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Performance of a component-based flight simulator architecture using the HLA paradigm

Performance of a component-based flight simulator architectu...

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aiaa modeling and simulation technologies conference and exhibit 2002

作者： Lemmers, Arjan J. J. Kuiper, Paul J. Verhage, F. René National Aerospace Laboratory NLR Flight Simulation department Anthony Fokkerweg 2 1059 CM Amsterdam Netherlands

ISBN: (纸本)9781624101212

simulation components are the building blocks for simulators and can be used in more than one type of simulator. To enable cost-effective simulator development through reuse and exchange of simulator components, component and distributed simulation technologies can play an important role. Based on the principles of the High Level Architecture, a component-based simulation architecture for a training system has been proposed by Dutch Space, TNO-FEL and the National Aerospace Laboratory NLR. The federate is composed of various simulation components that interact using the same architecture and infrastructure as the overall HLA federation. Verification of the improved architecture performance has been performed by the NLR. The NLR Pilot Station has been restructured in accordance with the component-based concept and an experiment has been set up and carried out to measure the performance with an emphasis on latency issues. Comparison of the componentbased simulation architecture with the performance of the validated NLR flight simulation facilities shows the capabilities. © 2002 by the author(s). Published by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Flight simulators

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A simulation tool for on-line real time parameter identification

A simulation tool for on-line real time parameter identifica...

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aiaa modeling and simulation technologies conference and exhibit 2002

作者： Perhinschi, M.G. Campa, G. Napolitano, M.R. Lando, M. Massotti, L. Fravolini, M.L. Department of Mechanical and Aerospace Engineering West Virginia University Morgantown WV 26506/6106 United States Department of Electrical Systems University of Perugia Perugia Italy

ISBN: (纸本)9781624101212

This paper describes a simulation tool developed at West Virginia University (WVU) for online aircraft parameter identification (PID) within a specific fault tolerant flight control scheme for the NASA IFCS F-15 program. The simulation package developed by WVU researchers is modular and flexible so that different methods and/or approaches can be used for each of the tasks of the general fault tolerant control system, such as aircraft model, controller, parameter identification method, and on-line data storage. Numerous simulation options are directly available to the user through specific graphical user interface. These options allow to select among different control loop configurations, different versions of the parameter identification method, and different failure scenarios. © 2002 by the author(s). Published by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Graphical user interfaces

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modeling and simulation of launch vehicle digital auto pilot

Modeling and simulation of launch vehicle digital auto pilot

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aiaa modeling and simulation technologies conference and exhibit 2002

作者： Joshi, Ashok Pramodh, P.G. Department of Aerospace Engineering IIT Bombay Mumbai India VSSC Thiruvananthapuram India

ISBN: (纸本)9781624101212

This study is concerned with the effect of nonlinearities in the configuration design of Digital Auto Pilot (DAP) in launch vehicles. An electro- hydraulic actuator model of a launch vehicle control system is considered for analysis of nonlinearities. Various non-linear effects like saturation (in current and stroke limit), dead zone and coulomb friction are taken into account. DAP, which is an interface between the guidance system and control system, is designed to cater to the model (linear/ non-linear) adopted for the actuator. In the actuator alone case, without considering the total flight regime and vehicle model, the performance is found to be satisfactory for linear as well as non-linear actuator models. In the actuator- vehicle combination, when the simulation is carried out for the total flight regime considering the vehicle model, the performance of the linear/nonlinear actuator model is dependant on DAP configuration. This study brings out the fact that the DAP configuration is specific to the actuator model, so that satisfactory performance of launch vehicle control system can be ensured only by choosing proper configuration for DAP, based on consideration of non-linearities in actuator model. © 2002 by the author(s). Published by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Launch vehicles

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Transitioning to PC-based simulation - One perspective

Transitioning to PC-based simulation - One perspective

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aiaa modeling and simulation technologies conference and exhibit 2002

作者： Nalepka, Joseph Dube, Thomas Williams, Glenn Snyder, Adam Danube, Thomas Slutz, G. Jeff Air Force Research Laboratory United States L3 Communications Inc United States Protobox LLC United States

