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| 09:55 | 10:20 | 1.1.1 |
THE WHOLE JOURNEY: PEOPLE, PLANET AND PROGRESS AT QANTAS F Messent, Qantas Group, Australia The Qantas Group, which operates Qantas and Jetstar, has committed to a target of net zero emissions by 2050, backed by an interim goal to reduce net emissions by 25% by 2030 (relative to 2019). This presentation provides an overview of the strategy, challenges, opportunities, and progress towards a more sustainable future at Qantas, including investments in Sustainable Aviation Fuel and the Group’s largest ever fleet renewal program. | ||||
| 10:20 | 10:45 | 1.1.2 |
JAL’ CHALLENGE TO THE NET-ZERO GH GAS EMISSION MS Suzuki, JAL, Japan JAL’ challenge to the Net-zero greenhouse gas emissions | ||||
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| 09:55 | 10:20 | 3.1.1 |
AURAL DIGITAL TWIN FOR AIRCRAFT CABIN DESIGN M.C, Moruzzi, Università di Bologna, Italy The development of new technologies, aircraft configurations, materials, and methods can lead to significant reductions in aircraft internal noise. This work aims to develop and validate, through an experimental campaign, a method for creating virtual mock-ups of passenger cabins with both visual and aural layers to evaluate variations in visual and acoustic comfort using a human-centred approach. | ||||
| 10:20 | 10:45 | 3.1.2 |
AUTOMATED KNOWLEDGE-BASED CABIN DESIGN AND EVALUATION WITHIN A PRELIMINARY AIRCRAFT DESIGN LOOP S. Hellbrück, DLR e.V., Germany A new multidisciplinary preliminary aircraft design process integrates an novel automated knowledge-based cabin and structural design approach which supports new disruptive cabin concepts.It enhances the overall aircraft design fidelity and allows for the efficient assessment of the integration and performance of multiple cabin configurations within one aircraft. | ||||
| 10:45 | 11:10 | 3.1.3 |
ASSESSING THE POTENTIAL OF MULTI-MODEL TOPOLOGY OPTIMIZATION FOR MODULAR LIGHTWEIGHT DESIGN OF AIRCRAFT CABIN STRUCTURES P. Inselmann, TUHH, Germany This paper investigates the potential of Multi-Model Topology Optimization for modular lightweight aircraft cabin structures. By comparing Multi-Model and Single-Model Optimization results, the influence of simulation parameters is analyzed, demonstrating both the applicability of MMO and its increased sensitivity to parameter selection in early design phases. | ||||
| 11:10 | 11:35 | 3.1.4 |
A FRAMEWORK FOR AUTOMATED SYSTEM COMPONENT PLACEMENT IN AIRCRAFT CONCEPTUAL DESIGN J.J Vézina, Concordia University, Canada Innovative methods are required to address the system integration challenges of novel, sustainable aircraft. This work proposes a framework for automated component placement in aircraft conceptual design that supports engineering assessments, design space exploration, and optimization while accounting for thermal, maintenance, safety, and wiring constraints. | ||||
| Reserve Paper | 3.1.R |
MULTI-STATE FLIGHT DECK DISPLAY LAYOUT OPTIMIZATION UNDER FAILURE AND REVERSION SCENARIOS Y Yamai, Tsukuba University, Japan | |||||
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| 09:55 | 10:20 | 4.1.1 |
LAMTA: A LAMINAR TAILORED WING WITH CATNLF AND HLFC FOR EXTRA LONG RANGE J. Ruberte Bailo, German Aerospace Center (DLR), Germany A Natural Laminar Flow (NLF), backward swept wing with a lift coefficient of 0.52, a wingspan of 63.84 meters and an aspect ratio of 11.74 for a Reynolds number of 44.6 Million and a Mach number of 0.83 has been de- veloped during the Laminar Tailored Aircraft (LamTA) project. Starting with the preliminary design, a reference lift distribution, a thickness distribution, and a detailed turbulent design was developed, looking for the best Lift- Drag-Weight trade-off. An outstanding glide ratio of 25.64 was achieved which has been further improved to TBD by implementing laminar flow. In order to achieve laminar flow on the configuration, Crossflow Attenuated Natural Laminar Flow (CATNLF) profiles were designed in wingspan region from 85% inwards. The config- uration has been designed using the DLR in-house inverse design code and the stability analysis coco/lilo. | ||||
| 10:20 | 10:45 | 4.1.2 |
AERODYNAMIC CIRCULATION CONTROL FOR ULTRA-STOL ON THE SEAFLIGHT AURA-E ELECTRIC CARGO DRONE DEMONSTRATOR GC Doig, UNSW Sydney, Australia Seaflight Technologies developed a fixed-wing 6.5m wingspan cargo drone flight demonstrator, working with Australian universities. This battery-electric aircraft incorporates aerodynamic circulation control to achieve ultra-short takeoff and landing with attached flow over flaps up to 60 degrees. This allows the wings to be very high aspect ratio, extending cruise range by as much as 30%. | ||||
| 10:45 | 11:10 | 4.1.3 |
EVALUATION OF PERCEIVED X-15 FLYING QUALITIES BASED ON RAPID AERODYNAMIC PREDICTIONS H.B. Rogers¹, T.T. Takahashi¹, J.A. Camberos¹, R.V. Grandhi¹; ¹AFIT, United States We examine the utility of rapid aerodynamic prediction methods to support the design of high-speed vehicles. Conceptual-design aerodynamic data can predict bare-airframe and augmented-control flying qualities of high-speed aircraft like the X-15. We study its motions using ELOS analysis and time-domain non-linear simulations. We compare our computation with actual pilot reports from flight test. | ||||
| 11:10 | 11:35 | 4.1.4 |
MULTIDISCIPLINARY APPROACH FOR THE AERODYNAMIC CHARACTERIZATION OF AN INFLATABLE CLOSED-WING HYBRID HIGH-ALTITUDE PSEUDO-SATELLITE Eleonora Riccio¹, Rocco Bombardieri¹, Alessandro Ceresa¹, Vincenzo Rosario Baraniello¹, Francesco Tufano¹, Giuseppe Persechino¹, Domenico Coiro, University Federico II of Naples, Italy; ¹Italian Aerospace Research Centre, Italy This paper shows that pressurization-induced structural deformations significantly affect the aerodynamic performance, trim, and stability of a closed-wing hybrid inflatable HAPS. Results indicate that designing on nominal rigid geometries can lead to inaccurate cruise and control predictions, supporting the inclusion of structural–aerodynamic effects in early aircraft design | ||||
| Reserve Paper | 4.1.R |
RESEARCH ON OVERALL AERODYNAMIC DESIGN OF GRID-DUCT INTEGRATED VERTICAL TAKE-OFF AND LANDING (VTOL) FIXED-WING AIRCRAFT B.L Li, Northwestern Polytechnical University, China | |||||
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| 09:55 | 10:20 | 5.1.1 |
LARGE EDDY SIMULATIONS OF LOW-REYNOLDS NUMBER FLOWS IN THE COMPRESSIBLE REGIME P. Catalano, CIRA - Italian Aerospace Research Center, Italy The focus of the paper is on the numerical simulations of flows at low Reynolds number at subsonic Mach numbers. The interest for the compressible aerodynamics of low-Reynolds number flow has recently grown for the possible use of aircrafts for exploring the Martian surface. Large eddy simulations have been performed for the flow around the NACA 0012-34 airfoil at low Reynolds number and Mach numbers varying from 0.20 to 0.61. The achieved results are compared to reference data available in literature. The focus is on the role of the Mach number and in particular on the behaviour of the lift coefficients that do not follow the classical compressibility rules. | ||||
| 10:20 | 10:45 | 5.1.2 |
LAMINAR SEPARATION ON AN AIRFOIL WITH PERTURBATION OF BOUNDARY CONDITIONS E. Tangermann, UniBw München, Germany Laminar separation is very sensitive to perturbations of the boundary conditions. Using numerical simulations, the present study provides an assessment of the impact of boundary perturbations to laminar separation on a quasi two-dimensional airfoil configuration. The two aspects of surface unevenness and ambient turbulence are considered in parametric variations. | ||||
| 10:45 | 11:10 | 5.1.3 |
VARIATIONAL MULTISCALE LES OF PRE-STALL SEPARATION ON A LOW-REYNOLDS AIRFOIL C. Brunelli, Royal Military Academy, Belgium This work presents a Variational Multiscale Large Eddy Simulation of pre-stall low-Reynolds flow over the Eppler 387 airfoil. The unified VMS formulation provides subgrid-scale modeling and stabilization, enabling accurate prediction of laminar separation bubbles and surface quantities without ad hoc transition models. | ||||
| 11:10 | 11:35 | 5.1.4 |
REYNOLDS NUMBER EFFECTS OF A BIRD-FEATHER-INSPIRED POROUS-MEDIUM AIRFOIL ZhaoPeng Zhang¹, ZhengYin Ye¹; ¹Northwestern Polytechnical University, China This bird-feather-inspired porous-medium airfoil can significantly enhance lift and lift-to-drag ratio, and is capable of suppressing leading-edge separation within certain Reynolds number ranges. The present findings provide physical insights into the aerodynamic role of bird feather distributions and offer guidance for the design of biomimetic porous airfoils in low-Reynolds-number applications. | ||||
| Reserve Paper | 5.1.R |
TURBULENCE MODELLING IN URBAN ENVIRONMENTS FOR UAV DESIGN CRITERIA DL Laubscher, South Africa | |||||
| additional information (interactive) | 5.1.R |
NUMERICAL STUDY ON DYNAMIC STALL OF FIGHTER AIRCRAFT AT HIGH ANGLE OF ATTACK USING DYNAMIC IMPROVED DELAYED DETACHED EDDY SIMULATION H. Wang¹, T. Lin¹, G. Wang¹; ¹Northwestern Polytechnical University, China Presenter: Huiyue Wang, Northwestern Polytechnical University | |||||
| additional information (interactive) | 5.1.R |
ASSESSING VORTEX BREAKDOWN AND COUPLING IN DELTA WING PLANFORMS THROUGH HIGH-FIDELITY DDES SIMULATIONS T. A. Missato, Brazil | |||||
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| 09:55 | 10:20 | 6.1.1 |
RESPONSE CHARACTERISTICS OF WINGTIP VORTEX INSTABILITY TO EXTERNAL DISTURBANCES Yiming Wu¹, Zhenglin Xiao¹, Yang Xiang¹, Ziyi Zhu¹; ¹Shanghai Jiao Tong University, China This work reveals that vortex decay is driven by critical-layer expansion, which disrupts core symmetry and causes spanwise stretching. This distortion enhances mean-flow coupling, increasing wandering amplitude by 30% and amplifying Reynolds stresses. This establishes a self-reinforcing energy transfer loop, providing key insights for managing aircraft wake vortex lifespan | ||||
| 10:20 | 10:45 | 6.1.2 |
NONLINEAR 3-DOF MOTION PREDICTION OF A BOX IN WAVES USING PHYSICS-INFORMED NEURAL OPERATORS ZP Hoffman, Australia This paper presents an interpretable, data-driven surrogate model for real-time prediction of the coupled 3-DoF surge–heave–pitch motion of a freely floating rectangular box in waves. A validated high-fidelity CFD framework is used to generate long time-series datasets of body motion and local wave measurements across a range of wave frequencies and steepnesses, spanning near-linear and strongly nonlinear response regimes. The proposed approach combines Sparse Identification of Nonlinear Dynamics (SINDy) with an interpretable neural-operator (Onet) surrogate. SINDy is first used to identify a compact set of high order coupled nonlinear oscillator equations that provide priori constrains for the potential set of coefficients describing the box’s motion. The neural operator network then learns a continuous mapping of these coefficients over the input space (wave-measurements), enabling motion prediction for unseen input waves. Initial results indicate that the surrogate can, in real-time, reproduce CFD-predicted motion trajectories with good fidelity under complex loading. Beyond this benchmark problem, the framework is in principle applicable to other fluid–body interaction problems, where a rigid body can be represented by a low-order state description and the model coefficients vary smoothly with parameters or measured inputs | ||||
| 10:45 | 11:10 | 6.1.3 |
THIN AEROFOILS OSCILLATING IN A CONFINED INVISCID FLOW J-M Mourad, ISAE-Supaero, France Confinement effects strongly influence aerodynamic measurements in wind tunnels by accelerating the flow and altering wake development. This work presents an unsteady vortex-lattice solver to model two oscillating aerofoils in confined inviscid flow. Confinement is represented using mirror and blockage methods, allowing wake deformation and wake–wall interaction. Validation against literature and in-house experiments shows good agreement and highlights the impact of reduced frequency, spacing, and oscillation amplitude on gust intensity and wake structure. | ||||
| 11:10 | 11:35 | 6.1.4 |
INTERACTION OF COUNTER-PLUNGING BIPLANE AIRFOILS WITH A FLAT PLATE BOUNDARY LAYER AND WAKE B. Anilir, METU Aerospace Engineering Department, Turkey The aim of the current study is to numerically investigate the unsteady aerodynamics of a counter-plunging biplane configuration inside the boundary layer and the wake of a flat plate at low Reynolds number flows. This arrangement is inspired by previously proposed micro air vehicle (MAV) concepts employing biplane plunging propulsive systems operating close to the main body. The effects of incoming shear flow and wake deficit along with the vortex interaction and merging mechanisms on thrust generation and efficiency will be analyzed. | ||||
| Reserve Paper | 6.1.R |
CHARACTERISTICS AND UNDERLLYING MECHANISMS OF VORTEX WANDERING NONE Gao, China | |||||
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| 09:55 | 10:20 | 7.1.1 |
INVESTIGATION OF DISTRIBUTED PROPELLER PROPULSIVE CHARACTERISTICS UNDER NON-AXIAL INFLOW B.-X. Boming, School of Aeronautics, Northwestern Polytechnical University, China To address DEP aircraft challenges in crosswinds, this paper investigates non-axial inflow effects on distributed propulsive characteristics. Using CFD validated by wind tunnel tests, we analyze aerodynamic performance across varying propeller spacings and quantities. The study reveals interference mechanisms caused by sideslip and quantifies efficiency impacts. The research findings aim to provide theoretical support and data references for the layout optimization of distributed propulsion systems and the modeling of flight control laws in robust crosswind environments. | ||||
| 10:20 | 10:45 | 7.1.2 |
EFFECT OF LIP/NOZZLE DEFLECTION ANGLE ON THE AERODYNAMIC AND PROPULSIVE CHARACTERISTICS OF PROPULSIVE WING UNITS Ming-Hao: M. -H Li, Northwestern Polytechnical University, China This study numerically analyzes a distributed propulsive wing (DPW) for eVTOLs, focusing on variable lip/nozzle deflection. A parametric model and CFD simulations (MRF method) examine key geometric and flow parameters. Results show deflection angle critically affects aero-propulsive performance. The work provides design insights through aero-propulsive coupling. | ||||
| 10:45 | 11:10 | 7.1.3 |
PROPELLER AERODYNAMICS UNDER NON-UNIFORM INFLOWS S. Montagner¹, J. Serpieri¹, G. Cafiero¹; ¹Politecnico di Torino, Italy Presenter: Sara Montagner, Politecnico di Torino Unmanned Aerial Vehicles (UAVs) operate in a complex's environment, where propellers often encounter non-uniform inflows. These conditions can deteriorate the performance and stability of the vehicle, making standard uniform-inflow assumptions unrealistic. In this work we detail the effects of non uniform inflows on propellers, exploring a broad range of inflow conditions. | ||||
| 11:10 | 11:35 | 7.1.4 |
AERODYNAMIC EFFECTS OF DISTRIBUTED PROPELLER PLACEMENT ON LIFT CHARACTERISTICS OF A WING–FLAP CONFIGURATION H.-X. He, China This study numerically investigates the impact of distributed propeller positions on the lift characteristics of a wing-flap configuration during the takeoff phase. The effect of propeller slipstream location on fluctuations in the spanwise lift distribution is studied, and the underlying mechanisms of these fluctuations are analyzed through flow fields, with implications for STOL aircraft design. | ||||
| Reserve Paper | 7.1.R |
DATA-DRIVEN AERODYNAMIC MODEL OF THE DISTRIBUTED PROPULSION WING Baiyang Li, China; Xiaoping Zhu, China; Zhou Zhou, China; Minghao Li, China; Rui Wang, China Presenter: Minghao Li, School of Aeronautics, Northwestern Polytechnical University | |||||
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| 09:55 | 10:20 | 8.1.1 |
FINITE ELEMENT MODELLING OF ADDITIVELY MANUFACTURED TANTALUM UNDER HIGH-HEAT CONDITIONS FOR AEROSPACE APPLICATIONS M.J Davids, HH Industries, South Africa This work will provide insight into the use of Finite Element Modelling for use in the additive manufacturing industry, to assist in resource management for countries with material limitations, like South Africa. By validating the use of FE modelling for AM Tantalum components under high-heat conditions, the design of components for aerospace applications can be optimised without wastage. | ||||
| 10:20 | 10:45 | 8.1.2 |
NUMERICAL AND EXPERIMENTAL ANALYSIS OF TENSILE BEHAVIOR OF 2024-T6 ALUMINUM ALLOY OBTAINED BY DIRECT SELECTIVE LASER MELTING R. P. Solís, University Technical Federico Santa María, Chile The study aims to experimentally and numerically characterize the tensile behavior of an Al–Cu alloy fabricated by Direct Selective Laser Melting. The properties obtained are compared with both conventionally manufactured 2024 and reported data for additively manufactured aluminum alloys, contributing to the understanding of the capabilities and limitations of DSLM for aerospace-grade Al–Cu alloys | ||||
| 10:45 | 11:10 | 8.1.3 |
4D PRINTING VIA ELECTROMAGNETISM FOR COMPOSITE STRUCTURES SHV Vattathurvalappil, King Fahd University of Petroleum and Minerals, Saudi Arabia This paper presents a 4D printing approach using magnetite-reinforced thermoplastic composites that undergo programmable deformation and motion under external electromagnetic fields. Additively manufactured ABS–Fe?O? structures demonstrate contactless magnetic actuation and induction-assisted heating, enabling shape morphing and adaptive behavior for aerospace and smart structural applications. | ||||
| 11:10 | 11:35 | 8.1.4 |
ACCESSIBLE MATERIAL COMPOSITES FOR UAVS IN HUMANITARIAN AND DEVELOPMENT CONTEXTS C Koutsambasis, RMIT University , Australia This paper explores accessible composite materials for UAV airframes in humanitarian and development contexts. Using locally sourced cotton fabrics, low-cost, and simple materials, composites were fabricated, tested, and applied to a flying-wing UAV. Results demonstrate feasibility for low-cost, locally manufacturable UAVs that support localisation and capacity building. | ||||
| Reserve Paper | 8.1.R |
COMPRESSION AND FATIGUE PERFORMANCE OF ADDITIVELY MANUFACTURED NITI ARCHITECTED SHAPE MEMORY ALLOYS B.B. Zwerink, NLR, Netherlands | |||||
| Reserve Paper | 8.1.R |
DETECTION OF SURFACE DISCONTINUITIES IN ADDITIVELY MANUFACTURED ALSI10MG USING THERMOELASTIC STRESS ANALYSIS J. D. Rodrigues, RMIT University, Australia | |||||
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| 09:55 | 10:20 | 9.1.1 |
ONTOLOGY-BASED EXPLORATION OF SYSTEM-OF-SYSTEMS ARCHITECTURES USING A FEDERATED STRUCTURE L. Knöös Franzén, Linköping University, Sweden System-of-systems architecture design coordinates independent systems with diverse goals, posing challenges for traditional modelling methods. This paper introduces a federated ontology-based approach for early-stage architecture exploration for system of systems, using description logic to support semantic queries. A wildfire suppression case study shows how suitable architectures are identified. | ||||
| 10:20 | 10:45 | 9.1.2 |
DIGITAL TWIN FOR AIR DEFENSE: LIVE-VIRTUAL-CONSTRUCTIVE INTEGRATION AND DECISION SUPPORT S. Malka¹, O. Yakimenko¹, M. Ben-Simon¹; ¹Naval Postgraduate Shcool, United States Integrated Air and Missile Defense (IAMD) is a strategic system-of-systems (SoS) comprising command-and-control (C2), radars, optical sensors, networks, launchers, interceptors, and datalinks operating under strict interoperability constraints. Digital twin (DT) concepts provide a dynamic digital representation of a physical system, continuously synchronized with operational data and grounded in Model-Based Systems Engineering (MBSE) principles. In air defense SoS modeling, the greatest value lies not only in high-fidelity physics but in creating a holistic ecosystem that integrates live operations, virtual analysis, and constructive reasoning to enable data-driven decisions and actionable operational recommendations. This paper proposes a reference architecture for an air-defense DT designed to support Live-Virtual-Constructive (LVC) integration. Based on well-defined requirements, this paper presents an MBSE-driven decomposition into data, model, and decision layers, forming an LVC interface that supports training, testing, operations, and Verification, Validation, and Accreditation (VV&A). The result is a practical blueprint for building an operational DT-enabled decision-support capability for complex defense SoS—while remaining standards-compliant and unclassified. | ||||
| 10:45 | 11:10 | 9.1.3 |
COARSE–FINE COUPLED MBSE FOR SURVIVABILITY PARAMETER DESIGN OF STEALTH CARRIER-BASED TANKER P.F Li, Northwest Polytechnic University, China For the scientific forward design of new stealth carrier-based tanker (SCBT) survivability parameters, this paper integrates DoDAF-based coarse-grained requirement models with fine-grained survivability computation models under MBSE. A traceable design chain and full-link data transmission are established, offering a systematic MBSE solution for accurate SCBT survivability parameter design. | ||||
| 11:10 | 11:35 | 9.1.4 |
INTERFACING MISSION SIMULATION WITH INTELLIGENT AGENTIC SYSTEMS FOR OPERATIONAL AND ETHICAL EVALUATION H. Budig¹, E. Zegarra Berodt¹, N.-G. Wood¹, V. Gollnick¹; ¹Hamburg University of Technology, Germany Intelligent agentic systems play an increasing role in to date military systems, raising urgent ethical considerations. This paper describes a method to implement AI-algorithms into commercial wargaming simulation software, with a focus on airborne systems. A specific interface is presented to link the simulation to new intelligent agentic systems and evaluate them. | ||||
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| 09:55 | 10:20 | 10.1.1 |
NEURAL NETWORK BASED SLIDING MODE CONTROL FOR HYPERSONIC LONGITUDINAL CONTROL H. Kim, South Korea We propose NN-SMC for hypersonic longitudinal tracking where a neural tuner updates SMC design parameters online using control commands, states & sliding surface. Filtered and rate-limited ? prevents oscillations. Under identical uncertainties, NN-SMC improves velocity transient convergence and reduces residual errors while maintaining stable altitude tracking versus fixed-? SMC in simulation. | ||||
| 10:20 | 10:45 | 10.1.2 |
ON ROBUST AIRCRAFT CONTROL WITH AI: TARGETED TRAINING STIMULI OVER EXPERIENCE VOLUME C Koopman, University of Malta, Malta AI-based aircraft control offers potential advantages in robustness, however, realization requires approaches that differ fundamentally from classical control. This paper highlights these differences and examines how specific flight conditions shape learned control–response relationships, showing that carefully designed training exposure improves robustness more effectively than maximizing experience volume | ||||
| 10:45 | 11:10 | 10.1.3 |
SUPPORTING PILOT SITUATIONAL AWARENESS BY EXTRACTING INSIGHTS FROM AN AI EXPERT C Koopman, University of Malta, Malta Loss of control in commercial aircraft can occur even within safe flight envelopes, arising from the human–automation gap and becoming especially critical in complex or failure conditions. This paper explores how knowledge extracted from an AI system can enhance pilot situational awareness, informing on failures, recovery maneuvers, and dynamic safe flight states without replacing the pilot. | ||||
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| 09:55 | 10:20 | 11.1.1 |
ADAPTIVE FLIGHT CONTROL LAWS APPLIED TO AIR REFUELING WITH RECEIVERS EQUIPPED WITH RECEPTACLE OUT OF THE PLANE OF SYMMET M-J Martinez, Airbus, Spain Air refueling operation with receivers equipped with receptacles out of plane of symmetry is challenging from a flight control laws view, so this paper aims at presenting the most problematic issues found and how we solved them. This adaptive algorithm has been tested in Singapore in 2023 and is now certified after almost 300 automatic contacts between the A330-MRTT and F-15SG receivers. | ||||
| 10:20 | 10:45 | 11.1.2 |
BACKSTEPPING-BASED PREDICTIVE PERFORMANCE CONTROL FOR AERIAL REFUELING BOOM ATTITUDE CONTROL Y. L. Niu, Beihang University, China This paper addresses boom attitude control in flying-boom aerial refueling. A PPC-based backstepping controller confines tracking errors within predefined bounds for guaranteed transient and steady-state behavior. A sliding-mode observer compensates lumped disturbances. Simulations show high accuracy, strong rejection, and compliance with performance constraints. | ||||
| 10:45 | 11:10 | 11.1.3 |
AIRBRAKES CONTROL SYSTEM FOR PRECISE APOGEE CONTROL OF A SOUNDING ROCKET N. Gee-Landman, Royal Melbourne Institute of Technology, Australia An airbrakes control system has been developed to provide precise apogee control for the Atlas sounding rocket. The approach uses a model predictive control algorithm supported by Kalman-filter-based state estimation and reduced-order modelling. Monte Carlo simulations demonstrate robust performance under a range of uncertainty, with over 80% of flights achieving apogee within 5 m of the target. | ||||
| 11:10 | 11:35 | 11.1.4 |
FIXED-WING AIRCRAFT PORT-HAMILTONIAN DYNAMICS AND CONTROL E. M. Fernandes, Instituto Tecnologico de Aeronautica, Brazil This work presents a port-Hamiltonian (pH) model for fixed-wing aircraft. The pH framework enables an energy-based perspective for system analysis and control design, emphasizing modularity and physical insight. This approach offers significant advantages for the aerospace industry and broader transportation sectors by facilitating complex system integration and analysis. | ||||
| Reserve Paper | 11.1.R |
BENEFITS AND DRAWBACKS OF USING DIFFERENTIAL THRUST WITH DEP FOR FLIGHT CONTROL ON PROPELLER DRIVEN FIXED WING AIRCRAFT T. Sachtleben Dahmann, DLR, Germany | |||||
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| 09:55 | 10:20 | 12.1.1 |
IMPACT OF SYSTEM LATENCIES ON PILOT INTERACTION AND HANDLING OF AN ELECTRICALLY POWERED GYROPLANE UAV WITH FPV-BASED REMOTE CONTROL G. Schmitz, Germany The design, implementation, and experimental validation of a 450 kg electrically powered gyroplane drone operated via a ground-based first-person view control station is presented in this study. Emphasis is placed on system architecture, the end-to-end control and feedback chain, and the impact of latency on the pilot’s ability to safely handle the vehicle. | ||||
| 10:20 | 10:45 | 12.1.2 |
RECONFIGURABLE MULTILEVEL BATTERY ARCHITECTURE FOR SMALL UAV PROPULSION SYSTEMS N Sorokina, Universität der Bundeswehr München, Germany This paper investigates the feasibility of a multilevel battery system applied to an octocopter. A multilevel battery is implemented using Li-ion cells and compared against a LiPo battery with equal mass and energy. Experimental measurements are conducted on platform to characterize thrust–power relationships and validate system operability. In addition, a detailed simulation model is developed. | ||||
| 10:45 | 11:10 | 12.1.3 |
ROTATIONAL STABILITY ENHANCEMENT OF A SMALL TWO STROKE ENGINE FOR SMALL UAV WITH INTEGRATED FLYWHEEL CLUTCH SYSTEM H.-R. Gwon, Korean Air / R&D Center, South Korea This paper proposes a flywheel-integrated clutch system for small UAV two-stroke engines to enhance rotational stability during start and idle. By integrating a high-inertia flywheel into the clutch, the design mitigates instability. Structural and dynamic analyses confirm the system ensures operational safety and significantly improves propulsion reliability. | ||||
| 11:10 | 11:35 | 12.1.4 |
DYNAMIC MODELING AND STATE-SPACE SIMULATION OF PASSIVE LANDING GEAR FOR FIXED-WING UAVS L. H. J. Machado, UFMG, Brazil A passive landing gear for a fixed-wing UAV is modeled as a two-degree-of-freedom mass–spring–damper system and simulated through a state-space approach to analyze impact response. The model enables rapid assessment of stiffness–damping trade-offs on sprung-mass displacement and acceleration, supporting early sizing and optimization of UAV and other small-scale impact-attenuation systems. | ||||
| Reserve Paper | 12.1.R |
A DISTRIBUTED MULTI-SOURCE SENSOR FUSION METHOD FOR COLLABORATIVE TARGET TRACKING J. Cheng, China | |||||
| Reserve Paper | 12.1.R |
DEVELOPMENT OF A MODULAR SENSOR FUSION PAYLOAD FOR FLIGHT TESTING OF VISUAL-INERTIAL NAVIGATION ALGORITHM IN SMALL UAVS A Fathurrahman, Insitute Teknologi Bandung, Indonesia | |||||
| additional information (interactive) | 12.1.R |
SYSTEM-LEVEL ARCHITECTURE OPTIMISATION FOR GROUND AND TERMINAL OPERATIONS OF NARROW-BODY AIRCRAFT S Lyu, United Kingdom | |||||
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| 09:30 | 09:55 | 13.1.1 |
DIGITALISATION AND INTELLIGENT AUTOMATION IN GROUND HANDLING AND ENGINEERING: ENABLING NEXT-GENERATION AIRPORT EFFICIENCY D. So Man Fung, Singapore DIGITALISATION AND INTELLIGENT AUTOMATION IN GROUND HANDLING AND ENGINEERING: ENABLING NEXT-GENERATION AIRPORT EFFICIENCY | ||||
| 09:55 | 10:20 | 13.1.2 |
DESIGN AND FEASIBILITY ASSESSMENT OF TRANSPORT OPERATIONS FOR DELIVERING TYPHOON CONTROL SUBSTANCES H. Akiyama, Yokohama National University , Japan This study evaluates the macroscopic operational feasibility of transport operations for typhoon control. Numerical simulations demonstrate that dynamic airfield selection and a mixed-fleet approach are essential for maximizing operational throughput. The findings clarify the logistical requirements for conducting sustained typhoon control missions. | ||||
| 10:20 | 10:45 | 13.1.3 |
A PEAKS-OVER-THRESHOLD APPROACH TO RUNWAY COLLISION RISK ESTIMATION FOR EFFICIENT ARRIVAL OPERATIONS N.K. Wickramasinghe, Electronic Navigation Research Institute, Japan The paper proposes a Peaks-Over-Threshold framework to estimate runway collision risk for arrival procedures with reduced separation minima. Using surveillance-based data and physical modeling, the approach enables extrapolation of rare collision events beyond empirical observation, providing a robust safety analysis tool to support evidence-based development of future separation standards. | ||||
| 11:10 | 11:35 | 13.1.4 |
NEXT-GEN FLAP SYSTEMS: VALIDATION RESULTS AND IMPLICATIONS FOR AIR TRAFFIC MANAGEMENT R. Sáez, Technical University of Catalonia (UPC), Spain We present a preliminary assessment of the benefits of introducing continuous and dynamic adjustment of aircraft flaps and slats, as opposed to the current discrete settings. We developed a new system known as STEPLESS, which allows pilots greater control of the aircraft aerodynamic configuration, leading to improved energy management while complying with air traffic control (ATC) speed restrictions. This paper focuses on the benefits of this system from an air traffic management (ATM) perspective, considering different scenarios with varying characteristics, such as traffic mix, weather, or airport location. Fast-time simulations are used to evaluate the impact of the system through a set of performance indicators, including—but not limited to—fuel consumption, noise, and capacity. | ||||
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| 09:55 | 10:20 | 14.1.1 |
MULTI-CAMERA PANORAMIC SENSING FOR LOCALISATION AND MULTI-OBJECT TRACKING IN UAVS R. Perz, Institute of Aeronautics and Applied Mechanics, WUT, Poland Perception-driven localization and control constitute a core enabling capability for next-generation autonomous unnamed aerial vehicle (UAV) systems. This paper presents SauronEye (SE) project, a 12-camera, hardware-synchronized omnidirectional perception system integrating panoramic reconstruction, multi-object detection, and vision based geolocalization for navigation in GNSS-denied environments. | ||||
| 10:20 | 10:45 | 14.1.2 |
ROBUST MOTION ESTIMATION FOR INDOOR MAVS USING WIDE-FIELD-INTEGRATION OF OPTIC FLOW M. Yanagisawa¹, R. Okabayashi¹, T. Yamaguchi², M. Takamoto², M. Bando¹, S. Hokamoto¹; ¹Kyushu University, Japan ;²Mitsubishi Electric Corporation, Japan We propose a robust motion estimation method for indoor MAVs based on Wide-Field-Integration (WFI) of optic flow. By identifying and rejecting outlier flow vectors caused by low-texture regions or obstacles, our algorithm significantly improves estimation stability. Numerical simulations confirm its robustness and accuracy against environmental disturbances compared to conventional methods. | ||||
| 10:45 | 11:10 | 14.1.3 |
FLIGHT TEST VALIDATION OF A VISION-GUIDED MULTIROTOR TERMINAL INTERCEPTION SYSTEM Y.R. Kim, Cheongju University, South Korea This paper proposes a video-based multi-rotor terminal guidance system utilizing YOLOv8. By employing a ROS2 topic-based communication architecture, nodes for image recognition, guidance, and control are separated. The system reduces false alarm rates by utilizing data trained on real images and verifies the feasibility of target recognition and terminal guidance execution through flight tests. | ||||
| 11:10 | 11:35 | 14.1.4 |
A SYSTEMATIC, TUNING-FREE ATTITUDE CONTROL METHOD FOR VTOL UAVS K. Okamoto¹, T. Tsuchiya¹; ¹The University of Tokyo, Japan Presenter: Kazuki Okamoto, The University of Tokyo This paper proposes a novel attitude control scheme for VTOL UAVs operating over a wide range of airspeeds. The method addresses attitude nonlinearities without requiring an accurate aircraft model by employing an airspeed-adaptive phase-lag compensator whose parameters are systematically derived from rough aircraft geometry. | ||||
| Reserve Paper | 14.1.R |
DEEP LEARNING VS. TRADITIONAL COMPUTER VISION FOR UAV LANDING SITE DETECTION IN ADVERSE WEATHER R. Schmidt¹, J. Rüter¹; ¹German Aerospace Center (DLR), Germany | |||||
| additional information (interactive) | 14.1.R |
AUTONOMOUS FLIGHT AND INTELLIGENT TARGET LOCALIZATION OF JUNGLE RECONNAISSANCE UAV S. Li, China | |||||
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| 09:55 | 10:20 | 15.1.1 |
ON THE APPLICABILITY OF SAFETY NETS: A SAFETY-BY-DESIGN SOLUTION FOR CERTIFYING NEURAL NETWORKS J. M. Christensen, German Aerospace Center (DLR), Germany This work analyzes Safety Nets for certifiable AI in aviation, combining neural networks and lookup tables to guarantee correct runtime behavior. It evaluates architectural trade-offs, identifying compact designs achieving high accuracy with minimal storage. Results show significant size reductions and provide the first open-source Safety Net implementations for collision-avoidance systems. | ||||
| 10:20 | 10:45 | 15.1.2 |
COVERAGE-DRIVEN VERIFICATION FOR SAFETY-BY-DESIGN IN AI-BASED COLLISION AVOIDANCE SYSTEMS T Stefani, German Aerospace Center, Germany As aviation adopts AI-based Systems (such as HCAS and VCAS), meeting EASA safety standards is a major hurdle. This work provides a first-of-its-kind method to quantify ODD coverage in high-dimensional data, bridging the gap between regulation and engineering. By enabling a "Safety-by-Design" approach, this methodology is applicable beyond aviation to autonomous driving AI certification. | ||||
| 10:45 | 11:10 | 15.1.3 |
RINGCO-DETR: INFERENCE-NEUTRAL STABILIZATION OF ORIENTED TRANSFORMER DETECTION FOR AERIAL SENSING J Gao, The University of Sydney, Australia We propose RingCo-DETR, a training-only, inference-neutral improvement to DETR-style oriented detection. It stabilizes matching by balancing heterogeneous costs and strengthening supervision, and improves rotation robustness via frequency regularization. On DOTA-v1.5 and HIT-UAV, it achieves 81.7/83.1 mAP@50 with higher recall and more stable training, benefiting airfield monitoring. | ||||
| 11:10 | 11:35 | 15.1.4 |
ADVANCING TRUST FOR THRUST: PAIRING AND SHARING L.J.A. Jansen, German Aerospace Center (DLR), Germany Building on an existing quantitative trust framework that measures trust in bits, this paper proposes extensions that account for the length of trust chains and the position of weaker links within them. The extended model is applied to secure aircraft-to-aircraft communication in civil aviation, with particular focus on cooperative formation flying for wake energy retrieval. | ||||
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| 13:30 | 13:55 | 1.2.1 |
SETTING THE STAGE FOR THE GLOBAL SUSTAINABLE AVIATION TRACK WITH GLOBAL AIRLINES AH Krein, Clean Aviation, Belgium Invited speaker for the Global Sustainable Aviation track | ||||
| 13:55 | 14:20 | 1.2.2 |
BOEING PRODUCT DEVELOPMENT - CHALLENGES AND OPPORTUNITIES IN SUSTAINABILITY M L Drake, The Boeing Company, United States This presentation provides a Boeing perspective on the challenges and opportunities around the broader considerations around sustainability and commercial aviation. Addressing sustainability includes balancing the different focus avenues (climate, environment, resources), the full lifecycle timeline, and the broader stakeholder considerations and requirements for successful implementation. | ||||
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| 13:30 | 13:55 | 3.2.1 |
A POINT-CLOUD-BASED METHOD FOR INTELLIGENT AIRCRAFT CONFIGURATION LAYOUT GENERATION J.Z. Zhang, China A POINT-CLOUD-BASED END-TO-END FRAMEWORK INTEGRATING DEEP-LEARNING AERODYNAMIC SURROGATES AND GENERATIVE DESIGN TO AUTOMATICALLY CREATE DIVERSE AIRCRAFT GEOMETRIES AND RAPIDLY PREDICT AERODYNAMIC PERFORMANCE IN A CLOSED-LOOP PIPELINE. | ||||
| 13:55 | 14:20 | 3.2.2 |
INVERSE CONSTRAINT ANALYSIS FOR DESIGN SPACE EXPANSION: DERIVING AERODYNAMIC TARGETS IN SUPERSONIC FIGHTER CONCEPTUAL DESIGN S.-J. Kim Kim, Agency for Defense Development, South Korea Constraint analysis is a fundamental tool in early aircraft design, yet conventional constraint diagrams provide limited guidance on how to expand the feasible design space or improve robustness. This paper introduces a post-processing framework that augments baseline constraint analysis with sensitivity heatmaps and goal-post tables to identify influential design parameters and quantify the changes required to achieve prescribed performance margins. Applied to a representative fighter-class configuration, the proposed approach transforms constraint analysis from a static feasibility check into a quantitative decision-support method for early-stage design. | ||||
| 14:20 | 14:45 | 3.2.3 |
DEVELOPMENT OF A FRAMEWORK FOR INTEGRATION AND PERFORMANCE ANALYSIS OF NOVEL ENGINES DURING AIRCRAFT CONCEPTUAL DESIGN S. Hosseini, Amirkabir University of Technology (Tehran Polytechnic), Iran This research presents the development of framework for multidisciplinary design of conventional and novel engine cycles during aircraft conceptual design. In addition to conventional cycles, a series of novel engine cycles are examined. The propfan performance for aircraft design is examined. This method enables the optimization of engine in parallel to aircraft, which result emission reduction. | ||||
| 14:45 | 15:10 | 3.2.4 |
ASSESSMENT OF LIQUID HYDROGEN-POWERED AIRCRAFT RANGE: A NOVEL BREGUET FORMULATION G. Palaia, Polytechnic of Turin, Italy A Breguet-like formulation is proposed to estimate the cruise range of liquid-hydrogen-powered aircraft, accounting for cryogenic tank thermodynamics and boil-off losses. The proposed approach yields a compact surrogate model with limited error, suitable for rapid assessments and trade-off analyses in conceptual aircraft design. | ||||
| Reserve Paper | 3.2.R |
SCENARIO-BASED TECHNOLOGY ROADMAPPING IN AEROSPACE USING DBSCAN AND LLM T. A. Brutscher, Liebherr-Aerospace Lindenberg GmbH, Germany | |||||
| Reserve Paper | 3.2.R |
FORMALIZING THE INTEGRATION BETWEEN MODEL-BASED SYSTEMS ENGINEERING AND SYSTEM ARCHITECTURE OPTIMIZATION S. Valencia-Ibanez, Concordia University, Canada | |||||
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| 13:30 | 13:55 | 4.2.1 |
PERFORMANCE COMPARISON BETWEEN PASSENGER AIRCRAFT WITH NOVEL PROPULSION SYSTEMS AT CONCEPTUAL DESIGN LEVEL JC Chan, Cranfield University, United Kingdom Performance comparison between aircraft with novel propulsion systems, including, hydrogen combustion engine, hydrogen fuel cell system, battery powered aircaft, against conventional jet fuel aircraft. This will explore the true improvement and drawback of these design in respect to different mission requirement. | ||||
| 13:55 | 14:20 | 4.2.2 |
FUTURE LONG RANGE AIRCRAFT CONCEPT EXPLORATION AND FLIGHT TEST NEEDS IDENTIFICATION P. Schmollgruber, ONERA, France This paper presents the aircraft design activities that are carried out in the EU project EXAELIA. The conceptual design of Future Long Range Aircraft looks at 3 different main options (SAF BWB, H2 BWB, H2 strut-brace wing) and identifies Flight Tests needs that will be used to define several Flying Test Beds. These flying vehicles will help in accelerating the EIS of the future airplane concepts. | ||||
| 14:20 | 14:45 | 4.2.3 |
SUPPORTING THE REGULATORY COMMUNITY SHAPING THE FUTURE OF SUSTAINABLE HIGH-SPEED CIVIL AVIATION: THE ESATTO FRAMEWORK N. Viola, Politecnico di Torino, Italy The H2020 MORE&LESS final objective was to support regulatory entities to shape global environmental regulations for supersonic aviation. The results of extensive high-fidelity modelling activities, validated through test campaigns, have been merged into a multi-disciplinary optimization framework to holistically assess the impact of supersonic aviation onto the environment. This paper aims at disclosing the framework using a Mach 2 aircraft as case study. | ||||
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| 13:30 | 13:55 | 5.2.1 |
OVERVIEW OF VERIFICATION AND VALIDATION EFFORTS FOR PDE-BASED LAMINAR-TURBULENT TRANSITION MODELS J. G. Coder, Penn State University, United States This paper provides a status update on verification and validation efforts for laminar-turbulent transition models in RANS CFD applications. Despite such models having been in the literature for two decades and implemented in numerous government and commercial solvers, there is still a lack of code-to-code agreement in model definition, which inhibits verification efforts. | ||||
| 13:55 | 14:20 | 5.2.2 |
ACCURACY AND EFFICIENCY OF TRANSITION–TURBULENCE MODELS IN PREDICTING HIGH AND LOW REYNOLDS NUMBER PROPELLER PERFORMANCE F. Parra¹, D. Domínguez¹, A. Delgado¹, J. Gonzalo¹; ¹Universidad de León, Spain The emergence of new aircraft concepts has renewed interest in optimizing propeller design. This research assesses the accuracy and efficiency of different transition-turbulence models to determine whether the use of a more complex turbulence model is worth it. The prediction of propeller performance parameters for both high and low Reynolds propellers is compared using various turbulence models. | ||||
| 14:20 | 14:45 | 5.2.3 |
RESEARCH ON TRANSITION PREDICTION METHODS FOR HELICOPTER ROTOR BLADES Z.-K Zhou, China The aerodynamic characteristics of rotor blades directly determine helicopter flight performance. Accurately predicting boundary layer transition is crucial for refined rotor analysis and laminar flow drag reduction design. Currently, the widely used ?-Re?t transition model in engineering, while convenient for CFD coupling, struggles to account for rotational effects and crossflow instability, limiting its application in the complex flow fields of rotors. To address this, this paper develops a transition prediction method suitable for three-dimensional rotor flows: firstly, a Galilean invariant-based G-?-Re?t model is developed to ensure prediction consistency across different moving coordinate systems; secondly, a crossflow transition criterion based on the C1 criterion is developed to achieve reliable prediction of crossflow transition; finally, an unsteady RANS solver with autonomous transition judgment capability is established. Validation against a PSP rotor hover test case shows that the improved model can accurately predict rotor aerodynamic performance and transition location. This research provides a refined analysis tool for high-fidelity numerical simulation and laminar flow design of rotor blades. | ||||
| 14:45 | 15:10 | 5.2.4 |
HYPERBOLIC RECEPTIVITY TO FREESTREAM DISTURBANCES OVER A BLUNT WEDGE: A LINEARIZED NAVIER–STOKES APPROACH Zhichao Zhu, Tsinghua University, China This study employs an AD-based Linearized Navier-Stokes (LNS) solver with shock-fitting to analyze Mach 15 flow over a blunt wedge. Results show that at identical frequencies, wall vibration excites initial crossflow amplitudes substantially larger than those induced by freestream acoustic waves.. The framework efficiently predicts complex 3D transition mechanisms. | ||||
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| 13:30 | 13:55 | 6.2.1 |
PHYSICAL DESIGN CONCEPTS OF VORTEX GENERATOR ARRAYS FOR AIRCRAFT AFT-BODIES DRIVEN BY DISTINCT DRAG REDUCTION MECHANISMS Y. Mou¹, Y. Wu¹, T. Liu², D. Li², Y. Xiang¹, H. Liu¹; ¹School of Aero. & Astro., Shanghai Jiao Tong Univ., China ;²COMAC Shanghai Aircraft Design and Research Institute, China This study investigates physics-driven design strategies for vortex generator arrays on aircraft aft-bodies. Using high-fidelity DES, we clarify how Counter-Rotating Pairs and Co-Rotating Arrays utilize distinct mechanisms, specifically dissipative mixing versus topological partitioning, to manipulate wake vortices and maximize pressure recovery. | ||||
| 13:55 | 14:20 | 6.2.2 |
ACTIVE FLOW CONTROL AND THERMAL PROTECTION FOR A WING-BODY CONFIGURATION BASED ON LATERAL JET L. He, China This study proposes an active flow control and thermal protection method based on lateral jet. The heat flux on the leading edge is significantly reduced when the jet pressure ratio is appropriate. Furthermore, this work develops a deep learning-based virtual sensor to underpin future intelligent control. | ||||
| 14:20 | 14:45 | 6.2.3 |
REDUCED-ORDER MODELLING OF MINI-TAB SPOILER DYNAMICS FOR GUST LOAD ALLEVIATION A. Jürisson, Royal Netherlands Aerospace Centre, Netherlands This paper studies dynamic mini-tab spoiler behavior that can effectively be used for gust load alleviation. High-fidelity CFD simulations are performed for varying deflection amplitudes and rates from which a reduced-order model (ROM) is created. The model is used to develop a control law for gust load alleviation which is evaluated and validated again in a high-fidelity CFD simulation. | ||||
| 14:45 | 15:10 | 6.2.4 |
MODELING, SIMULATION, AND VALIDATION OF COVERT FLAPS FOR IMPROVED TRANSITION CONTROL OF TILTWING AIRCRAFT A.M. Comer, Oklahama State University, United States Tiltwing VTOL aircraft face instability during the hover to forward flight transition. This study explores bird-inspired feather flaps as a flow-control method for improved stability. URANS CFD on a NACA 63-215 airfoil tests a suction-side flap at various location to assess unsteady flow, stall delay, and lift-to-drag gains. | ||||
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| 13:30 | 13:55 | 7.2.1 |
NUMERICAL SIMULATION OF SUPERCOOLED LARGE DROPLET IMPINGEMENT ON ROTATING FAN BLADES H. Yan, Shanghai Jiao Tong University, China This research simulates supercooled large droplet (SLD) impingement on rotating turbofan fan blades, where centrifugal and Coriolis forces create distinct patterns. Research offers a tool for evaluating SLD impingement on rotating machinery, fundamentally affecting ice accretion predictions—essential for designing effective de-icing systems. | ||||
| 13:55 | 14:20 | 7.2.2 |
STUDY OF THE SONIC AND SUBSONIC JET-INDUCED SWIRLING FLOW AND WALL HEAT TRANSFER IN D-DUCT FOR AERO-ENGINE NACELLE SWIRL ANTI-ICING SYSTEM D.Z Dong, Shanghai Jiao Tong University, China Swirl anti-icing is a promising aero-engine nacelle protection method. This study develops practical heat transfer calculation methods for jet entrainment and wall heat transfer. Sonic and subsonic jet expansion and mixing are analyzed to summarize entrainment laws. Spatially distributed heat transfer correlations are formulated for both swirling and jet impingement regions. | ||||
| 14:20 | 14:45 | 7.2.3 |
AIRFRAME-INLET INTEGRATION DESIGN FOR AN OVER-WING-MOUNTED SUPERSONIC TRANSPORT CONFIGURATION Q. Chen, China In this paper, a design method for a supersonic inlet is developed and integrated with a low-boom configuration over the wing. The interference between the inlet and the airframe is investigated, and the mechanism of total pressure distortion at the aerodynamic interface is clarified. In addition, an integrated design optimization is conducted, effectively enhancing the performance of the inlet. | ||||
| 14:45 | 15:10 | 7.2.4 |
AI-BASED FORECASTING OF ICE-INDUCED AERODYNAMIC DEGRADATION S. Corcione, University of Naples Federico II, Italy Ice accretion causes strongly time-dependent aerodynamic degradation, motivating predictive models able to capture its temporal evolution. This work presents a data-driven surrogate framework built on physics-based icing simulations. Preliminary results show accurate snapshot prediction and physically consistent trends across exposure time, establishing a foundation for fully time-aware and forecasting surrogate models. | ||||
| Reserve Paper | 7.2.R |
HEATING EFFECT OF DRONE DOWNWASH UNDER INVERSE TEMPERATURE CONDITIONS P. Kirschnek, FH JOANNEUM GesmbH, Austria | |||||
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| 13:30 | 13:55 | 8.2.1 |
VISUAL MACHINE LEARNING ANALYSIS OF MULTIFUNCTIONAL PERFORMANCE IN GRAPHENE FRP COMPOSITES V.M Kannan, Australia This paper presents a visual machine learning assisted analysis of multifunctional graphene fibre-reinforced polymer composites. Experimental mechanical and electrical responses are combined with image based learning to interpret damage evolution, enabling automated assessment of multifunctional performance for advanced aerospace and structural applications. | ||||
| 13:55 | 14:20 | 8.2.2 |
EFFICIENT SIMULATION AND UNCERTAINTY QUANTIFICATION OF PROGRESSIVE CRUSHING IN COMPOSITE LAMINATES Johannes Reiner, Deakin University, Australia; Reza Vaziri, The University of British Columbia, Canada This study presents an approach to better understand how composites behave when they are crushed, something important for designing safer and lighter structures. Using fast simulations and machine?learning models, it captures natural variability at low cost. The method supports safer, lighter designs and is relevant to aerospace, automotive, energy and defence sectors. | ||||
| 14:20 | 14:45 | 8.2.3 |
DEVELOPMENT OF CONDUCTIVE COMPOSITE MATERIALS FOR HIGH VOLTAGE APPLICATIONS S.A. Brown, UNSW, Australia A carbon fibre composite with enhanced electrical conductivity and sufficient mechanical performance has been developed using soft conductive stitching with thin silver-coated carbon fibre veil integration. Additionally, this composite has demonstrated comparable high-voltage protection to conventional copper mesh, indicating potential for application as integrated lightning strike protection. | ||||
| 14:45 | 15:10 | 8.2.4 |
COMPRESSIVE PERFORMANCE OF VARIABLE-STIFFNESS COMPOSITE HYPERBOLIC STIFFENED PANELS BASED ON GEOMETRIC PATH MAPPING R.B. Ma¹, C.Y. Wang¹, X.M. Chen, Aircraft Strength Research Institute of China, China; W.Z. Wang¹; ¹Northwestern Polytechnical University, China Automated fiber placement enables the manufacture of variable-stiffness composite structures with complex curvature, yet modeling non-developable surfaces remains challenging. This study proposes a geometric path mapping method for variable-stiffness composite hyperbolic stiffened panels and develops a parametric finite element model. Numerical results demonstrate improved compressive performance of variable-stiffness layups compared with constant-stiffness layups. | ||||
| Reserve Paper | 8.2.R |
USING LIGHTWEIGHT COMPOSITE TIE-RODS IN PLACE OF HIGH STRENGTH STEEL TIE-RODS A.-K. Kumar, THE BOEING COMPANY, India | |||||
| Reserve Paper | 8.2.R |
ENHANCEMENT AND DEGRADATION: THE DUAL ROLE OF GRAPHENE NANOPLATELETS ON THE STRUCTURAL PERFORMANCE OF COMPOSITE T-JOINTS M. Bhasin, RMIT University, Australia; A.P. Mouritz, RMIT Univeristy, Australia | |||||
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| 13:30 | 13:55 | 9.2.1 |
THE CONFERENCE LOCATIONS: A QUANTITATIVE APPROACH TO REDUCING IMPACT GLOBAL TRAVEL C. Jouannet, Linköping University, Sweden Environmental concerns touch every type of organization and are hard not to include in strategical decisions. International conferences are generally accepted as one of the best means for fruitful interactions, they foster dialogue and exchange of ideas, but there is a significant environmental impact associated with the delegates traveling to the venue. Therefore, the authors posed the question whether a decision-making tool can be developed, to support planning of conference locations targeting the minimization of air travel. | ||||
| 13:55 | 14:20 | 9.2.2 |
MODELING, SIMULATION AND CASE STUDY OF LARGE-SCALE FOREST FIRE EXTINGUISHING AND RESUE SYSTEM BASED ON AVIATION METERIEL W. Cheng, Aviation Industry Development Research Center of China (ADR) , China Large scale forest fires are one of the important tasks in China's current emergency rescue, and using aviation equipment to carry out firefighting tasks is becoming an increasingly practical and efficient solution. This article analyzes the current demand and typical scenarios for large-scale forest firefighting in China, sorts out the task process of typical aviation equipment forest firefighting, constructs equipment system models, fire spread models, operation models, etc. for large-scale forest firefighting and rescue scenarios, and constructs simulation processes and methods. And taking the forest fires in Northeast China as the object, typical aviation equipment was selected for static effectiveness evaluation and task effectiveness evaluation, and the advantages and disadvantages of using aviation equipment to carry out large-scale forest firefighting tasks were presented, providing support for the subsequent construction of the national firefighting emergency rescue system layout. | ||||
| 14:20 | 14:45 | 9.2.3 |
FEATURE MODEL CREATION THROUGH MISSION ANALYSIS IN THE CONTEXT OF VEHICLE FAMILIES A.M. Zarate Villazon, Georgia Institute of Technology - Aerospace Systems Design Lab, United States The paper presents a methodology to enable a traceable feature model creation through the connection of CONOPS diagrams with the feature model artifacts leveraging SysML v2. The paper describes manual and automatic approaches to achieve this such as Large Language Models. It is demonstrated through a case study of proposed missions for Urban Air Mobility. | ||||
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| 13:30 | 13:55 | 10.2.1 |
SYSTEM IDENTIFICATION USING FLIGHT TEST DATA AND MACHINE LEARNING G. Larsson, Saab Aeronautics, Sweden The usability of flight mechanical simulations relies on sub-models. A method for estimating nonlinear aerodynamic properties, using flight test data in combination with machine learning is investigated. Here, a subscale radio-controlled aircraft is used. Neural Network functions for system identification are possible. It can handle nonlinear system behavior but relies heavily on data available. | ||||
| 13:55 | 14:20 | 10.2.2 |
AUTOMATIC GROUND COLLISION AVOIDANCE VIA SUPERVISED LEARNING–BASED RECOVERY TRAJECTORY PREDICTION J. Han, Korea Advanced Institute of Science and Technology (KAIST), South Korea This paper presents a supervised learning–based approach for predicting recovery trajectories in Automatic Ground Collision Avoidance Systems. Motivated by accurate trajectory representation for timely maneuver initiation, the proposed method learns a parametric model from recovery maneuver data. The results demonstrate trajectory prediction accuracy across representative flight conditions. | ||||
