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检索条件"任意字段=AIAA Modeling and Simulation Technologies Conference and Exhibit"

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A generic T-tail transport airplane simulation for high-angle-of-attack dynamics modeling investigations

A generic T-tail transport airplane simulation for high-angl...

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aiaa modeling and simulation technologies conference, 2018

作者： Cunningham, Kevin Shah, Gautam H. Hill, Melissa A. Pickering, Brent P. Litt, Jonathan S. Norin, Scott B. NASA Langley Research Center Flight Dynamics Branch Mail Stop 308 HamptonVA23681 United States NASA Langley Research Center Flight Dynamics Branch TASA MS 308 HamptonVA23681 United States Unisys Corporation NASA Langley Research Center Mail Stop 169 HamptonVA23681 United States NASA Glenn Research Center Intelligent Control and Autonomy Branch Mail Stop 77-1 ClevelandOH44135 United States Vantage Partners LLC ClevelandOH44142 United States Intelligent Control and Autonomy Branch 3000 Aerospace Parkway Brook ParkOH United States

ISBN: (数字)9781624105289

ISBN: (纸本)9781624105289

A preliminary simulation of a generic T-tail transport airplane configuration has been developed at the National Aeronautics and Space Administration Langley Research Center. The primary purpose of this piloted simulation is to assess aerodynamic model fidelity requirements for training airline pilots to recognize and recover from full-stall flight conditions in a T-tail airplane. As a result, significant flexibility has been designed into the flight dynamics model. The flight dynamics model is based on newly acquired static and dynamic stability and control data from sources that include: wind tunnel, water tunnel, and computational fluid dynamics. Preliminary results for initial stall show an unstable stall pitch break (if the stick pusher is inhibited), un-commanded motions due to stall asymmetries, significantly reduced dynamic roll stability, and decreased control effectiveness. Preliminary studies indicated an insensitivity to the fidelity of the pitch damping model. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Wind tunnels

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A versatile simulation environment for design verification, system integration testing and pilot training of a diamond-shaped unmanned aerial vehicle

A versatile simulation environment for design verification, ...

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aiaa modeling and simulation technologies conference, 2018

作者： Kuchar, Richard O. Institute of System Dynamics and Control Weßling82234 Germany Germany

ISBN: (数字)9781624105289

ISBN: (纸本)9781624105289

The OpenInnovation/Sagitta project – under the lead management of Airbus Defence and Space and the active participation of numerous academic institutions† – has its focus on the contribution of innovative technologies within the scope of unmanned aviation. As part of the project, the Sagitta Demonstrator UAV has been constructed, tested and finally flight tested at the Overberg flight test range in South Africa. Before the actual flight tests were performed, intensive simulation and integration testing activities as well as operator training sessions in advance of its maiden flight had to be performed along with the general progress of the project. This paper is dedicated to the description of the general setup of the employed simulation and Integration Testing environment (SIT) for this aircraft, continued with a specific focus on the implementation of the flight dynamics model (FDM), landing gear model (LDG) and respective systems models as well as the data flow between these entities. The utilized setup and fault insertion capabilities are presented, that provided a good preparation base for all involved personnel. Finally the respective models embedded within the overall simulation setup are compared with currently available flight test results. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Integration testing

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Monte carlo simulation based design of a robust trajectory guidance for loitering aerial vehicles

Monte carlo simulation based design of a robust trajectory g...

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modeling and simulation technologies conference, 2018

作者： Altıntaş, Oğuz Han Ateşoğlu, Özgür Advanced Technologies and Systems Division Roketsan Missiles Inc Ankara Turkey

ISBN: (纸本)9781624105517

This paper presents a practical and robust implementation of a nonlinear autopilot design with guidance and navigation capabilities in the presence of disturbances and modeling uncertainties. Different from well-known model-based autopilot designs, the proposed method involves a robust sliding mode controller which is tuned by Monte Carlo simulations. The aircraft model used consists a nominal simplified loitering aerial vehicle dynamics plus bounded random parameter variations or uncertainties. The simulations of aircraft trajectory are represented in the presence of parametric perturbations and both disturbance rejection and tracking performance are investigated. In addition to autopilot design, in the paper, the computational costs of the whole process on cross-platforms are presented as well. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Uncertainty analysis

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Agent-based simulation of urban air mobility

Agent-based simulation of urban air mobility

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modeling and simulation technologies conference, 2018

作者： Rothfeld, Raoul L. Balac, Milos Ploetner, Kay O. Antoniou, Constantinos Bauhaus Luftfahrt e. V. TaufkirchenBavaria82024 Germany ETH Zurich Canton of Zurich Zurich8093 Switzerland Technical University of Munich MunichBavaria80333 Germany

ISBN: (数字)9781624105517

ISBN: (纸本)9781624105517

While a new generation of electric Vertical Take-off and Landing (eVTOL) or Personal Air Vehicles (PAV) projects receive much attention, little research is available on modeling their integration into urban transport systems. An early methodology of the Urban Air Mobility (UAM) extension for the multi-agent transport simulation, MATSim, is being presented, which enables first analyses of system-wide urban transport performance considering the effects of variations in VTOL vehicle properties and dedicated VTOL infrastructure placement. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Air mobility

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A cybernetic analysis of biodynamic effects in touchscreen operation in turbulence

A cybernetic analysis of biodynamic effects in touchscreen o...