ISBN: (纸本)9781624101212

Doing"more for less"is a recurring theme facing researchers in many simulation facilities. In the area of simulation, one way to reduce operational costs is to invest in and operate inexpensive simulation computer systems. Traditionally, this has not been possible because very specialized computer systems were required to build simulation architectures that provided a deterministic timing mechanism and also assured that simulation processes executed in a predetermined order throughout the entire execution period of the simulation. However, with the advent of 2.0 GHz processors, powerful graphics cards and the wide availability of software, the Personal Computer (PC) is now becoming a realistic option for developing real-time simulation architectures. Air Force Research Laboratory (AFRL) researchers at the Aerospace Vehicle Technology Assessment and simulation (AVTAS) Laboratory have integrated and tested a simple, PC-based, real-time simulation framework that executes under the Linux operating system. Using various hardware and software- based timing mechanisms, along with nonspecialized software tools, the AVTAS Laboratory has developed a real-time simulation architecture that will enable the execution of simulation experiments on dual-CPU and quad-CPU PCs. © This material is declared a work of the U.S.

关键词： Personal computers

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ATTAS & ACT/FHS system simulation for pre-flight software and hardware testing

ATTAS & ACT/FHS system simulation for pre-flight software an...

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aiaa modeling and simulation technologies conference and exhibit 2002

ISBN: (纸本)9781624101212

At the German Aerospace Center (DLR) in Braunschweig currently two elaborate ground based system simulators are in operation. These system simulators provide essential support for the two unique in-flight simulation and research aircraft ATTAS (Advanced technologies Testing Aircraft System) and ACT/FHS (Active Control Technology/Flying Helicopter System). As an indispensable part of the in-flight simulation as well as the flight test and research philosophy at DLR they play a vital role during the pre-flight development and testing phase of every experiment. Their sophisticated setup provides an elaborate simulation environment under realtime conditions covering all crucial aspects from the realistic representation of flight performance and dynamics, hardware-in-theloop capabilities and man-machine interaction. This allows a wide variety of utilization ranging from software development over hardware testing to the realization of complete in-flight simulations with pilot-in-the-loop feedback. This paper will give a general overview over the two system simulators and their capabilities, their hardware and software structure and their potential of use for pre-flight test and research. © 2002 by the author(s). Published by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Flight simulators

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Simulating simulations to lower cost of simulation solutions

Simulating simulations to lower cost of simulation solutions

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aiaa modeling and simulation technologies conference and exhibit 2002

作者： Cluff, Cal Strelich, Thomas Illgen Simulation Technologies Inc 130 Robin Hill Road Suite 200 Goleta CA 93117 United States

ISBN: (纸本)9781624101212

Great engineering value is obtained using simulations in place of systems before they are built or when the systems are unavailable. As systems have gotten more complicated, simulations have gotten more complicated. Now, many simulations are as (or more) complicated than the systems which inspired the use of simulation in the first place. Why try to build these complicated systems (simulations) without the benefit of simulation? PCs have entered the realm of high performance computing by combining the low per unit cost of the PC with distributed and/or clustered architectures. While CPU performance scales linearly with CPU speed, processing performance does not scale linearly with the number of computers. Look at the architectural elements of a distributed simulation: User element - provides the interaction protocol whether it is a human or another software application. Analysis element - models of the system being simulated. Control element - Implements distributed component integration and manages interoperation. Data element - provides component persistence and data for"after action"analysis. Infrastructure element - hardware and software of the processing and communications network. While the interesting science and engineering is computed in the analysis element, to the computer this is just"load."A simulation of a distributed simulation is a model of how the other four elements manage the"load"over time. By simulating the simulation you can determine physical infrastructure and runtime architecture suited for your simulation problem early in the development lifecycle and deploy your low cost PC distributed simulation with confidence. © 2002 by the author(s). Published by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Application programs

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Predator weaponization - An application of simulation based acquisition

Predator weaponization - An application of simulation based ...

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aiaa modeling and simulation technologies conference and exhibit 2002

