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Time domain pilot model identification using maximum likelihood estimation

Time domain pilot model identification using maximum likelih...

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作者： Berger, T. Zaal, P.M.T. Mulder, M. Van Paassen, M.M. Delft University of Technology P.O. Box 5058 2600 GB Delft Netherlands Stanford University Department of Aeronautics and Astronautics United States University Affiliated Research Center United States Control and Simulation Division Faculty of Aerospace Engineering United States

ISBN: (纸本)9781563479458

Currently, multi-channel pilot models parameter estimation is done using a two-step frequency domain technique - identifying a non-parametric frequency response and fitting a parametric model to it. A time domain identification method would only require one step-directly fitting a parametric pilot model to the time domain data. Time domain identification has additional advantages in that the forcing functions used do not have specific limitations and multi-channel identification can be accomplished with only one forcing function. This paper displays the results of single- and multi-channel pilot model identifications done using the MATLAB MMLE3 toolbox. Identification was performed first on Simulink simulations and then on actual data collected using the SIMONA Research Simulator at the Delft University of Technology. © 2008 by Delft University of Technology. Published by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Maximum likelihood estimation

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Optimal reconstruction of flight simulator motion cues using extended Kalman filtering

Optimal reconstruction of flight simulator motion cues using...

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作者： Pool, D.M. Chu, Q.P. Van Paassen, M.M. Mulder, M. Delft University of Technology Delft Netherlands Control and Simulation Division Faculty of Aerospace Engineering P.O. Box 5058 2600 GB Delft Netherlands

ISBN: (纸本)9781563479458

For evaluation of simulator motion and motion platform dynamics, the motion cues generated in flight simulators need to be measured. For the SIMONA Research Simulator at Delft University of Technology, the availability of redundant kinematic motion sensors - i.e. an Inertial Measurement Unit and sensors that measure the lengths of the motion system actuators - was expected to allow for optimal estimation of the flight simulator motion state using an Extended Kalman Filter. As a starting point, this sensor fusion problem was evaluated for only symmetrical simulator motion, omitting the additional asymmetrical motion states. The highly nonlinear relation between the extension of the motion base actuators and simulator position and orientation was found to require the application of an Iterative Extended Kalman Filter to ensure adequate filter convergence. Using this iterative filter, optimal estimates of the symmetrical simulator state and the IMU biases could be obtained from the two sets of redundant kinematic observations. © 2008 by Delft University of Technology. Published by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Flight simulators

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An investigation into crossover regression and pilot parameter adjustment

An investigation into crossover regression and pilot paramet...

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作者： Beerens, G.C. Damveld, H.J. Mulder, M. Van Paassen, M.M. Delft University of Technology Delft Netherlands Control and Simulation Division Faculty of Aerospace Engineering P.O. Box 5058 2600 GB Delft Netherlands

ISBN: (纸本)9781563479458

This paper provides an investigation into crossover regression in manual control tracking tasks. In addition, the adjustment, between-subject variation and accuracy of linear human operator model parameters are analyzed. A theoretical investigation into closed-loop error minimization led to the formulation of a set of hypotheses. The most important hypothesis was that the generalized cause of crossover regression originates from the inability to sufficiently decrease the time-delays to allow limited forcing function resonance. To test the hypotheses and explore linear human operator model parameters, an experiment similar to McRuer's landmark 1965 experiment was performed. Comparison of the regressive and non-regressive conditions revealed that crossover regression is indeed adopted to decrease forcing function resonance. The crossover-regression frequency was found to be person-specific. Additionally, increased between-subject variability in crossover frequencies and model parameters were found with crossover regression, as well as decreased pilot control behavior linearity. © 2008 by Delft University of Technology. Published by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Regression analysis

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Scene generation and target detection development for HWIL simulation

Scene generation and target detection development for HWIL s...

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作者： Sherrill, Ryan E. Sinclair, Andrew J. Cochran Jr., John E. Auburn University Auburn AL 36849 United States Department of Aerospace Engineering 316 Davis Hall United States Department of Aerospace Engineering 310 Davis Hall United States Department of Aerospace Engineering 211 Davis Hall United States

ISBN: (纸本)9781563479458

Hardware-in-the-Loop simulations are useful in developing and testing missile systems at lower cost than experimental tests. Accurate results require the missile's optical sensor be stimulated by an artificial environment that represents the physical world. As part of Auburn University's ongoing development of a Hardware-in-the-Loop lab, several software modules have been created that generate a simulated infrared engagement scene, and emulate the target detection and tracking which occurs onboard a missile. These scene generation and target detection tools allow for pure-digital and static-HWIL simulations to be performed. © 2008 by Ryan E Sherrill, Andrew J Sinclair, and John E Cochran Jr.

