| Tu, 05.9. 08:00 - 09:00 | Registration open | 08:00 - 09:00 | ||||||
| Tu, 05.9. 09:00 - 10:30 | Opening Ceremony | 09:00 - 10:30 | ||||||
| Networking and Refreshmentbreak | 10:30 - 11:00 | |||||||
| 0.1 Tu, 05.9. 11:00 - 11:30 | Plenary Lecture 1 Chair: K. Pahlke, DLR, DE | |||
| 11:00 | 11:30 |
Rotorcraft Research at German Aerospace Center (DLR) – Science and Application Stefan Levedag, Director of the Institute of Flight Systems Technology at German Aerospace Center (DLR) | ||
| 0.2 Tu, 05.9. 11:30 - 12:00 | Plenary Lecture 2 Chair: K. Pahlke, DLR, DE | |||
| 11:30 | 12:00 |
Airbus vision for the future of vertical flight Rainer Heeger, Research Program Manager at Airbus Helicopters | ||
| 0.3 Tu, 05.9. 12:00 - 12:30 | Plenary Lecture 3 Chair: K. Pahlke, DLR, DE | |||
| 12:00 | 12:30 |
Validation of a Motion Sickness Prediction Model via Flight Tests on DLR's Bo-105 Helicopter Philippe Petit, Research Engineer at Institute of Flight Systems at German Aerospace Center (DLR) | VFS Best paper Award Winner 2023 | ||
| Networking Lunch | 12:30 - 13:30 | |||||||
| 1.4 Tu, 05.9. 13:30 - 15:30 | Aerodynamics 1: Airfoil Characteristics Chair: T. Schwarz, German Aerospace Center, DE | City Hall | Großer Rathaussaal |
| 13:30 | 14:00 | 0001 |
Factors affecting Rotor Stall Computation by Comprehensive Rotor Codes B.G. van der Wall, German Aerospace Center (DLR), DE This paper focuses on the prediction of hovering and high-speed rotor stall limits and the aerodynamic factors that in parts significantly affect these: steady or unsteady aerodynamics, steady or dynamic stall, blade tip losses, centrifugal forces, yaw angle, downwash model, blade-vortex and fuselage-rotor interaction. Yaw angle, dynamic stall and tip loss are found as most important factors. | |
| 14:00 | 14:30 | 0099 |
An Innovative CFD Methodology for Evaluation of Airfoils Aerodynamic Characteristics F. Manara¹, G. Frassoldati, Leonardo Helicopters Division, Università degli Studi Roma Tre, IT; D. Malacrida, Leonardo Labs, IT; S. Platzer¹; ¹Leonardo Helicopters Division, IT Leonardo Helicopters CFD methodology for 2D airfoil simulations was reviewed, updated and validated against literature data available for the SC1095 airfoil. An improved methodology was selected, which was found to predict with satisfying accuracy the main aerodynamic characteristics of the SC1095 at different Mach numbers and angles of attack. | |
| 14:30 | 15:00 | 0109 |
Aerodynamic Analysis of Rotor Airfoils with Camber Morphing Mechanism versus Plain Flaps A. Abdelmoula¹, F. Grimm¹, I. Yavrucuk¹, J. Rauleder, Georgia Institute of Technology, US; ¹Technical University of Munich, DE This paper investigates the aerodynamic effects of FishBAC vs. plain flap mechanism. CFD analysis was conducted on NACA23012 and SC1094 R8 airfoils with varying camber morphing, evaluating effects on aerodynamic efficiency, moment, pressure distribution, etc. The study will include high-speed rotor airfoils like ONERA OA212, VR-12, Bell/Wortmann FX69-H-083, and Boeing VR-15. | |
| 15:00 | 15:30 | 0117 |
Drone Rotor Performance under Icing Conditions A. Gupta, Linde Inc., US; A. Gahlot¹, L.N. Sankar¹; ¹Georgia Institute of Technology, US While much work has been done to model the effects of icing on conventional helicopter performance, relatively less work has been done on assessing how freezing rain and icing would affect the performance of small rotors. In this study, a blade element based propeller analysis XROTOR has been used in conjunction with the NASA Glenn Research Center Ice Accretion Code LEWICE to asses the performance degradation under icing conditions. Qualitative comparisons are presented for a rotor tested in Quebec, Canada. Fully 3-D Navier-Stokes simulations with a 3-D ice accretion solver are in progress and will be included in the full paper. |
| 1.5 Tu, 05.9. 13:30 - 15:30 | Acoustics 1: Propeller Chair: B. Ohlenforst, Netherlands Aerospace Centre, NL | City Hall | Le-Theule-Saal |
| 13:30 | 14:00 | 0020 |
CFD Validation for eVTOL Propeller Performance and Acoustics G. Qiao¹, G.N. Barakos¹; ¹University of Glasgow, GB Research in aerodynamically generated noise attracts significant interest from industry, academia, and the government. One of the most promising aircraft configurations in the growing Urban Air Mobility (UAM) market is the electric vertical take-off and landing (eVTOL) concept because of zero-emission and safety. However, public acceptance of the noise emitted by such vehicles is one of the primary issues in future VTOL/eVTOL development. The main motivation for this work comes from the need for better performance, quieter and safer VTOL aircraft. To this end, accurate prediction of the aerodynamics and aeroacoustics of eVTOL/VTOL is very important. This work conducted CFD performance and acoustics validation using the HMB3 tool from the University of Glasgow with the conformal folding High Lift Propeller experimental data from the NASA Langley Research Centre. Further acoustics validation was conducted with experimental data from GARTEURO AG26 Group DLR. Computational results from the HMB3 tool agree well with experimental data from NASA and DLR. The novelty of this work is to provide efficient and accurate performance and noise prediction strategies for rotors operating at different flight conditions. | |
| 14:00 | 14:30 | 0024 |
Investigation of the Ducted-Propeller Effects on Aeroacoustic Performance using Phase-Locked PIV J. Sun¹, K. Yonezawa, Central Research Institute of Electric Power Industry, JP; H. Liu¹; ¹Chiba University, JP An experimental investigation of aeroacoustics of a ducted propeller for multicopters was carried out. We found that the relative location between the duct and propeller significantly affects the aero-acoustic characteristics. The mechanisms of increase in the FoM and decrease in the noise are discussed using PIV measurements of propeller wakes. | |
| 14:30 | 15:00 | 0057 |
Assessment of Aeroacoustic Optimisation Schemes for a Tilt-Propeller Application in Hover and Cruise O. Bergmann¹, F. Möhren¹, D. Frey¹, F. Janser¹, C. Braun¹; ¹FH Aachen University of Applied Sciences, DE The presented paper provides a novel and detailed guideline on the propeller design under aeroacoustic and aeroelastic constraints. This guideline leads to a computationally efficient design of propellers. Different optimisation schemes are evaluated and compared. |
| 1.7 Tu, 05.9. 13:30 - 15:30 | Dynamics 1: Methods Chair: P. Masarati, POLIMI - Politecnico di Milano, IT | City Hall | Neuer Ratssaal |
| 13:30 | 14:00 | 0132 |
Rotor Loads Prediction via Virtual Sensors - Blending Physics and AI F. Midei¹, A.A. Trezzini², M. Zilletti², C. Sbarufatti¹; ¹Politecnico di Milano, IT; ²Leonardo, IT This paper presents a novel approach for rotor loads prediction via virtual sensors that blend physics-based modeling and artificial intelligence (AI) techniques reconstructing the loads (in this work the lead-lag damper load) by means of merging AI predictions of aeromechanical parameters such as rotor trim with a rotor damper physical model. | |
| 14:00 | 14:30 | 0135 |
Machine Learning Based Approaches for Estimating Rotor Airloads in Hover H. Lee¹, P. Mortimer², P. Seshadri¹, J. Sirohi², J. Rauleder¹; ¹Georgia Institute of Technology, US; ²The University of Texas at Austin, US In this work, we present a machine learning based approach to create a mapping between hub loads, blade air loads, blade deflections, and flow fields. The work aims to overcome the shortcomings of current blade load estimation methods, which are either purely computational with limited expandability, or experimental with difficulties in sensor implementation, especially with smaller-scale rotors. |
| 1.8 Tu, 05.9. 13:30 - 15:30 | Flight Mechanics 1: flow modelling Chair: M. Hoefinger, German Aerospace Center, DE | Helicopter Museum | Eventraum |
| 13:30 | 14:00 | 0004 |
Comparison of different Inflow Models for Intermeshing Rotors T. Ehlert¹, F. Guner¹, A.E. Voigt¹; ¹DLR Institute of Flight Systems, DE The planned paper shows that the calculation of flight performance of a rotorcraft featuring intermeshing rotors can be improved by an adequate inflow model. The Combined Momentum Theory Simple Vortex Theory (CMTSVT)-Model is validated for an intermeshing rotor configuration in hover using flight test data. | |
| 14:00 | 14:30 | 0163 |
System Identification of E-VTOL Rotor in Vortex Ring State by Viscous Vortex Particle Method M. Senipek¹, I.D. Okcu¹, O. Tekinalp², K. Leblebicioglu²; ¹Turkish Aerospacec, TR; ²Middle East Technical University, TR This work includes investigation of vortex ring state by using mid-fidelity viscous vortex particle code. VRS envelopes are investigated for an eVTOL rotor for both RPM and collective pitch control. VRS boundaries are discussed and system identification tasks are performed to identify linear inflow models to represent VRS conditions. The purpose is to minimize VRS boundaries by hybrid control. | |
| 14:30 | 15:00 | 0005 |
An Efficient Helicopter Main Rotor Trim Method based on Computational Fluid Dynamics J. Fu¹, L. Vigevano¹; ¹Politecnico di Milano, IT Presented by: Vigevano, Politecnico di Milano This paper introduces a multi-dimensional delta trim method for the numerical simulation based on CFD to further improve the computational efficiency of helicopter main rotor aerodynamic predictions. With the present trim method, the computational time is saved by about 12% to 31% compared to the original delta trim method for two employed practical helicopter rotor test cases, respectively. |
| 1.9 Tu, 05.9. 13:30 - 15:30 | Crew Station 1 Chair: L. Medici, LEONARDO Helicopters, IT | Helicopter Museum | Archivraum |
| 13:30 | 14:00 | 0076 |
Effect of a Haptic Torque Protection with an Active Sidestick on Pilot's Eyes-Out Capability during a Helicopter Takeoff M. Müllhäuser, DLR, Institut für Flugsystemtechnik, DE Tactile limit cueing with active inceptors can reduce limit exceedances and workload. The assumption, that it would enable the pilots to look more outside and less on the instruments, was not verified yet. In a simulator study the pilots’ gaze during a high performance takeoff maneuver with and without a haptic torque protection system was now measured. It confirmed the assumption. | |
| 14:00 | 14:30 | 0101 |
Usability Analysis and UX Design Recommendations for an Enhanced User Experience of O.R.I.O.N, , the Technical Documentation Digital Viewing Platform M. Faye¹, N. Jahchan¹; ¹Airbus Helicopters, FR The O.R.I.O.N platform is a digital tool/interface used to access Airbus Helicopters technical documentation for maintenance operations. In this human factors study, we sought to test some functionalities that could enhance user experience with the tool and facilitate access and interaction with the technical documentation provided. After conducting an expert ergonomic evaluation, as well as a user’s needs study, we integrated some of the results concerning interactivity and navigation in a software mockup inspired from the current O.R.I.O.N platform using FIGMA, an open source prototyping software. This mockup, which included the new proposed UX (User-eXperience) functionalities was tested using several objective measures such as number of clicks and reaction times, as well as subjective measures such as questionnaires and debriefs. The results showed a statistically significant improvement when technicians used the new mock-up versus the older version of the platform in performance (faster and more accurate), usability, satisfaction, and in some cases overall safety. The study allowed us to validate this Human Factors methodology use-case as part of Airbus Helicopters support and services’ continuous improvement, especially for accompanying IT development and having a validated, intuitive, and satisfactory interface design right the first time and thus economizing on overall costs. It also showed that small easily implementable changes could make a big difference for the end-user and for Airbus in general. | |