| 14:20 | 14:45 | 10.2.3 |
LEARNING-BASED CONTROL ALLOCATION FOR OVER-ACTUATED VTOL AIRCRAFT WITH NONLINEAR DYNAMICS D. Kim, Korea Advanced Institute of Science and Technology, South Korea This study presents a learning-based control allocation method for over-actuated VTOL aircraft while explicitly accounting for nonlinear dynamics. A deep auto-encoder is employed to learn the mapping between actuator commands and the resulting control effects, enabling effective utilization of available control authority under actuator constraints. Simulation results demonstrate improved allocation performance compared to conventional methods. | ||||
| 14:45 | 15:10 | 10.2.4 |
RESIDUAL LEARNING FRAMEWORK FOR NONLINEAR AEROELASTIC–FLIGHT-DYNAMICS CONTROL-ORIENTED MODELING OF VERY FLEXIBLE AIRCRAFT Carlos E. S. Cesnik, University of Michigan, United States Enhanced flight dynamics model for aircraft exhibiting strong aeroelastic coupling. A modular residual learning approach is used in which analytical linearized aerodynamics is augmented with data-driven corrections. This formulation preserves physical interpretability while improving robustness, generalization, and training efficiency. Results demonstrate improved dynamic response accuracy. | ||||
| additional information (interactive) | 10.2.R |
PHYSICS-INFORMED NEURAL NETWORK BASED MODELING OF DYNAMIC BEHAVIOR OF AERIAL REFUELING HOSE Z. Wu¹, S. Yang¹, Z. Zhang¹, Y. Qu¹, B. Xiao¹; ¹Northwestern Polytechnical University, China | |||||
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| 13:30 | 13:55 | 11.2.1 |
STABILITY AUGMENTATION SYSTEM DESIGN FOR LONGITUDINALLY UNSTABLE TAILLESS AIRCRAFT S. Riethausen, Linköping University, Sweden A fast, simple method for designing a flight control system for unstable tailless UAVs is presented. A linear airframe model based on panel method stability derivatives was combined with actuator and controller models to determine parameters safe initial controller parameters. Test flights confirm the methods feasibility, with full evaluation ongoing. | ||||
| 13:55 | 14:20 | 11.2.2 |
ROBUST ESTIMATION-AWARE GUIDANCE FOR STOCHASTIC INTERCEPTION WITH PARAMETRIC UNCERTAINTY LM Mudrik, United States Standard guidance fails under parametric uncertainty. We propose a Robust Estimation-Aware Guidance Law (REAGL) utilizing Bayesian decision theory to manage risk, coupled with Information-Enhancement Trajectory Shaping (RIETS). Simulations demonstrate this unified approach prevents catastrophic performance loss, restoring high kill probabilities against agile targets. | ||||
| 14:20 | 14:45 | 11.2.3 |
DOB-BASED ADAPTIVE NONSINGULAR TERMINAL SLIDING MODE CONTROL FOR FAULT-TOLERANT CONTROL OF QUAD-TILTROTOR EVTOL S.W. Kim¹, T.W Yun¹, D.H. Seo¹, J.Y. Suk¹, S.K. Kim¹; ¹Chungnam National University, South Korea This paper proposes a robust DOB-based Adaptive NTSMC for Quad-tiltrotor eVTOLs. By integrating active disturbance rejection with adaptive gain tuning, the method effectively minimizes chattering and compensates for wind gusts and actuator faults. Simulations demonstrate a 79% tracking improvement over PID, ensuring high reliability for safe Urban Air Mobility operations | ||||
| 14:45 | 15:10 | 11.2.4 |
FLIGHT ENVELOPE PROTECTION FOR HIGH ALTITUDE LONG ENDURANCE AIRCRAFT C. Weiser, DLR - German Aerospace Center, Germany In this paper, a flight envelope protection algorithm for a High Altitude Long Endurance (HALE) aircraft is presented. Two major approaches are investigated and fusioned: a physical approach based on flight physics equations, and a signal based approach. The result is tested within the non-linear HALE simulator and integration into the overall flight control algorithm is presented. | ||||
| Reserve Paper | 11.2.R |
CONTROL ALLOCATION AND SIZING FOR OVER-ACTUATED AIRCRAFFT C. Doll, ONERA, France | |||||
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| 13:30 | 13:55 | 12.2.1 |
A THERMO-MECHANICAL PHASE FIELD MODEL CONSIDERING SOLID-LIQUID TRANSITION: APPLICATION TO ELECTROTHERMAL DE-ICING Yuxuan Ying, Northwestern Polytechnical University , China; Xudan Yao¹, Ye Feng¹, Wei Huang¹; ¹Northwestern Polytechnical University, China This work presents an innovative thermo-mechanical phase field model considering solid-liquid transitions. An accurate predictive equation for critical strain energy density is derived and utilized in the multi-physical model. An idealized electrothermal de-icing process is numerically modelled, and the melting-shedding behavior is in good agreement with the experimental observations. | ||||
| 13:55 | 14:20 | 12.2.2 |
ICE DETECTOIN: CORRELATION ICE ACCRETIONS AND DYNAMIC RESPONSES ON SMALL-SCALE AIRFOIL PROTOTYPES G. Mingione, CIRA, Italy Presenter: Luigi Mangiacrapa, Centro Italiano Ricerche Aerospaziali In UP WING project, two small-scale NACA 0012 airfoil were realized to prove the functionality of an Ice Protection System and to develop the capability of detecting ice accretions based on piezoelectric (PZT) technology. The two test articles and have been tested in the IFAM Icing Wind Tunnel. The objective is to the demonstrate that the comparison of tests performed with and without ice accretion make it possible to use the PZT system also as an ice-detector system. | ||||
| 14:20 | 14:45 | 12.2.3 |
A MPC STRATEGY FOR THE VECTOR CONTROL OF RESONANT ELECTROMECHANICAL DE-ICING SYSTEMS J. Pothin, ISAE Suapero, France Ice accretion drives lightweight, energy-efficient de-icing using resonant piezoelectric systems. Beyond frequency sweeps and PI vector control, this paper proposes Model Predictive Control to optimally track resonance, enforce constraints, and minimize power. Validation on a plate is extrapolated to a NACA airfoil. | ||||
| 14:45 | 15:10 | 12.2.4 |
ELECTROMECHANICAL RESONANT ICE PROTECTION SYSTEMS USING VOICE COIL ACTUATORS - AIR INLET SECTION CASE STUDY Y. R. Rafik, INSA, France Ice accretion may cause performance degradation and safety hazards for aircraft. To prevent these problems, ice protection systems (IPS) are implemented on surfaces to be protected. Thermal systems are the most commonly used IPS. While they are efficient, they are also energy-consuming. Electromechanical systems have garnered interest due to their potential to reduce weight and energy consumption, but very few have been implemented on aircraft. Studies have demonstrated the potential of resonant electromechanical IPS actuated by piezoelectric actuators. However, some piezoelectric actuator technologies, such as PZT patches, are vulnerable to impact damage. This paper aims to evaluate the potential for using voice coil actuators to activate a resonant de-icing system. This article aims to assess the capacity of electromagnetic actuators to replace PZT in a resonant de-icing system operating at frequencies up to 2 kHz. A previous article demonstrated that this was possible in the case of de-icing a plate. Here, the geometry under study is a section of an air inlet with a span of 300 mm and a diameter of 1,300 mm | ||||
| Reserve Paper | 12.2.R |
DESIGN METHODOLOGY OF A LOW-COST FOREBODY FOR SUBSONIC WIND TUNNEL TESTING NQ Nghiem, VIETTEL AEROSPACE INSTITUTE, Vietnam | |||||
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| 13:30 | 13:55 | 13.2.1 |
TRAJECTORY ADJUSTMENTS IN JAPANESE MOVING SECTORS TO REDUCE AIR TRAFFIC COMPLEXITY S. Goeppel, University of the Bundeswehr, Germany Lateral trajectory adjustments within moving sectors reduce air traffic complexity in Japanese airspace, supporting future flow-centric air traffic management. Metaheuristic waypoint optimization applied to high-density arrival flows to Tokyo yields 15–27% reductions in time-integrated complexity and up to 30% lower peak values. | ||||
| 13:55 | 14:20 | 13.2.2 |
RUNWAY-AWARE CAPACITY ENVELOPES FOR LONG-RANGE ARRIVAL METERING UNDER OPERATING-DIRECTION CHANGES AT SINGAPORE CHANGI E. Asadi, Bundeswehr University of Munich, Germany Weather-driven runway direction changes create short but critical capacity losses at major hubs. This work shows that modeling these transitions as time-varying capacity envelopes and applying modest upstream arrival metering can reduce overload by more than 80 percent at Singapore Changi. The approach improves operational resilience and is transferable to other complex transportation systems. | ||||
| 14:20 | 14:45 | 13.2.3 |
AIRCRAFT SEQUENCING UNDER UNCERTAINTY: GAME-THEORETIC OPTIMIZATION AND A COMPARATIVE ANALYSIS OF GLOBAL AND INTRA-AIRLINE COOPERATIVE DECISION FRAMEWO S Tsuru, Osaka Metropolitan University, Japan This study proposes a game-theoretic framework for aircraft sequencing under uncertainty. Comparing global optimization with airline competition shows a 2-4% efficiency loss when airlines prioritize their own fleets. High-cost flights often hoard early slots, delaying others. Proposed probabilistic sequencing method protects cost privacy and outperforms the First-Come, First-Served rule, aiding autonomous traffic management. | ||||
| 14:45 | 15:10 | 13.2.4 |
IMPACT OF DYNAMIC METERING OPERATIONS UNDER ADVERSE WEATHER AND MITIGATION THROUGH OPTIMAL SEQUENCING Y Matsuno, Japan Aerospace Exploration Agency, Japan Dynamic metering under adverse weather is essential for safety but can degrade operational efficiency. This study quantifies delay increases caused by dynamically changing metering fixes and demonstrates that optimal arrival sequencing can effectively mitigate such inefficiencies. The results highlight the value of optimization-based flow management for weather resilient operations. | ||||
| Reserve Paper | 13.2.R |
AIRCRAFT CLIMB PROFILE PREDICTION VIA MACHINE LEARNING-BASED FRAMEWORK H Seon, Korea Aerospace University, South Korea | |||||
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| 13:30 | 13:55 | 14.2.1 |
DYNAMIC RECONFIGURABLE PATH PLANNING FOR FIRE-FIGHTING UAVS Z. Lin¹, D. Geraghty¹, S. F. Armanini¹, L. Mainini¹; ¹Imperial College London, United Kingdom We present a reconfiguration-capable multi-objective mission planning framework enabling UAVs to dynamically adjust their planning strategy in response to real-time changes in environment or mission requirements. Simulations in real-time evolving wildfire scenarios, show higher mission success rate, information acquisition efficiency and UAV survivability compared to traditional strategies. | ||||
| 13:55 | 14:20 | 14.2.2 |
COOPERATIVE GROUND AND AERIAL SURVEILLANCE FOR TRACKING OF UNAUTHORIZED AERIAL VEHICLES D. Y. Yoon, Hanseo University, South Korea Ground sensors face FOV limits and LoS occlusions, causing shadow regions, higher uncertainty, and track loss. We propose cooperative ground–air tracking: UAVs reposition to preserve geometry, and a PSO waypoint generator replans online. ROS2–Gazebo simulations validate improved information gain and tracking stability over an FIM baseline. | ||||
| 14:20 | 14:45 | 14.2.3 |
MODELING OF CRITICAL WEATHER FLIGHT PERFORMANCE OF MULTICOPTER UAVS FOR RESILIENT CONTROLLER DESIGN A. Fallast, FH JOANNEUM, Austria This work presents unique free-flight wind-tunnel and outdoor experiments investigating multicopter UAV performance under real icing conditions. Data-driven degradation modeling and adaptive gain-scheduled control are validated using measured propulsion data and virtual ice-mass estimation. The results improve resilience of UAV control systems and are relevant to aerospace, robotics, and autonomous systems operating in adverse weather. | ||||
| 14:45 | 15:10 | 14.2.4 |
SIMULATION-BASED ANALYSIS OF REDUNDANT UAV NAVIGATION UNDER GNSS OUTAGES M. Ben Simon¹, S. Malka¹, D. Chudnovsky¹, O. Yakimenko¹; ¹Naval Postgraduate School, United States we present the design, simulation, and evaluation of a redundant navigation architecture for UAVs enabling reliable PNT solutions under GNSS degradation or denial. we propose a solution comprising four embedded EGI units of varying quality, integrated through a supervisory voter using consensus logic, hysteresis, and debounce filtering to generate a reliable and robust PNT solution. | ||||
| Reserve Paper | 14.2.R |
GEOMETRY-AWARE AERIAL LIGHT SHOW: JOINT OPTIMIZATION OF SWARM SIZE AND ENERGY-EFFICIENT TRAJECTORIES K.-G. Yuksel, Aselsan, Turkey | |||||
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| 13:30 | 13:55 | 15.2.1 |
WHO SHOULD SIT AT THE EXIT ROW? A HUMAN FACTORS APPROACH TO EMERGENCY EVACUATION PASSENGER SELECTION IN COMMERCIAL AVIAT A Reisier¹, M Machado Cardoso Júnior ¹, C Lessa¹, P Kurka, ITA , Brazil; R Freitas¹; ¹ITA, Brazil This research develops an evidence-based emergency exit seat passenger selection framework through evolutionary integration of Hierarchical Task Analysis, Event Analysis of Systemic Teamwork, and Work Domain Analysis. Analysis reveals systemic constraints preventing optimal practice implementation despite the existence of technical knowledge, proposing regulatory reforms structurally decoupling safety logic from commercial priorities in aviation emergency evacuation systems. | ||||
| 13:55 | 14:20 | 15.2.2 |
CONCEPT OF OPERATIONS FOR A HYDROGEN-ELECTRIC POWERED MODIFIED DASH8-300 REGIONAL AIRCRAFT: PERFORMANCE, OPERATIONAL, AND CERTIFICATION IMPACTS B Rietdijk, Conscious Aerospace, Netherlands This Concept of Operations (CONOPS) details integrating a Hydrogen Aircraft Powertrain and Storage System (HAPSS) into the Dash 8-300. It addresses impacts on aircraft performance, network integration, and air traffic management, providing stakeholders a roadmap for introducing hydrogen-powered regional aviation with minimal infrastructure changes and significant emission reductions. | ||||
| 14:20 | 14:45 | 15.2.3 |
TOWARD THE INTEGRATION OF NEUROPHYSIOLOGICAL SIGNALS AND HUMAN BODY DYNAMICS FOR ADAPTIVE CONTROL ALLOCATION T. Treichl, German Aerospace Center, Germany This work presents a novel experimental design to assess the potential of combining both neurophysiological signals and biomechanics to estimate pilots capabilities. A motion simulator and the MATB-II are used to induce mental and physical stress to subjects while several neurophsiological and biodynamic data streams are recorded in order to assess their correlation with performance afterwards. | ||||
| 14:45 | 15:10 | 15.2.4 |
A CENTRALIZED KEY MANAGEMENT ARCHITECTURE FOR SECURE GROUP COMMUNICATION ON IMA PLATFORM C. A. Dautel, Institute of Aircraft Systems, University of Stuttgart, Germany This paper presents a proof of concept demonstrating that centralized key management can effectively support group key distribution for avionics communication patterns. The proposed approach introduces two modifications to the avionics platform architecture. In contrast, classical key negotiation mechanisms such as TLS require each IMA computer to perform its own key negotiation. | ||||
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| 16:30 | 16:55 | 1.3.1 |
PRATT & WHITNEY: MEETING THE FUTURE PROPULSION NEEDS OF COMMERCIAL AVIATION A.M. Murphy, Pratt & Whitney, United States Invited speaker for the Global Sustainable Aviation track. | ||||
| 16:55 | 17:20 | 1.3.2 |
CFM INTERNATIONAL\'S RISE PROGRAM: A STEP-CHANGE FOR DURABILITY AND EFFICIENCY C.-A. Andrews, GE Aerospace, United States Open Fan architecture, developed under CFM International’s RISE program, removes the traditional fan casing to enable a larger, more efficient fan with less drag. Leveraging adaptive cycle and hybrid electric technologies, it targets cooler cores, improved durability, and lower fuel burn. Christine Andrews will share why the time for Open Fan is now. | ||||
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| 16:30 | 16:55 | 3.3.1 |
AN INTEGRATED CONCEPTUAL DESIGN WORKFLOW FOR LIQUID HYDROGEN-POWERED BOX-WING AIRCRAFT K. Abu Salem, University of Trento, Italy A multidisciplinary design optimization framework is proposed for liquid hydrogen-powered box-wing aircraft. By coupling aerodynamics, structures, propulsion, and cryogenic tank thermodynamics, the approach supports a system-level assessment of box-wing configurations and identifies operating domains where hydrogen propulsion and box-wing offer advantages over conventional layouts. | ||||
| 16:55 | 17:20 | 3.3.2 |
AGENTIC AI FOR AIRCRAFT PRELIMINARY DESIGN: PROOF OF CONCEPT A. Kirste, RWTH Aachen University, Germany Agentic AI enables autonomous code generation and iterative reasoning for complex engineering tasks. This work presents the first proof of concept for agentic AI in aircraft preliminary design. Multiple AI platforms are benchmarked against aircraft-specific metrics using an A320-class reference. Results establish baseline capabilities for AI-assisted design workflows and integration with UNICADO. | ||||
| 17:20 | 17:45 | 3.3.3 |
AI-SUPPORTED AIRCRAFT SYSTEM ARCHITECTURE SYNTHESIS P. Krus, Linköping University, Sweden This paper proposes a structured methodology for AI-supported aircraft system architecture synthesis using large language models. Systematic prompt composition encodes generic rules, domain constraints, and component libraries. Applied to hybrid-electric propulsion, the approach improves architectural reasoning, and integration within model-based systems engineering in early design phases. | ||||
| 17:45 | 18:10 | 3.3.4 |
DEVELOPING AN AGENTIC AI WORKFLOW FOR AUTOMATED CONCEPTUAL DESIGN OF AIRCRAFT USING RISPECT+ J. Song¹, S. Park², D. Lee², Y.-E. Kang¹, Y. Kim¹, S. Lee¹; ¹Manufacturing AI Research Center, KITECH, South Korea ;²Department of Unmanned Aircraft Systems, Hanseo University, South Korea Presenter: Juhun Song, Korea Institute of Industrial Technology/Sungkyunkwan University This paper presents an agentic AI framework that automates aircraft conceptual design through coordinated large language model–based agents integrated with the RISPECT+ design toolkit. The agents collaboratively refine natural language requirements, translate them into engineering parameters, and autonomously execute sizing, weight, and cost analyses, reducing reliance on expert intuition and improving design efficiency and accessibility. | ||||
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| 16:30 | 16:55 | 4.3.1 |
BOEING 777 FREIGHTER CONVERSION STRATEGY: FORWARD \"STANDARD\" VS. REAR EXTRA-LARGE (XL) MAIN DECK CARGO DOOR I. Berlowitz, IBAero Engineering, Israel Two U.S.-based Supplemental Type Certificate (STC) programs are currently converting Boeing 777 aircraft into freighters. The paper and presentation compare the design approaches, advantages, and challenges of the KMC 777-300ER and Mammoth 777-200LR/-300ER freighter conversions and assess their mechanical, electrical, avionics, and integrated systems, focusing on differences in design philosophies-especially regarding main deck cargo door location and e-commerce-driven lightweight/high-volume cargo vs. containerized high-gross freighter weights. | ||||
| 16:55 | 17:20 | 4.3.2 |
CONCEPTUAL DESIGN OF A PROPFAN-POWERED TRUSS-BRACED WING REGIONAL AIRCRAFT S. Hosseini, Amirkabir University of Technology (Tehran Polytechnic), Iran This research presents the development of a methodology for conceptual multidisciplinary design of a propfan-powered truss-braced wing regional aircraft. The TBW configuration has shown potential benefits for performance improvement and reduction in environmental emission. In this research, the propfan engine is integrated into the wings of a high-wing truss-braced wing for further improvement. | ||||
| 17:20 | 17:45 | 4.3.3 |
FLIGHT TESTING OF A HIGH-ALTITUDE UNCREWED AND SOLAR POWERED PLATFORM HEAVIER THAN AIR F. Nikodem, German Aerospace Center (DLR e.V.) / Institute of Flight Systems, Germany High-altitude platforms (HAPs) represent new and promising application of uncrewed aircraft. This paper will provide an overview of the major design challenges associated with high-altitude platforms, introduce the DLR HAP-alpha project and outline the current status of the project. The focus will be on the conducted flight tests, including test preparation, ground handling and team training. | ||||
| 17:45 | 18:10 | 4.3.4 |
CONCEPTUAL DESIGN OF A MIDDLE-OF-THE-MARKET AIRCRAFT FOR EDUCATIONAL PURPOSES S. J. van Heerden, University of Glasgow, United Kingdom This paper presents the G-26, a 2040-entry middle-of-the-market aircraft developed as an educational and research platform for a new project-based MEng course at the University of Glasgow. The concept integrates boundary-layer ingestion, turbo-electric propulsion, composites and active laminar control to allow students to explore sustainable, industrially relevant aircraft design. | ||||
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| 16:30 | 16:55 | 5.3.1 |
RIGID AND AEROELASTIC RESPONSE OF A COMMERCIAL TRANSPORT AIRCRAFT TO TRANSONIC SHOCK BUFFET M. J. Candon, RMIT University, Australia This paper will compare Unsteady Reynolds-Averaged Navier-Stokes (RANS), Large-Eddy Simulation (LES) and/or Hybrid RANS-LES models for transonic buffet on the NASA Common Research Model - an important contribution towards establishing best practices in shock buffet modeling for real-world aircraft configurations. | ||||
| 16:55 | 17:20 | 5.3.2 |
HIGH-FIDELITY ANALYSIS OF AIRCRAFT TAIL BUFFETING UNDER DYNAMIC MANEUVERING Y Lua, Global Engineering and Materials, Inc., United States This paper aims to investigate and validate a new stabilized compressible-flow finite element framework for coupled aeroelastic simulation of aircraft tail buffeting under maneuvering conditions. The framework comprises streamline upwind/Petrov–Galerkin (SUPG)–based Navier–Stokes equations for compressible flow, weakly enforced essential boundary conditions that act as a wall function, and an entropy-based discontinuity-capturing formulation that serves as a shock-capturing operator. The developed stabilized finite element–based compressible-flow fluid–structure interaction (FSI) approach is implemented within an arbitrary Lagrangian–Eulerian (ALE) framework, enabling rigid-body motion of the aircraft model. Aircraft forward velocity, Euler angles, and body angular rates are used to update the mesh motion in the ALE framework, allowing accurate replication of dynamic maneuvers. A component-level validation study is performed using flow over a NACA 0012 airfoil. Simulations of the NASA Common Research Model (CRM) aircraft are then conducted to investigate tail buffeting using time-dependent maneuver data. A simple wind-up turn maneuver is simulated to demonstrate the modeling framework and to capture the structural response of the horizontal stabilizer of the NASA CRM model induced by buffeting loads. | ||||
| 17:20 | 17:45 | 5.3.3 |
BUFFETING SCALE EFFECTS ON A LAUNCH VEHICLE: HYBRID RANS-LES ANALYSIS D. Palma, Sapienza university of Rome, Italy Buffeting is a critical unsteady aerodynamic phenomenon affecting launch vehicles during atmospheric ascent. This work investigates the effect of geometric scale on buffeting by means of hybrid RANS–LES simulations of a reference launcher configuration. Results show a clear influence of scale on unsteady pressure loads, highlighting limitations in direct wind-tunnel data extrapolation. | ||||
| 17:45 | 18:10 | 5.3.4 |
AILERON EFFICIENCY ANALYSIS OF FLEXIBLE HIGH-ASPECT-RATIO WING Y. Zhao, Northwestern Polytechnical University, China This paper investigates the influence of aeroelastic deformation on static aileron control efficiency and free-flight dynamic roll maneuverability of high-aspect-ratio wings based on an aeroelastic-flight dynamics platform embedded with enhanced modal approach, which captures geometrically nonlinear effects and analyzes aileron efficiency by deflecting ailerons at various spanwise locations | ||||
| additional information (interactive) | 5.3.R |
COST-EFFECTIVE STAR-CCM+ REPRODUCTION OF DPW-7 CASE 2A: MESH EFFECTS ON CRM TRANSONIC PITCHING MOMENT AND ADAPTIVE REFINEMENT LIMITS G. C. Ribolla¹, M. B. Stergiou¹, L. J. F. Meirelles¹, L. F. S. Gomes¹, R. M. Granzoto, Embraer, Brazil; P. Bufacchi¹; ¹Insper, Brazil | |||||
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| 16:30 | 16:55 | 6.3.1 |
RECEPTIVITY OF NON-MODAL STREAKS IN HYPERSONIC BLUNT BOUNDARY LAYERS: FROM NUMERICS TO ASYMPTOTICS M. Dong, Institute of Mechanics, Chinese Academy of Sciences, China We study the receptivity of hypersonic blunt boundary layers of non-modal perturbations. By developing an efficient SF-HLNS approach and asymptotic analysis, we identify a slow-down convection mechanism near the stagnation point that amplifies streamwise vorticity by a factor of O(R^-1/2). The excited perturbations eventually evolve into streaky structures with an amplitude of O(R). | ||||
| 16:55 | 17:20 | 6.3.2 |
ORIGIN OF TRANSIENT TURBULENT SPOTS IN HYPERSONIC SWEPT BOUNDARY-LAYERS WITH MORPHING SWEEP ANGLES Jiang Genrui¹, Dong Ming¹; ¹Institute of Mechanics, Chinese Academy of Sciences, China This study explores hypersonic boundary layer transition during dynamic sweep-angle morphing. Using DNS and instability analysis, we identify a wave-packet collision mechanism that accelerates crossflow mode growth and triggers transient turbulent spots. These findings reveal critical aerodynamic heating risks essential for the thermal management of future morphing vehicles. | ||||
| 17:20 | 17:45 | 6.3.3 |
NUMERICAL SIMULATION OF HYPERSONIC PLASMA FLOW BASED ON NONLINEAR COUPLED CONSTITUTIVE RELATIONS H. Shi, Northwestern Polytechnical University, China ?????????NCCR-MHD????????????????????????67%?????????????????????????????MHD?????????????????????????????????????????? | ||||
| 17:45 | 18:10 | 6.3.4 |
AFTERBODY CURVATURE EFFECTS ON FLOW LOSS CHARACTERISTICS BASED ON ENTROPY PRODUCTION X.W. Chen, Shanghai Jiao Tong University, China An entropy-production-based loss decomposition framework is used to quantify curvature-induced loss on a 2D wide-range speed aircraft profile. Varying the afterbody radius leaves the loss pattern largely unchanged but alters entropy-production intensity and integrated afterbody loss. The findings highlight unresolved afterbody loss mechanisms for further study. | ||||
| Reserve Paper | 6.3.R |
MASSIVELY-SEPARATED HYPERSONIC TURBULENT SWBLI ON HIFIRE-1 AXISYMMETRIC CONE-CYLINDER-FLARE IN RAREFIED FLOW RO Bura, Republic of Indonesia Defense University, Indonesia | |||||
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| 16:30 | 16:55 | 7.3.1 |
TOWARDS AN OPTIMAL STRUT-BRACED-WING REGIONAL JET WITH NATURAL LAMINAR FLOW N Saladeh, University of Toronto, Canada This work aims to find the optimal combination of cruise altitude and wing sweep angle for a transonic strut-braced-wing regional jet with natural laminar flow operating at a cruise speed of Mach 0.78. Using aerodynamic shape optimization with integrated transition prediction, cruise drag can be minimized while ensuring a design that is robust to variations in cruise speed and lift coefficient. | ||||
| 16:55 | 17:20 | 7.3.2 |
AERODYNAMIC SHAPE OPTIMIZATION OF NATURAL LAMINAR FLOW SWEPT WINGS FOR REGIONAL AND SINGLE-AISLE AIRCRAFT F. Husain, University of Toronto Institute for Aerospace Studies, Canada This paper addresses the challenge of achieving natural laminar flow on transonic swept wings. A high-fidelity RANS-based aerodynamic shape optimization coupled with a transition prediction model is applied to infinite swept and finite wings representative of regional and single-aisle aircraft, to quantify NLF benefits and to ensure robustness across varying operating conditions. | ||||
| 17:20 | 17:45 | 7.3.3 |
MULTIPOINT INVERSE DESIGN FOR TRANSONIC, SLOTTED, NATURAL-LAMINAR-FLOW WINGS J. G. Coder, Penn State University, United States A new multipoint design method is proposed for slotted NLF wings on transonic, ultra-efficient aircraft. It is based on the CDISC framework augmented by the laminar-flow design strategy of Eppler. It works by specifying the target pressure distribution on segments of the wing, and the segments can be driven by different design conditions. | ||||
| 17:45 | 18:10 | 7.3.4 |
LAMINAR-TURBULENT-SUPERCRITICAL-WING CONCEPT AND ITS AERODYNAMIC PROPERTIES IN TRANSONIC FLIGHT W. Stalewski, ?ukasiewicz Research Network – Institute of Aviation, Poland A laminar-turbulent-supercritical wing concept was developed and tested using computer simulations. The essence of this concept is that, depending on the current flight conditions, it exhibits aerodynamic properties characteristic of either a natural-laminar-flow wing or a turbulent wing. Movable micro-vanes were proposed to control the flow type (laminar or turbulent) on the wing. | ||||
| Reserve Paper | 7.3.R |
VORTEX TOPOLOGY AND DRAG REDUCTION ANALYSIS IN SPIROID WINGTIP DEVICES USING PARTICLE TRACKING VELOCIMETRY Merina Amon Mwasandube, Australia | |||||
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| 16:30 | 16:55 | 8.3.1 |
A PROCESS-STRUCTURE-PROPERTY-PERFORMANCE FRAMEWORK FOR DIGITAL ENGINEERING-ENABLED FABRICATION AND REPAIR OF ALUMINUM PARTS Y Lua, Global Engineering and Materials, Inc., United States Aircraft corrosion maintenance and control are major drivers of sustainment cost and contributors to reduced aircraft availability. Structural repair based on either melting-based or solid-state approaches aims to restore the original geometry while achieving adequate post-repair mechanical performance. Unlike mainstream fusion-based additive manufacturing (AM) methods, additive friction stir deposition (AFSD) does not involve metal melting and solidification; therefore, defects such as lack of fusion, keyholing, and large residual stresses can be largely eliminated. AFSD integrates the friction stir principle with a material-feeding mechanism to enable location-specific material deposition, from which three-dimensional components can be built. AFSD is particularly well suited for the repair of damaged AA7075 components because it produces fully dense material in the as-deposited state with fine, equiaxed microstructures. Severe plastic deformation at elevated temperatures during deposition promotes dynamic recrystallization, typically resulting in refined microstructures with wrought-like mechanical properties. In addition, strong metallurgical bonding can be established between the deposited material and the substrate, eliminating weak interfaces commonly observed in repaired systems. The mechanical performance of AFSD-repaired components strongly depends on the distribution of process-induced defects and microstructure-driven constitutive behavior. Although AFSD offers significant flexibility to tailor microstructure through control of machine inputs, feedstock selection, and external thermal conditions during and after deposition, reliance on trial-and-error approaches to identify optimal repair strategies within a high-dimensional design space is both costly and time-consuming. For a given damage configuration and performance requirement, it is therefore critical to rapidly define an operational process window and associated thermal boundary conditions that min | ||||
| 16:55 | 17:20 | 8.3.2 |
MOLECULAR DYNAMICS SIMULATION OF MULTI-COMPONENT SUSTAINABLE EPOXY SYSTEMS FOR STRUCTURAL AEROSPACE APPLICATIONS IG Garay, Australia This work investigates the validity of introducing sustainable resins into conventional aerospace epoxy systems to synthesise novel aerospace materials for structural applications. Molecular dynamics simulations are employed to predict the thermomechanical properties such as density, gel point, glass transition temperature (T_g), Young’s modulus (E), and toughness of the multi-component systems. | ||||
| 17:20 | 17:45 | 8.3.3 |
FRACTURE AND GRAIN BOUNDARY DAMAGE IN AM NI-BASED SUPERALLOYS UNDER HIGH-TEMPERATURE TENSILE LOADING X Liu, China This study investigates the uniaxial tensile behavior at 500°C of an SLM-produced Ni-based superalloy. Macroscopic testing and microstructural analysis examine failure characteristics and grain boundary damage. Findings aim to elucidate damage mechanisms, support constitutive modeling, and enhance aerospace applications. | ||||
| 17:45 | 18:10 | 8.3.4 |
MODELING CREEP DEFORMATION AND PREDICTING RUPTURE LIFE OF STRESS-CONCENTRATED DZ411 SUPERALLOY COMPONENTS USING A THREE-STAGE CREEP FRAMEWORK Z.-K. Li, Beihang University, China This study investigated the creep deformation and rupture life of circumferentially notched round-bar specimens made of the DS nickel-based superalloy DZ411 under various temperatures and loading conditions at elevated temperatures. Finite element analyses based on a three-stage creep constitutive model were performed and validated against corresponding high-temperature creep rupture tests. | ||||
| Reserve Paper | 8.3.R |
LOAD-BEARING CAPACITY AND DAMAGE MODE OF THERMOELECTRIC DEVICES WITH TEMPERATURE-DEPENDENT ASYMMETRIC ELASTOPLASTICITY Y Lu, Northwestern Polytechnical University, China | |||||
| Reserve Paper | 8.3.R |
A NANOINDENTATION-BASED APPROACH FOR CALIBRATING CRYSTAL PLASTICITY PARAMETERS OF TI-6AL-4V N/A Yu, Beihang University, China | |||||
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| 16:30 | 16:55 | 9.3.1 |
KEY PARAMETER IDENTIFICATION IN AIRCRAFT STRAIN PREDICTION MODELS K. E. Niessen, Defence Science and Technology Group, Australia Individual aircraft tracking models are used to prevent the catastrophic failure of aerospace vehicle structures due to fatigue. This paper reports on computationally efficient methods used to select key parameters for inclusion in sophisticated tracking models developed using artificial intelligence techniques. | ||||
| 16:55 | 17:20 | 9.3.2 |
AIRFRAME HEALTH MONITORING ON THE BAE SYSTEMS HAWK T1A JET TRAINER AIRCRAFT G Dessena, Universidad Carlos III de Madrid, Spain This work demonstrates vibration-based airframe health monitoring on a full-scale BAE Systems Hawk T1A aircraft using modal analysis. Damage sensitivity is assessed through mode shape correlation across multiple excitation scenarios. Results show that selected modes exhibit clear monotonic trends with damage severity, supporting SHM adoption in aerospace and other safety-critical industries. | ||||
| 17:20 | 17:45 | 9.3.3 |
MTCL FOR COMPOSITE DAMAGE SM Miao , Northwestern Polytechnical University, China Damage tolerance and high survivability of aircraft structures are key design indices for modern aircraft. When a wing box sustains composite damage, the elastoplastic coupling mechanism significantly reduces its load-bearing capacity. Detection, classification, and quantitative assessment of composite damage are critical for evaluating structural load-bearing capacity. However, existing methods often face challenges such as difficulties in multi-task collaboration and scarcity of labeled data. To achieve efficient multi-task synergy from detection to quantitative analysis, this paper proposes a consistency regularization-based semi-supervised multi-task learning framework (MTCL). The framework deeply integrates damage detection/classification and dent depth estimation through a multi-task learning mechanism, utilizing YOLOv8 as the backbone for shared feature extraction. Specifically, one branch focuses on the localization and classification of multiple types of damage, while the other branch performs pixel-level depth estimation for dent defects. In addition, to address the challenge of scarce real labels in multi-task learning models, a Mean Teacher collaborative training mechanism is proposed. This mechanism combines supervised loss with unsupervised loss based on consistency regularization, forming a joint optimization objective that enables the fusion of labeled and unlabeled data. For the dent depth estimation task, a scale-aware depth regression module is designed, which decouples relative depth prediction from absolute scale estimation and achieves precise quantification of pit defect depth with only a small amount of real depth-annotated data. Validation demonstrates that the framework exhibits superior data utilization efficiency under conditions of scarce label data. It not only provides a technical pathway for quantitative assessment of composite structure damage, but also offers a referential framework for visual inspection and depth estimation through | ||||
| 17:45 | 18:10 | 9.3.4 |
IMPACT LOAD IDENTIFICATION METHOD FOR AIRCRAFT RUDDER PLANES BASED ON NARX NEURAL NETWORK S.-Y. Liang, China Accurate identification of impact loads has great influence on the safe and reliable operation of practical engineering structures. To ensure the reliability of structural design, designers need to accurately know the effect of impact loads acting on structures, such as load amplitude and duration, so as to effectively reduce or even eliminate the adverse effects of impact loads on structural performance. Taking aircraft rudder plane model as the research object, this paper investigates the application of the Nonlinear Autoregressive with Exogenous Inputs (NARX) neural network in impact load identification. The recurrent neural network, which is widely used in the field of deep learning, is introduced into the research on impact load identification. By combining the "memory" characteristic of recurrent neural networks with the solution principle of impact response, the goal of impact load identification is achieved. | ||||
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| 16:30 | 16:55 | 10.3.1 |
IMPACT ASSESSMENT OF COMPONENT FAILURES IN A PEM-FUEL CELL BASED PROPULISON SYSTEM FOR AIRCRAFT APPLICATIONS S. Bäumler, MTU Aero Engines AG, Germany A quantitative assessment of the impact of component failure modes occurring in a fuel cell propulsion system on available power and efficiency of the system is conducted using a simulation model. The general understanding of failure effects is enhanced and valuable insights for safety assessments are provided. Furthermore, recommendations for system design or control strategies may be derived. | ||||
| 16:55 | 17:20 | 10.3.2 |
NUMERICAL AND EXPERIMENTAL EVALUATION OF COMPACT TPMS AND OFFSET-STRIP-FIN HEAT EXCHANGERS FOR FUEL CELL SYSTEM COOLING IN AN ELECTRIC AIRCRAFT C.K. Sain, German Aerospace Center (DLR), Germany The challenges of fuel cell power aircraft lie in reducing the weight and size of the system and its critical components. This paper presents a performance study of three compact heat exchanger designs for cooling fuel cell systems. The results of the CFD analysis show that the optimized gyroid pipe HEX design achieved the best thermohydraulic results outperforming offset-fin-plate design. | ||||
| 17:20 | 17:45 | 10.3.3 |
DESIGN AND OPTIMIZATION OF AXIALLY GRADED OFFSET STRIP-FIN HEAT EXCHANGERS FOR MEGAWATT-CLASS FUEL CELL ELECTRIC AIRCRAFT Shivaji Bhapkar, German Aerospace Center (DLR), Germany Axially graded offset strip-fin heat exchangers are investigated for megawatt-class fuel-cell electric aircraft. A segment-wise rating and optimization framework redistributes aerodynamic losses along the flow direction while maintaining heat duty and volume constraints. Results demonstrate reductions exceeding 30% in air-side pressure drop and pumping power compared to uniform designs, enabling more efficient and scalable thermal management system for electric aircraft. | ||||
| 17:45 | 18:10 | 10.3.4 |
FUEL CELL ASSISTED DISTRIBUTED BOUNDARY LAYER INGESTION FANS FOR CRUISE EFFICIENCY IMPROVEMENT IN SINGLE AISLE TRANSPORT AIRCRAFT P.W.T. Somaweera, RMIT University , Australia This paper investigates a fuel cell assisted distributed boundary layer ingestion concept for single aisle aircraft. Electrically driven aft fuselage fans ingest and re energise the boundary layer during cruise to reduce wake losses. First order modelling identifies efficiency trends and break even conditions under realistic installation constraints. | ||||
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| 16:30 | 16:55 | 11.3.1 |
DATA-DRIVEN SYNTHESIS OF AIRCRAFT FEEDBACK CONTROL LAWS FOR NEW COMMERCIAL FLIGHT SCENARIOS M.W. Szymanski, Hamburg University of Technology, Germany Designing feedback control laws for commercial aircraft has mostly relied on classical linear control methods. However, they often lack a full understanding of the actual control problem and fail to enable climate-friendly flight, namely formation and air-to-air refueling flight. The proposed methodology shall improve the current process by using modern numerical and data-driven control methods. | ||||
| 16:55 | 17:20 | 11.3.2 |
COMPARISON OF NONLINEAR DYNAMIC INVERSION TECHNIQUES FOR FIGHTER JET LONGITUDINAL CONTROL AT TRANSONIC SPEEDS J.M. Drummond, Brazil This paper evaluates nonlinear control strategies for improving short?period flying qualities of a generic fighter in the transonic regime. Simulations assesses responses to variations in mass, CG, altitude, and feed?forward gain, comparing NDI and INDI tracking performance and disturbance rejection using a C?star–based controlled variable. | ||||
| 17:20 | 17:45 | 11.3.3 |
AUTOPILOT DESIGN OF AN UNSTABLE FIGHTER USING MODEL PREDICTIVE CONTROL M Morales, ITA, Brazil; M Rempel, Embraer, Brazil Model Predictive Control (MPC) has been widely studied for flight control systems due to its inherent fault-handling capabilities enabled by analytical redundancy. This work investigates the design of autopilot functions using nonlinear MPC to perform altitude hold and flight-level change, evaluated on the nonlinear ADMIRE aircraft model. | ||||
| 17:45 | 18:10 | 11.3.4 |
KNOW YOUR LIMITS: ESTIMATING THE TILT-WING TRANSITION CORRIDOR UNDER FAILURE CONDITIONS M. S. May, DLR e.V., Germany The backward transition from cruise to hover flight is the decisive flight maneuver for tilt-wing aircraft, as it is required to maintain the vertical landing capability. At the same time, this flight phase is especially challenging, as the low thrust settings for decelerating flight reduce positive slipstream effects, and the wings are pushed towards or beyond flow separation. These conditions become even more severe under failure conditions. To maintain safe flight states, flight guidance and flight control have to respect the resulting aircraft limitations. This, however, requires a sound knowledge of the reduced flight envelope, which is expressed by the transition corridor for transition maneuvers. Therefore, this study estimates the reduced transition corridor with an optimal-control-based approach for selected failure cases. The presented method provides a foundation for fault-tolerant operations of transformational aircraft, which is a crucial step towards their market readiness. | ||||
| Reserve Paper | 11.3.R |
ROBUST ATTITUDE RECOVERY CONTROL FOR AIR-LAUNCHED FOLDING-WING UAVS VIA DISTURBANCE-COMPENSATED SUPER-TWISTING SLIDING MODE S. Han, China | |||||
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| 16:30 | 16:55 | 12.3.1 |
MULTI-OBJECTIVE OPTIMIZATION OF AERO-ENGINE BEARING CHAMBER SCAVENGE STRUCTURE BASED ON NSGA-II ALGORITHM Z Zhu, Northwestern Polytechnical University, China The multi-objective optimization framework proposed in this study for the coordinated enhancement of oil scavenging and thermal management effectively improves bearing chamber performance. It can be extended to rotating machinery such as gas turbines and electric drivetrains, providing a general solution for designing low-loss lubrication systems aligned with carbon-neutral objectives. | ||||
| 16:55 | 17:20 | 12.3.2 |
OSCILLATORY FAILURE DETECTION IN AIRCRAFT ACTUATION SYSTEMS USING WAVELET TRANSFORM IO Skusa, Brazil This work presents an analytical redundancy-based method to detect oscillatory faults in flight control systems. In this context, the focus is to evaluate wavelet transforms applied as a signal processing method on residuals generated by observers in a system-level perspective. The results demonstrate that the proposed approach achieved reliable fault detection within three cycles of fault onset. | ||||
| 17:20 | 17:45 | 12.3.3 |
PERFORMANCE DEGRADATION ANALYSIS OF RESOLVER FAULTS IN ELECTRO-MECHANICAL ACTUATOR S. Guan, Beihang University, China Resolvers are used for EMA servo feedback; position accuracy affects motor control. In harsh long-term service, turn-to-turn shorts and rotor eccentricity degrade sin/cos signals and performance. We build a mutual-inductance WR-resolver model with physical injection for SCF and eccentricity, and quantify impacts on signal quality, angle estimation, and motor behavior via THD and angle error. | ||||
| 17:45 | 18:10 | 12.3.4 |
MECHANISM-DATA FUSION MODELING METHOD FOR AEROSPACE ELECTROMECHANICAL ACTUATOR SYSTEMS Y.T.-Q. Yang, School of Mechanical Engineering and Automation, Beihang Univers, China This study develops a mechanism-data fusion model for aerospace electromechanical actuators to overcome the limitations of traditional modeling. It integrates a high-fidelity physical model with a deep learning-based compensator trained on data from a dedicated test bench, creating a high-accuracy digital model for system analysis and control validation. | ||||
| Reserve Paper | 12.3.R |
PRACTICAL ASPECT OF FLIGHT TESTING DRONE NAVIGATION SYSTEMS UNDER GPS-DENIED CONDITIONS Y.I. Jenie, Faculty of Mechanical and Aerospace Engineering, Institut Teknol, Indonesia | |||||
| additional information (interactive) | 12.3.R |
INTEGRATED CONTROL STRATEGY BASED ON PHYSICS-INFORMED MODEL-BASED REINFORCEMENT LEARNING FOR AIRBORNE LASER WEAPON S. Bai, China | |||||
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| 16:30 | 16:55 | 13.3.1 |
FLIGHT PLANNING, THE FORGOTTEN ASSET A. Dickinson, Australia FLIGHT PLANNING, THE FORGOTTEN ASSET | ||||
| 16:55 | 17:20 | 13.3.2 |
GLOBAL AVIATION MONITORING IN 2023 M. Clococeanu¹, C.-M. Weder¹, H. Bruder¹, Z.-L. Zengerling¹; ¹German Aerospace Center, Germany A global aviation monitor for 2023 is developed, combining an emissions inventory with system-level analyses. ADS-B data is used to reconstruct global flight trajectories across all aviation sectors and, together with aircraft performance and meteorological data, to quantify emissions. A dedicated cargo flight plan is derived, and system responses to geopolitical and natural events are assessed. | ||||
| 17:20 | 17:45 | 13.3.3 |
JOINT TRAJECTORY OPTIMIZATION AND DECONFLICTION FOR CLIMATE IMPACT MITIGATION T Ehlers, German Aerospace Center, Germany We show first results in a free-flight scenario where the non-CO2 climate impact of individual trajectories is optimized using the trajectory optimizer pyTOM and conflicts are resolved afterwards using NDMap. These results indicate that an optimize-first - deconflict-later approach leads to conflict-free traffic scenarios while preserving a large portion of the climate impact mitigation potential. | ||||
| 17:45 | 18:10 | 13.3.4 |
EXPOSURE-AWARE COMPOUND CLIMATE HAZARDS FOR AIRPORTS: A TIERED EXTREMES FRAMEWORK LINKED TO FLIGHT TRAFFIC K.- S. Sumaja, University of New South Wales, Australia We introduce an exposure?aware, tiered framework that uses standard climate extreme indices for temperature and rainfall and a normalised flight traffic index to quantify single and compound hazards (heat–rain, rain–wind, heat–wind, triples). Demonstrated at Sydney Airport, it pinpoints high?risk months and sites and informs targeted, operational decisions. | ||||
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| 16:30 | 16:55 | 14.3.1 |
AUTONOMOUS LANDING OF UAVS ON SHIPS USING DECOUPLED REINFORCEMENT LEARNING T. K. Gerner, RMIT University, Australia Autonomous UAV landing on ship decks is challenged by stochastic winds and wave-induced motion. This paper presents a decoupled actor–critic reinforcement learning framework with separate horizontal/attitude and vertical controllers. Evaluated in a Gazebo–ROS–PX4 simulation, the approach achieves robust deck tracking with 25 cm horizontal error and soft landings with 0.35 m/s RMS relative velocity under varying wind conditions. | ||||
| 16:55 | 17:20 | 14.3.2 |
A SIMULATION METHODOLOGY FOR MULTIROTOR-ASSISTED UAV LAUNCH A. G. P. Sarmento, Aeronautics Institute of Technology (ITA), Brazil This work introduces a safe, repeatable, human-in-the-loop simulation method for multirotor-assisted fixed-wing UAV launch, coupling Unreal Engine realism with MATLAB/Simulink dynamics via ROS 2 and UDP. It enables systematic evaluation of separation, control, and operator decisions, reducing flight-test risk for forestry, inspection, defense, and logistics. | ||||
| 17:20 | 17:45 | 14.3.3 |
AUTONOMOUS PATHPLANNING ALGORITHM FOR EMERGENCY LANDING OF AAM CONSIDERING WIND DISTURBANCES H. Iwamoto, Yokohama National Univercity, Japan Addressing strict battery and environmental constraints in AAM, this study develops an autonomous emergency landing system. By coupling wind-aware power modeling with real-time vertiport congestion analysis, the algorithm filters unreachable ports and selects the safest landing site, providing critical decision support for operators during in-flight emergencies. | ||||
| 17:45 | 18:10 | 14.3.4 |
ASSESSMENT OF THE LANDING CAPABILITIES OF A FLEXIBLE HIGH-ALTITUDE PLATFORM AT LONGITUDINAL AND LATERAL-DIRECTIONAL WIND Y. J. Hasan, DLR Institute of Flight Systems, Germany This paper deals with landing simulations of the flexible high-altitude platform developed by DLR at different wind conditions. The test cases comprise constant wind, wind shear and gusts, each from different horizontal directions between 0° and 180°and encountered at different altitudes. Moreover, light continuous turbulence is superimposed in all cases. | ||||
| Reserve Paper | 14.3.R |
A SIMULATION BENCHMARK FOR AUTONOMOUS TAXIING CONTROL BASED ON VALIDATED UAV NONLINEAR GROUND DYNAMICS A Zajdel, ?ukasiewicz Research Network - Institute of Aviation, Poland | |||||
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| 16:30 | 16:55 | 15.3.1 |
QUANTIFYING THE EFFECT OF IN-CABIN AIRCRAFT NOISE ON COGNITION. B. R. C. Molesworth , University of New South Wales Sydney, Australia The effects of in-cabin aircraft noise on cognition and performance remains largely unknown. The present study describes three applied experiments articulating the effect of in-cabin aircraft noise on cognition and performance. Noise at levels present during cruise are shown to adversely affect recognition and dynamic decision-making performance. These effects adversely affect safety. | ||||
| 16:55 | 17:20 | 15.3.2 |
PILOT WORKLOAD PROFILES UNDER CONTINUOUS MULTI-TASKING AND SPARSE EVENTS VIGILANCE W.-D. Xiao¹, C.-L. Zhao, Shanghai Aircraft Design and Research Institute, China; Y. Gao¹, Y.-Y. Lu¹, S. Fu¹; ¹Shanghai Jiao Tong University, China This study compares pilot workload under continuous multi-task control and sparse event vigilance in highly automated flight contexts. Behavioral, ocular, and EEG measures reveal distinct workload profiles. While continuous control leads to performance degradation, sparse vigilance induces sustained anticipatory readiness, reflected in neural dynamics despite improved behavioral efficiency. | ||||
| 17:20 | 17:45 | 15.3.3 |
UNCERTAINTY ANALYSIS AND EYE-TRACKING-BASED CLUSTERING IN AIR TRAFFIC CONTROLLER WORKLOAD PREDICTION A. Lemetti¹, L. Meyer², M. Peukert², T. Polishchuk¹, C. Schmidt¹, H. Alpfjord Wylde²; ¹Linköping University (LiU), Sweden ;²Air Navigation Services of Sweden (LFV), Research & Innovation, Sweden We analyze how socio-demographic, temporal, and variability-based factors shape machine-learning workload prediction from eye-tracking and head-movement data of air traffic controllers. Time-on-task raises performance slightly, while experience and clustering based on variability in eye-tracking and head-movement patterns yield larger gains, showing that models benefit when they incorporate individual differences. | ||||
| 17:45 | 18:10 | 15.3.4 |
HRV BASED PILOTS WORKLOAD PREDICTION FOR AN INTELLIGENT COCKPIT WARNING SYSTEM A. E. Esposito, Kore University of Enna, Italy This study explores the integration of heterogeneous data to improve cognitive workload assessment. HRV features from 49 subjects (34 pilots, 15 students) who performed several tasks on a full-flight simulator are analyzed. Random Forest and AdaBoost models assess workload classification, aiming to boost statistical power through mixed-population datasets. | ||||
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| 08:55 | 09:20 | 1.4.1 |
IFAR 2025 PERSPECTIVES ON NOISE REDUCTION FOR EMERGING AND CONVENTIONAL AIR TRANSPORT K. Benameur, ONERA, France This paper summarize outcomes of the IFAR café discussions at the 2025 IFAR Summit, reviewing technologies, AI?based tools, and regulatory measures for quieter aircraft, AAM, and supersonic transport. It identifies research and policy priorities for future low?noise aviation. | ||||
| 09:20 | 09:45 | 1.4.2 |
CHALLENGES IN ADVANCED AIR MOBILITY NOISE PREDICTION - FROM SOURCE TO PERCEPTION B.I. Schuchard, German Aerospace Center (DLR, Germany Advanced air mobility concepts introduce new challenges for aircraft noise and annoyance prediction. The relevance of psychoacoustic metrics and perception-based assessment methods are highlighted, emphasising the need for integrated, perception-oriented noise prediction frameworks for urban and regional AAM applications. | ||||
| 09:45 | 10:10 | 1.4.3 |
SONIC BOOM PREDICTION TECHNOLOG FOR SUPERSONIC CIVIL TRANSPORTS W Wang, AVIC Aerodynamics Research Institute, China Excessive sonic boom intensity disrupts residential life and ecological balance, leading to strict restrictions on supersonic flight over land. This paper summarizes the key technologies for sonic boom prediction of supersonic civil transports. | ||||
| 10:10 | 10:35 | 1.4.4 |
RECENT ADVANCES IN AEROACOUSTIC DESIGN OF ADVANCED AIR MOBILITY VEHICLES AS Sieradzki, ?ukasiewicz - Institute of Aviation, Poland Presenter: Witold Klimczyk, Lukasiewicz Research Network - Institute of Aviation The rapidly growing Advanced Air Mobility (AAM) sector encompasses a wide range of air vehicles differing in type, size, and intended use. This includes, among others, small unmanned multirotor systems or fixed- and tilt-wing aircraft, often featuring distributed or custom-designed propulsion systems. The continuous evolution of AAM, with a range of contributing technological advancements, is progressively mitigating the limitations that have constrained large-scale use of AAM vehicles in densely populated areas, although noise reduction remains a key challenge. In the present work, we address some of the challenges in the aeroacoustic design of AAM vehicles and outline ongoing activities focused on developing solutions for reducing noise emissions to acceptable levels. Selected aspects of aeroacoustic design of rotor propulsion systems are presented, including examples of noise-reduction technologies developed at ?ukasiewicz – Institute of Aviation. Finally, opportunities for further development and plans for future work are described. | ||||
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| 08:55 | 09:20 | 3.4.1 |
IMPACT OF SERIAL-PARALLEL POWERTRAIN SIZING STRATEGIES ON HYBRID-ELECTRIC AIRCRAFT PERFORMANCE G. Palaia, Polytechnic of Turin, Italy The study investigates serial-parallel hybrid-electric aircraft, focusing on how powertrain sizing parameters affect aircraft-level performance. An integrated MDO framework links installed power allocation and power management to mass, aerodynamics, and mission fuel burn, enabling a systematic exploration of design trade-offs and performance potential in conceptual aircraft design. | ||||
| 09:20 | 09:45 | 3.4.2 |
IMPLEMNTATION OF PROPELLER-WING INTERFERENCE MODEL AND HORIZONTAL TAIL ANALYSIS INTO A VISCOUS FULL POTENTIAL FLOW SOLVER FRAMEWORK FOR AIRCRAFT DESIG D.D.P. Di Pasquale, Cranfield University, United Kingdom This work extends a viscous full potential solver for propeller-driven aircraft by integrating a momentum-based propeller–wing interference model and a wake-based tailplane aerodynamic model. Validation using Cranfield’s SAAB 340 flight data demonstrates improved prediction of power-on performance, stability, and control effects with minimal computational cost. | ||||
