the design space which is currently restricted because of the use of non-gradient based methods and therefore great improvement in the structural performance of the s | ||||
| 11:30 | 12:00 | 7.7.3 |
INVESTIGATION OF BUCKLING RESPONSE OF CYLINDRICAL SHELLS USING 3D-PRINTING TECHNOLOGY C. Bisagni¹, E. Labans¹; ¹Delft University of Technology, Netherlands The 3D-printing techniques open broad possibilities for the design of aerospace structures. In this paper the buckling behavior of different configurations of 3D-printed cylindrical shells under axial compressive loads is studied, obtaining higher buckling loads and less sensitivity towards geometric imperfections compared to conventional cylindrical shells with the same weight. | ||||
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| 10:30 | 11:00 | 8.7.1 |
PARAMETER IDENTIFICATION BY UPDATING THE STRUCTURAL MODEL OF A UAV WITH FLEXIBLE WING T.R. De Paula¹, V.P. Fernandes¹, A.G.P. Sarmento¹, D.F.C. Zuñiga¹, A.G. Souza, Universidade de Lisboa, Portugal; R.G.A. Silva¹, L.C.S. Góes¹; ¹Aeronautics Institute of Technology, Brazil Presenter: Clecio Fischer, Aeronautics Institute of Technology In order to improve the flight mechanics model of a flexible aircraft, the objective of this work is to update the structural for the UAV, identifying properties for orthotropic materials, elastic axis and moment of inertia for each beam using MAC to assess whether the estimated parameters have been improved. | ||||
| 11:00 | 11:30 | 8.7.2 |
RESEARCH ON THE EFFECT OF THE PROCESS FIRST SHOT PEENING STRENGTHENING THEN SHOT PEENING FORMING ON FATIGUE STRENGTH OF 7050 HIGH-STRENGTH ALUMINUM ALLOY G.-W. Li¹, T.-H. Luo¹, H.-Y. Hang¹; ¹Northwestern Polytechnical University, China The experimental and simulation results show that the process of strengthening before forming can effectively avoid the stress concentration on the surface of the test parts, which improves the overall fatigue strength. Compared with 1.2mm pit diameter, the fatigue strength of 1.4mm pit diameter test piece is increased by 6.24%. | ||||
| 11:30 | 12:00 | 8.7.3 |
DESIGNING SUSTAINABLE AVIATION SOLUTIONS WITH DIGITAL TWIN APPROACH M. Grundström¹, S. Ferrari¹; ¹Tampere University, Finland DESIGNING SUSTAINABLE AVIATION SOLUTIONS WITH DIGITAL TWIN APPROACH | ||||
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| 10:30 | 11:00 | 9.7.1 |
FEASIBILITY STUDY OF SHORT SUBSONIC DIFFUSER CONCEPT FOR SUPERSONIC INLET H. Miki¹, J. Akatsuka¹, I. Kikura, Tokyo University of Agriculture and Technology, Japan; Y. Watanabe¹; ¹JAXA, Japan One of a direction of technology development of supersonic inlet is shortening a subsonic diffuser for reducing nacelle weight. Design concept for preventing flow separation was applied to inlet models, and its feasibility was discussed from results of CFD analysis and wind tunnel test in this study. | ||||
| 11:00 | 11:30 | 9.7.2 |
A STUDY ON THE DEVELOPMENT OF THE FLOW DISTORTION DOWNSTREAM OF AN S-DUCT INTAKE M. Migliorini¹, P.K. Zachos¹, D.G. MacManus¹, V. Monnier¹; ¹Cranfield University, United Kingdom This work quantifies the decay of the unsteady peak distortion levels downstream of the S-duct inlet planes. It highlights how the development of the flow distortion downstream of the S-duct intake cannot be ruled out independently from the conditions at the inlet of the intake since these can alter the inherent distortion. This is a step forward for the integration of the intake and aero-engine. | ||||
| 11:30 | 12:00 | 9.7.3 |
STUDY OF THE IMPACT OF AZIMUTHAL FLOW DISTORTION ON IN-DUCT ACOUSTIC PROPAGATION USING A MULTIMODAL FORMULATION B. Mangin¹, M. Daroukh¹, G. Gabard, LAUM, France; ¹ONERA, France The evolution of aero-engines towards UHBR architectures goes with a shortening of the nacelle length that is responsible for an important circumferential inhomogeneity of the flow. Such a distortion have a significant impact on the acoustic propagation inside the nacelle. This paper presents a fast and accurate multimodal method applicable to the computation of the acoustic field in such cases. | ||||
| Reserve Paper (Interactive) | 9.7.R |
NUMERICAL SIMULATION ANALYSIS OF INFRARED RADIATION AND ELECTROMAGNETIC SCATTERING CHARACTERISTICS OF DIFFERENT MIXERS R. Wang¹, Q. Yang¹, S. Zhang¹, K. Du, Guiyang Aero-engine Research Institute, China; ¹Northwestern Polytechnical University, China | |||||
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| 10:30 | 11:00 | 10.7.1 |
META-REINFORCEMENT LEARNING-BASED FAULT TOLERANT CONTROL FOR A QUADROTOR WITH A SEVERE LOSS OF ROTOR S.-H. Kim¹, Y. Jung¹, Y. Kim¹; ¹Seoul National University, South Korea This study proposes a design scheme to obtain an optimal fault-tolerant controller to deal with a severe actuator fault by leveraging a meta-reinforcement learning (meta-RL) technique. The meta-RL trains an outer-loop network to infer the faulty situation and help an inner-loop RL process to optimize the controller quickly. | ||||
| 11:00 | 11:30 | 10.7.2 |
FLIGHT CONTROLLABILITY ANALYSIS IN TIGHT FORMATION AND CRUISE FLIGHT FOR FUEL SAVING D.B. Rossato, Faculdade de Tecnologia SENAI , Brazil; K.H. Kienitz, Instituto Tecnológico de Aeronáutica, Brazil Using data obtained from the simulation of two similar medium size cargo aircraft in cruise and tight formation flight for fuel saving, the paper presents results about the flight conditions inside the vortex in order to contribute both to the definition of control strategies and to the specification of criteria of acceptance for regular flights. | ||||
| 11:30 | 12:00 | 10.7.3 |
DESIGN OF STABILITY AUGMENTATION SYSTEMS FOR A FLEXIBLE AIRCRAFT USING LQ OUTPUT-FEEDBACK CONTROL VIA LMI R.L. Pereira, ITA, Brazil; P.J. González¹, F.J. Silvestre¹; ¹TU Berlin, Germany This paper presents novel linear quadratic (LQ) output-feedback synthesis conditions for stability augmentation systems in a flexible aircraft. The proposed conditions have been formulated using the linear matrix inequalities (LMIs) theory to provide two different approaches: centralized and decentralized LQ with output-feedback framework. | ||||
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| 10:30 | 11:00 | 11.7.1 |
DOOR-TO-DOOR TRAVEL PLANNER FOR IMPROVED TRAVELER EXPERIENCE USING DIGITAL TWIN CONCEPT J. La¹, C. Bil¹, I. Heiets¹, K.A. Lau, Qatar Airways, Qatar; ¹RMIT University, Australia Presenter: Cees Bil, RMIT University A digital door-to-door air travel model will be developed for a long-distance trip, which is supported by digital technologies and digital tools. Specifically, this trip will cover a journey from Australia to Sweden. After the digital model development, real data and resources will be obtained to examine the functionality and efficiency of the door-to-door model in the simulation. | ||||
| 11:00 | 11:30 | 11.7.2 |
ENVIRONMENTAL AGENT-BASED MODELLING FOR A FIREFIGHTING SYSTEM OF SYSTEMS J.L. Lovaco¹, I. Staack¹, P. Krus¹; ¹Linköpings Universitet, Sweden The presented work describes the approach to wildfire spread simulations using an Agent-Based Model (ABM) and the Geographic Information System (GIS) to simulate scenarios at specific locations. This ABM will be used for simulation and study of firefighting SoS: design and optimization of tactics, aircraft constituent systems and their subsystems. | ||||
| 11:30 | 12:00 | 11.7.3 |
REQUIREMENTS-BASED GENERATION OF OPTIMAL VERTICAL TAKEOFF AND LANDING TRAJECTORIES FOR ELECTRIC AIRCRAFT C. Krammer, Germany; F. Schweighofer, Germany; D. Gierszewski, Germany; S.P. Scherer, Germany; T. Akman, Germany; H. Hong, Germany; F. Holzapfel, Germany We present an automated process for generating trajectories considering regulatory requirements and associated operational procedures while optimizing for energy efficiency. The corresponding optimal control problems are derived automatically from a flexible trajectory definition database expressing the constraints and operational requirements for vertical takeoff and landing trajectories. | ||||
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| 10:30 | 11:00 | 12.7.1 |
UK-AEROSPACE RESEARCH CONSORTIUM - EXPANDING THE VALUE OF UK ACADEMIC RESEARCH (invited) R. Gardner, UK - Aerospace Research Consortium, United Kingdom; I. Gray, Cranfield University, United Kingdom The UK-Aerospace Research Consortium was set up in 2020 to coordinate and expand the UK academic research community. Its aim is to strategically support the initiation of excellent collaborative aerospace research that aligns with industry needs. The growing UK consortium is working to leverage international academic relationships for mutual benefit. | ||||
| 11:00 | 11:30 | 12.7.2 |
MAXIMISING VALUE FROM UK ACADEMIC RESEARCH - THE UK-AEROSPACE RESEARCH CONSORTIUM THEME APPROACH (invited) R. Gardner, UK-Aerospace Research Consortium, United Kingdom This paper explains how the UK-ARC is analysing the state of lower TRL aerospace research in the UK. Six academic theme groups have been set up to look at the state-of-the-art in technology and operational research as well as capabilities required for the future. Resulting research narratives will be worked through with industry and international experts to determine optimal research pathways. | ||||
| 11:30 | 12:00 | 12.7.3 |
THE BENEFIT OF BILATERAL RESEARCH NETWORKS - THE SARC AND BARINET INITIATIVES AND THE BRAZILIAN SWEDISH COLLABORATION IN AERONAUTICS E. Villani, Aeronautics Institute of Technology (ITA), Brazil; P. Krus, Linköping University, Sweden; V.J. de Negri, Federal University of Santa Catarina (UFSC), Brazil; L. Pereira, Federal University of ABC (UFABC), Brazil; G. Caurin, University of São Paulo (USP), Brazil In this paper the creation and maintenance of a bilateral network is presented. Sweden and Brazil have a long standing relation stretching far beyond aeronautics. However, it was intensified with the acquisition of the Swedish Saab Gripen combat aircraft for the Brazilian Air force. This led to an intense build-up of industrial collaboration and in the wake of this, also a bilateral academic network was formed to both take advantage of this, as well as support the process and encourage spin-off effects to other parts of society. To be sustainable it is argued that a network needs the right support and encouragement to be able to grow organically in a sustainable way, based on personal relations. Once this is in place, an academic bilateral network can be formed that can be maintained effectively over time at a low cost. | ||||
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| 10:30 | 11:00 | 13.7.1 |
MOTION STROKE DESIGN ON FLEXIBLE ASSEMBLY TOOLING FOR MULTIPLE AIRCRAFT COMPONENTS F. Guo¹, C. Song¹, X. Zhang², Q. Xiao²; ¹University of Science and Technology Beijing, China ;²AVIC Manufacturing Technology Institute, China For multiple aircraft components, the optimal design on flexible assembly tooling system was studied in this paper. Firstly, a new motion stroke and layout optimization process of flexible locators was proposed, and eleven steps were contained and modelled. Then The proposed method was verified on different leading edge flap components, and benifit results were gained. | ||||
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| 10:30 | 11:00 | 14.7.1 |
NON-INTRUSIVE AEROTHERMAL CHARACTERIZATION OF SURFACE HEAT EXCHANGERS FOR TURBOFAN AEROENGINES A. Broatch¹, J. García-Tíscar¹, A. Felgueroso¹, M. Gelain², A. Couilleaux²; ¹Universitat Politecnica de Valencia, Spain ;²Safran Aircraft Engines, France Presenter: Jorge García-Tíscar Non-intrusive measurement techniques (PIV, LDA, LDV, IR thermography) have been successfully applied to determine the aerothermal performance of a turbofan surface heat exchanger in a new reduced-scale facility, which reproduces the flow conditions of the actual bypass duct. This will facilitate the development and validation of this key thermal management technology for future aeroengines. | ||||
| 11:00 | 11:30 | 14.7.2 |
ZONAL MODEL VALIDATION FOR AN ENVIRONMENTALLY FRIENDLY AIRCRAFT CARGO FIRE PROTECTION SYSTEM WITH CONTAINERIZED LOAD A. Pathak¹, M. Pschirer¹, M. Kienberger¹, V. Norrefeldt¹; ¹Fraunhofer IBP, Germany Due to the high ozone depletion potential of this chemical, alternative solution to Halon as cargo fire suppression agent are researched. The cargo bay in the Flight Test Facility has been equipped with a nitrogen fire suppression system. Test data for containized load is used to validate a zonal model predicting the local distribution of agents in the cargo hold. | ||||
| Reserve Paper (Interactive) | 14.7.R |
STUDY ON OIL-GAS TWO-PHASE FLOW CHARACTERISTICS IN AIR-OIL HEAT EXCHANGER X. Pang¹, H. Sui¹, X. Jiang¹, G. Liu¹; ¹AECC, China | |||||
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| 13:55 | 14:25 | 1.8.1 |
TOWARD DIRECT DRIVE ELECTRIFIED PROPULSION CONCEPTS FOR SUSTAINABLE AVIATION (invited) C. Tschida, United States By focusing on a proven 100-passenger aircraft and flights of less than one hour, the Wright Spirit addresses the world’s key city pairs, such as Frankfurt-Paris, New York-Boston, and Seoul-Jeju. The Wright Spirit presents an opportunity to impact the short-haul end of the single-aisle fleet and pushes forward the long-term goal of a zero-emissions single-aisle commercial aircraft. | ||||
| 14:25 | 14:55 | 1.8.2 |
REGIONAL AIR MOBILITY MARKET STUDY (invited) C.Y. Justin¹, D.N. Mavris¹; ¹Georgia Institute of Technology, United States Recent years have shown renewed interest in regional air mobility. Efficiency improvements brought by electric powertrains have brought optimism amongst operators. We investigate if technologies and revamped concept of operations are sufficient to re-energize this segment. We quantify the demand for operations from underutilized regional airports and assess the demand for these electric aircraft. | ||||
| 14:55 | 15:25 | 1.8.3 |
UPDATE ON SUBSONIC SINGLE AFT ENGINE (SUSAN) ELECTROFAN TRADE SPACE EXPLORATION R. Jansen¹, C.C. Kiris², T. Chau², L. Machado², T.P. Dever¹, J.S. Litt¹, J.J. Arthur³, M.N. Lynde³, J.W. Chapman¹, J.L. Kratz¹, M.G. Turner¹, A. Mirhashemi¹, C.L. Denham³, J.M. Wishart*, K. Mahavier*, M.J. Boucherº, N. Heersemaº, E.J. Stalcup¹; ¹NASA Glenn Research Center, United States ;²NASA Ames Research Center, United States ;³NASA Langley Research Center, United States ;*Volpe National Transportation Systems Center, United States ;ºNASA Armstrong Research Center, United States A trade space exploration of a new NASA regional transport aircraft concept called the SUbsonic Single Aft eNgine (SUSAN) Electrofan is presented. The SUSAN concept uses a 20MW Electrified Aircraft Propulsion (EAP) system to enable advance Propulsion Airframe Integration (PAI) in transport category aircraft. This paper presents the status of the trade space exploration; however the concept definition is not finished. | ||||
| 15:25 | 15:55 | 1.8.4 |
EUROPEAN AVIATION RESEARCH AND INNOVATION TOWARDS CLIMATE NEUTRALITY (invited) M. Kyriakopoulos, Belgium EUROPEAN AVIATION RESEARCH AND INNOVATION TOWARDS CLIMATE NEUTRALITY | ||||
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| 13:55 | 14:25 | 2.8.1 |
A CREDIBILITY-BASED CRITERION FOR THE ASSESSMENT OF FUTURISTIC AIRCRAFT CONCEPTS N.F.M. Wahler¹, L. Radomsky², L.V. Hanisch², R. Mallwitz², M. Henke², A. Elham¹; ¹University of Southampton, United Kingdom ;²TU Braunschweig, Germany Presenter: Nicolas Wahler, University of Southampton Novel (hybrid-)electric aircraft designs often use assumptions for future performance of crucial design parameters. These estimations can vary widely between studies, making a judgment of the design feasibility and comparisons between designs difficult. This study proposes a criterion to assess the credibility of main component performance estimations and a proposed futuristic aircraft concept. | ||||
| 14:25 | 14:55 | 2.8.2 |
INSTALLATION PENALTY OF AERO-ENGINES ON NARROW BODY AIRCRAFT T.E. Boogaart¹, M.F.M. Hoogreef¹, A. Gangoli Rao¹; ¹Delft University of Technology, Netherlands A major factor for improving engine fuel consumption has been the increase of bypass ratio. However, this has significant impact on engine dimensions and weight, and installation of the engine on the airframe. This article investigates the performance impact of installation penalties from an increase in bypass ratio on narrow body aircraft, specifically the fuel consumption, weight and stability. | ||||
| 14:55 | 15:25 | 2.8.3 |
FAST-OAD-GA: AN OPEN-SOURCE EXTENSION FOR OVERALL AIRCRAFT DESIGN OF GENERAL AVIATION AIRCRAFT F. Lutz¹, J. Jézégou¹, A. Reysset, INSA Toulouse, France; A. Busteros-Ramos¹, V. Pommier-Budinger¹; ¹ISAE-SUPAERO, France This paper presents FAST-OAD-GA, an open-source extension of FAST-OAD that completes its aircraft design techniques with general aviation (GA) specific models to enable the preliminary sizing of aircraft regulated by the EASA CS-23. The FAST-OAD framework is introduced along with the models added by FAST-OAD-GA for GA aircraft sizing and the upcoming changes to model innovative architectures. | ||||
| 15:25 | 15:55 | 2.8.4 |
THE USE OF COMPUTATIONAL FLUID DYNAMICS METHODS IN THE PRELIMINARY DESIGN OF A NEW GENERATION LIGHT COMBAT AIRPLANE L. Kiszkowiak¹, A. Olejnik¹, A. Dziubinski, Lukasiewicz Research Network – Institute of Aviation, Poland; ¹Military University of Technology, Poland In the following paper the basic design assumptions of a new generation light combat airplane have been presented. What is more, the results of the aerodynamic characteristics identification process of the newly designed object were presented. Aerodynamic analysis was performed using specialized software based on solving partial differential equations using the Finite Volumes Method. | ||||
| Reserve Paper | 2.8.R |
CONCEPTUAL DESIGN OF FUTURE MILITARY AIR SYSTEMS - AN EDUCATIONAL APPROACH V. Gollnick¹, B. Muth, TU Braunschweig, Germany; T. Weber¹, K. Scheibe, HAW Hamburg, Germany; M. Grünewald, FH Aachen, Germany; E. Aydin¹; ¹TU Hamburg, Germany | |||||
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| 13:55 | 14:25 | 3.8.1 |
A SCALABLE HYDROGEN PROPULSION SYSTEM FOR CIVIL TRANSPORT AIRCRAFT A.S.J. van Heerden¹, S. Sasi¹, R. Ghelani¹, D. Sanders¹, I. Roumeliotis¹; ¹Cranfield University, United Kingdom The aim of this paper is to introduce a concept for a ‘scalable’ hydrogen propulsion system for future civil transport aircraft. This system could potentially aide in managing some of the risk associated with the major uncertainty involved in hydrogen technology development for aviation. This paper covers the conceptual design of the aircraft as well as selected transient system analyses. | ||||
| 14:25 | 14:55 | 3.8.2 |
AUTOMATED HYBRID PROPULSION MODEL CONSTRUCTION FOR CONCEPTUAL AIRCRAFT DESIGN AND OPTIMIZATION M. Fouda¹, E.J. Adler², J.H. Bussemaker¹, J.R.R.A. Martins², D.F. Kurtulus, Middle East Technical University, Turkey; L. Boggero¹, B. Nagel¹; ¹DLR, Germany ;²University of Michigan, United States A framework for aircraft-level evaluation of hybrid-electric propulsion system architectures is presented. Architectures are defined modularly and flexibly to enable dynamic generation of architectures in an optimization loop. Evaluation includes mission simulation using OpenConcept and overall aircraft sizing using OpenAD, and is demonstrated using a regional tuboprop aircraft. | ||||
| 14:55 | 15:25 | 3.8.3 |
DESIGN AND PERFORMANCE OF LIQUID HYDROGEN FUELLED AIRCRAFT FOR YEAR 2050 EIS C. Xisto, Chalmers University of Technology, Sweden; A. Lundbladh, GKN Aerospace AB, Sweden Presenter: Anders Lundbladh , GKN Aerospace In the present paper we investigate year 2050 low-risk tube and wing aircraft with LH2 tanks mounted above the fuselage. The paper aims at providing a reasonable estimate of the upper efficiency levels set by low-weight rigid cell foam insulated tank technology when integrated in a conventionally shaped airframes. | ||||
| 15:25 | 15:55 | 3.8.4 |
NUMERICAL INVESTIGATION ON THE AERO-PROPULSION EFFECT OF DISTRIBUTED PROPULSION FOR V/VTOL APPLICATION S. Song¹, S. Deng¹, Q. Li, AVIC General Aircraft Research Institute, China; H. Qiao¹, Y. Lu¹; ¹Nanjing University of Aeronautics and Astronautics, China The aim of this paper is to first explore the benefits and its inner method for various EDF integrated concepts. Then for a given-flight envelope V/STOL high speed aircraft, a best concept will be chosen. Finally, large amounts of calculation could provide enough reference data for the evaluation in general design phase. | ||||
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| 13:55 | 14:25 | 4.8.1 |
DATA-DRIVEN ADAPTATION AND OPTIMIZATION OF TURBULENT FLOWS (invited) K.J. Fidkowski, University of Michigan, United States We present a data-driven approach for calculating adjoint sensitivities in high-order simulations of unsteady turbulent flows, with application to shape optimization and output-based adaptation. The approach relies on using unsteady data to train a corrected turbulence model, which then yields adjoint solutions for calculating gradients and driving mesh and order adaptation. It is non-intrusive and inexpensive, requiring only a small number of unsteady forward simulations, but sufficiently powerful to capture unsteady effects in the sensitivities. | ||||
| 14:25 | 14:55 | 4.8.2 |
HIGH-ORDER ACCURATE EMBEDDED-BOUNDARY DISCONTINUOUS GALERKIN METHODS FOR INVISCID GAS DYNAMICS V. Gulizzi, University of Palermo, Italy Presenter: Vincenzo Gulizzi, University of Palermo This work presents a computational framework for solving the equations of inviscid gas dynamics over embedded geometries based on the Runge-Kutta discontinuous Galerkin method. The novelty of the proposed scheme is the ability to control the spurious oscillations that are typical of high-order schemes for non-linear hyperbolic PDEs by the use of suitably-defined damping terms. | ||||