| 14:30 | 15:00 | 0120 |
Analysis of Multimodal Signal in Rotorcraft Cockpit D. Marchesoli¹, M.S. Lukasiewicz¹, C. Talamo¹, A. Zanoni¹, P. Masarati¹; ¹Politecnico di Milano, IT A methodology to test and validate the efficiency of multimodal signals in aircraft cockpits is presented. The effects of visual, aural and tactile sensors in acquiring the external information is evaluated through objective and subjective methods in a controlled experimental setting. The results are used in novel cue analysis and in extending existent pilot models. |
| Networking and Refreshmentbreak | 15:30 - 16:00 | |||||||
| 2.4 Tu, 05.9. 16:00 - 17:30 | Aerodynamics 2: Multirotors Chair: A. Le Pape, ONERA - The French aerospace lab, FR | City Hall | Großer Rathaussaal |
| 16:00 | 16:30 | 0006 |
High-fidelity Aerodynamic and Acoustic Evaluations of a Heavy-lift eVTOL in Hover T. Zhang, University of Leicester, GB; G.N. Barakos, University of Glasgow, GB This paper presents the high-fidelity aerodynamic and acoustic evaluations of a complete heavy-lift eVTOL named Skybus, proposed by GKN Aerospace. High-fidelity CFD simulations were performed using the HMB3 solver with SAS modelling. The resolved interactional aerodynamics and near-/far-field acoustics provide valuable guidance for future large eVTOL designs. | |
| 16:30 | 17:00 | 0081 |
Variable Rotor Speed Trim and Interactional Aerodynamics for Quadcopter UAS J.W. Lim, US Army, US; A.D. Thai, Joby Aviation, US UAS/UAM vehicles typically comprise multi-rotors. Thus, strong aerodynamic interactions are not avoidable. Since the rotors operate typically at different RPMs, vehicle simulations are complicated and accordingly vehicle trim in simulation becomes challenging. This paper will investigate variable rotor RPM trim strategy and correlate with the measured data. Using CFD simulations, interactional aerodynamic behaviors will be examined. | |
| 17:00 | 17:30 | 0105 |
Multi-Rotor Wake Interaction Characterization F. De Gregorio¹, K.-S. Rossignol², G. Ceglia¹, J. Yin²; ¹CIRA, IT; ²DLR, DE The paper illustrates the experimental activities carried out on two different test campaigns, one performed at the DLR AWB facility and the second carried out at CIRA laboratories. The scope of the activities is focused on the multi-rotor characterization in terms of loads, velocity fields and acoustic emissions. The acoustic and aerodynamic results are supported by the fluid dynamic measurements. |
| 2.5 Tu, 05.9. 16:00 - 17:30 | Aircraft Design 1 Chair: P. Masarati, POLIMI - Politecnico di Milano, IT | City Hall | Le-Theule-Saal |
| 16:00 | 16:30 | 0046 |
Automated Calculation of the Internal Structure and the Natural Frequencies of Helicopter Rotor Blades with Regard to Automated Rotor Blade Optimization F. Becker¹, S. Kalow¹, R. Bartels¹; ¹German Aerospace Center (DLR), DE In view of an automated multidisciplinary optimization of helicopter rotor blades, a sensitivity and frequency analysis were performed. These are used to assess stiffness, mass and axis positions, as well as the resulting natural frequencies, resulting from the parameter variations of the structural airfoil cross-section topology, to get a more precise choice of suitable parameter constellations. | |
| 16:30 | 17:00 | 0052 |
Development and Application of Improved Tandem Neural Networks for Inverse Design of Rotorcraft Airfoil A. Anand¹, K. Marepally¹, B. Lee¹, J.D. Baeder¹; ¹University of Maryland, US The development and application of improved Tandem Neural Networks (T-NNs) architecture for the inverse design of rotorcraft airfoils is explained in this paper. T-NNs is a novel Deep Learning module for airfoil design, which works like a push-button solution taking 0.36 milliseconds for the design of one airfoil. The improvement in rotor performance by optimization using T-NNs is also presented. | |
| 17:00 | 17:30 | 0175 |
Trajectory Modelling of Transition Regime Using Blade Element Method for Different eVTOL Aircraft Configurations S.K.Y. Lim¹, Z.Y. Boon¹, J. Wang¹; ¹Nanyang Technological University Singapore, SG Presented by: S.-L. Lim Kin Yip, Nanyang Technological University This paper investigates the modelling and derivation of the complete transition regime for an eVTOL aircraft based on the transitional flight trajectory and power requirements. The models are applicable for different eVTOL aircraft configurations, enabling detailed analytical comparisons to be used for the sizing of motor and battery systems and certification of take-off and landing profiles. |
| 2.7 Tu, 05.9. 16:00 - 17:30 | Dynamics 2: Whirlflutter Chair: A. Irwin, LEONARDO Helicopters, GB | City Hall | Neuer Ratssaal |
| 16:00 | 16:30 | 0072 |
Whirl Flutter Predictions for Distributed Tiltrotor Configurations S. Gul, Science and Technology Corporation, US; H. Yeo, U.S. Army, US This paper analyzes high-speed whirl flutter stability of various distributed tiltrotor configurations. Wing beam mode damping increases with distributed rotors, but wing chord and torsion mode damping decreases. The instability speed remains the same. Analysis shows that replacing the large rotor at the wing tip by two smaller rotors can considerably increase the stability at high speeds. | |
| 16:30 | 17:00 | 0102 |
Whirl Flutter Analysis of a Tiltrotor Semi-Span Wind Tunnel Model for Test Results Correlation J. Montaño-Oliveros¹, F. Fonte¹, S. van't Hoff², B. Timmerman²; ¹Leonardo Helicopters, IT; ²Royal Netherlands Aerospace Centre, NL The Clean Sky 2 ATTILA project is aimed at whirl flutter testing of a semi-span wind tunnel model of a tiltrotor. This paper provides a project overview and describes the numerical models used to predict its whirl flutter characteristics. It also presents the sensitivity of such predictions by evaluating the uncertainty of model parameters to get a more useful comparison with experimental results. | |
| 17:00 | 17:30 | 0162 |
A Minimum Complexity Model for the Aeroelastic Analysis of Distributed Propulsion Aircraft A. Tamer, University of Bath, GB; A. Tatar, Leonardo Helicopters, GB Presented by: A. Tatar, Leonardo Helicopters Whirl-flutter occurs as a result of aeroelastic interactions in propellers. Urban mobility designs are expected to exhibit similar and even more complex behaviour with their multiple propellers distributed over the structure. This work aims to extend Reed's flutter model to an multiple propellers to provide a method suitable for the early design phases of distributed propulsion aircraft. |
| 2.9 Tu, 05.9. 16:00 - 17:30 | Engine & Propulsion Chair: R. Heger, AIRBUS Helicopters, DE | Helicopter Museum | Archivraum |
| 16:00 | 16:30 | 0065 |
Engine Air Intake Design and Evaluation - Examples from the Bluecopter™ Demonstrator. A. Garavello¹, T. Kneisch¹, M. Müller¹, A. D'Alascio¹; ¹Airbus Helicopters Deutschland GmbH, DE The Bluecopter demonstrator was developed to prove the feasibility of eco-friendly rotorcraft by demonstrating reduction of CO2, fuel consumption and noise. Several different engine air intakes were designed and tested, with the aim of improving engine efficiency. The present paper summarizes the engine intake design and testing activities carried out in the frame of the Bluecopter project. | |
| 16:30 | 17:00 | 0148 |
Effects of Aero-Propulsive Coupling on High Solidity Electric Ducted Fan Performance for Various Wing Integrations D.A. Safieh¹, J. Rauleder¹; ¹Georgia Institute of Technology, US Wing-mounted electric ducted fans (EDF) have been an enabling propulsive technology for VTOL regional mobility vehicles. Previous research has studied this integration at a systems level but little work has been done at the EDF level. This paper focuses on characterizing the effects that integration location has on the performance and rotor dynamics of the EDF through experiments and CFD. |
| Tu, 05.9. 18:00 - 21:00 | Welcome Reception @ Helicopter Museum Bückeburg | 18:00 - 21:00 | ||||||
| We, 06.9. 08:30 - 09:00 | Registration open | 08:30 - 09:00 | ||||||
| 3.4 We, 06.9. 09:00 - 10:30 | Aerodynamics 3: Methods Chair: T. Schwarz, German Aerospace Center, DE | City Hall | Großer Rathaussaal |
| 09:00 | 09:30 | 0031 |
Validation of a New Solver based on the Vortex Particle Method for Wings, Propellers and Rotors J. Valentin¹, L. Bernardos¹; ¹ONERA, FR The method proposed allows for the simulation of a variety of lifting surfaces (wings, propellers, rotors ...). It is able to account for the viscous effects in the fluid, wake mixing, vortex reconnexion and multiple interaction sources. Several cases are validated and relevant quantities are extracted from the solver and compared with other experimental, analytical and numerical results. | |
| 09:30 | 10:00 | 0113 |
Detached-Eddy Simulation of UH-60A Airloads using an Immersed Boundary Method J.H. Park¹, D. Linton¹, B. Thornber¹; ¹The University of Sydney, AU The full configuration of UH-60A Black Hawk in forward flight is numerically studied using an immersed boundary method and an actuator surface model. This method hugely improves the setup and computational cost by allowing the meshing to be fully automated and solving the high Reynolds number flow on a Cartesian mesh. Results will include fuselage and rotor loads compared with flight test data. | |
| 10:00 | 10:30 | 0152 |
Validation of a Mid-Fidelity CFD/CSD Coupling using the Lattice-Boltzmann Method B. Horvat¹, I. Yavrucuk¹; ¹Institute. f. Helicopter Technology, Technical University Munich, DE This paper focuses on mid-fidelity modeling of a rotor with a Lattice-Boltzmann method (LBM) based fluid solver tightly coupled to a rotor dynamics code. Modelling approaches for an actuator disc and an actuator line model are presented and compared against experimental rotor data. The aim is to validate the LBM setup and leverage its high computational in a rotorcraft context. |
| 3.5 We, 06.9. 09:00 - 10:30 | Acoustics 2: Rotor Chair: R. Heger, AIRBUS Helicopters, DE | City Hall | Le-Theule-Saal |
| 09:00 | 09:30 | 0085 |
Validation of a Surrogate-Based Methodology for Low-Noise UAV/UAM Rotor Design A. Sieradzki¹, P. Kekus¹, W. Klimczyk¹; ¹Lukasiewicz Research Network, Institute of Aviation, PL One of the main problems of UAV and UAM markets is the noise generated by these aircraft. The work focuses on the development of a design methodology for low-noise, high-efficiency rotors. The capabilities of the method are demonstrated and validated through UAV propeller optimization, manufacturing of technology demonstrators, and tests on a dedicated test stand in an anechoic chamber. |
| 3.7 We, 06.9. 09:00 - 10:30 | Dynamics 3: Loads Chair: P. Masarati, POLIMI - Politecnico di Milano, IT | City Hall | Neuer Ratssaal |
| 09:00 | 09:30 | 0063 |