关键词： Hardware-in-the-loop simulation

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Improving system models using Monte Carlo techniques on plant Models

Improving system models using Monte Carlo techniques on plan...

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作者： Wakefield, Amory Miller, Steve MathWorks Inc. United States Simulation and Test Applications 3 Apple Hill Drive Natick MA United States Physical Modeling Adalperostr. 45 Ismaning Germany

ISBN: (纸本)9781563479458

Model-Based Design has become a standard in the aerospace industry. A system model is at the center of the development process, supporting the design of complex algorithms combined with physical hardware. In addition to the advantages that come from modeling control algorithms, modeling plants can lead to more robust designs. Using commercial-off-the-shelf (COTS) software allows both the controller and hardware to be modeled and simulated in a single environment. modeling plants in the same simulation environment as an embedded controller enables engineers to test a controller with multiple plant parameters, as well as simulating with nominal or ideal values. modeling variable physical parameters provides a better representation of what will happen in real hardware. Monte Carlo analysis is a standard method of simulating variability that occurs in real physical parameters. In aerospace applications, Monte Carlo techniques can be used to ensure high-quality, robust designs. Even using a shared COTS environment, fully testing or optimizing a design can take thousands of simulation iterations and days to complete. Depending upon the complexity of the system and fidelity of the model, each iteration could take hours to run. simulation time can become a critical bottleneck in the development process. Being able to run multiple, independent scenarios in parallel can lessen this time significantly. In this paper, we will discuss techniques for modeling, optimizing, and testing plant models to build better system models in MATLAB® and Simulink® from The MathWorks. We will also present new techniques for speeding up Monte Carlo techniques by using high-performance computing clusters. © 2008 by The MathWorks, Inc.

关键词： Aerospace applications

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F-18 hornet landing simulations using adams and simulink co-simulation

F-18 hornet landing simulations using adams and simulink co-...

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作者： Öström, John Lähteenmäki, Juha Viitanen, Tomi VTT Technical Research Centre of Finland Espoo Finland Patria Aviation / Aircraft Naulakatu 3 FI-33100 Tampere Finland VTT Technical Research Centre of Finland P.O. Box 1000 FI-02044 VTT Finland Patria Aviation / Aircraft Finland

ISBN: (纸本)9781563479458

The Finnish Air Force (FiAF) has been funding the development of several different F-18 Hornet simulations for research purposes. One of these simulations is a fully functional model of F-18 Hornet Landing Gear by Patria Aviation. The landing gear model is used in studying the landing gear function during different landing conditions. The FiAF has also been funding the development of a low-cost flight simulation software. The combination of these two simulation models provides a very accurate and realistic landing simulation of the F-18 Hornet aircraft. This paper discusses the co-simulation of these two models using commercial-off-the-shelf software and how the low-cost flight simulation is used to provide a realistic approach flight for the landing gear model. The co-simulation has been validated and was found to perform realistically. © 2008 by the authors.

关键词： Landing gear (aircraft)

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A preliminary investigation of achievable motion cueing in ground-based flight simulators for upset recovery maneuvers

A preliminary investigation of achievable motion cueing in g...

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作者： Chung, William W. SAIC Lexington Park MD 20653 United States Simulation and Research Services United States

ISBN: (纸本)9781563479458

Using ground-based flight simulators for upset recovery training is appealing due to significant cost saving and safety enhancement. However, difficulty in obtaining acceptable simulation cueing, i.e., motion cues due to large amplitude of airplane's response, or lack of them, i.e., using fixed-base simulator, poses a question if positive transfer-of-training can be achieved on the ground providing aerodynamics database is improved to correctly address simulated airplane's response in abnormal flight conditions. This is a preliminary analysis to see if any motion related issues can be identified based on existing experience and known system constraints. Two mild upset and recovery maneuvers were analyzed based on different motion parameters to examine typical motion cueing fidelity issues in ground-based flight simulators. © 2008 by Science Applications International Corporation. Published by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Flight simulators

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Airframe and trajectory pursuit modeling for simulation assisted air race planning

Airframe and trajectory pursuit modeling for simulation assi...