| 14:55 | 15:25 | 4.8.3 |
HIGH-ACCURATE NUMERICAL SIMULATION FOR VORTEX FLOW OVER A SLENDER MISSILE AT HIGH ANGLE OF ATTACK C.-H. Gao¹, W.-P. Song¹, S.-Q. Han¹, K. Lu¹, Y. Wang¹, Z.-H. Han¹, B. Wu, Shanghai Electro-mechanical Engineering Institute, China; ¹Northwestern Polytechnical University, China Accurate simulation of asymmetrical vortex flow over slender missile at high angle of attack is crucial for predicting the aerodynamic characteristics of the missile. A novel high-order scheme (we call it WENO-K) proposed by our research group is employed to simulate the unsteady supersonic viscous flows dominated by asymmetrical vortices over a Sparrow III type missile model with IDDES method. | ||||
| 15:25 | 15:55 | 4.8.4 |
A COMPUTATIONAL STUDY ON BLADE-VORTEX INTERACTION FOR COAXIAL ROTORS IN HOVER USING A NOVEL HIGH-ORDER SCHEME S.-Q. Han, Sichuan University, China; W.-P. Song¹, Z.-H. Han¹; ¹Northwestern Polytechnical University, China Presenter: Shao-Qiang Han, Sichuan University A novel high-order and low-dissipation scheme (WENO-K) is extended to numerical simulation of unsteady flows dominated by tip vortices around coaxial rotors in hover. The results indicates that the tip vortex structure and its unsteady evolution can be completely simulated and preserved by WENO-K scheme, and the pressure impulses on the blade caused by BVI can also be well captured. | ||||
| Reserve Paper (Interactive) | 4.8.R |
VISCOUS CORRECTION FOR HIGH ORDER IMMERSED INTERFACE METHOD FOR COMPRESSIBLE TRANSONIC FLOWS L.P. Velandia Luis¹, P. Celso Greco Junior¹; ¹University of Sao Paulo, Brazil | |||||
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| 13:55 | 14:25 | 7.8.1 |
ADAPTIVE PATH PLANNING FOR SPRAYING UAS IN VINEYARD UNDER VARIABLE WIND CONDITION L. Scagnellato¹, M. Lecce¹, N. Bloise¹, M. Carreño Ruiz¹, E. Capello¹, G. Guglieri¹; ¹Politecnico di Torino, Italy Presenter: Nicoletta Bloise, Politecnico di Torino Precision agriculture is considered as a great challenge for improving agricultural productivity. The main aim is the design of an adaptive path planning, in which variable wind condition for a sprayer Unmanned Aerial System (UAS) is considered. The scenario includes precision spraying operations in vineyards and variable mass properties. | ||||
| 14:25 | 14:55 | 7.8.2 |
DESIGN OF AN EFFICIENT CLIMBING FLIGHT TRAJECTORY FOR A FLAPPING-WING MICRO AIR VEHICLE S.-G. Lee¹, H.-H. Yang¹, Y.-J. Han¹, J.-H. Han¹; ¹Korea Advanced Institute of Science and Technology, South Korea In this study, a flight dynamics model of a hawkmoth-like flapping-wing micro air vehicle (FWMAV) is established. The climbing trajectory is designed with energy consumption per unit altitude as the cost function. Finally, the designed 2-dimensional trajectory is converted to the spiral trajectory in 3-dimensional space. | ||||
| 14:55 | 15:25 | 7.8.3 |
THREE DIMENSIONAL PATH FOLLOWING CONTROL FOR A FIXED-WING UAV ON SO(3) WITH INPUT SATURATION B. Zhang¹, W. Li, The Second Representative Office of Air Force Armament Departmen, China; Z. Miao¹, Y. Zhang, Beijing System Design Institute of Mechanical-Electrical Enginee, China; ¹Northwestern Polytechnical University, China A three-dimensional path following controller on SO(3) is proposed for a fixed-wing UAV. It has a faster convergent rate and proper damping with the aid of an adaptive auxiliary frame. It suppresses disturbances by tuning the control gain dynamically, and is capable of coping with input saturation by using hyperbolic tangent functions. | ||||
| 15:25 | 15:55 | 7.8.4 |
COOPERATIVE PATH PLANNING AND ADJUSTING STRATEGY FOR UAVS WITH STRICT TIME CONSTRAINS Y. Lu¹, Q. Chen¹, Y. Wang¹; ¹National University of Defense technology, China Presenter: Yafei LU, National University of Defense Technology Multi-UAVs cooperative operations with strict time constraint have become a common form for future application. The methods of time-constrained path planning based on ant colony algorithm is proposed to improve the efficiency and effectiveness. Three strategies for multi-UAVs time adjustment are demonstrated, including takeoff time adjustment, discrete speed adjustment, and hovering for waiting. | ||||
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| 13:55 | 14:25 | 8.8.1 |
DESIGN AND EXPERIMENTAL TESTING OF A DROOP NOSE MORPHING FOR ADVANCED REGIONAL AIRCRAFT A. De Gaspari¹, V. Cavalieri¹, S. Ricci¹; ¹Politecnico di Milano, Italy Presenter: Vittorio Cavalieri, Politecnico di Milano This paper describes the design and experimental testing of a morphing droop nose ground demonstrator at different scales. A multi-level and multi-disciplinary design procedure goes from aerodynamic requirements to the realization of the prototypes. The functionality test of the full-scale device will contribute to increase the technological readiness level of the morphing concept. | ||||
| 14:25 | 14:55 | 8.8.2 |
STRUCTURAL ANALYSIS OF TWISTED/CURVED BEAMS USING A HYBRID METHOD A. Siami¹, F. Nitzsche¹; ¹Carleton University, Canada Presenter: Fred Nitzsche, Carleton University This paper presents a numerical approach for the structural dynamic analysis of initially twisted and curved beams. The variational asymptotical beam sectional theory due to Hodges is used to extract the set of nonlinear equations associated to the 2D beam cross-sectional analysis. The conventional perturbation solution is used as an analytical solution for the set of nonlinear equations obtained from the cross-sectional analysis. To compensate for the effect of neglecting the higher order terms, which have been eliminated in the perturbation solution of the equations, the Firefly algorithm (FA) as an iterative solution is introduced for the first time to the problem. To eliminate the sensitivity of the method to the initial values, the perturbation solution is chosen as an initial guess for the FA. The stiffness matrix obtained from the Firefly algorithm for twisted/curved beam is then used in the geometrically exact, fully intrinsic equations to analyze the dynamic behavior of the beam. The effect of flexible joints is introduced to the one-dimensional beam equations to consider more realistic boundary conditions. The accuracy of the calculated stiffness matrix of the proposed algorithm is evaluated by comparing the eigenfrequencies of an initially twisted blade with the results of a modal analysis done in ANSYS. The Campbell diagram of an initially twisted/curved rotating blade is extracted from the developed one-dimensional equations to demonstrate that the numerical solution provides a sufficiently accurate and fast solution of the problem. | ||||
| 14:55 | 15:25 | 8.8.3 |
EXPERIMENTAL AND NUMERICAL ANALYSIS OF A PRE-STRESSED TENSEGRITY MEMBRANE V.A.S. Paiva¹, L.H.S. Teixeira¹, J.H. Izuka¹, P.G. Ramos¹, P.R.G. Kurka¹; ¹UNICAMP, Brazil Tensegrity is a class of pre-stressed structures in which tension provides integrity. Tensegrity-membrane systems are comprised of membranes, bars, and cables or tendons. They belong to the class of flexible multibody structures and can be treated as an extension of tensegrity systems and their members perform functions such as sensing, actuating, and feedback controlling simultaneously. The low weight and structural integrity make tensegrities an important component in airospace applications. The present work analyzes the numerical and experimental aspects of prediction of vibration of a pre-stressed triangular tensegrity membrane. | ||||
| 15:25 | 15:55 | 8.8.4 |
MORPHING FORWARD WING SECTION SKIN DESIGN FOR A SAILPLANE CONSIDERING WING BENDING F. Sturm¹, M. Hornung¹; ¹Technical University of Munich, Germany To increase aerodynamic performance of a sailplane, a morphing forward wing section and a flap can be applied. A composite skin is designed to achieve desired airfoil shapes for cruise and slow flight. A modelling approach which considers spanwise wing bending is shown, as this influences the elastic behavior of the morphing skin. With that, a parameter study of the laminate properties is done. | ||||
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| 13:55 | 14:25 | 9.8.1 |
THERMODYNAMIC POTENTIAL OF TURBOFAN ENGINES WITH DIRECT COMBUSTION OF HYDROGEN A. Görtz, German Aerospace Center, Institute of Propulsion Technology, Germany; D. Silberhorn, German Aerospace Center, Institute of System Architectures in Ae, Germany This work investigates the impact of direct hydrogen combustion on the thermodynamic cycle of aero engines. Besides the combustion process, the influence of the heat exchanger, for conditioning of liquid hydrogen, and its position within the gas turbine will be considered and evaluated based on a reference aircraft. | ||||
| 14:25 | 14:55 | 9.8.2 |
THE INFLUENCE OF THE VANE LEAN ON THE FLOW IN A TURBINE REAR STRUCTURE V. Vikhorev¹, V. Chernoray¹, A.M. Zuher², J. Larsson²; ¹Chalmers University of Technology, Sweden ;²GKN Aerospace Engine Systems, Sweden This paper presents a detailed comparison of the aerodynamics of two engine realistic Turbune Rear Structures (TRS), one with radial Outlet Guide Vanes (OGVs) and one with leaned OGVs. The effect of the OGV lean is studied for the first time in an engine realistic TRS with implemented regular, thick and bump OGVs typical for the modern TRS. | ||||
| 14:55 | 15:25 | 9.8.3 |
DEVELOPMENT OF THE LOW-COST AND LIMITED SPACE SEA-LEVEL RAM AIR TEST (RAT) MACH 0.8 SYSTEM T.-G. Nguyen¹, Q.-H. Nghiem¹, Q.-H. Nguyen¹, N.-V. Nguyen¹, D.-L. Chu¹, P.-M. Nguyen¹; ¹Viettel Aerospace Institute, Vietnam Presenter: Giang Nguyen, Viettel Aerospace Institute The low-cost and limited space sea-level RAT Mach 0.8 system design process is proposed and presented for both small turbojet engines and flight vehicle system development. Overall steps from requirements to the final RAT system layouts are addressed and discussed briefly. The main plenum chamber design optimization section is presented with the extensively using CFD as the analysis solver. The special treatments are performed on the guide vane aero-dynamical design for turning corner to minimize the turbulence and loss in order to match for the limited space. The diffuser, honeycomb and screen for plenum chamber are thoroughly considered and design for the customized length of plenum while maintaining the stability, uniform of flow and Mach 0.8 of exit. The proposed methodology shows the feasibility and effectivity of the low-cost and limited space sea-level SAT Mach 0.8 system for the small turbojet engines and flight vehicle system development. | ||||
| 15:25 | 15:55 | 9.8.4 |
ANALYSIS OF THE OPERATION OF THE PULSEJET ENGINE J. Tegner, FOI, Sweden Simulations of a pulsejet were used to vizualize important processes. A simplified model was used to explicitly control the combustion - in the sense of how fast, and at what time in the pulse the fuel/air-mixture was burnt. Simulations of this kind revealed that the specific impulse can be significantly increased (our studies indicated an increase of 200%) by proper control of the combustion. | ||||
| Reserve Paper (Interactive) | 9.8.R |
EXPERIMENTAL STUDY ON THE LASER PLASMA JET PROPULSION - PLASMA JET GENERATION AND THRUST MEASUREMENT M. Harada¹, N. Osawa¹, H. Moriai¹; ¹Kanazawa Institute of Technology, Japan | |||||
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| 13:55 | 14:25 | 10.8.1 |
ESTIMATION OF STEPWISE VARYING WIND BASED ON DERIVATIVE ESTIMATION OF AIRCRAFT USING SLIDING WINDOW RECURSIVE LEAST SQUARES METHOD H.S. Luu¹, Y. Ochi¹; ¹National Defense Academy, Japan In ICAS2021, we proposed a method for estimating constant wind without using the airspeed measurements and motion model’s parameters. This paper extends the method to estimate the wind changing stepwise using a sliding-window recursive least squares method. | ||||
| 14:25 | 14:55 | 10.8.2 |
A GENERALISED MULTI-OBJECTIVE ISLAND MODEL FOR FLIGHT CONTROL SYSTEM CLEARANCES P. Piprek¹, P.M. Dias¹, D. Schwalb¹; ¹Airbus Defence and Space GmbH, Germany In modern fly-by-wire aircraft, the Flight Control System plays a key role in the safety, performance, and reliability of the aircraft, and is assessed in a clearance process. This study proposes a global multi-objective optimisation algorithm as a means for automatizing this process and enhancing the chances of finding relevant problematic regions inside the flight envelope. | ||||
| 14:55 | 15:25 | 10.8.3 |
STATISTICAL DATA SELECTION FOR BETTER FLIGHT CHARACTERISTIC MODELING M. Naruoka¹, T. Ninomiya¹; ¹Japan Aerospace Exploration Agency, Japan Presenter: Tetsujiro Ninomiya, Japan Aerospace Exploration Agency To perform reasonable and reliable estimation of flight characteristics of aircraft by using actual flight data, a combination of the data and a postulated model is an important factor. This study shows how the data affects the estimation results from the aspect of the estimated distribution of the model parameters, and proposes a method to select the data for the better estimation. | ||||
| 15:25 | 15:55 | 10.8.4 |
RESEARCH ON SERVO CONTROL METHOD AND DAMPING CHARACTERISTICS OF ACTIVE CONTROL DEVICE L. Yao¹, H. Yu¹, Z. Zhao¹, J. Zheng¹; ¹Shenyang Aircraft Design and Research Institute, China In this paper, three control methods of the active stick are studied. After simulation analysis, the dynamic characteristics of the three control methods are compared. The PID algorithm is used to find out the key parameters affecting the dynamic characteristics of the system, so as to improve the rapidity and stability of the system effectively. At the same time, the influence of the damping characteristics is studied. | ||||
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| 13:55 | 14:25 | 11.8.1 |
VIRTUAL RECONFIGURATION AND ASSESSMENT OF AIRCRAFT CABINS USING MODEL-BASED SYSTEMS ENGINEERING M. Fuchs¹, F. Beckert¹, F. Rauscher¹, C. Goetz¹, J. Biedermann¹, B. Nagel¹; ¹German Aerospace Center (DLR), Germany This paper presents a method to combine geometric data of physical cabin components with virtual models to enable the building of a digital aircraft cabin. As a result, a baseline architecture for the digital cabin has been created, which enables fast system reconfigurability, traceability of changes, identification of interdependencies, and investigation of new cabin variations (retrofit). | ||||
| 14:25 | 14:55 | 11.8.2 |
MORE ELECTRIC AIRPLANE: CASE STUDY STOCKHOLM - COPENHAGEN A. Johansson, Saab Aeronautics, Sweden; M. Yildiz¹, L. Bertling-Tjernberg¹; ¹Royal Institute of Technology (KTH), Sweden Electrification of non-propulsive aircraft subsystems such as the environmental control system and actuation promises fuel savings by lowering the outtake of non-propulsive power from the engines. Here the possible savings through electrification are investigated through a case study of a Stockholm-Copenhagen round-trip by a mid-size airliner. | ||||
| 14:55 | 15:25 | 11.8.3 |
HMI-HUFLAB – A BRAZILIAN - SWEDISH INITIATIVE IN HUMAN FACTORS FOR AERONAUTICS E. Villani¹, J. Alfredsson², M. Bång³, B. Johansson³, U. Anderini², D. Arjoni¹; ¹Aeronautics Institute of Technology (ITA), Brazil ;²SAAB AB, Sweden ;³Linköping University, Sweden This paper presents the HMI-HUFLab Project, a joint Brazilian Swedish initiative in the area of human factors and design of human machine interface for future air systems. It gives a short introduction to Brazilian Swedish collaboration in Aeronautics and, particularly, the area of human factors. It describes the main challenges for setting up the bilateral HMI-HUFLab project and how these challenges were tackled. Finally, it presents the first projects results, which includes the definition of relevant context and scenarios for the future air domain, a review of literature and implementation of complementary simulation environments in both countries. | ||||
| 15:25 | 15:55 | 11.8.4 |
CRITICALITY AND COMFORT ZONE SUPPORTING DESIGN CHOICES TO ACHIEVE SUSTAINABLE REQUIREMENTS: THE CASE OF ELECTRIC AIRCRAFT L. Pereira, Federal University of ABC, Brazil; P. Krus, Linköping University, Sweden This paper proposes an analytical framework for estimating the domain in which a technology combination can be used in a system. To accomplish this goal, the concepts of technology critical zone and technological comfort zone were proposed in order to analyze the impact of a new technology during the design phases of a system. In this paper it is demonstrated on electric aircraft technologies, i.e., battery electric and hydrogen fuel cell aircraft. | ||||
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| 13:55 | 14:25 | 12.8.1 |
PRELIMINARY STUDY ON A FLUIDIC DEVICE SUPPORTING AIRCRAFT-FLIGHT CONTROL W. Stalewski, Lukasiewicz Research Network- Institute of Aviation, Poland A novel fluidic device concept designed to support aircraft control through the control of velocity circulation around an aircraft wing has been developed and pre-investigated based on a computational approach. The device operates based on simultaneous blowing and suction through the mini-nozzles located at the trailing edge of any lifting or control surface of aircraft. | ||||
| 14:25 | 14:55 | 12.8.2 |
EXPERIMENTS TO INVESTIGATE LIFT PRODUCTION MECHANISMS ON OSCILLATING TRAILING-EDGE FLAPS M. Bremm¹, R. Hörnschemeyer¹, E. Stumpf¹; ¹RWTH Aachen University, Germany An oscillating trailing-edge flap of a rigid aerofoil is investigated, to gain a better understanding of the unsteady aerodynamic phenomena of lift increase due to trailing-edge flap oscillations. Therefore, the contribution of lift due to circulation and "added mass" effects are studied in an experimental approach. The unsteady aerodynamic forces and the unsteady flow fields are measured. | ||||
| 14:55 | 15:25 | 12.8.3 |
IMPROVING STALL CHARACTERISTICS OF UCAV WING WITH VORTEX GENERATORS (invited) P. Eliasson, Saab, Sweden; A. Rizzi¹, J. Oppelstrup¹, M. Zhang, Airinnova AB, Sweden; ¹KTH, Sweden Presenter: Arthur Rizzi, KTH We study a UCAV configuration by CFD and investigate how rows of small VGs can improve its stalling characteristics. The VGs are imagined to work similar to the stall fence for Saab J32. By optimizing the placement and strength of the VGs we demonstrate how the vortical flow patterns can be controlled. | ||||
| 15:25 | 15:55 | 12.8.4 |
OPTIMIZATION STUDY ON THE FLOW SEPARATION CONTROL USING A SAWTOOTH PLASMA ACTUATOR L. Wang, Beihang University, China; C.W. Wong¹, Y. Zhou¹; ¹Harbin Institute of Technology, China With aim to improve the flow control performance and reduce the power consumption of Dielectric Barrier Discharge plasma actuator, an novel configuration of plasma actuator with sawtooth electrodes was developed. Under the optimum unsteady actuation modes, the power consumption reduced by 95% but the applicable Reynolds numbers is tripled. This flow control technique is good option to UAV and MAV. | ||||
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| 13:55 | 14:25 | 13.8.1 |
REDUCED TRANSMISSION RISKS FOR PASSENGER OPERATIONS DURING COVID-19 PANDEMIC M. Schultz, Universität der Bundeswehr München, Germany; M. Soolaki, University of Westminster, United Kingdom; O. Michler, Dresden University of Technology, Germany; E. Itoh, University of Tokyo, Japan The current pandemic situation requires major changes to normal passenger handling procedures and passengers must maintain a certain distance when boarding and disembarking. Simulation results exhibit that an optimized passenger handling (seat allocation and boarding/ disembarkation sequences) can reduce the boarding/ disembarkation times significantly (40%) at a low level of transmission risk. | ||||
| 14:25 | 14:55 | 13.8.2 |
QUANTUM ARRIVAL AND DEPARTURE MANAGEMENT N. Yoshikawa, Mitsubishi Electric, Japan The arrival management (AMAN) and departure management (DMAN) system solved by quantum annealer is investigated. The ising model for AMAN/DMAN is built by converting the aircraft sequencing problem formulated by mixed integer programming. To reduce number of decision variables descritized time slots and slot blocking function to represent separation manner is introduced. | ||||
| 14:55 | 15:25 | 13.8.3 |
V/A-R AIR GESTURES HMI INTERACTION IN AIRPORT CONTROL TOWERS S. Bagassi¹, M. Corsi¹, F. Galuppi¹; ¹University of Bologna, Italy This paper presents the experimental campaign conducted to asses the introduction of V/A-R Air Gestures HMI interaction in airport control towers. The results of the validations performed at University of Bologna's real-time Humans-in-the-loop simulation platform, are analysed against success criteria in terms of human performance and safety. | ||||
| 15:25 | 15:55 | 13.8.4 |
DESIGN & VALIDATION OF A FLIGHT CENTRIC WORKLOAD MODEL INCLUDING ATC TASK CHANGE & CONSIDERING INFLUENCING FACTORS T. Finck¹, M.-C. Névir, Technische Universität Dresden, Germany; C. Kluenker¹; ¹German Aerospace Center, Germany Airspace capacity is limited by the ATCOs' control resources, which depend on their workload. For a sectorized airspace, a variety of workload models for distributing air traffic equally among controllers exist, but approaches for a sectorless airspace are absent. This paper is the first to establish a workload model for Flight Centric ATC by adapting a workload model for sectorized airspace | ||||
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| 13:55 | 14:25 | 14.8.1 |