| 09:45 | 10:10 | 3.4.3 |
IMPACT OF DIFFERENT PROPELLER CONFIGURATIONS ON THE FLIGHT DYNAMICS AND STABILITY OF A SMALL REGIONAL ELECTRIC AIRCRAFT A. H Hammad, Germany This research establishes a multi-fidelity framework to evaluate the stability of a regional electric aircraft. By integrating Digital DATCOM with VSPAERO/AVL simulations, it quantifies how shifting from nose-mounted to wing-tip mounted, inboard wing mounted and distributed wing-mounted propulsion effects the static margin and overall flight dynamics and stability of the aircraft. | ||||
| 10:10 | 10:35 | 3.4.4 |
PROPULSIVE EFFICIENCY AND ENERGY ANALYSIS OF AIRCRAFT CONCEPTS WITH AFT-FUSELAGE BOUNDARY-LAYER-INGESTION Z.-C. Zhou, China The evaluation of energy efficiency during the aircraft design phase is increasingly important, particularly for aircraft that operate at lower speeds and are of small or medium size. Although conventional propulsion efficiency theories relying on the energy balance approach are well established, significant limitations arise when these methods are applied to advanced CFD simulations and highly integrated propulsion configurations, such as fuselage boundary layer ingestion (BLI). This study provides a systematic review of traditional efficiency assessment frameworks and examines why these approaches are unsuitable for situations involving nonuniform incoming flows and strong interactions between aerodynamic and propulsive systems. Such limitations make it challenging to accurately relate local changes in propulsive efficiency to the energy consumption of the entire aircraft. In response, an improved method is introduced, which uses CFD-based energy decomposition within control volumes to quantify the specific efficiency advantages offered by boundary layer ingestion. By combining the resulting efficiency metric with a comprehensive aircraft mission energy model, the proposed analysis framework is made suitable for the design and evaluation of lower speed aircraft in the small and medium class. Through comparative analysis of flow fields and power allocation with and without aft fuselage BLI propulsion, the capability of boundary layer ingestion to reduce wake energy loss and enhance propulsive efficiency at the system level is demonstrated. The results confirm that the method provides a clear and quantitative connection between the local benefits of BLI and changes in overall aircraft energy use, offering robust support for engineering practice and optimization of BLI propulsion systems. | ||||
| Reserve Paper | 3.4.R |
RESONANT ELASTIC SHAFT THRUST VECTORING: IMPLICATIONS FOR UAV DESIGNS HF.G. Guan, Australia | |||||
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| 08:55 | 09:20 | 4.4.1 |
DESIGN AND INVESTIGATION OF A SHORT-TO-MEDIUM-RANGE AIRCRAFT WITH LIQUID HYDROGEN AND SAF MULTI-FUEL PROPULSION B. Tuerkyilmaz, Bauhaus Luftfahrt e. V., Germany In this paper, a dual-fuel (SAF and liquid hydrogen) short-to-medium-range aircraft is designed and evaluated against a SAF only baseline aircraft. The study setup and methodology are explained, including the design heuristics for the dual-fuel aircraft. Although the dual-fuel aircraft consumes more energy than the baseline aircraft, it can be advantageous in terms of energy cost. | ||||
| 09:20 | 09:45 | 4.4.2 |
CHALLENGES AND SOLUTIONS FOR LIQUID HYDROGEN-POWERED UAVS: REGULATIONS AND CASE STUDY INSIGHTS B. Legrand, ISAE-SUPAERO, France The current UAV market provides a vast selection of aircraft with useful loads ranging from grams to kilograms. However, commercial UAVs retain a limited operational range. With its compactness and weight, a LH2 powertrain increases the UAV range while safekeeping its useful load. Although its design remains challenging, solutions were found for the use case here presented: Drone Mermoz. | ||||
| 09:45 | 10:10 | 4.4.3 |
ADVANCED MODELING AND ANALYSIS OF A LIQUID HYDROGEN SHORT-MEDIUM RANGE AIRCRAFT CONCEPT FOR 2035 M. Kotzem, German Aerospace Center (DLR), Germany This study contributes to the maturation of a conceptual LH2 aircraft by integrating results of high-fidelity simulations into the OAD process: a hydrogen specific engine model including preconditioning, an LH2 system architecture and on-board system topology, and a structural tank integration concept validated by crash simulations are introduced and the corresponding integration effects analysed. | ||||
| 10:10 | 10:35 | 4.4.4 |
AN INTEGRATED SYSTEM-LEVEL AND MULTIPHYSICS APPROACH FOR AIRCRAFT LH2 FUEL SYSTEM DESIGN A. Tramposch, University of Applied Sciences FH JOANNEUM GesmbH, Austria This work presents an integrated system-level and multiphysics framework for the design of cryogenic LH2 fuel systems for aircraft. By combining mission-based system modeling, CFD analysis, and experimental validation, the approach enables evaluation of conflicting objectives such as boil-off reduction, pressure control, and throttle response. | ||||
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| 08:55 | 09:20 | 5.4.1 |
A PARAMETER-FREE ADAPTIVE LIMITER FOR HIGH-RESOLUTION SIMULATION OF COMPLEX SHOCK-DOMINATED FLOW G. Wang, Northwestern Polytechnical University, China Using pressure/Mach fluctuations and interface pressure gradients, the proposed parameter-free adaptive slope limiter dynamically adjusts limiting strength: reduces dissipation in smooth regions, suppresses oscillations at discontinuities, and improves stability, convergence, and drag/heat-flux accuracy. | ||||
| 09:20 | 09:45 | 5.4.2 |
A STUDY ON THE CELL REYNOLDS NUMBER AS A PARAMETER FOR MESH QUALITY ON HYPERSONIC FLOWS G. M. Poltronieri, Instituto Tecnologico de Aeronautica, Brazil The present work is concerned with studying the capability of addressing severe hypersonic flow conditions using a continuous formulation and defining an indicator for adequate mesh refinement for such simulations. The focus of the work is in discussing appropriate mesh refinement approaches in order to yield adequate treatment of all nonequilibrium phenomena present in such flows. | ||||
| 09:45 | 10:10 | 5.4.3 |
PLUME CHARACTERIZATION OF SOLID ROCKET MOTORS: COMPARISON OF EULERIAN AND DISCRETE PHASE MODELING APPROACHES A.O. Unsal, Roketsan Missiles Inc., Turkey This work provides a validated comparison of Eulerian and Lagrangian particle modeling approaches for solid rocket motor plumes. It clarifies when particle-resolved CFD is necessary and when gas-phase modeling is sufficient, offering practical guidance for accurate yet efficient multiphase simulations relevant to propulsion, and high-speed gas–solid flow applications. | ||||
| 10:10 | 10:35 | 5.4.4 |
INVESTIGATION OF PLUME NON-EQUILIBRIUM INFRARED RADIATION CHARACTERISTICS AT DIFFERENT MACH NUMBERS XU Jianyu, China; ZHOU Li, China; SHI Jie, China; WANG Zhanxue, China; SHI Hao, China The work investigates plume IR signatures at 80km across Ma 5-25 using an nonequilibrium flow-infrared simulation. Results show a "crescent+spike" morphology. As Ma increases, IR intensity follows a U-shaped trend, while nonequilibrium effects weaken. The plume shifts from expansion to compression-dominated. Higher Ma enhance core radiation and mixing, leading to trailing effects. | ||||
| additional information (interactive) | 5.4.R |
NUMERICAL INVESTIGATION OF SHOCKWAVE TURBULENT BOUNDARY LAYER INTERACTION AT MACH 2.5 OVER A COMPRESSION RAMP Z.A. Rana, Prince Mohammad bin Fahd University, Saudi Arabia | |||||
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| 08:55 | 09:20 | 6.4.1 |
FLUCTUATING SURFACE PRESSURE MEASUREMENTS OF JET IMPINGEMENT ON A SMALL ROTOR B. M. Malkki, The University of New South Wales, Australia This work presents the experimental measurement of small rotor blade interaction with a jet of air. This blade interaction has been captured through the measurement of fluctuating surface pressure (FSP) on the blades using a novel experiment rig. The full paper will cover frequency domain analysis of FSP, far-field microphone array results and comparison with blade interaction models. | ||||
| 09:20 | 09:45 | 6.4.2 |
STUDY OF THE FEASIBILITY OF ACOUSTIC LINERS INSIDE THE BEAM THAT INTERACTS WITH A UAV DRONE ROTOR Santiago Montoya-Ospina¹, Romain Gojon¹, Hélène Parisot-Dupuis¹, Frank Simon, DMPE-ONERA, France; ¹ISAE-SUPAERO, France This paper addresses the growing demand for advancements in rotorcraft technology by proposing the concept of acoustic liners integrated within surfaces surrounding a rotor. The study is involving a rotor working in installed conditions, where a beam simulates the connection between the propulsion system and the airframe of a classical drone configuration. The concept proved to be effective in reducing noise at the harmonics of the BPF. | ||||
| 09:45 | 10:10 | 6.4.3 |
EXPERIMENTAL INVESTIGATION ON THE INNER DUCT SURFACE UNSTEADY PRESSURE OF A DUCTED PROPELLER J. Li¹, Y. Yendrew¹, D. Moreau¹, C. Doolan¹; ¹University of New South Wales, Australia The unsteady wall pressure generated by a ducted propeller is measured using the remote microphone method. The variations in inner-wall pressure fluctuations with duct length and propeller axial position are characterized, and the results are compared with predictions from an analytical model and with far-field noise measurements to provide further insight into the underlying physical mechanisms. | ||||
| 10:10 | 10:35 | 6.4.4 |
MISSION-WIDE SEMI-EMPIRICAL AEROACOUSTIC NOISE MODELING OF A CARGO EVTOL UAV WITH CONSIDERATION OF A SIMPLE URBAN FLYOVER I. Peleshok, Technical University of Munich, Germany Mission-wide, flight-phase-specific semi-empirical noise source models are derived from flight-test measurements of a cargo eVTOL UAV. The approach enables mission-wide noise prediction and supports urban operational noise assessment. A simple urban flyover experiment reveals deviations between free-field and near-wall measurements, motivating reflection-aware extensions of the source models. | ||||
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| 08:55 | 09:20 | 7.4.1 |
VORTEX FLOW CONTROL USING JUNCTURE FILLETS ON A BLUNT-NOSED, CRANKED SWEPT WING N. van Luijk¹, A. van Meenen¹, R. Vos¹; ¹Delft University of Technology, Netherlands This study examines leading-edge juncture fillets for vortex flow control on a blunt-nosed, highly swept compound wing. The results show that these small geometric modifications can serve as passive vortex flow control devices, extending the usable angle-of-attack range by delaying vortex breakdown-induced pitch break, thereby supporting the design of novel configurations in off-design conditions. | ||||
| 09:20 | 09:45 | 7.4.2 |
INFLUENCE OF ZIGZAG TAPE–INDUCED TRANSITION ON THE DU89-134 AIRFOIL PERFOMANCE AT LOW REYNOLDS NUMBER M. Avirovic, Royal Military Academy, Belgium The influence of zigzag tape–induced boundary layer transition on the aerodynamic performance of the DU89-134 airfoil is investigated at low Reynolds number. Wind-tunnel force-balance measurements, pressure data, infrared thermography, and Reynolds-averaged Navier–Stokes simulations reveal Reynolds-number-dependent drag reduction linked to modifications of laminar separation bubble behaviour. | ||||
| 09:45 | 10:10 | 7.4.3 |
EXERGY AND INTEGRAL BOUNDARY LAYER PARAMETERS CHARACTERISTIC CURVES FOR AERODYNAMIC DESIGN G. Bourreau-Tirel, AURA AERO/ISAE-SUPAERO, France This work explores the design space of a low-fidelity exergy method by establishing its characteristic curves against classical integral boundary layer parameters. Analysis of exergy-based distributions along 2D airfoils demonstrates the approach's utility as a rapid diagnostic tool, guiding aerodynamic optimization by quantifying thermodynamic performance during conceptual aircraft design phases. | ||||
| 10:10 | 10:35 | 7.4.4 |
PARAMETRIC AERODYNAMIC STUDY OF LEADING-EDGE SERRATIONS ON WING SECTIONS ACROSS REYNOLDS NUMBERS J.J Whittaker, Australia This paper maps how leading-edge serrations' wavelength, amplitude, and termination distance increase wing performance across pre-stall, stall, and post-stall regimes. Provides starting point for industry investigations and gives evidence for supporting applications that operate at high angles of attack, including UAVs, eVTOL, rotor blades, and high-lift devices. | ||||
| additional information (interactive) | 7.4.R |
EFFECTS OF LEADING-EDGE HIGH-LIFT DEVICES ON THE LOW-SPEED VORTEX FIELD AND AERODYNAMIC FORCES FOR A SUPERSONIC CIVIL TRANSPORT X. -R. Zheng Zheng, Chinese Aeronautical Establishment, China | |||||
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| 08:30 | 08:55 | 8.4.1 |
COMPOSITE FUSELAGE TECHNOLOGIES FOR NEXT GENERATION COMMERCIAL AIRCRAFT Y. C. Roth, Airtbus Operations GmbH, Germany; P. Joern, Airbus Operations GmbH, Germany; A. Sadelfeld, Airbus Aerostructures GmbH, Germany; C. Rowedder, CTC GmbH, Germany; J. Buck, CTC GmbH, Germany; B. Demel, Airbus Helicopters Deutschland GmbH, Germany Next generation commercial aircraft need to meet a future demand of 40,000 units for the next 20 years resulting in higher delivery rates than today. Composite materials for large scale structures have been introduced over the last decades whereas novel designs, material alternatives and technologies will play a major role to meet future needs. Dedicated fuselage applications will be discussed. | ||||
| 08:55 | 09:20 | 8.4.2 |
COMPOSITE PLATE OPTIMIZATION UNDER COMBINED COMPRESSION AND SHEAR BUCKLING LOAD R.P Pereira da Silva, Boeing, Brazil In this work, optimal laminate configurations are identified for different compression–shear load ratios and boundary conditions, maximizing buckling resistance. The results provide discussion on the influence of load interaction, boundary conditions, and stacking sequence on the optimal design of composite plates for aerospace applications. | ||||
| 09:20 | 09:45 | 8.4.3 |
FIVE DECADES OF T-38 WING TEARDOWNS TJ Moran, Southwest Research Institute, United States For five decades, Southwest Research Institute (SwRI) and the United States Air Force (USAF) have been performing wing teardowns that drive design improvements, damage tolerant analysis refinement, risk assessments, and maintenance plans. These efforts have extended the fleet’s lifespan providing vital insights into aging aircraft durability and supporting 64 years of USAF pilot training operations. | ||||
| 10:10 | 10:35 | 8.4.4 |
GEOMETRICALLY EXACT MODEL OF CANTILEVER BEAM UNDERGOING LARGE DEFLECTION AND LINEARIZED DYNAMICS CHARACTERIZATION C.-Y. Yang¹, R. Zhao¹, Y.-S. Gu¹, Z.-C. Yang¹; ¹Northwestern Polytechnical University School of Aeronautics, China Presenter: Changyun Yang, School of Aeronautics, Northwestern Polytechnical University Nonlinear beam theories are widely used to study the mechanical behavior of high-aspect-ratio flexible wings, helicopter rotor blades, deep-sea risers and pipelines. However, present theoretical models usually introduce some simplifications in the research process. For example, the higher-order terms of are neglected when using Green's strain to characterize the geometric nonlinear relationship, using the axial coordinates of the beam to approximately replace the arc-length coordinates, or simplifying the structure stress or strain when using the arc-length method to characterize the structural deformation. These treatments may cause the theoretical analysis results to deviate from the finite element simulation or experimental results. In this paper, the kinetic energy and potential energy of Euler-Bernoulli beam undergoing large deformation are accurately described with arc length and curvature coordinates. The rotation angle of the beam is discretized by Galerkin method, and the control equation of the cantilever beam structure with applied load is derived based on Lagrange method. The static large deformation of the beam structure subjected to external loads is solved, and the modal frequencies in the resulting deformed state are obtained. The calculation results of the present model agree well with those by the finite element simulation and experiment, which indicates that the geometrically exact model based on curvature and arc length coordinates has high accuracy. | ||||
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| 08:30 | 08:55 | 9.4.1 |
ENERGY ABSORPTION OF THIN-WALLED CONCENTRIC SPHERES FOR CARGO AIRDROP A.E. Lloyd, The University of Sydney, Australia Conventional airdrop uses a cardboard honeycomb developed half a century ago to absorb energy at impact. This solution is logistically inefficient and has a sub-optimal crush efficiency. This study embraces additive manufacturing to create an energy absorbing structure with a low initial force, crush behaviour that promotes stroke and prolongs the onset of densification. | ||||
| 08:55 | 09:20 | 9.4.2 |
GROUND VIBRATION TEST ANALYSIS OF A PC-9 AIRCRAFT USING DELAY-EMBEDDED DYNAMIC MODE DECOMPOSITION WITH CONTROL A. Das, RMIT University, Australia Output-only modal identification for a Pilatus PC-9 GVT is performed using delay-embedded DMDc on acceleration-only data. Hankel embedding and a latent-input linear model recover modes, frequencies, and damping via SVD/least squares, with reconstruction checks and comparison to FRF/Siemens Testlab benchmarks. | ||||
| 09:20 | 09:45 | 9.4.3 |
NUMERICAL PREDICTION OF CABIN NOISE FOR FUTURE SHORT-HAUL AIRCRAFT IN EARLY AIRCRAFT DESIGN C. Hesse, DLR e.V., Germany A multi-disciplinary process to numerically predict the cabin noise in the the early aircraft design stage is proposed. This starts at conceptual level and entails disciplines like loads, structure and cabin design as well as noise prediction. Utilizing CPACS to ensure consistency among the different disciplines, interior noise for aircraft concepts using different energy carriers is compared. | ||||
| 10:10 | 10:35 | 9.4.4 |
DATA-DRIVEN MULTI-MODAL PREDICTION OF IMPACT RESPONSE IN COMPOSITE LAMINATES: FORCE–TIME HISTORIES AND INTERLAMINAR DELAMINATION G.J.-Zh Zhang, China Dual-modality surrogates predict composite-laminate impact response under material variations. A validated simulation dataset (3 parameters) provided aligned force–time histories and binary delamination projections. A GRU model with positional encoding predicts force–time curves; a conditional GAN generates delamination maps. Metrics confirm close agreement for low-cost design screening. | ||||
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| 08:55 | 09:20 | 10.4.1 |
ASSESSMENT OF ENGINE-OUT ATMOSPHERIC EMISSIONS FROM COCONUT-OIL-DERIVED BIOJET FUEL S. Ogawa, Osaka Metropolitan University, Japan This study demonstrates that coconut-oil-derived biojet fuel produced via a low-energy co-solvent process can significantly reduce CO2 and NO emissions in micro-jet engine tests. The results highlight a scalable, low-carbon fuel pathway applicable not only to aviation but also to other gas turbine and distributed energy systems. | ||||
| 09:20 | 09:45 | 10.4.2 |
MAGNETOPLASMAIONIC (MPI) ENGINE N. K. Chaudhary, Australia The Magnetoplasmaionic (MPI) Engine introduces a transformative propulsion concept by harnessing atmospheric electricity instead of conventional fuels. It accelerates plasma using electromagnetic forces within a magnetic confinement system, supported by advanced ionisation and energy collection technologies. This innovation redefines propulsion for sustainable, zero-emission air transportation. | ||||
| 09:45 | 10:10 | 10.4.3 |
EXPERIMENTAL EVALUATION OF THE PERFORMANCE & EMISSION FORMATION IN A MICRO-GAS TURBINE UTILISING SUSTAINABLE AVIATION FUEL (SAF) M.R Muhammad, NATIONAL AEROSPACE INDUSTRY CORPORATION MALAYA (NAICO MALAYSIA), Malaysia This study will experimentally investigate micro-gas turbine performance and emissions using SAF. A custom gate-to-gate cycle will compare a 38% SAF blend with Jet A-1, assessing transient response, fuel consumption, combustion stability, and NOx/CO emissions. Linear projections will estimate 100% SAF operation, volumetric penalties, and ECU calibration requirements. | ||||
| 10:10 | 10:35 | 10.4.4 |
SYSTEM-LEVEL MODELLING OF TURBOFAN NOISE SUPPRESSION AND ACOUSTIC LINER ATTENUATION X Zhao, Chalmers University of Technology, Sweden This paper presents a recent development of a system level noise model implementing a semi-empirical liner model that accounts for grazing flow effects and incident sound pressure levels. The study provides a rigorous comparison between the simplified constant noise suppression factor method and the implemented semi-empirical approach. By applying both methods to standardized ICAO certification trajectories and noise mapping scenarios, we quantify the errors introduced by "crude" suppression assumptions. Our results indicate that while constant suppression factors may be sufficient for preliminary estimates, they fail to capture the spectral shifts and performance variations across different flight phases and the requirements of preliminary multidisciplinary design in “new” engines. Ultimately, this work demonstrates that integrating semi-empirical liner physics into system-level frameworks significantly improves the accuracy of noise predictions while keeping the computations efficient. This approach offers a critical compromise for researchers who require both speed and physical reliability in noise assessment of new concepts. | ||||
| Reserve Paper | 10.4.R |
EVALUATION OF LIQUID HYDROGEN CONDITIONING CONCEPTS FOR AIRCRAFT ENGINES EMPLOYING EXHAUST GAS WASTE HEAT RECOVERY P. Kirschnek, FH JOANNEUM GesmbH, Austria | |||||
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| 08:55 | 09:20 | 11.4.1 |
TRAJECTORY OPTIMIZATION FOR TAKEOFF/LANDING BASED ON FLAP-AND-GLIDE FOR FLAPPING-WING UNMANNED AERIAL VEHICLE W.S. Lee¹, S.J. Kim¹, S.K. Kim¹; ¹Chungnam National University, South Korea Birds have evolved flight mechanisms optimized for Earth's environment, with energy efficiency being a key advantage. Accordingly, this study addresses an optimization problem to achieve efficient flight for Flapping Wing Aerial Vehicles (FWAVs). This paper presents a takeoff and landing strategy that mimics avian behavior to minimize energy consumption. | ||||
| 09:20 | 09:45 | 11.4.2 |
SENSITIVITY-BASED REFERENCE TRAJECTORY UPDATES FOR AIRCRAFT PATH-FOLLOWING MODEL PREDICTIVE CONTROL S. Fuchsgruber, Technische Universität München, Germany This paper deals with the post-optimal sensitivity analysis for trajectory optimization problems in order to carry out sensitivity-based reference trajectory updates for path-following Model Predictive Control. These updates are performed when deviations from the reference path occur. We show that following this updated reference trajectory is more beneficial. | ||||
| 09:45 | 10:10 | 11.4.3 |
OPTIMAL ZEM-BASED MIDCOURSE GUIDANCE FOR INTERCEPTORS USING TRAJECTORY PREDICTION S. Kim¹, K.-W. Jung¹, C.-H. Lee¹; ¹Korea Advanced Institute of Science and Technology, South Korea This paper proposes an energy-optimal guidance law for DACS-equipped interceptors. It explicitly minimizes control usage while ensuring finite-time convergence. Using a partial closed-form solution for aerodynamics, the method achieves high-fidelity prediction with minimal computational load. This offers a practical, fuel-efficient solution for real-time onboard missile defense systems. | ||||
| 10:10 | 10:35 | 11.4.4 |
TRAJECTORY OPTIMIZATION FOR ENERGY STATE RECOVERY DURING APPROACH: ENHANCING LOW ENERGY AWARENESS AND AUTOMATION J.L Nunes de Jesus Luz, Institute of Aeronautical Technology, Brazil The takeoff and landing phases remain the most critical segments of a flight, accounting for a significant proportion of aviation accidents, many of which are associated with inadequate energy management. Several historical events have shown that low-energy states during approach may develop gradually and remain insufficiently perceived by flight crews until recovery options become limited. This highlights the need for methods that go beyond conventional speed or path monitoring and provide predictive insight into the aircraft’s energetic condition. This paper proposed a trajectory optimization framework for energy state recovery during the approach phase, aimed at enhancing Low Energy Awareness and supporting the progression toward higher levels of flight automation. By formulating the problem in terms of aircraft energy dynamics and solving it as a nonlinear optimal control problem, the proposed approach enables the generation of dynamically feasible trajectories that guide the aircraft back to a nominal energy profile while respecting operational and safety constraints. | ||||
| additional information (interactive) | 11.4.R |
CONVEX OPTIMIZATION-BASED EMERGENCY LANDING TRAJECTORY GENERATION FOR UAM VEHICLES Y. Jung, Korea Aerospace Research Institute, South Korea | |||||
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| 08:55 | 09:20 | 12.4.1 |
DYN-MARS: A NEW CONCEPT ENABLING THE BEST APPROACH FLIGHT PROFILE P. Thöne, German Aerospace Center - DLR, Germany The main goal of the DYN-MARS project is to minimize the flight environmental footprint during descent and approach through operational implementation relying on improved collaboration between pilot and ATC in planning and executing the flight through novel avionic functions, and improved arrival routes and procedures. | ||||
| 09:20 | 09:45 | 12.4.2 |
WEATHER, AVIATION, AND CLIMATE: CURRENT TOPICS IN AIRBORNE RESEARCH Z. R. Milani, National Research Council of Canada, Canada A warming climate may increase hazardous weather that threatens aviation safety and efficiency. Using heavily instrumented research aircraft, this work delivers rare in situ data on icing, lightning, aerosols, and emissions. Results support safer aircraft design, improved weather awareness, cleaner aviation, and benefit industries from weather forecasting to climate monitoring. | ||||
| 09:45 | 10:10 | 12.4.3 |
A CONCEPT FOR SMARTPHONE-BASED EMERGENCY FLIGHT DATA INDICATION SYSTEM IN LIGHT AIRCRAFT P. Chudý, Julius-Maximilians-Universität Würzburg, Germany Access to mobile devices is widespread among general aviation pilots. The objective of this study was to determine the feasibility of using smartphones as emergency flight parameter indication systems in light aircraft. The conducted analysis and preliminary tests demonstrated that the accuracy of a mobile device enables future use of smartphones as pilot support systems in emergency situations. | ||||
| 10:10 | 10:35 | 12.4.4 |
AUTOMATING SYSTEM MODELING USING LARGE LANGUAGE MODELS I. S. Rehder, Brazil This work integrates LLMs into an Arcadia-based MBSE workflow to support early system modeling. A case study with a multimodal HMI for ISR missions in a MUM-T context shows that structured JSON descriptions can be transformed into Operational Analysis diagrams with reduced effort and consistent results. | ||||
| Reserve Paper | 12.4.R |
A RELIABLE AND COST-EFFICIENT DATA ACQUISITION SYSTEM FOR MIL-1763 STATIC EJECTION TESTING OF AIRCRAFT EXTERNAL STORES N.-V. Nguyen, Viettel Aerospace, Vietnam | |||||
| additional information (interactive) | 12.4.R |
CAPABILITY ANALYSIS OF CHINA’S AERIAL EMERGENCY COMMUNICATION SYSTEM: AN EFFECTIVENESS EVALUATION METHOD FOR AERIAL EMERGENCY COMMUNICATION SYSTEMS L Zhao, Aerial Industry Development Research Center of China, China | |||||
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| 08:55 | 09:20 | 13.4.1 |
VALUE DRIVEN CO-ARCHTIECTING AND TRADESPACE EXPLORATION: AN AERONAUTICAL CASE STUDY INVOLVING INDUSTRIAL SYSTEMS G. Donelli, German Aerospace Center DLR, Germany To satisfy the demand of innovative, sustainable and circular aircraft configurations, nowadays it is essential to investigate the entire aircraft life-cycle from design to production, to the disposal after the end of the system operation. Within the German-funded Project Dimension, a value-driven co-architecting methodology is exploited and applied to an aeronautical system component, that is the cargo door latching system. The aim is to show the advantages of including industrial systems (mainly manufacturing and supply chain) decisions in the early design phase. A value-driven tradespace is generated: each (co)architecture refers at the same time to a system configuration, materials and processes choice and supply chain combination. The exploration of this value-driven co-architecting tradespace allows to identify the most performant, competitive and sustainable solution by considering multiple stakeholders’ perspectives and expectations. This gives aeronautical companies the possibility to make robust and strategic decisions and define cutting edge solutions to remain competitive in the nowadays global aviation market. | ||||
| 09:20 | 09:45 | 13.4.2 |
ENABLING HIGH RATE COMPOSITE MANUFACTURING THROUGH A ROBUST MANUFACTURING DIGITAL ECOSYSTEM M.A. Rabiega, The Boeing Company, United States Delivering first?time quality at production rates for composite structures requires a robust manufacturing digital ecosystem. We will discuss a hub?and?spoke infrastructure and part?centric digital twin that contextualize and standardize composite fabrication and shop?floor data to validate engineering requirements. The standards-driven ecosystems enables high?rate process control and conformance. | ||||
| 09:45 | 10:10 | 13.4.3 |
A SYSTEMS-LEVEL MACHINE LEARNING FRAMEWORK FOR PREDICTIVE TRACKING IN AIRCRAFT DESIGN AND PRODUCTION S. Dutta, India A systems-level machine learning framework is presented for predictive tracking of aircraft design and manufacturing workflows. The approach models interdependencies across hierarchies and uses regression-based prediction to capture delay propagation. The framework is applicable to other complex engineering systems, including space systems, automotive manufacturing, and infrastructure projects. | ||||
| 10:10 | 10:35 | 13.4.4 |
AIRCRAFT AND INDUSTRIAL SYSTEMS CO-ARCHITECTING BASED ON VALUE-DRIVEN MBPLE APPROACH G. Donelli, German Aerospace Center DLR, Germany Traditionally, decisions related to the manufacturing and supply chain are taken after the design of a new aircraft configuration is completely defined. This sequential approach, however, limits the ability to adapt to market changes, technological advancements or unexpected disruptions, causing a drastic increase of cost. Integrating production decisions in the early design phase is therefore crucial for overcoming these limitations and making informed decisions that optimize the product for manufacturability and supply chain efficiency rather than only aircraft performance. In this frame, this paper proposes and applies a methodology combining the Model-Based Product Line Engineering with a value-driven trade-off analysis for the aircraft and industrial systems, mainly manufacturing and supply chain systems, co-architecting. With this approach, a value-driven tradespace of (co)architectures or variants representing at the same time an aircraft configuration, a combination of materials and manufacturing processes and a supply chain is generated. Therefore, decisions related to design and production can be addressed at the same time while trading stakeholders’ expectations for the identification of the best (co)architecture. An aeronautical application case shows the advantages of using the proposed approach. | ||||
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| 08:55 | 09:20 | 14.4.1 |
DISCRIMINATORY AUTONOMY: OPERATING FASTER, SMARTER, AND WITH PURPOSE J. Garth, Australia DISCRIMINATORY AUTONOMY: OPERATING FASTER, SMARTER, AND WITH PURPOSE | ||||
| 09:20 | 09:45 | 14.4.2 |
CFD/MBD-COUPLED FLIGHT SIMULATION OF FOLDING MORPHING UAV Y.-K. Bu¹, L. Qiao¹, L. Li, Chang'an University, China; H.-J. Feng¹, J.-Q. Bai¹; ¹Northwestern Polytechnical University, China Presenter: Yikai Bu, Northwestern Polytechnical University A high-fidelity CFD/MBD two-way coupled framework is developed to simulate the airdrop deployment of a folding UAV. Simulations show that unsteady asymmetric aerodynamic loads induce roll-yaw motion and asymmetric wing deployment, while geometric asymmetry stabilizes roll. Agreement with LG2K tests validates the framework for accurate deployment analysis and separation safety assessment. | ||||
| 09:45 | 10:10 | 14.4.3 |
SIMULATION MODEL CALIBRATION USING SYSTEM IDENTIFICATION FOR A VECTORED-THRUST MULTI-TILT-ROTOR CONFIGURATION B. Kunwar, Auburn University, United States This paper presents a simulation model development and calibration approach for a novel subscale aircraft configuration. A component-based aero-propulsive performance model, an actuator model, and experimental mass properties are incorporated into the MADCASP framework. The initial simulation model is then calibrated using data from system identification flight tests. | ||||
| 10:10 | 10:35 | 14.4.4 |
A WORKFLOW FOR RAPID DESIGN, SIMULATION, FABRICATION, AND SUBSCALE FLIGHT-TESTING OF NOVEL AIRCRAFT CONCEPTS I Chakraborty, Auburn University, United States This paper describes a workflow for rapid prototyping, simulation, and subscale flight-testing aimed at risk reduction of novel vertical takeoff and landing configurations that transition between vertical and forward modes of flight. The workflow is demonstrated using the example of a multi-tiltrotor configuration, the VT-03-s Shadow. | ||||
| Reserve Paper | 14.4.R |
CASCADE ADRC FOR TRAJECTORY TRACKING OF A FLYING-WING SOLAR AIRCRAFT UNDER WIND DISTURBANCES S.Q. Song, Northwestern Polytechnical University, China | |||||
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| 08:55 | 09:20 | 15.4.1 |
FACTORS AFFECTING COMMUNICATION IN AVIATION D Estival, UNSW, Australia Communication is crucial for aviation safety. Investigating factors that affect aviation communication (native language, speech rate, information density and workload) the research 1) validates the adage Aviate, Navigate, Communicate in flight training, 2) proposes that native English speakers should modify their speech patterns in international contexts and 3) highlight the need for effective fatigue management to mitigate risks of miscommunication. | ||||
| 09:20 | 09:45 | 15.4.2 |
EVALUATION OF THE USE OF THE EYE TRACKER IN AERONAUTICAL PRODUCT DEVELOPMENT AS A HUMAN FACTORS METHOD G. Cicelini, Brazil This study validates gaze entropy as an objective workload marker, aligning with NASA-TLX. It offers a scientific basis for optimizing HMI in high-risk environments by identifying cognitive bottlenecks. These metrics provide cross-industry relevance for any safety-critical system. Tested via flight simulation, it advances automated deck design through precise, real-time human factors assessment. | ||||
| 09:45 | 10:10 | 15.4.3 |
INVESTIGATING PILOT COMMUNICATION BEHAVIOURS DURING TAXI OPERATIONS UNDER DEGRADED COMMUNICATION CONDITIONS Y Yan, Australia This study investigates how degraded radio communication affects pilot communication accuracy and clarification behaviour during taxi operations. Using simulated taxi scenarios, it identifies key error types and individual differences influencing in-taxi communication. Findings highlight human factors risks contributing to runway incursions and inform communication training and system design improvements. | ||||
| 10:10 | 10:35 | 15.4.4 |
SUBSCALE FLIGHT TRAINING EFFECTS ON PILOT WORKLOAD AND PERFORMANCE DURING VTOL HQTES A.M. Comer, Oklahoma State University, United States This study quantifies how adding subscale flight-test exposure changes simulator training outcomes for fly-by-wire VTOL tasks. Using Froude-scaled HQTE courses with matched FPV view, we compare sim-only vs sim+subscale training pipelines. Results will inform how subscale training can complement simulation for future VTOL operations and pilot training standards and digital-twin-based training. | ||||
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| 11:00 | 11:25 | 1.5.1 |
ECONOMIC, ENVIRONMENTALLY SUSTAINABLE AVIATION ENERGY J.I. Hileman, Boeing, United States Drop-in sustainable aviation fuels are preferred for aviation decarbonization as they work with today’s fleet. However, that does not mean they are the most cost-effective means of decarbonizing aviation. This presentation provides an overview of ongoing Boeing efforts to examine potential aviation energy carriers under a variety of future scenarios. | ||||
| 11:25 | 11:50 | 1.5.2 |
NASA RESEARCH FOR AIRLINERS OF 2050 AND BEYOND N.K. Madavan, NASA/ARMD, United States This presentation provides an overview of NASA’s research efforts aimed at developing systems and technologies for airliners envisioned for 2050 and beyond. A significant challenge during this period is the uncertain but changing aviation energy landscape in which these future airliners will operate. The presentation will highlight in-house research, sponsored projects, and collaborative partnerships. | ||||
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| 11:00 | 11:25 | 2.5.1 |
AI-ASSISTED DESIGN OF HOLISTICALLY SUSTAINABLE AEROSTRUCTURES A. Filippatos, University of Patras, Greece We present an AI-assisted framework for the early-stage design of sustainable aircraft structural components. Machine-learning models trained on finite-element data predict geometry–material configurations that balance structural performance with environmental impact, cost, and circularity. The approach enables rapid exploration of design spaces and supports sustainability-driven decision-making. | ||||
| 11:25 | 11:50 | 2.5.2 |
CHALLENGES AND BREAKTHROUGHS IN AIR TRANSPORT SYSTEM: VISION FROM EUROPE G. Alonso-Rodrigo, Universidad Politecnica de Madrid, Spain European air transport system faces the challenge of sustaining growth while achieving climate neutrality by 2050. Our contribution reviews key technological, operational, industrial, and regulatory drivers shaping the transition, including Clean Aviation, SAF deployment, SESAR-driven ATM modernization, and market-based measures, highlighting major breakthroughs and remaining challenges in Europe. | ||||
| 11:50 | 12:15 | 2.5.3 |
CURRENT AND ALTERNATIVE PROPULSION SYSTEMS IN EUROPE; TECHNOLOGIES AND THEIR INTEGRATION O. Isaksson, Chalmers University of Technology, Sweden This paper reviews current and emerging alternative aircraft propulsion systems being researched and developed in Europe, including hybrid-electric, hydrogen, fuel cell and battery concepts. Propulsion efficiency, capacity, and maturity are discussed, highlighting integration, qualification, sustainability compliance, and the need for strong industry–academia collaboration | ||||
| 12:15 | 12:40 | 2.5.4 |
OVERVIEW OF CRITICAL ISSUES AND OPPORTUNITIES FOR NEW A/C WITH HYBRID AND FULL-ELECTRIC POWERTRAIN F. Nicolosi, University of Naples Federico II, Italy This work highlights critical issues for the design of hybrid and full electric aircraft with green innovative powertrain including batteries or fuel cell and hydrogen. These new powertrain configurations, especially with achievable technological level for EIS 2040, could enable drastic and massive impact in emission reduction. The article will highlight most relevant critical issues and their impact in the design of the aircraft. | ||||
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| 11:00 | 11:25 | 3.5.1 |
A HYBRID 0D–2D WHOLE-ENGINE MATCHING FRAMEWORK FOR TURBOJET ENGINE PERFORMANCE SIMULATION Q.-H.-T.-X. Hoang Thi Xuan, Viettel Aerospace Institute, Vietnam Accurate whole-engine matching is essential for reliable performance prediction of turbojet engines at the early design stage. This paper presents a hybrid 0D-2D whole-engine matching framework that balances computational efficiency and physical fidelity. Two-dimensional through-flow models are employed for the compressor and turbine, while the inlet, combustor, and nozzle are represented using simplified zero-dimensional performance models. To robustly determine the matched operating point, a hybrid global-local optimization strategy is adopted, combining Monte Carlo sampling for global exploration with the Nelder-Mead algorithm for local refinement. The proposed method is validated against experimental data under both static and flight conditions. The results demonstrate good agreement across key performance parameters, with differences remaining within 5%. These findings indicate that the proposed framework provides an effective and reliable tool for preliminary turbojet engine performance analysis and early-stage design applications. | ||||
| 11:25 | 11:50 | 3.5.2 |
TOWARDS AN ONTOLOGY-BASED APPROACH FOR DISCIPLINE-SPECIFIC ENGINEERING VIEWS IN ENGINE DESIGN K. Becker, German Aerospace Center (DLR), Germany The increasing complexity of engine development requires effective collaboration across engineering disciplines. This paper presents an ontology-based approach for connecting heterogeneous engineering models and providing hierarchical, discipline-specific views for the different engineers. This shall enable consistent cross-domain reasoning and improved collaboration in multi-disciplinary design. | ||||
| 11:50 | 12:15 | 3.5.3 |
MIXED-FIDELITY, NONLINEAR AIRCRAFT MISSION MODELING FOR HYBRID REGIONAL AIRCRAFT DESIGN VERIFICATION Agostino: A. De Marco, University of Naples Federico II, Italy A mixed-fidelity, nonlinear flight dynamic model of a hybrid regional aircraft is presented in this work. The model is designed to be integrated as a Functional Mock-up Interface into the Open Digital Platform of the European project ODE4HERA. The goal is to develop a pilot behavioral model in a typical flight mission. This research provides a general tool for simulation-based design workflows. | ||||
| 12:15 | 12:40 | 3.5.4 |
EFFECT OF ENGINE RESPONSE TIME IN AIRCRAFT CONCEPTUAL DESIGN A.P.S. Inderawan, Delft University of Technology, Netherlands Engine response time is not something typically considered early in aircraft conceptual design. In this study, by incorporating engine response time, we propose a method of constructing a go-around constraint curve that also addresses the decision height as the operational limit. This method ensures that safety of operation of aircraft with novel engine options are considered from the early stage. | ||||
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| 11:00 | 11:25 | 4.5.1 |
INTEGRATION OF A SOLID OXIDE FUEL CELL PROPULSION SYSTEM: A TECHNOLOGY DEVELOPMENT GOAL FOR REGIONAL AIRCRAFT N. Schneiders, German Aerospace Center (DLR), Germany This study derives a development goal for SOFC concerning its power density. Therefore, the integration of a SOFC propulsion system into a regional aircraft in the category of 50 passengers is investigated on overall aircraft level. | ||||
| 11:25 | 11:50 | 4.5.2 |
HYBRID-ELECTRIC AND HYDROGEN-FUEL-CELL PROPULSION AS ALTERNATIVES TO KEROSENE FOR REGIONAL AIRCRAFT F. Nicolosi, UNIVERSITY OF NAPLES , Italy This work compares full-electric and hybrid-electric hydrogen fuel cell propulsion with conventional kerosene turboprops for regional aircraft in a 2040 entry-into-service timeframe. Using a conceptual design framework, multiple payload are analyzed to assess mission energy demand and emissions, identifying how payload and architecture influence the competitiveness of hydrogen-based solutions. | ||||
| 11:50 | 12:15 | 4.5.3 |
EXPLORATION OF ALTERNATIVE PROPULSION ARCHITECTURES FOR BUSINESS AVIATION M. Bouchard, Createk Innovation Group, Canada This paper summarizes the key findings of the CRIAQ project EAP, a four-year university-industry collaboration that investigated the feasibility of alternative propulsion concepts for business aviation. Operational requirements derived from flight data are presented, followed by the feasibility studies of three architectures, based on a multidisciplinary design analysis and optimization approach. | ||||
| 12:15 | 12:40 | 4.5.4 |
AERODYNAMIC EFFECTS OF DISTRIBUTED PROPULSION WING CONFIGURATION PARAMETERS K. W. Wang, Northwestern Polytechnical University, China This study investigates the aerodynamic characteristics of an innovative distributed propulsion wing (DPW), a configuration that fully integrates ducted fans within the wing structure. From dual perspectives—considering the DPW as a wing and as a propulsion system—the effects of varying the number of propulsors at constant total thrust are analyzed using the momentum source method (MSM) for computational efficiency. The results clarifies the dual aerodynamic role of the DPW configuration and offer valuable theoretical insights for the conceptual design of future distributed electric propulsion (DEP) aircraft. | ||||
| Reserve Paper | 4.5.R |
PROPULSION SYSTEM MODELING AND OPTIMIZATION FOR CONCEPTUAL DESIGN OF HYBRID-ELECTRIC VTOL AIRCRAFT D. E. Lampl, Technical University of Munich, Germany | |||||
| Reserve Paper | 4.5.R |
PRELIMINARY SIZING METHODOLOGY FOR HYBRID-ELECTRIC PROPULSION SYSTEM IN CARGO AIRSHIPS S. Trivedi, Indian Institute Technology Bombay, Mumbai, India, India | |||||
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| 11:00 | 11:25 | 5.5.1 |
NUMERICAL REBUILDING OF AERODYNAMIC WIND TUNNEL ANALYSES OF A CREW RETURN VEHICLE N. Montella, CIRA (Centro Italiano Ricerche Aerospaziali), Italy This work presents a numerical rebuilding of low-speed wind tunnel analyses of a Crew Return Vehicle based on unconventional blended wing body aeroshapes. Experimental and CFD results are compared for longitudinal and lateral–directional aerodynamic coefficients to evaluate subsonic behavior, landing suitability, and the reliability of an automated open-source CFD pipeline for design assessment. | ||||
| 11:25 | 11:50 | 5.5.2 |
NUMERICAL BOUNDARY LAYER VALIDATION TECHNIQUE USING RAE M2155 SWEPT WING M.H. Mohsin, Cranfield University, United Kingdom A validation study on the RAE M2155 swept wing compares numerical results with experimental boundary layer data. Free air and wind tunnel modelling approaches are assessed, revealing better accuracy with tunnel geometry included in the simulation. Additionally, Tecplot® macro boundary layer extraction was modified to include integral calculation for supporting future flow control designs. | ||||
| 11:50 | 12:15 | 5.5.3 |
SIMULATION OF FIFTH-GENERATION HIGH-PERFORMANCE AIRCRAFT USING VISCOUS SURFACE-VORTICITY PANEL METHOD S Shahjahan, 1Siemens Digital Industries Software Inc., United States This study shows that a mid-fidelity viscous surface-vorticity panel method can accurately predict the aerodynamic performance of a fifth-generation aircraft with very low computational cost. The results support faster, reliable design trade studies and benchmarking, with relevance to aerospace design workflows where rapid iteration is critical. | ||||
| 12:15 | 12:40 | 5.5.4 |
EXERGY-BASED AERODYNAMIC CHARACTERISTICS ANALYSIS OF THE NASA COMMON RESEARCH MODEL AND BWB CONFIGURATION CIVIL AIRCRAFT H.C. Yang, Northwestern Polytechnical University, China The exergy?based method is applied to analyze both the CRM and BWB configurations, ensuring the accuracy of the exergy analysis. Through quantitative examination of exergy outflows and anergy generation, the origins of different drag components and their physical conversion mechanisms are clarified. | ||||
| Reserve Paper | 5.5.R |
INFLUENCE OF ADDITIVE MANUFACTURING ON IMPROVING THE TRADITIONAL MICRO JET COMBUSTOR PERFORMANCE M Muddada, Powertech, EDGE Group, United Arab Emirates | |||||
| Reserve Paper | 5.5.R |
INVESTIGATING A STABLE LIFTING FUSELAGE FOR A TWO SEAT SAILPLANE OF THE GULL WING CONFIGURATION B Huyssen, University of Pretoria, South Africa | |||||
| additional information (interactive) | 5.5.R |
EFFECTS OF FLYING WING CONFIGURATION PARAMETERS ON AERODYNAMICS AND STABILITY G.-Y. Gao, Northwestern Polytechnical University, China | |||||
| additional information (interactive) | 5.5.R |
STUDY ON THE INJECTOR JETTING CHARACTERISTICS FOR VENTILATION EFFICIENCY OPTIMIZATION IN AIRCRAFT ENGINE LUBRICATION SYSTEMS? X.-T XIE, Northwestern Polytechnical University, China | |||||
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| 11:00 | 11:25 | 6.5.1 |
EVALUATING THE LAMINAR FLOW ON A SLOTTED, NATURAL-LAMINAR-FLOW WING IN THE NASA AMES 11-FOOT TRANSONIC WIND TUNNEL J. G. Coder, Penn State University, United States In this article, we describe how laminar flow was evaluated over the fore-element of a Slotted, Natural-Laminar-Flow (SNLF) wing at the full-scale conditions in the NASA Ames 11-ft transonic test section. | ||||
| 11:25 | 11:50 | 6.5.2 |
EXPERIMENTAL INVESTIGATION OF BOUNDARY LAYER CONTROLLED CAVITY FLOW FOR PIEZOELECTRIC ENERGY HARVESTING APPLICATIONS M Kirkness, The University of Sydney, Australia This work introduces a boundary layer controlled experimental configuration for cavity driven piezoelectric energy harvesting. Representative results show consistency with previous measurements, improving confidence in experimental repeatability. The approach is relevant to aerospace and defence applications, supporting future development of low power structural health monitoring and autonomous sensing systems. | ||||
| 11:50 | 12:15 | 6.5.3 |
REYNOLDS NUMBER SCALING EFFECTS IN TRANSONIC CAVITY AERODYNAMIS: A HIGH-FIDELITY EXPERIMENTAL AND NUMERICAL FRAMEWORK A. Goerttler¹, S. Koch¹, M. Werner¹, F. Tocci¹, F. Mayer, Airbus Defence and Space GmbH, Germany; A. Wagner¹; ¹German Aerospace Center (DLR), Germany This study quantifies Reynolds number scaling in transonic cavity flows. Using cryogenic testing and CFD, it decouples viscous and compressibility effects to bridge the gap between wind tunnel data and flight conditions. Findings refine semi-empirical models and validate solvers, enabling reliable virtual flight testing in aircraft design. | ||||
| 12:15 | 12:40 | 6.5.4 |
INTERMITTENT LOW FREQUENCY EXPERIMENTAL CAVITY DYNAMICS J. McCarthy, Defence Science and Technology Group, Australia Low frequency and intermittent cavity dynamics are found to generate significant temporal variation of the pressure RMS and subsequently the loads exerted on flight vehicles. Wavelet analysis performed on long duration transonic wind tunnel test data shows bands and structures at very low frequencies which can match or exceed Rossiter tone amplitudes. | ||||
| additional information (interactive) | 6.5.R |
EFFECTS OF SLOT LOCATION ON FLOW AND HEAT TRANSFER IN A LATTICEWORK COOLING CHANNEL: AN MRV EXPERIMENT AND NUMERICAL STUDY Y. Jia, Xian Jiaotong University, China | |||||
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| 11:00 | 11:25 | 7.5.1 |
AERODYNAMIC TRANSONIC DESIGN OF A STRUT-BRACED WING D Losada Costoso¹, O Atinault¹, M Meheut¹, G Starck¹, E Stragiotti¹, E Nguyen Van¹; ¹ONERA, France This paper focuses on the aerodynamic design of a strut-braced wing aircraft. Following a multidisciplinary Overall Aircraft Design (OAD), a refined aerodynamic phase addresses wing–strut interactions, junction design, and transonic airfoils. An adjoint-based aerodynamic shape optimization is then performed on the resulting configuration. | ||||
| 11:25 | 11:50 | 7.5.2 |
SPARSE POLYNOMIAL CHAOS-BASED ROBUST OPTIMIZATION DESIGN OF AERODYNAMIC AND SONIC BOOM S. Wang, Northwestern Polytechnical University, China This work presents a sparse polynomial chaos based framework for robust aerodynamic and sonic boom optimization design under multi-source uncertainty. The method enables uncertainty quantification and robust optimization design with limited samples, reducing computational cost while enhancing the robustness of aerodynamic and sonic boom designs under uncertain flight and atmospheric conditions. | ||||
| 11:50 | 12:15 | 7.5.3 |
SUPERSONIC GROUND EFFECT AERODYNAMICS OF A SLENDER BODY Y. Xun, Beihang University, China This study investigates the supersonic ground effect aerodynamics of a slender body, focusing on the interaction between reflected shock waves and the body. Preliminary numerical results show that decreasing flight height significantly alters aerodynamic coefficients, with shock waves impacting the lower surface and diffracting onto the upper surface, changing pressure distribution. | ||||
| 12:15 | 12:40 | 7.5.4 |
FLOW SOLUTIONS AROUND VON KARMAN NOSES AT SUPERSONIC SPEEDS USING PHYSICS INFORMED NEURAL NETWORKS AND PRESSURE-SENSITIVE PAINT MAE Escudero, Cranfield University, United Kingdom To the best of the authors knowledge, this is the first work to couple pressure-sensitive paint measurements with physics informed neural networks for full supersonic flow field predictions. It demonstrates improved pressure fidelity while retaining physics consistency. The approach is relevant to aerospace, and high speed vehicle design, enabling faster validation and data driven optimization. | ||||
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| 11:00 | 11:25 | 8.5.1 |
FEASIBILITY OF ELECTROPULSING-INDUCED FATIGUE CRACK CLOSURE IN AEROSPACE METALLIC MATERIALS H. Park, Korea Institute of Materials Science, South Korea This study demonstrates the feasibility of electropulsing-induced fatigue crack closure in aerospace metallic materials. By combining multiphysics simulations and experiments, key process parameters governing crack closure were identified. The results suggest electropulsing as a promising, non-destructive crack management approach applicable to aerospace structures and other safety-critical metallic components. | ||||
| 11:25 | 11:50 | 8.5.2 |
LABORATORY METHOD FOR REPLICATING FASTENER HOLE CORROSION IN AA 7085 NB Tugwell, Defence Science and Technology Group, Australia Fastener holes are corrosion-prone, particularly with increasing use of AA 7085, which is susceptible to intergranular corrosion (IGC), which is difficult to detect and mitigate. This study identifies laboratory conditions that reliably induce representative IGC while limiting pitting, enabling realistic fatigue, SCC, and corrosion mitigation testing to support structural integrity management. | ||||
| 11:50 | 12:15 | 8.5.3 |
NEW INSIGHTS INTO AA7085 ENVIRONMENTALLY ASSISTED CRACKING THROUGH HIGH RESOLUTION FRACTOGRAPHY I.C.W. Field, DSTG, Australia Environmentally assisted cracking (EAC) in the new generation aluminium alloy 7085 has recently become a critical area of research in aircraft sustainment due to its inclusion in modern aircraft structures and the recent formalisation of its EAC susceptibility by EASA. This work provides a detailed analysis of coupon and fleet EAC cracks, focusing on key features that reveal how they grow. | ||||
| 12:15 | 12:40 | 8.5.4 |
INCREMENTAL LEARNING-DRIVEN XGBOOST MODEL FOR FATIGUE LIFE PREDICTION OF AA7050-T7451 ALUMINUM ALLOY UNDER LIMITED EXPER X.-C. Chen, China Fatigue failure stands as a primary failure mode of engineering components in service, and accurate fatigue life prediction is crucial for ensuring structural safety. Traditional experiment-based fatigue life prediction methods suffer from limitations such as heavy reliance on extensive datasets, long testing cycles, and high costs. Existing data-driven machine learning models often face significant accuracy degradation when applied to new material systems or loading environments due to poor generalization and domain adaptability. Effectively transferring knowledge from existing fatigue data spaces to novel data domains has thus become a critical challenge in this field. To address this issue, this study proposes an incremental learning-based fatigue life prediction method for aluminum alloys. First, a basic data-driven model was established using 1958 pieces of literature data on aeronautical aluminum alloys, covering 24 input features including material information, chemical cssposition, mechanical properties, and loading conditions. The XGBoost algorithm was adopted for model training, combined with SHAP analysis for feature dimensionality reduction to optimize predictive performance. Subsequently, constant amplitude tension-tension fatigue tests were conducted on AA7050-T7451 aluminum alloy using an INSTRON8801 testing machine, yielding 51 experimental samples. Three incremental learning strategies—experience replay, regularization, and structural optimization—were employed to fine-tune the pre-trained model with limited experimental data, aiming to balance prediction accuracy on new tasks and forgetting rate on old tasks. The results demonstrate that the original XGBoost model achieves an R² of only 0.04 when predicting AA7050-T7451 experimental data, indicating poor generalization. After fine-tuning with incremental learning strategies, the model’s R² for AA7050-T7451 fatigue life prediction exceeds 0.80, with most predictions falling within the triple error b | ||||