Rapid Dynamic Load Estimation Procedure for Lifting Propellers in Forward Flight F. Möhren¹, O. Bergmann¹, F. Janser¹, C. Braun¹, K.-U. Schröder, RWTH Aachen University, DE; ¹FH Aachen, DE Lifting propellers of air taxis or cargo drones are operated at severe transverse flow, resulting in dynamic loads. This paper presents a rapid dynamic load estimation procedure capable of estimating these loads without needing coupled aeroelastic simulation in the time domain. The steady-state nonlinear equilibrium is linearized to calculate dynamic loads in the frequency domain. | |
| 09:30 | 10:00 | 0142 |
An Exploration of Rotor System Component Loads of the NRC Bell412 Advanced Systems Research Aircraft due to Variations in Flight Control Augmentation M. Alexander, National Research Council Canada / Flight Research Laboratory, CA The Royal Canadian Air Force contracted the National Research Council of Canada’s Flight Research Laboratory to perform flight test research in exploratory Rotorcraft Structural Life Cycle Management. Experimental instrumentation including Rotor State Measurement and Flight Loads Measurement systems were integrated into the NRC Bell 412 Advanced Systems Research Aircraft’s fixed and rotating frame components. Enabling interdependent high bandwidth control and structural loads flight test data gathering, these systems provided insight into factors leading to the generation and the propagation of structural loads through the aircraft’s airframe, hingeless rotor control, and composite rotor blade system. | |
| 10:00 | 10:30 | 0112 |
Direct Load Recognition to Estimate the Damper Load on the H175 Fleet C. Del cistia Gallimard, Airbus Helicopters / Sorbonne Université, FR; K. Nikolajevic¹, F. Beroul¹, J. Denoulet², B. Granado², C. Marsala²; ¹Airbus Helicopters, FR; ²Sorbonne Université, FR This paper applies the load estimation methodology combining Machine learning algorithm and harmonic decomposition to estimate the main rotor Damper load during operational flights. The load estimator is built and evaluated on flight test data showing a good tendency with a little underestimation on the higher load values. It is then computed on the H175 fleet to be analyzed on customer’s flights. |
| 3.8 We, 06.9. 09:00 - 10:30 | Flight Mechanics 2: Fl. Dyn. Modelling Chair: M. Hoefinger, German Aerospace Center, DE | Helicopter Museum | Eventraum |
| 09:00 | 09:30 | 0044 |
Flight Dynamic Modeling and Stability of a Small-Scale Side-By-Side Helicopter for Urban Air Mobility F. Mazzeo¹, D. Fattizzo², G. Bertolani², E.L. de Angelis², F. Giulietti², F. Leali¹, M.D. Pavel, Delft Technical University, NL; ¹University of Modena and Reggio Emilia, IT; ²University of Bologna, IT The main goal of this paper is to investigate the dynamic properties of a small-scale side-by-side helicopter. The analysis will provide important results on the capabilities of VTOLs for Urban Air Mobility scenarios and will be used as a reference model for the control system design of this rotorcraft category. This configuration, which has been little analyzed so far, guarantees high handling qualities, together with a fairly simple design, a high level of societal acceptance, and all the capabilities that characterize a vertical take-off and landing vehicle. Because of these reasons, the paper aims to propose this particular configuration as a major candidate for future UAM missions. | |
| 09:30 | 10:00 | 0078 |
Metrics and Guidelines for Rotorcraft Modeling Accuracy and their Relation to Model Uncertainty: A State-of-the Practice Survey M.D. Pavel¹, A. Aba¹, P. Capone, ZURICH University of Applied Sciences, CH; ¹Delft University of Technology, NL The goal of the present paper is to assess present validation metrics and extend them to new metrics needed for validation of time dependent dynamic models for rotorcraft. Such metrics are especially needed for aircraft/rotorcraft simulation models where model time-dependency and transient behaviour influence the validation confidence. The paper will zoom into the so-called model ‘reliability metrics’ quantifying the probability of the difference between model output and experimental data to be within a desired tolerance interval. In this sense, a new ‘accumulated reliability metric’ will be defined in order to elapse both over aleatory (the inherent variation in the physical system) and epistemic (lack of knowledge of the quantities or processes identified with the system) model uncertainty. | |
| 10:00 | 10:30 | 0093 |
Vibrational Stability Effects in Rotorcraft Flight Dynamics U. Saetti, University of Maryland, US; Z. Chen¹, J.F. Horn¹, T. Berger, U. S. Army , US; ¹Penn State , US Vibrational stabilization is a phenomena where the unstable dynamics of a system about an equilibrium point of interest can be stabilized via periodic forcing of the system at a high-enough forcing frequency. Examples of this phenomena include an inverted pendulum with vibrating suspension point (Ref. 1) or hovering insects, where their hovering cubic is stabilized by the wing periodic flapping motion 3. This paper, starting from a simple example involving an inverted pendulum, will demonstrate the use of the harmonic decomposition method for the study of vibrational stabilization effects. The concept is then extended to analyze the effect of blade imbalance on the flight dynamics of a helicopter. A similar approach was used in Ref. 6 to explain vibrational stabilization of hovering insects. This study is motivated by the fact that eigenvalues of the rotorcraft flight dynamics identified from flight test often differ from those computed with physics-based simulations, and that some commonly observed mismatches may be ascribed to vibrational stability effects due to rotor blade imbalance or other periodic disturbance on the rotorcraft. |
| 3.9 We, 06.9. 09:00 - 10:30 | UAM 1 Chair: B. Ohlenforst, Netherlands Aerospace Centre, NL | Helicopter Museum | Archivraum |
| 09:00 | 09:30 | 0061 |
Technology Requirements for the Development of Aircraft for Urban Air Mobility - Status Quo B. Lukic¹, U. Durak¹; ¹German Aerospace Center (DLR), DE Integrated Modular Avionics (IMA) is an enabler for new technologies. One of these emerging technologies, Urban Air Mobility (UAM), is benefiting from the IMA paradigm. However, it also adds requirements and constraints to the avionics development process. Five major requirements have been identified for the development of next-generation avionics for UAM which are discussed in this paper. | |
| 09:30 | 10:00 | 0103 |
Do VTOL Aircraft create an inherently more Problematic Downwash than Conventional Helicopters? R.E. Brown, Sophrodyne Aerospace, GB Interactions between the multiple wakes of the rotors of eVTOL aircraft could amplify and modify key features of the downwash field, potentially posing a significant danger to personnel on the ground. This paper will present some initial findings regarding the physics of the downwash field that is generated by some of the more common eVTOL configurations that are about to take to the skies. | |
| 10:00 | 10:30 | 0115 |
Stochastic Aeroelastic Analysis of eVTOL Aircraft S. Murugan, IIT Madras, IN Aeroelastic stability and response analysis of an eVTOL with distributed proprotors is performed with uncertainties in system parameters. Initial results of isolated proprotor stability show that randomness in structural and aerodynamic parameters has considerable impact on whirl flutter. In final paper, stochastic model of eVTOl with multiple proprotor designs will be developed and analysed |
| Networking and Refreshmentbreak | 10:30 - 11:00 | |||||||
| 0.4 We, 06.9. 11:00 - 11:45 | Plenary Lecture 4 Chair: K. Pahlke, DLR, DE | |||
| 11:00 | 11:45 |
Advancing Air Mobility – New Paradigms and Lessons Learned Luca Medici, Head of Aircraft System Integration at Leonardo Helicopter Division | ||
| 0.5 We, 06.9. 11:45 - 12:30 | Conference Foto Chair: , , DE | |||
| 11:45 | 12:30 |
Meeting of the participants of the ERF for a group photo at the Helicopter Museum | ||
| Networking Lunch | 12:30 - 13:30 | |||||||
| 4.4 We, 06.9. 13:30 - 15:30 | Aerodynamics 4: Active Rotors Chair: A. Le Pape, ONERA - The French aerospace lab, FR | City Hall | Großer Rathaussaal |
| 13:30 | 14:00 | 0017 |
Simulation of Active Twist Rotor Blades using a Thermal Analogy Method in HMB3 R. Steininger¹, G.N. Barakos¹, M.A. Woodgate¹; ¹University of Glasgow, GB For the development and certification of active twist actuators on rotor blades, accurate simulation of the aeroservoelastic response is required. 1D beam and 2D/3D FEM rotor blade structural models are developed for the STAR rotor and compared within HMB3 CFD solver, and the piezoelectric actuators are implemented via rigid rotation and a thermal analogy method. | |
| 14:00 | 14:30 | 0075 |
Investigations of a Boxed Rotor: The STAR II Rotor in DLR’s Test Hall. G. Wilke, DLR AS-HEL, DE; H. Sugawara¹, T. Yasutada¹, O. Schneider², B.G. van der Wall²; ¹JAXA, JP; ²DLR FT-HUB, DE In anticipation of the upcoming wind tunnel test of the STAR II rotor, it is tested before hand in the rotor test hall at DLR. The rotor is thus operated in-ground effect and within re-circulation. Prior CFD simulations are carried out to investigate the impact on the operation within the test hall. The results are compared against out-of-ground simulations. | |
| 14:30 | 15:00 | 0121 |
Fluid Structure Interaction Investigation of the Aerodynamic Characteristics of a Dynamic Camber Morphing and Pitching Rotor Airfoil M.-K. Yurt¹, A. Abdelmoula¹, J. John¹, I. Yavrucuk¹; ¹Technical University of Munich, DE This paper aims to investigate the fluid-structure interaction effects of the FishBAC concept's dynamic morphing. This study showed that the aerodynamics at different Mach numbers can vary in comparison to uncoupled unsteady CFD results due to aeroelastic effects. The study aims to demonstrate these effects while simultaneously considering pitching and camber morphing. | |
| 15:00 | 15:30 | 0150 |
Towards Active Rotor Analysis using Viscous Vortex Particle Method S. Kumar¹, J. Rauleder, Georgia Tech, US; I. Yavrucuk¹; ¹TU Munich, DE Recently, a large experimental measurement dataset of the full-scale Bo105 rotor was made public that, per our knowledge, has not been used for rotor aeromechanics model validation. This paper brings together a set of analysis tools together for accurately predicting every aspect of rotor performance. Such an excercise is expected to render confidence to active rotor analyses later in the study. |
| 4.5 We, 06.9. 13:30 - 15:30 | Aircraft Design 2: Concept Design Chair: P. Masarati, POLIMI - Politecnico di Milano, IT | City Hall | Le-Theule-Saal |
| 13:30 | 14:00 | 0016 |
Concept Study of a Fast VTOL-UAV Technology-Demonstrator for MUM-T A. Štrbac¹, A.E. Voigt¹, D.H. Greiwe¹, P. Weiand¹, R. Bartels¹, M. Müller², J. Schmiedel², M. Meunier², U.T.P. Arnold², J. Litzba²; ¹German Aerospace Center (DLR), DE; ²Airbus Helicopters Technik GmbH (AHTech), DE The formation of tactical units, which consist of manned and unmanned aircraft, offers the potential to increase the effectivity of the combined flight system. Currently, commercially available VTOL-UAVs are not specifically designed for the fast forward flight. The proposed paper presents an overview of a concept study concerning a fast VTOL-UAV with a maximum speed of at least 180 kt. | |
| 14:00 | 14:30 | 0032 |