MEASUREMENT OF NOISE AND INDOOR CLIMATE ON BOARD A TURBOPROP AIRPLANE FLIGHT B. Müller¹, A. Lindner¹, V. Norrefeldt¹, Y. Song, TU Delft, Netherlands; N. Mansfield, Nottingham Trent University, United Kingdom; P. Vink, vhp Human Performance, Netherlands; ¹Fraunhofer IBP, Germany On Nov. 3rd 2021 we accompanied two subject test round flight on a turboprop airplane. The flight took off at Rotterdam, flew a round over the North Sea and landed in Rotterdam again. The measurements of noise and indoor climate conducted in this flight are reported in the paper. | ||||
| 14:25 | 14:55 | 14.8.2 |
USE OF THE FLIGHT TEST FACILITY MOCK-UPS IN THE EUROPEAN CLEAN SKY 2 PROGRAM V. Norrefeldt¹, F. Mayer¹, A. Pathak¹, M. Pschirer¹, M. Kienberger¹, A. Lindner¹, S. Johann¹, A. Nagele-Renzl¹, M. Buschhaus¹, G. Grün¹; ¹Fraunhofer IBP, Germany This paper highlights the value the Fraunhofer Flight Test Facility brings to the Clean Sky 2 program. It gives an overview of projects that have been realized like passenger comfort related to air quality, environmentally friendly fire suppression systems for the cargo hold, hazard and comfort considerations in the business jet aircraft and a short look into Covid-risk reduction in the cabin. | ||||
| 14:55 | 15:25 | 14.8.3 |
COMPUTATIONAL STUDY OF AIRFLOW AND DISPERSION OF AIRBORNE PATHOGENS INSIDE AN AIRCRAFT CABIN C.L.S. Raposo¹, J.M.M. Sousa¹; ¹IDMEC, Instituto Superior Técnico, Portugal Presenter: Carlos Raposo, IDMEC, Instituto Superior Técnico A computational study of airflow and dispersion of airborne pathogens inside an aircraft cabin is conducted with the aim of assessing the feasibility of installing bioaerosol sensors. Such sensors would gather information during flight about the dispersion of a pathogen within each row of seats in the cabin, thereby providing a warning about possible infected passengers. | ||||
| 15:25 | 15:55 | 14.8.4 |
IMPACT OF MOTION-DEPENDENT ERRORS ON THE ACCURACY OF AN UNAIDED STRAPDOWN INERTIAL NAVIGATION SYSTEM K. Borodacz¹, C. Szczepanski¹; ¹Lukasiewicz Research Network - Institute of Aviation, Poland This paper presents motion-dependent components of the total navigational error for a particular maneuvers, obtained from the analysis of the full inertial measurement unit model. These components can be arbitrarily combined to analyze the relationship between sensor measurement errors and navigation errors for the considered trajectory, which supports the selection of the optimal IMU. | ||||
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| 16:15 | 16:45 | 1.9.1 |
SYSTEM LEVEL STUDIES FOR NASA - MODEL DEVELOPMENT TOWARD ZERO EMISSIONS (invited) J. Tai, Georgia Tech, United States Will describe U.S. efforts toward sustainable aviation. Several invited papers/presentations will be used to highlight significant progress. | ||||
| 16:45 | 17:15 | 1.9.2 |
TRANSONIC TRUSS-BRACED WING VISION VEHICLE TECHNOLOGY MATURATION N.A. Harrison, Boeing Research & Technology, United States; G.M. Gatlin, NASA Langley Research Center, United States; E.D. Dickey¹, A.M. Malone¹; ¹Boeing Commercial Airplanes, United States The maturation of technologies that can potentially enable a Transonic Truss-Braced Wing (TTBW) vision vehicle have continued under the latest phase of the Subsonic Ultra Green Aircraft Research (SUGAR) program. Ground testing in this phase has further reduced configuration unknowns, and provided valuable data for future potential design activities. | ||||
| 17:15 | 17:45 | 1.9.3 |
AN INNOVATIVE HYDROGEN-POWERED PROPULSION SYSTEM FOR SINGLE-AISLE AIRCRAFT (invited) W. Orisamolu, United States the speaker will highlight progress toward a hydrogen-powered propulsion system aimed at the single aisle seat class transport aircraft marketplace | ||||
| 17:45 | 18:15 | 1.9.4 |
JETZERO BWB ENABLING TECHNOLOGIES (invited) M. Page, United States; J. Vassberg, United States JetZero was formed in 2016 to develop a commercial BWB Airliner. This airplane will enter service in 2030-2035 with a family that will span the 737/A320 Single-Aisle market to the 787/A330 twin-aisle market. Current projections show 30% lower fuel-burn than future tube-and-wing airliners with the same engine technology. In addition, the BWB offers a cumulative noise benefit of 30dB compared to the same benchmark, and 40dB to the latest Chapter-14/Stage-V standard. Perhaps the most exciting opportunity afforded by the JetZero BWB is transition to Hydrogen. BWB’s offer the volume needed for LH2 at a much lower cost than today’s Tube-and-Wing technology. The JetZero family is being designed simultaneously to provide aircraft that span 190 to 300 passengers with provisions for full LH2 adoption, plus Freighter and Tanker options. This presentation will describe the present baseline design, NASA initiatives directed to advancing BWB readiness, the technologies that increased the BWB energy advantage to 30%, and the path to LH2 integration. | ||||
| 18:15 | 18:45 | 1.9.5 |
JETZERO BWB ENABLING TECHNOLOGIES (invited) M. Page, United States; J. Vassberg, United States THE JETZERO BLENDED WING BODY – RISK REDUCTION RESEARCH AND DEVELOPMENT | ||||
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| 16:15 | 16:45 | 2.9.1 |
DESIGN AND ECO-EFFICIENCY ASSESSMENT OF A PEOPLE-MOVER AIRCRAFT IN COMPARISON TO STATE-OF-THE-ART NARROW BODY AIRCRAFT S. Wöhler¹, J.-N. Walther¹, W. Grimme¹; ¹German Aerospace Center (DLR), Germany Presenter: Sebastian Wöhler, German Aerospace Center (DLR) The focus of the is paper is the quiestion weather a People Mover aircraft can make its contribution towards the climate targets by replacing highly efficient narrow body aircraft where preliminary results indicate a significant disadvantage in terms of CO2 emissions per passenger seat. Therefore, the concept will be assessd on its economic performance and on its climate impact contribution. | ||||
| 16:45 | 17:15 | 2.9.2 |
MINIMIZING THE CLIMATE IMPACT OF THE NEXT GENERATION AIRCRAFT USING NOVEL CLIMATE FUNCTIONS FOR AIRCRAFT DESIGN K. Radhakrishnan, 1Institute of Air Transportation Systems, TUHH, Germany; K. Deck¹, P. Proesmans¹, F. Linke², F. Yin¹, V. Grewe¹, R. Vos¹, B. Lührs², M. Niklaß², I. Dedoussi¹; ¹Delft University of Technology, Netherlands ;²Air Transportation Systems, DLR, Germany The aircraft’s environmental performance on fleet level is so far completely decoupled from the design process. Complex climate models used to evaluate the non-CO2 emissions impact on climate is far too computationally demanding for a multidisciplinary design optimisation. In this paper, a computationally efficient approach to design climate-optimal aircraft using novel CFADs is presented. | ||||
| 17:15 | 17:45 | 2.9.3 |
PROPELLER AIRCRAFT DESIGN OPTIMIZATION FOR CLIMATE IMPACT REDUCTION R. Thijssen¹, P. Proesmans¹, R. Vos¹; ¹Delft University of Technology, Netherlands This paper yields insight into the climate impact reduction of propeller-powered aircraft. CO2 and non-CO2 climate effects and operating costs are considered in a multidisciplinary design optimisation. A comparison with turbofan counterparts shows that climate-optimal, propeller aircraft can outperform turbofan aircraft in the medium-range category. This is relevant for future design studies. | ||||
| 17:45 | 18:15 | 2.9.4 |
AIRCRAFT FLEET MODELS USING A BOTTOM-UP APPROACH FOR SIMULATING AVIATION TECHNOLOGICAL PROSPECTIVE SCENARIOS S. Delbecq¹, T. Planès¹, M. Delavenne¹, V. Pommier-Budinger¹, A. Joksimovic¹; ¹ISAE-SUPAERO, France This paper focuses on the use of a bottom-up approach to establish aircraft fleet models for simulating aviation prospective scenarios. These models allow representing the gradual replacement of current aircraft by future architectures obtained from overall aircraft design. Some case studies are performed using CAST, an open source platform for analyzing scenarios for sustainable aviation. | ||||
| 18:15 | 18:45 | 2.9.5 |
SUSTAINABLE AVIATION FOR SWEDEN - TECHNOLOGY & CAPABILITY ASSESSMENT TARGETING 2045 C. Jouannet, Saab Aeronautics, Sweden; I. Staack¹, T. Grönstedt², X. Zhao², P. Krus¹, A. Lundbladh, GKN Aerospace, Sweden; B. Nagel, DLR, Germany; ¹Linköpings University, Sweden ;²Chalmers, Sweden The goal of the sustainable aviation for Sweden project is to analyze the possibilities offered by different technological solutions to achieve zero emission aviation. Firstly, the Swedish/Nordic network context is addressed and secondly the study is extended to the European context. The project will investigate the potential and feasibility of new or upgraded aircraft types based on the different technologies mapped from various published roadmaps and national expertise. This involves developing aircraft conceptual designs studies and trade analysis with regards to different fuel types, propulsion technologies, structure, operations, network and fleet management, and a range of relevant technologies. The project will, on a common technology basis, analyse a number of zero carbon fuels and associated technologies through operational studies and optimization to accelerate the introduction of fossil free aircraft technology and choosing optimal paths for making aviation sustainable. | ||||
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| 16:15 | 16:45 | 3.9.1 |
SORA-BASED RISK ASSESSMENT FOR CARGO UNMANNED AERIAL VEHICLES IN THE UAM FRAMEWORK L. Babetto¹, B. Kniebel¹, E. Stumpf¹; ¹ILR, RWTH Aachen University, Germany Increasing urbanization and e-commerce encourage Urban Air Mobility (UAM) for cargo transportation. Today, the integration of the UAM into the manned air traffic is challenging due to the risk to third parties. Thus, this paper deals with the application of the SORA approach to three different Cargo UAVs involved in a green airfreight logistics chain, reinforcing safety as a UAV design driver. | ||||
| 16:45 | 17:15 | 3.9.2 |
MEDIUM SIZE UAV AS TEST PLATFORM FOR NEW TECHNOLOGIES J. Mieloszyk¹, A. Tarnowski¹, A. Kwiek¹, R. Topolewski¹, T. Goetzendorf-Grabowski¹; ¹Warsaw University of Technology, Poland To introduce innovation in aerospace new technologies have to be developed and tested, which requires suitable test equipment. Efficient way to do this is UAV platform as a testbed. This paper describes manufacturing of such a platform. A variety of new technologies, that can be investigated are discussed, including alternative propulsion systems, new avionics and new aerodynamic devices. | ||||
| 17:15 | 17:45 | 3.9.3 |
CONCEPTUAL DESIGN AND SIZING FOR A FIXED WING UAV FOR EXPLORATION OVER MARS P. Gupta, Manipal Institute of Technology, Manipal, India, India; R.S. Pant, Indian Institute of Technology Bombay, Mumbai, India, India Presenter: Pranav Gupta The key aim of this paper is to design a lightweight compact UAV for high endurance-loiter in the Martian atmosphere. On the basis of the mission requirements, the design process will be initiated. A constraint analysis diagram will be plotted to identify the design variables, the further appropriate initial weight will be selected to initialize the iterative design calculations. | ||||
| 17:45 | 18:15 | 3.9.4 |
AN INVESTIGATION ON THE IMPROVEMENT FOR TANDEM WING PITCHING MOMENT CHARACTERISTICS X. Wang¹, T. Ma, Institude of Unmanned System, Beihang University, China; N. Qiao¹, J. Fu, SchoolofTransportationScienceandEngineering, Beihang University, China; ¹School of Aeronautic Science and Engineering, Beihang University, China Our investigation concentrates on changing the flow interaction of tandem wing. The conclusion is the wingtip vortex of the front-wing and the spanwise flow of the rear-wing are the critical reasons causing the undesired pitching-moment of a tandem wing. Optimizing the front-wing wingtips improves the nonlinear pitching-moment, moreover, a better rear-wing aerodynamic performance is accompanied. | ||||
| 18:15 | 18:45 | 3.9.5 |
TASK ALLOCATION METHOD FOR COMPLEX RECONNAISSANCE AREA BY MULTIPLE UAVS Y. Yue¹, Y. Pei¹, P. Hou¹; ¹School of Aeronautics, Northwestern Polytechnical University, China Reconnaissance task allocation is a hot spot in the research of multi-UAV cooperative operations. Geographical obstacles and electromagnetic interference jointly affect the reconnaissance of UAVs to the target area. Considering these limitations uniformly can more effectively analyze the reconnaissance benefit and range cost of a UAV swarm in a reconnaissance mission. | ||||
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| 16:15 | 16:45 | 4.9.1 |
ENHANCING CFD PREDICTIONS FOR THE GRIPEN AIRCRAFT (invited) P. Eliasson¹, P. Weinerfelt¹, F. Bramkamp, NSC, Sweden; ¹Saab, Sweden We demonstrate the advantages we obtain with a fully implicit solution technique of the Navier-Stokes equations on unstructured grids. We show comparative results for several test cases with focus on large scale on the Gripen calculations leading to more than a factor of three reduction in computing time. In many cases we also get improved steady state convergence leading to improved accuracy. | ||||
| 16:45 | 17:15 | 4.9.2 |
STUDY OF THE EFFECTS OF NUMERICAL MODEL ENHANCEMENTS FOR AEROSTRUCTURAL ANALYSIS IN TRANSONIC FLOWS J.A.A. Lyrio¹, J.L.F. Azevedo², D.A. Rade¹, R.G. da Silva², C. Breviglieri, Embraer, S. A., Brazil; ¹Instituto Tecnologico de Aeronautica, DCTA/ITA, Brazil ;²Instituto de Aeronautica e Espaço, DCTA/IAE/ALA, Brazil Presenter: Domingos A. Rade, Aeronautics Institute of Technology, Brazil This work focuses on the impact of recent improvements in numerical models for aerostructural analysis using a fluid-structure interaction (FSI) framework called BRU3D-FSI. Results using the NASA CRM and the HIRENASD geometries are analyzed in terms of wing pressure distribution, integrated aerodynamic coefficients and wing deflection, and compared with available experimental data. | ||||
| 17:15 | 17:45 | 4.9.3 |
A STATIC STABILITY COMPARISON OF WIND TUNNEL AND COMPUTATIONAL FLUID DYNAMICS METHODS L.K. Fitzgerald¹, A.J. Niven¹, P.C. Griffin¹; ¹University of Limerick, Ireland The field of aircraft stability and control has traditionally relied on pertinent information from wind tunnel experiments, semi-empirical methods, and flight testing. The current study utilises the results from wind tunnel testing and computational fluid dynamics to investigate the static longitudinal and lateral directional stability of the standard dynamics model. | ||||
| 17:45 | 18:15 | 4.9.4 |
EXTERNAL-INTERNAL AERODYNAMIC COUPLING ON A TURBOPROP ENGINE USING THE BODY-FORCE METHOD R. Moretti¹, J. Decours¹; ¹ONERA, France This paper presents a numerical simulation of the aerodynamics around the Tech TP turboprop demonstrator, including internal parts such as the air inlet and the first stage of Ardiden3 centrifugal compressor simulated by Body-Force. The performance of the compressor has been analyzed on the isolated and installed configuration. | ||||
| 18:15 | 18:45 | 4.9.5 |
DEVELOPMENT OF A CFD MODEL AND METHODOLOGY FOR THE INTERNAL FLOW SIMULATION IN A HYDROGEN-POWERED UAV A. Porcarelli, KTH - Royal Institute of Technology, Sweden The onboard carrying of a hydrogen fuel cell leads to unexplored internal flow characteristics, including the introduction of water vapour. Given the strict environmental operational requirements of PEM fuel cells, a Runge-Kutta-based solver is developed and tested to effectively assess the evolution of the UAV internal bay flow temperature and humidity fields. | ||||
| Reserve Paper (Interactive) | 4.9.R |
A FAST PREDICTION METHOD FOR DROPPING WATER OF FIRE FIGHTING AIRCRAFT BASED ON EXTERNAL BALLISTICS OF PARTICLES H.-Y. Li¹, X. Zhao¹, Z.-X. Xia¹; ¹School of Aeronautics, Northwestern Polytechnical University, China Presenter: H.-Y. Li, School of Aeronautics, Northwestern Polytechnical University | |||||
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| 16:15 | 16:45 | 5.9.1 |
WIND TUNNEL TEST OF A BLENDED WING BODY UNMANNED AERIAL VEHICLE R. Mariani¹, S. Suewatanakul¹, S. Ghika¹, L.A. Penela¹, P. Wennhage¹, B. Zang, University of Bristol, United Kingdom; ¹KTH Royal Institute of Technology, Sweden A wind tunnel test campaign on a 37.5%-scale model on has been conducted to examine the aerodynamic characteristics of a blended wing body unmanned aerial vehicle. Boundary and support interference corrections have been pre-determined through numerical simulations of the model in the tunnel. Preliminary experimental and numerical results show good agreement validating the methodology. | ||||
| 16:45 | 17:15 | 5.9.2 |
WIND TUNNEL EXPERIMENT OF TAXIDERMY BLACK-TAILED GULL (LARUS CRASSIROSTRIS) AND BLACK KITE (MILVUS MIGRANS) N. Kishimoto, Setsunan University, Japan; D. Wada¹, M. Tamayama¹, Y. Iwami², N. Tomita², T. Ikeda³, Y. Tanahashi³, K. Katagiri, Osaka Research Institute of Science and Technology, Japan; ¹JAXA, Japan ;²Yamashina Institute for Ornithology, Japan ;³Chubu University, Japan We obtained basic aerodynamic characteristics through wind tunnel experiments using taxidermy black-tailed gull and black kite as a first step. Instead of commercially available taxidermy birds, we collaborated with ornithologist researchers to select accessible and useful birds and to create taxidermy birds in the most desirable shape. In this paper, we report on the details and results of the experiment conducted in the JAXA's low-speed large wind tunnel. | ||||
| 17:15 | 17:45 | 5.9.3 |
ANALYSIS OF LOW-SPEED AERODYNAMIC CHARACTERISTICS OF BUSEMANN BIPLANE AIRFOIL INSTALLED HIGH LIFT DEVICES T.D. Nguyen¹, M. Taguchi¹, M. Kashitani¹, K. Kusunose, Formerly Japan Aerospace Exploration Agency, Japan; ¹National Defense Academy of Japan, Japan In this paper, the effects of leading-edge flaps and trailing-edge flaps on the low-speed performance of supersonic Busemann biplane are clarified by wind tunnel tests and CFD simulations. Also, the staggering wing incorporated flaps also investigated. The measured system measures consist of the three-component balance system and a turntable, designed in the test section's sidewall. The position of the hinges of flaps is 0.3 times of chord length away from the leading edge and trailing edges. The stagger is set of 0.25 and 0.5 times of chord length. The results of single configurations showed the increment of lift and drag when flaps are installed. The lift slopes are nearly constant in the case of upper elements with the deflection of trailing flap lower than 30°. In cases of the lower element, the lift slope decreases when the deflection of the trailing-edge flap increases. The leading-edge flap makes the lift slope increase in both upper and lower elements. The results of biplane configurations show the increment in lift and drag when flap installed, as results of conventional monoplane wing. The results of the Busemann biplane (baseline configuration) show a good agreement with references and CFD data. When a trailing-edge flap is installed, the lift slope decreases when the deflection of the trailing flap increases. Also, the proportion of lower element to total lift and drag decreases when deflection increases at the angle of attack larger than 0°. The leading-edge flap and the stagger make the lift slope increase. Both flaps and stagger also make the maximum lift increase and decrease the stall angle compared with the baseline model. The stagger also makes the proportion of lower wing to total lift and drag decrease at the angle of attack larger than 0°. | ||||
| 17:45 | 18:15 | 5.9.4 |
EXPERIMENTAL INVESTIGATION ON TRANSPORT AIRPLANE LONGITUDINAL STABILITY ENHANCEMENT IN CRITICAL ICING CONDITION L. Fan¹, T. Guo¹, L. Zhang¹, H. Zhang¹; ¹CARDC, China Presenter: Litao Fan, China Aerodynamics Research and Development Center To improve the flight safety in icing conditions, a wing strake solution is proposed. Wing strake selection tests are performed in FL-11 wind tunnel using the 1:7 horizontal tail half model. A series of wing strakes are tested to be validated on the 1:15 full model in FL-12 wind tunnel. The preliminary test results indicate that the wing strake can enhance the stability in landing condition. | ||||
| 18:15 | 18:45 | 5.9.5 |
INFLUENCE OF MANEUVERING PROCESS ON PERFORMANCE CHARACTERISTICS OF BELLY INLET OF AIRCRAFT B.-B. XU¹, C.J. Wu¹, F.Z. Sun¹, J.P. Tang¹, W.T. Xiong¹; ¹China Aerodynamics Research and Development Center, China In order to obtain the influence of maneuvering process on the aerodynamics characteristics of inlet, the dynamic inlet wind tunnel experiment was performed in ?3.2m wind tunnel of the CARDC. For the inlet located at the belly of aircraft, the pitching maneuver has small effect , while the sideslip maneuver has larger effect on aerodynamic characteristics of inlet. | ||||
| Reserve Paper (Interactive) | 5.9.R |
EXPERIMENTAL STUDY ON NON-COMMAND MOTION CHARACTERISTICS OF SMALL ASPECT RATIO FLYING WING Y. Shen¹, S. Feng¹, Y. Wang¹, C. Bu¹, H. Tan¹, W. Mu¹, H. Chen¹; ¹AVIC Aerodynamics Research Institute, China | |||||
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| 16:15 | 16:45 | 7.9.1 |
FORMABILITY OF TITANIUM TI-6AL-4V SHEETS AT MODERATE TEMPERATURE COMBINED WITH HIGH-PRESSURE S. Olsson¹, B. Carlsson¹, B. Helgesen¹; ¹Quintus Technologies AB, Sweden Formability of Titanium Ti-6Al-4V A new sheet metal forming method for Titanium 6Al-4V has been evaluated, using 1400 bar pressure, combined with relatively low temperature, 270°C. Forming limits, repeatability and process predictability is evaluated and also compared with forming simulation results. The process has a capacity to form Ti sheets at high accuracy and with excellent repeatability. | ||||
| 16:45 | 17:15 | 7.9.2 |