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| 11:00 | 11:25 | 9.5.1 |
INTERNAL I-DVA FOR 6U CUBESAT LAUNCH RANDOM VIBRATION MITIGATION K.-A. Kassa, King Fahd University of Petroleum and Minerals, Saudi Arabia CubeSats experience severe broadband random vibration during launch, leading to resonance and acceleration amplification that threaten structural integrity and deployment reliability. This study investigates an internal, mass-efficient inerter-based dynamic vibration absorber for a 6U CubeSat. Analytical and finite-element models show up to 13% reduction in peak acceleration PSD when tuned to the primary structural resonance. | ||||
| 11:25 | 11:50 | 9.5.2 |
VALIDATION OF A LOW-COST DATA COLLECTION SYSTEM FOR AIRCRAFT VIBRATION TESTING G Dessena, Universidad Carlos III de Madrid, Spain An affordable, modular data acquisition system for aircraft vibration testing is validated through ambient, taxi, and impact hammer experiments. Benchmarking against industry-standard equipment shows expected agreement between spectral peaks, supporting reliable modal identification and demonstrating applicability to aerospace research, prototyping, and other vibration-sensitive industries. | ||||
| 11:50 | 12:15 | 9.5.3 |
IMPACT RESISTANCE ENHANCEMENT IN FIBER-REINFORCED COMPOSITES USING CARBON/BASALT HYBRIDIZATION APPROACHES A.H. Baluch¹, Z. Sajid¹, T. Rehman¹; ¹King Fahd University of Petroleum & Minerals, Saudi Arabia Presenter: Abrar Ul Haq Khan Baluch, King Fahd University of Petroleum & Minerals Low-velocity impact (LVI) is a serious problem for aerospace composite structures. It can produce barely visible damage that reduces the structural integrity. This study experimentally investigates the low-velocity impact behavior of hybrid fiber-reinforced composites. Four different stacking configurations were prepared to evaluate the effect of fiber hybridization and layer sequencing on impact behavior. These hybrids are designed to overcome the impact limitations of traditional carbon fiber composites. The configurations included pure carbon (CCCC), pure basalt (BBBB), and two hybrid layups (CBBC and BCCB), where carbon (C) and basalt (B) plies were arranged in varying surface and core positions. Impact tests were carried out to measure force-time response, energy absorption, and damage patterns under low-velocity impact conditions. According to the impact test results, hybrid laminates outperformed monolithic composites in regard to impact performance. The order of peak forces for each configuration can be described as: CCCC > CBBC > BCCB > BBBB. Configurations with carbon fibers on their outer surfaces experienced greater force than configurations that used basalt fibers on their outer surfaces. Basalt-faced laminates absorbed more energy than carbon-faced laminates. BCCB was the configuration that absorbed the greatest amount of energy, supporting the conclusion that the combination of basalt and carbon fibers is an effective method for dissipating impact energies. The results of this study indicate that the use of strategic fiber combinations and stacking sequences provides a means for improving the impact resistance and damage tolerance of composite based aerospace structures. | ||||
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| 11:00 | 11:25 | 10.5.1 |
A MPC STRATEGY FOR THE ENERGY MANAGEMENT OF HYBRID ELECTRIC PROPULSION SYSTEMS IN FIXED-WING UAVS A. Suti¹, M. Budinger¹, G. Di Rito, Università di Pisa, Italy; A. Reysset¹, I. Hazyuk¹; ¹INSA Toulouse, France This paper proposes a model predictive control based energy management strategy for retrofitting conventional internal combustion engine based propulsion systems with hybrid electric ones in fixed-wing UAVs. The proposed strategy, assessed through an experimentally validated simulator, shows improved performance in terms of fuel savings and battery state-of-charge variation over flight missions. | ||||
| 11:25 | 11:50 | 10.5.2 |
POWER-HIL TESTING OF LI-PO BATTERY PACKS FOR LIGHTWEIGHT EVTOL UAVS A. Suti¹, M. Budinger¹, G. Di Rito, Università di Pisa, Italy; A. Reysset¹, I. Hazyuk¹; ¹INSA Toulouse, France This paper proposes a Power-HIL testing framework for battery packs and the BMS of lightweight eVTOL UAVs. The setup, including real-time simulated flight dynamics, enables monitoring of the real battery over successive missions and validation of the BMS across all states in a controlled environment. This approach supports faster development and safer testing for electric powered vehicles. | ||||
| 11:50 | 12:15 | 10.5.3 |
TOWARDS A DATABASE OF MICRO-ELECTRIC MOTORS AND ELECTRONIC SPEED CONTROLLERS FOR SMALL UNCREWED AERIAL SYSTEMS B.P. van Magill, The University of Sydney, Australia Measured performance for small electric motors is extremely scarce. This paper presents an air-braked dynamometer to characterise motors and speed controllers for small uncrewed aerial systems. Aerodynamic braking enables stable measurement at extremely low torque and high rotation speeds. This work establishes a foundation for future validation of analytical motor modelling techniques. | ||||
| 12:15 | 12:40 | 10.5.4 |
IN-FLIGHT LOW-COST THRUST MEASUREMENT SYSTEM FOR SMALL UNMANNED AERIAL VEHICLES C. Rieger, Technical University of Munich - Chair of Aircraft Design, Germany To determine the drag of small UAV in flight, it is necessary to know the applied propeller thrust. The design, implementation, and validation of a low-cost and compact onboard thrust sensor is described. By directly measuring thrust in-flight, this sensor addresses inaccuracies in currently used thrust estimation methods that do not account for manufacturing variances or airflow conditions. | ||||
| Reserve Paper | 10.5.R |
HIGH-FIDELITY NUMERICAL INVESTIGATION OF ROTOR-WING INTERACTIONS IN A MULTI-ROTOR DISTRIBUTED ELECTRIC PROPULSION CONFIGURATION H A Abid, Queen Mary, University of London, United Kingdom | |||||
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| 11:00 | 11:25 | 11.5.1 |
PREFERENCE INCORPORATION INTO GENERALIZED MULTI-OBJECTIVE ISLAND MODEL FOR FLIGHT CONTROL SYSTEM CLEARANCES P. Piprek, Airbus Defence and Space GmbH, Germany This paper presents the preference incorporation in an optimization-based clearance toolchain. The preference incorporation is used to gradually push the island-model-based optimization algorithm to preferred domains in the solution space having the most practical relevance. The applicability in a fighter aircraft clearance is discussed. | ||||
| 11:25 | 11:50 | 11.5.2 |
ANALYSIS OF HOVER CONTROL CAPABILITY DEGRADATION OF EVTOL AIRCRAFT UNDER PITCH ACTUATOR JAMMING C. Wu, Northwestern Polytechnical University, China This work reveals that pitch actuator jamming in eVTOL aircraft can cause directional loss of hover control even when trim remains feasible. The results highlight limitations of scalar controllability metrics and provide practical insights for safer propulsion system design and airworthiness assessment. | ||||
| 11:50 | 12:15 | 11.5.3 |
FLIGHT DYNAMICS AND GUIDANCE CONTROL FOR AERCRAFT IN TYPHOON ENVIRONMENT FOR DELIVERLY OF TYPHOON CONTROL SUBSTANCE T. Sakurai, Yokohama National University, Japan To mitigate severe disasters via typhoon control, the typhoon environment is established and simulated the aircraft guidance and control for delivering typhoon control substance. The spatial wind gradients were found to play dominant role in instability of the flight rather than wind velocity. The results show reactive systems are insufficient; navigation needs gradient-sensitive route planning. | ||||
| 12:15 | 12:40 | 11.5.4 |
SYNCHRONIZATION CONTROL OF AEROSPACE ELECTROMECHANICAL ACTUATORS BASED ON MECHANISM-DATA FUSION MODELING Y.T.-Q. Yang, School of Mechanical Engineering and Automation, Beihang Univers, China This study proposes a mechanism-data fusion model to enhance synchronization control for dual electromechanical actuators (EMAs). A high-fidelity mechanism model is combined with a Long Short-Term Memory network, and a deep learning-based disturbance observer is designed for feedforward compensation. This approach aims to significantly improve synchronization tracking accuracy and robustness. | ||||
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| 11:00 | 11:25 | 12.5.1 |
A MULTIDIMENSIONAL FRAMEWORK FOR DEMONSTRATION AND V&V CAPABILITIES FOR NEXT-GENERATION FLIGHT CONTROL SYSTEMS O. Bertram, DLR e.V., Germany Early system-level integration, validation and qualification-oriented testing are essential for next-generation flight control systems. This paper presents modular and hybrid demonstration capabilities combining system demonstrators, avionics, real-time simulation and qualification-oriented test facilities to reduce integration risks and support technology maturation of innovative flight control technologies. | ||||
| 11:25 | 11:50 | 12.5.2 |
EXPERIMENTAL VALIDATION OF A FUEL CELL SYSTEM DIGITAL TWIN FOR A FULL-ELECTRIC AIRCRAFT POWERTRAIN A. Testera¹, G. Ferrara¹, F. Di Fede¹, S. Caggese¹, V. Barba¹, G. Accardo¹, R. Pennino¹; ¹Leonardo SpA, Italy This work presents a full-scale experimental rig and its high-fidelity Digital Twin for a hydrogen fuel cell based electric aircraft propulsion system. Using an MBSE V-Model framework and Simcenter Amesim, physics-based digital models are calibrated with mission-profile tests, enabling predictive analysis, advanced control development, and real-time monitoring of full-electric propulsion systems. | ||||
| 11:50 | 12:15 | 12.5.3 |
HARDWARE-IN-THE-LOOP VERIFICATION OF A SAFETY-CRITICAL MULTILEVEL BATTERY MANAGEMENT SYSTEM FOR AN ELECTRIC AIRCRAFT P Panchal, University of the Bundeswehr Munich, Germany This work presents a system-level hardware-in-the-loop verification framework for a safety-critical multilevel battery management system using real embedded controllers and real-time battery cell, temperature, and fault emulation. The approach enables realistic in-flight fault analysis and reduces integration risk. The modular framework is applicable to electric aviation and automotive industries. | ||||
| 12:15 | 12:40 | 12.5.4 |
AN EMBEDDED PHYSICS-INFORMED NEURAL NETWORK (PINN) FRAMEWORK FOR HIGH-FIDELITY REAL-TIME SIMULATION OF A FLIGHT CONTROL SURFACE ACTUATION SYSTEM D.C. Lyu, China This study proposes a novel embedded Physics-Informed Neural Network (PINN) framework for a flight control dual-channel hydraulic servo actuator. It overcomes traditional modeling limitations by enabling real-time, high-fidelity simulation, achieving millisecond-level predictions with enhanced accuracy, thus offering a breakthrough for system design and analysis. | ||||
| Reserve Paper | 12.5.R |
NEUROMORPHIC ASCENT: REVOLUTIONISING AIRCRAFT STORES COMPATIBILITY AND AUTONOMOUS SYSTEMS M.G. Tutty, JAIME AMERICA, LLC, United States | |||||
| additional information (interactive) | 12.5.R |
POWER FLOW DYNAMICS AND COUPLING MECHANISMS IN POWER-BY-WIRE ACTUATION: A COMPREHENSIVE MODELING AND ANALYSIS APPROACH Linlin Jiang¹, Yang Li¹, Shilong Bai¹, Zhuo Li¹, Kaixiang Jia¹, Yaoxing Shang¹; ¹Beihang University, China | |||||
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| 11:00 | 11:25 | 13.5.1 |
MODEL PREDICTIVE CONTROL AND ENERGY MANAGEMENT OF AIRPORT MICROGRIDS INTEGRATING ELECTRIC AND HYDROGEN AIRCRAFT Y. Chen, University of New South Wales, Australia This study proposes a model predictive control (MPC) framework for airport microgrids integrating electric and hydrogen aircraft. The approach significantly reduces grid peaks and improves renewable utilization, contributing to sustainable aviation energy management aligned with ICAO’s CORSIA goals. The method can also inspire optimization solutions for ports, campuses, and smart transportation hubs. | ||||
| 11:25 | 11:50 | 13.5.2 |
SYSTEM OF SYSTEMS ENGINEERING ROADMAP FOR INTEGRATING SUSTAINABLE AVIATION FUEL INTO MEXICO\'S AIRPORT FUEL INFRASTRUCTURE G.-L. Gomez Falcon, UNIVERSIDAD AUTÓNOMA DE BAJA CALIFORNIA, Mexico This work demonstrates that the main barrier to Sustainable Aviation Fuel adoption in Mexico is not fuel production, but system integration across airport fuel infrastructure. By applying a system-of-systems engineering approach, the study delivers a data-driven roadmap that translates sustainability targets into operationally verifiable actions. Using real consumption data and a case study at Guadalajara International Airport, the research shows how SAF can be introduced safely and progressively without disrupting existing fuel operations. The results provide a replicable framework that reduces integration risk, supports investment decisions, and enables scalability. Beyond aviation, the proposed methodology is applicable to other sectors that must integrate low-carbon fuels into legacy infrastructure, including maritime transport, defense logistics, and space-related fuel supply chains. | ||||
| 11:50 | 12:15 | 13.5.3 |
SOFTWARE ARCHITECTURE FOR A RECONFIGURABLE BATTERY SYSTEM FOR USE IN AN ELECTRIC AIRCRAFT W. Bliemetsrieder, UniBw Munich, Germany The DO-178C and DO-331 standards offer opportunities to accelerate the development process for safety-critical software. A reconfigurable battery provides the safety required for a fully electric aircraft and represents a complex software-controlled system. This project develops such a system with adaptive output voltage and describes the methods used. Different methods are evaluated and compared. | ||||
| 12:15 | 12:40 | 13.5.4 |
IMPACT OF GNSS INTERFERENCE ON AIRCRAFT NAVIGATION SYSTEMS: OPERATIONAL RISKS, SAFETY IMPLICATIONS, AND EARLY ASSESSMENT PP Pinheiro, Universidade Beira do interior, Portugal This paper provides a detailed technical assessment of how interference affecting Global Navigation Satellite Systems (GNSS) influences navigation performance in commercial aviation. GNSS has become a core element of modern air operations, supporting lateral and vertical guidance, surveillance functions, and the synchronisation of multiple avionics subsystems. As aircraft increasingly depend on satellite-derived Position, Navigation, and Timing (PNT) information, the operational implications of signal degradation have become more pronounced. This study examines verified interference occurrences and evaluates their impact on aircraft navigation chains, with the aim of characterising the mechanisms by which disruptions propagate through typical avionics architectures. The analysis demonstrates that both intentional jamming and unintentional interference can rapidly degrade satellite signal availability and integrity, thereby affecting the performance of RNAV and RNP navigation modes. Interference events were found to alter the stability of guidance solutions, reduce the reliability of approach path tracking, and in some cases initiate automatic reversion to inertial or barometric sources. These transitions, while necessary for safety, introduce additional uncertainty into the navigation solution and may lead to increased deviations during critical terminal procedures. | ||||
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| 11:00 | 11:25 | 14.5.1 |
MODELING PROPELLER-WING INTERACTIONS FOR SUBSCALE LIFT + CRUISE VTOL UAV - Bhandari, Oklahoma State University, United States This study presents the experimental development of a reduced-order model to quantify lift-propeller and wing interaction effects on a subscale lift + cruise VTOL UAV. Results are incorporated into an integrated simulation model to predict wing and control surface effectiveness behind the propeller wake. It provides design insights for emerging VTOL aircraft employing dedicated lift propulsors. | ||||
| 11:25 | 11:50 | 14.5.2 |
RAPID FLIGHT DYNAMICS EVALUATION OF STRONGLY COUPLED DISTRIBUTED PROPULSION Y. Zhu, Northwestern Polytechnical University, China To address high-dimensional coupling in DEP UAVs, an agile evaluation methodology is proposed. A BEMT-VLM approach enables rapid, high-fidelity computation, followed by a dynamics model using analytical derivations to quantify slipstream effects. A small-perturbation modal analysis is developed to account for strong coupling. A case study reveals dynamic laws, validating the methodology. | ||||
| 11:50 | 12:15 | 14.5.3 |
ENSEMBLE MACHINE LEARNING FOR UAV PROPELLER PERFORMANCE PREDICTION WITH UNCERTAINTY QUANTIFICATION M. I. Alam, King Fahd University of Petroleum and Minerals (KFUPM), Saudi Arabia This work presents a physics-informed ML framework for UAV propeller prediction with dual Uncertainty Quantification. Achieving R²>0.92 on 30,188 samples, it offers real-time, accurate predictions with safety margins. This enables reliability-aware optimization, addressing critical safety gaps in electric UAV design. | ||||
| 12:15 | 12:40 | 14.5.4 |
STABILITY ANALYSIS OF A LIGHT UAV WITH SOLAR PROPULSION T. Goetzendorf-Grabowski, Warsaw University of Technology Institute of Aeronautics and App, Poland The paper presents the results of research on an experimental solar-powered UAV. High flight stability and generally good handling characteristics are crucial because this aircraft is designed for precise measurements. The specific design, including a flat-top profile, unparalleled in other designs, and an unusual upper mass distribution, posed additional challenge. The paper presents the results of stability analysis on various configurations. | ||||
| Reserve Paper | 14.5.R |
FLIGHT TESTING CONTROL LAWS OF A TANDEM TILT-WING EVTOL DEMONSTRATOR THROUGH TETHERED HOVER FLIGHTS D. Milz¹, L. Ott¹, M. May¹; ¹German Aerospace Center (DLR), Germany | |||||
| additional information (interactive) | 14.5.R |
COMPARISON OF TWO METHODS FOR OBTAINING LONGITUDINAL AERODYNAMIC DERIVATIVES AND THEIR DYNAMIC STABILITY ANALYSIS OF HIR G Gao, Northwestern Polytechnical University, China | |||||
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| 11:00 | 11:25 | 15.5.1 |
ACCELERATING THE LEARNING CURVE: GENERATIVE AI FOR WORKED EXAMPLES IN HUMAN FACTORS ANALYSIS A. Reisier¹, M.M. Cardoso-Junior¹; ¹Technological Institute of Aeronautics, Brazil Presenter: Moacyr Cardoso-Junior, Technological Institute of Aeronautics We present a GenAI-driven pedagogical approach using worked examples to accelerate learning of aviation safety tools (HTA, GDTA, OESD). We implemented comprehensive examples across authentic scenarios and assessed student satisfaction with 21 ITA graduate students. The study contributes empirical evidence and practical insights for integrating AI into safety-critical engineering education. | ||||
| 11:25 | 11:50 | 15.5.2 |
ASSESSING AN ALTERNATE AIRPORT ASSISTANT J. I. Gonzalez Cabeza, DLR e.V., Germany To alleviate pilots' workload, DLR designed an Electronic Flight Bag (EFB) application. It assists pilots with evaluating airport options during diversions, focusing on aspects such as distance, fuel availability, stop margin, and crosswind conditions. The objective of a simulator study was to evaluate its effectiveness and gather pilot feedback. | ||||
| 11:50 | 12:15 | 15.5.3 |
EVALUATION OF METHODS FOR ANOMALY DETECTION IN THE APPROACH PHASE OF OPERATIONAL FLIGHT DATA R. Haehnel, German Aerospace Centre (DLR), Germany This paper investigates anomaly detection methods for large-scale, unlabeled flight data from commercial aircraft, focusing on the approach phase. Multiple distance-, forecasting-, and reconstruction-based algorithms are compared using missed approaches as a surrogate benchmark. The study highlights strengths, weaknesses, and complementarities of methods beyond traditional exceedance detection. | ||||
| 12:15 | 12:40 | 15.5.4 |
PRELIMINARY SAFETY AND CERTIFICATION RISK ASSESSMENT FOR AN INNOVATIVE REGIONAL HYBRID AIRCRAFT CONFIGURATION G. B Buzzo, CIRA - Italian Aerospace Research Centre, Italy Recent technological advancements are transforming aviation practices, through hybrid-electric propulsion, which enhances fuel efficiency, reduces pollution, and noise. This Clean Aviation AMBER project focuses on developing an ultra-low-emission hybrid-electric system for regional aviation. The work includes a Preliminary Safety analysis and evaluates existing certification requirements to address risks related to innovative technologies. | ||||
| Reserve Paper | 15.5.R |
EVALUATION OF A MULTI-SENSOR OBSTACLE TRACKING SYSTEM FOR AIRCRAFT USING REAL-WORLD DATA K.D. Theuma, MCAST, Malta | |||||
| additional information (interactive) | 15.5.R |
CONTEXT-AWARE FLIGHT SAFETY EVENT DETECTION AND CLASSIFICATION USING A TWO-STAGE HYBRID MACHINE LEARNING MODEL T. Asghar, National University of Sciences and Technology (NUST), Pakistan | |||||
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| 13:40 | 14:05 | 1.6.1 |
REGIONAL ELECTRIFIED/HYDROGEN DEMONSTRATIONS PANEL G.M. Bezos-O'Connor, NASA, United States The panel is part of the Global Sustainable Aviation track and features focused discussion amongst experts who are in the midst of regional aircraft scale technology demonstrations advancing electrification and/or hydrogen powered aviation. Panelists include experts from GE Aerospace, Raytheon/Pratt & Whitney, magniX, and Harbour Air. After opening remarks, panel discussion will follow including questions from the audience. | ||||
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| 13:40 | 14:05 | 2.6.1 |
X-59: THE FIRST CHAPTER IN THE QUESST FOR QUIET COMMERICAL SUPERSONIC FLIGHT C.M Bahm, NASA, United States IInvited speaker for the Global Sustainable Aviation track. This presentation will provide an overview of NASA's Quesst Mission, the X-59 and its flight test | ||||
| 14:05 | 14:30 | 2.6.2 |
X-59: PART 2 BY C.M.BAHM AND P.G.COEN C. Bahm, United States X-59: THE FIRST CHAPTER IN THE QUESST FOR QUIET COMMERICAL SUPERSONIC FLIGHT PART 2 | ||||
| 14:30 | 14:55 | 2.6.3 |
X-59 EXTERNAL VISION SYSTEM FLIGHT TESTING R.E. Bailey, NASA, United States As part of its Quiet SuperSonic Technologies (QueSST) mission, NASA has developed the X-59 Low Boom Flight Demonstrator (LBFD) aircraft, designed specifically to create a low boom noise signature during supersonic cruise flight. The forward fuselage/nose shaping of the X-59 design is one of the critical elements of this design, but, as a result, forward-facing windows are impractical. NASA designed and delivered an eXternal Visibility System (XVS) as government-furnished equipment for installation on the Lockheed-Martin-built X-59 that, with other aircraft systems and subsystems, may ensure safe and efficient operations in all phases of flight by providing an electronic means of forward visibility . XVS technologies have been researched but the X-59 represents the first operational vehicle reliant on an electronic means of vision in all phases of flight. The X-59 XVS design goal is to create an electronic means of vision with equivalent or better levels of safety and performance to windows. This presentation and paper will discuss the design of the X-59 XVS and the findings, to date, including the operational and airworthiness performance of the X-59 XVS and the challenges of flight without forward-facing windows. | ||||
| 14:55 | 15:20 | 2.6.4 |
X-59 FLIGHT DYNAMICS AND CONTROL M.J. Boucher, NASA, United States invited speaker for the X-59 Detail Session | ||||
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| 13:40 | 14:05 | 3.6.1 |
A SINGLE-LOOP OPTIMIZATION METHOD FOR MULTIDISCIPLINARY DESIGN UNDER UNCERTAINTY B Wang, The University of Sydney, Australia This paper explores a single-loop stochastic optimization approach for multidisciplinary design optimization under uncertainty. By employing a surrogate-assisted strategy, the proposed method requires only a single model evaluation per optimization iteration, enabling efficient aerospace system design in scenarios with tight computational budgets. | ||||
| 14:05 | 14:30 | 3.6.2 |
MULTIDISCIPLINARY PHYSICS-CONSTRAINED GENERATIVE DESIGN OF DISTRIBUTED ELECTRIC PROPULSION AIRCRAFT W. Wei, Northwestern Polytechnical University, China This work proposes a multidisciplinary physics-constrained generative design framework for Distributed Electric Propulsion (DEP) aircraft, fusing CWGAN-GP with MDAO to address data scarcity, poor physical consistency, and low engineering feasibility in traditional generative design. By integrating domain knowledge, physical mechanisms, and multi-objective optimization, it enables end-to-end mapping from task requirements to reliable DEP schemes. Its conclusions validate the critical role of physics constraints and performance optimization in intelligent engineering design. Beyond aviation, this framework offers a scalable paradigm for other complex multi-disciplinary systems requiring efficient, data-limited iterative design, advancing cross-industry intelligent manufacturing. | ||||
| 14:30 | 14:55 | 3.6.3 |
A MULTI-FIDELITY ROBUST OPTIMIZATION APPROACH FOR HYPERSONIC WAVERIDERS DESIGN A. Perlini¹, G. Gori¹; ¹Politecnico di Milano, Italy Hypersonic waveriders are designed to ride their own shock wave to achieve high lift-to-drag ratios. This mechanism is highly sensitive to off-design operating conditions. This work proposes a robust design optimization framework for hypersonic waveriders that explicitly accounts for uncertainty in operating conditions. A multi-fidelity approach is adopted to reduce the cost of the analysis. | ||||
| 14:55 | 15:20 | 3.6.4 |
A MIXED-FIDELITY VISCOUS-INVISCID INTERACTION APPROACH FOR THE DESIGN OPTIMIZATION OF NOVEL AIRCRAFT CONCEPTS S.A. Bakhshi, University of Michigan, United States This work implements a coupled viscous-inviscid interaction method between a VLM and RANS to develop a medium fidelity aerodynamic analysis approach for aerodynamic design. The method is differentiated using a coupled adjoint method for use in gradient-based design optimization and MDO frameworks. We demonstrate the approach for optimizing a cruise-slotted wing. | ||||
| Reserve Paper | 3.6.R |
METHODOLOGICAL APPROACH TO MULTI-CRITERIA OPTIMISATION OF PRODUCT FAMILY ARCHITECTURES UTILISING SYSTEM MODELS F. H. Christiansen, Hamburg University of Technology, Germany | |||||
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| 13:40 | 14:05 | 4.6.1 |
ENDURANCE EVALUATION OF DIFFERENT UAV CONFIGURATIONS AND POWERTRAIN ARCHITECTURES A. Orgiu, Concordia University, Canada This paper introduces FAST-UAV, an open-source MDO framework for preliminary UAV design, extended with thermal propulsion models for fixed-wing and hybrid VTOL configurations. The framework allows to compare endurance across architectures, vehicle masses, and payloads, highlighting differences between electric and thermal propulsion to support informed preliminary design decisions. | ||||
| 14:05 | 14:30 | 4.6.2 |
DEVELOPMENT OF A 130-KG-CLASS LIFT-CRUISE VTOL UAV INCORPORATING A FUEL CELL–BATTERY HYBRID POWER SYSTEM J. Jeong, Korea Aerospace Research Institute, South Korea This paper presents a development of a 130kg-class VTOL UAV, powered by a fuelcell and battery hybrid system. The UAV is designed to carry a 15kg payload and complete a round trip to a destination 50 km away within 1 hour. For propulsion, custom-developed 6phase BLDC motors were implemented. A prototype has completed component-level performance test and a wind tunnel test, a tethered flight test. | ||||
| 14:30 | 14:55 | 4.6.3 |
COMMON RESEARCH MODELS FOR SMALL UNCREWED AERIAL VEHICLES J.-A. Rasines Mazo, The University of Sydney, Australia Few open-source and well-established research models for small uncrewed aerial vehicle exist compared to larger aircraft. Two small UAV configurations are presented as common research models, enabling low-Reynolds-number simulation tool validation. Publicly released geometry and extensive tests include mass, inertia, wind-tunnel data, as well as exemplar aerodynamic validation against FlightStream | ||||
| 14:55 | 15:20 | 4.6.4 |
DESIGN AND TESTING OF A BUOYANT UAV FOR AGRICULTURAL SURVEILLANCE P.-P. Kapoor, University of Hull, United Kingdom his work presents a buoyant UAV platform designed to overcome endurance limitations of conventional drones. By integrating a lightweight structure with a Lighter than air (LTA) gas filled envelope, the system achieves extended flight time. The prototype enables low-energy hover and is ready for precision agricultural surveillance missions | ||||
| Reserve Paper | 4.6.R |
FLIGHT OPERATIONS AND TESTING OF A 450?KG EXPERIMENTAL GYROPLANE UAV I. Pruter¹, G. Schmitz¹, H. Duda¹, M. Laubner¹, S. Lorenz¹; ¹DLR e.V., Germany Presenter: Gregor Schmitz, DLR e.V. | |||||
| Reserve Paper | 4.6.R |
AN INTEGRATED CONCEPTUAL-DESIGN FRAMEWORK FOR MULTICOPTER URBAN AIR MOBILITY VEHICLES B Mufti, National University of Science and Technology, Pakistan | |||||
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| 13:40 | 14:05 | 5.6.1 |
DATA-DRIVEN RANS CLOSURES USING AN ADAPTIVE CURVATURE-BASED CLASSIFIER FOR VORTEX FLOWS P West, Williams F1 team, United Kingdom We concentrate on identifying and building models specifically for vortex-dominated regions using an adaptive curvature parameter classifier that distinguishes vortex cores from the surrounding flow field. Within these identified regions, correction models for the Reynolds stress anisotropy tensor are developed using the Sparse Regression of Turbulent Stress Anisotropy (SpaRTA) framework. | ||||
| 14:05 | 14:30 | 5.6.2 |
DATA-DRIVEN TURBULENCE MODELING FOR MULTI-MECHANISM SEPARATED FLOWS OVER ICED AIRFOILS Z.Z. HE¹, Y.F. ZHANG¹; ¹Tsinghua University, China Accurate iced wing aerodynamic prediction is hindered by the "dual error mechanism" in RANS models, where eddy viscosity is overestimated upstream and underestimated downstream in separated shear layers. This study proposes the field inversion and physics-driven-classification modeling (FI-PDCM) framework to decouple these opposing error modes. A correction factor ? is first determined via discrete adjoint-based field inversion, followed by the formulation of an explicit algebraic model using local features. Validation on the GLC305-944 iced airfoil benchmark demonstrates that the corrected model accurately replicates the ? distribution derived from field inversion, capturing the separation bubble physics, surface pressure, and the entire lift curve through stall. Future research will focus on testing the model’s generalizability across a broader range of ice shapes to further establish its robustness and engineering utility. | ||||
| 14:30 | 14:55 | 5.6.3 |
AN EVALUATION OF NONLINEAR EDDY-VISCOSITY MODELS FOR HIGH REYNOLDS NUMBER TURBULENT FLOW SIMULATIONS T. Chagas Silva, Instituto Tecnologico de Aeronautica, Brazil The present work describes an effort to demonstrate that the use of nonlinear turbulence models in general aeronautical applications could be quite advantageous. The work addresses explicit algebraic Reynolds stress models, and demonstrates that these closures can bring additional physics to the flow simulations at very modest additional costs, thus extending the application of RANS formulations. | ||||
| 14:55 | 15:20 | 5.6.4 |
NUMERICAL INVESTIGATION OF GUST LOAD ALLEVIATION FOR ULTRA-HIGH ASPECT RATIO WINGS WITH PASSIVELY RELEASED FFWT TR Chen, NorthWestern Polytechnical University, China Addressing UHARW’s gust loads, this study uses EDH-connected FFWT for GLA via CFD-multi-body loose coupling. Key parameters (flare angle, inertia, stiffness, damping) and gust wavelengths analyzed. Prelim results: max 14.92% lift (30° flare) & 25.77% wing root bending reduction (120.0c gust) vs fixed tips. FFWT adapts, cutting local loads. | ||||
| Reserve Paper | 5.6.R |
CFD ANALYSIS OF MMRTG THERMAL PLUME ON THE EXTERNAL AERODYNAMICS OF A MARS ROVER J. Fernandez Anton, Instituto Nacional de Técnica Aeroespacial, Spain | |||||
| additional information (interactive) | 5.6.R |
MORPHING TRAILING-EDGE AERODYNAMICS AND THE ROLE OF TURBULENCE MODELLING P. Kovár, Czech Republic | |||||
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| 13:40 | 14:05 | 6.6.1 |
UNSTEADY SWIRL AND TOTAL PRESSURE DISTORTION ANALYSIS IN AN ASPIRATED SHORT INTAKE IN CROSSWIND CONDITIONS USING STEREOSCOPIC PIV DATA T. Piovesan, Cranfield University, United Kingdom This work demonstrates that short, compact intakes for next-generation high-bypass turbofan engines are highly susceptible to unsteady flow distortion under crosswind conditions, as flow separation occurs more severely than in conventional designs due to the reduced internal diffusion capability of short intakes compared to conventional configurations. By combining time-resolved stereoscopic PIV with methods for reconstructing total pressure from velocity fields, the study captures and characterizes both swirl and total pressure distortion in a scaled short intake under crosswind conditions without relying on intrusive probes. This approach has strong potential to reduce the need for conventional intrusive instrumentation while providing higher spatial and temporal resolution. The results improve understanding of the aerodynamics of short intakes under off-design conditions and support the development of more robust and efficient fan–intake systems through better-informed design and certification practices. | ||||
| 14:05 | 14:30 | 6.6.2 |
EXPERIMENTAL STUDY OF GROUND EFFECT ON A HEAVING NACA0012 AEROFOIL M. Li, University of Sydney, Australia Unsteady aerodynamics in ground effect plays an important role in a wide range of engineering systems. For a stationary aerofoil, decreasing ground clearance leads to an initial increase in the normal force, followed by a reduction due to viscous effects. In this work, we specifically focus on the effect of ground proximity on dynamic stall. An experimental investigation of a heaving NACA0012 aerofoil operating in ground effect is conducted using stereo particle image velocimetry and unsteady surface pressure measurements. Force hysteresis over an oscillation cycle is examined, and correlated with the measured velocity fields, providing insight into the interaction between vortical structures and the ground plane. | ||||
| 14:30 | 14:55 | 6.6.3 |
LOW-SPEED EXPERIMENTAL INVESTIGATION OF PODDED ENGINE INTEGRATION OF FLYING V AIRCRAFT A. Kumar, TU Delft Faculty of Aerospace Engineering, Netherlands This work focuses on over-the-wing engine integration for Flying V Aircraft, an underexplored area with the potential to reduce fuel consumption by 20% through reduced cruise drag. This research experimentally investigates the aerodynamic impact of an over-the-wing engine installation using a 4.6% scaled down Flying V wind tunnel model tested in the Open Jet Facility at TU Delft. Aerodynamic forces and inlet performance are investigated for mass flow ratios of 0.3, 0.7, and 2.1, representing windmilling, cruise, and takeoff conditions for various angles of attack. The results provide insights into the aerodynamic behavior, and inlet efficiency, which is essential for achieving decreased fuel consumption. This research is also relevant to other aerospace applications involving integrated propulsion systems, including blended-wing body (BWB) aircraft, UAVs, and future hybrid-electric aircraft concepts. By enabling more aerodynamically efficient aircraft designs, this work supports reductions in fuel burn, and emissions, contributing to sustainable aviation and broader societal climate goals. | ||||
| 14:55 | 15:20 | 6.6.4 |
WHEN ROTOR WAKE MEETS THE GROUND: INFLUENCE OF BLADE COUNT AND BLADE PITCH ON ROTOR OUTWASH - Pradyumna, The University of Sydney, Australia This study investigates rotor wake development in ground effect using Particle Image Velocimetry, focusing on the influence of blade pitch and blade count. The results provide quantitative insight into near-ground outwash and wall-jet formation, directly supporting eVTOL certification, vertiport safety assessment, and rotor design for urban operations. | ||||
| Reserve Paper | 6.6.R |
WIND TUNNEL INVESTIGATION OF HELICOPTER LOADS DURING URBAN OPERATIONS ON A BUILDING WITH COLUMNAR VORTEX GENERATORS (CVG J. C. Matias¹, R. Bardera¹, E. Barroso¹, J. Fernández¹; ¹INTA, Spain | |||||
| additional information (interactive) | 6.6.R |
INFLUENCE OF PROPELLER ON SIDE EDGE VORTICES IN A STOL UAV D.-P. Pastuszko, Poland | |||||
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| 13:40 | 14:05 | 7.6.1 |
AERODYNAMIC EFFECT OF PITCHING MOTION FOR FLAPPING AIRFOIL ACROSS DIFFERENT SWEEPING TRAJECTORIES - Liu, China The study reveals the influence and mechanism of pitching motion under different plunging-sweeping trajectories during the cruise flight of pigeon,which provides critical insights into avian flight aerodynamics and offer practical guidance for bio-inspired flapping-wing vehicle design. | ||||
| 14:05 | 14:30 | 7.6.2 |
AERODYNAMIC OPTIMISATION OF BIOINSPIRED CORRUGATED WINGS FOR HIGH-EFFICIENCY MAV GLIDING M Krasniqi, Flat 63 Nottingwood House, United Kingdom Free-flight experiments provide bio-inspired, novel, and practical design rules for low-Re MAV gliding, showing which corrugation features and wing geometries most improve efficiency. A low-amplitude, trailing-edge sinusoidal corrugation improved efficiency by 17.5% over a smooth baseline. The results support the development of more energy-efficient MAVs for long-duration monitoring applications. | ||||
| 14:30 | 14:55 | 7.6.3 |
AERO-MECHANICAL ANALYSIS OF A BIRD-INSPIRED ORNITHOPTER USING AN INTEGRATED SIMULATION FRAMEWORK H.-H. Yang, Korea Advanced Institute of Science and Technology, South Korea This paper introduces ORNISP, a validated simulation framework for bird-inspired ornithopters. It integrates a multi-flexible body dynamics solver with a modified unsteady vortex lattice method. The effects of main spar stiffness and mean dihedral angle on longitudinal dynamics and crank driving torque are investigated, providing key insights for the systematic design of the main wing. | ||||
| 14:55 | 15:20 | 7.6.4 |
THREE-DIMENSIONAL FLOW STRUCTURES OVER A LOW-ASPECT-RATIO PLUNGING WING B. Anilir, METU Aerospace Engineering Department, Turkey The objective of the current study is to numerically investigate the three-dimensional flow structures over a sinusoidally plunging low-aspect-ratio wing (sAR = 1) dominated by strong wing tip vortices and vortices shed from the leading and trailing edges. This configuration is analyzed by solving Unsteady Reynolds-averaged Navier-Stokes (URANS) equations and using the shear stress transport (SST) ? ? Re_? turbulence model to capture transition effects. The effects of Reynolds number (Re = 2.5×10^3?6×10^4) and nondimensional plunge velocity (v_p = 1.05?6.28) on the wake topology and flow stability will be analyzed. | ||||
| Reserve Paper | 7.6.R |
AERODYNAMIC PERFORMANCE ANALYSIS OF A NOVEL LIFT-THRUST INTEGRATED ROTARY FLAPPING AERIAL VEHICLE L Liu, School of Aeronautics, Northwestern Polytechnical University, China | |||||
| additional information (interactive) | 7.6.R |
STUDY ON AERODYNAMICS OF THE WING WITH FLAP INSPIRED FROM BIRD COVERTS X Xu, Northwestern Polytechnical University, China | |||||
| additional information (interactive) | 7.6.R |
INVESTIGATION ON THE HIGH-EFFICIENCY PROPULSION MECHANISMS OF DUCK-WEBBED PADDLING FOR BIOINSPIRED AIRCRAFT APPLICATION C. Cao, Northwestern Polytechnical University, China | |||||
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| 13:40 | 14:05 | 8.6.1 |
TOPOLOGY-OPTIMIZATION OF INTERCONNECTED 3D-PRINTED STRUCTURES FOR COST-EFFICIENT UAVS A.M. Comer, Oklahoma State University, United States This work presents a stress-driven topology-optimization workflow that turns printer-size PETG modules into large, flight-testable Group 1-2 UAV structures. Dovetail joints enable fast field replacement of damaged sections. Planned load tests and CT/SEM will quantify strength and porosity. The same approach can cut cost/time for robotics, marine, and space structures. | ||||
| 14:05 | 14:30 | 8.6.2 |
TRACING MATERIAL PROPERTIES TO SYSTEM-LEVEL PERFORMANCE: A NORMALISED SENSITIVITY ANALYSIS FOR A BOEING 737 CLASS AIRCRAFT S Stekovic, Linköping University, Sweden This paper presents a quantitative framework that links material properties to aircraft level performance metrics using a Normalised Sensitivity Matrix (NSM) and an Aggregated Design Impact Matrix (ADIM). The method evaluates how fractional variations in material strength, stiffness, density and temperature capability influence payload, range and climb rate for a Boeing 737–800 baseline configuration under fixed maximum take-off weight (MTOW = 79,000 kg), fuel mass (21,300 kg) and geometry constraints. The constraint conditions make sure that performance changes arise solely from material-driven effects by holding aerodynamic conditions, mission profile and structural layout constant. Payload sensitivity is computed from the mass balance equation W_pl=W_0-W_e-W_f, where operating empty weight (OEW) is 41,400 kg and nominal payload is 16,300 kg. Range sensitivity reflects changes in specific fuel consumption at constant fuel mass, while climb performance is linked to thrust capability through excess power. The NSM results reveal strong material-to-performance linkages. For payload, normalised sensitivities reach +0.67 for airframe strength and ?1.14 for airframe density, indicating that a 1% reduction in density yields a 1.14% payload increase. Engine material properties exert smaller payload effects (e.g., ?0.10 for hot-section density). Range is dominated by hot-section material improvements: +0.31 for stiffness, +0.29 for temperature capability while airframe properties show negligible influence. Climb rate exhibits the highest sensitivity to propulsion materials with +1.20 for temperature capability and +0.86 for stiffness, confirming that thermal limits and high temperature strength govern thrust potential. The ADIM aggregates these effects by material domain. Airframe materials contribute 2.12 to payload impact, compared to 0.24 for hot-section materials, whereas hot-section materials dominate range (0.75) and climb performance (2.64). Thes | ||||
| 14:30 | 14:55 | 8.6.3 |
GRADIENT-BASED STRUCTURAL OPTIMISATION OF COMPOSITE WING STRUCTURES USING HIGH-ORDER BEAM MODELS D. Cardone, Universidad Carlos III de Madrid, Spain Gradient-based optimisation of composite wings requires high-fidelity analysis, but 2D/3D FEM is prohibitive for large design spaces. We propose 1D Carrera Unified Formulation (CUF), adjoint sensitivities in reverse-mode for ply sizing. On Z-stringer panel, CUF with Taylor expansion matches 3D strains within 5% at 1-2 orders of magnitude lower cost. Scalable to DLR wing-box benchmark. | ||||
| 14:55 | 15:20 | 8.6.4 |
THE STUDY ON STIFFNESS OPTIMIZATION ANALYSIS OF CIVIL AIRCRAFT FUSELAGE DOOR OPENINGS Kaijun Yin, China In order to meet structural stiffness and load transmission, the paper studies the stiffness and strength of the opening structure of the fuselage: clarifying the factors affecting the stiffness of opening structure and optimizing opening angle and the size of the reinforcing structure. The above research provides the direction and method for the design and reinforcement of the opening structure | ||||
| Reserve Paper | 8.6.R |
SENSITIVITY ANALYSIS OF THE JOHNSON-COOK MODEL PARAMETERS FOR AL2024-T3 IN BIRD STRIKE ANALYSIS ON FIXED LEADING EDGES R. Martins Martins, Boeing, Brazil | |||||
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| 13:40 | 14:05 | 9.6.1 |
A FULL-SCALE DEMONSTRATOR FOR RAPID TESTING OF HELICOPTER AIRFRAMES USING ADVANCED CONTROL SYSTEM METHODOLOGIES G. Swanton, Defence Science and Technology Group, Australia DSTG has conducted a multi-year program to deliver a full-scale concept demonstrator for rapid testing of helicopter airframes. In order to apply a sufficient number of representative loads within a viable test schedule, a novel model-in-the-loop capability was implemented into the control system architecture to predict and optimise test performance. | ||||
| 14:05 | 14:30 | 9.6.2 |
HIGH SPEED ACTUATION SYSTEM DESIGN AND VALIDATION FOR A TRANSONIC WIND TUNNEL MODEL C.C.W. van der Post, Netherlands Aerospace Centre, Netherlands Design and experimental characterization of an actuation system for a transonic aero-servo-elastic scaled wind tunnel model. Actuator requirements are derived from closed-loop aeroelastic simulations. A compact and high speed system optimized to the model volume was designed. The actuation system is tested and validated to experimentally evaluate performance and identify dynamics models. | ||||
| 14:30 | 14:55 | 9.6.3 |
WIND TUNNEL TESTING OF WHIRL FLUTTER AEROELASTIC DEMONSTRATOR J. Cecrdle¹, O. Vich¹, P. Malinek¹, R. Kulhanek¹; ¹VZLU AEROSPACE, Czech Republic Submitted paper is focused on the wind tunnel tests using W-WING aeroelastic demonstrator aimed at investigation into whirl flutter aeroelastic phenomenon. The paper includes description of the demonstrator mechanical concept, instrumentation, test methodology and the examples of results including dynamic response measurements and aerodynamic steady and unsteady flow field measurements. | ||||
| 14:55 | 15:20 | 9.6.4 |
EFFECT OF MORPHOLOGICAL CHANGES ON THE AERODYNAMIC CHARACTERISTICS OF THE WING AND TAIL FEATHERS OF A TAXIDERMY BLACK-TAILED GULL N. Kishimoto, Kwansei Gakuin University, Japan In this study, we developed a reconfigurable taxidermy model and measured the effects on aerodynamic characteristics of changing the wing and tail feathers of a single specimen. This approach, which bridges ornithological knowledge and engineering methods, allows for direct comparison of the aerodynamic characteristics of different wing shapes. | ||||
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| 13:40 | 14:05 | 10.6.1 |
NUMERICAL INVESTIGATION OF GEOMETRIC EFFECT ON INFRARED CHARACTERISTICS OF MULTI-STREAM SERPENTINE NOZZLES Y. Wu, Northwestern Polytechnical University, China To optimize stealth performance, this work quantifies the IR sensitivity of multi-stream serpentine nozzles to geometric configurations. Results indicate that the Shield Ratio is the dominant factor, where a higher ratio reduces wall radiation by up to 91.8%. This study establishes a correlation between nozzle geometry and IR signatures, offering a theoretical basis for the low-observable design of advanced propulsion systems. | ||||
| 14:05 | 14:30 | 10.6.2 |
COMPARATIVE ASSESSMENT OF PROPULSION SYSTEM ARCHITECTURES TAILORED FOR SUPERSONIC APPLICATIONS L. Carrea, Mälardalen University, Sweden The study presents a comparative assessment of different engine architectures suitable for civil transport applications (mixed flow turbofans and variable cycle engines). Through multi point scheme and optimization methods, optimal candidates are selected based on specific key performance indicators, aiming to extract trends and guidelines from the analysis and supporting the engine design process | ||||
| 14:30 | 14:55 | 10.6.3 |
SPILLAGE DRAG REDUCTION IN DIVERTERLESS SUPERSONIC INLET H. Miki, JAXA, Japan This study investigates spillage drag reduction in diverterless supersonic inlets through CFD-based parametric analysis of bump and cowl shape. It also examines vortex generators installed upstream of the inlet as a complementary method to enhance drag reduction and mitigate boundary layer ingestion. | ||||
| 14:55 | 15:20 | 10.6.4 |
NUMERICAL STUDY OF UNSTEADY DISTORTION IN AN S-DUCT INTAKE SUBJECTED TO BLAST SHOCK WAVES L. Shi, China Unsteady distortion in an S-duct intake subjected to blast shock waves is numerically investigated. Shock wave ingestion induces strong transient distortion, large-scale flow separation, and significant intake performance degradation at the aerodynamic interface plane. A body force model is adopted to represent the fan response, enabling efficient capture of unsteady distortion evolution with reduced computational cost. The proposed approach provides a reliable and efficient tool for intake performance assessment under explosive shock loading. | ||||
| Reserve Paper | 10.6.R |
TOWARDS SUSTAINABLE SUPERSONIC PROPULSION: INTEGRATED PROPULSIVE-EMISSIONS MODEL FOR MACH-2 MIXED-FLOW TURBOFAN ENGINES Fabrizio Borgna¹, Roberta Fusaro¹, Davide Ferretto¹, Nicole Viola¹, Marco Marini, Italian Aerospace Research Centre (CIRA), Italy; ¹Politecnico di Torino, Italy | |||||
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| 13:40 | 14:05 | 11.6.1 |
A HYBRID CNN-LSTM AND PSEUDOSPECTRAL METHOD FOR RAPID SPACECRAFT REENTRY OPTIMIZATION Y.X. Yang¹, Z. Xu¹; ¹Northwestern Polytechnical University, China This paper proposes an online trajectory optimization algorithm combining a CNN-LSTM network with the Radau pseudospectral method for constrained spacecraft re-entry. The network provides an initial guess, enabling the pseudospectral method to converge rapidly with fewer iterations and less computation. Simulation results confirm the method's effectiveness and engineering applicability. | ||||
| 14:05 | 14:30 | 11.6.2 |
OPTIMAL GUIDANCE ALGORITHM FOR BOOST-BACK OF REUSABLE LAUNCH VEHICLES J. Shim, Korea Advanced Institute of Science and Technology, South Korea Reusable launch vehicles require fuel-efficient boost-back burns. Existing laws underperform in RTLS missions and lack a theoretical background. This paper proves constant-attitude burn is optimal and offers a predictor-corrector algorithm using null-space optimization. It achieves near-optimal results with minimal computation, providing a robust, real-time guidance solution for diverse missions. | ||||
| 14:30 | 14:55 | 11.6.3 |
AIRSPACE CAPACITY IMPLICATIONS OF CONTRAIL-AWARE TRAJECTORY OPTIMIZATION Anastasia Lemetti¹, Tatiana Polishchuk¹, Lucie Smetanova¹; ¹LiU, Sweden Persistent aircraft contrails can offset climate benefits of emission-optimized flights. While contrail-aware routing is widely studied, its feasibility is constrained by airspace capacity. This study adapts a maxflow/mincut-based sector capacity methodology to quantify flight-level-dependent capacity reductions caused by contrail avoidance, highlighting operational limits of rerouting strategies. | ||||
| 14:55 | 15:20 | 11.6.4 |
TRIM OPTIMIZATION FOR AN AIRCRAFT WITH DISTRIBUTED ELECTRIC PROPULSION AND A TAIL THRUST UNIT C. Varriale, TU Delft , Netherlands This work explores trim optimization for distributed electric propulsion aircraft with redundant controls. Randomized analysis reveals exponential and quadratic power-angle of attack relationships across flight speeds. Empirical correlations between power, angle of attack, and airspeed enable efficient performance prediction for DEP aircraft with horizontal thrust units. | ||||
| Reserve Paper | 11.6.R |
CALIBRATED AIRSPEED AS A DECISION VARIABLE FOR LOW-CARBON OPERATIONS: ESF METRICS, SAF, AND FUZZY CONTROL Celia Mendez Cubillos, Opencadd Advanced Technology , Brazil | |||||
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| 13:40 | 14:05 | 12.6.1 |
DESIGN AND OPERATION OF LOW-COST MULTI-SCALE TEST BEDS FOR BATTERY THERMAL RUNAWAY INITIATION AND PROPAGATION William Mooney¹, Mathieu Gendron, Calogy Solutions, Canada; Xavier Arcand¹, Dany Francoeur¹, David Rancourt¹; ¹Université de Sherbrooke, Canada This paper presents three low-cost experimental test beds to study and mitigate Li-ion battery thermal runaway, from single cells to full modules. They capture gas, temperature, propagation, and module-level effects, and enabled the test of over 600 Li-ion cells in 2025. The setups support model calibration, mitigation strategy development, and pre-certification testing for aircraft applications. | ||||
| 14:05 | 14:30 | 12.6.2 |
MODAL-BASED FUEL LEVEL ESTIMATION OF CRYOGENIC PROPELLANT TANKS S Pfeifer, FH JOANNEUM Ges.mbH, Austria This work explores non-invasive cryogenic fuel level measurement for hydrogen aircraft tanks using modal, eigenfrequency-based gauging. Experimental liquid-nitrogen tests reveal limitations of thermal methods, while coupled simulations and laboratory measurements demonstrate how modal frequency shifts enable robust, slosh-insensitive fill-level estimation relevant beyond aviation. | ||||
| 14:30 | 14:55 | 12.6.3 |
SIZING OF LINEAR ACTUATORS FOR SPAN EXTENSION OF HALE UAV T Prakash, India In order to effectively predict the penalties of span extension for HALE UAV wings, there is need of a preliminary model for actuator weight and size estimation. Actuator design is an involved process requiring the use of several detailed design parameters such as operating pressure and mounting arrangement, which are outside the scope of the preliminary aircraft design process. Three kinds of actuators are considered suitable for span extension morphing of HALE UAV wings, viz., Electromechanical, Hydraulic and Pneumatic. Based on what is already available, each of these types corresponds to a range of force and stroke combinations. For lower values of span extension, lighter Pneumatic actuators are suitable. Hydraulic and Pneumatic actuators have an overlap for medium values of span extension. For longer extensions, telescopic Hydraulic actuators are the only available option, though they are found to be significantly heavy. Two different approaches to actuator modelling are proposed, FINDACT and DESACT, using an actuator selection and design approach respectively The actuator models were then utilised in a framework for estimation of Endurance of a HALE UAV with span-extended wings. It was found that selecting only existing actuators using FINDACT leads to jerky solutions for actuator mass as the model abruptly switched between different classes of actuators. DESACT is a model which interpolates between existing actuators and generates a notional actuator meeting the force and stroke requirements for each telescopic span morphing scenario. On following this approach, it was found that the results became smoother and less heavy. A representation of variation of actuator weight with increasing span and its effect on Endurance is evaluated and presented. | ||||
| 14:55 | 15:20 | 12.6.4 |
DYNAMIC PERFORMANCE DEGRADATION OF FLIGHT CONTROL EHA UNDER HIGH-TEMPERATURE CONDITIONS M. -W. Sun, Beihang University, China The Electro-Hydrostatic Actuator (EHA) exhibits performance degradation at high temperatures due to its integrated design. Existing models often neglect temperature-dependent parameters. This study develops a thermal simulation model that incorporates temperature-dependent hydraulic-fluid properties and motor flux linkage to analyse the dynamic response over the temperature range of 25°C to 135°C. Experiments in a thermal chamber validate the performance decline in bandwidth and settling time. The work provides a basis for enhancing the reliability and environmental adaptability of EHA in aircraft. | ||||
| Reserve Paper | 12.6.R |
NONLINEAR FRICTION MODELING OF HELIX SWING HYDRAULIC CYLINDERS FOR MORPHING AIRCRAFT USING PHYSICS-INFORMED NEURAL NETWORKS S. Chen, Beihang University, China | |||||
| Reserve Paper | 12.6.R |
LIGHTWEIGHT BIMETALLIC GEARS FOR AEROSPACE TRANSMISSIONS ENABLED BY OPEN-AIR DIFFUSION BONDING J Jiang, Imperial College London, United Kingdom | |||||