作者： Weyer, Robert M. ASC/EN Wright-Patterson AFB OH 45433-7101 United States

ISBN: (纸本)9781624101212

The Aeronautical Systems Center's Engineering Directorate implemented portions of the construct known as simulation Based Acquisition in the demonstration phase of the Predator Weaponization Program. During Phase I, the Reconnaissance Systems Program Office was challenged with a 90-day effort to execute three, first-ever, live launches of an Army Hellfire missile from an Unmanned Air Vehicle. The effort included the use of many modeling, simulation, and Analysis tools such as Computational Fluid Dynamics;stability and control margin, and response analysis;a highfidelity, six-degree-of-freedom simulation for aircraft response to missile launch;and a Forward Looking Infrared performance model. These simulation Based Acquisition tools provided critical insight into the technical performance issues, increased confidence, reduced flight test launches, and shortened schedule. The flight test program was a complete success, and by implementing simulation Based Acquisition, the Systems Program Office reduced the schedule from nine months to three months, reduced the flight test program from 75 to 50 flight test hours, and reduced the cost from $3.4M to $3.0M. For the Phase II expansion of altitude, launch range, and warhead type, the use of simulation Based Acquisition is expected to reduce the schedule from 90 days to 45 days, reduce the flight test program from 115 to 75 flight test hours, and reduce the cost from $3.5M to $2.5M.

关键词： Computational fluid dynamics

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Control of inflow distortion in a scarf inlet

Control of inflow distortion in a scarf inlet

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8th aiaa/CEAS Aeroacoustics conference and exhibit, 2002

作者： Gerhold, Carl H. Clark, Lorenzo R. Biedron, Robert T. Aeroacoustics Branch Computational Modeling and Simulation Branch NASA Langley Research Center Hampton VA 23681 United States

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Flight test rehearsal using computer connectivity to increase flight test safety

Flight test rehearsal using computer connectivity to increas...

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aiaa modeling and simulation technologies conference and exhibit 2002

作者： Burnett, Edward L. Flight Controls and Simulation Lockheed Martin Aeronautics Company Palmdale CA United States

ISBN: (纸本)9781624101212

As computer computational power has increased, the level of fidelity of flight simulators has increased along with it. This increased fidelity has provided for better flight test rehearsals for the test pilot but has not accounted for the fact that the pilot is not alone in the testing of a new vehicle. The flight test 'team' is just that, a team. The test pilot has been given many chances to rehearse the flights of the aircraft but not often with the entire flight test crew. By using the interconnectivity of modern computers, Flight Test can now rehearse as an entire team. Pilots, test conductors, and control room engineers can practice integrated test maneuvers, control room engineers from different disciplines can train together, flight test data displays can be checked out in an operational and dynamic environment, and emergency procedures can be tested all before the aircraft's first flight. The flight simulator can "telemeter" data packages across a company's intranet into the flight test data processing computers, thus creating a tool which allows the entire flight test team to interact during flight test rehearsals. The end result increases the team's ability to work efficiently and safely. © 2002 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： Flight simulators

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DIMSS - JSHIP's modeling and simulation process for ship/helicopter testing & training

DIMSS - JSHIP's modeling and simulation process for ship/hel...

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aiaa modeling and simulation technologies conference and exhibit 2002

作者： Roscoe, Michael F. Wilkinson, Colin H. Joint Shipboard Helicopter Integration Process - Joint Test and Evaluation Patuxent River MD United States

ISBN: (纸本)9781624101212

The Dynamic Interface modeling and simulation System (DIMSS) was a modeling and simulation project of the Joint Shipboard Helicopter Integration Process (JSHIP), Joint Test and Evaluation Force. JSHIP was chartered and sponsored by the Office of Secretary of Defense to improve the interoperability of joint forces with U.S. Navy air capable ships. The goal of DIMSS was to define a process for expanding wind over the deck (WOD) flight envelopes for any ship/helicopter combination using modeling and simulation. In order to demonstrate that the process was effective, a man in the loop flight simulator, which replicated the dynamic interface environment for the LHA class ship and UH-60A Black Hawk helicopter, was developed and integrated into the NASA Ames Vertical Motion Simulator (VMS). The simulation included several high fidelity models of the ship and ocean environment, aircraft cockpit, flight controls and flight characteristics. The project was supported by an extensive verification, validation and accreditation (VV&A) process, which included an accreditation team of independent subject matter experts and representatives of the Department of Defense user community. Validation data were collected during two at-sea dynamic interface tests with a LHA class ship and UH-60A helicopter. Tests included measurements of the ship's airwake and ship motion characteristics, aircraft flight characteristics, and pilot workload while flying the aircraft in the vicinity of the ship. Methods of quantifying pilot workload from control activity were developed and documented in test reports. simulation evaluations to determine capability to predict WOD flight envelopes were conducted in June 2001. Test results indicated pilot workload in the simulation was quantitatively and qualitatively comparable to workload experienced during at-sea dynamic interface tests under similar conditions. Previous papers on this project have focused on the VV&A process, the fidelity determination proces

关键词： NASA

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