INFLUENCE OF KEYHOLE TIG WELDING PARAMETERS ON WELD GEOMETRY OF NEWLY-DEVELOPED SUPERALLOY VDM ALLOY 780 A. Ariaseta, Sweden; N. Sadeghinia, Sweden; J. Andersson, Sweden The effect of Force TIG welding process parameters on the weld geometry, porosity, and cracking susceptibility of new nickel-based superalloy VDM 780 will be investigated. The results obtained in this work will be used to optimize the Force TIG welding process parameters that produce the VDM 780 weld that meets tight industrial quality criteria and with the lowest cracking susceptibility | ||||
| 17:15 | 17:45 | 7.9.3 |
USE OF FRICTION STIR WELDING ON PRIMARY STRUCTURES OF AIRCRAFTS INSTEAD OF RIVETED JUNCTION D. Desgaches, AIRBUS, France Typical junction area of fuselage is riveted for common commercial aircraft. These junctions are sized by fatigue and damage tolerance criterion, due to pressurization loading, with single-shear or double-shear geometries, and potential overlap. The use of Friction Stir Welding could be a solution to solve criticality of fuselage junctions due to the proof of its high mechanical properties. | ||||
| 17:45 | 18:15 | 7.9.4 |
EXPERIMENTAL INVESTIGATIONS ON TENSILE PROPERTIES OF ALUMINUM HONEYCOMB SANDWICH STRUCTURES WITH SINGLE-SIDED REPAIRING B. Yan¹, G. Zhang¹, M. Tong¹, L. Li¹, D. Yu¹, S. Zhu¹, Z. Wu², H. Wang², T. Jin, China Special Vehicle Research Institute, China; ¹Nanjing University of Aeronautics & Astronautics, China ;²Nanjing University of Aeronautics and Astronautics, China Presenter: Bing Yan Tensile properties of single-sided panel repair(SP) and panel/core repair(SPC) of aluminum alloy honeycomb sandwich structure(AAHSS) used in civil aircraft were researched by experiments and compared with that of AAHSS without repair. Firstly, a clamp suitable for testing the tensile properties of wide-wall panels with different thicknesses was designed. Then, the failure behavior, the strain and deformation characteristics of SP and SPC structures were firstly studied by digital image correlation (DIC) technology. The results showed that the debonding of the patch and the fracture near the root were the main failure modes of the SP structure, and the strength recovery rate was 101%. A summary was that the repairing method for this configuration could effectively improve the bearing capacity of the original structure, and the adhesive performance was more stable. For SPC structure, debonding of the patch was the primary failure mode with only a 94% strength recovery rate. Besides, the strain concentration of both repairing structures was located in the substrate near the upper and lower edges of the patch. It can be concluded that the repairing technology of SP structure is sufficient to be used in civil aircraft repair, while that of SPC structure needs to be further improved. | ||||
| 18:15 | 18:45 | 7.9.5 |
RESEARCH ON THE DUCTILE FRACTURE OF AL7085 AND TC11 UNDER COMPLEX STRESS STATE Y.J. Liu, AVIC the First Aircraft Institute, China In this paper, ductile fracture behaviors of aluminon alloy AL7085 and titanium alloy TC11 under complex stress state are experimentally and numerically studied. Based on coupon tests and simulations, the curves of triaxiality-fracture strain are obtained as fracture criteria of AL7085 and TC11. The experimental and numerical studies of joint structure are made to verify the fracture criteria. | ||||
| Reserve Paper | 7.9.R |
ELECTROMAGNETIC INTERFERENCE SHIELDING EFFECTIVENESS OF THE THIN CARBON NANOFIBERS/ SILICON CARBIDE FABRICS COMPOSITES X. Jia¹, H. Du¹, L. Zhang¹, X. Zhang¹, Z. Zhong¹; ¹AVIC The first Aircraft Institute, China | |||||
| Reserve Paper (Interactive) | 7.9.R |
HIGH IMPACT AND DAMAGE TOLERANT MULTICOMPONENT ALLOY FOR HIGH STRAIN RATE APPLICATIONS M. Atif¹, X.Z. Shi¹, M.A. Raza¹, M.Z. Sheikh¹, J. Shen, Joint International Research Center of Impact Dynamics and Its E, China; Y. Li, School of Civil Aviation, Northwestern Polytechnical University, China; ¹Northwestern Polytechnical University, China | |||||
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| 16:15 | 16:45 | 8.9.1 |
NONLINEAR VIBRATION-BUCKLING INVESTIGATION OF UNSTIFFENED AND STIFFENED STRUCTURES SUBJECTED TO MECHANICAL AND THERMAL LOADINGS R. Azzara¹, M. Filippi¹, A. Pagani¹, E. Carrera¹; ¹Politecnico di Torino, Italy This work intends to present a novel numerical approach for carrying out virtual Vibration Correlation Technique (VCT) in unstiffened and stiffened structures subjected to mechanical and thermal loadings in order to predict the buckling load, to characterize the natural frequencies variation for progressively increasing loads, and to provide a verification of the experimental VCT results. | ||||
| 16:45 | 17:15 | 8.9.2 |
GROUND VIBRATION TESTING OF A HIGH ASPECT RATIO WING WITH REVOLVING CLAMP G. Dessena¹, D.I. Ignatyev¹, J.F. Whidborne¹, A. Pontillo, University of Bristol, United Kingdom; L. Zanotti Fragonara¹; ¹Cranfield University, United Kingdom A case study of a high aspect ratio wing is proposed to study the effect of operating conditions on its structural properties. A revolving clamp is designed to mount the specimen to a clamp-on shaker at different setting angles, allowing for ground vibration tests in different conditions. The objective is to detect a change in the wing’s modal properties in relation to the setting angle. | ||||
| 17:15 | 17:45 | 8.9.3 |
UPDATING OF JET TRAINER AIRCRAFT DYNAMIC MODEL TO RESULTS OF GROUND VIBRATION TEST J. Cecrdle, Czech Aerospace Research Centre (VZLU), Czech Republic This paper discusses updating of a jet trainer aircraft dynamic model according to the results of ground vibration test (GVT). The paper outlines the process of flutter analysis with the special regard to the role of the GVT. Next, the Bayesian parameter estimation method is outlined. Finally, the application example is provided. The results of the symmetric model are shown and evaluated. | ||||
| 17:45 | 18:15 | 8.9.4 |
DYNAMIC STRESS SIMULATION AND ASYMMETRY STATOR DESIGN FOR A FAN BLISK Y. Liu¹, K. Xu, Aero Engine Academy of China, China; Y. Chen¹, Y. Wu¹, Q. Du¹, D. Mo¹; ¹AECC Shenyang Engine Research Institute, China A systematic investigation was performed to estimate the dynamic stress of fan blisk. Modal analysis was carried and the geometry nonlinearity was considered. The coupled Campbell diagram was obtained. The unsteady analysis was undertaken considering stators. The dynamic stress was obtained. The asymmetry stator design made dynamic stress dropped. The numerical results were validated by test. | ||||
| 18:15 | 18:45 | 8.9.5 |
A NEW APPROACH TO SHAPING THE PUSHROD TUBE AS THE MAIN COMPONENT OF THE CONTROL SYSTEM, OPTIMIZATION, AND MANUFACTURING TECHNOLOGY. W. Grendysa, Warsaw University of Technology, Poland Thesis of the research and it's original idea, is that it is possible to increase the critical buckling force of a compression tube by using a shape other than a constant cross-section, without changing the material and for a constant mass and wall thickness of the tube. Obtained results show the possibility of increasing the buckling strength of the pushrod tube by 23% compared to a fixed section | ||||
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| 16:15 | 16:45 | 9.9.1 |
THE IMPACT OF REACTION MECHANISM COMPLEXITY IN LES MODELING OF LIQUID KEROSENE SPRAY COMBUSTION A. Åkerblom, Lund University, Sweden Due to the high computational cost of LES and detailed chemistry models for aviation fuel, reaction mechanisms employed for finite-rate combustion in LES must be compact yet realistic. The influence of reaction mechanism complexity on LES results should therefore be measured, so that appropriate mechanisms can be chosen for future studies and new LES-optimized mechanisms can be developed. | ||||
| 16:45 | 17:15 | 9.9.2 |
NUMERICAL ANALYSIS OF PROPAGATION OF DETONATION WAVE PLUNGING ENTRY THE FUEL JET TRAIN INSIDE ROTATING DETONATION COMBUSTOR F. Wang¹, T. Mizukaki¹; ¹Tokai University, Japan In this paper, to clarify the effect of detonation propagation by incomplete fuel mixing in RDC, construct a linear detonation channel that simulate the RDC flow field and carried out a numerical analysis of propagation of detonation wave plunging entry the combustible gas jet train with different mixing states. | ||||
| 17:15 | 17:45 | 9.9.3 |
LES OF COMBUSTION DYNAMICS IN AN ETHYLENE-HYDROGEN-AIR RAMJET N. Zettervall¹, K. Nordin-Bates¹, C. Ibron¹, C. Fureby, Lund University, Sweden; ¹FOI, Sweden A computational study using Large Eddy Simulations to investigate combustion dynamics in an ethylene-hydrogen-air ramjet test rig. The flame in the current set-up changes its anchoring point between a jet-wake stabilized and a cavity-stabilized position. The highly dynamic combustion behaviour is investigated numerically and compared against previously published experimental data. | ||||
| 17:45 | 18:15 | 9.9.4 |
HIGH PRESSURE HYDROGEN OXYGEN COMBUSTION KINETIC ASSESSMENT FOR AIR-BREATHING PROPULSION SUPERSONIC GREEN AVIATION G. Saccone¹, M. Marini¹; ¹Italian Aerospace Research Centre - CIRA, Italy This work contributes to a more thorough understanding of the complex and nonlinear chemical kinetic behavior of hydrogen/oxygen combustion at intermediate and high pressure conditions up to about 33 atm that are usually encountered in supersonic, air-breathing green aviation. | ||||
| 18:15 | 18:45 | 9.9.5 |
RESEARCH ON FLOW HEAT TRANSFER CHARACTERISTICS OF HEAT EXCHANGER BASED ON BIONIC FRACTAL STRUCTURE B.-W. Yu¹, X. Yu¹, M.-G. Cao¹, X.-Z. Zhang¹, C.-L. Zhang¹, H.-B. Ji, Institute of Metal Research, Chinese Academy of Sciences, China; W.-T. Tong, Avic GuZhou YongHong Aviation Machinery Co, China; ¹Shenyang Aeroengine Research Institute, China In this paper, based on the bionic fractal idea, a typical alveolar pores heat exchanger was designed, and the flow heat transfer in the heat exchanger was numerically simulated. The experimental parts were processed and experimented with 3D printing technology, and the numerical simulation results were verified. The results show that the typical alveolar pores heat exchanger has obvious advantages such as high heat transfer area, small pressure drop, and has good flow heat transfer characteristics. | ||||
| Reserve Paper | 9.9.R |
STUDY ON THE APPLICATION OF EMULSIFIED FUEL IN SMALL JET ENGINES A. Sato¹, R. Yasuda¹, M. Harada¹, S. Shibasaki¹, H. Moriai¹; ¹Kanazawa Institute of Technology, Japan Presenter: Ryota Yasuda, Kanazawa Institute of Technology | |||||
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| 16:15 | 16:45 | 10.9.1 |
THE NEW RESEARCH AIRCRAFT ISTAR - EXPERIMENTAL FLIGHT CONTROL SYSTEM D. Niedermeier¹, K. Giese¹, D. Leißling¹; ¹DLR, Germany This paper describes the experimental flight control system design of DLR’s new flight control testbed Falcon 2000LX ISTAR. The integration of an experimental flight control system will enbale the aircraft to be used as Variable Stability System (VSS) and for rapid inflight testing of any Guidance, Navigation and Control (GNC) research software application. | ||||
| 16:45 | 17:15 | 10.9.2 |
RAPID PROTOTYPING IN AIRCRAFT DESIGN USING CFD, WIND TUNNEL AND FLIGHT TESTING R. Larsson¹, U. Ringertz, Royal Institute of Technology, KTH, Sweden; D. Lundström, Linköping University, LIU, Sweden; A. Sobron¹; ¹Saab Aeronautics, Sweden This paper describes the process and methods used for rapid prototyping, sub-scale flight-testing and analysis of an aircraft design. New wings have been designed for a radio controlled flying demonstrator. The results can be used in education and research to further enhance and explore the field of Aeronautical engineering. | ||||
| 17:15 | 17:45 | 10.9.3 |
SYNTHETIC AIR DATA - A COMPARATIVE PRACTICAL STUDY V.L.M. Veras, EMBRAER, Brazil; L.C.S. Góes, ITA, Brazil Presenter: Clecio Fischer, ITA Synthetic Air Data Systems are in its essence airspeed estimation algorithms. Commonly, estimation algorithms are built based on measurements from which airspeed can be calculated. This paper presents simulations using F16 model performing simple maneuvers using some proposed algorithms that use inertial sensors and GPS. The possibility to use an angle-of-attack and/or temperature probes is also discussed. We also discuss practical aspects regarding airspeed, altitude and temperature estimations. | ||||
| 17:45 | 18:15 | 10.9.4 |
FREE FLIGHT TEST IN HORIZONTAL WIND TUNNEL WITH POWERED AIRCRAFT J.-F. Wang¹, S.-G. Lu¹, S. Feng¹, M.-H. Wang¹; ¹AVIC Aerodynamics Research Institute, China Modern advanced layout aircraft is faced with multi-disciplinary coupling problems such as aerodynamic layout and flight control system design. In order to carry out aerodynamic/flight/control integration research at the early stage of design, shorten the development cycle and reduce the development cost, a model free flight test system was established in 8m×6m open wind tunnel based on similarity criterion. | ||||
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| 16:15 | 16:45 | 11.9.1 |
THE AGILE 4.0 MBSE-MDAO DEVELOPMENT FRAMEWORK: OVERVIEW AND ASSESSMENT L. Boggero¹, T. Lefèbvre, ONERA/DTIS, France; J. Vankan, Royal Netherlands Aerospace Centre (NLR), Netherlands; B. Beijer, KE-works, Netherlands; V. Saluzzi, Bombardier Aviation, Canada; B. Nagel¹; ¹German Aerospace Center (DLR), Germany A new methodology and digital technologies in the context of MBSE and MDAO are developed in the project. The methodology and the technologies are part of the AGILE 4.0 MBSE-MDAO Development Framework. This paper aims at presenting an overview of this framework, and assess its efficacy, i.e. demonstrate that the proposed framework improves the current state-of-the-art. | ||||
| 16:45 | 17:15 | 11.9.2 |
EXPERIMENTAL INVESTIGATION OF FUEL SLOSH IN A GENERIC FIGHTER WING TANK CONFIGURATION L. Debschütz¹, A. Seefried², T. Westermeier¹, R. Kuchar², D. Schwalb¹; ¹Airbus Defence and Space, Germany ;²German Aerospace Center, Germany Presenter: David Schwalb Real-time modeling of dynamic fuel slosh effects in the Flight Control System design and clearance process of highly agile unstable aircraft configurations is gaining importance as fuel-to-weight ratios increase on modern fighter planes. A ground test to validate associated simulations in the context of typical fighter applications is outlined in the presented paper. | ||||
| 17:15 | 17:45 | 11.9.3 |
COUPLING OF MODEL-BASED SYSTEMS ENGINEERING AND SAFETY ANALYSIS IN CONCEPTUAL AIRCRAFT SYSTEM DESIGN S.M. Lübbe¹, M. Schäfer¹, O. Bertram¹; ¹German Aerospace Center (DLR), Germany DLR conducted a design study for conceptual design of the Landing Gear System as part of their project MOBEFAS. An approach to model ARP4761 and ARP454A methods in aircraft system design within an MBSE model has been applied. It tracks safety related dependencies between systems and system levels. The adequacy and effectiveness of the method is examined. | ||||
| 17:45 | 18:15 | 11.9.4 |
ONTOLOGY-ASSISTED AIRCRAFT CONCEPT GENERATION L. Knöös Franzén¹, R. Chaitanya Munjulury¹, P. Krus¹; ¹Linköping University, Sweden This paper presents a method for generating an aircraft concept from an ontology represented design space, where relevant information subsequently can be extracted and expanded through different approaches. A case study is performed to illustrate how the method can be used to estimate the characteristics of an existing aircraft and to perform an initial geometrical sizing. | ||||
| 18:15 | 18:45 | 11.9.5 |
HYBRID ELECTRIC PROPULSION SYSTEM OPTIMIZATION FOR A COMMUTER AIRCRAFT P. Krus¹, I. Staack¹, A.A.M. Oliveira, Federal University of Santa Catharina, Brazil; ¹Linköping University, Sweden In this paper it is shown how simulation based optimization can be used to investigate the impact of development of different technologies on the feasibility of electrical aircraft. This work investigates the design of an electric/hydrogen-powered commuter aircraft (certified according to CS/FAR 23). Based on a dynamic holistic cyber-physical system model with a 6DOF flight dynamics model for mission simulation | ||||
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| 16:15 | 16:45 | 12.9.1 |
FIT FOR CHANGE - DLR STRATEGY TOWARDS ZERO-EMISSION AVIATION E. Campillo Borrás¹, M. Fischer¹, A. Kaysser-Pyzalla¹, A. Klöckner¹, D. Kügler¹, R. Mönig¹, B. Nagel¹, C.-C. Rossow¹, M. Wiedemann¹; ¹Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR), Germany In future, aviation will continue to connect the world’s people, cultures and economic regions. However, a comprehensive transformation is necessary, because by the middle of the century, the economy and society are to be climate-neutral within the framework of the European Green Deal. To that end, DLR presents an aviation strategy that sets out a research path to achieve climate-neutral flight. | ||||
| 16:45 | 17:15 | 12.9.2 |
NOVEL PATHWAYS TO SUSTAINABLE AVIATION (invited) C. Voigt, Germany; M. Rapp, Germany; U. Herrmann, Germany The major share of aviation’s climate impact is driven by contrails and aircraft CO2 emissions. The German Aerospace Centre fosters projects with the goal to reduce the aviation’s climate impact by sustainable fuels, technological progress, and aircraft routing, in order to give guidance for future climate-friendly aviation. | ||||
| 17:15 | 17:45 | 12.9.3 |
CITY-ATM – LIFE DRONE DEMONSTRATIONS OF NEW CONCEPT ELEMENTS ENABLING OPERATIONS IN URBAN AREAS A. Kuenz¹, J. Lieb¹, M. Rudolph¹, A. Volkert¹, D. Geister¹, N. Ammann¹, D. Zhukov¹, P. Feurich, FlyNex, Germany; J. Gonschorek¹, M. Gessner¹, T. Kraft¹, H. Hackbarth, KopterKraft OÜ, Estonia; G. Peklar, NXP Semiconductors, Germany; L. Schalk¹, D. Becker¹, D. Gerbeth¹, C. Zhu¹, O. Garcia Crespillo¹, K. Caprdja², H. Walther²; ¹DLR, Germany ;²DFS, Germany This paper describes the work performed in the City-ATM project. Besides explaining the concept enabling UAS operations in urban areas, a focus is put on the description of three life flight trial demonstrations carried out in Hamburg City and at the National Experimental Test Center in Cochstedt. | ||||
| 17:45 | 18:15 | 12.9.4 |
ELIMINATING CLIMATE IMPACT FROM AVIATION – REVIEW OF PROMISING AIRCRAFT CONCEPTS AND ENABLING TECHNOLOGY BRICKS (invited) J. Hartmann, German Aerospace Center (DLR), Germany While increasing the disciplines involved in the technology impact assessment for climate neutral flight the perimeter of the aircraft design methods of components and new technologies must be increased at the same time. One of the key results is that the materialization of envisaged improvements of new technologies is declining when more details are properly modelled and considered. | ||||
| 18:15 | 18:45 | 12.9.5 |
DESIGN,MANUFACTURING & CERTIFICATION STRATEGIES FOR INNOVATIVE HYDROGEN STORAGE SYSTEMS TO ENABLE ZERO EMISSION AVIATION M. Wiedemann¹, D. Wilckens¹, M. Kleineberg¹; ¹DLR, Germany Presenter: Christian Wilberg, DLR DESIGN,MANUFACTURING & CERTIFICATION STRATEGIES FOR INNOVATIVE HYDROGEN STORAGE SYSTEMS TO ENABLE ZERO EMISSION AVIATION | ||||
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| 16:15 | 16:45 | 13.9.1 |
CLUSTER STRUCTURE AND GATEWAY AVAILABILITY OF AD-HOC COMMUNICATION NETWORKS IN THE NORTH ATLANTIC AIRSPACE T. Marks¹, A. Hillebrecht¹; ¹German Aerospace Center, Germany The North Atlantic airspace is one of the busiest airspaces in the world, while at the same time lacking radar coverage and exhibiting limited data link capabilites. In our paper we analyze ad-hoc communication networks among airplanes in terms of cluster structure and gateway availability by time series and by per scenario analyses and show the dependencies to higher level scenario parameters. | ||||
| 16:45 | 17:15 | 13.9.2 |
DEMAND PATTERN INFLUENCE ON RELATION OF TURNAROUND DURATION AND GATE OCCUPATION DEPENDING ON AVAILABLE RESOURCES M. Jameel, DLR, Germany This case study based on traffic data of an European Airport presents an investigation of relation between the key resource passenger gate and the overall turnaround time depending on other available resources for some given demand list and its numerous variations. | ||||
| 17:15 | 17:45 | 13.9.3 |
ASSESSMENT OF REAL-TIME DATA TRANSMISSION VIA AD-HOC COMMUNICATION NETWORKS IN THE NORTH ATLANTIC OCEANIC AIRSPACE A. Hillebrecht¹, T. Marks¹, V. Gollnick, Hamburg University of Technology, Germany; ¹German Aerospace Center, Air Transportation Systems, Germany Aeronautical data link communication plays an increasingly important role in the current air transport system, enabling efficient and safe operation of aircraft even in congested airspace. In our work we present an operational performance assessment of a novel data link technology enabling data link communication via ad-hoc aircraft networks in an oceanic airspace. | ||||
| 17:45 | 18:15 | 13.9.4 |
AIR TRAFFIC SIMULATION ACROSS FIR IN JAPAN USING CELLULAR AUTOMATON K. Sekine¹, T. Tatsukawa¹, K. Fujii¹, E. Itoh, The University of Tokyo, Japan; ¹Tokyo University of Science, Japan This study simulates every 4934-aircraft flying across FIR in Japan by using a cellular automaton-based model. Interestingly, spacing adjustments of arrival flights to hub-airports account for only 40% of the total amount. This indicates that identifying flight delay bottleneck not only on the airways to hub airports but also on other routes is also paramount for totally efficient ATM operation. | ||||
| 18:15 | 18:45 | 13.9.5 |
OPTIMIZATION OF AIRCRAFT FLIGHT PATHS CONSIDERING THE CONFLICTING PARAMETERS OF ECONOMY AND SAFETY T. Nagashima¹, M. Ding, Institutes of Innovation for Future Society, Nagoya University, Japan; K. Fujii¹, K. Takeda¹; ¹Graduate School of Informatics, Nagoya University, Japan A method is proposed to automatically execute a flight planning task in various flight situations considering the conflicting characteristics of flight economy (fuel consumption) and safety (possibility of safe landing in an emergency). A Pareto-optimal solution is derived by applying the method for Haneda-Naha route. | ||||