| additional information (interactive) | 12.6.R |
HIGH-PRECISION EDDY CURRENT TIP CLEARANCE SENSOR WITH EXCEPTIONAL HIGH-TEMPERATURE RESISTANCE F. L. Liu, Northwestern Polytechnical University, China | |||||
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| 13:40 | 14:05 | 13.6.1 |
APPROPRIATE ATC GO-AROUND INSTRUCTION TIMING TO PREVENT RUNWAY COLLISIONS S. Kontani, Graduate School of Maritime Sciences, Kobe University, Japan This study seeks to optimize alert timing for runway conflict detection systems during go-around scenarios. By modeling aircraft motion and air traffic controller/pilot responses, we develop a stochastic simulation model to balance the necessity of a safe go-around against the nuisance of unnecessary alerts. | ||||
| 14:05 | 14:30 | 13.6.2 |
COMPARATIVE VALIDATION OF TRADITIONAL COMPETENCY-BASED ASSESSMENT AND EXPERIENCE-BASED AUTHORISATION FOR AIR TRAFFIC CONTROLLERS J. Meier, German Aerospace Center (DLR), Germany This work demonstrates how experience-based, data-driven competency assessment can complement traditional endorsement schemes in air traffic control. The results show that flexible, constraint-based deployment decisions can be supported without compromising safety, providing an empirical basis for evolving endorsement and rostering concepts under fluctuating traffic demand. | ||||
| 14:30 | 14:55 | 13.6.3 |
FLIGHT CENTRIC ATC – HOW TO SOLVE CONFLICTS WITHOUT COMMUNICATION AND COORDINATION OVERLOADS? T. Finck, German Aerospace Center, Germany Flight Centric ATC (FCA) replaces sector-based ATC with flight-based responsibility allocation, enabling higher capacity without coordination overload. This paper examines conflict resolution in FCA using rule-based priority assignment and automated decision support. High-fidelity simulations show safe, scalable conflict management with reduced controller workload and no loss of separation. | ||||
| 14:55 | 15:20 | 13.6.4 |
AUGMENTED REALITY SAFETY NETS FOR INCREASED AIRPORT SAFETY T. Fadda, University of Bologna - Italy, Italy Research at the University of Bologna has long focused on Augmented Reality for the airport control tower to increase safety and performance while reducing workload. This paper describes subsequent research on an AR interface for Safety Nets, summarising results from two European projects and an upcoming validation campaign that will soon assess the concept in an operational environment. | ||||
| Reserve Paper | 13.6.R |
EVALUATING HUMAN-MACHINE-TEAMING CONCEPTS FOR A HIGHLY AUTOMATED GROUND CONTROLLER WORKING POSITION L. Nöhren, DLR, Germany | |||||
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| 13:40 | 14:05 | 14.6.1 |
AN AUTONOMY ARCHITECTURE FOR COLLABORATIVE UAV SWARMS - A BOTTOM-UP PERSPECTIVE Pranav Nagarajan¹, Simon Schopferer¹, Karolin Thomessen¹; ¹German Aerospace Center (DLR), Germany Presenter: Karolin Thomessen, German Aerospace Center (DLR) This paper proposes an autonomy architecture for drone swarms operating under degraded communication with a central coordination instance. Hierarchical planning supports scenario-based selection of centralized, collaborative, and decentralized replanning modes at runtime. The derived capabilities enable scalable and verifiable coordination of UAV swarms across various operational contexts. | ||||
| 14:05 | 14:30 | 14.6.2 |
SOFTWARE-IN-THE-LOOP SIMULATION OF DISTRIBUTED 3D INTEGRATED SWARM GUIDANCE FOR FIXED-WING UAVS Y. Yang, Chungnam National University, South Korea This paper proposes a distributed three-dimensional integrated guidance that simultaneously achieves path following, swarm formation maintenance, and collision avoidance for fixed-wing unmanned aerial vehicles (UAVs) in swarm flight. Fixed-wing UAVs are limited by their kinematics: they cannot hover and require bank-angle control for circling flight. Therefore, balancing the conflicting control objectives of precise path following and safe swarm maintenance poses a significant challenge. To overcome this problem, this study present a regularization-based integrated method that combines the outputs of vector field guidance, augmented Cucker-Smale model, and potential field guidance within the physical maneuvering limits of the UAV. The proposed algorithm is implemented in a Software-In-the-Loop (SILS) environment utilizing PX4, ROS2, and Gazebo, validating the theoretical derivations in a practical flight software stack. The SILS simulation demonstrates the feasibility of cooperative swarm flight for multiple UAVs to simultaneously launch and perform diverse missions. | ||||
| 14:30 | 14:55 | 14.6.3 |
REINFORCEMENT LEARNING-BASED ADAPTIVE WEIGHTING OF SWARM GUIDANCE LAWS FOR SMALL FIXED-WING UAVS C Kang, Hanseo University, South Korea This paper proposes a reinforcement learning-based adaptive weighting framework for swarm guidance of small fixed-wing UAVs. The approach preserves established guidance laws while employing a reinforcement learning agent to dynamically adjust their relative weights in real time. Augmented Cucker–Smale guidance is adopted to maintain swarm coherence, a potential-field-based term ensures inter-vehicle collision avoidance, and vector-field guidance provides path-following capability. An actor--critic reinforcement learning algorithm with a continuous action space is trained to optimize the trade-off among these guidance laws according to the current swarm state. Simulation results demonstrate that the proposed adaptive weighting strategy achieves improved robustness and overall performance compared to conventional fixed-weight guidance schemes under varying scenarios. | ||||
| 14:55 | 15:20 | 14.6.4 |
2D AND 3D TRAJECTORY PLANNING FOR UAVS FORMATION SYSTEM USING DYNAMIC WINDOW APPROACH RB.-Z. Zhu, Northwestern Polytechnical University, China This paper proposes a leader-follower trajectory planning method for large UAV formations to enhance efficiency. Using the Dynamic Window Approach (DWA) to handle kinematic constraints, it ensures feasible 2D/3D paths. Results show successful mission execution with adaptive climbing in 3D scenarios. | ||||
| Reserve Paper | 14.6.R |
IMPLEMENTATION OF DISTRIBUTED SWARM GUIDANCE ALGORITHMS ON LOW-COST UAVS J.L. McGuire, DSTG, Australia | |||||
| additional information (interactive) | 14.6.R |
ADAPTIVE PRESCRIBED-TIME COOPERATIVE CONTROL FOR FORMATION OF SMALL TANDEM-ROTOR UAVS Changqing Wang¹, Yong Guo¹, Aijun Li¹; ¹Northwestern Polytechnical University, China | |||||
| additional information (interactive) | 14.6.R |
PREDEFINED-TIME AFFINE FORMATION FAULT-TOLERANT CONTROL FOR FIXED-WING UAVS WITH INPUT SATURATION F. Fang, Northwestern Polytechnical University, China | |||||
| additional information (interactive) | 14.6.R |
RESEARCH ON OFFENSIVE AUTONOMOUS VEHICLE TRAJECTORY PREDICTION METHOD BASED ON IMPROVED INVERSE REINFORCEMENT LEARNING IN AIRCRAFT ACTIVE DEFENSE MODE H. ZHANG¹, J.-N LIU¹, Z. XU¹, Y.-X. YANG¹; ¹School of Astronautics, Northwestern Polytechnical University, China | |||||
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| 13:40 | 14:05 | 15.6.1 |
A MODEL OF DISEASE TRANSMISSION AND MITIGATION OPTIONS FOR AVIATION FROM GATE BOARDING TO IN-FLIGHT, A BOEING/FAA/US CDC JA Armstrong¹, OM Ozcakir¹, LL Waite¹, Thomas Austin¹, CA Pepper¹, A Tvaryanas², H Uyhelji², S Gearhart, US CDC, United States; P Lebbin, Canadian NRC, Canada; I Koolhof¹; ¹Boeing, Australia ;²FAA, United States Global pandemics and seasonal epidemics have significant economic and health impacts on the aviation industry, travelling public, and to public health bodies. Despite the impact, the aviation industry currently lacks evidence-based knowledge of the mechanistic dynamics of infectious disease transmission in air travel and how multiple control measures fit together to prevent disease transmission. The work to be discussed was developed in response to the U.S. Department of Transportation National Aviation Preparedness Plan and is a collaboration between the FAA, US CDC, Boeing and the Canadian NRC. We have developed a systematic and holistic framework approach to examine disease transmission risk that is transferable to multiple pathogens and settings in the aviation system. The framework provides a method and visualization by integrating a number of empirically driven mathematical models, including screening and testing, computational fluid dynamics, pathogen transmission; agent-based human movement and behaviour; and epidemiological models within the operational environment of commercial aircraft and airports. The framework defines the functionality required in each sub-model, and the required interfaces between models for data exchange. The integrated framework is then run using Monte Carlo methods to evaluate transmission risk and to optimise control strategies for a given pathogen. We show that the framework can be used to simulate a variety of infectious agents and characterise control measures used in risk reduction and mitigation. The framework is able to be run in a systematic way that allows data to be transferred between the different sub-models and for each sub-model to be run independently and at the numerical fidelity required. | ||||
| 14:05 | 14:30 | 15.6.2 |
PROBABILISTIC VALIDATION OF A NUMERICAL MODEL FOR RUN-BACK ICE SHAPES PREDICTION M. Gallia, TU Braunschweig, Germany This work presents a probabilistic validation of a numerical model for run-back ice prediction in electro-thermal Ice Protection Systems under Appendix O conditions. Operational uncertainties are propagated through the model and compared statistically with icing wind tunnel data, demonstrating that uncertainty-aware validation is essential to assess ice accretion numerical models. | ||||
| 14:30 | 14:55 | 15.6.3 |
EARLY WARNING FOR POTENTIAL BIRD STRIKES: STRATEGIC OPTIMIZATION OF PAN-TILT-ZOOM SENSOR NETWORKS FOR BIRD HAZARD DECREASE IN AIRPORT ENIRONMENT - Mei, The University of Sydney, Australia Bird strikes represent a critical safety and economic challenge for global aviation. While automated optical detection systems offer high-precision classification, their effectiveness is strictly limited by sensor placement and occlusion. This paper proposes a computational framework, " Pan-Tilt-Zoom (PTZ) Camera Deployment Optimize," to solve the Optimal Camera Placement problem in complex airport environments. Use a Python-based digital twin and a greedy heuristic algorithm, the study transitions from traditional 2D perimeter monitoring to 3D volumetric coverage of the critical flight corridor. Simulation results demonstrate that the optimized sensor topology achieves 99.3% coverage of the Runway Safety Area (RSA) and Approach Funnels while reducing hardware requirements by approximately 30% compared to standard equidistant layouts. | ||||
| 14:55 | 15:20 | 15.6.4 |
REAL-TIME AIRPORT BIRD-STRIKE PROTECTION WITH IMPROVED EDGE DEVICE DETECTION METHOD J Gao, The University of Sydney, Australia Addressing airport safety, our optimized YOLOv11 framework detects small birds using a novel MVPA module. By employing hardware-aware pruning on Jetson AGX Orin, we achieve 47.8% mAP and >60 FPS. This delivers a plug-and-play, real-time surveillance solution for detecting small, high-velocity targets. | ||||
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| 16:40 | 17:05 | 1.7.1 |
JET ZERO: ATJ SAF PROJECT DEVELOPER J Mason, Jet Zero Australia, Australia Invited speaker for the Global Sustainable Aviation track. Will present an overview of the SAF market, the role of the most commercialised technologies to produce SAF and challenges and opportunities for development of projects in Australia. | ||||
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| 16:40 | 17:05 | 2.7.1 |
THE GARTEUR GROUP OF RESPONSABLES IN AERODYNAMICS (GOR AD) AN OVERVIEW OF ACTIVITIES AND SUCCESS STORIES M. Tormalm, Sweden THE GARTEUR GROUP OF RESPONSABLES IN AERODYNAMICS (GOR AD) AN OVERVIEW OF ACTIVITIES AND SUCCESS STORIES | ||||
| 17:05 | 17:30 | 2.7.2 |
GARTEUR AG59 IMOLA: IMPROVING THE MODELLING OF LAMINAR SEPARATION BUBBLES P. Catalano, CIRA, Italy The action group 59 of the GARTEUR association started its activities in February 2019 with a consortium made of four research centers and five Universities from Italy, France, Germany, and Uk. The main aim was the improving of the numerical simulation of the laminar separation bubbles with particular focus on turbulence modelling. The importance of employing turbulence models making use of transition functions (????, and/or ?????????) has been highlighted. Interesting approaches based on functions for the boost of the turbulent kinetic energy have been proposed. Good results have been achieved by employing the Spalart-Allmaras model with transition functions, especially the version modified for decreasing the destruction term of the model. This has as a consequence the enhancement of the skin friction levels in the recovery region of the flow. The same effect can be obtained by a function that multiplies the production term of the kinetic turbulence equation as shown by the ???? ? ???? LSST model. A function for the boost of the turbulent kinetic energy has also been coupled to the transition ???? ? ???? SST model retrieving the beneficial effect of a transition function and, at the same time, ensuring the enhancement of the friction levels. These remarks apply also at high Reynolds number for the simulations of the tiny laminar separation bubbles present over turbine operating at Reynolds number of order of magnitude 10^6. | ||||
| 17:30 | 17:55 | 2.7.3 |
AI IN AVIATION CYBERSECURITY RISK ASSESSMENT: OPPORTUNITIES AND CHALLENGES C. Doll, ONERA, France A literature survey about the use of AI to support cybersecurity risk assessment was conducted within GARTEUR Aviation Security group. The paper reports the main findings, it identifies opportunities where it was already established that AI can efficiently support risk assessment and challenges where research activities are still needed. | ||||
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| 16:40 | 17:05 | 3.7.1 |
COMPARING DIFFERENT SEMI-EMPIRICAL AERODYNAMIC TOOLS FOR ANALYSING NOVEL AIRCRAFT CONFIGURATIONS J.C Chan, Cranfield University, United Kingdom A comparison between different semi-empirical aerodynamic tools with respect to analysing the Blended Wing Body at the conceptual design level. | ||||
| 17:05 | 17:30 | 3.7.2 |
DEEP LEARNING-BASED INVERSION OF NEAR-FIELD OVERPRESSURE SIGNATURES FOR LOW-BOOM SUPERSONIC TRANSPORT Y.-P. Peng, Northwestern Polytechnical University, China Supersonic transport (SST) aircraft face challenges from sonic booms over land. Low-boom design aims to minimize these effects but is computationally expensive. This study introduces a DNN-based framework to invert ground-level sonic boom signals to near-field overpressure signatures, using autoencoders, PCA, and MLPs. The approach reduces costs, accelerating low-boom SST design. | ||||
| 17:30 | 17:55 | 3.7.3 |
EASIBILITY-AWARE MULTISOURCE DESIGN METHODOLOGIES FOR HYDROGEN-POWERED SUSTAINABLE AVIATION R Obasa, Imperial College London, United Kingdom Hydrogen-powered aircraft introduce unconventional power solutions, bringing two foundational challenges: a sparse and fragmented feasible solution space and numerical models that span multiple fidelity levels, whose credibility cannot be assumed a priori. This motivates the need for feasibility-aware and fidelity-adaptive methodologies to support the robust exploration of aircraft architectures. | ||||
| 17:55 | 18:20 | 3.7.4 |
AN INCREMENTAL MODULAR MDO FRAMEWORK FOR HYDROGEN-ELECTRIC POWERTRAIN SIZING AND INTEGRATION IN GENERAL AVIATION AIRCRAFT Pablo Moreno-Escolástico, Universidad Carlos III de Madrid, Spain Hydrogen-electric powerplants introduce strong couplings between propulsion, electrical, thermal, and aerodynamic subsystems that are not captured by conventional sequential sizing methods. This work presents a physics-based MDO framework that simultaneously sizes fuel cell, motor, propeller, air intake, and thermal management system, enabling integrated, design-driven preliminary optimisation. | ||||
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| 16:40 | 17:05 | 4.7.1 |
A MULTI-SCALE COMPUTATIONAL FRAMEWORK FOR EVALUTATING TECHNOLOGY IMPACTS ON FUTURE AIRCRAFT FLEETS ES Cassidy, University of Michigan, United States This paper presents a computational framework that integrates physics-based aircraft performance modeling with fleet evolution and scenario management to assess new technologies influence on individual aircraft, operational performance, and fleet fuel burn, allowing early-stage technology impacts to be evaluated under realistic operational and adoption constraints. | ||||
| 17:05 | 17:30 | 4.7.2 |
MULTIDISCIPLINARY DESIGN OPTIMIZATION OF HYBRID AIRCRAFT: INFLUENCE OF THE RANGE OF MISSION PROFILES ON OPTIMAL DESIGN D.-B. Brousset-Matheu, ONERA, France This paper extends previous MDA/MDO work on hybrid?aircraft design by optimizing over a range of mission profiles instead of a single reference mission. A dedicated method is introduced to manage the high computational cost, enabling efficient exploration of how mission variability affects the optimal configuration. | ||||
| 17:30 | 17:55 | 4.7.3 |
COST-DRIVEN MULTIDISCIPLINARY OPTIMIZATION OF WINGLETS FOR A REGIONAL AIRCRAFT L. Falcone¹, S. Corcione¹, F. Nicolosi¹, S. Trepiccione¹; ¹University of Naples Federico II, Italy The objective of this work is to examine the role of winglets for regional aircraft from a cost-driven multidisciplinary perspective. Rather than evaluating winglets solely on aerodynamic performance, an integrated framework is adopted to consistently capture their effects on aerodynamics, structural sizing, mission performance, and economic metrics. | ||||
| 17:55 | 18:20 | 4.7.4 |
TOP-LEVEL AIRCRAFT REQUIREMENT TRADE STUDIES FOR HYDROGEN FUEL CELL REGIONAL AIRCRAFT M. Di Stasio, University of Naples Federico II, Italy This work investigates how top-level aircraft requirements influence the design of fuel cell-powered regional aircraft. Hydrogen-electric concepts are compared with conventional turboprops using a consistent conceptual design framework to assess TLAR sensitivity, energy demand, and operating cost implications for a 2040 entry-into-service scenario. | ||||
| Reserve Paper | 4.7.R |
MISSION-PROFILE-BASED HYBRID POWER SYSTEM DESIGN AND OPTIMIZATION FOR VTOL AIRCRAFT IN REGIONAL AIR MOBILITY G. Shen, Northwestern Polytechnical University, China | |||||
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| 16:40 | 17:05 | 5.7.1 |
THE NUMERICAL SIMULATIONS OF THE ACOUSTIC SHIELDING EFFECTS ON THE BLADE-VORTEX INTERACTION NOISE OF THE HART-II MODEL T. Ikeda, Japan Aerospace Exploration Agency, Japan The HART-II blade-vortex interaction noise is numerically simulated using the convected wave equation, emphasizing the noise shielding capability of the model. The evidence is clearly captured in the BVISPL noise carpet, compared with the results of the Ffowcs Williams-Hawkings equation and the wind-tunnel experiment. | ||||
| 17:05 | 17:30 | 5.7.2 |
NOISE-OPTIMIZED HOVER PROPELLER DESIGN FOR VTOL CARGO DRONES IN TRANSIENT FLIGHT CONDITIONS T. Moses, Technical University of Munich, Germany Community noise is a major challenge for cargo drones during hover and transition. This work presents a hover propeller optimized specifically for transient flight conditions of a eVTOL cargo drone using a multidisciplinary design optimization framework. Aerodynamic and acoustic performance are assessed, with vehicle-level noise evaluated via a hybrid acoustic analogy approach. | ||||
| 17:30 | 17:55 | 5.7.3 |
HIGH-FIDELITY AEROACOUSTIC AND UNSTEADY FLOW ANALYSIS OF WIND TURBINE BLADES H A Abid, King Fahd University of Petroleum and Minerals, Saudi Arabia The increasing global commitment to reducing carbon emissions while meeting accelerating energy demand has placed wind energy at the forefront of sustainable development, though aeroacoustic emissions remain a growing concern affecting public acceptance and regulatory compliance. This study utilizes the high-fidelity Lattice Boltzmann Method (LBM) to quantify the aerodynamic and acoustic effects of slot-induced flow control on S809 aerofoils, providing a physically consistent mechanism for predicting far-field noise. Preliminary results demonstrate that the slotted configuration delays stall and enhances lift generation compared to the baseline geometry, while consistently showing lower drag, particularly in the post-stall regime due to the suppression of flow separation. Flow visualizations confirm that the slot acts as a passive energization mechanism, transferring high-momentum fluid from the pressure side to the suction side to stabilize the boundary layer and re-energize the suction side flow. Direct noise computation (DNC) is employed within the unified LBM framework to capture unsteady pressure fluctuations and evaluate far-field power spectral density, facilitating a low noise design strategy for next-generation turbines. | ||||
| 17:55 | 18:20 | 5.7.4 |
LOWERING THE BARRIER TO AEROACOUSTIC PREDICTION: GPU-COMPUTED SBES FOR FAR-FIELD LANDING GEAR NOISE PREDICTION B. P. Edmonds, LEAP Australia Pty. Ltd., Australia In conclusion, the ANSYS Fluent 2026 R1 GPU-native solver for SBES coupled with FW-H provides a practical and accurate route to predict landing gear aerodynamics and far-field noise during flight specific conditions. The demonstrated gains in turnaround and energy efficiency, without loss of fidelity, argue for broader adoption of GPU-solved aeroacoustics in early-stage design. | ||||
| Reserve Paper | 5.7.R |
PRACTICAL ASPECTS OF ROTOR AERODYNAMIC AND AEROACOUSTIC DESIGN OPTIMIZATION W. A. Klimczyk, Lukasiewicz Research Network - Institute of Aviation, Poland | |||||
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| 16:40 | 17:05 | 6.7.1 |
EXPERIMENTAL STUDY OF LOAD ALLEVIATION WITH PASSIVE ADAPTIVE CAMBER AIRFOILS A. Sumi, Tokyo University of Agriculture and Technology, Japan We present the Passive Adaptive Camber (PAC) airfoil, a purely passive concept for unsteady load alleviation. Wind tunnel tests confirm load reduction, and show that the alleviation rate collapses when organized by the Cauchy number. This provides transferable, dimensionless design guidance for load-sensitive systems such as wind turbines and aircraft. | ||||
| 17:05 | 17:30 | 6.7.2 |
EVALUATION OF MORPHOUS WING CHARACTERISTICS IN WATER AND WIND TUNNEL IN THE CONTEXT OF UAV OPERATIONAL FLEXIBILITY M. A. Marciniuk, Wroc?aw University of Science and Technology, Poland These work evaluates a novel micro-UAV design that utilizes an innovative continuous trailing-edge camber-morphing airfoil, in comparison with the conventional NACA 24012 airfoil. The results show that camber morphing increases lift and delays stall throughout the tested angle of attack (AOA) range, which also introduces the rise in drag. Pitching-moment trends indicate that the baseline airfoil remains statically stable across the useful range of AOA, whereas the cambered configuration maintains static stability up to approximately 20° of AOA. Overall, the implementation of a continuous trailing-edge morphing airfoil to a micro-UAV provides enhanced lift and controllable drag, offering enhancement in landing distance reduction and mitigating damage risk during operations from unprepared terrain. | ||||
| 17:30 | 17:55 | 6.7.3 |
GUST RESILIENCE: PASSIVE GUST MITIGATION MECHANISMS USED BY GLIDING KESTRELS D Penn, RMIT University, Australia Wind-tunnel experiments show that gliding nankeen kestrels passively mitigate gusts through wing and tail morphing and flight at high angles of attack. Rapid, load-aligned aeroelastic responses damp perturbations with near-zero latency, offering bio-inspired strategies to improve gust resilience in small unmanned aerial vehicles. | ||||
| 17:55 | 18:20 | 6.7.4 |
AERODYNAMIC PERFORMANCE INCREASE OF AN A320 MORPHING WING IN SUBSONIC REGIME AT REYNOLDS NUMBER OF 1 MILLION J.A.K. Abu Kalil, ICUBE/IMFT, France The “live-skin” actuation creates Travelling Waves (TW) on the flap, interacting with the flow instabilities along the shear layers and hence modifying its organization. This new morphing concept has been investigated in take-off configuration through experiments and numerical simulations on a near full-scale A380 wing prototype. A compromise was even experimentally found between lift and drag. | ||||
| Reserve Paper | 6.7.R |
WIND-TUNNEL FORCE BALANCE AND MOUNTING SYSTEM FOR INFLATABLE WINGS B Desale, IITB-Monash Research Academy, India | |||||
| additional information (interactive) | 6.7.R |
EFFECTS OF MOLTING ON THE AERODYNAMIC CHARACTERISTICS OF BLACK-TAILED GULLS Y Tanahashi, Chubu University, Japan | |||||
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| 16:40 | 17:05 | 7.7.1 |
A GRAPH NEURAL NETWORK SIMULATOR FOR TRANSONIC VORTEX-DOMINATED FLOWS ON THE DLR-F23 CONFIGURATION A. Goerttler¹, D. Hines¹, A. Wagner¹; ¹German Aerospace Center (DLR), Germany This study presents a GNN surrogate for complex, vortex-dominated transonic flows. Validated on DLR-F23 data, the model delivers high-fidelity predictions within the training envelope, significantly accelerating analysis. By identifying current operational boundaries, this work offers a scalable path to bypass the computational bottleneck in aerospace design and related fluid dynamics industries | ||||
| 17:05 | 17:30 | 7.7.2 |
SUPERVISED DIMENSIONALITY-REDUCED MULTI-FIDELITY SURROGATE MODEL ASSISTED HIGH-DIMENSIONAL NATURAL LAMINAR FLOW OPTIMIZATION Y. Gan, Northwestern Polytechnical University, China A high-dimensional NLF optimization method based on a supervised partial least squares dimensionality-reduced multi-fidelity polynomial chaos–Kriging (PLS-DR-MFPCK) surrogate is proposed. Applied to an 88-dimensional transonic flying wing, it significantly improves efficiency and accuracy, achieving a 24.44-count (22.7637%) drag reduction while satisfying aerodynamic and geometric constraints. | ||||
| 17:30 | 17:55 | 7.7.3 |
AIRFOIL DESIGN OPTIMIZATION FOR HIGH-LIFT AND HIGH-EFFICIENCY APPLICATIONS USING DEEP REINFORCEMENT LEARNING P Scavella, UNIVERSITY OF NAPLES FEDERICO II, Italy Presenter: Gerardo Paolillo, UNIVERSITY OF NAPLES FEDERICO II A single-step deep reinforcement learning framework is applied to airfoil shape optimization using a direct coupling with a physics-based viscous–inviscid solver. Without surrogate models or embedded aerodynamic knowledge, the method converges to high-lift and high-efficiency airfoils, revealing classical pressure recovery and laminar flow strategies across varying flow conditions. | ||||
| 17:55 | 18:20 | 7.7.4 |
UNSTEADY AERODYNAMIC OPTIMIZATION OF THIN ANGULAR AIRFOIL USING CARTESIAN MESH CFD WITH LEVEL SET METHOD D Sasaki, Osaka Metropolitan University, Japan In this study, a thin angular airfoil was optimized to improve aerodynamic performance under Reynolds number 10000. Unsteady CFD computation on Cartesian mesh with level set method was used to predict time-averaged aerodynamic performance. Through the optimization, it is concluded that the existence of laminar separation bubble highly affects the lift caused by the maximum camber position. | ||||
| Reserve Paper | 7.7.R |
MULTI-SCALE LINEAR FEATURE MODULATION DEEP NEURAL OPERATOR FOR RAPID PRESSURE COEFFICIENT PREDICTION ZWF Zhang, NWPU, China | |||||
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| 16:40 | 17:05 | 8.7.1 |
ARCHITECTED LATTICE SANDWICH STRUCTURES FOR LIGHTWEIGHT IMPACT AND ENERGY ABSORPTION APPLICATIONS George Catalin: Cristea, INCAS, Romania This work demonstrates how architected and functionally graded lattice sandwich structures can significantly improve impact energy absorption while reducing peak loads. The results highlight a geometry-driven design strategy applicable to aeronautics, rotorcraft structures, and lightweight protective systems in transportation and defense industries. | ||||
| 17:05 | 17:30 | 8.7.2 |
AN EFFICIENT MULTIPARAMETRIC METHODOLOGY FOR DAMAGE PROGNOSTICS AND SHM OF ICE PROTECTION COMPOSITE LAMINATES S B Bushpalli, Collins Aerospace , Ireland The proposed approach employs an integrated framework comprising a 1D Timoshenko beam-based [1] electro-thermo-mechanical (ETM) analytical model and a multiparametric Unified Butterfly Optimisation Algorithm (UBOA) to characterise bulk and delamination damages in 3D finite element (FE) beams. The analytical ETM model simulates the vibratory response of electrothermal ice protection laminate comprising heaters sandwiched between fibreglass layers and vitrimer polymer with embedded sensors. The vibratory signal from the ETM model is then optimised by multiparametric UBOA technique which combines local exploitative and global explorative search strategies to synchronise damage detection, localisation and quantification. In the prognostic phase, the analytical model is extended to assess the influence of damage on the static, dynamic and potentially thermo-mechanical response of the degraded beam. Validation against 3D FE simulations demonstrates that the proposed method achieves substantial computational savings while maintaining a high level of accuracy as shown in Figure 1. This unified framework therefore offers a promising basis for real-time Structural Health Monitoring (SHM) and damage prognostics of composite aircraft wing structures, supporting the goals of PLEIADES toward enhanced safety and reduced maintenance costs through smart sensing and integrated SHM-IPS systems. | ||||
| 17:30 | 17:55 | 8.7.3 |
IMPACT OF COATING COLOR ON THERMAL RESPONSE OF GFRP/CFRP AIRCRAFT STRUCTURES UNDER SOLAR RADIATION B Goliszek, Warsaw University of Technology, Poland This study reveals how aircraft paint colors critically affect GFRP/CFRP heating under solar radiation, potentially exceeding epoxy Tg and risking structural failure. Novel UAV in-flight testing quantifies cooling rates. Value: empirical data linking livery design to composite safety margins; UAV/aircraft industries can adapt color-temperature guidelines for heat-exposed polymers. | ||||
| 17:55 | 18:20 | 8.7.4 |
MULTIPHYSICS COUPLING EFFECT ON INTERFACIAL PROPERTIES OF CNT/GFRP/CFRP COMPOSITES FOR ELECTROTHERMAL AI/DI APPLICATIONS X. Yao, Northwestern Polytechnical University, China The mismatch between different plies and materials of CNT/GFRP/CFRP composites will lead to property degradation under multiphysics coupling effect. Thermal cycles between -55 ? and +80 ? were studied in this work, to simulate the anti-/de-icing conditions, with hygrothermal aging and thermo-hygro-mechanical coupling effect considered, and the interlaminar shear strength evaluated periodically. | ||||
| Reserve Paper | 8.7.R |
NUMERICAL SIMULATION OF STRESS-OXIDATION DAMAGE IN C/SIC COMPOSITES AT HIGH TEMPERATURES Guoqing chen¹, Leijiang Yao¹, Bin Li¹, Xiaoyan Tong¹; ¹Northwestern Polytechnical University, China | |||||
| Reserve Paper | 8.7.R |
IMPACT TOLERANCE OF DRILLED THICK C/SIC CERAMIC MATRIX COMPOSITE A. M. Caporale¹, G. Janszen¹, A. S. Jambhulkar¹, M. Ursic², A. Tasca², R. Passoni², A. Airoldi¹; ¹Politecnico di Milano, Italy ;²Brembo N.V., Italy | |||||
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| 16:40 | 17:05 | 9.7.1 |
COMBINED TOPOLOGY AND COMPOSITE LAMINATE OPTIMIZATION OF A STRUT-BRACED DRY WING FOR A HYDROGEN AIRCRAFT LEM Vertonghen, France To assess the structural potential of strut-braced dry wings, an optimization method is presented combining topology optimization of the wing and strut volumes with composite layup optimization of skins and spars. The goal is to identify novel load paths and evaluate mass within an aircraft design framework for a hydrogen-powered aircraft, benchmarking against a classical rib-stiffened wing. | ||||
| 17:05 | 17:30 | 9.7.2 |
OPTIMIZATION APPROACHES FOR THE SHEAR-POSTBUCKLING DESIGN OF THERMOPLASTIC THIN-PLY COMPOSITE SHELLS IN HELICOPTERS M. Mauersberger¹, J. Rehfeldt¹, F. Hähnel¹, J. Markmiller¹; ¹Dresden University of Technology (TUD), Germany This study applies sustainable technologies for optimizing a shear-postbuckling design of helicopter composite shell structures. Multi-objective evolutionary algorithms and nonlinear finite element analysis are used. Results show major influence of stiffener layout and stringer-shell interfaces on buckling factors. Hence, lightweight designs are favoured, although brittleness limits performance. | ||||
| 17:30 | 17:55 | 9.7.3 |
AN AUTOMATED PARAMETRIC FRAMEWORK FOR EARLY-STAGE STRUCTURAL DESIGN AND OPTIMIZATION OF COMPOSITE AIRFRAMES N Ziakos, Universidad Carlos III de Madrid, Spain This paper presents an automated parametric framework for early-stage structural design and optimization of composite airframes. The approach integrates parametric finite-element model generation with physics-based structural analysis and data-efficient surrogate-assisted optimization, enabling systematic exploration of wing and fuselage structural designs. | ||||
| 17:55 | 18:20 | 9.7.4 |
DYNAMIC BUCKLING ANALYSIS OF VARIABLE STIFFNESS COMPOSITE CYLINDRICAL SHELLS Y. Guo, Nanjing University of Aeronautics and Astronautics, China Variable stiffness (VS) composite laminates allows tailoring the material stiffness continuously, thus the overall structural performance, such as buckling loads, can be significantly improved. The buckling behaviors of the VS laminates are mainly focused on the static case, while for the dynamic load case, its buckling behaviors are not well understood yet. In this paper, we focused on the dynamic buckling behaviors of the VS cylindrical shell under impulsive axial pressure and torsional loads. Especially, we use the geometrically exact and high order continuous isogeometric method (IGA) to study the dynamic buckling problems of the shell. To assess the influences of geometric imperfection on the dynamic buckling of VS composite cylindrical shell, eigenmode based geometric imperfections are considered which can be naturally incorporated into the framework of isogeometric analysis by using NURBS surface fitting method. Besides, failure criterion is considered to better capture its dynamic buckling behaviors under extremely short load durations. | ||||
| Reserve Paper | 9.7.R |
MULTIAXIAL MECHANICAL BEHAVIOR OF PLAIN-WOVEN CFRP TUBES UNDER COMBINED TENSION–TORSION LOADING Z.-L. Liu, Northwestern Polytechnical University, China | |||||
| Reserve Paper | 9.7.R |
CURVATURE-CONTROLLED MORPHING OF FOLDING WINGTIPS USING HONEYCOMB PLATES Rui Yang¹, Shenghua Li¹, Shiyong Sun ???¹; ¹School of Mechanical Engineering Dalian University of Technology, China | |||||
| additional information (interactive) | 9.7.R |
DESIGN CONCEPT FOR STRUCTURAL ELEMENTS MANUFACTURED FROM THICK LAMINATED COMPOSITE MATERIALS G. C. Fonseca, Embraer Minas Gerais, Brazil | |||||
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| 16:40 | 17:05 | 10.7.1 |
PROPULSION-AIRFRAME INTEGRATED AERODYNAMIC PREDICTION METHOD USING FASTAR FOR SPACEPLANE CONCEPTUAL DESIGN K. Tsukuda, Osaka Metropolitan University, Japan This study presents a novel propulsion-airframe integrated analysis coupling a validated quasi-one-dimensional flow solver with CFD. It resolves thermal choking limitations in conventional Rayleigh models at high angles of attack or low flight Mach numbers, enabling accurate, efficient prediction of power-on aerodynamics and stability essential for future spaceplane conceptual design. | ||||
| 17:05 | 17:30 | 10.7.2 |
NUMERICAL PREDICTION AND EXPERIMENTAL VALIDATION ON THRUST PERFORMANCE OF SCRAMJET EXTERNAL NOZZLES T.-I. Isono, Japan Aerospace Exploration Agency, Japan My work developed the numerical model to predict thrust performance of a Scramjet External Nozzle (SEN), with reasonable computation cost and time. The wind tunnel validation test demonstrated the applicability of this model to conceptual design tool. Consequently, my work should accelerate the scramjet engine development. | ||||
| 17:30 | 17:55 | 10.7.3 |
REPRESENTATIVE THERMO-STRUCTURAL TESTING OF SCRAMJETS USING COMMERCIAL ROCKET ENGINE TEST A Lockley, Australia Presenter: Alison Roco Short Abstract (397/400 chars): We demonstrate a low-cost direct-connect scramjet thermo-structural test using a commercial hybrid rocket engine. Two 30 s firings on a Mach 6-8 C/C module reached 66-295 kPa wall pressure and 7.1 MW/m^2 heat flux, overlapping flight loads for 10x longer duration. The method enables rapid, affordable validation of high-temperature structures (TPS, nozzles) for aerospace and adjacent industries. | ||||
| 17:55 | 18:20 | 10.7.4 |
GREEN PROPULSION VIA SUSTAINABLE 3D-PRINTED METAL-DOPED PLA HYBRID ROCKET FUELS N. Binti Abd Razak, Malaysia This study demonstrates that sustainable 3D-printed PLA hybrid rocket fuels can achieve high regression rates when doped with metallic additives and optimised port geometry. High-entropy alloys increased regression by up to 36%, enabling greener, low-cost propulsion with performance relevant to small launchers, space education, and advanced energy materials. | ||||
| Reserve Paper | 10.7.R |
A COUPLED ANALYTICAL AND NUMERICAL FRAMEWORK FOR PREDICTING MIXING DEVICE PERFORMANCE IN HYBRID ROCKET ENGINES G.-P. Puri, Australia | |||||
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| 16:40 | 17:05 | 11.7.1 |
PILOT-IN-THE-LOOP SIMULATION OF OPTIMAL DEEP-STALL RECOVERY FOR T-TAIL AIRLINER K. Yoshioka¹, T. Tsuchiya¹; ¹The University of Tokyo, Japan Pilot-in-the-loop simulations are conducted to evaluate the recovery control from the deep-stall equilibrium of a T-tail airliner. The optimal longitudinal and lateral input is obtained via an optimal control problem. In the real-time-simulator experiment, the optimal input is given to the pilot as a text instruction or is automatically executed. | ||||
| 17:05 | 17:30 | 11.7.2 |
A SIMULATION STUDY ON THE EFFECT OF EXTENDED ROTATIONAL KINEMATICS IN HEXAPOD MOTION SIMULATORS T. Bernhofer, Germany This work examines hexapod motion simulators extended with rotational kinematics from a motion-cueing-centric perspective. Using the same nonlinear model predictive control formulation for the motion cueing algorithm, the study identifies the effect of different simulator configurations on perceptual cue fidelity across different flight maneuvers. | ||||
| 17:30 | 17:55 | 11.7.3 |
HPC-BASED PARAMETER SPACE EXPLORATION FOR DENSE PICOSAT FORMATION FLYING TOWARD DIRECT-TO-DEVICE COMMUNICATIONS S. Joshin, The University of Osaka, Japan This paper presents an HPC-based simulation framework for dense PicoSat formation flying toward distributed phased array antennas. Using multi-fidelity Bayesian optimization on the Fugaku supercomputer, we systematically explore the high-dimensional design space to identify critical parameters affecting formation stability for broadband Direct-to-Device satellite communications. | ||||
| 17:55 | 18:20 | 11.7.4 |
A CFD-BASED METHODOLOGY FOR SEPARATING COUPLED PITCH-DAMPING DERIVATIVES AND ASSESSING MOTION-PARAMETER SENSITIVITY L-E Strydom, Council for Scientific and Industrial Research , South Africa Forced motion in CFD is used to separate the pitch-damping derivatives, normally reported as a combined derivative due to wind tunnel testing constraints. Prescribed pitching, plunging and flapping motions of the Standard Dynamic Model are run across Mach number, mean incidence, amplitude and reduced frequency to show how the split changes as phase lag and hysteresis increase. | ||||
| Reserve Paper | 11.7.R |
HYPERSONIC VEHICLE FLIGHT SIMULATION AND FLIGHT CONTROL Hyoung Sik Choi, KARI, South Korea | |||||
| Reserve Paper | 11.7.R |
A FRAMEWORK FOR VIRTUAL CERTIFICATION OF AIRCRAFT IN ICING CONDITIONS: WORKFLOW IMPLEMENTATION AND ASSESSMENT H. P. Heramarwan, Politecnico di Milano, Italy | |||||
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| 16:40 | 17:05 | 12.7.1 |
ANOMALY B-VALUE DETECTION AND EXCLUSION OF GBAS BASED ON WAVELET MULTI-RESOLUTION ANALYSIS R.-X. GONG, Airbus (Tianjin) Final Assembly Company Limited, China; S.-G. SUN¹, M. XU¹, Y. ZHENG, Northeast Air Traffic Management Bureau of Civil Aviation of Chi, China; ¹civil aviation university of China, China Multiple Reference Consistency Check (MRCC) based on maximum likelihood estimation is widely used for Ground Based Augmentation System (GBAS) ground reference station anomaly B-value detection and exclusion to ensure the reliability of the integrity data. But B-value slowly deviating under certain conditions is a time consumption and effectiveness challenge. An anomaly B-value detection and exclusion method based on wavelet multi-resolution analysis (WMRA) technology is proposed to distinguish the fault sources effectively. The simulation results indicate that WMRA technology shortens the detection time and can determine the fault characteristics of the ground reference station which improves the detection accuracy. | ||||
| 17:05 | 17:30 | 12.7.2 |
MODELING OF AIRCRAFT COMPONENT PLACEMENTS WITH BIN PACKING J Chang, McGill University, Canada Component placement in conceptual aircraft design is necessary to quantify the impact of new systems. A modified bin-packing algorithm is proposed to permit optimization by describing where components can be placed and approximate estimation of wiring weight and safety requirements. | ||||
| 17:30 | 17:55 | 12.7.3 |
HYBRID RF-LIFI CONNECTIVITY WITH PREDICTIVE SWITCHING: TRANSFORMING PASSENGER AND CREW COMMUNICATION INSIDE AIRCRAFT CABINS N/A Kodukula, Boeing India Engineering and Technolog Center, India This Abstract Presents a hybrid RF-LIFI connectivity system for aircraft cabins that employs smart deterministic predictive algorithms to intelligently switch between communication modes achieving 700% bandwidth improvement and 99.9% connection availability while maintaining full regulatory compliance with aviation standards (DO-178C, DO-254, FAA/EASA) | ||||
| 17:55 | 18:20 | 12.7.4 |
LOW-COST MACH-2 SUPERSONIC FREE-JET FACILITY USING COMMERCIAL OFF-THE-SHELF COMPONENTS N.M Hoang, Viettel Aerospace Institute, Vietnam A low-cost Mach-2 supersonic free-jet facility based on a blowdown concept is presented. Using COTS hardware and reused subsonic infrastructure, the system delivers a 600-mm Mach-2 jet for 30 s with stable stagnation conditions, enabling affordable high-speed aerodynamic and propulsion testing. | ||||
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| 16:40 | 17:05 | 13.7.1 |
WEATHER-DRIVEN DEEP LEARNING FOR AIRPORT RUNWAY CONFIGURATION FORECASTING H.W. Kim¹, Y.J. Eun¹, D.K. Jeon¹; ¹Korea Aerospace Research Institute, South Korea We propose a weather-only deep learning model for hourly runway-configuration forecasting up to 24 hours ahead at Incheon International Airport. An encoder-only inverted Transformer with a switch-aware training objective improves transition-timing localization while preserving per-hour configuration accuracy, achieving over 90% overall accuracy on five years of data. | ||||
| 17:05 | 17:30 | 13.7.2 |
A PRELIMINARY STUDY ON DYNAMIC AIRSPACE CONFIGURATION USING FLEXIBLE VERTICAL BOUNDARIES IN DOUBLE-LAYER AIRSPACE H Suizu, Electronic Navigation Research Institute, Japan The radar control airspace in the Fukuoka FIR was reorganized into two layers separated by FL335. This study focuses on the Kobe ACC and conducts optimization simulations by varying the boundary altitude. Kobe ACC was divided into three sectors based on controller qualifications, and the optimal boundary altitudes were found to be FL315, FL295, and FL335, based on traffic flow characteristics. | ||||
| 17:30 | 17:55 | 13.7.3 |
EVALUATING IMPACT OF INTERNATIONAL DEPARTURE TIME CONTROL ON DOMESTIC ARRIVAL DELAYS IN JAPAN USING MULTI-OBJECTIVE SIMULATION-BASED OPTIMIZATION Katsuhiro Sekine¹, Tomoaki Tatsukawa, Tokyo University of Science, Japan; Yoshiaki Kawagoe, Tohoku University, Japan; Eri Itoh¹; ¹The University of Tokyo, Japan This paper investigates how time adjustments applied to international flights can mitigate domestic arrival delays in Japan. A multi-objective simulation-based optimization framework shows that small adjustments to selected international flights can significantly reduce domestic delays up to 26.7 h on a representative high-demand day, highlighting a new lever for cross-border ATFM coordination. | ||||
| 17:55 | 18:20 | 13.7.4 |
UNDERSTANDING THE IMPACT OF OPERATIONAL VARIABLES ON ELECTRIC AIRCRAFT BATTERY PERFORMANCE VIA REAL-FLIGHT DATA ANALYSIS J.H. Kim, Sejong University, South Korea Electric aircraft can reduce short-range emissions but are constrained by limited battery capacity. This research analyzes real-flight data from Toff Mobility to quantify how operational variables affect battery performance. A data-driven framework identifies phase-dependent energy trends and operational sensitivities, highlighting the value of real-world data for battery-aware operations. | ||||
| Reserve Paper | 13.7.R |
SENSITIVITY STUDY OF DEPARTURE TIME ACCURACY FOR AIRPORT COLLABORATIVE DECISION MAKING USING FAST-TIME SIMULATION Yota Iwatsuki, Mitsubishi Research Institute, Inc./ Kyushu University, Japan; Akinori Harada¹, Shin-ichiro Higashino¹; ¹Kyushu University, Japan | |||||
| additional information (interactive) | 13.7.R |
QUANTIFYING LAND AERIAL RESCUE DEMAND INTENSITY: A DATA-DRIVEN MODELING APPROACH FOR DEFINING THE AIR-GROUND OPERATIONAL BOUNDARY G. Wang, Aerial Industry Development Research Center of China, China | |||||
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| 16:40 | 17:05 | 15.7.1 |
DESIGN, BUILD AND TEST A FULLY AUTONOMOUS UAV FOR HUMANITARIAN AID DELIVERY B. Sebastiani, University of Bologna, Italy Founded in 2024, AirOne is a student team competing in the IMechE UAS Challenge, where innovation meets education. The team designed, built, and tested an autonomous UAV for humanitarian aid delivery, transforming theory into practice. The final aircraft showcases a commitment to sustainability, with over 50% of its structure made from recycled carbon fibre. | ||||
| 17:05 | 17:30 | 15.7.2 |
A STRUCTURED CONCEPTUAL AND PRELIMINARY DESIGN FOR A SMALL-SCALE ELECTRICALLY POWERED FIXED-WING AIRCRAFT N.A Azmitia, Universidad Panamericana, Mexico This paper details the AIAA DBF 2025 aircraft design. Using an MDO framework, Monte Carlo runs, XFLR5, and OpenVSP, the layout was optimized for payload and banner missions. It integrates additive manufacturing with carbon fiber. The final configuration balances mission goals and constraints, established prior to experimental validation. It presents analytical foundations for a fixed-wing UAV. | ||||
| 17:30 | 17:55 | 15.7.3 |
EVALUATING LEARNING EFFECTIVENESS THROUGH A MIXED REALITY TRAINING FRAMEWORK FOR AEROSPACE MAINTENANCE TASKS MA Higinio, RMIT UNIVERSITY, Australia This work is a MR training for aerospace maintenance with aims: 1) increase the understanding of learning and training performance using MR technology; 2) identify and select the appropriate performance measures to reliably capture the effectiveness of MR in representative aerospace scenarios; and 3) explore the integration of MR process representations in multi-criteria decision support models. | ||||
| 17:55 | 18:20 | 15.7.4 |
FROM DATA TO DEBRIEF: A FRAMEWORK FOR PILOT PERFORMANCE ASSESSMENT P. B. Kurka, ITA, Brazil This work brings a framework that introduces automated, objective pilot performance assessment by statistically comparing simulated flight data against standardized profiles. It generates reports quantifying the pilot’s performance. Novelty lies in scalable, data-driven feedback replacing subjective debriefings. Applicable to aviation training using flight simulators. | ||||
| Reserve Paper | 15.7.R |
EDUCATING UNDERGRADUATE STUDENTS WORKING IN HANDS-ON ENGINEERING PROJECTS ON REQUIREMENT DEFINITION AND DOCUMENTATION IN MEXICO. A Pedroza-Díaz, Universidad Panamericana, Mexico | |||||
| Reserve Paper | 15.7.R |
TOWARDS AN ECOSYSTEM FOR AERONAUTICAL RESEARCH IN MEXICO A. M. Zarate Villazon, Georgia Institute of Technology - Aerospace Systems Design Lab, United States | |||||
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| 10:50 | 11:15 | 1.8.1 |
GLOBAL SUSTAINABLE AVIATION SUPER PANEL R.A. Wahls, NASA, Retired, United States The panel concludes the Global Sustainable Aviation track, featuring experts from airlines, airplane and engine original equipment manufacturers (OEMs), government research, regional aircraft and propulsion demonstration projects, and future aviation infrastructure, selected from the six track sessions. The session will feature summary observations, discussion, and opportunities for audience interaction. | ||||
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| 10:50 | 11:15 | 2.8.1 |
MULTIFUNCTIONAL METAMATERIALS FOR AEROSPACE APPLICATIONS F. J. San Millan, INTA, Spain A MetaMaterial (MM) is an engineered material with an internal micro-structure designed to achieve innovative properties not found in natural materials. MM can be applied to many fields: structures, optics, acoustic absorption, etc. Within GARTEUR an Exploratory Group on “Multifunctional MM for Aerospace Applications has recently been launched. | ||||
| 11:15 | 11:40 | 2.8.2 |
ADDITIVE MANUFACTURING OF NOVEL HIGH STRENGTH ALUMINIUM ALLOYS M.L. Montero-Sistiaga¹, M. de Smit¹, A. Pastor Muro², N. Redondo Torrico², M. Thomas³, A Morel³, S Drawin³, F. Palm, Airbus, Central Research & Technology (CRT), Germany; ¹Royal NLR-Netherlands Aerospace Centre, Netherlands ;²National Institute of Aerospace Technology (INTA), Spain ;³ONERA-The French Aerospace Lab, France Presenter: Francisco Javier San Millan Fiel, INTA- Spanish National Institute for Aerospace Research In the aerospace sector, aluminium alloys are extensively applied to structural components and Additive Manufacturing (AM) offers new opportunities in creating complex components, reducing further their weight. However, high strength aluminium alloys are challenging to process with AM. This collaborative works aims at exploring new alloys and characterising them. | ||||
| 11:40 | 12:05 | 2.8.3 |
CHARACTERIZATION AND MODELLING OF CERAMIC MATRIX COMPOSITES SUBMITTED TO SEVERE THERMO-MECHANICAL LOADING F Roudolff, ONERA, France The standards recommended by the Advisory Council for Aeronautics Research in Europe (ACARE) in 2030 require the next generation of civil aircraft engines to reduce their fuel consumption and environmental footprint. Reducing the mass of structural components through the introduction of innovative composite materials, including in the hot parts of engines, is therefore a major industrial challenge. Ceramic Matrix Composites (CMC), due to their excellent mechanical properties up to over 1500°C, are therefore potential candidates for the manufacturing of some hot parts in future commercial aircraft engines. Performing multi-instrumented mechanical tests at high temperature remain highly complex on CMC coupons, and current standards need to be improved in order to accurately determine damage and failure scenario, which are closely linked to the constituents and the architecture. Furthermore, tests carried out on structures at higher levels of the certification pyramid are not standardised and should be taken into account to better prepare tests such as L-angle specimens for instance. Nevertheless, the efficient design of such composite parts cannot rely only on test campaigns, due to the cost of such materials, and therefore requires the use of damage and failure approaches, physically based but ensuring the requirements of a design office in aeronautics in terms of modelling complexity, robustness and computational costs. Moreover, efficient computational strategies still need to be developed in order to apply an advanced multiscale damage model specific to a CMC demonstrator. There are very few studies focusing on thermo-mechanical testing and advanced damage simulation on large CMC demonstrators representative of industrial applications, due to the difficulties associated to manufacturing, testing and simulation of CMC structures. As part of the GARTEUR SM GoR, the Exploratory Group EG-45 dedicated to the “Characterization and modelling of CMC submitted | ||||
| 12:05 | 12:30 | 2.8.4 |
GARTEUR RESEARCH GROUP AG60 EXPERIENCE AND ACTIVITIES ON MACHINE LEARNING AND DATA-DRIVEN APPROACHES FOR AERODYNAMICS AND UNCERTAINTY QUANTIFICATION P. Catalano, Italy This article provides an overview of the activities and results achieved in the GARTEUR AD/AG60 project, titled ”Machine Learning and Data Mining Techniques for Aerodynamic Analysis and Uncertainty Quantification.” The project partners developed and compared several machine learning models for surrogate modeling and uncertainty quantification and applied them to the AIRBUS XRF1 aircraft configuration of industrial interest. They assessed the feasibility of advanced Machine Learning methods for predicting aerodynamic behaviors in industrially relevant configurations. The article details the models created and the different approaches adopted, along with a comprehensive analysis and discussion of the results, highlighting their implications for advancing aerodynamic predictions in practical industrial scenarios. | ||||
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| 10:50 | 11:15 | 3.8.1 |
ULTRA HIGH ASPECT RATIO STRUT-BRACED DRY WING CONCEPTUAL DESIGN FOR HYDROGEN-POWERED AIRCRAFT ES Stragiotti, ONERA, France This paper presents conceptual design of a hydrogen-powered transport aircraft with ultra high aspect ratio strut-braced dry wing. A multidisciplinary framework integrates buffet margin prediction, wing planform optimization, and high-fidelity structural sizing with buckling constraints. Surrogate models enable design space exploration using high fidelity data. | ||||
| 11:15 | 11:40 | 3.8.2 |
RESEARCH ON EFFECTIVENESS-DRIVEN INTELLIGENT OPTIMIZATION METHOD FOR CONCEPTUAL LAYOUT OF AIRCRAFT W. Liu, School of Aeronautics, Northwestern Polytechnical University, China This paper proposes an intelligent optimization method for air combat SoS aircraft layout. It integrates parametric modeling, performance estimation, agent-based simulation, and an improved GA into a closed loop. Validated in an escort strike scenario, it automatically generates layouts balancing stealth and flight performance to maximize overall effectiveness. | ||||
| 11:40 | 12:05 | 3.8.3 |
A BILEVEL STRATEGY FOR ON-DESIGN EVTOL SIZING AND OFF-DESIGN STRUCTURAL WEIGHT OPTIMIZATION L.L. Liu, HONG KONG UNIVERSITY OF SCIENCE AND TECHNOLOGY, Hong Kong SAR of China This paper presents a bilevel optimization framework for Lift-Plus-Cruise eVTOL sizing, coupling system-level aeropropulsive MDO with component-level structural material optimization. On-design optimization achieves 17.5% takeoff weight and 16.3% energy reductions versus the NASA LPC reference, with CFRP substitution indicating up to 70% weight reduction potential for primary structures. | ||||
| 12:05 | 12:30 | 3.8.4 |
OPTIMAL CONCEPTUAL DESIGN AND UPGRADE STRATEGIES FOR EVTOL AIRCRAFT UNDER EVOLVING TECHNOLOGIES M. A. Hariansyah, The Hong Kong University of Science and Technology, Hong Kong SAR of China Coupling MDO with technology forecasting, this study mitigates eVTOL obsolescence. Results identify battery specific energy as the early design driver, shifting to powertrain specific power later. Using a new future-aware metric, we show non-uniform upgrade schedules (clustered early) outperform uniform ones by 22%, offering a robust framework for long-lifecycle product design under evolving tech. | ||||
| Reserve Paper | 3.8.R |
MULTIDISCIPLINARY DESIGN OF COMPLIANT DEFORMABLE WINGS FOR IMPROVED AIRCRAFT EFFICIENCY L Mainini, Imperial College London, United Kingdom | |||||
| Reserve Paper | 3.8.R |