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aiaa modeling and simulation technologies conference, 2018

作者： Mobertz, X.R.I. Pool, D.M. Van Paassen, M.M. Mulder, M. Delft University of Technology Control and Simulation Section Faculty of Aerospace Engineering P.O. Box 5058 Delft2600GB Netherlands

ISBN: (数字)9781624105289

ISBN: (纸本)9781624105289

This paper describes a human-in-the-loop experiment performed in TU Delft’s SIMONA Research Simulator to explicitly investigate the effects of biodynamic feedthrough (BDFT) on the execution of a two-dimensional touchscreen waypoint dragging task in turbulence. In the experiment, 16 participants performed the same task in a stationary simulator and whilst being perturbed in either surge, sway, or heave directions by the same motion disturbance signal. In addition, the effect of screen location on biodynamic effects was tested by considering two touchscreen display positions, i.e., representative for the Primary Flight Display (PFD) and the Control Display Unit (CDU), respectively. The collected results show significantly more issues with loss of screen contact for the PFD display, due to the extended arm position when operating this display. Despite the fact that small biodynamic effects are also found for off-axis disturbances, the results clearly show that issues with BDFT predominantly occur when motion disturbances are aligned with the touchscreen control input direction. Due to the use of a multisine motion disturbance signal in the experiment, explicit BDFT detection and identification was possible with spectral methods. For the conditions where sufficient BDFT was detected to allow for modeling the BDFT dynamics, a second-order BDFT model was proposed and found to explain at least 70% of the BDFT input components. With consistent BDFT model parameter estimates between conditions, this approach shows clear merit for quantitative analysis of biodynamic effects on touchscreen operation and potentially even for BDFT mitigation through model-based input cancellation. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Turbulence

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Design of a haptic feedback system for flight envelope protection

Design of a haptic feedback system for flight envelope prote...

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aiaa modeling and simulation technologies conference, 2018

作者： Van Baelen, Dirk Ellerbroek, Joost René Van Paassen, M.M. Mulder, Max Division of Control & Simulation Delft University of Technology Kluyverweg 1 Delft2629 HS Netherlands

ISBN: (数字)9781624105289

ISBN: (纸本)9781624105289

Current Airbus aircraft use a fly-by-wire control device: a passive spring-damper system which generates, without any force feedback, an electrical signal to the flight control computer. Additionally, a hard flight envelope protection system is used which can limit the inputs of the pilot when approaching the edges of the flight envelope. To increase the situation awareness of the pilot, this research aims to provide intuitive information on the flight envelope through haptics, force feedback trough the control device, integrated in the existing Airbus control laws. The goal of this paper is to describe when and how haptics is used in this design. The pilot can get five cues of the flight envelope: when approaching the flight envelope a discrete force cue is given. Next, control inputs which move the aircraft closer to the flight envelope are indicated with an increased spring coefficient. Moving too close to the lower velocity limit activates a stick shaker: a vibration force on the stick. If a stick neutral position is not sufficient to return to the safe flight envelope, the stick is moved forward to the desired control input. Finally, following the automatic Airbus pitch up command during an overspeed condition, the stick is moved back to follow this command. This new system is expected to help identifying the situation and choosing a possible mitigation technique which is evaluated for two scenarios: when the aircraft is moving to the flight envelope, i.e. a windshear, or when the flight envelope moves towards the aircraft. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Flight envelopes

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A novel framework approach enabling model-based requirements validation and verification

A novel framework approach enabling model-based requirements...

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modeling and simulation technologies conference, 2018

作者： Binder, Bastian Gottschall, Marcel Blochwitz, Torsten Center of Excellence System Simulation ESI ITI GmbH Dresden01067 Germany

ISBN: (数字)9781624105517

ISBN: (纸本)9781624105517

Scope of a project called MISSION, funded within the European CleanSky2 initiative, is to develop a software toolchain that supports seamless integrated workflows within aerospace design processes along the different levels of system decomposition (aircraft, system, component) and integration from requirements to certification. The aim of this paper is the demonstration of a multitool integration framework implementation using model-based techniques to achieve fully traceable (early stage) requirements verification by virtual testing. The paper will outline the motivation, describe the technical background briefly and introduce the proof of concept used within the project. It will focus on the demonstration and the value for common multipartner, multitool collaborative workflows in aerospace design. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Integration testing

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Identification of time-varying manual-control adaptations with recursive ARX models

Identification of time-varying manual-control adaptations wi...