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| 16:15 | 16:45 | 14.9.1 |
ENERGY-BASED SYSTEM ARCHITECTURE DESIGN - ENVIRONMENTAL CONTROL SYSTEM A. Joksimovic¹, X. Carbonneau¹, F. Brazier, Delft University of Technology, Netherlands; R. Vingerhoeds¹; ¹ISAE-SUPAERO, France First principles of physics and systems engineering are leveraged to yield a method for material aeroplane systems architecture design starting from basic abstract functional architectures. The focus is air conditioning system, but the method is generic. The flexibility of the method opens doors to identifying functional synergies with other systems for overall aeroplane energy efficiency gain. | ||||
| 16:45 | 17:15 | 14.9.2 |
METHODOLOGY FOR THE AUTOMATED PRELIMINARY CERTIFICATION OF ON-BOARD SYSTEMS ARCHITECTURES THROUGH REQUIREMENTS ANALYSIS C. Cabaleiro¹, M. Fioriti, Politecnico di Torino, Italy; L. Boggero¹; ¹German Aerospace Center (DLR), Germany The aim is to establish a list of rules and requirements to be used to define the connections among on-board systems during architecture design to find certifiable solutions. The connectivity requirements shall be used as a certification check while evaluating the impact of new innovative architectures and is the first step to achieve a virtual certification process during on-board systems design. | ||||
| 17:15 | 17:45 | 14.9.3 |
A SYSTEM INTEGRATOR’S PERSPECTIVE ON VEHICLE SYSTEM EVALUATION AT THE AIRCRAFT CONCEPT STAGE A. Drego¹, S. Steinkellner¹; ¹Saab AB, Sweden Identification of unanticipated behavior can determine if a vehicle system architecture is feasible for an aircraft or not. This paper discusses this issue by mostly using the ECS for a manned fighter aircraft as a case study. The outcomes from this paper could also provide guidance on how other vehicle systems could be evaluated at the aircraft concept stage. | ||||
| 17:45 | 18:15 | 14.9.4 |
EXTENSIBLE AIRCRAFT FUSELAGE MODEL GENERATION FOR A MULTIDISCIPLINARY, MULTI-FIDELITY CONTEXT J.-N. Walther¹, C. Hesse¹, J. Biedermann¹, B. Nagel¹; ¹German Aerospace Center (DLR), Germany In this paper, a knowledge-based approach to support analysis model generation based on a central product data format is proposed. It is implemented here for the fuselage and aims to improve consistency among the models used by different contributors in collaborative multi-disciplinary design optimization, while also being open novel product architectures such as fuselage-mounted hydrogen tanks. | ||||
| 18:15 | 18:45 | 14.9.5 |
MATHEMATICAL MODELLING AND ANALYSIS OF THERMAL MANAGEMENT SYSTEM ARCHITECTURE FOR HYPERSONIC AIRCRAFT S. Nambiar¹, D. Ferreto¹; ¹Politecnico di Torino, Italy Recent high speed aircraft design studies, like STRATOFLY MR3, were done to increase the TRL of aircraft and optimizing its performance within the supersonic range. Also these studies indicated the importance of aircraft systems interface analysis, in increasing the TRL of the aircraft. This paper presents a mathematical model for the TEMS taking STRATOFLY MR3 aircraft as the baseline, based on Conceptual Multi-Disciplinary Optimization (CMDO). | ||||
| Reserve Paper | 14.9.R |
HYDRO ENVIRONMENTAL AND ELECTRICAL ASSETS MAPPING TOOL USING SWARMS AND MACHINE LEARNING, UAV & USV R.K. Rangel¹, V.A. Rodrigues¹, A.L. Maitelli¹, T.M. de Souza¹; ¹IBRV - Institute of Research & Development, Brazil | |||||
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| 10:00 | 10:30 | 1.10.1 |
CLEAN SKY 2 PROGRAMME OVERVIEW S. Dubois, Clean Aviation JU, Belgium Clean Sky 2 is currently the largest European research programme developing innovative, cutting-edge technology aimed at reducing CO2, gas emissions and noise levels produced by aircraft. Funded by the EU’s Horizon 2020 programme with €1.8 billion over 10 years, Clean Sky contributes to strengthening European aero-industry collaboration, global leadership and competitiveness by delivering innovative solutions for the aviation sector. In this presentation, progress up to date will be highlighted, covering the latest technical achievements made. | ||||
| 10:30 | 11:00 | 1.10.2 |
SUSTAINABLE TECHNOLOGIES FOR COMMERCIAL AIRCRAFT OF TOMORROW - INTEGRATED MULTIFUNCTIONAL FUSELAGE DEMONSTRATOR Y.C. Roth, Airbus, Germany Sustainability is a key element for future commercial aircraft and new technologies need to meet very challenging requirements. In the framework of Clean Sky 2 - Large Passenger Aircraft platform, a consortium led by Airbus consisting of universities, research centers and industrial partners across Europe has been established with the mission to mature a set of innovative technologies and integrate them into one flagship demonstrator: the Multifunctional Fuselage Demonstrator (MFFD). Technologies have been matured on a large scale for this 8-meter long demonstrator entirely made of thermoplastics and referring to a single aisle aircraft. Key enablers include the use of sustainable materials like thermoplastic composites enabling dustless assembly through welding, multifunctional integration of cabin systems and the use of pre-equipped modules to ease pax floor installation. | ||||
| 11:00 | 11:30 | 1.10.3 |
OPEN FAN ENGINE ARCHITECTURE FOR NEXT GENERATION SMR C. Diette, Safran Aircraft Engines, France The Clean Sky 2 programme is supporting a Technology maturation plan through modules & rigs ground demonstrations to prepare the design of a scale 1 Engine Ground Test Demonstrator. Multiple maturation studies have been performed to identify and select an innovative engine architecture capable to achieve 20% of CO2 reduction. The key features of the GTD Engine will include a large open fan with a variable pitch, an integrated gearbox, a high speed booster and a high speed low pressure turbine. Clean Sky 2 is contributing to the preliminary design phase of the GTD Engine with the aim to validate the new engine architecture and the Low Pressure Modules. | ||||
| 11:30 | 12:00 | 1.10.4 |
PROGRESS IN WING DESIGN, STATUS AND PERSPECTIVES J. Lery, Dassault Aviation, France; M. Werner, Airbus, Germany; E. Coustols, ONERA, France The presentation describes the activities performed on Wings by the Leaders Airbus, Saab, and Dassault Aviation, and the Core Partners ONERA and DLR (NACOR consortium) in the frame of Clean Sky 2 Airframe ITD. The activities are covering various Technology Streams from the Airframe ITD “High Performance & Energy Efficiency” Activity Line, with the objective to mature wing technologies spanning from Natural Laminar Flow, composite structure technologies, electrical wing ice protection systems, and active load and flutter control. Following ground testing that is being carried out under Clean Sky 2 Airframe ITD, technology maturation will continue under Clean Aviation to meet the 2030/35 EIS target for implementation in future products. The presentation describes the activities performed on Wings by the Leaders Airbus, Saab, and Dassault Aviation, and the Core Partners ONERA and DLR (NACOR consortium) in the frame of Clean Sky 2 Airframe ITD. The activities are covering various Technology Streams from the Airframe ITD “High Performance & Energy Efficiency” Activity Line, with the objective to mature wing technologies spanning from Natural Laminar Flow, composite structure technologies, electrical wing ice protection systems, and active load and flutter control. Following ground testing that is being carried out under Clean Sky 2 Airframe ITD, technology maturation will continue under Clean Aviation to meet the 2030/35 EIS target for implementation in future products. | ||||
| 12:00 | 12:30 | 1.10.5 |
THE CLEAN SKY 2 TECHNOLOGY EVALUATOR 1ST GLOBAL ASSESSMENT (invited) J.-F. Brouckaert, Belgium The 1st Global Assessment of the Technology Evaluator has been a milestone in the timeline of activities of Clean Sky 2 programme. Based on a set of 11 concept aircraft, designed on the basis of various advanced technologies developed under the CS2 programme (aerodynamics, engines, airframe, systems), the Technology Evaluator has performed a first assessment at three major levels: aircraft mission level, airport level and fleet level. The present paper/presentation will describe the various CS2 concepts (commuter, regional, short-medium range and long range) including their performance improvements based on the integration of new technologies, as well as their environmental impact (CO2, NOx and Noise) at airport and air transport system level when introduced into the fleet forecast performed by DLR up to 2050. | ||||
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| 10:00 | 10:30 | 2.10.1 |
COMBINED APPLICATION OF HYBRID LAMINAR FLOW CONTROL AND VARIABLE CAMBER IN PRELIMINARY AIRCRAFT DESIGN T. Effing¹, V. Schmitz¹, F. Schültke¹, F. Peter, Bauhaus Luftfahrt e.V, Germany; E. Stumpf¹; ¹RWTH Aachen University, Germany Within this work, an approach to integrate the combined application of hybrid laminar flow control and variable camber into the preliminary aircraft design suite MICADO is presented. The authors apply this methodology to a turbulent mid-range technology demonstrator. The goal is to demonstrate the potential of the combined application of the two technologies on overall aircraft design level. | ||||
| 10:30 | 11:00 | 2.10.2 |
CLEAN-SKY 2 LARGE PASSENGER AIRCRAFT PLATFORM 1 ADVANCED ENGINE AND AIRCRAFT CONFIGURATIONS D. Kierbel, AIRBUS, France The Clean-Sky 2 Large Passenger Aircraft platform1 aims at integrating the most fuel efficient propulsion concepts into compatible airframe configurations, for the next generations of short and long range aircrafts and also studying laminarity as well as new radical aircraft configuration concepts. The task is done with different concepts, which use multiple demonstrators to evaluate them. Platform 1 covers 16 different demonstrators. Airbus cooperates with many partners to achieve these ambitious objectives. Overall Platform 1 gross Budget from 2014 to 2023: 600mEuros incl. all Partners Main Partners involved: Rolls Royce, Safran, General Electrics, Avio Aero, Liebherr, Dassault Aviation, Aernnova, Sonaca, GKN, Fokker, DLR, CIRA, NLR, Fraunhofer, Onera, TU Delft, Akira, FIDAMC, Erneo | ||||
| 11:00 | 11:30 | 2.10.3 |
AERODYNAMIC DESIGN AND ANALYSIS OF HLFC WINGS WITHIN THE EUROPEAN PROJECT HLFC-WIN T. Streit¹, M. Kruse¹, T. Kilian¹, J. v. Geyr, DLRK, Germany; I. Petropoulos, ONERA, France; ¹DLR, Germany Results for the numerical aerodynamic design and analysis of a long range, large passenger aircraft equipped with a Hybrid Laminar Flow Control (HLFC) system are presented. In addition, extensions of the numerical methods used to predict the transition line position in the case of suction are described. | ||||
| 11:30 | 12:00 | 2.10.4 |
ECONOMICS OF SUSTAINABLE REGIONAL AIR MOBILITY P. De Felipe¹, D. Yang¹; ¹Imperial College London, United Kingdom Study presents a novel simple sizing method for 4 different architectures of propulsion systems which include parallel and series hybrids, hydrogen fuel cell and finally fully electric retrofits. Performance is analysed on a typical regional mission and shows that parallel retrofits are able to save up to 20% in fuel. The hydrogen retrofit has the greatest improvement in operating costs. | ||||
| 12:00 | 12:30 | 2.10.5 |
TOWARD A GREENER AIRCRAFT ARCHITECTURE F. Vidal de Saint Jean, Dassault Aviation, France Greener aircraft is no longer an ambition, but a necessity. It requires to work simultaneously on the aircraft itself, on everyday operations and on the type of fuel used (SAF). Focusing on the platform, the challenge is to build an aircraft using all the different studies in every disciplines around aircraft performances. Indeed, this presentation will show how new technologies studied by Dassault tends to be integrated in a future concept able to gain on carbon footprint while minimizing community noise. In the field of aerodynamics, the specificities of business jets, size and altitude of flight, make it easier to obtain an extended laminarity by adapting the aerodynamic design and the manufacturing process. A laminar high aspect ratio wing is being studied. In terms of structural conception, this wing should be in composite to reduce weight penalty and ensure feasibility of the shape. Flutter control and load alleviation are managed by fly-by-wire to optimize the wing conception. From a system point of view, hot air ice protection system is no more feasible due to the coupling of high wing span with small core engine. An electrical wing ice protection system is then mandatory. Moreover, to allow short root chords, main landing gears usually under wings, have to be moved under the fuselage. This architecture leads to specific constraints for business jet with smaller diameter than liners. Going further in reducing the carbon footprint requires moving towards hybrid powerplant, and thus the use of green hydrogen as an alternate to Kerosene. It would bring full decarbonisation; the feasibility of the integration of large and heavy pressurized tanks is explored in that direction. The greener aircraft concept, is a complex equilibrium dealing with the above technologies. Timely deployment of aircrafts integrating major innovations requires that certification of such aircrafts is prepared in parallel to technology developme | ||||
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| 10:00 | 10:30 | 3.10.1 |
SCALABILITY ANALYSIS OF RADICAL TECHNOLOGIES TO VARIOUS AIRCRAFT CLASS - PART I: INITIAL DESIGNS M.F.M. Hoogreef¹, V.O. Bonnin¹; ¹Delft University of Technology, Netherlands Various research initiatives in hybrid-electric aviation typically address only a single vehicle or single vehicle class. However, novel propulsion and energy solutions can be differently applicable in different vehicle classes. The objective of is to identify areas suitable for scaling, as well as limitations/challenges for application of radical technologies on different aircraft classes. | ||||
| 10:30 | 11:00 | 3.10.2 |
SCALABILITY ANALYSIS OF RADICAL TECHNOLOGIES TO VARIOUS AIRCRAFT CLASS - PART II: SENSITIVITY ANALYSIS V.O. Bonnin¹, M.F.M. Hoogreef¹; ¹Delft University of Technology, Netherlands This study aims at providing a landscape of opportunities and limitations for hybrid-electric aircraft (HEA) by investigating several technological combinations applied to various aircraft classes. The preliminary sizing of HEA using different hybrid-electric powertrain architectures, combined with various distributed propulsion layouts is conducted. The relative benefit of resulting HEA, with respect to a conventional design, are then compared on the basis of several performance metric. | ||||
| 11:00 | 11:30 | 3.10.3 |
REGIONAL TRANSPORT AIRCRAFT DESIGN USING TURBO-ELECTRIC DISTRIBUTED PROPULSION (TEDIP) SYSTEM V. Polepeddi¹, P. Raj¹, M. Emeneth, PACE America, United States; ¹Virginia Tech, United States The overall objective of the present research is to evaluate the advantages and disadvantages of integrating a turbo-electric distributed propulsion (TEDiP) system for a 70-passenger ATR 72-500 aircraft with a nominal range of 1,500 km at a cruise speed of 510 km per hour. The goal is to significantly energy efficiency and reduce harmful emissions into the atmosphere. | ||||
| 11:30 | 12:00 | 3.10.4 |
ARRIVING AT CERTIFIABLE NOVEL AIRLINER USING LIQUID HYDROGEN & EFFICIENCY METRICS R.K. Nangia, Nangia, United Kingdom; L. Hyde, Consulting, United Kingdom Environmental considerations are focussing on using LH2 for future airliners. However, LH2 is hazardous, safety and certification issues dominate design. We cover several possible configurations before proposing a twin fuselage "Gondola" arrangement that isolates LH2 from passengers and crew during all flight phases, meeting the regulations. We show Efficiency metrics. | ||||
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| 10:00 | 10:30 | 4.10.1 |
STEADY-STATE AERODYNAMICS TIP GAP INFLUENCE IN A TRANSONIC LINEAR CASCADE AT NEAR STALL C. Tavera Guerrero¹, N. Glodic¹, H. Mårtensson, GKN Aerospace Sweden AB, Sweden; ¹KTH, Sweden A steady-state aerodynamics for two tip gaps configurations in the KTH transonic linear cascade is presented. The experimental campaign is performed at two different tip clearances. The operational point is representative of a virtual compressor at near stall at part speed, producing a leading-edge separation bubble. Numerical results are compared to experimental data as a source of potential validation. | ||||
| 10:30 | 11:00 | 4.10.2 |
LARGE EDDY SIMULATION OF A LYNX HELICOPTER LANDING IN THE BARROSO CORVETTE SHIP D.M. Pio¹, C.F. Rafael¹, P.S.C. Villela¹, G.A.L. da Silva¹, M. Ferro, Laboratorio Nacional de Computacao Cientifica -, Brazil; M.J.M. Guedes, Marinha do Brasil, Brazil; ¹Aerothermal Solutions - ATS, Brazil The present study objective is to simulate the helicopter landing on a ship under wind to verify the decrease in predictions errors at points near the landing deck.The present paper will compare the CFD LES results with previous CFD RANS results and experimental data. The conclusions of the present work will directly affect the SHOL definition by simulation mainly at landing deck proximities. | ||||
| 11:00 | 11:30 | 4.10.3 |
NUMERICAL INVESTIGATION OF ROTORCRAFT PRESSURE ERROR CORRECTION BY UTILIZATION OF AIR DAMS A.-O. Sezer¹, M. Elfarra, Ankara Y?ld?r?m Beyaz?t University, Turkey; H.-I. Ünlü¹; ¹Turkish Aerospace, Turkey To achieve satisfying airspeed readings with pitot static systems during unsteady flight conditions, the static ports must be able to read free stream data. Installation of small barriers called air dams around static ports can help the system to achieve accurate airspeed readings. Different dam configurations are investigated utilizing computational fluid dynamics. | ||||
| 11:30 | 12:00 | 4.10.4 |
TRANSONIC FLOW OVER DELTA WING USING ENTROPIC LATTICE BOLTZMANN METHOD M. Dhake¹, C. Thantanapally¹, S. Arcidiacono¹, S. Ansumali¹; ¹SankhyaSutra Labs Ltd, India Presenter: Chakradhar Thantanapally, SankhyaSutra Labs Limited This work investigates the transonic flow (Ma=0.85) over a swept-back delta wing with a sharp leading edge at Re= $6times10^6$ . The behaviour of vortex breakdown in cross-flow shocks makes the problem setup highly complex in contrast to subsonic vortical flows. The simulation is carried out using a higher order Entropic Lattice Boltzmann Method (ELBM) transonic solver. | ||||
| 12:00 | 12:30 | 4.10.5 |
CFD TAKE-OFF ANALYSIS OF A SEAPLANE HULL THROUGH A DYNAMIC MULTIPHASE MODEL M. Sinisi¹, G. Cantanna¹, G. Occhipinti¹, A. Caramazza¹, G. Dilonardo¹, E. Cestino¹; ¹Politecnico di Torino, Italy Presenter: Gaetano Dilonardo, Politecnico di Torino The analysis provides the aerodynamic behavior in take-off of the hulls of the seaplane Savoia-Marchetti S55-X model aircraft, built by the student team “Team S55”. The analytical results, in terms of velocity and pressure field, trust and drag coefficient changes, are compared with experimental data collected by NASA through the S55-X tank test registered in the Technical note no.635. | ||||
| Reserve Paper (Interactive) | 4.10.R |
VALIDATING AIRSPACE CFD MODELS FOR DRONE OPERATION WITH FLIGHT TEST DATA D. Standingford¹, C. Sequeira², M. Allan¹, C. Rider², G. Furse², J. Sharpe¹; ¹Zenotech, United Kingdom ;²Flare Bright, United Kingdom | |||||
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| 10:00 | 10:30 | 5.10.1 |
AERONAUTICAL CFD AND TURBULENCE - PROGRESS AND CHALLENGES (invited) A. Rizzi¹, D. Henningson¹; ¹KTH, Sweden This lecture addresses how CFD simulations have been used for predicting separated flows, and the associated aerodynamic performance, throughout the flight envelope, giving special focus to actual aircraft. It entails a summary of the physics of flow separation that is especially difficult to model numerically along with results from DNS studies that shed new light on the physics and that lay out a path for substantial progress. Among the cases reviewed are: turbulent separation from a smooth-surface including short laminar-turbulent bubbles, Incipient vortex separation including bursting and buffet onset and stalling characteristics. | ||||
| 10:30 | 11:00 | 5.10.2 |
AERONAUTICAL CFD AND TURBULENCE - PROGRESS AND CHALLENGES PART 2 (invited) A. Rizzi¹, D. Henningson¹; ¹KTH, Sweden This lecture addresses how CFD simulations have been used for predicting separated flows, and the associated aerodynamic performance, throughout the flight envelope, giving special focus to actual aircraft. It entails a summary of the physics of flow separation that is especially difficult to model numerically along with results from DNS studies that shed new light on the physics and that lay out a path for substantial progress. Among the cases reviewed are: turbulent separation from a smooth-surface including short laminar-turbulent bubbles, Incipient vortex separation including bursting and buffet onset and stalling characteristics. | ||||
| 11:00 | 11:30 | 5.10.3 |
OPEN CAVITY SIMULATIONS UNDER SIDESLIP FLOW CONDITIONS K. Rajkumar¹, J. Radtke¹, E. Tangermann¹, M. Klein¹; ¹University of the Bundeswehr Munich, Germany Weapon bays resonate under certain flow and geometrical conditions. The effects of sideslip conditions on the resonance modes are explored, which have gained little attention so far. Used numerical methodologies are high fidelity DES (Reference data) and SAS approaches (Time-efficient simulation). Spectral and experimental validations for both approaches will be shown in the paper. | ||||