A Comparison of three Conceptual Design Approaches applied to an Electric Distributed Lift Aircraft J.M. Vegh¹, R. Scott¹, P.-M. Basset², R. Perret², N. Beals³, R. Singh³; ¹U.S. Army DEVCOM Aviation and Missile Center, US; ²ONERA – The French Aerospace Lab, FR; ³U.S. Army DEVCOM Army Research Lab, US This paper introduces a collaborative effort between the DEVCOM, ONERA, and ARL. Each organization uses their conceptual design toolchain for a common set of geometry. Initial weight, drag, and power estimates for a common sizing mission and set of assumptions are provided along with sizing sensitivities and optimization cases. This work informs areas of uncertainty in eVTOL assessment and directions for tool development. | |
| 14:30 | 15:00 | 0040 |
Rotorcraft Fuselage Drag Estimation Method for Conceptual Design Phase F. Yilmaz¹, A.E. Coskun¹, H. Ibacoglu¹, M. Kilcik¹, T. Kayabasi¹; ¹Turkish Aerospace Industries, TR This paper discusses what changes can be made to drag force, its estimation methods, and how to take it to the desired levels at the earliest phase of the rotorcraft design. To examine the aerodynamic performance of a basic fuselage, a parametric rotorcraft fuselage was generated and CFD analyses have been conducted on different geometries. | |
| 15:00 | 15:30 | 0064 |
Rotor Aeroelastic Stability Assessment in the New Coral Framework C. Pasquali¹, N. Spyropoulos², R. Leibbrandt³, M. Gennaretti¹, V.A. Riziotis², S. Radler³, G. Bernardini¹, G. Papadakis²; ¹Universita degli studi di Roma Tre, IT; ²National Technical University of Athens, GR; ³Kopter Germany GmbH, DE The work presents the development of a data-driven method to assess the aero-elastic stability into the new CORAL design suite (the project involved partners in Italy (RM3), Greece (NTUA) and Canada (CU) under the coordination of Kopter Germany, a member of the Leonardo Group.). The methodology is based on the integration of a reduced order model representation of the unsteady aerodynamic into a linearised blade structural dynamic system. |
| 4.7 We, 06.9. 13:30 - 15:30 | Test & Evaluation 1 Chair: B. van der Wall, German Aerospace Center, DE | City Hall | Neuer Ratssaal |
| 13:30 | 14:00 | 0002 |
Engine Back-up System in Flight Test Campaigns: a new Approach to the Height-Velocity Diagram Demonstration S. Taheri¹, A. Delavet¹; ¹Airbus Helicopters, FR The height-velocity diagram (H/V) is one of the key stages in the Maximum Takeoff Weight demonstration during the certification of a new helicopter or in the event of an increase in mass of an existing helicopter. The recent development of hybrid propulsion solutions allows for the implementation of an electric backup system (EBS). In case of thermal engine failure, this electric power assistance could change the paradigm. Between October and December 2021, Airbus Helicopters France carried out an extensive flight test campaign on the H130 Flightlab presented in this paper. The EBS installed in the Flightlab provides an electric assistance of about 100kW in case of engine failure. Preliminary studies had shown that it could allow a MTOW increase close to 200kg without an H/V diagram modification on the H130 helicopter type. To avoid flying above the certified MTOW on the Flightlab prototype, Airbus Helicopters France used the H130 performance model to convert the 200kg target of mass increase to a H/V diagram area reduction, thus minimizing the applied stress constraint during that campaign. Moreover, battery autonomy and time of charge limited the training of the flight test crew and the gradual approach to these critical points. Airbus Helicopters adapted the thermal engine software to simulate the EBS assistance. The analysis of the flight test results has demonstrated the validity of the mass to the H/V reduction equivalence, successfully mitigating the risk in approach during the flight test procedure. Thanks to this process, Airbus Helicopters is now actively taking into consideration an H130 MTOW extension with a hybrid propulsion system for an upcoming certification. | |
| 14:00 | 14:30 | 0013 |
Development of the UK National Rotor Rig for Aeroelastic Testing of Rotary Wings D. Zagaglia¹, A.D. Croke¹, R.B. Green¹, G.N. Barakos¹; ¹University of Glasgow, GB The purpose of this paper is to detail the development of the UK National Rotor Rig (UKNRR). This rig allows the investigation of Mach-scaled propellers in close to stall conditions, in terms of blade strain gauge data, overall loads, flow diagnostics (PIV, LDA) and blade deformation (DIC). Points of discussion will include its design and development together with some sample data. | |
| 14:30 | 15:00 | 0029 |
Icing and De-icing under Centrifugal Load in DLR’s Whirl Tower Facility S. Kalow¹, R. Bartels¹, O. Schneider¹, D. Sahyoun¹, R. Keimer¹; ¹German Areospace Center (DLR), DE This paper presents the status of the DLR whirl tower, which is being impowered to do icing tests for rotors. In particular the following elements will be discussed: - installation of cooling chamber - flow guiding system - cooling system - spray bar system In this paper detailed information about the technology demonstrators and some results of the first icing and de-icing tests are presented. | |
| 15:00 | 15:30 | 0030 |
Holographic Visual Cues for Mission Task Elements T. Jusko¹, C. Walko¹, L. Kante, TU Dresden, DE; ¹German Aerospace Center (DLR), DE Presented by: T. Jusko, DLR DLR has developed an Augmented Reality (AR) Visual Cueing System (ARVIS) for MTE Handling Qualities Evaluation. The system is designed to simplify the testing process and reduce the need for physical MTE courses. The system uses a Helmet-Mounted Display (HMD) to provide holographic MTE courses for evaluating the aircraft without interfering with the pilot's natural scanning behavior. |
| 4.8 We, 06.9. 13:30 - 15:30 | Flight Mechanics 3 Chair: K. Pahlke, DLR, DE | Helicopter Museum | Eventraum |
| 13:30 | 14:00 | 0077 |
Rotor Control Equivalent Turbulence Input (RCETI) Models for Multi-Rotor Vehicles M.A. Hayajnh, Georgia Institute of Technology, US; J.V.R. Prasad, Georgia Institute of Technology , US This research paper aims to investigate the applicability and scalability of the Rotor Control Equivalent Turbulence Input (RCETI) models to multi-rotor vehicles. The study begins with the development of RCETI models for variable-RPM rotors using the rotor RPM as input and the rotor hub-loads as outputs. Next, the input is changed to incorporate rotor collective-cyclic deflections, which could be used in multi-rotor systems. The resulting RCETI models are then compared to previous work, providing insights into the effectiveness of the proposed approach. Overall, this study offers insights into the potential of the generalization of RCETI models for the use in multi-rotor systems. | |
| 14:00 | 14:30 | 0100 |
Retracting Blade Stall Phenomenon - Review of Investigations Performed during the PZL W-3A Serial and New Blade Projects J. Malecki¹, M. Pokwapisz¹; ¹“PZL-Swidnik” S.A. Leonardo Helicopters Company, PL Submitted paper presents step by step various aspects of the blade stall investigation activities performed from design stage up to qualification flight tests. The results of performed activities are included in the paper together with critical review of possible analytical prediction methods compared with in-flight helicopter investigations. |
| 4.9 We, 06.9. 13:30 - 15:30 | Crew Station 2 Chair: L. Medici, LEONARDO Helicopters, IT | Helicopter Museum | Archivraum |
| 13:30 | 14:00 | 0147 |
Convertiplane Control during Transition: the Collective and Throttle Lever (CATL) A. Abà¹, A. Pedrioli¹, R. Monstein¹, M. Hitz¹, G. Schneider¹, P. Capone¹; ¹ZHAW, CH A novel inceptro has been developed at the ZHAW Centre for Aviation to provide intuitive and effective control of convertiplanes. The paper describes the design and developmenmt of this device called CATL (Collective and Throttle Lever). | |
| 14:00 | 14:30 | 0137 |
Spatial Audio Cueing Algorithms for Augmented Pilot Perception in Degraded/Denied Visual Environments M.T. Morcos¹, S.M. Fishman¹, U. Saetti¹, T. Berger, U.S. Army Combat capabilities DEVCOM, US; M. Godfroy-Cooper², E.N. Bachelder²; ¹University of Maryland, US; ²San Jose State University, US Current perception models for symbiotic human-machine piloting of vehicles are based on the dominant visual (i.e., sight) and vestibular (i.e, equilibrium) cues, but neglect less dominant perception cues, such as somatosensory cues (e.g, full-body haptics) or auditory cues (e.g., 3D audio). The objectives of the present investigation are three-fold. The first objective is to extend the crossover model (Refs. citenum{McRuer}) to secondary sensory cueing paths like full-body haptics. The second objective is to develop efficient haptic cueing strategies that can be used in compensatory tracking experiments (Refs. citenum{McRuer, Klyde}) in place of visual cues. The third objective is to estimate crossover frequency and pilot workload, as well as to identify the human pilot dynamics, for full-body haptics-only, and for combined full-body haptics and visual feedback strategies. Comparisons with visual cueing will help understand the potential differences in pilot equalization and workload when using this secondary sensory path to fly an aircraft. | |
| 14:30 | 15:00 | 0090 |
The Impact of the Installation of Digital Avionics Equipment on the Power Consumption of the Helicopter P. Stronikowski, PZL-Swidnik S.A., PL Main topic of the following document is to analyze and present how the type of avionics built on the helicopter affect its energy requirements. The test object used was a SOKOL helicopter with classic avionics, next a partially modernized version, and finally a planned retrofit with an implemented full glass cockpit. |
| Networking and Refreshmentbreak | 15:30 - 16:00 | |||||||
| 5.4 We, 06.9. 16:00 - 17:30 | Aerodynamics 5: Windtunnel Test Chair: A. Le Pape, ONERA - The French aerospace lab, FR | City Hall | Großer Rathaussaal |
| 16:00 | 16:30 | 0014 |
Experimental Investigation into the Onset of Stall Flutter on Tiltrotor Blades A.D. Croke¹, D. Zagaglia ¹, M.A. Woodgate¹, R.B. Green¹, G.N. Barakos¹; ¹University of Glasgow, GB The purpose of this paper is to characterise the structural behaviour of a tiltrotor blade set at the onset of stall flutter by means of unsteady strain gauge and overall load data. Both the average and spectral content of the strain signals is analysed. Measurements were gathered using the UK National Rotor Rig in DeHavilland wind tunnel at the University of Glasgow. | |
| 16:30 | 17:00 | 0173 |
Experimental Study on Aerodynamic Drag of Booms and Boom Mounted Stationary Rotors on eVTOL Aircraft P.J.K. Koh¹, S.K.Y. Lim¹, J. Wang¹; ¹Nanyang Technological University Singapore, SG Presented by: J.W Wang, eVTOL Research and Innovation Centre This paper investigates the aerodynamic performance and design of longitudinal booms and boom-mounted hover rotors on a tandem wing eVTOL aircraft. Wind tunnel tests were conducted to evaluate the drag contributions at a component level. Subsequently, the placement and sizing of hover rotors were studied to define the directions to achieve an optimal eVTOL aircraft design with longitudinal booms. |
| 5.5 We, 06.9. 16:00 - 17:30 | Aircraft Design 3: Config. Chair: R. Heger, AIRBUS Helicopters, DE | City Hall | Le-Theule-Saal |
| 16:00 | 16:30 | 0054 |
Modelling and Simulation of a Novel Bioinspired Flapping-Wing Rotary MAV X. Huang¹, L. Lu¹, J. Whidborne¹, S. Guo¹; ¹Cranfield University, CN Cranfield University proposed a new flapping-wing rotor system (FWR) that can be applied to MAV (Micro Air Vehicle). Compared with traditional flapping-wing MAV such as Delfly, the product of this project has higher efficiency. , this paper conducts a specific study on its control. | |