THREE-DIMENSIONAL AERODYNAMIC ANALYSIS OF A WING–ROTOR CONFIGURATION FOR A FOLDING WINGUAV S. Choi¹, B. Cho¹, D. Jung¹; ¹Korea Aerospace University, South Korea Presenter: Byeonggeun Cho, Korea Aerospace University | |||||
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| 10:50 | 11:15 | 4.8.1 |
A HYBRID-ELECTRIC OPEN-ROTOR AIRCRAFT FOR HIGHLY EFFICIENT LONG-RANGE AND PEOPLE-MOVER OPERATIONS G. Atanasov, DLR, Germany This paper presents a hybrid-electric open-rotor aircraft concept demonstrating that high efficiency can be achieved across both long-range and people-mover missions with a configurable vehicle. The results highlight the potential of reduced cruise speed and configurable energy storage to significantly lower fuel consumption, offering new design pathways for future low-emission air transport. | ||||
| 11:15 | 11:40 | 4.8.2 |
BUZZ-E: A BIOINSPIRED HIGH-PAYLOAD CARRYING FLAPPING WING ROBOT A. H Hammad, Technical University Munich, Germany, Germany This work develops a bio-inspired flapping-wing aerial vehicle (FWMAV) inspired by the buzzard, designed to carry a payload twice its weight. Utilizing aerodynamic calculations and 3D-printed structural components for rigidity, the design leverages the agility and high thrust-to-weight ratio of FWMAVs. Performance is validated through simulation and experimental testing. | ||||
| 11:40 | 12:05 | 4.8.3 |
COMPARATIVE DESIGN OF SBW AIRCRAFT WITH AERODYNAMIC SHAPE OPTIMIZATION FOR THREE DIFFERENT PROPULSION LAYOUTS L. Li, Chang’an University, China For a SBW wing-body-engine configuration (inner-wing, outer-wing and aft-fuselage mounted engine), the complex interaction among the wing, strut, fuselage and engine are different. The optimization results show both the outer-wing and aft-fuselage-mounted ones have a high L/D of 20.0 and 19.7, and are better than the inner-wing one with a L/D of 19.4, which is quite interesting and surprising. | ||||
| 12:05 | 12:30 | 4.8.4 |
RESEARCH PLATFORM AIRSHIP: DESIGN AND FLIGHT CHARACTERISTICS FOR URBAN OPERATIONS H. Reindle, Technical University of Munich, Germany An unmanned airship is developed as a research platform for sensor evaluation in urban environments, with a design tailored to the challenges of this use case. Analysis of its flight characteristics enables the assessment of applicability for airships of similar size and configuration. | ||||
| Reserve Paper | 4.8.R |
EMISSION REDUCTION POTENTIAL OF UNCONVENTIONAL CONFIGURATIONS FOR LONG-RANGE AIRCRAFT E. M. Künstler, University of Stuttgart, Germany | |||||
| additional information (interactive) | 4.8.R |
EMISSION REDUCTION POTENTIAL OF UNCONVENTIONAL CONFIGURATIONS FOR LONG-RANGE AIRCRAFT E. M. Künstler, University of Stuttgart, Germany | |||||
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| 10:50 | 11:15 | 5.8.1 |
AERODYNAMIC OPTIMIZATION DESIGN METHOD FOR ROTORS USING A MULTI-FIDELITY NEURAL NETWORK MODEL Z.-Q. Shen, Northwestern Polytechnical University, China This paper introduces a novel MFNN-based optimization method for helicopter rotor design, achieving a 150x speedup over traditional CFD while maintaining high accuracy (errors <1%). Its news value lies in demonstrating a breakthrough in balancing computational efficiency with precision, a challenge across many engineering fields like aerospace, automotive, and wind turbine design. | ||||
| 11:15 | 11:40 | 5.8.2 |
MACHINE LEARNING-DRIVEN AERODYNAMIC SHAPE OPTIMIZATION OF NACA AIRFOILS UNDER GEOMETRIC DESIGN CONSTRAINTS M. I. Alam, King Fahd University of Petroleum and Minerals (KFUPM), Saudi Arabia This automated framework couples Kriging surrogates with high-fidelity CFD for NACA airfoil optimization. Uniquely incorporating practical wing-box constraints, it achieves a lift-to-drag ratio of 60.21 with <1% deviation from CFD. Reducing manual preprocessing by 98%, this tool enables rapid, structure-aware aerodynamic design. | ||||
| 11:40 | 12:05 | 5.8.3 |
A COMPARATIVE STUDY OF PHYSICS-INFORMED NEURAL NETWORK FORMULATIONS FOR PARABOLIZED STABILITY EQUATIONS L. Olichevis Halila, PUCPR, Brazil Physics-informed data-driven modeling for flow stability analysis represents an inexpensive, easy-to- operate, and easy-to-automate technique for complex flow phenomena. While standard neural net- works are used as surrogates for computational fluid dynamics (CFD) simulations, they require large volumes of data, and the associated errors may not be acceptable. Physics-informed neural networks (PINNs) address this by using the underlying flow physics, represented by partial differential equa- tions, to enhance modeling accuracy and enable successful training even from sparse data. This work investigates the suitability of different PINN architectures for recovering disturbance fields in nonlocal, nonparallel flow stability analysis. The objective is to benchmark these architectures against data from a Parabolized Stability Equations (PSE) solver for a flat plate incompressible boundary layer flow. The analysis will be conducted across a range of Reynolds numbers to assess the robustness, accuracy, and limitations of each model. As a proof of concept, preliminary results are presented which indicate that a standard PINN can accurately recover relevant stability metrics, including a precise reconstruc- tion of the associated eigenfunctions. These results show that the PINN predictions accurately capture the disturbance’s amplitude spatial behavior, confirming the method’s viability even when only sparse training data is available. | ||||
| 12:05 | 12:30 | 5.8.4 |
EXPLAINABLE KNOWLEDGE DRIVEN LLM AGENTS FOR TRUSTWORTHY AIRFOIL AERODYNAMIC OPTIMIZATION DESIGN Y. Fan, NORTHWESTERN POLYTECHNICAL UNIVERSITY, China This work introduces an explainable, knowledge-driven LLM-agent framework for airfoil aerodynamic optimization. A pyramid knowledge model fuses data regularities with expert experience, guiding geometry updates and recording traceable evidence. Initial experiments show consistent gains over genetic algorithms indicating improved performance and optimization stability. | ||||
| Reserve Paper | 5.8.R |
RESEARCH ON AERODYNAMIC-STEALTH INTEGRATED DESIGN METHODOLOGY BASED ON MPPO ALGORITHM K.-G Gan, China | |||||
| additional information (interactive) | 5.8.R |
PHYSICS-CONSTRAINED INVERTIBLE NEURAL NETWORKS FOR AIRFOIL OPTIMIZATION MODEL AT LOW REYNOLDS NUMBER Z. Peng Peng, Nanjing University of Aeronautics and Astronautics, China | |||||
| additional information (interactive) | 5.8.R |
A HYBRID MACHINE LEARNING PIPELINE FOR AIRFOIL AERODYNAMICS: COMPARING UNIVERSAL AND CLUSTER-SPECIFIC PREDICTION STRATEGIES R. M. Coelho, Universidade Federal de Uberlândia, Brazil | |||||
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| 10:50 | 11:15 | 6.8.1 |
TOWARDS A FOUNDATIONAL AI MODEL FOR AIRCRAFT DESIGN: FROM HIGH-FIDELITY DATASETS TO SCALING LAWS n. Ashton, United States TOWARDS A FOUNDATIONAL AI MODEL FOR AIRCRAFT DESIGN: FROM HIGH-FIDELITY DATASETS TO SCALING LAWS | ||||
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| 10:50 | 11:15 | 7.8.1 |
FLIGHT-TEST DATA-DRIVEN HIGH-ANGLE-OF-ATTACK DYNAMICS MODELING VIA LSTM-POLYNOMIAL HYBRID APPROACH Z.G. Zhang, Northwestern Polytechnical University, China ????????????????/??????????????????????????????????????????????????LSTM???????????????????????????????????????????????????????????????????????????????????????????????????????????LSTM??????????????????????????????????????????????????????????????????????????????????????????????????????????6-DoF?????????????????????????????????????0.35%??????0.47%?????2.65%???????????????????????????????????????????????? | ||||
| 11:15 | 11:40 | 7.8.2 |
MULTI-OBJECTIVE SHAPE OPTIMIZATION OF A LAUNCH VEHICLE FAIRING ACROSS MULTIPLE FLIGHT REGIMES D. Palma, Sapienza university of Rome, Italy This work presents a multi-objective shape optimization of a launch vehicle fairing across multiple flight regimes. Aerodynamic drag and peak surface heat flux are minimized using a CFD-based framework integrated in a generic algorithm procedure. | ||||
| 11:40 | 12:05 | 7.8.3 |
STUDY ON THE IMPACT OF TRIM CONDITION ON LATERAL AND DIRECTIONAL STABILITY FOR A TAILLESS AIRCRAFT K. Kania, Warsaw University of Technology, Poland This paper presents outcomes of the numerical study into the impact of the trim condition on the static stability for an unconventional, tailless aircraft. Both the quantitative and qualitative comparison is conducted based on the stability derivatives due to sideslip and visualizations generated using Ansys Fluent. | ||||
| 12:05 | 12:30 | 7.8.4 |
GROUND-EFFECT ANALYSIS OF SMALL DUCTED PROPELLERS: A NUMERICAL–EXPERIMENTAL STUDY P. Kantzidis, RMIT University, Australia This work investigates the ground-effect aerodynamics of small, ducted propellers through a combined numerical and experimental approach. Simulations are performed using the mid-fidelity solver DUST and validated against wind-tunnel measurements, providing preliminary guidelines and highlighting the strengths and limitations of vortex-particle methods. | ||||
| Reserve Paper | 7.8.R |
NUMERICAL STUDY OF MEDIUM-WEIGHT UAV AERODYNAMIC CHARACTERISTICS DURING APPROACH AND RECOVERY TO JUAN CARLOS/CANBERRA CLASS LHDS M. J Ericksen, The University of Sydney, Australia | |||||
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| 10:50 | 11:15 | 8.8.1 |
FROM MICROCRACKING TO CRACK-NETWORK INDUCED GAS LEAKAGE IN CARBON FIBRE COMPOSITES: A MULTISCALE MODELLING FRAMEWORK W. Chang, University of New South Wales, Australia Hydrogen leakage via through-thickness percolating crack networks in carbon fibre reinforced polymer (CFRP) composites is a major concern for the safe operation of CFRP pressure vessels. However, predicting the critical load at which the leak rate exceeds allowable limits remains a major challenge for leakage-controlled composite design. Existing leakage analyses for CFRP composites remain semi-empirical, relying on post-mortem measurements of ply-splitting crack density and calibration of an effective crack-intersection conductance from leak tests, which limits predictive capability and hampers the development of analysis-based leakage criteria in design standards. This work presents a new mechanics-based multiscale framework that predicts leak-rate evolution. A micromechanical damage model (MDM) provides matrix-dominated strengths, fracture energies and mixed-mode softening relations, which are upscaled into a laminate continuum damage mechanics (CDM) model to predict ply-wise ply-splitting evolution and split-induced delamination under biaxial loading. Crucially, the MDM—CDM replaces the numerous ply-level strength/toughness inputs of conventional CDM with a small set of constituent-level fracture tests, while remaining accurate for ply splitting and subsequent delamination growth prediction, as verified by sequential uniaxial tests on cross-ply laminates that mimic equal-biaxial tension. The predicted damage states are mapped to a representative unit cell with a prescribed cohesive-zone network to compute the effective crack-intersection throat area for gas flow, which is then supplied to a compressible-gas orifice model to obtain leak rate as a function of load. Predicted leakage-load responses show good agreement with reported helium-leak measurements and enable in-situ hydrogen leak-rate predictions under biaxial loading in this work, from which crack-percolation load and leakage-threshold load are determined relative to allowable limits in existing standards | ||||
| 11:15 | 11:40 | 8.8.2 |
ULTRASONIC NON-DESTRUCTIVE TESTING: SYSTEM SELECTION FOR CHARACTERISATION AND DETECTION OF DEFECTS IN REPAIRED COMPOSITE MATERIALS H.R Spratling, Defence Science and Technology Group, Australia This paper presents a study of the effect of ultrasonic non-destructive inspection system selection on the detection and sizing of defects in repaired polymer-matrix composite materials. We provide a quantitative study of the variance due to ultrasonic test parameters and arrays on the sizing of epoxy-repaired delaminations, and the detection of barely visible impact damage (BVID). | ||||
| 11:40 | 12:05 | 8.8.3 |
EXPERIMENTAL INVESTIGATION OF BLOWING RATIO EFFECT ON THE FLOW REGIMES OF TRANSPIRATION COOLING IN LATTICE POROUS MEDIA J. Heo¹, J. Lee¹, A.-A. Reynolds¹, J. Cho¹, J.-H. Han¹; ¹KAIST, South Korea Reentry vehicles face extreme heating beyond conventional protection limits. Transpiration cooling offers high efficiency with minimal coolant and reusability. This study uses additive manufacturing to fabricate precise lattice structures, investigating cooling performance under varying coolant flow rates to advance thermal protection systems for hypersonic vehicles. | ||||
| 12:05 | 12:30 | 8.8.4 |
EXPERIMENTAL INVESTIGATION OF FRETTING WEAR IN TI6-AL-4V DOVETAIL ASSEMBLIES UNDER RESONANT VIBRATION X.-Z. Zhang, Beihang University School of Energy and Power Engineering, China The fretting wear behavior of Ti-6Al-4V dovetail assemblies under resonant vibration was investigated using fan blades manufactured with real geometry and a newly developed vibration test platform. The effects of clamping level, excitation load, and cycle number on resonance response and surface wear were analyzed. An energy dissipation based model was proposed to predict wear evolution. | ||||
| Reserve Paper | 8.8.R |
ADVANCES IN NON-DESTRUCTIVE BUCKLING PREDICTION OF THIN-WALLED STRUCTURES BY VIBRATIONS R. Degenhardt, DLR, Germany | |||||
| Reserve Paper | 8.8.R |
ALUMINA ENHANCED CARBON/PHENOLIC NOZZLE LINER COMPOSITE: MULTISTAGE MIXING, DSC GUIDED CURING, AND MICROSTRUCTURAL VALIDATION Kalid-Abebe: K.- Kassa, King Fahd University of Petroleum and Minerals, Saudi Arabia | |||||
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| 10:50 | 11:15 | 9.8.1 |
A FLUTTER VERIFICATION METHOD FOR ALL-MOVABLE CONTROL SURFACE CONSIDERING FREE-PLAY NONLINEARITY W. Qian, Dalian University of Technology, China The traditional flutter verification method primarily relies on the subjective judgment of designers. This paper proposes a novel flutter verification method applicable to all-movable control surface with free-play nonlinearity. It can to some extent supplement traditional flutter verification methods and provide reference for the design of all-movable control surface. | ||||
| 11:15 | 11:40 | 9.8.2 |
FLUTTER RESPONSE OF NOZZLE AFT DECK IN UNSTEADY ACCELERATING FLOW CONDITIONS Haibo Zheng, Northwestern Polytechnical University, China Thin-walled nozzle aft decks are prone to aeroelastic instability under varying NPR, yet their dynamic response is poorly understood. This study reveals two flutter stages, with Stage II exhibiting multi-frequency quasi-chaotic oscillations. Findings provide new insights into nonlinear aeroelastic behavior and state transitions under continuously varying nozzle conditions. | ||||
| 11:40 | 12:05 | 9.8.3 |
MECHANISM OF ALL-MOVABLE RUDDER NONLINEAR AEROELASTIC BEHAVIOR INDUCED BY BENDING FREEPLAY X.-Y. Ai, Dalian University of Technology, China Modern high-speed aircraft commonly adopt all-moving rudder to enhance maneuverability. However, freeplay within all-movable rudder system can induce limit cycle oscillation (LCO). This paper investigates the influence of bending freeplay on the nonlinear aeroelastic behavior. A novel mechanism for LCO induced by bending freeplay is proposed. | ||||
| 12:05 | 12:30 | 9.8.4 |
TIME-VARYING AEROELASTIC MODELING AND FLUTTER ANALYSIS OF TELESCOPIC WINGS C. Li, China This paper develops a time-varying aeroelastic model for the telescopic wing that accounts for the overlapping region. It evaluates the flutter stability and aeroelastic behavior of the telescopic wing during morphing process, providing insights for ensuring the flight safety of morphing aircraft. | ||||
| Reserve Paper | 9.8.R |
AEROELASTIC STABILITY AND FLUTTER PREDICTION OF A FLEXIBLE WING USING PHYSICS-BASED MODELS AND LIGHTWEIGHT AI-AIDED SURROGATE MODELS M.V. Mehta, VIT Bhopal University, India | |||||
| additional information (interactive) | 9.8.R |
FLUTTER ANALYSIS OF A DYNAMIC VARIABLE-SWEEP WING Z.-Y. Xi, Beihang University, China | |||||
| additional information (interactive) | 9.8.R |
MODELING AND ANALYSIS OF ACTIVE FLUTTER SUPPRESSION OF THE PREPOSITIVE ELLIPTICAL WING-MAIN WING COMPOSITE CONFIGURATION C. -Z. Zhao, Northwestern Polytechnical University, China | |||||
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| 10:50 | 11:15 | 10.8.1 |
CONCEPTUAL PERFORMANCE AND MASS ASSESSMENT OF AN OPEN FAN ENGINE FOR A SHORT-MEDIUM RANGE AIRCRAFT P. Wehrel¹, J. Häßy¹, R. Schnell¹, S. Wöhler¹; ¹German Aerospace Center (DLR)), Germany Open propulsion systems are promising concepts for civil aircraft due to their high propulsive efficiency. This paper considers an open fan engine with adjustable rotor and stator blades and assesses the performance and mass of such a configuration for a short-medium range aircraft in the early phase of conceptual design. CFD-generated maps are used to model the propulsor on overall engine level. | ||||
| 11:15 | 11:40 | 10.8.2 |
SURROGATE-BASED OPTIMIZATION OF AIRCRAFT PROPELLER PERFORMANCE USING A HIGH-FIDELITY AND EFFICIENT RANS FRAMEWORK A W Stuermer, DLR, Germany In the frame of the DLR PrOpti-project, the DLR Institute of Aerodynamics and Flow Technology is utilizing a surrogate based optimization approach built around a high-fidelity RANS aerodynamic analysis for the multi-disciplinary design of aircraft propeller blades to meet the increasingly challenging requirements for a high propulsive efficiency with low cabin and community noise levels | ||||
| 11:40 | 12:05 | 10.8.3 |
FEASIBILITY OF ELECTRIC DUCTED FANS TO REPLACE OPEN PROPELLERS ON AN ELECTRIFIED TRAINING AIRCRAFT G Braggett¹, K. F. Joiner¹, A. Somerville¹, D. Hill, Altavia Aerospace, Australia; ¹University of New South Wales, Australia Presenter: Georgia Braggett, University of New South Wales Our research design provides the first all-electric after-market trainer aircraft of this size that is lighter and more efficient. EDF propulsion is shown to be a feasible alternative to the conventional open propeller. We encourage other designers and operators to similarly reduce the disproportionate contribution of aviation to carbon emissions. | ||||
| 12:05 | 12:30 | 10.8.4 |
FLIGHT-DATA-DRIVEN PHYSICS-INFORMED COMPONENT MAP DERIVATION WITH STRUCTURAL COMPLIANCE Y. Liu, Northwestern Polytechnical University, China ???????????????????????????????????????????????????????????????????????????????????????????????? | ||||
| Reserve Paper | 10.8.R |
ENHANCED T-MATS MODELING OF COMPRESSOR SURGE AND STALL DYNAMICS USING THE MOORE-GREITZER FRAMEWORK Huy Nguyen, Viettel Aerospace Institute, Vietnam | |||||
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| 10:50 | 11:15 | 11.8.1 |
SYSTEM IDENTIFICATION OF SMALL-SCALE HELICOPTER VIA EKF WITH DATA-DRIVEN NOISE COVARIANCE DETERMINATION E Kim, Chungnam National University, South Korea This paper performs the system identification for a small-scale helicopter using the Extended Kalman Filter (EKF). The dynamics model of the small-scale helicopter is composed of 6-degree-of-freedom (6-DOF) rigid body equations of motion. The EKF is specifically designed to facilitate system identification. The noise covariance matrix of the EKF is determined from flight data collected during hovering conditions. Using this noise covariance matrix, the system identification of the helicopter is executed. The performance of the system identification based on the noise covariance matrix is verified through numerical simulations | ||||
| 11:15 | 11:40 | 11.8.2 |
REAL TIME MODEL IDENTIFICATION OF A MICRO FLAP-BASED DELIVERY VEHICLE T. D. Fields, University of Missouri-Kansas City, United States A terrestrial micro decelerator vehicle using servo-actuated edge flaps for attitude and velocity control is proposed. The concept is comprised of miniature servomotors, Pixracer autopilot, Raspberry Pi, and 3D printed components. Modeling and control is accomplished with multisine-based system identification. Drop testing was conducted and results from the modeling are provided. | ||||
| 11:40 | 12:05 | 11.8.3 |
GUST ERROR METHOD (GEM): PARAMETER IDENTIFICATION FOR AIRCRAFT SUBJECT TO VON KÁRMÁN PROCESS NOISE P Cox, The University of Sydney, Australia We propose Gust Error Method (GEM), improving aircraft parameter identification under stochastic gusts by modelling process noise with a low-rank decomposition. Simulations show reduced residual correlation and improved estimates. GEM separates disturbance structure, intensity, and realization, providing a practical method to account for unknown gust input during flight test. | ||||
| 12:05 | 12:30 | 11.8.4 |
WIND FIELD PERCEPTION AND FEATURE PREDICTION FOR LOW-ALTITUDE SMALL FIXED-WING UAVS TOWARDS ENERGY HARVESTING Y. He, China This research enables small fixed-wing UAVs to actively harvest wind energy like birds, breaking endurance limits. Our novel method achieves real-time 3D wind estimation without dedicated sensors and predicts key energy-rich features (e.g., shear, updrafts) via deep learning. This core perception technology is pivotal for achieving ultra-long endurance for the low-altitude economy. | ||||
| Reserve Paper | 11.8.R |
AFFINE-INVARIANT ELLIPTICAL STATE ESTIMATION FOR ROBUST EXTENDED OBJECT TRACKING In-Ho:I.-H. lee, Korea Institute of Industrial Technology, South Korea Presenter: inho lee | |||||
| Reserve Paper | 11.8.R |
INVESTIGATION OF SAFETY-CRITICAL GROUND INTERFACE (TAKEOFF, LANDING) REGIME RECOGNITION FOR AUTOMATED/AUTONOMOUS VERTICAL LIFT MISSION TASK DESIGN M.-D. Alexander, National Research Council of Canada/Flight Research Laboratory, Canada | |||||
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| 10:50 | 11:15 | 12.8.1 |
A COMPARATIVE WMLES STUDY OF THE CRM-HL IN FREE-AIR AND IN THE NTF FACILITY C. B. Sousa, United States Using WMLES, this study compares the differences between free-air and National Transonic Facility (NTF) environments on the CRM-HL. Findings reveal significant aerodynamic discrepancies at lower Reynolds numbers, where tunnel effects trigger earlier stall. However, increasing the Reynolds number reduces the variance between environments. | ||||
| 11:15 | 11:40 | 12.8.2 |
AERODYNAMIC CHARACTERISTICS OF 8% SCALE SEMISPAN CRM-HL AT THE JAXA 6.5M X 6.5M LOW SPEED WIND TUNNEL M. Kohzai, JAXA, Japan JAXA participates in the international framework “CRM-HL Ecosystem” for the purpose of verifying CFD technology development of high-lift configurations and has prepared an 8% half-span high-lift configuration of the NASA Common Research Model (CRM-HL). This presentation will introduce an overview of the wind tunnel model and test plan. Early 2025, wind tunnel tests were conducted in JAXA's 6.5m x 5.5m low-speed wind tunnel to obtain the basic performance of the CRM-HL model and to investigate the noise reduction effect of the high-lift device and main landing gear. Aerodynamic coefficients, pressure distribution, unsteady pressure, and noise source measurements were conducted and here shown. Flow visualization over the tufted wing was also conducted on the baseline configuration. Furthermore, tests to understand aerodynamic phenomena in the stall region were conducted in November 2025, including aerodynamic coefficients, pressure distribution, surface visualization using oil flow, and PIV measurements. The results of these tests on the baseline configuration are reported. | ||||
| 11:40 | 12:05 | 12.8.3 |
NEW TEST RESULTS OF THE 3.23% FULL-SPAN HIGH-LIFT COMMON RESEARCH MODEL AT KHI AERO-ACOUSTIC LOW-SPEED WIND TUNNEL T.H. Hashioka, Kawasaki Heavy Industries,Ltd., Japan Kawasaki Heavy Industries, Ltd. (KHI), an aircraft company in Japan, developed the 3.23% High lift Common Research Model (CRM-HL) as a check model of 3 x 3m Kawasaki Low-speed aero-acoustic Wind Tunnel (KLWT), firstly tested it in Jan.2023 and reported the results at the special session of ICAS 2024. In this paper, new test results of the KHI 3.23% CRM-HL model taken after 2024, will be presented. | ||||
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| 10:50 | 11:15 | 13.8.1 |
THE JOINT OPTIMIZATION OF COMMUNICATION INFRASTRUCTURE AND FLIGHT CORRIDOR IN LOW-ALTITUDE URBAN AIRSPACE Y. He, Hong Kong SAR of China This research introduces a joint optimization framework for UAM flight corridors and base station deployment. Using 3D ray tracing and a reciprocity-based greedy algorithm, the method minimizes infrastructure costs while ensuring link reliability. Preliminary results show significant gains over standard strategies. Ongoing work integrates RL-MCTS to refine solution quality further. | ||||
| 11:15 | 11:40 | 13.8.2 |
SIMULATION-BASED EVALUATION OF MULTIMODAL TRAFFIC COORDINATION AT SIGNALISED INTERSECTIONS FOR EMERGENCY SAFETY LANDINGS IN URBAN AIR MOBILITY S K Sathya Kumar, Universität der Bundeswehr München, Germany Safety landings of Urban Air Mobility (UAM) vehicles in dense urban environments pose risks to third parties, including ground traffic and pedestrians. While additional landing sites may be considered during flight planning, their availability during operations is strongly influenced by dynamic ground traffic conditions. In conventional aviation, Extended Diversion Time Operations define alternate aerodromes for diversion scenarios; however, an equivalent operational concept remains limited for UAM in constrained urban areas. This study investigates the use of signalised urban intersections as temporary emergency safety landing sites enabled through advanced ground traffic management. A network-oriented intersection management concept is formulated and initially evaluated using a microscopic simulation framework based on the Simulation of Urban Mobility (SUMO), in which emergency landing scenarios are represented through controlled intersection restrictions. Baseline results reveal significant network-level traffic impacts under uncoordinated emergency handling, highlighting the limitations of localised responses and motivating the need for coordinated, optimisation-based air–ground traffic management strategies. | ||||
| 11:40 | 12:05 | 13.8.3 |
SCHEDULING AND ROUTING FOR TIMETABLE-BOUND URBAN AIR MOBILITY OPERATIONS A. Edsel, Purdue University, United States To model timetable-bound urban air mobility (UAM) operations, the work presented draws upon features of commercial airline planning and rapid transit planning, both employing demand-driven flight scheduling and network flow-based aircraft routing. The work is expected to show that a commercial-airline-like scheduled UAM service model would carry more passengers than a rapid-transit-like model. | ||||
| 12:05 | 12:30 | 13.8.4 |
ESTIMATION AND ANALYSIS OF RNP REQUIREMENTS FOR HETEROGENEOUS UAM CONFIGURATIONS: INSIGHTS FROM K-UAM GRAND CHALLENGE OPPAV DEMONSTRATION J. Lee, Korea Aerospace Research Institute (KARI), South Korea This study presents a comprehensive estimation of RNP requirements for UAM operations, leveraging empirical flight data from the 'K-UAM Grand Challenge'. We analyzed the flight trajectories of the KARI OPPAV. The OPPAV demonstrated the capability to maintain an RNP 0.02. These findings suggest that UAM airspace design must adopt the concept of 'Adaptive RNP' criteria. | ||||
| Reserve Paper | 13.8.R |
WHAT UAM CNS NEEDS AND WHAT IT COSTS: AN EXPERT SURVEY FN Naeem, TUHH, Germany | |||||
| additional information (interactive) | 13.8.R |
OPTIMISATION OF OPERATING RADII FOR DRONE WAREHOUSES A. Tiwari, Indian Institute of Technology Bombay, India | |||||
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| 10:50 | 11:15 | 14.8.1 |
AERODYNAMIC AND AEROACOUSTIC ASSESSMENT OF 3D PRINTED AAM PROPELLER BLADES WITH SURFACE TREATMENTS D. Skrna, TU Wien, Austria In this study, conventional AAM propeller blades are replicated by computed tomography scanning and 3D-printing. By comparing the aerodynamic performance parameters, structural results and acoustic emissions with the original propellers, the relevance of rapid prototyping for drone propeller manufacturing is assessed. Additional post-processing steps are applied to improve surface properties | ||||
| 11:15 | 11:40 | 14.8.2 |
PREDICTION OF BOUNDARY LAYER TRANSITION FOR SUPERSONIC CIVIL AIRCRAFT BASED ON NEURAL NETWORK S.H. Yu, China In recent years, supersonic civil aircraft has again received widespread attention from the international aviation community due to its unique advantages in travel efficiency.And laminar-to-turbulent transition is very important for aircraft design to ruduce drag. In order to improve the computational efficiency of the prediction of the transition in the 3-D supersonic boundary layer, a neural network model method instead of the Linear stability analysis method is developed for the efficient prediction of 3-D compressible boundary layer transition. First, based on the study of the Linear stability analysis method and the characteristics of the flow field, a characteristic parameter for predicting the transition of supersonic swept wing is proposed, including Reynolds number of boundary-layer thickness, Mach number at boundary-layer edge,the streamwise shape factor of boundary-layer, maximum crossflow velocity, the crossflow shape factor and the wall temperature ratio. Then the neural network model we used is Radial Basis Function-based neural network model. For verifying the neural network model method, we calculate the boundary-layer of compressible blunt plant as the sample set of neural network, and calculate the 65 degrees straight-sweep- wing model designed by AVIC as the test case. The accuracy and efficiency of neural network model method are verified by comparing the results of neural network model method and stability analysis method. The results show that the predicted transition locations by neural network agree well with those by stability analysis and the neural network method reduce the computation time consumption greatly. | ||||
| 11:40 | 12:05 | 14.8.3 |
ON THE GROUND AND IN FLIGHT: AERODYNAMIC AND AEROELASTIC TESTING SUPPORTING INNOVATION IN AERONAUTICS C. Mertens, Royal Netherlands Aerospace Centre, Netherlands Presenter: Christoph Mertens, Royal Netherlands Aerospace Centre ON THE GROUND AND IN FLIGHT: AERODYNAMIC AND AEROELASTIC TESTING SUPPORTING INNOVATION IN AERONAUTICS | ||||
| 12:05 | 12:30 | 14.8.4 |
UNDERSTANDING HYPERSONIC BOUNDARY LAYER LAMINAR TO TURBULENT TRANSITION IN WIND TUNNEL ENVIRONMENT M. Lugrin, France UNDERSTANDING HYPERSONIC BOUNDARY LAYER LAMINAR TO TURBULENT TRANSITION IN WIND TUNNEL ENVIRONMENT | ||||
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| 10:50 | 11:15 | 15.8.1 |
PREPARING AERONAUTICAL ENGINEERING UNDERGRADUATES FOR WORKING IN GLOBAL TEAMS J. Abulawi, HAW Hamburg, Germany The strategic partnership between Virginia Tech and HAW Hamburg has facilitated various forms of international student participation in undergraduate design team projects, some of which were successful while others were not. This paper examines challenges experienced in these international team projects, identifying success factors, root causes for potential problems and possible countermeasures. | ||||
| 11:15 | 11:40 | 15.8.2 |
REFLECTIONS ON THE AEROSPACE ENGINEERING DEVELOPMENT PROGRAMME AT THE CSIR K Ramotsabi, CSIR, South Africa Reflections are detailed on the AEDP that is hosted at the CSIR for early career engineers. The AEDP provides experience to early career engineers within the full scope of aerospace systems’ lifecycles in an IPDT, which serves to bolster the skills for South Africa's aerospace and defence industry. | ||||
| 11:40 | 12:05 | 15.8.3 |
AN INDIVIDUALISED, SCALABLE PROJECT-BASED LEARNING FRAMEWORK FOR STRUCTURE DESIGN COURSES ESTABLISHED IN A LARGE AEROSPACE STUDY PROGRAMME N. Moser, Germany In this paper, a didactic tool is presented that allows for conducting highly individualised student projects for the education of engineers in large classes in academia and industry. Submissions, subsequent evaluations and personalised feedback are fully automatised. The successful application has been shown in the scope of structural design courses. | ||||
| 12:05 | 12:30 | 15.8.4 |
EDUCATION-ORIENTED MODEL-BASED SYSTEMS ENGINEERING FOR AERONAUTICAL ENGINEERING TRAINING AND INNOVATION L. H. J. Machado, UFMG, Brazil This paper presents an education-oriented, model-based framework for aeronautical engineering training, combining Systems Engineering principles with real-world, industry-driven project contexts. The approach emphasizes Model-Based Systems Engineering (MBSE) as an enabling structure to integrate multidisciplinary knowledge, requirements thinking, and innovation practices. A university-based case illustrates how project-driven learning supported by MBSE can enhance systems thinking, engineering integration, and workforce readiness for future aircraft development. | ||||
| Reserve Paper | 15.8.R |
DESIGNING AND DELIVERING A NEW PROJECT-BASED CAPSTONE AIRCRAFT DEVELOPMENT COURSE S.J. van Heerden, University of Glasgow, United Kingdom | |||||
| additional information (interactive) | 15.8.R |
INTERACTIVE NOTEBOOKS TO BRIDGE THE DIDACTIC GAP BETWEEN CALCULUS AND FLIGHT PERFORMANCE OPTIMIZATION C. Varriale, TU Delft, Netherlands | |||||
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| 15:40 | 16:05 | 2.9.1 |
ETF 2025 INTRO FOLLOWED BY INDIVIDUAL PRESENTATIONS AND A PANEL DISCUSSION AT THE END Fayette Collier, NASA, United States; Gunnar Holmberg, Saab AB, Sweden Presenter: Fayette Collier, NASA "In 2025 the topic of the ICAS ETF (Emerging Technology Forum) was “Shaping Aviation for Society”. We focused on the role of aviation in society and how our business and research should evolve to support future society. This ETF was based on a mix of technical possibilities, evolving needs and the relatively turbulent situation we experience, where sustainability challenges, natural disasters, conflicts and recent experiences from pandemics have influenced our business in ways difficult to predict and expectedly will continue so. We built the programme based on presentations of societal and aviation perspectives, highlighted by specific examples and some thematic discussions sharing opportunities and challenges. This presentation will give a brief overview of the thematic discussions including Setting the scene- needs and challenges, Sustainability and efficiency, Resilience, and finally The way forward.” | ||||
| 16:05 | 16:30 | 2.9.2 |
PRACTICAL INNOVATION IN AEROSPACE D. Donovan, United States his presentation will discuss the obstacles and opportunities to create commercially viable opportunities in aerospace. How can entrepreneurial innovators find a path to success in an industry dominated by large OEMs and a regulatory process that slows deployment of many types of technological innovation? What types of opportunities are better served by large OEMs and what types are fertile ground for new companies? | ||||
| 16:30 | 16:55 | 2.9.3 |
AVIATION VISION 2050: THE POTENTIAL FOR CLIMATE NEUTRAL GROWTH S. Kumar, United States AVIATION VISION 2050: THE POTENTIAL FOR CLIMATE NEUTRAL GROWTH | ||||
| 16:55 | 17:20 | 2.9.4 |
A MULTI-FUEL PROPULSION SYSTEM STRATEGY FOR AVIATION TRANSPORT RESILIENCE I. Orisamolu, United States A MULTI-FUEL PROPULSION SYSTEM STRATEGY FOR AVIATION TRANSPORT RESILIENCE | ||||
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| 15:40 | 16:05 | 3.9.1 |
CONCEPTUAL DESIGN OF A NOVEL VTOL UAV USING MINI TURBOJET VERTICAL LIFT RO Bura, Republic of Indonesia Defense University, Indonesia This paper presents the conceptual design of a hybrid vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) employing a mini turbojet engine exclusively for vertical lift, while forward flight is provided by a conventional piston engine and propeller. The proposed configuration is motivated by the aerodynamic and payload limitations observed in quadrotor-based VTOL UAVs, where permanently exposed lift propellers contribute significantly to parasitic drag during cruise. Literature reports indicate that VTOL lift systems based on quadrotor architectures can account for up to 38% of total parasitic drag. The study focuses on a UAV class with a target maximum take-off weight of approximately 100–120 kg and an endurance requirement of three hours. A vertically mounted TJ-120 class mini turbojet engine provides lift during short-duration VTOL phases, while auxiliary electric propellers mounted on twin tail booms provide attitude stabilization. Preliminary mass, balance, and performance analyses indicate that the proposed configuration offers improved cruise efficiency compared to quadrotor-based VTOL concepts, while maintaining operational flexibility for confined-area missions. The results suggest that the proposed architecture is a viable alternative for long-endurance surveillance UAVs requiring VTOL capability with minimal cruise drag penalty. | ||||
| 16:05 | 16:30 | 3.9.2 |
DYNAMIC ANALYSES AND FLIGHT TESTING FOR THE DESIGN OF FLOATING CANARD AIRCRAFT N. Morita, Velocity Aeroworks Inc., Japan This study investigates the longitudinal dynamics of a floating canard aircraft, in which an all-moving canard is aerodynamically self-balanced and does not contribute to static longitudinal stability. The results show that dynamic coupling between the canard pitch motion and the aircraft short-period mode limits the allowable pitch feedback gain, as confirmed by analysis and flight tests. | ||||
| 16:30 | 16:55 | 3.9.3 |
LOW BOOM DESIGN AND ANALYSIS OF A BLENDED-WING-BODY CONFIGURATION FOR LARGE-SIZED SUPERSONIC TRANSPORT L.-Y Lin, Northwestern Polytechnical University, China Compared with Tube-and-Wing (TAW) configuration, the Blended-Wing-Body (BWB) configuration features higher volumetric efficiency. This study proposes a low-boom design method for blended-wing-body supersonic transport (SBWB), including integrated wing-body design and rear-body waveform adjustment strategy, to facilitate advanced large-sized supersonic transport development. | ||||
| 16:55 | 17:20 | 3.9.4 |
STUDY ON INDUCED DRAG CALCULATION FOR BIRD-LIKE WINGTIP SLOTS USING WAKE-PLANE INTEGRATION Xia-Ru?X.-R. Liu, Northwestern Polytechnical University, China This study quantitatively analyzes how wingtip slots reduce induced drag, using a vulture-inspired bionic model of eight primary feathers. Induced drag was decomposed via wake-plane integration. Results show wingtip slots lower the induced angle of attack, mitigate vortex-induced flow deflection,. This verifies the method's applicability for evaluating and optimizing wingtip slot designs. | ||||
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| 15:40 | 16:05 | 4.9.1 |
MODELING & PRELIMINARY ANALYSIS OF AN ECOFRIENDLY AIRBORNE GLOBAL LUXURY EKRANOPLAN M.K.V. Sankrithi, RIC Enterprises, United States This presentation will share progress on modeling and preliminary analysis of an unconventional aviation system that utilizes an all-new vehicle called an Ecofriendly Airborne Global Luxury Ekranoplan or EAGLE. This new flight in ground-effect vehicle uses hydrogen fuel to enable intercontinental transportation for passengers and cargo with high speed, comfort, economy and zero carbon emissions. | ||||
| 16:05 | 16:30 | 4.9.2 |
TECHNOLOGY OPPORTUNITIES FOR CIVIL BLENDED WING BODY AIRCRAFT J. R. O'Doherty-Jennings, Aerospace Technology Institute, United Kingdom Interest in Blended Wing Body aircraft for civil applications has increased both for improved aerodynamic efficiency and as an alternative configuration for zero emission energy carriers. Consideration of established operational and certification constraints can identify technologies that may need developing to enable compliance and to minimise the impact of a new configuration on market uptake. | ||||
| 16:30 | 16:55 | 4.9.3 |
LIFT-AND-CRUISE EVTOL BOX-WING CONFIGURATION FOR THE LOW ALTITUDE ECONOMY K. Abu Salem, University of Trento, Italy This paper presents the design, development, and prototyping of a lift-and-cruise eVTOL aircraft based on a box-wing configuration for low-altitude economy applications. The proposed architecture combines vertical lift capability with aerodynamic efficiency in cruise, supporting scalable, low-noise, and energy-efficient operations, and is validated through flying tests of a scaled demonstrator. | ||||
| 16:55 | 17:20 | 4.9.4 |
PROPOSING A STABLE LIFTING FUSELAGE FOR AN AIRLINER OF THE IDEAL AIRCRAFT CONFIGURATION Reinhard Joachim Huyssen, CSIR, South Africa This study explored lifting stable fuselages for airliners based on guidelines for the ideal aircraft configuration. The aft-body is shaped to enforce some circulation with a stable centre of pressure on the fuselage. CFD was used to propose the aerodynamic shape around a shorter, wider seat arrangement in the cabin. | ||||
| Reserve Paper | 4.9.R |
BIOMIMICRY: INSPIRATION FOR NEXT-GENERATION AIRCRAFT N J Wood, Macromia Aviation Ltd, United Kingdom | |||||
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| 15:40 | 16:05 | 5.9.1 |
WIND TURBINE AERODYNAMIC SHAPE OPTIMIZATION BASED ON A DISCRETE ADJOINT APPROACH L. Olichevis Halila, PUCPR, Brazil Wind turbine configurations are characterized by complex aerodynamic phenomena. Their design must ac- count for turbulence effects, as well as flow separation. Vortex-boundary layer interaction are also relevant in the aerodynamic design of wind turbines. To capture these effects, computational fluid dynamics (CFD) tech- niques based on Reynolds-averaged Navier–Stokes (RANS) models are usually deployed in preliminary design phases. Mathematically rigorous numerical optimization techniques may be combined with RANS-based CFD simulations to explore the design space in an efficient way. Results available in the literature have shown that gradient-based optimization methods are more efficient than gradient-free ones for aerodynamic shape opti- mization (ASO). The adjoint method allows for accurate derivative estimation at a computational cost that is independent of the number of design variables. This makes it ideal for ASO investigations. In this paper, we present adjoint-based ASO studies for wind turbine configurations. We focus on the S809 wind turbine airfoil and perform its numerical optimization, aiming at aerodynamic efficiency maximization. Our preliminary results indicate a 22.19 % improvement in aerodynamic efficiency. In the final paper, we will present wind turbine blade adjoint-based ASO investigations, with a focus on strategies to design effective configurations. We will explore numerical strategies, constraint selection, and objective function choices that enable high-fidelity wind turbine aerodynamic shape optimization. | ||||
| 16:05 | 16:30 | 5.9.2 |
CONTINUOUS UNSTEADY ADJOINT VARIATIONAL MULTISCALE METHOD FOR AIRFOILS SHAPE OPTIMIZATION C. Brunelli, Royal Military Academy, Belgium This work extends adjoint-based shape optimization to unsteady and transitional flows using a Variational Multiscale LES framework. By avoiding non-differentiable RANS closures, it enables robust optimization in flows with separation and transition. The approach is validated against finite differences and successfully achieves a prescribed lift target. | ||||
| 16:30 | 16:55 | 5.9.3 |
SIMULATION OF AERODYNAMIC GROUND EFFECT FOR TILTED PROPELLERS USING VISCOUS SURFACE-VORTICITY PANEL METHOD S Shahjahan, Siemens Digital Industries Software Inc., United States Presenter: Shahfiq Shahjahan, Siemens Digital Software Industries Software Inc. This work demonstrates that a mid-fidelity viscous surface-vorticity panel method can accurately predict propeller performance in aerodynamic ground effect, including tilted configurations. With errors below 5% in key thrust metrics, the approach enables fast, reliable evaluation for UAV and eVTOL design in near-ground operations. | ||||
| 16:55 | 17:20 | 5.9.4 |
A MACHINE-LEARNING-DRIVEN AERODYNAMIC SHAPE OPTIMIZATION FRAMEWORK USING FREE-FORM DEFORMATION AND DEEP NEURAL NETWORKS L. Olichevis Halila, PUCPR, Brazil Aerodynamic shape optimization (ASO) is a cornerstone of modern aerodynamic design, enabling system- atic performance improvements through high-fidelity computational fluid dynamics (CFD) analyses. Despite its effectiveness, conventional ASO frameworks remain computationally expensive due to the requirement of repeated use of CFD solutions throughout the optimization loop, which significantly limits design-space explo- ration. This work proposes a machine-learning-based aerodynamic shape optimization framework in which deep neural networks (DNNs) are employed as surrogate models to replace high-fidelity CFD evaluations during the optimization iterations. The surrogate models are trained on a large database of airfoil geome- tries generated through free-form deformation (FFD) of a NACA 2412 baseline airfoil and evaluated using steady-state Reynolds-averaged Navier–Stokes simulations. The DNNs predict lift, drag, and pitching moment coefficients as functions of geometric design variables and flight conditions. The trained neural networks are embedded within a gradient-based optimization framework based on sequential least squares programming, where drag minimization is performed subject to lift and thickness constraints. Preliminary optimization re- sults demonstrate that the proposed approach achieves a drag reduction of approximately 14% relative to the baseline configuration while satisfying all imposed constraints, highlighting both the accuracy and robustness of the surrogate-based optimization process. The results indicate that deep neural network surrogates can effectively replace high-fidelity CFD solvers within aerodynamic shape optimization loops, yielding substantial computational savings without compromising solution quality. For the final paper, additional developments are planned, including the application of principal component analysis to reduce the dimensionality of the design space and further enh | ||||
| Reserve Paper | 5.9.R |
OPTIMIZATION OF MORPHOLOGICAL AND KINEMATIC PARAMETER FOR FLAPPING WING IN FORWARD FLIGHT Dong Xue¹, Yating Gao¹, Tao Wu¹, Bifeng Song¹, Wenp[ing Song¹; ¹Northwestern Polytechnical University, China Presenter: Gao Yating, Northwestern Polytechnical University | |||||
| additional information (interactive) | 5.9.R |
META-HEURISTIC AIRFOIL OPTIMIZATION OF VARIABLE-PITCH LIFTING SURFACES S. J. Jain, Delhi Technological University, India | |||||
| additional information (interactive) | 5.9.R |
OPTIMIZATION OF GEOMETRIC PARAMETERS FOR STRAIGHT-THROUGH LABYRINTH SEALS USING ORTHOGONAL EXPERIMENT AND CFD DATA-DRIVEN NEURAL NETWORK SURROGATE MOD Xiaoling Li¹, Lixin Yang¹, Yuhang Wei¹; ¹Beijing Jiaotong University, China | |||||
| additional information (interactive) | 5.9.R |
SCALABLE HIGH-FIDELITY AERODYNAMIC CHARACTERIZATION OF WIG CRAFT USING NON-SEQUENTIAL RBF SURROGATES N-D Diaz, ITA, Brazil | |||||
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| 15:40 | 16:05 | 7.9.1 |
AERODYNAMIC OPTIMIZATION DESIGN OF FULL-WING SOLAR-POWERED UAV FOR FLOW SEPARATION CONTROL J.-W. Wang, Northwestern Polytechnical University, China This paper focused on the flow separation phenomenon in full-wing solar-powered UAVs at low angles of attack. By optimizing the aerodynamic layout of the transition section and incorporating propeller slipstream control, it effectively suppressed separation and improved the lift-to-drag ratio. The work provided a reference for the design of similar configurations. | ||||
| 16:05 | 16:30 | 7.9.2 |
STATIC GROUND EFFECT OF HIGH-ASPECT-RATIO WINGS C. Zheng, Beihang University, China Research on typical high-aspect-ratio wings has mainly focused on the behavior of wingtip vortices, analytical or numerical aerodynamic prediction, and various specific configurations, without systematic investigation or the establishment of a unified understanding. In this paper, numerical studies are carried out on simple high aspect-ratio rectangular wings and swept wings, and the main findings are as follows: 1. A two-dimensional flow region exists in the mid-span of the wing, and its flow behavior is completely consistent with that of a two dimensional airfoil at the same flight height; this also applies to swept wings. 2. The wingtip flow behavior of wings with different aspect ratios is consistent, and the physical length of its influence range is fixed. | ||||
| 16:30 | 16:55 | 7.9.3 |
AERODYNAMIC SHAPE OPTIMIZATION OF A FUEL-CELL POWERED FLYING WING CONCEPT P. Kirschnek, FH JOANNEUM GesmbH, Austria This work presents a multi-fidelity aerodynamic pre-design methodology for fuel-cell-powered flying-wing aircraft. By combining vortex-lattice optimization targeting bell-shaped spanloads with CFD-based refinement, the approach enables efficient exploration of stable, high-efficiency configurations while accounting for propulsion integration and fuel-cell thermal management effects. | ||||
| 16:55 | 17:20 | 7.9.4 |
AERODYNAMIC FEASIBILITY OF A NOVEL SWIVEL ROTOR ARCHITECTURE B.I. Soemarwoto, Royal Netherlands Aerospace Centre NLR, Netherlands A novel swivel rotor architecture aimed for high performance on all flight regimes (hover, VTOL and high-speed cruise) is presented. It features rotating blades attached on a ring with a large radius. The ring swivels from a horizontal to a vertical position, changing the flight mode from hover to cruise. CFD results highlighting the aerodynamic potentials of the new architecture are presented. | ||||
| Reserve Paper | 7.9.R |
DEVELOPMENT OF HYDROPHILIC COATINGS FOR PRACTICAL APPLICATION OF LAMINAR FLOW WINGS H Iijima, Japan Aerospace Exploration Agency, Japan | |||||
| additional information (interactive) | 7.9.R |
FLUTTER FEATURES AND AERODYNAMIC DAMPING CALCULATION METHODS FOR PLATE-HEAT EXCHANGERS IN HIGH-SPEED TURBINE ENGINES K.-Q. Qiao, Beihang University, China | |||||
| additional information (interactive) | 7.9.R |
UNCONTROLLED TAILLESS GLIDING: PAPER AEROPLANES GEOMETRY, AERODYNAMICS AND STABILITY ANALYSIS J. Guo, United Kingdom | |||||
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| 15:40 | 16:05 | 8.9.1 |
DESIGN ASSESSMENT OF A HELICOPTER BLADE K Warnakula¹, M Silla¹, C Barber¹, T Hallwright¹, O Kaleagasi¹, D Schoemaker, Gyro Technic Inc., United States; ¹SYOS Aerospace, New Zealand A comprehensive assessment of rotor blade design modification was carried out to ensure its structural integrity. The work covered stress analysis, fatigue and damage tolerance. For this purpose, CFD analysis was conducted on the blade for the case of forward flight, flying at cruising speed, then continued with FE modelling where the blade structure was subjected to the aerodynamic loads and centrifugal force. A model of mission load spectra was established based on a well-known statistical data of conventional helicopter. The fluctuation loads generated by advancing and retreating blades were used to estimate the life cycle of the blade based on Palmgren-Miner’s rule of linear damage accumulation. An estimation of crack-growth was then conducted to complete the design assessment for maintenance purposes. Keywords: CFD, FEA, stress-analysis, fatigue and fracture | ||||
| 16:05 | 16:30 | 8.9.2 |
CYCLOSTATIONARY ANALYSIS FOR CRACK DETECTION AND TRENDING IN HELICOPTER GEARBOX CASING Nader Sawalhi¹, Wenyi Wang¹; ¹Defence Science and Technology Group, Australia Early detection of cracks in helicopter gearbox casing is critical for safety and operational readiness. This work applies cyclostationary analysis combined with unsupervised clustering to analyze vibration data from a main rotor gearbox. Together, these methods improve early detection, reduce diagnostic uncertainty, and support predictive maintenance strategies for helicopters. | ||||
| 16:30 | 16:55 | 8.9.3 |
ANALYSIS OF CRACK GROWTH CHARACTERISTICS OF HOLE CORNER CRACKS IN EXPANDED FILM COOLING HOLES ON TURBINE BLADE FLANGES N/A Yan, Beihang University, China This study focuses on the film cooling holes in the shroud of an aero-engine turbine blade, conducting combined high- and low-cycle fatigue tests to investigate crack initiation and propagation behavior at 800?°C. Particular emphasis is placed on identifying crack initiation sites, determining initiation life, and analyzing crack propagation paths. | ||||
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| 15:40 | 16:05 | 9.9.1 |
AEROELASTIC TAILORING FOR COMPOSITE ADAPTIVE WINGLETS N. Tsushima, Kyushu University, Japan; R. Higuchi¹, T. Yokozeki¹; ¹The University of Tokyo, Japan This study investigates aeroelastic tailoring of composite adaptive winglets for passive morphing. A validated nonlinear framework, combining the vortex lattice method and corotational shell elements, evaluates how composite anisotropy optimizes deformation under aerodynamic loads. Preliminary results demonstrate feasibility of the framework for parametric layup optimization. | ||||
| 16:05 | 16:30 | 9.9.2 |
PARAMETRIC AEROELASTIC STUDY OF WINGLET GEOMETRY USING VORTEX LATTICE METHOD FOR FUTURE PASSIVE MORPHING APPLICATIONS M.N.-A. Kouchlef, The University of Tokyo, Japan This work presents a coupled aerodynamic-structural framework that enables a comprehensive parametric study of winglet geometries. By jointly analyzing aerodynamic performance, structural loads, and aeroelastic effects over a wide range of winglet design parameters, this method identifies the most promising design variables for passive morphing winglet applications. | ||||
| 16:30 | 16:55 | 9.9.3 |
AEROELASTIC DESIGN OF A STRUT-BRACED DRY WING FOR A HYDROGEN AIRCRAFT IN AN MDO FRAMEWORK C. Mollet, ONERA, France This work presents the results of aeroelastic optimisations of a LH2 powered strut-braced aircraft configuration. The influence of the strut under aeroelastic loads and especially how some geometries introduce in-plane bending and buckling issues (for negative loadcases) is studied . Flutter is also checked to ensure it does not appear within the flight enveloppe. | ||||
| 16:55 | 17:20 | 9.9.4 |
MANEUVER LOAD ALLEVIATION OF THE DRY WING FOR HYDROGEN AIRCRAFT F. Yu, Technical University of Munich, Germany "Dry wing" fuel relocation in hydrogen aircraft typically imposes a severe wing mass penalty. Using a high-fidelity aeroelastic toolchain on an A320-like configuration, this study proves Maneuver Load Alleviation (MLA) slashes this penalty to <1%. These findings establish MLA as the critical enabler for H2 aviation, resolving a primary structural barrier to the feasibility of zero-emission flight. | ||||
| Reserve Paper | 9.9.R |
DYNAMICS MODELING AND EXPERIMENTAL VERIFICATION OF ROTOR WITH COMPLEX THREE-DIMENSIONAL SHAPE BLADE J.H Huang, China | |||||
| Reserve Paper | 9.9.R |
AFP-BASED TOW STEERING FOR AEROELASTIC OPTIMIZATION OF HIGH ASPECT-RATIO WINGS WITH FOLDING WINGTIPS M. S. Poomadath, 1Khalifa University of Science and Technology, United Arab Emirates | |||||
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| 15:40 | 16:05 | 10.9.1 |
MODULAR JET AND PROPELLER ENGINE – PART I: INITIAL STUDIES T. Otten, German Aerospace Center (DLR), Germany A retrofit concept is investigated for adapting a small, off-the-shelf turbojet to a turboprop configuration via a modular kit consisting of a power turbine and propeller. Several configurations are evaluated using performance modeling, conceptual design methods and parametric studies across flight conditions | ||||
| 16:05 | 16:30 | 10.9.2 |
MODULAR JET AND PROPELLER ENGINE –– PART II: INTEGRATED DESIGN PROCESS AND DESIGN SPACE ASSESSMENT T. Matuschek, German Aerospace Center (DLR), Germany The Modular Jet and Propeller Engine (MOJO) concept is investigated using an integrated design process linking turbine, propeller and gearbox models. The resulting framework enables systematic exploration of the design space and reveals dominant trends and constraints governing feasible modular turboprop configurations, supporting architecture decisions without commiting to a specific platform. | ||||