| 11:30 | 12:00 | 5.10.4 |
APPLICATION OF GENETIC PROGRAMMING AND ARTIFICIAL NEURAL NETWORK APPROACHES FOR RECONSTRUCTION OF TURBULENT JET FLOW FIELDS V. Gryazev, United Kingdom; U. Armani, United Kingdom; A.R. Murali, France; A.P. Markesteijn, United Kingdom; S.A. Karabasov, United Kingdom; V. Toropov, United Kingdom; S.E. Naghibi, United Kingdom; V. Riabov, Japan Presenter: Umberto Armani The high-speed jets considered in this research correspond to the NASA Small Hot Jet Acoustic Rig (SHJAR) experiment at acoustic Mach numbers 0.5 and 0.9. The Spectral Proper Orthogonal Decomposition (SPOD) method is applied to compress the original LES data. The use of SPOD enabled separating spatial and temporal coherent structures which spread over a wide range of frequencies and can be considered as an extension of Proper Orthogonal Decomposition (POD) method to time-resolved data. The resulting time-dependent coefficients of the SPOD modes are reconstructed using machine learning methods. | ||||
| 12:00 | 12:30 | 5.10.5 |
UNSTEADY SIMULATIONS OF MASSIVELY SEPARATED FLOW AROUND NACA0021 AIRFOIL USING A TRANSITIONAL IDDES MODEL Y. Wang, China; S.-Q. Zhang, China; W.-P. Song, China; Z.-H. Han, China In this study, a blended IDDES model and a correlation-based transitional model were newly coupled in OpenFOAM for simulating flow involving massive flow separation and the layer transition. Validations have been taken on the massively separated flow around NACA0021 airfoil at AoAs from 20° to 90°. The force coefficients predicted by simulations have a good comparison with the experimental data. | ||||
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| 10:00 | 10:30 | 6.10.1 |
EXPERIMENTAL INVESTIGATIONS OF AN AEROELASTIC WIND TUNNEL MODEL FOR TAIL BUFFETING ANALYSIS J. Stegmüller¹, S. Hayböck¹, P. Hartl¹, C. Breitsamter¹; ¹Technical University of Munich, Germany For the experimental analysis of buffeting effects, a flexible modular wind tunnel model was developed. Quasi-rigid aluminum lifting surfaces serve as a reference case. An internal six-component balance measures forces and moments. The signals of unsteady pressure transducers and accerelometers integrated in the lifting surfaces of the rigid and the flexible configurations will be analyzed. | ||||
| 10:30 | 11:00 | 6.10.2 |
OPTIMIZATION OF AN ACTIVE DAMPING SYSTEM FOR USE WITH A SINGLE STRUT MOUNT J. Pereira, National Research Council Canada, Canada An active damping system is developed and optimized for use with a wind tunnel model mounted on a single strut. The effect of the pivot point on moment control is investigated through wind-on tests using an aircraft model. Single strut and three-strut mount results are compared and measurements acquired using continuous pitching motion are compared to those acquired with a pitch-pause motion. | ||||
| 11:00 | 11:30 | 6.10.3 |
WIND-TUNNEL TEST ON LEADING-EDGE VORTEX OF LOW-ASPECT-RATIO FLAPPING PLATES J.-S. Han¹, C. Breitsamter¹; ¹Technical University of Munich, Germany We introduce the wind tunnel tests for low-aspect-ratio flapping plates. A three-rotational-axis robotic arm, a high sensitive 6-axis force/torque transducer machine shop-made, and model flat plates with several different aspect ratios, which should have an appropriate rigidity and a lightweight for the lowest inertia, are presented. Deformation tests for the model plates follow. | ||||
| 11:30 | 12:00 | 6.10.4 |
POWERED WIND TUNNEL TESTING WITH HYDRAULIC MOTORS D. Steiling¹, P. Aschwanden¹, J. Müller¹, T. Jax¹; ¹RUAG AG, Switzerland Presenter: Peter Aschwanden, RUAG AG The integration of propulsors in aircraft can be a challenge and often needs to be investigated in a wind tunnel test. The hydraulic technology in use at the RUAG wind tunnel for powered testing is described. Examples of actual test setups ranging from isolated propeller tests, both full-scale and model scale, to complex multi-engine aircraft models are given. | ||||
| 12:00 | 12:30 | 6.10.5 |
EXPERIMENTING ROTORCRAFT FLIGHT IN COMPLEX ENVIRONMENTAL CONDITIONS USING THE WIND TUNNEL: HELICOPTER SHIP LANDING CASE N. Taymourtash¹, A. Zanotti¹, G. Gibertini¹, G. Quaranta¹; ¹Politecnico di Milano, Italy The present study will show how scaled wind tunnel tests can be implemented to simulate the aerodynamic response of a helicopter operating in the fully-coupled environment of Helicopter-Ship Dynamic Interface. The setup developed here is proven to be an effective instrument to measure both steady and unsteady aerodynamic responses of the rotor due to the interaction with the airwake of the ship. | ||||
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| 10:00 | 10:30 | 7.10.1 |
INCREMENTAL FATIGUE DAMAGE MODEL: APPLICATION TO PLANE PROBLEMS WITH NON-PROPORTIONAL LOADING Z. Kapidzic¹, S.B. Lindström, Linköping University, Sweden; J. Lundgren¹; ¹Saab AB, Sweden The paper presents an efficient model for assessment of fatigue damage in plane problems with stress raisers and complex loading. The advantage of the proposed model over the conventional methods is that it includes the notch effect and alleviates the need for cycle counting. It is applicable to any plane problem. | ||||
| 10:30 | 11:00 | 7.10.2 |
FATIGUE OF NOTCHED STANDARD SPECIMENS – THE INFLUENCE OF THE STRESS GRADIENT ON THE S-N CURVE IN AL2024 S. Sieberer¹, J. Homan, Fatec Engineering, Netherlands; M. Schagerl¹; ¹Johannes Kepler University Linz, Austria The fatigue life of three designs of notched aluminium specimens with nominally similar stress concentration factor is compared by experimental testing. It is shown to be dependent on the geometry of the notch, i.e. the stress gradient, and size of specimen. Usual correction factors do not account for this and new approaches may be necessary to utilise the full potential of the material. | ||||
| 11:00 | 11:30 | 7.10.3 |
FATIGUE LIFE ENHANCEMENT OF TYPICAL AERONAUTICAL JOINTS BY MEANS OF ENGINEERED RESIDUAL STRESSES D. Fanteria¹, L. Boni ¹, F. Bovecchi¹, D.O. Busse, IRBUS Operations GmbH, Germany; D. Furfari, AIRBUS Operations GmbH, Germany; ¹University of Pisa, Italy The fatigue behaviour of a typical joint configuration, available in two variants, has been investigated, assessing also the influence of various treatments. Different batches of specimens were evaluated: basic material, Tartaric Sulphuric Acid anodized and also coupons subjected to fatigue enhancement processes, such as Cold eXpansion and Laser Shock Peening. | ||||
| 11:30 | 12:00 | 7.10.4 |
FATIGUE CHARACTERIZATION OF ADHESIVE JOINTS IN AEROPLANES-THE DEVELOPMENT OF A NEGATIVE LOAD RATIO (R<0) TESTING METHOD O. Orell¹, J. Jokinen¹, M. Kanerva¹; ¹Tampere University, Finland Adhesive joints are an efficient method to transfer high loads between structural components. High-performing adhesive joints require careful design and precise knowledge of the adhesive product used. Especially in aeroplanes, load spectra range from negative to positive load (factor) levels. It is well known that the trajectory of crack growth in adhesive joints is highly sensitive to local stress state and fracture toughness. However, up to date, there are no methods to accurately study fatigue of adhesive joints under varying load (positive-to-negative loading, i.e., load ratio R changing its sign). In this study, a testing system is developed to perform negative R fatigue testing of adhesive joints and mode II crack propagation. | ||||
| 12:00 | 12:30 | 7.10.5 |
FATIGUE DAMAGE MODEL OF HIGH TEMPERATURE POLYMER COMPOSITES IN AERO-ENGINES V.R. Pakkam Gabriel¹, P. Fernberg¹; ¹Luleå University of Technology, Sweden Results from development of a methodology for prediction of consequences of the damage accumulation occurring during fatigue loading of fiber reinforced polymer composites (FRPC) are presented. The methodology is developed with the intention of being applied to temperature resistant FRPC with potential use in e.g. aeroengine applications. | ||||
| Reserve Paper | 7.10.R |
FATIGUE CRACK PROPAGATION IN ADDITIVELY MANUFACTURED POLYMER PARTS H. El Fazani¹, J. Coil¹, J. Laliberté¹; ¹Carleton University , Canada | |||||
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| 10:00 | 10:30 | 8.10.1 |
DEVELOPMENT OF A PREDICTIVE DAMAGE METHODOLOGY FOR HYBRID WING BODY AIRCRAFT STRUCTURES H. Raza¹, C. Harey¹, P. Vaghela¹, J. Bayandor¹; ¹CRASH Lab, University at Buffalo, United States Presenter: Christopher Harley, CRASH Lab, Dept. of MAE, University at Buffalo The T-cap structure of Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) is investigated using advanced finite element modeling techniques. The study focuses on developing a comprehensive methodology to capture the damage response of T-cap structures under loading conditions. Computational results are validated using benchmark experimental data. | ||||
| 10:30 | 11:00 | 8.10.2 |
NUMERICAL ANALYSIS AND COMPARISON WITH RESULTS OF FRACTURE TESTS OF LUG MANUFACTURED IN COMPOSITE MATERIAL G.C. Fonseca, Embraer Minas Gerais, Brazil; S.F.M. Almeida, Instituto Tecnológico de Aeronáutica, Brazil The results obtained in this work will contribute to a better understanding of the behavior of thick laminated components in composite material subjected to tensile stresses. A failure analysis methodology will be presented for thick laminated type aeronautical components, based on the results of the numerical models studied and validated in comparison to the experimental results in the fracture region of the component. This study may contribute to new developments in structures of high structural responsibility with a high level of reliability with respect to the working limits of the component, avoiding unplanned failures in service and catastrophic damages. | ||||
| 11:00 | 11:30 | 8.10.3 |
ENHANCEMENT OF FLEXIBLE STRATEGY FOR AUGMENTING DESIGN POINTS FOR COMPUTER EXPERIMENTS AND APPLICATION TO A MDO OF A FAN-BLISK A. Tamkan¹, P. Flassig¹, M. Meyer, Rolls-Royce Deutschland, Germany; ¹Technische Hochschule Brandenburg, Germany Usually, the number of design points for DoEs is not known a priori or defined by heuristics. After DoE execution, it is often the case that models fitted to the data lack accuracy which leads to the need for additional design points or new DoE. The study proposes a highly efficient and universal method to augment an existing DoE and its application to an industrial Fan-Blisk design problem. | ||||
| 11:30 | 12:00 | 8.10.4 |
TRANSIENT AND FREE-VIBRATION ANALYSIS OF LAMINATED SHELLS THROUGH THE DISCONTINUOUS GALERKIN METHOD G. Guarino¹, V. Gulizzi¹, A. Milazzo¹; ¹1University of Palermo, Department of Engineering, Italy Presenter: Vincenzo Gulizzi, University of Palermo - Department of Engineering A novel formulation for linear dynamic analysis of laminated shell structures is presented, based on Interior Penalty discontinuous Galerkin methods and variable-order through-the-thickness kinematics. Shell geometry is described by a NURBS-based parametrization and the presence of cut-outs is accounted for implicitly by a level set function. Numerical tests are provided to assess capabilities and accuracy of the proposed formulation. | ||||
| 12:00 | 12:30 | 8.10.5 |
DESIGN AND STUDY ON NOISE REDUCTION PROPERTIES OF A MULTISTAGE BIONIC MEMBRANE-TYPE ACOUSTIC METAMATERIAL X.J. Zhang¹, D. Guo¹, H.Y. Huang¹; ¹School of Aeronautics, Northwestern Polytechnical University, China In order to solve the problem of low frequency noise, a multistage bionic spider web model was designed based on the structural characteristics of spider web.The results shows that the cobweb model can effectively control the noise propagation and the multistate antiresonance mode of thin films enables the acoustic metamaterials to have high noise reduction and wide noise reduction bandwidth. | ||||
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| 10:00 | 10:30 | 9.10.1 |
AEROELASTIC TAILORING OF COMPRESSOR BLADES A.-P. Chalke¹, N. Glodic¹, M. Gutierrez Salas¹; ¹KTH Royal Institute of Technology, Sweden Paper explores the potential of using carbon-fibre reinforced composites for designing low-pressure compressor blades with improved aeroelastic performance. Comparison between the blades with different laminate stackups is made with respect to the modal behaviour and aerodynamic damping. It is found that if carefully designed, the composite blades can provide higher aeroelastic stability than the reference metallic blade. At the same time the results reveal that a laminate stackup with stabilizing behaviour in one mode could have a destabilizing effect for the other mode. The dependency on ply angle and arrangement of plies in laminates is observed to be complex and further investigations and experimental validation is therefore deemed necessary. | ||||
| 10:30 | 11:00 | 9.10.2 |
RAPID AEROACOUSTIC PLANFORM DESIGN OPTIMIZATION OF INSTALLED PROPELLERS T. Sinnige¹, W. de Gruijl¹, W. de Haan¹, G. Eitelberg¹; ¹Delft University of Technology, Netherlands A rapid design method for aeroacoustic optimization of installed propellers is described. Comparisons are made between optimizations with and without installation effects taken into account, for a 5-deg angle of attack and a wake-encounter case. The results highlight the impact of the blade count on the aeroacoustic performance, and the impact of installation effects on the optimum design. | ||||
| 11:00 | 11:30 | 9.10.3 |
PERFORMANCE BENEFITS OF A FAN ON BLADE – FLADE – FOR A VARIABLE CYCLE ENGINE M. Assato, IAE, Brazil; A. Altar Inceer¹, L. Moraes¹, J. Takachi Tomita², C. Bringhenti², P. Bravo-Mosquera, USP, Brazil; D. Rosell, SAAB Aeronautcs, Sweden; T. Grönstedt¹; ¹Chalmers University, Sweden ;²ITA, Brazil The impact of the FLADE component on a variable cycle engine is studied. Firstly, the paper goes ahead and develops a new algorithm for the simulation of mode switching in generic performance tools by introducing dynamic equation systems. Secondly, the paper then studies the FLADE component and its potential performance benefits if added to a conventional turbofan architecture. | ||||
| 11:30 | 12:00 | 9.10.4 |
STATUS OF GKN AEROSPACE\\\'S ENGINE MODULE DEMONSTRATORS IN THE CLEAN SKY-2 PROJECT R. Lundberg¹, L. Ellbrant¹, P. Johansson¹, U. Johansson¹, M. Billson¹, B. Gustafsson¹; ¹GKN Aerospace Sweden AB, Sweden Presenter: Lars Ellbrant, GKN Aerospace Sweden AB GKN Aerospace Sweden AB in Trollhättan, Sweden, is a Core Partner in the Engines ITD (Integrated Technology Demonstrator) in Clean Sky-2, with responsibility for design, development and manufacturing of a number of complex engine structures and modules. The paper will give more detail on the design, development and TRL validation of these complex structures and modules. | ||||
| 12:00 | 12:30 | 9.10.5 |
STUDY ON THE OBJECTIVE FUNCTION OF THE PROFILED ENDWALL OPTIMIZATION OF AN EMBEDDED COMPRESSOR STATOR J. Wang¹, D. Meng¹, D. Feng¹, Q. Zhao¹; ¹Shenyang Engine Research Institute of AECC, China This paper studied the endwall profiling in the embedded stator of a multistage compressor, with the method of numerical optimization based on CFD and experimental test under multistage condition. Compared with the whole-blade-height parameter, the partial-blade-height parameter is more suitable as the objective function in improving the endwall flow and reducing the blade loss. | ||||
| Reserve Paper | 9.10.R |
EXPERIMENTAL STUDY ON THE EFFECT OF INTERSTAGE BLEEDING ON THE PERFORMANCE OF FULL-SCALE MULTISTAGE AXIAL COMPRESSOR Z.-B. Zhang¹, Y.-H. Zhang¹, Y.-H. Chen¹; ¹Shenyang Engine Research Institute, China | |||||
| Reserve Paper (Interactive) | 9.10.R |
SURGE CHARACTERISTICS IN FRONT OF EACH STAGE FOR A HIGH PRESSURE FIVE STAGE COMPRESSOR B.-B. Jia¹, Z.-B. Zhang¹, H.-X. Li, AECC, China; ¹AECC Shenyang Engine Institute, China | |||||
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| 10:00 | 10:30 | 10.10.1 |
INCREMENTAL NONLINEAR DYNAMIC CONTROL WITH SPARSE NON-PARAMETRIC BAYESIAN REGRESSION OF DAMAGED AIRCRAFT L. Kim¹, D. Lee¹, H. Bang¹; ¹Korea Advanced Institute of Science and Technology, South Korea It is important to control the fixed wing aircraft even when it is damaged for safe flight. For this problem, we proposed Incremental Nonlinear Dynamic Control as baseline controller and used Sparse Gaussian Process Regression to estimate uncertainties with unknown basis functions due to incremental dynamics. | ||||
| 10:30 | 11:00 | 10.10.2 |
FAULT-TOLERANT CONTROL FOR AIRCRAFT WITH STRUCTURAL DAMAGE USING GAUSSIAN PROCESS REGRESSION D.-W. Lee¹, L.-S. Kim¹, H.-C. Bang¹; ¹KAIST, South Korea This paper presents the design of fault-tolerant control using Gaussian Process regression to stabilize an aircraft with left-wing damage. The structural damage causes the change of mass, moment of inertia, center of gravity, and aerodynamic coefficient. These variation parameters and unmodeled dynamics make the system unstable. Hence, we need the data-driven fault-tolerant control approach to compensate for the uncertainty under unexpected situations. Unlike the parametric adaptive control approach, Gaussian Process regression is a non-parametric method that does not need prior information about the uncertainty. Therefore, we suggest the fault-tolerant control using Gaussian Process regression to estimate the structural fault uncertainty. The numerical simulation results are compared with sliding mode control to analyze the tracking performance and robustness. | ||||
| 11:00 | 11:30 | 10.10.3 |
EFFECTIVENESS ANALYSIS OF DOBC Q-FILTER PARAMETERS FOR A MULTICOPTER UAV H.J. Jeaong¹, C. Roh¹, Y.H. Jang¹, J.Y Suk¹, S.K. Kim¹; ¹Department of Aerospace Engineering, Chungnam National Universit, South Korea The closed-loop characteristics may change depending on the Q-filter variables, and the position or attitude tracking performance may vary significantly. In this study, the control performance according to the change of Q-filter variables will be finally analyzed through the quadrotor modeling and flight test verification process. | ||||
| 11:30 | 12:00 | 10.10.4 |
CONVEX PROGRAMMING-BASED OPTIMAL THREE-DIMENSIONAL MID-COURSE GUIDANCE WITH LOSSLESS CONVEXIFICATION C.-G. Jung¹, C.-H. Lee¹, M.-J. Tahk¹; ¹KAIST, South Korea The problem of optimal mid-course guidance is studied. The final velocity is maximized with sequential convex programming. First, missiles flight phase is divided into boost and glide phases. Then, dynamics are converted to input-affine form and convexification is applied to input variables. An adaptive trust region method is developed to robustly find the solution despite the crude initial guess. | ||||
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| 10:00 | 10:30 | 11.10.1 |
TOWARDS CORRECT-BY-CONSTRUCTION DESIGN OF SAFETY-CRITICAL EMBEDDED AVIONICS SYSTEMS I. Sander¹, I. Söderquist², M. Ekman², R. Jordao¹, F. Bahrami¹, R. Chen¹, A. Åhlander²; ¹KTH Royal Institute of Technology, Sweden ;²Saab AB, Sweden The paper presents a novel correct-by-construction methodology aiming at the design of future high performance and safety-critical embedded aircraft systems. The paper focuses on the underlying foundations of the methodology, and demonstrates how they can be exploited in system modelling, design space exploration and code generation. The methodology is evaluated by an industrial case study. | ||||
| 10:30 | 11:00 | 11.10.2 |
CONCEPT LEVEL EXPLORATION OF IMA-BASED NETWORKED PLATFORMS WITH MIXED TIME-SENSITIVE COMMUNICATION REQUIREMENTS R. Saar de Moraes¹, S. Nadjm-Tehrani¹; ¹Linköping University, Sweden In this paper, we apply a grammar-based approach to generate computation and communication platforms for avionic applications with mixed classes of time-sensitive communication messages. Then, we propose an evolutionary algorithm to schedule communication in the platform considering the interaction between timetriggered and bandwidth-constrained traffic. Together, the platform generation approach and the scheduling algorithm support the exploration of avionic systems at the concept level. | ||||
| 11:00 | 11:30 | 11.10.3 |
SYSTEMS ARCHITECTING ASSISTANT (SARA) - ENABLING A SEAMLESS PROCESS CHAIN FROM REQUIREMENTS TO OVERALL SYSTEMS DESIGN N. Kuelper¹, J. Broehan¹, T. Bielsky¹, F. Thielecke¹; ¹Hamburg University of Technology, Germany Novel aircraft concepts and disruptive technologies drive upcoming systems architectures. To ensure a seamless process chain from aircraft level to overall system design, the heuristic systems architecting assistant (SArA) methodology is proposed. Different architecture variants of electric power supply system architectures of a hydrogen-powered concept aircraft are elaborated by applying SArA. | ||||
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| 10:00 | 10:30 | 13.10.1 |
ATCO STRATEGIES IN TACTICAL TBO: A SIMULATOR STUDY M. Nylin¹, J. Nilsson¹, J. Lundberg², M. Bång²; ¹LiU/LFV, Sweden ;²LiU, Sweden Trajectory based management is an important concept in future air traffic management. However, strategic optimization may conflict with tactical traffic solutions if trajectories are not kept intact. We conducted a real-time simulation study with air traffic controllers to explore how tactical trajectory management affects the controllers’ strategies for conflict resolution. | ||||
| 10:30 | 11:00 | 13.10.2 |