| 16:30 | 17:00 | 0098 |
A Weight Prediction Model for Electric Propulsion System applied on Light Helicopters (CS.27) F.L.C. Mauri¹, F. Merlo¹, G. Tramontana¹; ¹Leonardo S.p.A., IT Aim of this work is to present a possible high-level conceptual method of weight prediction to manage configurations where an electric propulsion system is able to support the thermal engine failure to guarantee a complete safe landing and not only an emergency one like autorotation |
| 5.7 We, 06.9. 16:00 - 17:30 | Dynamics 4: Vibration Reduct. Chair: A. Irwin, LEONARDO Helicopters, GB | City Hall | Neuer Ratssaal |
| 16:00 | 16:30 | 0066 |
Optimal Deployment Schedule for Vibration Reduction of Lift-Offset Coaxial Rotorcraft using Individual Blade Control S.H. Hong¹, D.K. Kim¹, S.N. Jung¹; ¹Konkuk University, KR In the present study, we aim at: 1) assessing the accuracy of the rotor-body coupled vibration predictions obtained between the one-way and two-way coupling methods, in reference to XH-59A flight test data in high-speed condition; 2) identifying the vibration behavior of the rotor and the fuselage with the changes in rotor lift-offsets; and 3) finding the best actuation scenario for the minimum vibration using the individual blade pitch control (IBC) scheme. | |
| 16:30 | 17:00 | 0082 |
An Integrated Three-Dimensional Aeromechanical Analysis for the Prediction of Stresses on Lift Offset Coaxial Rotors M. Patil¹, R. Lumba², B. Jayaraman², A. Datta¹; ¹UNIVERSITY OF MARYLAND, US; ²U.S. Army, US Three-dimensional (3-D) solid finite element analysis (FEA) is coupled with 3-D Reynolds-Averaged Navier-Stokes (RANS) computational fluid dynamics (CFD) to study blade and hub stresses of coaxial rotors in high-speed forward flight. This coupling is called the Integrated 3-D (I3D) analysis. The University of Maryland / U.S. Army 3-D structures solver -- X3D is coupled with the CREATE$^{text{TM}}$--AV Helios framework for this analysis. An open-source model with a generic internal structure but with rotor radius, planform, number of blades, hub type, and rotor frequencies loosely resembling the Sikorsky S-97 Raider is developed. Modern coaxial rotors are compromised from heavy rotor hubs reducing their high-speed performance. The subject of this paper is to use I3D analysis to understand 3-D dynamic stresses and strains at the hub. | |
| 17:00 | 17:30 | 0095 |
Feasibility and Effectiveness of a Higher Harmonic Control System for a Medium Utility Helicopter D.-H. Kim, Korea Aerospace Research Institute, KR; J.-S. Park¹, S.-W. Bang¹; ¹Chungnam National University, KR The feasibility and effectiveness of the HHC system for a medium helicopter are investigated through numerical simulation. The HHC system shows effectiveness and the actuators have sufficient control authority. The actuator stroke required for optimal vibration control is 50.6 % of the control range. This is the actuator motion required for changing the blade pitch angle by 1.01 degree. |
| 5.8 We, 06.9. 16:00 - 17:30 | Unmanned Rotorcraft 1 Chair: S. Topczewski, Warsaw University of Technology, PL | Helicopter Museum | Eventraum |
| 16:00 | 16:30 | 0012 |
Using Time-to-contact as a Flight Control Parameter to Improve Rotary-Wing UAS Ship Deck Landings C. Dadswell¹, M. Jump¹; ¹University of Liverpool, GB This paper analyses the use of the optical parameter time-to-contact, tau, to assist with UAS ship deck landings. It shows that tau-based guidance can be beneficial for recovery of UAS onto moving ship decks. Guiding the UAS in the temporal domain, rather than the spatial domain means that the ship motion can be ignored subject to sufficient heave control power. Limitations are also discussed. | |
| 16:30 | 17:00 | 0018 |
An Improved Method for Swing State Estimation in Rotorcraft Slung-Load Applications E.L. de Angelis¹, F. Giulietti¹; ¹University of Bologna, IT A recursive nonlinear filter is proposed to estimate the swing state of a suspended load in rotorcraft applications. The algorithm uses only the data available from onboard IMU and proves to be a fundamental instrument when the stabilization of oscillations is envisaged. The accuracy of the method is guaranteed by the estimation of external disturbances and experimental results prove its validity. | |
| 17:00 | 17:30 | 0019 |
Cooperative Transportation of a Cable-Suspended Load using Rotorcraft: A Minimal Swing Approach E. Costantini¹, E.L. de Angelis¹, F. Giulietti¹; ¹University of Bologna, Dept. of Industrial Engineering (DIN), IT A nonlinear control system is proposed for a cooperative transportation problem involving two agents. The approach satisfies requirements in terms of formation geometry-keeping, trajectory-tracking, payload swing damping, and inter-agent collision avoidance for a generic rotorcraft configuration. A proof of stability and numerical simulations demonstrate the validity of the approach. |
| 5.9 We, 06.9. 16:00 - 17:30 | Certification by Simulation 1 Chair: M. Hoefinger, German Aerospace Center, DE | Helicopter Museum | Archivraum |
| 16:00 | 16:30 | 0127 |
Rotorcraft Flight Simulation to support Aircraft Certification: A Review of the State of the Art with an Eye to Future Applications A. Rylko¹, S. van't Hoff, NLR, NL; L. Lu, Cranfield University, GB; G. Padfield², P. Podzus, DLR, DE; M. White², G. Quaranta¹; ¹Politecnico di Milano, IT; ²University of Liverpool, GB Presented by: G. Quaranta, Politecnico di Milano The paper will review and compare different approaches to better explain what it means to develop the credi-bility of M&S when used for certification purposes. The approach taken by the RoCS team for the uncertainty-quantification aspects of credibility assessment will be presented. Then, the paper will address why, in the opinion of the authors, certification by simulation should be considered the preferred option for the certification of the future class of eVTOL aircraft in Europe, under the Special Condition VTOL standard (SC-VTOL) developed by EASA. | |
| 16:30 | 17:00 | 0087 |
Case Studies to illustrate the Rotorcraft Certification by Simulation Process; CS 29/27 Low-Speed Controllability S. van 't Hoff, Royal Netherlands Aerospace Centre, NL; M. White¹, C. Dadswell¹, L. Lu, Cranfield University, GB; G. Padfield¹, G. Quaranta, Politecnico di Milano, IT; P. Podzus, German Aerospace Centre, DE; ¹University of Liverpool, GB The paper illustrates the application of the Rotorcraft Certification by Simulation (RCbS) process to the CS29/27 low-speed controllability requirements. The case study considers all phases of the RCbS process, exploiting existing low-speed controllability flight test data where available and reports on piloted simulations performed to explore practical implementation of the RCbS process. | |
| 17:00 | 17:30 | 0124 |
Case Studies to Illustrate the Rotorcraft Certification by Simulation Process; CS 29/27 Category A Rejected Take-Off, Confined Area M. White¹, C. Dadswell¹, G. Padfield¹, S. Van't Hoff², R. Bakker², L. Lu, Cranfield University, GB; G. Quaranta, Politechnico di Milano, IT; P. Podzus, DLR, DE; ¹The University of Liverpool, GB; ²Royal Netherlands Aerospace Centre, NLR, NL Presented by: D White, The University of Liverpool The Rotorcraft Certification by Simulation project is developing flight model and flight simulator fidelity guidance to support the use of simulation in certification. This abstract demonstrates the importance of flight simulator vestibular and visual motion features for supporting or replacing flight testing for the CS-29 Category A Rejected Take Off and will inform new guidance for Industry. |
| We, 06.9. 19:00 - 23:00 | Conference Dinner @ Schloss Bückeburg (Registration required!) | 19:00 - 23:00 | ||||||
| 6.4 Th, 07.9. 09:00 - 10:30 | Aerodynamics 6: Coaxial Rotors Chair: A. Le Pape, ONERA - The French aerospace lab, FR | City Hall | Großer Rathaussaal |
| 09:00 | 09:30 | 0034 |
Comparing 3D and 2D CFD for Mars Helicopter Ingenuity Rotor Performance Prediction W.J.F. Koning¹, B.G. Allan, NASA Langley Research Center, US; E.A. Romander¹, W. Johnson¹; ¹NASA Ames Research Center, US Coaxial rotor performance simulations for the Mars Helicopter Ingenuity rotor are carried out using comprehensive analyses in CAMRADII. Analyses are presented using both a high-fidelity 3D CFD model of the rotor, as well as 2D CFD models of the airfoil sections. Rotor performance metrics and differences between 2D and 3D airfoil performance and rotor stall behavior are presented. | |
| 09:30 | 10:00 | 0141 |
Vibration Reduction of Coaxial Rotor by Blade Installation Phase Angle T. Yumino¹, H. Sugawara², Y. Tanabe², M. Kameda¹; ¹Tokyo University of Agriculture and Technology, JP; ²Japan Aerospace Exploration Agency, JP Aerodynamic lift variations of an isolated coaxial rotor system were analyzed by a computational fluid dynamics (CFD) approach. The numerical results show that the appropriate blade installation phase angle could suppress the vibration during the high speed forward flight to the same level as that in hover. |
| 6.5 Th, 07.9. 09:00 - 10:30 | Acoustics 3: Toolchains Chair: R. Heger, AIRBUS Helicopters, DE | City Hall | Le-Theule-Saal |
| 09:00 | 09:30 | 0026 |
A Comprehensive Helicopter Acoustic Modeling Tool based on Simulation and Experiment F. Guntzer¹, J. Caillet¹, C. Cariou¹, J.-P. Pinacho¹, P. Dieumegard¹, E. Roca León¹; ¹Airbus Helicopters, FR The paper will describe the activities run in the frame of the MOTUS project. The developed methodology allows to correct an acoustic measurement database from simulation results in order to model the noise emission of a prototype H/C, accounting for the introduction of low-noise technology bricks (e.g. NR decrease, modified main rotor blade, modified Fenestron, engine soundproofing…). The obtained hemisphere database can then be used to simulate various use-cases, from certification levels predictions to noise footprints evaluation on realistic scenarios, accounting for Low Noise Procedures. All these results can then be auralized in a subsequent step, to address advanced metrics related to noise annoyance. | |
| 09:30 | 10:00 | 0080 |
Acoustic and Aerodynamic Evaluation of DLR Small-Scale Rotor Configurations within GARTEUR AG26 J. Yin¹, F. De Gregorio², K.-S. Rossignol¹, L. Rottmann¹, G. Ceglia², G. Reboul, French Aerospace Center - ONERA, FR; G. Barakos³, G. Qiao³, M. Muth*, M. Kessler*, A. Visingardi², M. Barbarino², F. Petrosino², A. Zanottiº, N. Obertiº, L. Galimbertiº, G. Bernardini, C. Poggi, L. Abergo, F. Caccia; ¹German Aerospace Center - DLR, DE; ²Italian Aerospace Research Center - CIRA, IT; ³University of Glasgow, GB; *University of Stuttgart, DE; ºPolitecnico di Milano, IT; Roma Tre University, SA; King Abdullah University of Science and Technology - KAUST, SA This paper focus on the numerical comparison activities conducted in GARTEUR Action Group HC/AG-26. The aim is to develop and validate numerical prediction methods for the noise prediction for multirotor systems. DLR small rotor configurations, including isolated and rotor/rotor configurations are chosen for the common simulations. For the simulation of the various test cases, the numerical approaches from each partner are applied. The aerodynamic simulations necessary for the aeroacoustic predictions are conducted with a range of fidelity numerical methods, varying from CFD to lifting line. In the case of the acoustic installation effects, a scattering code can be applied or directly extract from CFD. The introduction of the experimental approach used in the acoustic/PIV test, including the rotor model, the instrumentation and the data reduction will also be presented. The methodologies applied in the numerical simulations by the partners will then be described and analyzed to point out their strengths and weaknesses. The aerodynamic and acoustic predictions will be analyzed and compared either code to code or with available test results for different configurations. | |