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aiaa modeling and simulation technologies conference, 2018

作者： Van Grootheest, H.A. Pool, D.M. Van Paassen, M.M. Mulder, M. Delft University of Technology Control and Simulation Section Faculty of Aerospace Engineering P.O. Box 5058 Delft2600 GB Netherlands

ISBN: (数字)9781624105289

ISBN: (纸本)9781624105289

Time-varying human-operator (HO) adaptation in basic manual-control tasks is barely understood, as most HO identification methods do not explicitly take into account time variations. An identification procedure based on both batch and recursive autoregressive exogenous (ARX) models is used in this paper for capturing HO adaptation to time-varying changes in controlled-element dynamics in compensatory tracking tasks. Conditions with constant controlled-element dynamics, matching recent experimental work, and gradual and sudden transitions in the controlled-element dynamics were compared by means of Monte Carlo simulations with different remnant noise intensities. Overall, with batch ARX model identification results for conditions with constant dynamics, it is shown that differences between remnant noise and HO dynamics, both of which are directly coupled in the ARX model structure, will bias the identified ARX model parameters. Nevertheless, recursive ARX model identification results were still found to provide a reasonably estimate of time-varying HO model parameters for the tested time-varying scenarios. A direct comparison of using a constant scalar forgetting factor λ and a constant forgetting matrix Λ, containing separate forgetting factors for each ARX model parameter, showed that a forgetting matrix did not result in a significant improvement for the considered HO identification problem. A forgetting factor of λ = 0.99609, corresponding to a memory horizon of 256 samples at 100 Hz, is found to be optimal for all tested conditions. An evaluation of real experimental manual-control data shows that, with straightforward online implementation, the method has potential as a tool for investigating, modeling, and measuring operators’ adaptive control characteristics. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Dynamics

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Aerodynamic stall and buffet modeling for the cessna citation II based on flight test data

Aerodynamic stall and buffet modeling for the cessna citatio...

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aiaa modeling and simulation technologies conference, 2018

作者： van Horssen, L.J. de Visser, C.C. Pool, D.M. Delft University of Technology DelftZuid-Holland2629 HS Netherlands Control and Simulation Section Faculty of Aerospace Engineering P.O. Box 5058 Delft2600GB Netherlands

ISBN: (数字)9781624105289

ISBN: (纸本)9781624105289

To meet the required flight simulator-based stall recovery training that will become mandatory for all air-carrier pilots in 2019, many flight simulators will need to be updated with accurate flight models at high angles-of-attack. Using a database of 69 symmetrical and quasi-steady recorded stalls performed with TU Delft’s Cessna Citation II laboratory aircraft, this paper aims to show to what extent relevant stall characteristics can still be modeled using flight test data from such "natural" stall flight test data (i.e., without additional flight test inputs). For modeling the (low-frequency) changes to the aerodynamic characteristics, the well-known stall model structure based on Kirchoff’s flow separation theory is used. This aerodynamic stall model is augmented with a high-frequency stall buffet model identified based on power spectral density analysis of the flight test linear acceleration data. The stall model identification results obtained from a proposed methodology in which the aerodynamic and buffet model parameters were deliberately jointly estimated shows that the dynamic parameters capturing the stall hysteresis effect can indeed be estimated using quasi-steady stall maneuvers. Aerodynamic terms related to the pitch rate, however, are difficult to estimate for such quasi-steady maneuvers, given the correlation between pitch rate and angle-of-attack. It was found that estimating stall transient effects (i.e., hysteresis time constants), which normally require highly dynamic flight test maneuvers, was found to be improved with with explicit use of the measured accelerations caused by the stall buffet in the identification methodology. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Angle of attack

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Verification of HTV-X resilient design by simulation environment with model-based technology

Verification of HTV-X resilient design by simulation environ...

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aiaa modeling and simulation technologies conference, 2018

作者： Noumi, Ai Ujiie, Ryo Ueda, Satoshi Someya, Kazunori Ishihama, Naoki Kondoh, Yoshinori Japan Aerospace Exploration Agency 2-1-1 Sengen TsukubaIbaraki305-8505 Japan Japan Aerospace Exploration Agency 3-1-1 Yoshinodai Chuo-ku SagamiharaKanagawa252-5210 Japan Japan Aerospace Exploration Agency Sengen TsukubaIbaraki305-8505 Japan

ISBN: (数字)9781624105289

ISBN: (纸本)9781624105289

Japan Aerospace Exploration Agency (JAXA) has successfully launched and operated an unmanned supply cargo vehicle called the H-II Transfer Vehicle (HTV) six times as of 2017. Currently, a new-generation cargo vehicle called HTV-X is being developed. The first HTV-X flight is planned in JFY 2021. A new redundant design based on resilience engineering of HTV-X is being proposed. The new design policy, which stipulates that all redundant strings operate to manage degraded performance instead of switching one string due to failure, increases the complexity compared to conventional design. Therefore, various system behaviors, including such undesirable events as failure, must be evaluated and reflected in the system design. Generally, the control logic is validated using Simulink, but such issues as calculation time and event injection must still be overcome using Simulink. A system simulation environment that incorporates a native C code library generated by Matlab’s auto-coding function has been developed to overcome these issues. This paper describes the validation results of the GNC algorithm design of HTV-X using a simulation environment with model-based technology for this conceptual study. It also presents the results of Monte Carlo simulation and cases of simulated failure. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Simulink

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