| 16:30 | 16:55 | 10.9.3 |
INVESTIGATION OF GENERIC SWIRL DISTORTION AND ITS EFFECTS ON COMPRESSOR PERFORMANCE AND FLOW STABILITY L. Oberthür, University of the Bundeswehr Munich, Germany A new testsetup in a full sized turbofan engine test bed is used to determine the influence of inlet distortion induced by s-shaped inlet ducts. The focus of the first test campaign is swirl distortion which is induced by the usage of a vortex generator and the effects onto the engine is investigated in the whole operating range of an aircraft engine in ground test conditions. | ||||
| 16:55 | 17:20 | 10.9.4 |
INITIAL GEOMETRIC UNCERTAINTY ASSESMENT IN COMPRESSOR AIRFOILS USING PHYSICS-BASED DIRECT MANIPULATED FFD K. Omoto, Osaka Metropolitan University, Japan This study efficiently evaluates the aerodynamic impact of local leading-edge deformations using CFD. We confirm that leading-edge geometry significantly influences loss generation. By comparing two different LE shape airfoils, this research identifies shapes that maintain robust aerodynamic performance, offering vital guidelines for designing airfoils resilient to geometric uncertainties. | ||||
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| 15:40 | 16:05 | 11.9.1 |
TRAJECTORY OPTIMIZATION OF HIT-TO-KILL INTERCEPTORS VIA SEQUENTIAL CONVEX PROGRAMMING APPROACH Suk-jae: S.-J. Im, Korea Advanced Institute of Science and Technology (KAIST), South Korea A multi-phase trajectory optimization scheme based on sequential convex programming is proposed for hit-to-kill interceptors. This approach enables minimum-time interception under distinct phase dynamics and seeker lock-on constraints. The proposed framework is tested and is shown to be a computationally efficient and near-optimal solution suitable for constrained guidance problems. | ||||
| 16:05 | 16:30 | 11.9.2 |
A CONVEX PREDICTOR-CORRECTOR GUIDANCE METHOD FOR REUSABLE ROCKET ENTRY FEATURING ACTIVE WIND COMPENSATION J. K. Zhang, China To address high-altitude wind shear challenges in reusable rocket entry, this paper proposes a Convex Predictor-Corrector Guidance method with Active Wind Compensation. Leveraging Sequential Convex Programming, the algorithm actively counteracts wind disturbances to achieve high-precision landing robustness against environmental uncertainties, as validated by extensive Monte Carlo simulations. | ||||
| 16:30 | 16:55 | 11.9.3 |
DUAL BEZIER SPACE-TIME OPTIMIZATION UNDER HARD OBSERVATION-WINDOW CONSTRAINTS: A FEASIBILITY-ORIENTED JERK-CAP COMPARISON H Kim, Kookmin University, South Korea Dual Bezier space-time optimization co-designs trajectory and time scaling to meet hard viewing-angle limits in an observation window. SQP-stable fixed-length sampling and continuation enable a feasibility metric: minimum jerk cap. Tests show the dual method stays feasible under tight constraints where uniform-time baselines fail, benefiting surveillance and time-critical guidance. | ||||
| 16:55 | 17:20 | 11.9.4 |
OFFLINE REINFORCEMENT LEARNING FOR INFRARED IMAGE-BASED MISSILE GUIDANCE AND CONTROL S.Y Kim, Chungbuk National University, South Korea An offline reinforcement learning framework for missile guidance and control is proposed using expert data generated by a sliding mode guidance law. TD3+BC is adopted to mitigate distributional shift and Q-value underestimation by constraining the policy to expert behavior. Simulations demonstrate stable interception and a 1.2% higher success rate than the baseline. | ||||
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| 15:40 | 16:05 | 12.9.1 |
GAP OPTIMIZATION ADAPTIVE TOOL FOR LARGE SCALE FLEXIBLE STRUCTURE ASSEMBLY B Lakic ¹, R Noll¹, G Buckus¹, R Grube¹, M Walling¹; ¹Boeing, United States Assembly of large-scale flexible structures—such as commercial airplane fuselages and Space Launch System cryogenic tanks—poses a persistent challenge for assembly due to tight allocated engineering requirements for the large complex components/assemblies. These structures exhibit significant transformations during handling, assembly operations, deformations due to inherent flexibility, thermal exposure, cumulative tolerance stack-ups, different fixtures, etc. The ability to control, manipulate and verify shape during assembly is therefore fundamental to enabling stable, repeatable, and high-rate production systems that deliver consistent quality. | ||||
| 16:05 | 16:30 | 12.9.2 |
EVALUATION OF TRUST AS A HUMAN FACTOR IN COLLABORATIVE ROBOTICS ASSOCIATED WITH ARTIFICIAL INTELLIGENCE I. Ali¹, C. Silva², E. Villani², J. M. Mello¹, W. Oliveira²; ¹Embraer, Brazil ;²ITA, Brazil This study explores operator trust in an aeronautical task using collaborative robotics associated with artificial intelligence. Trust was assessed through subjective questionnaires and objective physiological signals. Results show that operators' trust decreases as system errors increase, and discuss the effectiveness of measurement tools, offering recommendations for experimental practices. | ||||
| 16:30 | 16:55 | 12.9.3 |
VIRTUAL COMMISSIONING APPLIED TO ROS AIRCRAFT ROBOTIC CELL A Teixeira Ferraz, Brazil This work introduces an virtual commissioning framework that enables safe and cost-effective validation of ROS-based robotic cells before final deployment. By progressively integrating simulation and hardware, the approach reduces integration risks and supports real-time requirements. The results are relevant beyond aerospace, supporting sensor-based robotic systems in industrial environments. | ||||
| 16:55 | 17:20 | 12.9.4 |
MIXED REALITY-BASED PROGRAMMING BY DEMONSTRATION FOR ROBOTIC GRINDING OF AERO-ENGINE BLADES Y. Liu, Chongqing University, China We propose an MR-based human-mimetic grinding method for aero-engine blades. Integrating a ROKAE 7-DoF robot and HoloLens 2, the system captures manual poses for trajectory generation. Using redundancy resolution and B-Spline smoothing, the framework is designed to digitize expert skills and achieve high-fidelity process reproduction. | ||||
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| 15:40 | 16:05 | 13.9.1 |
VERTIPORT FINAL APPROACH AND TAKEOFF AREA DESIGN USING COUPLED MICROSCALE WIND AND FLIGHT DYNAMICS ANALYSIS N.-D.-S Dhamodharasamy, Politecnico di Milano, Italy This paper presents an efficient, transferrable simulation-based methodology that integrates microscale urban wind modelling with VTOL flight dynamics to support vertiport FATO design. The framework identifies wind and aircraft performance based approach orientations and geometries, improving operational safety, efficiency, and data driven decision making for safe and sustainable UAM operations. | ||||
| 16:05 | 16:30 | 13.9.2 |
LOW-NOISE VERTIPORT PROCEDURE OPTIMIZATION BASED ON DEEP REINFORCEMENT LEARNING Y. Wang, The Hong Kong University of Science and Technology, Hong Kong SAR of China This study presents a Deep RL framework that transforms vertiport airspace design. By optimizing for acoustic fairness, we generate dynamic flight corridors that reduce community noise by max 5.8 dB. This offers a vital policy-in-the-loop tool for regulators to standardize low-noise procedures and quantify vertiport acoustic capacity. | ||||
| 16:30 | 16:55 | 13.9.3 |
IMPACT OF DEMAND PATTERNS AND BOOKING LEAD TIMES ON FLEET AND INFRASTRUCTURE IN URBAN AIR MOBILITY M. Swaid, German Aerospace Center (DLR), Germany This study analyzes the sensitivity of fleet and infrastructure requirements in UAM with respect to booking lead time and the temporal distribution of demand over the day. While short lead times improve service quality, they hinder efficient vehicle rotation. A rolling horizon algorithm is used to evaluate KPIs such as fleet size and infrastructure needs depending on lead time and demand patterns. | ||||
| 16:55 | 17:20 | 13.9.4 |
ADVANCING TRAFFIC MANAGEMENT SERVICES FOR VERTIPORT OPERATIONS IN EUROPE: INSIGHTS FROM THE EUREKA PROJECT M. Corsi, Deutsches Zentrum für Luft und Raumfahrt (DLR), Germany The EUREKA project extends the current scope of the existing ATM, air operations, and U-space frameworks for vertiport stakeholders, aiming to advance Traffic Management Services for vertiport operations in Europe. It develops and validates collaborative frameworks for vertiport and network-level operations and assesses how vertiport operations integrate with U-space services and ATM procedures. | ||||
| Reserve Paper | 13.9.R |
ADVANCING TELE-OPERATION IN URBAN AIR MOBILITY: A STRATEGY LEVERAGING DIGITAL TWIN TECHNOLOGY LV Nguyen, Konkuk University, South Korea | |||||
| additional information (interactive) | 13.9.R |
A BIONIC-INSPIRED COLLABORATIVE SYSTEM FOR MANNED AND UNMANNED AERIAL VEHICLES IN EMERGENCY RESCUE MISSIONS X. Minze, Beihang University, China | |||||
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| 15:40 | 16:05 | 14.9.1 |
ADVANCED AIR MOBILITY: THE CURRENT STATE OF DEVELOPMENT AND THE CHALLENGES V. Kramar, VTT Technical Research Centre of Finland, Finland This work synthesizes global AAM development, from the Scientific Assessment for UAM to ICAO harmonization. It compares regulatory progress in key regions (e.g., US, EU, China) and addresses challenges like certification, infrastructure, and public acceptance. It concludes by proposing international research collaboration to bridge the gap to operational maturity. | ||||
| 16:05 | 16:30 | 14.9.2 |
PREDICTION OF STRUCTURAL VIBRATIONS INDUCED BY MASS-UNBALANCED ELECTRIC PROPULSION SYSTEMS G. R. D. Rodrigues Dias, Aeronautics Institute of Technology, Brazil This work investigates vibrations in aircraft structures with distributed electric propulsion under propeller mass unbalance. A Rayleigh–Ritz wing model including bending, torsion, gyroscopic and aerodynamic effects is developed and validated. Simulations assess design and operating parameters, supporting safer, more reliable electric aircraft structures. | ||||
| 16:30 | 16:55 | 14.9.3 |
METHODOLOGY AND V1 PROTOTYPE OF AN ADAPTIVE/ADAPTABLE MULTI-UAV GCS HMI IN A FLOOD SAR CO-SIMULATION TESTBED A. G. P. Sarmento, Aeronautics Institute of Technology (ITA), Brazil This paper delivers a traceable method and a runnable V1 multi-UAV GCS HMI in a realistic flood-SAR co-simulation (MATLAB/Simulink+JSBSim+UE5.3+Cesium, UDP, synchronized logs). It proves feasibility for adaptive/adaptable LOA control and creates a repeatable testbed that other safety-critical industries can reuse (maritime, rail, utilities, robotics). | ||||
| 16:55 | 17:20 | 14.9.4 |
A SEMI-AUTONOMOUS DECISION SUPPORT TOOL FOR ATC IN EN-ROUTE REROUTING OPERATIONS R.F Viana, Aeronautics Institute of Technology, Brazil This work demonstrates a semi-autonomous decision-support tool that generates operationally feasible en-route reroutes under severe convective weather and traffic constraints. Results show that traffic separation, not geometry alone, drives feasibility, highlighting the relevance of optimization-based decision support for ATC, network operations, and other safety-critical transport systems. | ||||
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| 15:40 | 16:05 | 15.9.1 |
EXPLAINABLE NATURAL LANGUAGE PROCESSING FOR AIRCRAFT STRUCTURAL INTEGRITY DEFECT CLASSIFICATION V Kekoc, Defence Science & Technology Group, Australia Explainable NLP framework to classify structural integrity issues in aircraft defect reports, using transformer-based language models & XAI methods for transparency. Preliminary analysis on aviation safety datasets is promising, w/ explainability techniques identifying domain-relevant indicators. Further validation on ADF data & comparison to human reasoning within sustainment workflows to follow. | ||||
| 16:05 | 16:30 | 15.9.2 |
AI-BASED MAINTENANCE CODE CORRECTION FOR RELIABLE MTBF ANALYSIS K. Minyoung, Korea Aerospace Industries, LTD, South Korea This work improves the reliability of MTBF-based analysis by automatically correcting maintenance codes from free-text records using AI. It reduces human dependency, enforces logical consistency, and enables scalable reliability analysis. The approach is applicable to aviation and other asset-intensive industries relying on structured maintenance data. | ||||
| 16:30 | 16:55 | 15.9.3 |
V-MODEL-BASED DEVELOPMENT OF A SPATIOTEMPORAL AIRFRAME CORROSION DIGITAL TWIN W.Y. Chia, RMIT University, Australia Airframe digital twins (ADTs) have been developed in various forms and functions to support aircraft structural prognostics and health management, and predictive maintenance However, the development of an ADT to support aircraft corrosion prognostics and health management has been underexplored despite corrosion being the second-most concerning structural failure mode after fatigue. Particularly in aging aircraft, structural corrosion remains a threat to operations in terms of costs and safety. To fill these gaps, this paper proposes a novel Spatiotemporal Airframe Corrosion and Environmental Digital Twin (SpACE-DT) that models an aircraft’s dynamic operating environment through its operational and non-operational phases. The proposed SpACE-DT is built upon a systems engineering approach by application of a simplified V-model. This paper demonstrates the V-model methodology through the concept of operations for requirements definition, the developed prototype, and an evaluation of the integrated properties of the system against the functional and non-functional requirements. The proposed methodology reinforces traceability, modularity, and future scalability of the airframe corrosion digital twin system to be integrated with other forms of ADTs. This proof-of-concept paves the way for more comprehensive structural prognostics and health management, including corrosion, and demonstrates feasibility of modern digital systems to support aircraft predictive maintenance. | ||||
| 16:55 | 17:20 | 15.9.4 |
PHYSICS-INFORMED NEURAL NETWORKS FOR ULTRASONIC LAMB WAVE RECONSTRUCTION IN NON-DESTRUCTIVE TESTING L.J. Jilke, German Aerospace Center (DLR), Germany We propose a Physics-Informed sinusoidal representation network (PI-SIREN) embedding elastodynamic wave equations for reconstructing sparse ultrasonic guided wavefield data in the field of non-destructive testing. By capturing high-frequency oscillations, PI-SIREN significantly outperforms data-driven baselines and standard PINNs in ultrasonic data-scarce wavefield reconstruction. | ||||
| Reserve Paper | 15.9.R |
REDUCING OPERATIONAL DISRUPTION: DECISION-AUTOMATION FOR CBM UNDER UNCERTAINTY F Enayatollahi, Mount Royal University, Canada | |||||
| additional information (interactive) | 15.9.R |
REBUILDING AGRICULTURAL STATISTICS IN POST-WAR SUDAN: A STRATEGIC FRAMEWORK FOR RECOVERY AND RESILIENCE MohamedElamin Ahmed, Sudan Central Bureau of Statistics, Sudan | |||||
| additional information (interactive) | 15.9.R |
PARAMETER INVERSION ALGORITHM FOR AERO-ENGINE ? -PHOTON FLOW FIELD IMAGES BASED ON UNET-GAN ARCHITECTURE L. Hou, Nanjing University of Aeronautics and Astronautics, China | |||||
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| 09:15 | 09:40 | 1.10.1 |
EXPLAINABILITY AT ALL LEVELS OF SYSTEM DEVELOPMENT: INSIGHTS FROM THE DESIGN OF INTELLIGENT SYSTEMS IN AVIATION J Würfel¹, B Djartov¹, M Friedrich¹, S Schog¹, A Papenfuss¹; ¹German Aerospace Center (DLR), Germany This paper proposes a multi-level approach to operational explainability in aviation AI systems, combining bottom-up model design with top-down human-centered interface development. Using civil and military use cases, a simulator study shows that combining factor ratings with feature contributions improves perceived explainability and decision support effectiveness. | ||||
| 09:40 | 10:05 | 1.10.2 |
APPLYING HUMAN-CENTERED DESIGN: A PRACTICAL CASE STUDY OF A PILOT DIGITAL ASSISTANT A. Mayima, Penrose Business Centre, Ireland This project applies a human-centered design (HCD) methodology to develop a TRL4 Pilot Digital Assistant (PDA) for managing flight strategy and external communications. Lessons highlight challenges in balancing transparency and usability, adapting HCD for training vs. operational use, addressing diverse user preferences, and reconciling iterative design with time-sensitive development. | ||||
| 10:05 | 10:30 | 1.10.3 |
OFFLINE MULTIMODAL LARGE LANGUAGE MODELS FOR DECISION SUPPORT IN AIR OPERATIONS J. Dantas, Instituto de Estudos Avançados, Brazil Air operations rely on complex rules, established procedures, and time-critical analysis under limited connectivity and strict security constraints. In such environments, analysts must combine written doctrine with visual products such as satellite imagery and reconnaissance data, often without access to external computing resources. This paper investigates offline multimodal large language models as decision support tools, deployed in segregated and restricted environments to accept both text and image inputs and provide source-grounded access to doctrinal knowledge through natural language interaction. The multimodal interface enables queries that directly relate procedures to operational imagery. We describe a modular architecture suitable for operation without Internet connectivity and an evaluation methodology based on simulated operational exercises with military analysts, focusing on workload and perceived usefulness in operational and training contexts. | ||||
| 10:30 | 10:55 | 1.10.4 |
AI IN THE COCKPIT, A JARVIS STORY R. De Masellis, Collins Aerospace, Ireland In this paper, we present a prototype of a commercial pilot digital assistant, developed by Collins Aerospace in the context of the “JARVIS” project, co-funded by the European Union through the SESAR 3 Joint Undertaking programme. The focus of the report is not on the technical details, but rather on: (i) the considerations that lead the team to undertake a specific solution; (ii) the challenges faced and (iii) the outcomes and future directions. | ||||
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| 09:15 | 09:40 | 3.10.1 |
AERODYNAMIC SHAPE OPTIMISATION USING A STRUCTURAL MODAL PARAMETERISATION METHOD A. R. Wang, Boeing Aerostructures Australia, Australia A novel framework combining modal parameterisation and user-preference swarm optimisation for efficient aerodynamic shape tailoring under geometric constraints. Compared to traditional methods, it reduces design variables and enables flexible, physically realistic aircraft surface design. Applications to serpentine intake ducts and fuselage shaping demonstrate improved performance and robustness. | ||||
| 09:40 | 10:05 | 3.10.2 |
MODELLING COUPLED ON-BOARD SYSTEMS AND THEIR TOP-LEVEL IMPACT ON FIGHTER AIRCRAFT DESIGN E. Espinosa-Juárez, Linköping University, Sweden The entrance of More Electric Aircraft (MEA) architectures represents a paradigm shift that enables new design degrees of freedom and higher levels of integration. However, these On-Board Systems (OBS) have effects where the change on a single component has effects that propagate to other subsystems. Analyzing OBS in isolation during the aircraft conceptual design process fails to capture these cascading effects and risks achieving an unbalanced overall aircraft architecture. This study aims to model and understand on-board systems interactions and cascading effects in a fighter aircraft and their impact on top-level aircraft measures of performance. To achieve this, an Architecture and an Analysis Architecture model are developed using SysML v2. The Architecture model represents the physical aircraft, and the Analysis Architecture represents the models needed for its simulation. A process model is also presented to integrate OBS sizing with overall aircraft sizing. Analyzing and sizing OBS early in the design stage considering cascading effects enables more balanced architectures, improving trade-off decision making, and reduced risk of costly late-stage redesign. | ||||
| 10:05 | 10:30 | 3.10.3 |
MULTI-FIDELITY BAYESIAN NEURAL NETWORKS FOR STEALTH/AERODYNAMIC DATA FUSION METHOD J. He, China This study introduces a multi-fidelity Bayesian neural network to overcome the accuracy-efficiency trade-off in stealth simulation. By fusing data of varying fidelity and using variational inference for uncertainty estimation, it achieves higher predictive accuracy and more reliable uncertainty quantification than CoKriging, offering an efficient tool for multidisciplinary aircraft optimization. | ||||
| 10:30 | 10:55 | 3.10.4 |
FAST INTEGRATED EVALUATION AND OPTIMIZATION DESIGN METHOD FOR AERODYNAMIC AND STEALTH PERFORMANCE OF INLETS WITH ENTRANCE GRIDS J.-W. He, Northwestern Polytechnical University, China A fast integrated evaluation and optimization method for aerodynamic and stealth performance of S-shaped inlets with entrance grids is proposed. Neural-network-based surrogate models are developed to predict both global performance and local flow features, enabling efficient aerodynamic–stealth integrated design with significantly reduced computational cost. | ||||
| Reserve Paper | 3.10.R |
CONCEPTUAL DESIGN AND AERODYNAMIC ANALYSIS OF A GENERIC FUTURE FIGHTER AIRCRAFT P.-D. Bravo-Mosquera, EESC-USP, Brazil | |||||
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| 09:15 | 09:40 | 5.10.1 |
AERODYNAMICS OF OPEN FAN INTEGRATION FOR THE DLR-25 CONCEPT I.J. Pawlikow, DLR, Germany Open Fan propulsion systems for future transport aircraft cause strong aerodynamic wing–propulsor interference. This paper investigates installation effects and various engine positions using a SMR aircraft with a high aspect ratio wing in conventional and a gull-wing configuration for cruise condition. | ||||
| 09:40 | 10:05 | 5.10.2 |
STUDY OF THE AERODYNAMIC INTERFERENCE OF STRUT-BRACED WINGS WITH DISTRIBUTED PROPELLERS n/a Fossati, Unniversity of Strathclyde, United Kingdom This work presents a numerical study of the aerodynamic interaction between a propeller and the strut-wing junction region of a next-gen aircraft configuration featuring large aspect ratio wing and distributed hybrid-electric propellers. The study aims to highlight the key flow mechanisms that impact the aerodynamic loads acting on the wing-strut area as a consequence of the presence of a spinning propeller. The study will also aim to assess quantitatively the impact on Lift and Drag and overall aerodynamic efficiency. | ||||
| 10:05 | 10:30 | 5.10.3 |
UNSTEADY EXERGY ANALYSIS OF A HIGHLY LOADED HIGH-SPEED ROTOR UNDER ROTATING STALL C Paillard, ISAE-SUPAERO, France The work looks after validating exergy balance in Rotating Reference Frames (RRF) for turbomachinery test cases thanks to an open-source tool. Similar trends compared to the literature are achieved in a RRF steady case while the tool have been succesfully used for unsteady exergy analysis. | ||||
| 10:30 | 10:55 | 5.10.4 |
COMPARATIVE ANALYSIS OF DIFFERENT NUMERICAL SIMULATION METHODS FOR PROPELLER SLIPSTREAM J.-W He, Northwestern Polytechnical University, China This paper employs an unsteady actuator blade method(ABM) embedded in CFL3D code. ABM makes that complicated grid generation techniques are no longer required to describe the real propeller blade. It is worth well to evaluate the detailed differences of slip stream simulated by full blade method and ABM approach, especially the vortex concentration and fluctuation features. | ||||
| Reserve Paper | 5.10.R |
INVESTIGATION AND ONE-DIMENSIONAL MODELING OF THE DUAL-ROTOR GEROTOR PUMP AT HIGH ALTITUDES SZC Su, Northwestern Polytechnical University, China | |||||
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| 09:15 | 09:40 | 6.10.1 |
COMPARATIVE ATMOSPHERIC MEASUREMENTS USING UAV-MOUNTED ULTRASONIC ANEMOMETER AND DOPPLER LIDAR N Gavrilovic, ISAE-SUPAERO, France This paper investigates different systems for atmospheric probing. A portable ultrasonic anemometer, integrated with a GPS, wireless data transmission, and data acquisition systems, is mounted on a quadcopter platform. This configuration provides a mobile measurement unit capable of free movement in the atmosphere, delivering measurements of airspeed, temperature, pressure, humidity, air density, and the system’s physical orientation. In parallel, a ground-based Doppler LIDAR system (WindCube) is used as a reference, providing 20 simultaneous measurements at arbitrarily selected heights between 40 and 300 meters above ground level. | ||||
| 09:40 | 10:05 | 6.10.2 |
CONCURRENT UNSTEADY SURFACE PRESSURE FIELD AND SCHLIEREN MEASUREMENTS OF THE COMMON FRONT END HYPERSONIC GEOMETRY IN TRANSONIC CONDITIONS C.W Marshall, Defence Science and Technology Group, Australia The transonic performance of hypersonic vehicles is not well understood. An experimental test campaign has been designed in the DSTG Transonic Wind Tunnel for the Common Front End geometry to demonstrate a new concurrent reflected background oriented schlieren and Unsteady Pressure Sensitive Paint capability. Analysis will include on-board instrumentation and 6DOF force balance measurements. | ||||
| 10:05 | 10:30 | 6.10.3 |
FFECT OF THE FST ON THE BOUNDARY LAYER, THE WALL-PRESSURE FLUCTUATIONS, AND THE TRAILING-EDGE NOISE OF AIRFOILS L Botero-Bolivar, Universidad Industrial de Santander, Colombia This paper investigates how free-stream turbulence interacts with turbulent boundary layers under non-zero pressure gradients and its impact on airfoil noise. Velocity fluctuations, wall-pressure spectra, spanwise coherence, convection velocity, and far-field noise were measured on NACA 63018 and 0008 airfoils at varying turbulence levels, angles of attack, and inflow velocities. Boundary-layer properties strongly control turbulence penetration and trailing-edge noise, which increases across frequencies. | ||||
| additional information (interactive) | 6.10.R |
ANALYSIS OF A DUAL AIR DATA AND MULTI-HOLE PRESSURE PROBE BOOM D.-T Rajeepan, School of Aerospace, Mechanical and Mechatronics Engineering, Australia | |||||
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| 09:15 | 09:40 | 7.10.1 |
SIMULATION-BASED AUTOPILOT TUNING FOR FIXED-WING UAVS C.-V. Boruga, Linkoping University, Sweden This study evaluates the feasibility of using a commercially available flight simulator for initial control loop tuning of fixed-wing UAVs equipped with ArduPilot. Subscale flight tests are used to demonstrate that X-Plane 12 can provide a low-cost, low-risk approach to preliminary autopilot tuning, reducing development risk and cost for large UAVs. | ||||
| 09:40 | 10:05 | 7.10.2 |
A 3D-PRINTED TESTBED FOR FLIGHT CONTROL SYSTEM RESEARCH. D Lundström, Sweden A 3D?printed subscale fighter?type aircraft has been developed as a low?cost testbed for flight?control?system research. The platform integrates a custom airframe, modular FCS hardware and supporting sensors, with initial flight?test planned for spring 2026. | ||||
| 10:05 | 10:30 | 7.10.3 |
SLIPSTREAM MODELING AND CONTROL ALLOCATION OF A DISTRIBUTED HETEROGENEOUS ELECTRIC PROPULSION TANDEM-WING UAV Y.-H. Xie, China To address aero-propulsive coupling in DHEP tandem-wing UAVs, this paper establishes a finite-dimension slipstream model validated by experiments. A control allocation scheme is proposed. Simulations confirm high model accuracy and effective suppression of pitch fluctuations during high-angle takeoff. | ||||
| 10:30 | 10:55 | 7.10.4 |
RESEARCH ON FLIGHT DYNAMICS AND CONTROL CHARACTERISTICS OF MULTI-UAVS WINGTIP-LINKED FLIGHT R. Wang, Northwestern Polytechnical University, P.R.China, China Focusing on the flight dynamics and control of wingtip-linked multi-UAVs, this study systematically investigates dynamic modeling, aerodynamic analysis, modal characteristics, behavioral evolution, and flight control. A universal theoretical framework applicable to arbitrary unit numbers, hinge stiffness, and flight configurations is established and validated through flight tests. | ||||
| Reserve Paper | 7.10.R |
EXPERIMENTAL FLIGHT DYNAMICS AND CONTROL OF AN AGILE FIXED-WING UAV USING HYBRID ONBOARD & OFFBOARD CONTROL Y. Huang, the University of Sydney, Australia | |||||
| Reserve Paper | 7.10.R |
MODEL-PREDICTIVE-CONTROL-BASED TRAJECTORY GENERATION ENHANCED WITH REINFORCEMENT LEARNING FOR FORMATION MANEUVERING A. Rossi, Airbus Defence and Space GmbH, Germany | |||||
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| 09:15 | 09:40 | 8.10.1 |
STRENGTH DESIGN AND TEST VERIFICATION OF AIRCRAFT SUSPENSION TRACK CONNECTION ZONE K. Yin, China Based on the general commercial software MSC.NASTRAN, this paper simulates the common frame structure of aircraft fuselage, and uses the nonlinear finite element method to simulate the structure, and obtains the load-displacement curve from the initial load deformation to the post-buckling failure of the structure under complex working conditions. | ||||
| 09:40 | 10:05 | 8.10.2 |
INTERNATIONAL RESEARCH AND TECHNOLOGY INFRASTRUCTURE DATA BASES IN AVIATION R. Degenhardt, DLR, Germany Infrastructure databases are essential for providing transparent access to facilities, capabilities and data worldwide. They support collaboration, avoid duplication of efforts and enable efficient planning of experiments, fostering innovation, safety and sustainability across the global aviation research community. The paper presents 2 available data bases from EREA and IFAR and future strategy plannings of the EU project STARLET. | ||||
| 10:05 | 10:30 | 8.10.3 |
DIGITAL-PHYSICAL SYNERGY: FEM-DRIVEN CERTIFICATION OF AT-5 AND AT-6 AIRCRAFT M. Kowalski, Warsaw University of Technology, Poland The paper discusses FEM-driven certification of AT-5 and AT-6 aircraft. It focuses on how numerical models enabled rapid error correction, validated mid-design changes, and supported flight-clearance static tests under EASA CS-23. The study demonstrates that FEM-test synergy is essential for efficient and safe aircraft structural substantiation. | ||||
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| 09:15 | 09:40 | 9.10.1 |
AN AEROELASTIC DYNAMICS MODELING METHOD FOR INSECT-INSPIRED FLEXIBLE FLAPPING-WING UAV Y Guo, Northwestern Polytechnical University, China To meet the demand for efficient design of insect-inspired flexible flapping-wing unmanned aerial vehicles, this study proposes a high-precision and efficient theoretical aeroelastic model. Firstly, the kinetic energy of the flapping wing is decomposed into the kinetic energy of the leading-edge bar, root bar, and membrane, while the potential energy includes rotational, bending, and twisting potential energy. Combined with a dual-rigid-body linkage airframe model, a longitudinal dynamic equation with 9 generalized coordinates is established. Based on a quasi-steady aerodynamic model, the instantaneous aerodynamic force is decoupled into four components: translational, rotational, translation-rotation coupling, and added mass load. The rationality of the proposed method is verified by comparing its results with those from a high-precision computational structural dynamics/computational fluid dynamics (CFD/CSD) coupled model built on the ANSYS platform and experimental data reported in relevant literature. Computational performance tests show that the model only requires 21 minutes for a single-core computation of 5 flapping cycles. With 40-core parallel computing, it can simultaneously complete simulations of 40 groups of parameters within 21 minutes, significantly reducing computational resources and time costs compared to the traditional CSD/CFD coupled model (which takes approximately 2 weeks). This model provides an efficient tool for the parametric design of FFW UAVs and supports the rapid iteration of optimization schemes for lift, efficiency, and stability. | ||||
| 09:40 | 10:05 | 9.10.2 |
ENABLING FORWARD SWEPT WING DESIGNS J E Cooper, University of Bristol, United Kingdom In this paper, three design approaches will be considered for the design of forward swept wings: composite tailoring, floating folding wing tips and wing tip rake. A sizing process will be developed to evaluate the aircraft performance and fuel burn across the design flight envelope, as well taking flutter and divergence boundaries into account. Parametric studies will be performed using MSC NASTRAN using a baseline model of an A320-like sized aircraft with extended 45m wingspans to achieve an Aspect Ratio (AR) of 17. Conclusions will be drawn as to the most promising approach for forward swept high aspect ratio wing designs . | ||||
| 10:05 | 10:30 | 9.10.3 |
DEVELOPMENT OF CONTROL LAWS FOR ENHANCED PERFORMANCE AND AEROELASTIC STABILITY OF EVTOL AIRCRAFT P. Kantzidis, RMIT University, Australia This work proposes efficient control laws for electric aircraft with variable-pitch propellers to reduce electrical power consumption and improve aeroelastic stability. Numerical studies are performed on a scaled propeller–pylon model, using LPV-based control strategies validated through nonlinear simulations. | ||||
| 10:30 | 10:55 | 9.10.4 |
AEROSERVOELASTIC MODELING AND ANALYSIS OF THRUST VECTORING LAUNCH VEHICLE CONSIDERING RIGID-ELASTIC INTERACTION W.-L. Lei, China; Y.-S. Gu, China; Z.-C. Yang, China A modeling and analysis study has been conducted on the rigid–elastic interacting aeroservoelastic system of a slender-body launch vehicle equipped with thrust vector. The inertial forces, thrust, and moments generated by the nozzle are taken into account, leading to the derivation of the elastic vibration equations and attitude motion equations of the vehicle under thrust vector nozzle control. Based on this foundation, the paper considers the coupling effects among nozzle thrust vectoring, structural elasticity, aerodynamics, and the servo flight control system, and establishes a simulation and analysis model of the aeroservoelastic system for slender-body vehicles with thrust vector. The model yields the large-loop transfer characteristics of the system. For a typical thrust vectoring rocket example, the paper analyzes the transfer characteristics of its aeroservoelastic system and compares them with the results from classical aeroservoelastic modeling methods, thus validating the correctness of the proposed approach. | ||||
| Reserve Paper | 9.10.R |
AEROELASTIC TAILORING OF A SBW USING AFP TOW STEERED COMPOSITES TIANQIANG HUANG¹, Touraj Farsadi, Adana Alparslan Turkes Science and Technology University, Turkey; Wesley Cantwell¹, Rafic Ajaj¹; ¹Khalifa University, China | |||||
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| 09:15 | 09:40 | 10.10.1 |
ADVANCING CRYOGENIC COOLING AND ELECTRICAL DISTRIBUTION SYSTEMS FOR FUTURE HYDROGEN-POWERED AVIATION D. Kierbel, AIRBUS NL, Netherlands Led by Airbus and Dutch partners, ICEFlight advances hydrogen aviation by developing cryogenic cooling and electrical systems. The project leverages liquid hydrogen's "dual use" as fuel and coolant to boost powertrain efficiency. By establishing test facilities at Royal NLR, ICEFlight aims to validate technologies critical for decarbonized aviation. | ||||
| 09:40 | 10:05 | 10.10.2 |
EXPERIMENTAL AND NUMERICAL INVESTIGATION OF HYDROGEN FLAMES UNDER COLD INJECTION CONDITIONS F. Thilker, FH JOANNEUM GesmbH, Austria An experimental and numerical investigation of under-expanded hydrogen jet flames at cryogenic injection temperatures for aircraft engine applications is shown. Experiments are conducted in a coaxial non-premixed combustor using (non-) cooled hydrogen, with flame visualization via UV OH* imaging. Additional CFD simulations reproduce experimental trends and assess alternative injector geometries. | ||||
| 10:05 | 10:30 | 10.10.3 |
REAL-TIME EMULATION TESTBENCH FOR FUEL-CELL/BATTERY HYBRIDIZATION IN HYDROGEN-ELECTRIC AVIATION G. Marinaro¹, L. Garbarino¹, M. Inverno¹, C. Serpico¹, A. Bono¹, G. Malaponte¹, A. Pagano¹; ¹Italian Research Centre - CIRA, Italy A three-emulator, power-domain PHIL/HIL bench enables closed-loop validation of hydrogen-electric energy management under realistic mission transients and fault scenarios. Its stepwise swap from emulated to real fuel-cell/battery hardware offers a repeatable, risk-reduced integration path and a transferable method for automotive and microgrid hybrid power systems. | ||||
| 10:30 | 10:55 | 10.10.4 |
HEAT EXCHANGER MODELLING METHODS FOR HYDROGEN POWERED AERO ENGINES DURING THERMODYNAMIC CYCLE DESIGN F.-H. Görtz, German Aerospace Center, Germany This work compares three heat exchanger modelling methods that can be used during cycle analysis or preliminary design of an aero engine for hydrogen combustion. All three methods are used in literature for this purpose but there is no overview available. This work will provide guidance for selecting an appropriate modelling method by pointing out advantages, disadvantages and additional information of the respective method. | ||||
| Reserve Paper | 10.10.R |
AN OPTIMAL POWER MANAGEMENT POLICY FOR HYDROGEN BASED HYBRID AERO ENGINES F. Pak, Eindhoven University of Technology, Netherlands | |||||
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| 09:15 | 09:40 | 11.10.1 |
PHYSICS-INFORMED LSTM-BASED LONGITUDINAL STALL AEROFYNAMIC MODELING FRAMEWORK OF CIVIL AIRCRAFT USING FLIGHT TEST DATA J.-W. Wang, Beihang University, China A longitudinal stall aerodynamic modeling framework of civil aircraft based on physic-informed LSTM using flight test data is proposed. Partially high-accuracy aerodynamic parameter identified from flight test data are incorporated to compute physics-informed loss, which is fused with prediction error in loss function. The modeling framework is validated using flight test data of a civil aircraft. | ||||
| 09:40 | 10:05 | 11.10.2 |
AERO–PROPULSIVE MODELING AND PRELIMINARY FLIGHT TESTING OF INDIVIDUAL THRUST CONTROL FOR A DISTRIBUTED ELECTRIC PROPULSION DEMONSTRATOR G.F. Filippoli, Politecnico di Milano, Italy This work demonstrates, through flight testing, how Individual Thrust Control changes the dynamics of a DEP aircraft and requires dedicated aero–propulsive models. The proposed framework enables realistic simulation, system identification and control allocation for future distributed electric and hybrid aircraft. | ||||
| 10:05 | 10:30 | 11.10.3 |
PHYSICS-INFORMED MACHINE LEARNING FOR FLIGHT DYNAMICS IDENTIFICATION OF THE SAAB 340 USING FLIGHT TEST DATA M Alam, Cranfield University, United Kingdom A physics-informed machine learning framework is applied to identify the short-period longitudinal dynamics of the Saab 340 using flight test data. A hybrid neural architecture estimates reduced-order model parameters constrained by the equations of motion. Automated hyperparameter optimisation using Siemens HEEDS improves prediction accuracy relative to manual tuning, demonstrating enhanced modelling fidelity and workflow efficiency. | ||||
| 10:30 | 10:55 | 11.10.4 |
EVALUATION OF STALL BEHAVIOUR OF T-TAIL AIRCRAFT: MODELING AND FLIGHT TEST MH Lowenberg, University of Bristol, United Kingdom This paper describes ongoing activity to improve the understanding and modeling of flight mechanics in the stall region for T-tailed aircraft. It is based on wind tunnel and free-flight tests of the NASA GTT, as well as NASA data for the configuration. This work aims to inform the challenge of modeling nonlinear separated flow behaviour by comparing various model responses with flight tests. | ||||
| Reserve Paper | 11.10.R |
HANDLING QUALITIES ASSESSMENTS IN A FIXED-BASED AND FULL FLIGHT SIMULATOR FOR A FLEXIBLE TRANSPORT AIRCRAFT B. Boche, Berlin Institute of Technology, Germany | |||||
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| 09:15 | 09:40 | 12.10.1 |
MATERIAL-STRUCTURE INTEGRATED LASER ADDITIVE MANUFACTURING OF HIGH-PERFORMANCE PARTS FOR AERONAUTICAL APPLICATIONS D.D. Gu, Nanjing University of Aeronautics and Astronautics, China We report recent progress and outlook in material–structure integrated laser additive manufacturing for aeronautical metal parts. By coupling multi-material layouts, architected structures and tailored laser processing, we probe energy–matter interactions and the thermodynamic–dynamic origins of microstructure and properties, aiming for disruptive, multifunctional aerospace performance. | ||||
| 09:40 | 10:05 | 12.10.2 |
RESEARCH ON A DIGITAL-DRIVEN LIFE-CYCLE SUPPLY CHAIN MANAGEMENT SYSTEM FOR COLLABORATIVE AIRCRAFT DEVELOPMENT J. Chai, AVIC The First Aircraft Institute, , China Based on systems engineering theory, a high-confidence digital-driven framework and processe was constructed for the entire lifecycle collaborative development of aircraft supply chains. A typical case was showed to demonstrate the processe of supplier requirements, sourcing, and dynamic control. The method can improve supplier management levels for aircraft project effectively. | ||||
| 10:05 | 10:30 | 12.10.3 |
RE-THINKING END OF LIFE AIRCRAFT INTERIORS THROUGH CO-DESIGN AND REPURPOSING TJH Mahr, University of Melbourne, Australia This paper explores alternative end of life pathways through a circular economy and repurposing lens using airline passenger seats as a case study, focusing on co-designed reuse strategies for decommissioned aircraft components. The study demonstrates how aerospace components can be recontextualised beyond traditional recycling streams, extending service life and enhancing value retention. | ||||
| 10:30 | 10:55 | 12.10.4 |
A FORMALLY VERIFIED, EVENT-DRIVEN ROS SCADA SUPERVISORY SYSTEM ARCHITECTURE FOR SAFETY-CRITICAL ROBOTIC CELLS IN AEROSPACE MANUFACTURING F. S. Braga, Aeronautics Institute of Technology (ITA), Brazil This work presents a structured approach to design and validate supervisory control for collaborative robotic cells,based on a layered ROS architecture modeled using timed automata.By combining event-driven supervision with formal verification,it supports safer behavior at the design stage and reduces integration risks.The approach is applicable to other industrial domains and embedded platforms. | ||||
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| 09:15 | 09:40 | 13.10.1 |
FEASIBILITY STUDY ON LANDING CAPACITY ENHANCEMENT AT CONGESTED AIRPORTS VIA ARRIVAL TRAJECTORY ANALYSIS R. Kajikawa, Graduate School of Systems Design, Tokyo Metropolitan University, Japan This study examines landing capacity enhancement at congested airports using arrival trajectory analysis. Focusing on Point Merge System operations at Haneda Airport, actual flight data are analyzed to evaluate altitude and airspeed variability. The results show that reducing trajectory variability can safely shorten landing intervals and improve runway capacity. | ||||
| 09:40 | 10:05 | 13.10.2 |
AN AUGMENTED AIRPORT MODEL FOR GROUND OPERATIONS ANALYSIS: A CASE STUDY OF NARITA INTERNATIONAL AIRPORT S. X. Ng, The University of Tokyo, Japan This work presents an augmented airport model combining a 3D-printed physical representation with projected simulations of ground operations. The proposed platform aims to provide an intuitive means for evaluating and communicating the effectiveness of taxiing optimization strategies, such as single engine taxi (SET), in reducing fuel consumption and emissions. | ||||
| 10:05 | 10:30 | 13.10.3 |
A COMPARISON OF TRAJECTORY-BASED OPERATIONS IN UNITED STATES AND EUROPE IN SUPPORT OF GLOBAL HARMONIZATION G Enea, MIT Lincoln Laboratory, United States This paper compares the implementation of Trajectory-Based Operations (TBO) in the United States and Europe to support global harmonization. ?TBO, introduced in the ICAO Document 9854 (2005), aims to improve operational predictability, flexibility, strategic planning, and reduce uncertainty in air traffic management. ? | ||||
| 10:30 | 10:55 | 13.10.4 |
AVIATION NETWORK MODELLING IN THE CONTEXT OF SMALL ISLAND DEVELOPING STATES: CONSTRAINTS, LIMITATIONS AND OPPORTUNITIES FOR AVIATION IN FIJI P.F.D. Bowes, Australia Fiji's archipelagic geography and dispersed population shape aviation network performance. Using integrated topology, geospatial and demographic models, this study identifies infrastructure, environmental and operational constraints on capacity, then evaluates management and infrastructure options to improve connectivity, efficiency and resilience. | ||||
| Reserve Paper | 13.10.R |
ATTRIBUTION OF ATFM DELAY AS A RESULT OF A GROUND DELAY PROGRAM (GDP) C.A. Tait, Airservices Australia, Australia | |||||
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| 09:15 | 09:40 | 14.10.1 |
PROPAGATING SAFETY ASSESSMENT RESULTS FOR SYSTEM ARCHITECTURE CANDIDATES IN MBSE S. M. Lübbe, German Aerospace Center (DLR), Germany Efficient, connected safety and design processes help to improve entry into service time of new aircraft and technologies. We demonstrate the integration of PSSA results into a combined MBSE and safety analysis model. Results from safety analysis tool are connected to upstream and downstream process steps. This significantly improves readability and traceability of the safety analysis and design. | ||||
| 09:40 | 10:05 | 14.10.2 |
MODEL-BASED FUNCTIONAL HAZARD ASSESSMENT BASED ON ARP4761A USING SYSML V1 AND SYSML V2 M. Schäfer, German Aerosapce Center (DLR), Germany This work presents a model-based Functional Hazard Assessment (FHA) approach based on the ARP4761A and implemented using the Systems Modeling Language (SysML). A SysML v1 profile and a corresponding SysML v2 library are developed and described. The applicability and benefits of the proposed modeling approach are demonstrated using a flight control system. | ||||
| 10:05 | 10:30 | 14.10.3 |
ARCADIA VIEWPOINTS FOR ENTERPRISE ARCHITECTING COMPARISON WITH UAF VIEWS THROUGH AN EVTOL COMPANY OPERATION MODELING R.M. Machado Cezar, Technological Institute of Aeronautics (ITA), Brazil This work validates a method to model complex Urban Air Mobility ecosystems by bridging open-source Capella software with the industry-standard Unified Architecture Framework (UAF). It provides a reusable blueprint for integrating eVTOLs into cities. This approach enables the alignment of technical engineering with high-level enterprise strategy using accessible, cost-effective tools. | ||||
| 10:30 | 10:55 | 14.10.4 |
MANEUVER- AND DELAY-ROBUST DISTRIBUTED SATELLITE SSA VIA SPATIO-TEMPORAL GRAPH FORECASTING H.-M. Rizk, The University of Osaka, Japan The rapid growth of LEO constellations is turning Space Situational Awareness (SSA) into a real-time bottle- neck: conjunction screening must be refreshed frequently, yet catalog updates arrive with latency and gaps, and maneuvers can abruptly invalidate propagator-only predictions, destabilizing closest-approach estimates and risk ranking. We present a distributed SSA framework designed to remain reliable under delayed and incomplete information by combining interaction-aware trajectory forecasting with uncertainty-calibrated triage. Inputs are time-aligned inertial state sequences derived from TLE/SGP4 propagation, and outputs are multi- step forecasts of state means together with calibrated uncertainty. We model SSA as a dynamic spatio- temporal interaction graph whose edges encode relative motion and risk-relevant neighborhoods informed by CPA/TCA. A spatio-temporal graph forecaster predicts short-horizon trajectories, and candidate pairs are ranked using an uncertainty-aware score to produce a stable top-K triage list. Distributed execution exchanges only compact boundary summaries (forecast states, uncertainty, and timestamps) rather than raw catalogs, and robustness is evaluated under message delay and loss. In a 90-day catalog-driven test with 4,500 RSOs, our method reduces 60-min position RMSE by 33% (2.84?1.91 km) and improves triage quality by 27% in Re- call@50 (0.62?0.79), 27% in NDCG@50 (0.55?0.70), and 39% in PR-AUC (0.41?0.57). Under distributed delay/loss (? = 3, p = 0.3), Recall@50 remains 0.73 with 7.6 kB/update/node. | ||||
| Reserve Paper | 14.10.R |
MODEL-BASED SYSTEMS ENGINEERING APPLICATION USING FLIGHT-TEST DATA FROM THE ACS-100 SORA AIRCRAFT L. H. J. Machado, UFMG, Brazil | |||||
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| 08:50 | 09:15 | 15.10.1 |
ON THE FEASIBILITY OF MACHINE LEARNING-BASED DETECTION OF AIRCRAFT LIGHTNING STRIKE RISK AREAS E Yoshikawa, The University of Osaka, Japan Aircraft lightning can disrupt flight operations. We apply a support vector machine to radar-derived features to detect lightning strike risk areas. The proposed method achieves an 86% probability of detection and a 39% false alarm rate, demonstrating the feasibility of machine-learning-based risk detection for operational airline support. | ||||
| 09:15 | 09:40 | 15.10.2 |
ONTOLOGY-BASED SENSOR HEALTH MONITORING: A DYNAMIC ONTOLOGY-BASED FAULT DETECTION AND CLASSIFICATION FOR TIMESERIES DATA C. Klein, Deutsches Zentrum für Luft- und Raumfahrt, Germany We present an ontology-based Sensor Health Monitoring method for predictive maintenance, validated on Falcon 2000LX data. By integrating system metadata and simulation models, it detects sensor faults deterministically, enabling uncertainty quantification and expert insight. The approach is scalable to any asset with structured metadata, offering broad relevance beyond aerospace. | ||||
| 09:40 | 10:05 | 15.10.3 |
ACCELERATED EXPERIMENTAL INVESTIGATION OF ENVIRONMENTALLY ASSISTED CRACKING IN AA7085 J. P Rogers, RMIT University, Australia This research explores an accelerated test method to induce EAC in AA7085 test coupons and investigates the contributing factors to EAC initiation and growth in AA7085. Pre-treatment of the test coupons was critical in achieving an accelerated testing program, along with a bespoke environmental chamber system for in-situ environmental control during tensile loading. | ||||
| 10:30 | 10:55 | 15.10.4 |
INFRARED AND GREEN FEMTOSECOND LASER PAINT STRIPPING ON AIRCRAFT COATINGS: EXPERIMENTAL AND NUMERICAL ASSESSMENT S. Zhu¹, J. Panta¹, R. Yang¹, S. Zhang, Univeristy of Technology Sydney , Australia; ¹Western Sydney University, Australia Femtosecond laser paint stripping enables precise removal of composite aircraft coatings. This study combines single-pulse experiments and numerical simulations to reveal how wavelength (515?nm vs. 1030?nm) affects ablation thresholds and substrate damage. Results provide physics-based guidance for efficient, damage-free paint stripping in aerospace MRO and other composite industries. | ||||
| additional information (interactive) | 15.10.R |
LIGHTWEIGHT AND ROBUST REAL-TIME DETECTION SYSTEM FOR AIRCRAFT SKIN DEFECTS UNDER COMPLEX UAV INSPECTION CONDITIONS Wenqing Yang¹, Jianlin Xuan¹; ¹Northwestern Polytechnical University, China | |||||
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| 11:00 | 11:25 | 1.11.1 |
COMBINED IMPACT OF JET STREAM AND TURBULENCE ON LONG-TERM TRANS-OCEANIC FLIGHT ROUTES J.-H. Kim, Seoul National University, South Korea In this study, additional time required to avoid CAT has grown substantially that it negates and even reverses the wind-optimal efficiency gains for the safest routes. This rising cost is driven by a significant increase in CAT, which disproportionately affects eastbound flights. Our findings highlight the need for integrated approaches to assess aviation’s evolving risks in a changing climate. | ||||
| 11:25 | 11:50 | 1.11.2 |
PROGRESS IN AIRCRAFT-BASED METEOROLOGICAL OBSERVATIONS T.F. Rahmes, The Boeing Company, United States A promising solution to address evolving challenges of hazardous weather events is through sharing of real-time airborne meteorological observations. The Boeing Company provides airline customers with a baseline airplane capability for cross-model (777, 787, 737 MAX, 777X) real-time weather and turbulence observations. Customer benefits and use of such data in research will be discussed. | ||||
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| 11:00 | 11:25 | 2.11.1 |
A HOLISTIC APPROACH TO ENABLE ADVANCED AIR MOBILITY FOR REGIONAL, RURAL AND REMOTE AUSTRALIA P Burka, Swinburne University of Technology, Australia Advanced Air Mobility (AAM) will revolutionise air operations. It will enable alternative passenger and cargo transportation, provide the option of point-to-point delivery, and extend accessibility and connectivity for the benefit of society. Nevertheless, this progress is neither guaranteed nor without obstacles. This paper will outline the challenges, discuss their impact on AAM implementation, and suggest strategies to achieve the desired outcomes. | ||||
| 11:25 | 11:50 | 2.11.2 |
THE ROLE OF COMMUNITY ENGAGEMENT IN INTRODUCING UNMANNED AERIAL VEHICLE TECHNOLOGY: A RAPID SCOPING REVIEW J. Porter, Australia THE ROLE OF COMMUNITY ENGAGEMENT IN INTRODUCING UNMANNED AERIAL VEHICLE TECHNOLOGY: A RAPID SCOPING REVIEW | ||||
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| 11:00 | 11:25 | 3.11.1 |
ROBUST HIGH-FIDELITY DATASET-BASED AEROELASTIC OPTIMIZATION FOR AIRCRAFT DESIGN M. Maier¹, K. Sørensen-Libik², Ö. Petersson², C. Breitsamter¹; ¹Technical University of Munich (TUM), Germany ;²Airbus Defence and Space GmbH, Germany High-fidelity aeroelastic dataset-based optimization leverages the sets of load conditions from the aerodynamic analysis to perform simultaneous structural analysis for the full flight envelope. This reduces structural design risks significantly and enables robust optimizations, including the effect of elasticity on performance as well as stability and control in the aircraft design process. | ||||
| 11:25 | 11:50 | 3.11.2 |
LARGE-SCALE AEROSTRUCTURAL OPTIMISATION WITH MODAL AND NONLINEAR BUCKLING CONSTRAINTS ASSISTED BY ALGORITHMIC DIFFERENTIATION L Scalia, Universidad Carlos III de Madrid, Spain The work presents a high-fidelity aerostructural optimisation framework, using algorithmic differentiation to compute gradients of buckling and modal constraints, beyond stress-based ones which are commonly encountred in the literature. The tool is relevant to the aerospace industry (particularly for the deisgn of high-aspect ratio wings) and contributes to the advancement of sustainable aviation. | ||||
| 11:50 | 12:15 | 3.11.3 |
MULTI-OBJECTIVE OPTIMISATION OF AERIAL VEHICLES USING REINFORCEMENT LEARNING T Batty, Defence Science and Technology Group, Department of Defence, Australia Presenter: Trevor Batty, Defence Science And Technology Group A neural network agent is trained using reinforcement learning to achieve multi-objective optimisation of an aerial vehicle geometry, across a number of flight conditions. The agent utilises both low-fidelity aerodynamic and structural solvers to balance the conflicting target objectives, maximising L/D while minimising mass and achieving target values. | ||||
| 12:15 | 12:40 | 3.11.4 |
INVERSE AEROELASTIC SIZING FOR STRUT-BRACED WINGS VIA PHYSICS-GUIDED GENERATIVE MODELING Y. Ma, Northwestern Polytechnical University, China We propose a conditional generative framework that leams the multi-modal mapping from performance targets to structuraldesign variables. The proposed approach enables rapid generation of feasible Strut-braced wings design ensembles for conceptual trade studies, while maintaining physical credibility through solver-based re-verification. | ||||
| Reserve Paper | 3.11.R |
COMPARISON OF CONFIGRATIONS FOR FLEXIBLE AIRCRAFT USING AEROELASTIC ANALYSIS N.O. Okubo, The University of Tokyo, Japan | |||||
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| 11:00 | 11:25 | 4.11.1 |
CFD VISION 2030 PROGRESS AND NEXT STEPS J. P. Slotnick, United States Invited speaker for Special Session on CFD Vision 2030 (Panel 3.1) CFD Vision 2030 has established targets for CFD capabilities stemming from a 2015 NASA contractor report. This report has inspired CFD technology development in many areas. As 2030 is approaching, challenges remaining will be identified and progress reviewed. | ||||
| 11:25 | 11:50 | 4.11.2 |