| 10:00 | 10:30 | 0126 |
Deep Learning Surrogate Model for Rotorcraft Aeroacoustic Simulations using a Geodesic Convolutional Network B. Erwee¹, A. Scandroglio¹, N. Sanguini¹, T. Benacchio¹, F. Di Cintio¹; ¹Leonardo Helicopters, GB This paper presents a new deep learning surrogate model, able to accurately predict blade pressure distributions for helicopter main rotors in various flight conditions. Once trained, the surrogate model is able to predict new cases in 0.1s with an R2 of 99% - 10,000 faster than the existing tool. The helicopter aeroacoustic tool chain can now run in just 8 minutes, down from 8 hours. |
| 6.7 Th, 07.9. 09:00 - 10:30 | Dynamics 5 Chair: A. Irwin, LEONARDO Helicopters, GB | City Hall | Neuer Ratssaal |
| 09:00 | 09:30 | 0009 |
Possibilistic Uncertainty Quantification for Parametrically Reduced Models of Dynamic Systems with Many Inputs L. Frie¹, T. Könecke¹, M. Hanss¹, P. Eberhard¹; ¹ITM University of Stuttgart, DE Possibility theory is applied to describe how uncertain input parameters influence the dynamics of a mechanical flight system. To reduce numerical costs, parametric model order reduction with the decomposition of input directions is employed. This is a novel methodological approach that allows the use of arbitrary input information such as quasi-vacuous distributions. | |
| 09:30 | 10:00 | 0131 |
Wind Tunnel Test of a Single Electrical Lift Thrust Unit to assess Static and Dynamic Loads M. Zilletti¹, D. Prederi¹, R. Costantini¹, M. Zaccara¹, M. Ricciardi¹, G. Morelli, Politecnico di Miano, IT; P. Masarati, Politecnico di Milano, IT; ¹Leonardo, IT This paper is focused on the design of an experimental wind tunnel test rig to assess the static and dynamic loads generated by electrical Lift Thrust Units (LTUs) in different flight conditions. The test results are used for comparison and correlation with simulation results obtained from an analytical comprehensive tool. | |
| 10:00 | 10:30 | 0157 |
Comfort Assessment in Urban Air Mobility Vehicles A. Tamer, University of Bath, GB; A. Zanoni¹, P. Masarati¹; ¹Politecnico Di Milano, IT Small-scale urban air mobility (UAM) vehicles have already proved their feasibility for emission-free short-range missions. Most UAM designs are of unconventional architecture, which could lead to unanticipated vibrational issues. This work presents how comfort assessment in UAMs may be approached by offering a modular and versatile simulation environment. |
| 6.8 Th, 07.9. 09:00 - 10:30 | Flight Mechanics 4 Chair: P. Capone, Zurich University of Applied Sciences, CH | Helicopter Museum | Eventraum |
| 09:00 | 09:30 | 0149 |
Effect of Torsional Flexibility on an Unmanned Helicopter Performance Including Compressibility Effect A.F. Uzunkaya, ASELSAN, Middle East Technical University, TR; Y. Yaman, Middle East Technical University, TR In comprehensive helicopter analyses tools, helicopter blades could be modeled as rigid beams in terms of torsional direction. Main objective of this work to question how valid this rigid beam assumption is. To obtain the performance characteristics of the reference helicopter a trim code is written modeling the reference blade as either rigid or elastic including compressibility effects. | |
| 09:30 | 10:00 | 0166 |
AW09 Tail Rotor System Control Authority Assessment S. Bölk¹, A. Masi¹, F. Scorcelletti¹; ¹Kopter Group AG, CH Presented by: S. Bölk, Kopter Group AG An innovative formulation for ducted tail rotor is presented, including a validation of the model itself in hover against experimental data. Model is then used to assess the pedal control authority in typical helicopter flight conditions. | |
| 10:00 | 10:30 | 0167 |
Flight Trajectory Tracking for a Helicopter in Tail Rotor Failure Y.O. Arslan¹, I.D. Okcu¹; ¹Turkish Aerospace, TR Trajectory tracking for a conventional helicopter in tail rotor failure is achieved by introducing a new input, the main rotor speed The generated trajectories in the previous work are enhanced and are given as a reference to the tracking controller Communication of Simulink and Flightlab is established to have the controller and nonlinear model in separate environments and perform simulations |
| 6.9 Th, 07.9. 09:00 - 10:30 | Certification by Simulation 2 Chair: M. Hoefinger, German Aerospace Center, DE | Helicopter Museum | Archivraum |
| 09:00 | 09:30 | 0033 |
Case Studies to illustrate the Rotorcraft Certification by Simulation Process; CS 27/29 Dynamic Stability Requirements L. Lu, Cranfield University, GB; G. Padfield¹, M. White¹, C. Dadswell¹, G. Quaranta, Politecnico di Milano, IT; S. van’t Hoff, Royal Netherlands Aerospace Centre, NL; P. Podzus, German Aerospace Center, DE; ¹University of Liverpool, GB Under the framework of the RoCS project, preliminary Guidance for the application of (rotorcraft) flight modelling and simulation has been developed in support of certification for compliance with standards CS-27/29, PART B (Flight) and other flight-related aspects. This paper presents the results from the case study on Dynamic Stability, CS 29.181 and CS 27.171 plus Appendix B Instrument Flight Rule flight, to illustrate the application of the Guidance. The work present will benefit the government regulators, aerospace industry including the emerging EVTOL manufacturers, and other fields such as electrical vehicles. | |
| 09:30 | 10:00 | 0128 |
Rotorcraft Flight Simulation so support Aircraft Certification: Methodologies to Evaluate the Uncertainties on a Tiltrotor Model M. Daniele¹, M. Mamino¹, G. Quaranta¹; ¹Politecnico di Milano, IT Presented by: M. Daniele, Politecnico di Milano The paper will present the methodologies used to assess the uncertainties for a tiltrotor model flying at low speed. Calibration and uncertainty analysis have been performed using Dakota, an open source toolkit which provides a flexible interface between different simulation codes. Main advantage of Dakota toolkit is the ability to adapt to various kind of dynamic solvers, by providing a set of input variables and collecting the response functions to infer the results. | |
| 10:00 | 10:30 | 0145 |
Virtual-Pilot-in-the-Loop Simulation Model to assess Helicopter Routes Feasibility F. Roncolini¹, G. Quaranta¹; ¹Politecnico di Milano, IT In this work a closed-loop simulation model featuring the helicopter dynamics model and a virtual pilot model is developed. This closed-loop model is used to assess the feasibility of candidate Point-in-Space routes, in order to introduce an intermediate simulation step between the design phase and the experimental testing phase, saving a large amount of flight test hours. |
| Networking and Refreshmentbreak | 10:30 - 11:00 | |||||||
| 0.6 Th, 07.9. 11:00 - 11:45 | Plenary Lecture 6 Chair: K. Pahlke, DLR, DE | |||
| 11:00 | 11:45 |
Certification of eVTOL – Status and outlook David Solar, European Union Aviation Safety Agency | ||
| 0.7 Th, 07.9. 11:45 - 12:30 | Plenary Lecture 7 Chair: K. Pahlke, DLR, DE | |||
| 11:45 | 12:30 |
Future platforms and operations – a view on german army aviation Torsten Kasper, Army Concepts and Capability Development Center | ||
| Networking Lunch | 12:30 - 13:30 | |||||||
| 7.4 Th, 07.9. 13:30 - 15:30 | Aerodynamics 7: Appl./Eval. Chair: T. Schwarz, German Aerospace Center, DE | City Hall | Großer Rathaussaal |
| 13:30 | 14:00 | 0007 |
Coupled Ship Airwake and Rotor Airloads Simulation Methodology G. Frassoldati, Leonardo S.p.A., Università Degli Studi Roma Tre, IT; C. Capizzi¹, D. Prederi¹, S. Melone¹; ¹Leonardo S.p.A., IT This study describes a methodology to evaluate the aerodynamic field on ship decks, finding the best possible strategy to study their impact on airloads estimation for rotors operations when stationing on deck. The simulations spaced the possible settings in RANS and SRS. Airloads estimation on the rotor gives the measurable advantage in terms of accuracy with respect to legacy workflows. | |
| 14:00 | 14:30 | 0053 |
Actuator Surface Model and Blade Resolved Simulations of an Attack Reconnaissance Class Rotor in Hover and Forward Flight A. Coyle¹, B. Thornber¹; ¹The University of Sydney, AU Aerodynamic simulations of an Attack Reconnaissance Class helicopter rotor were preformed using a hybrid CFD technique and a blade resolved CFD method employing a novel Radial Basis Function approach which allows the scaling of the method to large and complex meshes. The results in hover and forward flight showed good agreement with experimental and simulation datasets. | |
| 14:30 | 15:00 | 0092 |
Sensitivity of Rotor Aeroelastic Predictions with Two-Equation Turbulence Models A. Crawford¹, P. Sridhar¹, M.J. Smith¹; ¹Georgia Institute of Technology, US This work is the first implementation of the Kok k-omega turbulence model in the structured CFD solver OVERFLOW. This allows for further comparison and insight into the effect of turbulence model on rotor systems investigated first by the US and French researchers in MOA Task 12. This work will examine the sensitivities of turbulence models under various aerodynamic and aeroelastic conditions. | |
| 15:00 | 15:30 | 0136 |
Evaluation of a Range of Modeling Approaches for UAV Unsteady Aerodynamics B. Oates¹, P. Su¹, J.T. Hrynuk, DEVCOM Army Research Laboratory, US; M.J. Smith¹, J. Rauleder¹; ¹Georgia Institute of Technology, US This paper examines and compares the fidelity and computational cost between three levels of aerodynamic model fidelity. Aerodynamic force predictions from a reduced-order model, and high fidelity Computational Fluid Dynamics (CFD) are compared with one another and correlated with experimental results for a novel Unmanned Aerial Vehicle (UAV) model. |
| 7.5 Th, 07.9. 13:30 - 15:30 | UAM 2 Chair: B. Ohlenforst, Netherlands Aerospace Centre, NL | City Hall | Le-Theule-Saal |
| 13:30 | 14:00 | 0116 |
Performance, Environmental, and Mobility Analysis of Large Capacity Fast Rotorcraft Configurations for the European Regional Air Traffic Market L. Declerck¹, M. Cruellas Bordes¹, C.A. Saias², D. Nalianda², B.D.J. Schreiner², G.A. Misté³, A. Dal Monte³, E. Benini³, A. Junior, German Aerospace Centre, DE; ¹Royal Netherlands Aerospace Centre, NL; ²Cranfield University, GB; ³University of Padova, IT Presented by: B. D. J. Schreiner, Cranfield University The FASTRIP2050 (Clean Sky2) project investigates the performance, environmental impact, and mobility benefits of a large capacity tiltrotor and compound rotorcraft on regional air traffic routes. Compared to other studies in this field, the project includes a feasibility study of a hybrid electric powertrain to reduce emissions and studies the mobility benefits on the European travel network. | |
| 14:00 | 14:30 | 0123 |