TRAJECTORY-BASED OPERATIONS TO IMPROVE LONG-RANGE AIR TRAFFIC FLOW MANAGEMENT G. Enea, MIT Lincoln Laboratory, United States; J. Bronsvoort, Airservices Australia, Australia Presenter: Gabriele Enea, MIT Lincoln Laboratory Trajectory-Based Operations (TBO) is a new paradigm for managing air traffic by using controlled times along flight routes in order to create a schedule for orderly and efficient traffic flows. Currently used in the US and Australia to manage flights close to their arrival destination, in the future TBO is planned to be extended to control flights farther and farther away from their destination airport in order to increase the scope of potential benefits from this concept. However, in order to extend the TBO concept, the challenges of Long-Range Air Traffic Flow Management (LR-ATFM) need to be understood and mitigated given they are impacted by multiple sources of uncertainty affecting the creation of an accurate schedule of flights, several hours in advance. By characterizing the main sources of uncertainty affecting TBO and LR-ATFM, this paper will address the key areas to integrate these concepts: data exchange necessary, wind and weather data needs, type of control to apply (Ground Delays, Extended Metering, etc.) | ||||
| 11:00 | 11:30 | 13.10.3 |
ASSESSMENT OF ENERGY-EFFICIENT APPROACHES WITH INCREASED GLIDESLOPE ANGLES D. Vechtel¹, P. Pauly¹; ¹German Aerospace Center (DLR), Germany A means to reduce noise during approach is to increase the glideslope angle. The steeper the glidepath, the worse aircraft can reduce their speed to landing speed. Pilots configure the aircraft earlier or even use spoilers with deteriorating effects on noise. The aim of this work is to analyse the most influencing factors on the ability of aircraft to fly steeper approaches. | ||||
| 11:30 | 12:00 | 13.10.4 |
COMPETITIVITY, STRATEGY AND VALUE ON AIRPORTS A METHOD OF DIAGNOSIS, SUGGESTIONS AND ACTIONS FOR INTERNATIONAL AIRPORTS WITH A CASE STUDY OF CNF A.H.O. Carvalho, Pontifícia Universidade Católica de Minas Gerais – PUC Minas, Brazil; E.M.M. Torga, Centro Universitário UNA, Brazil; F.R.V. Paiva, Universidade FUMEC - Fundação Mineira de Educação e Cultura, Brazil The study identifies competitivity factors influencing airports, considering macroenvironment, market, corporate, and internal scenarios, estimating actions to minimize negative & maximize positive competitive factors identified from literature, secondary data, questionnaires answered by relevant professionals, and airports assessed in their fundamental characteristics in a comparative approach. | ||||
| 12:00 | 12:30 | 13.10.5 |
AIRCRAFT MASS ESTIMATION USING CRUISE FLIGHT PROFILE R. Mori, ENRI, Japan This paper proposes a new mass estimation method using the data of cruise segment. A clustering technique is used to extract the flight segment where the aircraft appears to fly near the cost-optimal altitude, and the mean absolute error of 3.29 % is achieved. | ||||
| Reserve Paper | 13.10.R |
KINETIC ENERGY RECOVERY FROM A LANDING AIRCRAFT: ENERGY ANALYSIS, ENVIRONMENTAL AND ECONOMIC PROSPECTS R. Camilleri¹, A. Batra¹; ¹Institute of Aerospace Technologies (IAT), University of Malta, Malta | |||||
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| 10:00 | 10:30 | 14.10.1 |
MODEL-BASED SYSTEMS ENGINEERING FOR FUTURE DIGITAL FLIGHT LINES (invited) M.A. Kelly, Lockheed Martin Aeronautics, United States Model-Based Systems Engineering (MBSE) and Model-Based Engineering (MBE) are being embraced globally to accelerate product development and modernization. How will these processes and tools impact the flight line? Who needs to act to ensure the benefits are maximized? What market trends should be leveraged to accelerate positive outcomes? This presentation will explore these questions. | ||||
| 10:30 | 11:00 | 14.10.2 |
GRAPH-BASED KNOWLEDGE REPRESENTATION AND ALGORITHMS FOR AIR AND MAINTENANCE OPERATIONS E. Olsson¹, O. Candell¹, P. Funk², R. Sohlberg², M. Castaño, Luleå University of Technology, Sweden; M. Gustafsson¹, P. Bladh¹; ¹Saab Aeronautics, Sweden ;²Mälardalen University, Sweden This work presents a framework for information exchange between adjacent air operations domains by means by means of graph technologies. | ||||
| 11:00 | 11:30 | 14.10.3 |
AUGMENTED REALITY FOR AIRCRAFT FATIGUE NON-DESTRUCTIVE EVALUATION M.J. Scott¹, S. Koschel¹, W. Verhagen¹, O. Levinski, Defence Science and Technology Group, Australia; P. Marzocca¹; ¹RMIT University, Australia This paper presents a novel framework for proactive condition-based maintenance using augmented reality (AR) in non-destructive evaluation of aircraft fatigue. Developed using a PC-9/A aircraft and Digital Twin, it enables maintainers via AR compatible devices to visualise fatigue ‘hotspots’ of the airframe, helping to identify damage and enhance maintenance tasks. | ||||
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| 13:30 | 14:00 | 1.11.1 |
CLEAN AVIATION PROGRAMME RATIONALE AND OVERVIEW (invited) R. van Manen, Clean Aviation, Belgium The European Green Deal will enshrine climate-neutrality objective by 2050 in legislation. The task facing the aviation sector in the next decades is to develop and introduce safe, reliable, and affordable low- to zero emission air transport for citizens and to concurrently ensure Europe’s industrial leadership is maintained and strengthened throughout the transition to a climate-neutral Europe. The trajectory towards climate-neutral aviation is achievable but will be contingent on: [1] an exceptional research and technology effort to reduce energy needs and fuel consumption, while ensuring safety and competitiveness; [2] fast-tracked development and deployment of sustainable aviation fuels/energy; [3] climate-optimised air operations and networks and [4] a suitable global aviation regulatory framework creating the conditions for a successful transition. Clean Aviation will develop and demonstrate by 2030 disruptive new aircraft technologies which will deliver greenhouse gas (GHG) reductions of no less than 30%, compared to 2020 state-of-the-art aircraft. The technological and industrial readiness will allow the deployment of new aircraft with this performance no later than 2035, enabling 75% of the world’s civil aviation fleet to be replaced by 2050. The aircraft developed will enable net CO2 reductions of up to 90% when combined with the effect of sustainable ‘drop-in’ fuels, or zero CO2 emissions in flight when using hydrogen as energy source. | ||||
| 14:00 | 14:30 | 1.11.2 |
ULTRA-EFFICIENT AIRCRAFT AND PROPULSION ARCHITECTURES FOR LOW-EMISSION SHORT/MEDIUM RANGE [SMR] AIRCRAFT (invited) M. Calvo Blanco, Belgium The SMR Thrust in Clean Aviation will develop ultra-efficient propulsion and aircraft architectures to address the short- and medium-range needs with innovative aircraft architectures making use of highly integrated, ultra-efficient thermal propulsion systems and providing disruptive improvements in fuel efficiency. This will be essential for the transition to low/zero emission energy sources (synthetic fuels, non-drop in fuels such as hydrogen), which will be more energy intensive to produce, more expensive, and only available in limited quantities. An integrated approach to the overall aircraft and its design, development, certification, production, and operations and close alignment to aviation policy and infrastructure development will be essential to enable widespread, rapid deployment, and ensure a cost-competitive and ultra-low emissions aviation system by 2050. | ||||
| 14:30 | 15:00 | 1.11.3 |
HYBRID-ELECTRIC AND FULL ELECTRIC ARCHITECTURES FOR LOW-EMISSION HYBRID-ELECTRIC REGIONAL [REG] AIRCRAFT (invited) A. Marino, Belgium The HER Thrust will pursue hybrid electric and full electric architectures – driving research into novel (hybrid) electrical power architectures and their integration, and maturing technologies towards the demonstration of novel configurations, on-board energy concepts and flight control. An integrated holistic approach with the integration of propulsion, energy storage and systems into the airframe and overall aircraft design, while safeguarding a highly competitive acquisition and operating cost for operators can power a renaissance in regional air travel. The overall value proposition and minimal environmental impact of such a re-invented regional aviation system will ensure air mobility remains competitive while being equally sustainable as alternative modes of transport. | ||||
| 15:00 | 15:30 | 1.11.4 |
DISRUPTIVE TECHNOLOGIES TO ENABLE ZERO-CARBON HYDROGEN–POWERED [HPA] SHORT RANGE AIRCRAFT (invited) P. Trinchieri, Belgium The HPA Thrust will develop disruptive technologies to enable aircraft and engines to exploit the compelling potential of hydrogen as a non-drop-in alternative zero carbon fuel and to spearhead the development of solutions that can enable the market entry of hydrogen powered commercial flight. The focus will be on the challenges related to the utilisation of liquid hydrogen and the impact on storage, distribution, cryogenics and thermal management and design changes needed at aircraft, systems and powerplant level. Close cooperation with other EU and national programmes related to the production, distribution, storage, and liquefaction of Hydrogen, inter alia with the Clean Hydrogen Joint Undertaking will ensure the aircraft technology development and future deployment is synchronised with capabilities and infrastructure on ground. | ||||
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| 13:30 | 14:00 | 2.11.1 |
AERODYNAMIC CHARACTERISTICS OF BOX WINGS FOR AN INNOVATIVE EVTOL CONFIGURATION E. Shima, Japan Aerospace Exploration Agency, Japan; K. Yonezawa, Central Research Institute of Electric Power Industry, Japan; R. Nishida¹, S. Honda¹, M. Sato¹; ¹Kogakuin University, Japan The purpose of this study is to understand the aerodynamic characteristics of box wings using wind tunnel experiments and CFD to realize an innovative eVTOL that is lightweight and simple. It was found that box wings have characteristics suitable for a convertible VTOL, such as low drag near cruise compared to a normal cantilever , and low drag during transition flight. | ||||
| 14:00 | 14:30 | 2.11.2 |
IMPACT OF THE NUMBER OF WING STATIONS ON THE TWIST DISTRIBUTION OF A BWB CONCEPTUAL AIRCRAFT DESIGN IN A MDAO ENVIRONMENT TO MATCH TARGET LIFT DISTRIBUTION B. Fröhler¹, M. Iwanizki¹, P. Balack¹, J. Häßy¹, D. Silberhorn¹; ¹German Aerospace Center (DLR), Germany The design of BWBs, an optimized wing twist is important to achieve high aerodynamic performance, but on conceptual design level the number of wing stations is often limited to reduce complexity and impedes this optimization. Therefore, this paper presents the feasibility of flexible number of wing stations to achieve an aerodynamically optimized wing twist. | ||||
| 14:30 | 15:00 | 2.11.3 |
CS2 – MANTA – MULTI-FUNCTIONAL FLAP MECHANISM OFFERING A SECOND DEGREE OF FREEDOM M. Desmet¹, J. Vervliet¹, D. De Wit¹, R. Seidler, Deutsches Zentrum Fuer Luft und Raumfahrt E.V., Germany; J. Docter, Netherlands Aerospace Centre, Netherlands; B. Everaert¹; ¹Asco Industries nv/sa, Belgium The novel multi-functional flap mechanism saves weight by combining high-lift, load alleviation and roll control functionalities into one large control surface. The mechanism offers a second degree of freedom to the flap and this may lead to a performance increase and reduction on the fuel burn and emission of an aircraft. | ||||
| 15:00 | 15:30 | 2.11.4 |
INFLUENCES OF CHANGING THE INSTALLING POSITIONS OF MULTIPLE WINGLETS ON AERODYNAMIC CHARACTERISTICS E. Kobayashi¹, K. Chiba¹; ¹The University of Electro-Communications, Japan We investigated the effects on the aerodynamic characteristics by installing multi-winglets position on aircraft wingtips because the previous study implemented a single position. We have conducted numerical analyses for two wing geometry patterns with three winglets. Consequently, the multi-winglets improved the performance of the main wing with upwind-type than downwind-type. | ||||
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| 13:30 | 14:00 | 3.11.1 |
COOLING SYSTEM OF STRATOFLY HYPERSONIC VEHICLE: CONCEPTUAL DESIGN, NUMERICAL ANALYSIS AND VERIFICATION R. Scigliano¹, V. De Simone¹, R. Fusaro², D. Ferretto², M. Marini¹, N. Viola²; ¹Italian Aerospace Research Center - CIRA scpa, Italy ;²Politecnico di Torino (PoliTo), Italy This paper describes the thermal design processes of STRATOFLY hypersonic vehicle cooling system showing either the methodology and the supporting FEM numerical simulations. It focuses on two different regions that are both subjected to severe overheating: air-intake leading edges and the combustion chamber. Final remarks on structure survivability are presented. | ||||
| 14:00 | 14:30 | 3.11.2 |
HYPERSONIC AIRCRAFT AND MISSION CONCEPT RE-DESIGN TO MOVE FROM MACH 8 TO MACH 5 OPERATIONS N. Viola¹, R. Fusaro¹, D. Ferretto¹, O. Gori¹, M. Marini², P. Roncioni², B.O. Cakir³, A.C. Ispir³, B.H. Saracoglu³; ¹Politecnico di Torino, Italy ;²CIRA, Italy ;³VKI, Belgium Presenter: Oscar Gori, Politecnico di Torino This paper discloses the design of a new Mach 5 civil passenger aircraft developed in the H2020 MORE&LESS Project, by exploiting the results of the previous H2020 STRATOFLY Project. To assure that the highest aerodynamic, propulsive, and operating performance are reached when approaching Mach 5 conditions, instead of the original Mach 8, a multidisciplinary methodology is developed and applied. | ||||
| 14:30 | 15:00 | 3.11.3 |
LTO NOISE AND SONIC BOOM PREDICTIONS IN EARLY CONCEPTUAL DESIGN PHASES G. Piccirillo¹, S. Graziani¹, R. Fusaro¹, N. Viola¹; ¹Politecnico di Torino, Italy This paper discloses a workflow to integrate LTO noise and sonic boom predictions since the beginning of the design of future supersonic civil aircraft. The application of state-of-the-art models to future high-speed case study is discussed and solutions to overcome limitations are presented. The workflow is validated against Concorde literature data and then applied to the design of a future sustainable Mach 2 aircraft. | ||||
| 15:00 | 15:30 | 3.11.4 |
SIMPLIFIED MODELS FOR THE PRELIMINARY AERODYNAMIC CHARACTERIZATION OF HIGH-SPEED VEHICLES TO SUPPORT MISSION ANALYSIS O. Gori, Politecnico di Torino, Italy This paper reports the use of simplified models for the evaluation of aerodynamic performance of high-speed vehicles, to support mission analysis during the conceptual design phase. These methods are applied to two reference vehicles: the waverider STRATOFLY MR3 and a Concorde-like configuration. The accuracy of each method is evaluated, then empirical corrections are implemented. | ||||
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| 13:30 | 14:00 | 4.11.1 |
ACCURATE TWO-DIMENSIONAL STEADY-STATES FOR THE SUPERSONIC FLOW OVER A COMPRESSION CORNER R. Santos¹, L. Alves¹, N. Cerulus², H. Quintanilha Jr², V. Theofilis²; ¹UFF, Brazil ;²UoL, United Kingdom The present paper describes the numerical issues that had to be overcome in order to generate of accurate steady-states for the supersonic flow over a compression corner. Low-order schemes generate steady-states contaminated by temporal content. Switching to high-order schemes, however, eventually leads to disturbance free steady-states. | ||||
| 14:00 | 14:30 | 4.11.2 |
NUMERICAL MODELING OF LAMINAR-TURBULENT TRANSITION IN AN INTERCONNECTING COMPRESSOR DUCT A. Capitao Patrao¹, B. González Lozano¹, I. Jonsson¹, C. Xisto¹; ¹Chalmers University of Technology, Sweden Cryogenic hydrogen is being considered as a future aviation fuel since it eliminates CO2, CO, soot, sulphur, and unburnt hydrocarbons emissions. The storage temperature and high cooling capacity of cryogenic hydrogen also makes it a suitable coolant. In this paper a integrated heat exchanger in an interconnecting compressor duct (ICD) is analyzed with respect to heat transfer and transition. | ||||
| 14:30 | 15:00 | 4.11.3 |
ANALYSIS OF A LAMINAR SEPARATION BUBBLE ON A NACA0009 AIRFOIL AT DIFFERENT BACKGROUND DISTURBANCE LEVELS J.S. Kern¹, A. Hanifi¹, D.S. Henningson¹; ¹FLOW, Department of Engineering Mechanics, KTH Royal Institute o, Sweden The laminar separation bubble forming on a NACA0009 airfoil at a steady pitch angle of 8 degrees and Reynolds number of 200 000 under the influence of free-stream disturbances is computed using high-fidelity large-eddy simulations. The extracted flow data is analysed using Spectral Proper Orthogonal Decomposition (SPOD) to extract the dominant structures in exhibiting spatio-temporal coherence. | ||||
| 15:00 | 15:30 | 4.11.4 |
A STUDY ON THE NUMERICAL SIMULATION OF FLOW TRANSITION INCLUDING CROSSFLOW EFFECTS A.R.S. Righi, ITA, Brazil; G.L.O. Halila¹, J.L.F. Azevedo¹; ¹IAE, Brazil The laminar-turbulent transition triggered by crossflow vortices is important for aeronautical applications. The Langtry-Menter transition model, coupled to the SST model, is implemented and evaluated. This work is concerned with an assessment of different empirical correlations to address crossflow effects. The impact of different freestream turbulent properties is also addressed and discussed. | ||||
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| 13:30 | 14:00 | 5.11.1 |
COMPUTATIONALLY ECONOMICAL METHODS FOR LANDING GEAR NOISE SIMULATIONS R. Spencer, CFMS Ltd, United Kingdom; M. Allan, Zenotech Ltd, United Kingdom Landing gear generates lots of noise, but traditional aero-acoustic simulations are very expensive. In this paper, two cheaper simulation methods are applied to a landing gear acoustic test case and compared to the literature. First, an LES simulation using an Octree mesh and no grown boundary layer mesh is used. Secondly, a stochastic simulation using the Fast Random Particle Method is used. | ||||
| 14:00 | 14:30 | 5.11.2 |
PROPELLER AEROACOUSTIC MODELS IN VARIABLE-FIDELITY DESIGN OPTIMIZATION W. Klimczyk¹, A. Sieradzki¹; ¹Lukasiewicz Research Network - Institute of Aviation, Poland Current work provides a summary of crucial aspects in defining the propeller aeroacoustic optimization framework. It is focused on: defining the design process framework and selection of suitable aeroacoustic models. The advantages and limitations of using various models are discussed. The potential of merging data from models of various fidelities to speed up the optimization process is assessed. | ||||
| 14:30 | 15:00 | 5.11.3 |
NUMERICAL PREDICTION OF FOCUS BOOM GENERATED BY MANEUVERS S. Han¹, Y. Xu¹; ¹Chinese Aeronautical Establishment, China The acceleration from subsonic to supersonic performed by supersonic civil aircraft generates focus boom on the ground. The intensity of focus boom is several times higher than that of the cruising sonic boom, which greatly exceeds the low boom requirements for the commercial flight of supersonic civil aircraft. A numerical prediction method for sonic boom focusing based on the Lossy Nonlinear Tricomi Equation was studied and computational aeroacoustics techniques were applied to reduce the dispersion and dissipation caused by numerical method. The corresponding focus boom prediction code CBoom_NLTE, was developed. The numerical verification of the developed code was performed using SCAMP flight data, which indicates that the program has a high accuracy. The influence of the atmospheric loss mechanism and the accelerating rate of flight on the acoustic characteristics of the focus boom were investigated. The atmospheric loss mechanism can dissipate the acoustic energy in high frequency component and reduce the Perceived Loudness, which indicates that the atmospheric loss mechanism should be taken into consideration for sonic boom focusing prediction. | ||||
| 15:00 | 15:30 | 5.11.4 |
IN-FLIGHT MEASUREMENTS AND ESTIMATION OF SONIC BOOM SIGNATURE OF SUPERSONIC AIRCRAFT L. Qu, China; S. Han, China; Y. Song, China; Y. Xu, China; Y. Zhang, China; Y. Wang, China Sonic boom is one of the key problems to be solved in the development of supersonic civil aircraft. In-flight flow-field signature measurements is the most direct method to study the sonic boom characteristics of supersonic aircraft. It can provide truly credible verification data for the sonic boom prediction method and low sonic boom design technology, which is of great significance to the design of a new generation of low-sonic boom supersonic civil aircraft. Technologies related to sonic boom flight test track planning, ground-air integrated large-scale array sonic boom measurement are developed. A special in-flight sonic boom test programme was carried out, collecting multiple sets of sonic boom measured data under real atmospheric conditions, which confirmed the rationality of the in-flight test plan. The sonic boom waveform measured on track has significant correlation. The relative error of the sonic boom signal bow shock peak is about 18%, which of the tail shock peak is about 8%. The duration of the sonic boom signature is around 0.1s. The far-field boom measured data and numerical prediction results are compared and analyzed. The basic shape of the sonic boom signatures obtained is consistent, and the duration is relatively close. The relative error between the peak values of the bow shock and the wing leading edge shock is less than 5%; the subjective loudness evaluation of the sonic boom was carried out by the Stevens loudness method, and the loudness levels of the far-field sonic boom signals obtained were all around 120PLdB, with the error less than ±1PLdB, which verified the reliability of the sonic boom prediction method. | ||||
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| 13:30 | 14:00 | 6.11.1 |
WALL INTERFERENCE CORRECTIONS USING NONLINEAR LEAST-SQUARES OPTIMISATION S. Noel¹, D.M. Birch², J.J. Doherty², T. Tipnis¹; ¹QinetiQ, United Kingdom ;²University of Surrey, United Kingdom A novel approach to correcting the effects of wall interference has been developed for closed-wall wind tunnels using a nonlinear least squares optimisation process. The method is shown to apply blockage corrections to bluff bodies in line with the existing two-variable method, and achieves superior drag corrections through an improved representation of upwash interference for lifting bodies. | ||||