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作者： Fisch, F. Weingartner, M. Pfifer, H. Holzapfel, F. Sachs, G. Myschik, S. Institute of Flight System Dynamics Technische Universität München Boltzmannstrasse 15 D-85748 Garching Germany IABG mbH Einsteinstraße 20 D-85521 Ottobrunn Germany

ISBN: (纸本)9781563479458

Aviation displays like air shows or air races are attracting a large audience, increasing the popularity and fascination of aerospace in the public beyond mere air travel. Whereas in the past, such events have taken place separately, attempts are made to establish a worldwide series of air races, as an aerospace pendant to the Formula One car race series. With the events taking place in many different countries on all continents, different regulations apply for certifying the events. Furthermore, the tracks need to be comparable, attractive to the public, challenging for the pilots and more than everything else provide a high level of safety. To make the planning and assessment process for the different races more objective and to put it on a scientific basis, a track planning and analysis tool has been developed. This publication presents the kinematic and dynamic aircraft simulation used for initial track generation and assessment together with the control algorithms required to follow the highly curved trajectories utilizing the full envelope of the aircraft at maximum bandwidth. A nonlinear point-mass model is used and a new approach is developed where the attitude and rotational dynamics of the full 6-DoF model are given with respect to the Kinematic Flight-Path Frame, thus allowing to switch between different depths of modeling for the rotational dynamics without the need to modify the nonlinear point-mass model. Three alternatives for modeling the attitude and rotational dynamics are presented, namely a full, non-linear 6-DoF model, a simplified, hybrid 6-DoF model and a simulation model with linear transfer functions for the commanded load factors. In order to guarantee perfect trajectory following of the simulation model, a control system is implemented based on the principle of dynamic inversion. Therefore, the given reference trajectory has to be at least four times differentiable. Reference values for the aircraft inputs are computed from derivatives of

关键词： Trajectories

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Multi-disciplinary approach for the integration and testing phase of simulation development

Multi-disciplinary approach for the integration and testing ...

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作者： Wagner, David A. Hurst, Terril N. Raytheon Missile Systems Tucson AZ 85756 United States Performance Simulations Department Bldg 805 M/S L5. United States

ISBN: (纸本)9781563479458

This paper describes a process implemented to enable effective collaboration of dozens of people across multiple disciplines and organizations during the integration and testing phase of simulation development. Integration and testing is a particularly complicated phase due to the interactions of many engineered elements. Prior to the new process, work was mostly sequential: Documents describing models or algorithms were developed and handed to the simulation and flight software teams to drive their respective development efforts. Intrinsic to this sequential process were significant lag times between the discovery and resolution of design or implementation issues, which induced error-prone re-work and inefficient communication overhead. At the core of the new process is a Software in simulation (SIS) methodology and an open data collection procedure for timely capture of status and open issues. Once identified, these issues are rapidly addressed to assure that proper attention and resources are focused on their resolution. The enabling technologies for open, responsive are simple but effective: Flipcharts are used for any team member to enter an issue, and the information is periodically transcribed into simple spreadsheets for reporting and tracking. For each algorithm, an Integration Test Plan is created initially and periodically updated by developers of the simulation, software, or algorithms. The key is an open environment where any developer feels free to communicate concerns and to resolve issues quickly before they propagate within others' work products. © 2008 by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Integration

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Validation of yaw damper controller via hardware in the loop simulation

Validation of yaw damper controller via hardware in the loop...

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作者： Waszniowski, Libor Hanzálek, Zdeněk Doubrava, Jiří Department of Control Engineering Czech Technical University Faculty of Electrical Engineering Karlovo nám. 13 121 35 Prague 2 Czech Republic AERO Vodochody a.s. U Letiště 374 250 70 Odolena Voda Czech Republic Department of Control Engineering Czech Technical University Czech Republic Department of Aircraft System Development AERO Vodochody a.s. Czech Republic

ISBN: (纸本)9781563479458

The paper presents a validation of the Yaw Damper Controller with hydraulic actuators via hardware in the loop simulation on a stand with a revolving platform and a loading force actuator. The Yaw Damper Controller is briefly described and requirements on validation tests are mentioned. An architecture and software and hardware components of the developed simulator and the stand are described. The simulator instrumentation is based on distributed peripherals communicating via CANopen industrial field bus. The real time simulation of the plane model is performed via an embedded computer with Power PC processor and Linux operating system. Visualization and a data evaluation are provided via a graphical user interface in the Matlab environment. Validation test proving the Yaw Damper Controller software error is presented. © 2008 by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Hardware-in-the-loop simulation

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