Lightning Threat on VTOLS S. Zehar¹, B. Tagliana¹, M. Meyer¹, P. Lalande², F. Pechereau²; ¹Airbus Helicopters, FR; ²ONERA, FR Lightning zoning is the basis to define the threat at rotorcraft and components/equipment level, for both direct and indirect effects. Due to recent evolution of the lightning zoning, and with the development of new VTOL with non-conventional shapes, there is a need to have a validated mean of compliance or at least as an intermediate step a help for the design of protections and the certification phases. The paper presents the status of the numerical tools available with example of zoning computations/methodology. All the work done and presented in the framework of this paper could be also useful for the identification of the lightning threat of protuberant equipment items located in zone 3. Another future step could be the implementation of a validated Means of Compliance (MoC) by modelling, and revision of zoning document (ARP5414/ED-91) to include generic zoning of VTOLs. | |
| 14:30 | 15:00 | 0154 |
A Nature Inspired Guidance Method for Improving Social Acceptance of Urban Air Mobility Z. Bilgin¹, M. Bronz, ENAC, Université de Toulouse, FR; I. Yavrucuk¹; ¹Technical University of Munich, DE This study is the extension of our previous work where panel method based guidance algorithm for urban air mobility is proposed. This study aims to introduce further safety features to the existing method to improve social acceptance of urban air mobility. Furthermore, effectiveness of the proposed method will be evaluated through hardware experiments conducted in Toulouse, France. |
| 7.7 Th, 07.9. 13:30 - 15:30 | Test & Evaluation 2 Chair: B. van der Wall, German Aerospace Center, DE | City Hall | Neuer Ratssaal |
| 13:30 | 14:00 | 0036 |
Experimental and Numerical Evaluation on the Helicopter Rotor Response under the Crash Impact C. Lee¹, K. Kong¹, S.-H. Kang¹, M. Hwang¹, S. Shin¹; ¹Seoul National University, KR Collision analysis of the rotor blades under hard impact is conducted by both experimental and numerical approach. UH-60A main rotor blade is selected and designed for each experiment. Drop test is designed in accordance with MIL-STD 1290A and whirl tower test is conducted for hover of 4-blade and one-blade-out condition. In addition, the correlation against numerical result is investigated. | |
| 14:00 | 14:30 | 0074 |
Examination of Dynamic Characteristics of a CONEX Container in Dual Point Carriage from Simulation and Wind Tunnel Test Z. Chen¹, J.F. Horn¹, J. Enciu¹, R. Raz², A. Rosen², L. Cicolani, San Jose State Research Foundation, US; ¹Penn State University, US; ²Technion-Israel Institute of Technology, IL Presented by: J.F. Horn, Penn State University This paper discusses the dynamic characteristics of a dual point CONEX examined from simulations and wind tunnel tests with the purpose of expanding the speed envelope for slung load carriage for the supply of efficiency and safety in combat zones. The usage of an active cargo hook for load stabilization at higher speeds is also discussed which has not been looked at for dual point slung load. | |
| 14:30 | 15:00 | 0091 |
RACER - Testing of Major Components M. Blacha, Airbus Helicopters, DE; P. Burden, Hamble Aerostructures, GB In this paper a simple test strategy of the RACER's major structural assemblies. In this approach only main new major sub-assemblies are tested separately without the need for limit load tests on the real vehicle. This saves cost and time as no full second airframe structure has to be built. This approach supports the activities for the permit-to-flight in a quick, simple, and cheap manner. | |
| 15:00 | 15:30 | 0143 |
Powerplant Control System Tuning Activities C. Esen¹, H.M. Yalcinkaya¹, E. Zengin¹, K. Sansal¹, A.A. Ezertas¹, H.E. Tarhan¹; ¹Turkish Aerospace, TR Presented by: C. Esen, Turkish Aerospace T-625 helicopter is a light utility multi role helicopter that is designed by Turkish Aerospace Helicopter Group. It is equipped with twin CTS800-4AT turboshaft engines developed by the Light Helicopter Turbine Engine Company (LHTEC). Engines are controlled by an advanced, redundant dual-channel full authority digital engine control (FADEC) system. This paper presents aspects of the load anticipation and dynamic response characterization of engine control system in powerplant integration process of T-625 helicopter, together with the results of engine control tuning flight test campaign which are performed to fine-tune FADEC controller parameters during flight. |
| 7.8 Th, 07.9. 13:30 - 15:30 | Unmanned Rotorcraft 2 Chair: S. Topczewski, Warsaw University of Technology, PL | Helicopter Museum | Eventraum |
| 13:30 | 14:00 | 0047 |
Comprehensive Analysis of Single and Coaxial Small UAS Propellers in Axial Forward Flight J.D. Sinsay, Science & Technology Corp., US; L. Battey¹, A. Milligan¹; ¹U.S. Army DEVCOM AvMC, US CAMRADII results compared with single SUAS propeller WTT results. The SUAS propeller operates in a Reynolds Number range where laminar to turbulent boundary layer transition behavior strongly impacts airfoil section behavior. Results using various prediction methods for airfoil behavior are compared and discussed with regards to their impact on overall propeller performance prediction accuracy/ | |
| 14:00 | 14:30 | 0069 |
Hierarchal Planning demonstrated in Autonomous Flight; Integration of the Risk-Aware Path Planner with a Sense-And-Avoid Planner on a Black Hawk Helicopter C. Goerzen¹, M. Takahashi¹, M. Whalley², G. Schulein, San Jose State University Founcation, US; N. Mielcarek, Universities Space Research Association, US; W. Ogden², J. Carr², C. Ott², K. Thomazios², D. Waldman²; ¹Capabilities Development, US; ²U.S. Army Combat Capabilities Development, US A novel implementation of hierarchal planning has flown a Black Hawk helicopter. It has three levels: on top is a mission level planner based on terrain maps, in the middle is a fully 3-dimensional sensor-and-avoid planner, and on the bottom is the waypoint tracking and inner loop control. This is the first publication describing the full system, including simulation and flight test results. | |
| 14:30 | 15:00 | 0071 |
Non-Linear Approach for the Unmanned, Compound Helicopter Control S. Wasniewska¹, S. Topczewski¹; ¹WUT, PL The paper addresses the issue of an unmanned compound helicopter control. To date, there has been a lot of work dealing with small-scale rotorcraft control, but very little on compound helicopters. The proposed nonlinear control approach can overcome the limitations of the linear controllers and may be more suitable for objects with highly complex dynamics. | |
| 15:00 | 15:30 | 0084 |
A Model-Based Wind Estimation Method for Unmanned Helicopter S. Nazarov¹, P.-O. Gutman¹; ¹Technion IIT, IL This study describes a new algorithm for wind/turbulence estimating using a standard unmanned rotorcraft sensor kit. The identified linear helicopter model is modified into a quasi-nonlinear model. A nonlinear Kalman filter is designed using the scaled unscented transformation to estimate wind in the North-East-Down frame. Results are validated on actual Black Eagle-50 helicopter flight tests. |
| 7.9 Th, 07.9. 13:30 - 15:30 | Structures and HUMS 1 Chair: L. Medici, LEONARDO Helicopters, IT | Helicopter Museum | Archivraum |
| 13:30 | 14:00 | 0070 |
Analytic Mixed Variational Beam Approach for Thin-Walled Composite Blades with Three-Dimensional Warpings J.S. Bae¹, S.N. Jung¹; ¹Konkuk University, KR In this work, a fully analytic beam formulation based on Reissner-Tsai mixed variational theorem has been developed for general thin-walled composite beams with 3D contour warpings. Unlike most of the existing engineering beam theories, no priori or simplifying assumptions are introduced in the formulation. Several composite beam cross-sections are presented for validation of the present approach. | |
| 14:00 | 14:30 | 0108 |
Resonance Avoidance of Variable Speed Rotors using Variable Stiffness Blades M.R. Amoozgar¹, V. Portapas¹; ¹University of Nottingham, GB This paper presents a new resonance avoidance and load reduction concept based on designing a blade with adaptive structure. In this concept, layers of variable stiffness smart materials (e.g. temperature-variable polymers) are added to the original blade. When activated, their material properties (e.g. Young’s modulus) changes, and hence the blade stiffness can also be changed in flight. | |
| 14:30 | 15:00 | 0146 |
Aeroelastic Optimization of Helicopter Composite Horizontal Stabilizer Using the Superior Damping Properties of Flax Fibers J. John¹, L. Gaugelhofer¹, C. Hackner¹, J. Cumiskey¹, I. Yavrucuk¹; ¹Technical University of Munich, DE This study uses flax fiber hybridization to develop a composite vertical stabilizer with higher damping properties. High-performing flax and carbon prepregs are used to manufacture the tailplane structure, and a 3D-Layup design is developed using a Finite-Element Model to achieve maximum damping while maintaining similar eigenfrequencies and weight as a conventional reference stabilizer. Experimental modal analyses are conducted using a laser vibrometer, GOM Aramis optical measurement system, and impulse technique to determine dynamic behavior and calculate damping using the Half-Power Bandwidth Method. Stiffness is determined through dynamic modal analysis and static bending tests, and a special test bench is used to examine critical modes in a non-isolated environment. The simulation models are compared to experimental results to improve damping predictions, and design decisions for use on helicopter structures can be derived from the obtained results. Preliminary results indicate that a damping improvement of about four times is possible. |
| Networking and Refreshmentbreak | 15:30 - 16:00 | |||||||
| 8.4 Th, 07.9. 16:00 - 17:30 | Aerodynamics 8: Performance Chair: T. Schwarz, German Aerospace Center, DE | City Hall | Großer Rathaussaal |
| 16:00 | 16:30 | 0062 |
JAXA-ONERA-DLR Cooperation: Results from Multi-Point Aerodynamic Optimization of a Rotor in Hover and Forward Flight J. Bailly, ONERA, FR; G. Wilke, DLR, DE; K. Kimura¹, Y. Tanabe¹; ¹JAXA, JP Presented by: G. Wilke, DLR Helicopters are versatile machines, capable of vertical take-off and landing, hovering, and forward flight. Each flight configuration has its own physical characteristics and difficulties to be evaluated numerically. Different levels of fidelity of simulation codes, based on lifting line, unsteady aerodynamics, fluid/structure coupling can be used to simulate these types of flows, with increased degrees of accuracy. The optimization of helicopter rotor blades is a challenging problem, which may involve several disciplines, and/or several objectives, and/or several flight points. Generally, the different objectives are often antagonistic in nature, and require compromises and trade-off solutions. The three research organizations, JAXA, ONERA and DLR have decided to combine their efforts in 2019 to compare and improve their own aerodynamic simulation and optimization strategies. The first two work packages of this collaboration involved single-objective optimizations in hovering flight and then in forward flight. The objective of the study presented in this paper is to perform and compare aerodynamic optimizations combining these two flight cases. The optimization procedures are based on surrogate models, generated by low- and high- fidelity simulation codes. The first results clearly show the antagonism of the performances expected for the different designs according to the flight configurations. In particular, the Best Hover designs show an estimated gain of about 6% in hovering flight at the expense of a deterioration of about 25% in forward flight. Conversely, the predicted gains for the Best Forward Flight designs are of the order of 15% in forward flight at the expense of 15% degradation in hover flight. The Pareto fronts obtained by the partners will be used to estimate the gains as a function of the different mission types of the aircraft between hovering and forward flight. | |