| 14:00 | 14:30 | 6.11.2 |
A NEW FACILITY FOR HYPERSONIC FLOW SIMULATION DRIVEN BY A HIGH VELOCITY OXYGEN FUEL GUN A. Esposito, DEPT.OF INDUSTRIAL ENGINEERING UNIVERSITY OF NAPLES FEDERICO II, Italy; C. Allouis, STEMS-CNR, Italy; M. Lappa, Dept of Mech. and Aer.Engineering, University of Strathclyde, United Kingdom This paper reports on the development of a new Blowdown-Induction Facility driven by a High Velocity, Oxy Fueled Gun. The facility is conceived for Aerothermodynamic Applications, specifically to Test candidate materials for Thermal Protection Systems and simulate effectively Hypersonic Sustained Flows. | ||||
| 14:30 | 15:00 | 6.11.3 |
RECENT ACTIVITIES ON FLOW QUALITY ASSESSMENT AT THE EUROPEAN TRANSONIC WINDTUNNEL J.H. You¹, M.C.N. Wright¹, H. Quix¹; ¹European Transonic Windtunnel GmbH, Germany The present paper describes ETW’s recent activities on the flow quality assessment. Around 25 years after the primary flow quality assessment and several changes to the tunnel circuit, the new flow quality assessment confirms ETW’s ability to perform high-Reynolds-number laminar flow testing at low subsonic conditions as well as transonic Mach numbers. | ||||
| 15:00 | 15:30 | 6.11.4 |
INVESTIGATION ON CORRECTION OF TUNNEL WALL INTERFERENCE FOR DYNAMIC AIRFOIL TEST IN LOW-SPEED WIND TUNNEL Y. Jiao, China; H. Zou, China; B. Chen, China; C. Xiao, China Presenter: Yuqin Jiao Three kinds of correction methods for the wall interference of the dynamic airfoil wind tunnel test are proposed: 1. Experimental method; 2. Numerical simulation correction method; 3. The correction method based on the principle of image system and wall pressure signature method. The first two methods are easy to implement and give correct results, but are not easy to use in usual experiments. The third method is easy to apply, the workload is small, and the results are correct, but it still needs further research and improvement. | ||||
| Reserve Paper | 6.11.R |
DEVELOPMENT AND VERIFICATION OF OSCILLATING BLADE GUST GENERATOR IN LOW-SPEED WIND TUNNEL C. Bu¹, Z. Ma¹, Y. Zhang¹, L. Li¹; ¹AVIC Aerodynamics Research Institute, China | |||||
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| 13:30 | 14:00 | 7.11.1 |
DEVELOPMENT OF MULTI-CANARD UAV FOR ACTIVE AEROELASTIC CONTROL TOWARD PSEUDO-SMALL SATELLITES N. Morita¹, S. Nakasuka¹, T. Tsuchiya¹, K. Takashima¹, Y. Taguchi¹, K. Suzuki¹, T. Koyama¹, R. Eto¹, I. Baba¹; ¹the University of Tokyo, Japan To demonstrate and research the technology of active aeroelastic control, an experimental aircraft equipped with multiple canards has been developed and flight-tested. In this paper, the design and development of aerodynamic, structural, and control systems and the results of flight tests of this experimental aircraft are presented, and its application to pseudo-small-satellite is discussed. | ||||
| 14:00 | 14:30 | 7.11.2 |
INFLUENCE OF OVERALL LAYOUT DESIGN OF COMPOUND MULTI-ROTOR VEHICLES ON FLIGHT PERFORMANCE Y. Huang¹, M. Bando¹, S. Hokamoto¹; ¹Kyushu University, Japan The overall layout design of multi-rotor vehicles has great influence on flight performance. Traditional multi-rotor vehicles are usually not capable of high-speed flight and long endurance. This study discusses compound multi-rotor vehicle configurations and analyze the influence of the overall layout of multi-rotors on flight performance by Particle Swarm Optimization (PSO). | ||||
| 14:30 | 15:00 | 7.11.3 |
USE OF MULTIPLE LOW COST AUTONOMOUS DRONES FOR HIGH VOLTAGE LINE INSPECTION L.D. Jesus¹, A.J.D. Filho¹, M.A. Almeida¹, W. M. Martins¹, T.C. Pimenta¹, A.C.B. Ramos¹, L. A. Baldochi¹, L.O. Carvalho¹, P. Funk, Mälardalen University, Sweden; ¹Federal University of Itajubá, Brazil Given that high-voltage online inspection is essential today, the proposal is to assemble three low-cost drones that can perform autonomous flights, with an artificial intelligence embedded in each, where the first inspects the wires, according to inspect the tower and third inspect the servitude range independently, issuing alert in cases of irregularity in the area. | ||||
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| 13:30 | 14:00 | 8.11.1 |
A PRELIMINARY STRUCTURAL DESIGN OF A FLEXIBLE FLYING DEMONSTRATOR P.J. González¹, G. Stavorinus¹, H. Shahi¹, Y.M. Meddaikar², S. Cumnuantip², A. Voß², T. Klimmek², W.R. Krüger², F.J. Silvestre¹; ¹TU-Berlin, Germany ;²DLR, Germany Presenter: Pedro J. González, TU-Berlin This paper shows the preliminary structural design of the flexible aircraft demonstrator TU-Flex. This vehicle can gather coupled flight and structural dynamics data to validate flexible aircraft models. Due to its unconventional requirements, novel numerical procedures were used during conceptual and preliminary structural design. The full structural FEM and maneuver load envelope are presented. | ||||
| 14:00 | 14:30 | 8.11.2 |
DEVELOPMENT AND APPLICATIONS OF A VIRTUAL HYBRID PLATFORM FOR MULTISCALE ANALYSIS OF ADVANCED STRUCTURES OF AIRCRAFT (DEVISU) E. Carrera, Politecnico di Torino, Italy; U. Galvanetto, University of Padova, Italy; S. De Rosa, Università degli Studi di Napoli, Italy; P. Gardonio, University of Udine, Italy; A. Milazzo, Università degli Studi di Palermo, Italy; R. Vescovini, Politecnico di Milano, Italy; M. Zaccariotto, University of Padua, Italy This paper outlines the main findings of the project “DEvelopment and applications of a VIrtual hybrid platform for multiscale analysis of advanced StructUres of aircraft” (DEVISU), which deals with failure of composite structures and noise/vibration reduction, along with investigation of new materials for aerospace applications. | ||||
| 14:30 | 15:00 | 8.11.3 |
VIBRO-ACOUSTIC ANALYSIS OF MULTI-LAYER CYLINDRICAL SHELL-CAVITY SYSTEMS VIA CUF FINITE ELEMENTS M.C. Moruzzi¹, M. Cinefra, Poliecnico di Bari, Italy; S. Bagassi¹, E. Zappino, Politecnico di Torino, Italy; ¹Università di Bologna, Italy The noise footprint of a commercial passenger aircraft depends on several parameters. The sound travels through vibrations, which are displacements in a rigid body. These variables are described by the structural models depending on the structures itself and on other parameters. In this paper we apply an innovative shell model, based on Carrera's Unified Formulation, on a cylindrical structure. | ||||
| 15:00 | 15:30 | 8.11.4 |
WING LOADING PROCESS IN KNOWLEDGE-BASED AIRCRAFT DESIGN AND OPTIMIZATION FRAMEWORK S. Hosseini¹, H.R. Ovesy¹, M.A. Vaziri-Zanjani¹; ¹Amirkabir University of Technology, Iran An automated wing loading process is developed to be used in a multi-fidelity knowledge-based aircraft design framework. The overall process includes development of load cases, trimming, load distribution, and filtering of critical cases. This process is validated with available and verified data of a regional aircraft. In the end, this process is applied to a novel truss-braced wing jet aircraft. | ||||
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| 13:30 | 14:00 | 9.11.1 |
TECHNOLOGY MATURATION IN CLEAN SKY 2 FOR NEXT GENERATION SMR ENGINE C. Diette, Safran Aircraft Engines, France; E. Obert, Safran, France; G. Marion, Safran Transmission Systems, France; H. De Franssu, Safran Nacelles, France; A. Frezet, Avio Aero, Italy; B. Walther, GE Deutschland, Germany; A. Sjunnesson, GKN Aeropsace Engie Systems, Sweden Presenter: Christophe DIETTE, Safran Aircraft Engines Within Clean Sky 2 programme, the Ultra High Propulsive Efficiency (UHPE) demonstrator is tackling propulsion systems emissions for the Short & Medium Range market. Following engine architecture studies and multiple maturation studies, it has progressed towards an innovative architecture showing high potential on CO2 savings. It will target TRL5 on the LP modules technologies. | ||||
| 14:00 | 14:30 | 9.11.2 |
NOVEL AIRCRAFT PROPULSION AND AVAILABILITY OF ALTERNATIVE, SUSTAINABLE AVIATION FUELS IN 2050 J. Kos¹, J. Posada-Duque², B. Peerlings¹, N. Ben Salah², N. Lim¹, W. Lammen¹, I. Stepchuk, TU Delft, Faculty of Technology and Policy Management, Netherlands; E. van der Sman¹, M. Palmeros-Parada²; ¹Royal Netherlands Aerospace Centre, Netherlands ;²TU Delft, Faculty of Applied Sciences, Netherlands This paper investigates green hydrogen and bio-based sustainable aviation fuels, including their production technology and feedstock, in combination with Clean Sky 2 propulsion technologies and novel hydrogen-powered propulsion technologies. The impact that these alternative aviation fuels and propulsion technologies can have on greenhouse gas emissions is identified and the demand for alternative aviation fuels is compared with their expected availability, both until 2050. | ||||
| 14:30 | 15:00 | 9.11.3 |
MULTIDISCIPLINARY ASSESSMENT OF A YEAR 2035 TURBOFAN PROPULSION SYSTEM T. Grönstedt¹, C. Xisto¹, X. Zhao¹, I. Jonsson¹, A. Reinap², M. Genrup², N. Glodic³, M. Guiterrez Salas³, M. Lejon*, R. Avellan*, H. Mårtensson*; ¹Chalmers University, Sweden ;²Lund University, Sweden ;³Royal Institute of Technology, Sweden ;*GKN Aerospace, Sweden A conceptual design of a geared year 2035 turbofan is developed evaluating its mission CO2, noise and NOx emissions. An electric generator and a fan integrated cooling system is described, and the booster, HPC and LPT are subject to more detailed aero and mechanical design. Top-level component data is re-introduced back into the system model to evaluate system benefits. | ||||
| 15:00 | 15:30 | 9.11.4 |
LOW BPR TURBOFAN PERFORMANCE WITH POWER EXTRACTION D. Rosell, Saab Aeronautics, Sweden; T. Grönstedt, Chalmers Univerity of Technology, Sweden; P.D. Bravo-Mosquera¹, F. Martini Catalano¹; ¹University of Sao Paulo, Brazil A performance analysis of power extraction from a low bypass ratio mixed flow turbofan engine has been performed. Power extraction from the high-pressure and low-pressure shaft was evaluated at key parts of a fighter aircraft mission. It is shown how the engine net thrust and thrust specific fuel consumption depend on the mission definition, engine control limiters and the use of the afterburner. | ||||
| Reserve Paper (Interactive) | 9.11.R |
COMPARISON OF ANALYTICAL SEMI-EMPIRICAL MODEL FOR JET NOISE PREDICTION F. Petrosino¹, M. Barbarino¹; ¹CIRA, Italy | |||||
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| 13:30 | 14:00 | 10.11.1 |
ON LATERAL-LONGITUDINAL CONTROL COUPLING FOR SHORT- AND LONG-FUSELAGE BWB AIRCRAFT CONFIGURATIONS L.M.B.C. Campos, Instituto Superior Técnico, Universidade de Lisboa, Portugal; J.M.G. Marques, Universidade de Évora, Portugal The coupling of the longitudinal and lateral stability modes of an aeroplane is considered in two cases: weak coupling & strong coupling. The method presented in this paper is applied to the two flying wing designs concerning all modes in a total of eighteen flight conditions and the conclusion compares them not only from the point of view of flight stability, but also from other viewpoints. | ||||
| 14:00 | 14:30 | 10.11.2 |
OPEN-LOOP SUBSPACE IDENTIFICATION OF A FLEXIBLE UNMANNED AERIAL SYSTEM R.C. Machado, Instituto de Fomento e Coordenação Industrial (IFI), Brazil; D.F.C. Zúniga, 2Universidade Estadual Paulista Júlio de Mesquita Filho, Brazil; A. Souza, Instituto Superior Técnico de Lisboa, Portugal; T. Rosado¹, L.C.S. Góes¹; ¹Instituto Tecnológico de Aeronáutica, Brazil Presenter: Clécio Fischer This paper presents the identification of an Unmanned Aerial System (UAS) with flexible wings from open-loop data using subspace methods. For aerodynamic and flight control system, a reliable model is important to comprehend the system behaviour and to design a feedback loop, that can be applied as well to minimize the effects of structural flexibility. | ||||
| 14:30 | 15:00 | 10.11.3 |
LATERAL-DIRECTIONAL AERODYNAMIC MODELLING FOR NUMERICAL RESULTS USING NEURO-FUZZY WITH DIFFERENTIAL EVOLUTION V.T. Sant' Ana¹, I. Staack, Linköping University, Sweden; R.M. Finzi Neto¹; ¹Federal University of Uberlândia, Brazil This work has the objective to present an alternative methodology to obtain an unsteady aerodynamic model of an aircraft. The methodology used to accomplish this objective is a computational intelligence technique known as Neuro-Fuzzy, which combines the interpretability of Fuzzy Inference Systems with the adaptability of Artificial Neural Networks. The artificial intelligence technique will be supplied with numerical data acquired in XPLANE flight simulator, using a reduced scale model of the Cessna 182 airplane. After accomplishing the model, validation graphs are built to ensure the reliability of the model. | ||||
| 15:00 | 15:30 | 10.11.4 |
COMPARATIVE ANALYSIS OF AERODYNAMIC CHARACTERISTICS OBTAINED BY ANALYTICAL, PANEL AND CFD METHOD G. Muchla¹, A. Kwiecien¹; ¹Faculty of Power and Aeronautical Engineering, WUT, Poland Presenter: Adrianna Kwiecien, Faculty of Power and Aeronautical Engineering, WUT In the paper, description of methods that have been applied for calculations of loads on biplane wings are contained. Computation and comparison of aerodynamic coefficients for examined aircraft are presented. Analyses of stall are performed. Selection of optimal computational method is discussed. | ||||
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| 13:30 | 14:00 | 11.11.1 |
HETEROGENEOUS SYSTEMS MODELLING IN SUPPORT OF INCREMENTAL DEVELOPMENT R. Hällqvist¹, J. Naeser¹, J. Wallén Axehill¹, E. Herzog¹; ¹Saab AB, Sweden An integrated approach to development combining incremental development, MBSE and modeling and Simulation is presented. The proposed approach is exemplified and the application of FMI and the role of the novel SSP standard is presented. | ||||
| 14:00 | 14:30 | 11.11.2 |
A MODEL BASED SYSTEMS ENGINEERING APPROACH TO STREAMLINED NOISE CERTIFICATION OF TRANSPORT-TYPE AIRCRAFT D. Kim¹, F. Karagoz¹, S. Datta¹, M. Balchanos¹, D.H. Anvid¹, E.D. Harrison¹, D.N. Mavris¹; ¹Georgia Institute of Technology, United States This paper presents an approach for a model-based system verification for the validation of system design: applicable to the 14 CFR Part 36 Noise certification of transport aircraft. The goal is to present a streamlined process for certification utilizing a model-based verification through integration of system design model and current industry certification processes. The presented approach is demonstrated through a verification of a system under test (SUT), a transport-type aircraft block model, and a system verification model for the Federal Aviation Administration (FAA) 14 CFR Part 36 Noise Standards as a component of aircraft Type Certification. Both the aircraft and verification model are based on model-based systems engineering (MBSE) and utilizes systems modeling language (SysML). In order to implement the model into current practice of transport-type certification, the paper captures findings and inputs obtained by aircraft manufacturers, translates regulations to requirements, constrains requirements through modeled current procedures, verifies the SUT based on the constraints, and outputs the results as artifacts utilized in current certification process. The integrated model enhances data integrity, communication between stakeholders, and assessment of | ||||
| 14:30 | 15:00 | 11.11.3 |
A HOLISTIC AIRCRAFT CABIN METAMODEL AS AN APPROACH TOWARDS AN INTERCONNECTED DIGITISED CABIN LIFECYCLE M.C. Berschik¹, M. Blecken¹, H. Kumawat¹, J.-E. Rath¹, D. Krause¹, R. God¹, T. Schüppstuhl¹; ¹Hamburg University of Technology, Germany Advancing digitalisation, growing passenger needs and constantly changing requirements are leading to increased pressure on aircraft manufacturers. To address these challenges, the proposed holistic metamodel brings together all relevant product information in one central place to improve the product lifecycle and drive the coordination of all stakeholders. | ||||
| 15:00 | 15:30 | 11.11.4 |
A COLLABORATIVE DESIGN METHOD FOR CIVIL AIRCRAFT BASED ON AN ENDURING AND EVOLUTIONARY AUTHORITATIVE SOURCE OF TRUTH X. Sun¹, M. Luo¹, Z. Cui¹, Z. Ji¹, H. Liu¹; ¹Beihang University, China A human-software-hardware hybrid collaborative design method is proposed for civil aircraft based on an enduring authoritative source of truth and an aircraft conceptual schema. A future civil aircraft is designed conceptually in a collaborative environment based on the method. The results show that the collaborative design method can improve design efficiency and shorten the development cycle. | ||||
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| 13:30 | 14:00 | 12.11.1 |
EXPERIMENTAL ANALYSIS OF HEAT TRANSFER CHARACTERISTICS OF DIELECTRIC BARRIER DISCHARGE PLASMA ACTUATOR A. Hatamoto¹, K. Emori¹, H. Nishida¹; ¹Tokyo University of Agriculture and Technology, Japan The DBDPA is attracting attention as a device to prevent icing on airfoils because it induces airflow along the wall and generates heat through electrical discharge. The purpose of this study is to quantitatively clarify the heat transfer coefficient and temperature of the airflow of the DBDPA induced. For this purpose, the measured surface temperature is fitted to an analytical solution. | ||||
| 14:00 | 14:30 | 12.11.2 |
THE SENS4ICE EU PROJECT – SENSORS AND CERTIFIABLE HYBRID ARCHITECTURES FOR SAFER AVIATION IN ICING ENVIRONMENT – PROJECT OVERVIEW AND INITIAL RESULTS C.W. Schwarz, DLR, Germany The EU project SENS4ICE (GA no 824253) addresses reliable detection and discrimination of supercooled large droplets (SLD) icing conditions: technology development, icing wind tunnel and flight test. A hybrid approach combines direct sensing (atmospheric conditions / ice accretion) with indirect techniques based on changing aircraft characteristics. | ||||
| 14:30 | 15:00 | 12.11.3 |
STRESS AND ENERGY RELEASE RATE INFLUENCE ON ICE SHEDDING WITH RESONANT ELECTROMECHANICAL DE-ICING SYSTEMS G. Gastaldo¹, V. Palanque, ISAE-Supaero and ONERA, France; M. Budinger, INSA/ICA, France; V. Pommier-Budinger¹; ¹ISAE-Supaero, France Electromechanical ice protection systems (IPS) induce mechanical failure of ice layer. To design an efficient IPS, it is necessary to study the fracture mechanisms at play. This paper proposes an evaluation of the influence of stress and energy criteria on fracture propagation for different modes through numerical analyses and experiments. | ||||
| 15:00 | 15:30 | 12.11.4 |
NUMERICAL SIMULATION OF ICE ACCRETION ON A PITOT TUBE K. Szilder¹, P. Forsyth¹; ¹National Research Council, Canada The objective of this contribution is to demonstrate that the developed numerical tools, which consist of CFD, drop trajectory, and ice accretion modules, are able to simulate ice accretion on pitot tubes and its dependency on anti-icing heating. Developed tools will help reduce the number of icing wind tunnel test cycles before probe certification. | ||||
| Reserve Paper | 12.11.R |
EFFECTS OF ANISOTROPIC THERMAL CONDUCTIVITY OF COMPOSITE SHIELD ON THE ELECTROTHERMAL ANTI-ICING SYSTEMS X. Guo¹, Q. Yang¹, H. Zheng¹, W. Dong¹; ¹Shanghai Jiaotong University, China | |||||
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| 13:30 | 14:00 | 13.11.1 |
NEW ENTRANTS’ AIRSPACE INTEGRATION IN JAPAN: JAXA’S ONGOING CONTRIBUTION N. Matayoshi, Japan Aerospace Exploration Agency, Japan Initial UAS and eVTOL use cases in Japan are expected to focus on disaster response applications. The JAXA has identified technical challenges, including surveillance, flight intent sharing and mission information sharing. To address these challenges, JAXA plans to leverage the existing technologies and expertise gained through Disaster Relief Aircraft Information Sharing Network development. | ||||
| 14:00 | 14:30 | 13.11.2 |
ON KEY PARAMETERS FOR THE ATTRACTIVENESS OF ON-DEMAND INTER-CITY AIR MOBILITY T. Ehlers¹, S. Hagemann², V. Gollnick², K. Lütjens¹; ¹German Aerospace Center, Germany ;²Hamburg University of Technology, Germany We present a globally applicable approach for estimating the potential passenger demand for On-Demand Air Mobility on low-demand inter-city routes. It is used for estimating the impact of parameters like range, speed, transfer times and usable airports. We conduct this investigation for four regions: The US, the EU, China and India, and analyze the differences between these regions. | ||||
| 14:30 | 15:00 | 13.11.3 |
THE AUTOMATION EVOLVES: CONCEPT FOR A HIGHLY AUTOMATED CONTROLLER WORKING POSITION I. Gerdes¹, M. Jameel¹, R. Hunger¹, L. Christoffels¹, H. Gürlük¹; ¹German Aerospace Center DLR, Germany This concept of an automated Controller Working Position is to enable Air Traffic Management, to deploy Single Controller Operations in a resilient and safe manner. To achieve this goal, a cooperating digital controller is proposed, which can autonomously assess traffic situations, make decisions and execute actions based on artificial intelligence | ||||
| 15:00 | 15:30 | 13.11.4 |
AN OPERATIONAL CONCEPT FOR THE INTEGRATION OF URBAN AIR MOBILITY VEHICLES INTO THE AIR TRAFFIC CONTROL PROCESSES I.C. Metz¹, S. Schier-Morgenthal¹; ¹German Aerospace Center DLR, Germany A major use case for Urban Air Mobility is a shuttle service to and from airports. This paper proposes an operational concept for the safe and efficient integration into local air traffic control processes. The concept includes workflows and assistance systems to be validated in real-time human-in-the-loop simulations. | ||||
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