GEOMETRY AND MESHING ADVANCEMENTS TOWARD CFD VISION 2030 N. J. Wyman, Cadence Design Systems, Inc., United States Invited speaker for Special Session on CFD Vision 2030 (Panel 3.1) Progress toward achieving the milestones identified in the CFD Vision 2030 for geometry treatment and mesh generation are identified, along with additional challenges that remain to be addressed. While much progress has been made in grid generation automation since 2015, challenges still remain to enable high quality meshes on complex geometries. | ||||
| 11:50 | 12:15 | 4.11.3 |
THE ROLE OF NEXT-GENERATION HPC AND MACHINE LEARNING IN ACHIEVING THE 2030 VISION GOALS N. Ashton, NVIDIA, United States As the aerospace community pushes toward Vision 2030, the intersection of exascale High-Performance Computing (HPC) and machine learning is emerging as a critical catalyst for success. The talk will highlight recent progress in leveraging advanced HPC architectures to accelerate high-fidelity aerodynamic analyses. Integration of AI/ML into workflows can unlock new approaches to complex challenges. | ||||
| 12:15 | 12:40 | 4.11.4 |
CFD VISION 2030 LOOKING FORWARD: PANEL DISCUSSION A. W. Cary, United States Invited panel discussion session (Panel 3.1) | ||||
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| 11:00 | 11:25 | 5.11.1 |
SUPERIOR CRUISE EFFICIENCY OF A NOVEL EVTOL CONFIGURATION FEATURING INCLINED PROPELLERS AND A PARASOL WING E. Shima¹, K. Yonezawa, CRIEPI, Japan; M. SATO, Kogakuin Univ., Japan; A. Oyama¹; ¹JAXA, Japan Presenter: Eiji Shima This novel eVTOL design achieves threefold the efficiency of multicopters by combining inclined propellers and a parasol wing. It eliminates complex tilt-mechanisms while extending range and payload for transport. Lower cruise RPM significantly reduces urban noise. This offers a simpler, high-performance paradigm for sustainable future Urban Air Mobility. | ||||
| 11:25 | 11:50 | 5.11.2 |
PREDICTION OF PROPELLER NOISE IN LOW REYNOLDS NUMBER OPERATION USING MACHINE LEARNING MODELS M. de Rosa Jacinto, TU Wien, Austria Propeller noise is one of the main challenges for the social acceptance of Advanced Air Mobility aircraft. High-fidelity simulations are time- and cost-intensive, making them unsuitable for early design stages. This study aims to assess the potential of Machine Learning models to predict propeller noise using high-fidelity simulations and experimental data for training. | ||||
| 11:50 | 12:15 | 5.11.3 |
A COMPARATIVE STUDY OF THE AERODYNAMIC CHARACTERISTICS OF TWO CONFIGURATIONS K. You, Northwestern Polytechnical University, China Presenter: Kai You The X-45C configuration is scaled to the SACCON’s wingspan, evaluating forces, moments, surface pressure, and vortex dynamics. The SACCON configuration experiences pitch-up at 16°, while the scaled X-45C displays no pitch-up. The cranked-segment geometry of the X-45C optimizes spanwise pressure gradients, and delays vortex breakdown, thereby mitigating pitch-up. | ||||
| 12:15 | 12:40 | 5.11.4 |
INTEGRATION OF ACOUSTIC LINERS AND INTERNAL BYPASS CHANNELS INTO AAM PROPELLERS FOR NOISE REDUCTION D. Skrna, TU Wien, Austria In this study, the application of acoustic liners and internal bypass channels into Advanced Air Mobility (AAM) propeller blades is investigated regarding aerodynamic performance and noise emissions. The parametrised geometrical modifications are computationally analysed at various operational conditions, and the resulting propeller blades are 3D-printed for experimental validation. | ||||
| Reserve Paper | 5.11.R |
RESEARCH ON AN AERODYNAMIC LOAD METHODOLOGY FOR FLAPPING WINGS BASED ON EXPERIMENTALLY ACQUIRED DEFORMATION K.-Y. Yang, Northwestern Polytechnical University, China | |||||
| additional information (interactive) | 5.11.R |
ARODYNAMIC COUPLING OF TYPICAL FORMATION CONFIGURATION JY.-Z. Zhao, Northwestern Polytechnical University, China | |||||
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| 11:00 | 11:25 | 6.11.1 |
WIND-TUNNEL STATIC AND DYNAMIC TESTING OF A TRANSPORT AIRCRAFT MODEL IN-STALL AND POST-STALL FLIGHT REGIMES D. Farcy, ONERA, France This paper presents static and dynamic wind-tunnel tests conducted on a 1/14-scale model of a transport aircraft to support flight-dynamic modelling in-stall and post-stall regimes. Experiments were performed at Cranfield University and ONERA using complementary test techniques. Results highlight hysteresis effects in static stall characteristics and demonstrate the dominant influence of rotation rate about the velocity axis on stall departure tendencies. | ||||
| 11:25 | 11:50 | 6.11.2 |
SIDE JET-CROSSFLOW INTERACTION: PRESSURE DISTRIBUTION AND FLOW FIELD ANALYSIS IN SUBSONIC, TRANSONIC AND SUPERSONIC FLOW B. Ilic, Military Technical Institute, Serbia This experimental study examines side jet-crossflow interaction on a generic missile model tested in the VTI T-38 wind tunnel at Mach numbers ranging from 0.3 to 1.6. Surface pressure measurements and schlieren visualization are employed to analyze the parametric trends of pressure distributions and interaction flow fields with respect to nozzle design, jet pressure ratio, and angle of attack. Supported by quantitative metrics and flow visualization, this comprehensive assessment is expected to contribute meaningfully to the design optimization of side jet reaction control systems. | ||||
| 11:50 | 12:15 | 6.11.3 |
WATER TUNNEL EXPERIMENTS AND CFD ANALYSES OF A COMBAT AIRCRAFT WITH LEADING-EDGE VORTEX CONTROLLERS ?. P. Malicki, Wroc?aw University of Science and Technology , Poland The study demonstrates that Leading-Edge Vortex Controllers significantly improve lift, pitch control, and stall characteristics of delta-wing aircraft. Water tunnel experiments and CFD analyses reveal that LEVCON alters vortical flow behaviour when compared to traditional LEX / LERX designs, providing valuable insight for high-angle-of-attack aerodynamics and next-gen aircraft configurations. | ||||
| 12:15 | 12:40 | 6.11.4 |
EXPERIMENTAL ASSESSMENT OF SIDE JET EFFECTS ON AERODYNAMIC FORCES AND MISSILE CONTROL IN SUBSONIC, TRANSONIC, AND SUPERSONIC FLOWS M.-Dj Samardzic, Military Technical Institute (VTI), Serbia This paper presents experimental results of tests on a generic missile model in the VTI T-38 wind tunnel, concentrating on changes in normal force and pitching moment caused by side jet. Five-component flow-through balance was used in measurements for two jet outlet speeds and Mach numbers from 0.3 to 1.6. | ||||
| Reserve Paper | 6.11.R |
EXPERIMENTAL INVESTIGATION OF WISHBONE VORTEX GENERATOR EFFECTS ON THE NACA 4412 AIRFOIL AT LOW REYNOLDS NUMBERS D. Domínguez¹, F. Parra¹, D. López¹, A. García-Gutiérrez¹; ¹Universidad de León, Spain | |||||
| additional information (interactive) | 6.11.R |
DESIGN, MANUFACTURING, AND TESTING OF HUMPBACK WHALE-INSPIRED TUBERCLES FOR ENHANCED LOW-REYNOLDS WING PERFORMANCE. Estela Barroso Barderas, instituto Nacional de Técnica Aeroespacial (INTA),, Spain; Rafael Bardera Mora¹, Juan Carlos Matías García¹, Jaime Fernández Antón¹, Ángel A. Rodríguez Sevillano, Universidad Politécnica de Madrid, Spain; ¹Instituto Nacional de Técnica Aeroespacial (INTA),, Spain | |||||
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| 11:00 | 11:25 | 7.11.1 |
FLIGHT TRIALS OF DRONES CONTROLLED BY AI LARGE LANGUAGE MODELS S Crase, Australia For aerial autonomy, the ability of LLMs to interpret natural language and generate executable code introduces opportunities for dynamic, adaptive drone operations. While other researchers show the feasibility of LLMs for drones control through simulation, we have carried our research through to real-world flight trials. These successful flights and lessons learned form the basis for this paper. | ||||
| 11:25 | 11:50 | 7.11.2 |
FAMILIARIZATION, OPERATION AND DEBRIEFING: AN ADAPTIVE AUGMENTED REALITY SUPPORT SYSTEM FOR UAV FLIGHT TESTING M. Zintl¹, F. Holzapfel¹; ¹Technical University of Munich, Germany This paper presents an adaptive augmented reality system that enhances UAV flight testing by integrating flight parameters into the pilot's field of view and offering a simulated vehicle with a virtual camera view. A preliminary evaluation was conducted with test pilots of a 500kg rescue drone. Subsequent studies will include test pilots of a remotely controlled airship and other smaller drones. | ||||
| 11:50 | 12:15 | 7.11.3 |
INFORMATIVE PATH PLANNING BASED ON REDUCED-RANK GAUSSIAN PROCESS FOR HAZARDOUS SUBSTANCE MONITORING C.M lee, South Korea This study proposes an integrated framework that simultaneously performs information-theoretic, real-time path planning for an unmanned aerial vehicle (UAV) and hazardous substance mapping in environments where hazardous substance are released from within multiple chimneys (cylindrical structures). Considering the characteristics of mobile sensor data suitable for UAV deployment, we propose an Extended Reduced-Rank Gaussian Process (ERRGP) designed for non-Gaussian measurement modeling and applicable to various types of sensors. For path planning, the framework utilizes LiDAR-based frontiers to generate trajectories that actively avoid obstacles while maximizing information gain. The proposed framework is validated through simulation experiments. | ||||
| 12:15 | 12:40 | 7.11.4 |
SENSOR-DRIVEN CONTROL OF UAS UTILISING AI IN SIMULATION S. R. Pywell, Australia To accelerate the "concept to flight trial" pathway for AI development and sensor-driven control of UAS, we present a simulation system that enables the execution of AI for closed-loop sensor-driven control of UAS in simulation. | ||||
| Reserve Paper | 7.11.R |
ONBOARD MISSION MANAGEMENT FOR A DECENTRALIZED MULTI-UAV SYSTEM USING BEHAVIOR TREES K. Thomessen, DLR (German Aerospace Center), Germany | |||||
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| 11:00 | 11:25 | 10.11.1 |
NOVEL METHODS FOR THE CHARACTERISATION OF INTAKE FLOW DISTORTION J. Hueso Rebassa, Cranfield Univeristy, United Kingdom This work investigates unsteady intake–fan aerodynamic interactions of a short aero-engine intake under crosswind with URANS CFD. Distortion mechanisms and their influence on the fan and intake aerodynamics are assessed through a relative frame analysis. The approach reveals limitations of conventional metrics and enables improved characterization of unsteady distortion for future intake design. | ||||
| 11:25 | 11:50 | 10.11.2 |
RUBBER ENGINE INTEGRATED OPTIMIZATION STRATEGY FOR OVERALL AIRCRAFT DESIGN J. Häßy, DLR, Germany Aero-engines involve numerous design variables that strongly influence mission block fuel, climate impact and costs. Evaluating many engine designs at overall aircraft level using detailed design workflows is computationally expensive. This paper proposes a more efficient sub-level engine optimization strategy based on sensitivities to efficiently solve engine optimization problems. | ||||
| 11:50 | 12:15 | 10.11.3 |
ON THE ACCURACY AND ROBUSTNESS OF TRANSIENT PNEUMATIC TRAVERSES: AN EXPERIMENTAL STUDY ON SYSTEM PARAMETERS S. Eilers, University of the Bundeswehr Munich, Germany Transient traverses can enable a considerable reduction of the time demand for pneumatic traverses in the wake of turbomachinery components. The presented study investigates the influence of various system parameters, such as traversing speed or tubing length on the robustness and accuracy of the method. Limitations of the method, as well as the influence of individual parameters are determined. | ||||
| 12:15 | 12:40 | 10.11.4 |
EFFECT OF INTAKE AERODYNAMICS AND FLOW DISTORTION ON FAN STALL INCEPTION J. Hueso Rebassa, Cranfield Univeristy, United Kingdom This work investigates how intake aerodynamics and unsteady distortion influence fan stall inception for a short aero engine intake in crosswind using URANS CFD. A relative frame distortion analysis identifies mechanisms driving rotating stall formation. The findings highlight limitations of conventional metrics and improve understanding of distortion induced stall for future intake–fan design. | ||||
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| 11:00 | 11:25 | 11.11.1 |
STUDY ON FLIGHT PERFORMANCE DEGRADATION CHARACTERISTICS OF ABLATION-INDUCED DAMAGE IN LOITERING MUNITIONS MX-Z zhang, China This study investigates loitering munitions with asymmetric ablation-induced damage by identifying static and dynamic aerodynamic derivatives via high-fidelity CFD, incorporating damage-induced longitudinal–lateral coupling into a flight control model, and establishing mission-based quantitative damage criteria for post-damage effect assessment. | ||||
| 11:25 | 11:50 | 11.11.2 |
GAIN OPTIMIZATION FOR CASCADED INDI CONTROL WITH INTEGRATED PERFORMANCE AND ROBUSTNESS REQUIREMENTS D. Surmann, University of the Bundeswehr Munich, Germany Nonlinear control, especially INDI papers often report controller gains without a reproducible derivation, and optimization-based tuning is rarely documented. We address this gap by expressing performance and robustness requirements explicitly and embedding them in a constrained optimization based on linearized models and frequency-domain metrics, transferable to other control applications. | ||||
| 11:50 | 12:15 | 11.11.3 |
LATERAL-DIRECTIONAL HANDLING AND FLYING QUALITIES ASSESSMENT OF A BLENDED WING BODY (BWB) ACFA 2020 CONFIGURATION M Alam, Cranfield University, United Kingdom This paper investigates the lateral–directional flying qualities and passenger ride comfort of a flexible blended wing body aircraft developed within the ACFA 2020 programme. A robust H? feedback controller combined with a feedforward controller is evaluated during representative lateral manoeuvres with gust disturbances. Passenger comfort is assessed using the BS 6841 vibration standard at multiple cabin locations. Results demonstrate strong spatial variability in ride quality and highlight the sensitivity of outboard regions to gust-induced structural excitation. | ||||
| 12:15 | 12:40 | 11.11.4 |
FLIGHT PERFORMANCE ANALYSIS OF ELECTRIC AIRCRAFT UNDER MOTOR FAILURE CONDITIONS USING REDUCED-ORDER MODELING L. Hein¹, S. Myschik¹; ¹University of the Bundeswehr Munich, Germany This paper presents a data-driven reduced-order modeling approach for electric motor systems enabling efficient, failure-aware flight performance analysis of electric aircraft. The method significantly reduces simulation effort while retaining certification-relevant accuracy and is applicable to other safety-critical, electrically driven systems beyond aviation. | ||||
| Reserve Paper | 11.11.R |
ACHIEVING ACCURATE AND CONSISTENT AIRSPEED MEASUREMENT FOR AIRCRAFT DEVELOPMENT AND CERTIFICATION J. Luo, The Boeing Company, United States | |||||
| additional information (interactive) | 11.11.R |
AERODYNAMIC REQUIREMENTS ASSESSMENT OF CIVIL AIRCRAFT BASED ON AIRWORTHINESS PERFORMANCE R. Wang, China | |||||
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| 11:00 | 11:25 | 12.11.1 |
BALANCING STRENGTH AND THERMAL CONDUCTIVITY IN LPBF-PROCESSED ALUMINUM-BASED MATERIALS H. Z Zhang, Nanjing University of Aeronautics and Astronautics, China This study develops systematic manufacturing guidelines for LPBF-processed aluminum thermal management parts. The established process windows enable 31% strength improvement while maintaining high thermal conductivity (217.5 W/mK). Results provide practical frameworks for quality control and supply chain integration in aviation and electronics industries. | ||||
| 11:25 | 11:50 | 12.11.2 |
3D ANALYSIS AND PREDICTION OF ASSEMBLY STEP DEVIATIONS IN FOUR-BAR LINKAGE BAY DOORS R. Yang¹, L.-K. Yang¹, L. Wei¹, S.-Y. Sun¹; ¹Dalian University of Technology, China This work proposes a 3D tolerance analysis approach for complex spatial mechanisms and applies it to a four-bar linkage bay-door system. By integrating a 3D vector-loop model and an improved SOTA method, the approach enables efficient prediction of assembly step deviations and provides practical support for tolerance design. The framework can be extended to other complex mechanical systems. | ||||
| 11:50 | 12:15 | 12.11.3 |
A NOVEL MULTI-TASK LEARNING METHOD FOR DEFECT SUPPRESSION IN AERONAUTICAL PARTS DURING LASER POWDER BED FUSION Y.S. Chen, Nanjing University of Aeronautics and Astronautics, China We presented a dual-phase Bayesian estimation and physics-informed multi-task learning framework to suppress lack-of-fusion in laser powder bed fusion aeronautical parts. Multi-track melt-pool geometry and dimensionless criteria build lack-of-fusion sensitivity maps, revealing robust power–speed windows with minimal experiments for reliable aeronautical components. | ||||
| 12:15 | 12:40 | 12.11.4 |
A QUALITATIVE FRAMEWORK FOR AIRCRAFT WING MANUFACTURING AND DECISION MAKING Y. A. D. Martins¹, C. C. D. Silva¹, D. A. Rade¹, J. M. G. Mello², A. V. S. Silva², A. P. C. Cuco²; ¹Aeronautics Institute of Technology, Brazil ;²Embraer S. A., Brazil Presenter: Caroline Silva, Aeronautics Institute of Technology This paper presents the Aircraft Wing Manufacturing Decision-Making (AWMDM) framework, developed within the IFAR-X Challenge 2025 on Green Aviation, to support early-stage trade-off analyses between aircraft performance and manufacturing costs. The framework accounts for manufacturing- and assembly-induced geometric deviations and their impact on aerodynamic efficiency and fuel consumption. | ||||
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| 11:00 | 11:25 | 13.11.1 |
THREE-DIMENSIONAL ADAPTIVE TRAJECTORY OPTIMIZATION FOR RPAS-BASED ATMOSPHERIC MEASUREMENTS K.-A. Buchtal, German Aerospace Center, Germany This work extends 2D route optimization to 3D adaptive trajectory planning for RPAS-based atmospheric measurements. The system integrates real-time measurement feedback, physics-based flight constraints, and genetic algorithm optimization. Flight tests in 2025 validated the concept. The approach advances aviation safety monitoring during volcanic eruptions and radioactive contamination events. | ||||
| 11:25 | 11:50 | 13.11.2 |
A FIELD-THEORETIC FRAMEWORK FOR AUTONOMOUS COLLISION AVOIDANCE IN URBAN AIR MOBILITY F. Y. Wu, Hong Kong SAR of China This paper proposes the airspace risk vector field for urban air mobility conflict management. Utilizing Helmholtz-Hodge Decomposition, risk is modeled as a flux density. A Lagrangian-derived force law generates autonomous escape trajectories by repulsion, tangential guidance, and gyroscopic deflection, validated via simulations in three typical scenarios. | ||||
| 11:50 | 12:15 | 13.11.3 |
EXPLORING DETROIT METROPOLITAN WAYNE COUNTY AIRPORT AS A TESTBED FOR RESOLVING EVTOL INTEGRATION CHALLENGES FOR AIR TAXI OPERATIONS S.M. Abdulhak, United States As interest grows in rapidly connecting airports to major cities, there is a significant need to evaluate how air taxis can be deployed without disrupting existing airport operations. We explore the use of a major U.S. hub airport for evaluating air taxi integration challenges, and propose eVTOL trajectories and the use of extended reality headsets to enhance air traffic controller performance. | ||||
| 12:15 | 12:40 | 13.11.4 |
STANDARDIZED TAKE-OFF AND LANDING PROCEDURES FOR AIR TAXIS: URBAN AIR MOBILITY FN Naeem, TUHH, Germany Despite extensive research on UAM concepts of operations, vehicle design, airspace integration, and verti- port development, a key operational gap remains: standardized, implementable take-off and landing (TOL) procedures for air taxi services. This paper develops region-adaptive and standardized TOL procedures by translating and adapting established helicopter terminal procedures to air-taxi operations and evaluates their robustness across representative high-impact operating contexts, including airport approaches over densely populated areas and rail-station environments with terminal versus through-station constraints, selected to capture real-world limitations such as constrained approach sectors, runway/control-zone proximity, complex obstacles, and wind-driven directionality. The scenarios are deliberately drawn from contrasting operating conditions to derive procedure templates that can subsequently be mapped to additional UAM use cases with similar constraint patterns. For each scenario, TOL procedures are designed and assessed under three commuter-demand levels (1,000, 2,000, and 3,000 passengers/day) to quantify capacity limits and conflict sen- sitivity. Multi-year wind-direction statistics are used to optimize feasible take-off and landing directions for each site, ensuring alignment with prevailing wind conditions. Integrated simulation and visualization are performed using MATLAB for trajectory generation and wind-adaptive parameter studies and AnyLogic for event-driven vertiplace operations and turnaround interactions, supported by ATC-oriented expert review to assess control- lability, procedural clarity, and workload implications. The new value of this work is that it turns UAM take-off and landing from a “concept” into clear, repeatable procedures. Instead of inventing procedures from scratch, we adapt proven helicopter TOL procedures for air taxis and then adjust them for real urban constraints like | ||||
| Reserve Paper | 13.11.R |
DETERMINATION OF SAFE SEPARATION FOR UAVS: CONSIDERING AIRSPACE STRUCTURE AND MANEUVERING STRATEGIES K.H. Low, Civil Aviation University of China, China | |||||
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| 11:00 | 11:25 | 14.11.1 |
LLM-ASSISTED GENERATION OF SYSML V2 MODELS FROM HETEROGENEOUS SYSTEM REPORTS V. Voth, German Aerospace Center (DLR), Germany In early system development, technical information is often available in structured reports but must be manually transferred into formal models. SysML v2 enables new automation opportunities, yet its novelty limits reliable LLM-based code generation. This paper analyzes four transformation paths and compares their correctness, consistency, and reproducibility for MBSE workflows. | ||||
| 11:25 | 11:50 | 14.11.2 |
INTEGRATED SYSTEMS ARCHITECTURE FOR AEROSPACE DIGITAL THREAD ECOSYSTEM: A HUB-N-SPOKE TO MODELLING AND SIMULATION K Dang, Boeing, United States A unified, model-centric process mapping framework that harmonizes cross-functional engineering disciplines—including flight sciences, structures, production systems, and product support—with organizational capabilities and workflows. The framework ensures traceability, and accessibility of information products, eliminating data silos and enabling real-time collaboration and decision-making. | ||||
| 11:50 | 12:15 | 14.11.3 |
COMMON ONTOLOGY FOR PROPULSION ARCHITECTURES - COPA S. Reitenbach, German Aerospace Center (DLR), Germany This paper introduces COPA, a standardized SysML v2 based ontology for collaborative aircraft engine design. It enables consistent data exchange across heterogeneous tools and fidelity levels and is demonstrated through a software integrated implementation. The approach is transferable to other complex, multidisciplinary engineering domains. | ||||
| 12:15 | 12:40 | 14.11.4 |
AUTOMATIC GENERATION OF PHYSICAL SYSTEM MODELS FOR AIRCRAFT SYSTEMS BASED ON LLMS Y. REN, Beihang University, China Modelica is an object-oriented multi-domain unified modeling language widely applied in the simulation of Cyber-Physical Systems (CPS) and Model-Based Systems Engineering (MBSE).Although Large Language Models (LLMs) have enabled code generation,the automated modeling of Modelica remains a major challenge due to the scarcity of domain-specific training corpora and the high dependency on professional expertise.This paper presents a domain-specific LLM framework tailored for Unmanned Aerial Vehicle (UAV) Modelica modeling.Retrieval-Augmented Generation (RAG) technology is leveraged to construct a specialized knowledge base by performing structured extraction, intelligent chunking, and vectorization of UAV domain materials and Modelica specifications. This knowledge base is validated through recall testing.The LLM is integrated into an AI-Agent architecture, which utilizes API interfaces to access the knowledge base and perform adaptation.Then,specialized prompt templates are designed, and systematic transformation rules and constraints are established to convert modeling requirements described in natural language into JSON format expression and ultimately into high-fidelity Modelica code, thereby realizing the conversion process from unstructured text to high-fidelity models.The application in UAV system modeling scenarios demonstrates that the proposed system effectively comprehends modeling intent and automatically generates syntactically correct and executable domThe main contributions of this work are threefold. First, the proposed structured knowledge framework ensures unified domain organization, significantly enhancing knowledge retrievability and modeling consistency. Second, the RAG-enhanced generation mechanism fuses semantic matching with precise querying, thereby improving code accuracy and professional quality. Third, the collaborative AI-Agent architecture enables automated multi-model specialization, effectively optimizing system intelligence and modelin | ||||
| Reserve Paper | 14.11.R |
BEYOND THE HARDWARE: REGULATION AND CERTIFICATION AS THE CRITICAL PATH TO ADF AUTONOMOUS CAPABILITY K.J. Joyce, RAAF / UNSW, Australia | |||||
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| 11:00 | 11:25 | 15.11.1 |
FLIGHT MISSION MODELLING WITH VARYING BASELINE DATA: APPLICAITON IN BUSINESS AVIATION A. Lau, German Aerospace Center (DLR), Germany Realistic modelling of Business Aviation flights is impeded by missing flight tracks information and operational differences to commercial aviation. This paper presents different trajectory modeling approaches in dependence of data availability and quality. A comprehensive set of Business Aviation trajectories is calculated and validated with measurement. | ||||
| 11:25 | 11:50 | 15.11.2 |
PROVIDING SENSOR INFORMATION FOR BORDING TIME PREDICTION M. Schultz, Unibw M, Germany We focus on providing operationally relevant sensor information to observe passenger states and the amount of carry on baggage during the boarding process. We develop a machine learning based perception approach to quantify carry on baggage within the boarding sequence, using video based and LiDAR based sensing in a mixed reality aircraft cabin environment under realistic boarding scenarios. | ||||
| 11:50 | 12:15 | 15.11.3 |
INVESTIGATION OF DECARBONISATION PATHWAYS FOR SHORT HAUL AVIATION USING A DISCRETE OPTIMISATION DECISION-MAKING ALGORITHM N Barry, Trinity College Dublin, The University of Dublin, Ireland Development, validation and utilisation of a decision making algorithm which objectively assesses the validity of decarbonisation pathways within short haul aviation from a hybrid economic and environmental perspective using discrete optimisation methods. The ultimate goal of this research is to characterise the sustainable potential of various decarbonisation pathways as the sector transitions. | ||||
| 12:15 | 12:40 | 15.11.4 |
ASSESSING AIRLINE PURCHASE MOTIVATION FOR HYDROGEN AIRCRAFT UNDER FUTURE CORSIA H. Nakamura, The University of Tokyo, Japan This study evaluates the mid-to-long-term feasibility of hydrogen aircraft adoption by analysing fuel-related operational costs under future CORSIA. By integrating recent data from hydrogen aircraft design studies with realistic carbon-pricing schemes, the research reveals how regulatory frameworks may shape airline purchase motivation toward next-generation zero-carbon aircraft. | ||||
| Reserve Paper | 15.11.R |
LIMITED-HORIZON LOOK-AHEAD SCHEDULING FOR DEMAND-RESPONSIVE OVERNIGHT CARGO AIRLINE OPERATIONS Palak Singh¹, Rajkumar.S Pant¹, Geetika Kapil, Independent Researcher, United States; ¹IIT Bombay, India Presenter: Rajkumar S. Pant, Indian Institute of Technology (IIT) Bombay | |||||
| additional information (interactive) | 15.11.R |
LOSS OF RELIABILITY OF NEW GENERATION ENGINES IN COMMERCIAL AVIATION: THE BUSINESS IMPACT OF THE PW1100G ENGINE RECALL ON MEXICAN AVIATION A Sanchez Mata, SANMATC Consulting, Mexico | |||||
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| 13:40 | 14:05 | 3.12.1 |
INVERSE AIRFOIL DESIGN USING CONDITIONAL VARIATIONAL AUTOENCODERS K. Swannet, Delft University of Technology, Netherlands Introduces a CVAE for airfoil inverse design conditioned on aerodynamic metrics and trained on the UIUC database. It directly generates geometries meeting target performance, avoiding iterative optimization. Conditioning improves latent interpretability and reduces dimensionality, linking features to aero-geometric properties and enabling efficient, intuitive design exploration. | ||||
| 14:05 | 14:30 | 3.12.2 |
DATA-DRIVEN SHAPE PARAMETERIZATION FOR EFFECTIVE AERODYNAMIC DESIGN OPTIMIZATION OF PROPELLERS J. L. Li, Northwestern Polytechnical University, China A hybrid framework is proposed for efficient propeller shape optimization in low-altitude and urban air mobility. It integrates compact, data-driven blade parameterization with surrogate models trained on limited CFD data, reducing dimensionality while preserving shape diversity and accuracy. The approach is validated on three propellers with different scales and operating conditions. | ||||
| 14:30 | 14:55 | 3.12.3 |
AN INVESTIGATION OF KRIGING MODELS USING CORRELATED INDEPENDENT VARIABLES FOR AERODYNAMIC DESIGN T. Kanno, Purdue University, United States This study examines how correlated variables, altitude and Mach number, affect Kriging models in aerodynamic design. Using real flight data, the authors plan to construct distributions, sample flight conditions, and build surrogate models for the RAE 2822 airfoil. The work evaluates how flight data can guide aerodynamic optimization. | ||||
| 14:55 | 15:20 | 3.12.4 |
META-ENHANCED MULTI-OBJECTIVE REINFORCEMENT LEARNING FOR WIDE-SPEED-RANGE AIRFOIL OPTIMIZATION Z. Li, Northwestern Polytechnical University, China This study presents a meta-enhanced MORL framework with dynamic preference adjustment for wide-speed-range airfoil optimization. Applied to this problem, the method improves Pareto frontier diversity by 8.58%. A representative optimized airfoil shows a 19.38% reduction in transonic drag and a 57.11% increase in hypersonic L/D ratio, demonstrating effectiveness for complex multi-objective design. | ||||
| Reserve Paper | 3.12.R |
AN EFFICIENT TRANSITION PREDICTION METHOD USING NEURAL NETWORK SURROGATE MODELS J.-W Wu, Northwestern Polytechnical University, China | |||||
| Reserve Paper | 3.12.R |
RESEARCH ON GENERALIZED REPRESENTATION OF FLYING-WING CONFIGURATIONS BASED ON DEEP LEARNING Xiaomeng Zhang, China | |||||
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| 13:40 | 14:05 | 5.12.1 |
EFFECTS OF FLAPPING–PITCHING PHASE DIFFERENCE ON THE AERODYNAMIC PERFORMANCE OF HOVERING DRAGONFLY WINGS Haozhe Wang¹, Jialong Wang¹, Zhantao Li¹, Wenqing Yang¹, Xiaojun Yang¹; ¹Northwestern Polytechnical University, China This study reveals the influence of the phase difference between flapping and pitching motions on the aerodynamic performance of dragonfly tandem wings during hovering. By using a realistic three-dimensional wing model and observed hovering kinematics, the results demonstrate that a 90° phase difference provides more favorable aerodynamic characteristics for stable hovering flight. | ||||
| 14:05 | 14:30 | 5.12.2 |
UNCERTAINTY QUANTIFICATION AND CROSS-CORRELATION EFFECTS IN AERODYNAMIC COEFFICIENTS DERIVED QUANTITIES L. Pirillo, Italy This work investigates the propagation of CFD numerical uncertainties in aerodynamic coefficients and the role of their cross-correlations. Using Richardson extrapolation and sensitivity analysis, it quantifies how correlated errors affect uncertainty in derived quantities such as aerodynamic efficiency and center-of-pressure location. | ||||
| 14:30 | 14:55 | 5.12.3 |
A STALL EXTENSION TO LIFTING-LINE THEORY: IMPLEMENTATION AND VALIDATION IN ASWING L. Avoni, ISAE-Supaero, France This work introduces an Extended Lifting-Line Theory (ELLT) for post-stall predictions, implemented in ASWING, a fast aeroelastic solver. Validation against experimental and CFD data shows good agreement across pre- and post-stall regimes, supporting ELLT for studying flexible-aircraft stall dynamics and recovery strategies. | ||||
| 14:55 | 15:20 | 5.12.4 |
FALCON: FRAMEWORK FOR AIRFOIL CFD AND ANALYSIS OPTIMIZATION P. Desai, Manipal Institute of Technology, India FALCON is an open-source framework that automates CFD analysis for airfoils, integrating geometry parameterization, mesh generation, and RANS simulations. It achieves 3-7% accuracy without manual setup, bridging the gap between tools like XFOIL and complex high-fidelity methods, enabling accessible aerodynamic analysis and high-quality ML training data generation. | ||||
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| 13:40 | 14:05 | 6.12.1 |
PROPOSAL FOR DISTINGUISHING USALE DATA UNDER HIGH WIND TUNNEL BLOCKAGE USING AN RAE2822 TEST CASE M.H. Mohsin, Cranfield University, United Kingdom This study proposes a methodology that tackles the main issues in attaining usable data for a large model in a small-scale industrial wind tunnel. It employs tunnel top wall pressure measurements alone to (i) estimate model buffet onset and (ii) identify tunnel flow breakdown for instance in a chocked wind tunnel, thereby distinguishing usable from non-usable data for free air validation. | ||||
| 14:05 | 14:30 | 6.12.2 |
EXPERIMENTAL VALIDATION OF A COANDA-BASED FLUIDIC THRUST VECTORING NOZZLE USING A HIGH-SPEED WIND TUNNEL N. Schwagerus¹, M. Stößel¹, D. Kozulovic¹; ¹University of the Bundeswehr Munich, Germany This work provides experimental validation of a Coanda-based fluidic thrust vectoring nozzle using a high-speed wind tunnel with independently controlled flow streams. The results confirm key numerical predictions and deliver a unique pressure-based data set relevant for future propulsion, flow control, and aerospace applications. | ||||
| 14:30 | 14:55 | 6.12.3 |
FORCE RECONSTRUCTION TECHNIQUES FOR DYNAMIC LOAD ESTIMATION ON A HEMISPHERE IN LOW-SPEED WIND TUNNEL TESTING C.J.K Brown, RMIT University , Australia This work enables reliable estimation of unsteady aerodynamic loads from strain and acceleration data when direct force measurements are corrupted by vibration and inertia. The validated multi-algorithm framework improves wind-tunnel test fidelity and reduces reliance on CFD. It is relevant to aerospace, marine, and civil structures where transient fluid-structure loads drive fatigue and control. | ||||
| 14:55 | 15:20 | 6.12.4 |
METROLOGY METHODS FOR ISOLATING PROFILE FORM, WAVINESS, STEPS, AND TWIST FROM SCANS OF SMALL-SCALE LAMINAR FLOW WIND TUNNEL MODELS C. Hiemcke¹, R. Buth¹, C. Schneider¹, C. J. Jones¹; ¹General Atomics Aeronautical Systems, Inc., United States This paper presents a methodology for scanning and then evaluating the point cloud for a small-scale wind tunnel model, specifically to avoid unintended transition. The tolerances are based on the Carmichel criterion and stability theory. The method is applied to a 2-ft model of the PRANDTL-D flying wing. | ||||
| Reserve Paper | 6.12.R |
GROUND EFFECT EXPERIMENTAL ANALYSIS IN A NAVAL TESTING TANK AS AN ALTERNATIVE TO WIND TUNNEL L.G. Souza, Instituto Tecnológico de Aeronáutica, Brazil | |||||
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| 13:40 | 14:05 | 7.12.1 |
ONLINE TRAJECTORY PLANNING FOR FIXED-WING UAVS BASED ON PSEUDO-SPECTRAL CONVEX PROGRAMMING Y. Peng, National University of Defense Technology, China This paper investigates the real-time trajectory planning problem for fixed-wing UAVs. An online pseudo-spectral convex programming method is proposed. This approach integrates high-precision pseudo-spectral discretization into the sequential convex programming framework. Simulation and flight experiments validate that the proposed method can efficiently generate high-quality trajectories online. | ||||
| 14:05 | 14:30 | 7.12.2 |
THREE-DIMENSIONAL PATH PLANNING OF UAV IN WIND FIELD ENVIRONMENT OF PLATEAU MOUNTAINOUS AREA F. H.-F. Fan, Northwestern Polytechnical University, China This paper presents an improved Rapidly-exploring Random Trees* (RRT*) algorithm for optimizing the flight energy of unmanned aerial vehicles (UAVs) operating in plateau mountainous wind environments, where both terrain and wind effects must be considered. First, a mountain airflow model is constructed based on potential-flow theory, and an environment model that incorporates terrain obstacles and threat zones is established. By analyzing the UAV’s flight constraints within the wind field, we introduce an environment-adaptive sampling strategy, a dynamic step-size scheme, and an energy-loss cost function into the random-tree expansion process. The resulting path is further refined via B-spline curve smoothing. Simulation results indicate that, compared with the conventional RRT algorithm, the proposed method reduces the number of iterations by 40% and lowers energy consumption by 19.7%, thereby effectively improving UAV endurance. | ||||
| 14:30 | 14:55 | 7.12.3 |
VANE-LESS 3D WIND ESTIMATION FOR FIXED-WING UAVS: A TEMPORAL RESIDUAL NETWORK APPROACH WITH CHANNEL ATTENTION Ziyang Zhang¹, Shaokun Li¹, XiaoPing Xu¹, Zhou Zhou¹; ¹Northwestern Polytechnical University, China This paper proposes DeepWindNet, a physics-augmented framework for vane-less wind estimation in fixed-wing UAVs. By integrating kinematic equations as structural anchors to learn nonlinear residuals, the method utilizes a Squeeze-and-Excitation (SE) attention mechanism to recalibrate sensor weights based on physical flight contexts. Experimental results demonstrate that while achieving a horizontal RMSE of less than 0.3 m/s, this approach effectively eliminates the high-frequency oscillations and systematic biases inherent in traditional dynamics inversion. | ||||
| 14:55 | 15:20 | 7.12.4 |
TRAJECTORY FEASIBILITY AND CONTROL FOR DYNAMIC SOARING IN 6-DOF FLIGHT Y. Zhu, Northwestern Polytechnical University, China Guidance-control for tracking soaring trajectories is proposed. 6-DOF simulations confirm feasibility in strong winds. Limited propulsion is required to complete tracking in certain phases. | ||||
| Reserve Paper | 7.12.R |
MPPI-BASED COMPUTATIONAL GUIDANCE FOR MOTION PLANNING OF A MULTIROTOR UAV USING DEPTH-CAMERA-BASED OBSTACLE REPRESENTATION K.W. Jang, Electronics and Telecommunications Research Institute, South Korea | |||||
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| 13:40 | 14:05 | 9.12.1 |
EFFECT OF UNCERTAINTY ON ROBUST JIG SHAPE DESIGN OF A HIGH ASPECT RATIO WING G. Yang, University of Bristol, United Kingdom This is the first time that a robust / reliable optimisation design approach has been employed on a full size aircraft model with ultra-high aspect ratio wing, incorporating folding wing tips for loads alleviation, considering the uncertainty of the design requirements and inclusion of design mitigations during the entire design cycle once the jig twist has been defined. | ||||
| 14:05 | 14:30 | 9.12.2 |
METHODOLOGY FOR CRITICAL LOAD-CASE AND CONSTRAINT IDENTIFICATION IN PRELIMINARY COMPOSITE WING SIZING USING RAPID DESIGN TOOLS M Alam, Cranfield University, United Kingdom A methodology is presented for identifying critical load cases and governing structural constraints for preliminary composite wing sizing using a rapid multidisciplinary optimisation framework. The approach is demonstrated on a NASA Common Research Model wing using parametric wing-box discretisation and sensitivity analysis to quantify impacts on mass, stiffness, and aeroelastic response. Results show that refined discretisation improves torsional stiffness prediction while preserving global deflection accuracy. | ||||
| 14:30 | 14:55 | 9.12.3 |
NOVEL MULTIDISCIPLINARY MISSION-OPTIMISED AIRCRAFT DEVELOPMENT METHODOLOGY IN CONSIDERATION OF PASSIVE/ACTIVE CONTROL V. N. Mueller, Technical University of Munich, Germany A novel multidisciplinary mission-optimised aircraft development methodology is presented in this paper. It is considering the loft (aerodynamic shape), the internal structure, the jig-shape, comprehensive loads analysis and the control system fulfilling prescribed top level aircraft requirements (TLAR). | ||||
| 14:55 | 15:20 | 9.12.4 |
AIRCRAFT MASS EVALUATION MODEL: FROM TUBE-AND-WING TO BLENDED WING BODY USING WHALE. V Priasso¹, A Lannoo¹; ¹DMAS, ONERA, 59000, Lille, France, France A numerical model, named WHALE, is used to compute the mass breakdown of a blended wing body (BWB). Initially developed for traditional tube-and-wing structures, WHALE is applied to a BWB and the results are compared with those in the literature. | ||||
| additional information (interactive) | 9.12.R |
A STOCHASTIC GRADIENT ONLINE LEARNING AND PREDICTION METHOD FOR ACCELERATING TOPOLOGY OPTIMIZATION AND ITS APPLICATION IN THE DESIGN OF MORPHING WING Y. Xing, The University of Sydney, Australia | |||||
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| 13:40 | 14:05 | 10.12.1 |
INLET OPTIMIZATION DESIGN OF A BOUNDARY LAYER INGESTION PROPULSION SYSTEM X.K. Ma, Northwestern Polytechnical University , China This study develops a discrete adjoint-based optimization framework for BLI propulsion inlets. The IFCPT S-duct validation case achieves 35.4% objective function and 27.4% CDI reduction. BWB-based BLI inlet optimization at M=0.5, ?=90% reconstructs wall curvature and area distributions, eliminating flow separation. Results demonstrate 13.4% DC60 reduction and 0.5% pressure recovery improvement. | ||||
| 14:05 | 14:30 | 10.12.2 |
PD-STGNN: A PHYSICS-INFORMED DYNAMIC SPATIO-TEMPORAL GRAPH NEURAL NETWORK FOR AERO-ENGINE THRUST PREDICTION C. Song, Northwestern Polytechnical University, China This study proposes a physics-informed dynamic spatio-temporal graph neural network framework that jointly exploits and integrates complex spatio-temporal features from multi-source sensor data to construct a high-accuracy engine thrust prediction model. Validation on a real engine test dataset demonstrates that the proposed method achieves high prediction accuracy and strong robustness. | ||||
| 14:30 | 14:55 | 10.12.3 |
PARAMETRIC DESIGN AND MULTI-OBJECTIVE OPTIMIZATION OF EXHAUST NOZZLE FOR GAS TURBINE ENGINES T.-D Dinh, Vietnam This study addresses the challenge of designing and optimizing a convergent exhaust nozzle for gas turbine engines, integrating CFD simulations with advanced sensitivity analysis and optimization techniques, to develop a systematic methodology for refining nozzle geometry to achieve superior flow characteristics. | ||||
| 14:55 | 15:20 | 10.12.4 |
GPU-ENABLED SURROGATE MODEL-BASED AEROACOUSTIC OPTIMISATION FOR JET FLOWS G. Yang, University of Bristol, United Kingdom This paper presents a surrogate model-based aeroacoustic optimisation framework that is developed and applied to jet nozzle exit geometries. The optimisation package is wrapped around a LES flow solver that is implemented on GPUs, enabling highly efficient CFD and acoustic solutions and thus shape optimisations. Noise reductions are achieved for isolated chevron nozzle geometries. | ||||
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| 13:40 | 14:05 | 11.12.1 |
MULTI-BODY DYNAMIC MODELING OF A BIRD-LIKE FLAPPING-WING VEHICLE: ANALYSIS OF FLAPPING-AERODYNAMIC COUPLING EFFECTS L.Z. Zhou, China This study develops a multi-body dynamics model with an accurate instantaneous aerodynamic model for a bird-like flapping-wing vehicle, using wind tunnel data. By comparing single-body and multi-body models, it quantifies the essential effects of flapping motion and instantaneous aerodynamics on trim and maneuver response. | ||||
| 14:05 | 14:30 | 11.12.2 |
AIRCRAFT BUFFET QUANTIFICATION Jia Luo, The Boeing Company, United States Aircraft buffeting is a vibration of the airframe caused and sustained by unsteady turbulent flow resulting from flow separation during high angle of attack maneuvers, such as stalls and windup turns, as well as overspeed, control surface deflection, flap and slat deployment, and landing gear extensions, among other factors. Detecting and quantifying aircraft buffet is critically important for determining operating envelopes to ensure safety. As a dynamic aeroelastic response to a random broadband forcing function, it has been challenging to establish general procedures and formulations to quantify buffet intensity. Instead, qualitative evaluations by human pilots, combined with engineering judgment, have been used in the development and certification of aircraft in the aerospace industry. Acknowledging the complexities and wide variety of human whole-body responses to vibrations such as buffet, this paper proposes an initial buffet boundary and two deterrent buffet boundaries using a more scientific procedure for quantifying buffet intensity. These boundaries have been developed and refined over the last two decades based on extensive flight test data and pilot feedback. This work aims to provide general guidance for practicing engineers and pilots involved in aircraft development and certification in the industry. | ||||
| 14:30 | 14:55 | 11.12.3 |
METHODOLOGY FOR VERIFYING DYNAMIC PARAMETERS OF A STEWART PLATFORM FOR FLIGHT SIMULATION M. D. Dutra Turazza, University of São Paulo, Brazil This work presents a methodology for verifying dynamic parameters required for a flight simulation platform, according to ICAO standard document 9625, Annex F. A Stewart platform is tested in roll, pitch, yaw, surge, sway, and heave movements across a wide frequency range, and the response is measured using an IMU sensor. The methodology for testing and analyzing the data is presented. | ||||
| 14:55 | 15:20 | 11.12.4 |
A NEW APPROACH TO MODELLING THE FLIGHT DYNAMICS OF A TAILLESS AIRCRAFT A. Kwiek, Warsaw University of Technology, Poland The paper shows results of flight dynamics analysis for tailless unmanned aerial vehicle for lateral-directional motion. The aim of this study is to investigate how the flight dynamics characteristics and response to control change when the elevon deflection is included. | ||||
| Reserve Paper | 11.12.R |
EFFECTS OF LIFT DISTRIBUTION AND WING POSTURE ON THE STABILITY AND CONTROL OF TAILLESS AIRCRAFT MR de Kock, University of Pretoria, South Africa Presenter: Barbara Huyssen, University of Pretoria | |||||
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| 13:40 | 14:05 | 12.12.1 |
ACHIEVING HIGH-PERFORMANCE MAGNESIUM MATRIX COMPOSITES BY LASER POWDER BED FUSION L.X.XI Xi, China The inherent characters of magnesium alloys impose highly strict requirements for energy input in laser powder bed fusion (LPBF). Synthetic coordination of laser processing and alloy constituent on the energy input in the processing of magnesium alloys is pivotal for achieving optimal manufacturing quality and mechanical performance. In this work, the magnesium matrix composites with different laser energy densities and reinforcement contents have been manufactured by LPBF to investigate the synthetic effects of laser processing and alloy composition on the formability, microstructure and mechanical properties. At an optimal energy density of 150 J/mm3, the composites exhibit good forming quality with surface roughness of ~11 ?m and porosity of ~0.38%. The TiC addition refines the grains to an average size of ~4.5 ?m. The composites fabricated at 150 J/mm3 exhibit improved mechanical properties with microhardness of 108±3 HV0.2, nanohardness of 1.56±0.04 GPa and elastic modulus of 55.0±0.7 GPa. The strengthening contributions from grain refinement and dislocation strengthening dominate in the composites with high ultimate tensile strength of ~344 MPa and good elongation of ~7.3%. The tensile strength of the heat-treated composites slightly decreases, while the elongation significantly increases by ~83%, primarily due to grain growth and release of thermal stresses with heat treatment. High processability and comprehensive properties are obtained in the composites with optimal composition of 3 wt.% TiC, where the microhardness, ultimate tensile strength and elongation reach 110±3 HV0.2, ~352 MPa and ~6.5%, respectively. This work could provide insights to fabrication of high-performance magnesium matrix composites in synthetic consideration of processing and composition for engineering applications. | ||||
| 14:05 | 14:30 | 12.12.2 |
HIGH-RATE AUTOMATED STAMP FORMING OF CF/LM-PAEK COMPOSITES FOR NEXT-GENERATION UAV AEROSTRUCTURES M. Ravandi, Aerostructures Innovation Research (AIR) Hub, Swinburne Universi, Australia This paper presents part of a broader research programme on high rate automated stamp forming of carbon fibre reinforced LM PAEK composites for UAV aerostructures. An integrated manufacturing process is demonstrated on a UAV wingbox demonstrator, with process optimisation and formed part characterisation confirming feasibility, geometric accuracy, and suitability for high rate production. | ||||
| 14:30 | 14:55 | 12.12.3 |
THE MAKING OF LUCHTVAART IN TRANSITIE (LIT) – AND THE REMAKING OF A STRONG GLOBALLY CONNECTED NATIONAL AERONAUTICS INDUSTRY R. van Manen, Stichting Luchtvaart in Transitie, Netherlands This paper examines the socio-economic case and expected long-term value of public-private investment in disruptive 'cleantech' in aeronautics, the risks and rewards related to new startup initiatives and the challenges these face. | ||||
| 14:55 | 15:20 | 12.12.4 |
A MULTI-STAGE FORMING APPROACH FOR MANUFACTURING TITANIUM BIPOLAR PLATES FOR FUEL CELLS J.-H. Hong, Korea Institute of Materials Science, South Korea This study develops a forming-based manufacturing route for titanium bipolar plates for PEMFC applications. Carbon-coated commercially pure titanium sheets were used to enhance corrosion resistance and electrical conductivity. A multi-stage forming strategy optimized by finite element simulations enabled accurate micro-channel fabrication, reduced thinning and spring-back, and ensured stable forming performance. | ||||
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| 13:40 | 14:05 | 13.12.1 |
AEROACOUSTIC WIND TUNNEL TESTING AND CFD STUDY USING JAXA 8% SEMISPAN HIGH-LIFT COMMON RESEARCH MODEL IN JAXA FQUROH-2 PROJECT M. Murayama, Japan Aerospace Exploration Agency, Japan This paper provides an overview of JAXA’s aeroacoustic research using the CRM-HL model in the FQUROH-2 project. Wind tunnel tests have been conducted with an 8% semispan CRM-HL in various configurations. The effectiveness of low-noise concepts has been demonstrated on the CRM-HL. Comparative studies with CFD have also been conducted to evaluate the effectiveness of noise prediction methods. | ||||
| 14:05 | 14:30 | 13.12.2 |
CROSS-TEST COMPARISONS AND REYNOLDS NUMBER EFFECTS IN THE CRM-HL ECOSYSTEM S.M. Rivers, NASA Langley Research Center, United States Presenter: Courtney Winski To overcome limitations of CFD to accurately capture complex physics phenomena, the CRM-HL ecosystem integrates high-fidelity wind tunnel data with advanced computational methods. This paper summarizes the evolution of the CRM-HL ecosystem, details global wind tunnel campaigns, and presents cross-test comparisons that quantify Reynolds number influences and geometric sensitivities. | ||||
| 14:30 | 14:55 | 13.12.3 |
ICING EXPERIMENTAL DATABASE USING THE COMMON RESEARCH MODEL(ICED CRM) D.D.P. Di Pasquale, Cranfield University, United Kingdom The ICED CRM project will result in a definitive database of experimental data on which to base mitigation technology development, a better understanding of the best practice for accurate numerical computations for the effects of icing on aircraft performance and an enhanced international capability to deal with aircraft icing issues and share the data with the international research community. | ||||
| 14:55 | 15:20 | 13.12.4 |
ICING EXPERIMENTAL DATA ON THE NASA HIGH-LIFT CRM MODEL D.D.P. Di Pasquale, Cranfield University, United Kingdom ICED CRM project experimental test is scheduled for spring 2026 in the European Transonic Windtunnel. The project will make use of the NASA Common Research Model (CRM) to define, manufacture and test relevant Appendix-O ice configurations. Such high-quality data has not been attained and can only be attained using cryogenic wind tunnel testing. The ICED CRM project will result in a shared database of experimental data on which to base mitigation technology development, a better understanding of numerical computations practice for the effects of icing on aircraft performance. | ||||
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| 13:40 | 14:05 | 14.12.1 |
EVTOL AND PROPULSION R&D IN THE SYDNEY PROPULSION LAB D. Verstraete, Australia The Sydney Propulsion Lab (SPL) aims to advance propulsion technologies for uncrewed aerial vehicles and electric vertical take-off and landing (eVTOL) aircraft. This paper will detail activities in hybrid fuel-cell-based propulsion systems and proprotor performance for eVTOL aircraft. | ||||
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| 13:40 | 14:05 | 15.12.1 |
INTEGRATING MAINTENANCE, REPAIR, AND OVERHAUL (MRO) ASPECTS INTO SUSTAINABILITY-DRIVEN DESIGN OF AIRCRAFT STRUCTURES A.F. Filippatos, Department of Mechanical Engineering & Aeronautics, University o, Greece This contribution investigates the systematic integration of Maintenance, Repair, and Overhaul (MRO) considerations into early-stage sustainability-driven design of aircraft structural components. A set of MRO-related metrics is defined and applied to alternative design configurations of a representative aircraft structure. These metrics are embedded within a holistic sustainability assessment framework that combines structural performance, lifecycle cost, environmental impact, circularity, and social aspects. The proposed approach demonstrates that MRO, when considered at conceptual and preliminary design stages, can significantly influence the overall sustainability performance of aircraft structures and support more informed design trade-offs. | ||||
| 14:05 | 14:30 | 15.12.2 |
FROM DATA TO DECISIONS: A CONCEPTUAL FRAMEWORK FOR DATA-DRIVEN AIRLINE OPERATIONS AND SUSTAINMENT A. Apostolidis, KLM Royal Dutch Airlines, Netherlands A systems-level conceptual framework is presented for integrating prognostics and fleet analytics into airline operations and sustainment. The paper analyses current limitations in coupling predictive models with planning and scheduling, and proposes a layered decision architecture to support uncertainty-aware, integrated operational decision-making. | ||||
| 14:30 | 14:55 | 15.12.3 |
LIFE CYCLE ANALYSIS OF EMISSIONS IN AVIATION: IDENTIFIYING AND ADJUSTING FACTORS TO REDUCE CARBON EMISSIONS J. Roesing, RWTH Aachen University, Germany Due to climate change, CO2 emissions in the aviation sector must be reduced. To understand the causes of these emissions, we analyze emissions related to infrastructure and vehicles over the entire life cycle of a flight. We use system dynamics and existing studies to identify adjustment factors. | ||||
| 14:55 | 15:20 | 15.12.4 |
PERFORMANCE DEGRADATION ASSESSMENT METHOD FOR AERO-ENGINES ACROSS THE FULL-LIFE-CYCLE BASED ON DIGITAL TWIN D. Xiao, China This paper proposes a digital twin-based performance degradation assessment method for aero engines across their full life cycle. By establishing high-fidelity digital twin models, the proposed approach enables accurate monitoring and quantitative evaluation of engine performance deterioration under realistic operating conditions. | ||||
| Reserve Paper | 15.12.R |
ENGINEERING COMMERCIAL AIRCRAFT FOR SUSTAINABLE THROUGH-LIFE SUPPORT RG Ramachandran, Boeing, India | |||||
| additional information (interactive) | 15.12.R |
KEY STAKEHOLDERS IN AEROSPACE FOR A SUSTAINABLE AND CIRCULAR PRODUCT DEVELOPMENT - A SYSTEMATIC APPROACH I. Hallstedt, Chalmers University of Technology, Sweden | |||||