| 16:30 | 17:00 | 0104 |
Performance of Asymmetric Propellers under Varying Blade Spacing D. Usov¹, T. Chronis¹, A. Filippone¹; ¹The University of Manchester, GB This paper investigates the performance of two-bladed, radially asymmetric propellers with uneven blade spacing during axial flight. The study’s objective is to analyse the impact of blade spacing on thrust, power, and propulsive efficiency in a two-bladed asymmetric propeller. To achieve this, three asymmetric propellers were simulated using the free-vortex wake method, varying blade spacing from 30 to 90 degrees. The study compared the outcomes of the simulations to those of a reference propeller to identify any possible variations in performance. The results indicated only a slight change in overall propeller performance. It was determined that the marginal deterioration in the performance of the propeller was the consequence of the aerodynamic interference effects between the blades, which ultimately offset each other. Therefore, if such propeller geometries offer benefits beyond performance, it is sensible to utilise them. |
| 8.5 Th, 07.9. 16:00 - 17:30 | Aircraft Design 4: Components Chair: L. Medici, LEONARDO Helicopters, IT | City Hall | Le-Theule-Saal |
| 16:00 | 16:30 | 0050 |
Design and Manufacture of Dynamic Assemblies and Compo-Site Drive Shafts for Tiltrotor S. Barlet-Bas¹, F. Malburet², L. Roucoules², C. Lopez¹, B. Pierrel¹, F. Orsoni¹, G. Valembois, Conseil&Technique, FR; ¹NEXTEAM, FR; ²Arts et Métiers, FR Presented by: S. Sébastien, NEXTEAM The submitted paper aims to present the development of the components of a mechanical drive line using composite shafts between an engine and a rotor. This project is part of the STEADIEST (Supercritical Composite main Drive SysTem) project funded by Clean Sky 2, July 2019 to September 2022. Project team was consisting of Neaxteam group, Conseil & Technique (compagnies in the aircraft industry - France) and Arts et Métiers (University - France). The main objective was to study, develop and to demonstrate by testing a concept of supercritical composite shaft drive line with high level of technical performances (low weight, friendly support, improved dynamic behavior reducing vibration) and optimization of cost (architecture and interfaces between parts, reduction of references and design to cost approach). The first part will present the design approach implemented. The method used is based on simultaneous engineering concepts by modeling the interaction of all the actors to control the emergence of the CAD model. the method aims to provide a rational CAD model to the designer in order to help him identify the room for innovation as well as the immutable (i.e. constrained) elements. This approach has made it possible to master the solution design space by making it easier and more understandable to integrate new technical solutions into the initial design. The second part present the pre-design and the search for the optimal architecture to identify the main characteristics of the drive shafts and the associated components (geometry, characteristics of the composites). Work focused on optimizing the weight and reliability of the drive system through better control of the dynamic behavior of the shaft, and the control and reliability of manufacturing processes. Particular attention and work have been paid to the material and to the study of the coupling between composite and metal. As composite shafts use an original manufacturing process, it was essential t | |
| 16:30 | 17:00 | 0073 |
Mission Performance of Different Landing Gear Types in Medium Sized Twin Engine Helicopters V. Zappek¹, I. Yavrucuk¹; ¹Institute for Helicopter Technology, DE Retractable wheeled landing gears are standard equipment on most large helicopters. They offer better aerodynamics, improved passenger comfort during landing and easier taxiing compared to skids. However, they are significantly more complex, heavier and more expensive. This paper explores the influence of weight and aerodynamics on a medium sized helicopter using four example missions. |
| 8.7 Th, 07.9. 16:00 - 17:30 | Dynamics 6 Chair: K. Pahlke, German Aerospace Center, DE | City Hall | Neuer Ratssaal |
| 16:00 | 16:30 | 0160 |
Flutter Assessment of a Rotor Blade in Steady Axial Flight based on Indicial Aerodynamics J. Arnold, DLR German Aerospace Center, DE This abstract summarizes the aeroelastic modelling and steps performed towards an improved flutter assessment of the 7AD rotor model in steady axial flight utilizing a multibody system (MBS). The objective is the stability assessment of the elastic rotor blade using tight coupling between the multibody system and an unsteady aerodynamic model based on indicial functions for rotor blade sections. The aerodynamic model has been developed at the DLR Institute of Aeroelasticity and used for the analyses of isolated rotors before test entry. Here, the use of indicial functions allows to separate unsteady aerodynamic effects related to blade airfoil, rotor inflow as well as rotor wake periodicity and to study their influence on flutter onset. So far, the flutter assessment was limited to hover flight and it was found that rotor inflow contributes a major impact for the flutter onset of the rotor blade. The focus of this paper is to investigate how the flutter results change in steady axial flight including climb and descent. | |
| 16:30 | 17:00 | 0129 |
Development of a Mid-Fidelity Aeroelastic Coupling Framework for Analyzing Rotor-Airframe Interactions M. Linder¹, M.K. Yurt¹, J. John¹, I. Yavrucuk¹; ¹Institute for Helicopter Technology and VTOL, TU Munich, DE The aim of the present paper is the implementation of a mid-fidelity aeroelastic coupling framework for the analysis of rotor-airframe interactions. To be able to use this framework in early design phases to minimize the risk of adverse interaction effects, a computationally efficient freewake solver is used for the simulation of aerodynamics and a modal solver for the structural representation. |
| 8.8 Th, 07.9. 16:00 - 17:30 | Unmanned Rotorcraft 3 Chair: S. Topczewski, Warsaw University of Technology, PL | Helicopter Museum | Eventraum |
| 16:00 | 16:30 | 0114 |
Review of Calculation Analyzes and Tests of the SW-4 SOLO Helicopter in various Configurations J. Sokarski¹, R. Raczynski¹, A. Roslowicz¹, W. Kanadys¹; ¹„PZL-Swidnik” S.A. Leonardo Helicopters Company, PL Presented by: R. Radoslaw, „PZL-Swidnik” S.A. Leonardo Helicopters Company The article presents an overview of the SW-4 SOLO helicopter’s ongoing projects: OCEAN2020 - with helicopter modification for the needs of over water operational capabilities. RPAS In Air - with an innovative implementation of the system for satellite communication and a series of tests demonstrating the possibility of controlling an unmanned aerial vehicle with the use of a satellite data link. | |
| 16:30 | 17:00 | 0151 |
HIERARCHICAL DUAL LOOP ATTITUDE CONTROL FOR UNMANNED HELICOPTER G. Bertolani¹, A.D. Ryals, Università di Pisa, IT; E.L. de Angelis¹, F. Giulietti¹; ¹Università di Bologna, IT The present paper proposes a two-timescale controller for attitude control of a small-scale unmanned helicopter based on the combined action of a linear controller (LC) and of an output tracking SMC controller. The controller is applied to a nonlinear dynamic model of a small-scale aerobatic helicopter to achieve attitude tracking in the presence of turbulence. The main contributions of this paper is the implementation of the combined action of a linear controller with the SMC for helicopters. | |
| 17:00 | 17:30 | 0165 |
Helicopter Control with Dynamic Inversion and Inflow Rate Estimation G. Avanzini, University of Lecce, IT; E.L. de Angelis¹, D. Fattizzo¹, F. Giulietti¹; ¹University of Bologna, IT The work is a study of a mean inflow angle estimation algorithm based on a minimum complexity model and its application in the development of a dynamic inversion controller. The developed controller is applied to a higher order model helicopter. Good capability of the control system is obtained and a very good match results from estimated inflow ratio and high order model inflow comparison. |
| 8.9 Th, 07.9. 16:00 - 17:30 | Structures and HUMS 2 Chair: P. Capone, Zurich University of Applied Sciences, CH | Helicopter Museum | Archivraum |
| 16:00 | 16:30 | 0156 |
Hybrid Flax Fiber-Based Helicopter Cabin Door - Static and Dynamic Testing with Digital Image Correlation L. Gaugelhofer¹, J. John¹, M. Hajek¹, I. Yavrucuk¹; ¹Institute for Rotorcraft an Vertical Flight, TU Munich, DE Presented by: L. Gaugelhofer, Institute for Rotorcraft an Vertical Flight, TU Munich The paper describes the development and static/dynamic testing of three flax fiber-based carbon-reinforced helicopter cabin doors compared to a carbon door from the original manufacturer. The optically measured 3D displacements, surface strains and eigenfrequencies show that new flax prepreg materials, design and production quality significantly improve the overall strength, stiffness and damping. | |
| 16:30 | 17:00 | 0079 |
Monitoring of MGB Lubrication and Cooling System based on Big Data Normality Models and Fuzzy Expert Rules A. Mechouche¹, M. Houles¹, J. Belmonte¹, P.-L. Maisonneuve¹; ¹Airbus Helicopters, FR This paper presents a method for the monitoring of the Main GearBox (MGB) lubrication / cooling system. The method combines both MGB oil pressures / temperature normality models (machine learning based) built from big amounts of data collected from customers' helicopters, and fuzzy expert rules which allow a precise troubleshooting of the system' anomalies. | |
| 17:00 | 17:30 | 0027 |
A Time-Frequency Analysis based Filtering Policy for False Alarm Removal in Health-And-Usage Monitoring Systems J. Leoni¹, A. Palman, Electrical and Avionics Systems, Leonardo Helicopters Division, IT; M. Tanelli¹; ¹Politecnico di Milano, IT Helicopter maintenance and inspection are crucial for safety and cost control. Health Usage Monitoring Systems (HUMS) have been designed for diagnostic, monitoring, and predictive maintenance purposes, including transmission vibration monitoring to identify anomalous patterns related to faults. Machine- and deep-learning techniques have been explored to automatically identify faulty conditions, but false alarms still occur. A post-processing filtering policy is proposed to reduce false alarms by inferring concentric confidence boundaries that define the healthy distribution. This policy consists of an additional module that can filter out false alarms in case the vibrations signatures are available. The method was validated on real data collected for two AW169 helicopters over four years, proving to filter out all false alarms. Future developments involve testing the method's performance on other helicopter models and a broader range of faulty conditions. |
| Th, 07.9. 17:30 - 17:31 | End of ERF2023 | 17:30 - 17:31 | ||||||