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检索条件"任意字段=AIAA Modeling and Simulation Technologies Conference and Exhibit 2002"

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Fast-time simulation system for analysis of advanced air transportation concepts

Fast-time simulation system for analysis of advanced air tra...

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aiaa modeling and simulation technologies conference and exhibit 2002

作者： Sweet, Douglas N. Manikonda, Vikram Aronson, Jesse S. Roth, Karlin Blake, Matthew Seagull Technology Inc Campbell CA 95008 United States Intelligent Automation Inc Rockville MD 20855 United States Science Applications International Corporation Arlington VA 22201 United States NASA Ames Research Center Moffett Field CA 94035 United States

ISBN: (纸本)9781624101212

This paper describes the approach for creating a prototype modeling and simulation system that captures the interactions between key participants within the National Airspace System. The current operational paradigm for the National Airspace System has nearly reached its limits and cannot accommodate the projected increases in air travel demand. As a result, systems-engineering practices are being used to develop and evaluate candidate operational concepts for air traffic control. As these new concepts are considered, it is imperative that adequate and credible models are available to: 1) perform conceptual trade evaluations covering many issues and metrics;2) provide detailed evaluations from many viewpoints of changes to the system prior to their implementation;and 3) conduct real-time and non-real-time analyses of system-wide performance. It is planned that an effective modeling and simulation capability, known as the Airspace Concept Evaluation System, will be achieved by improvements to existing models, as well as development of extensive new modeling capabilities. The initial effort concentrates on the development and validation of a toolbox of compatible models that can be configured to address many different concepts and evaluation criteria. This modeling strategy is supported by the emergence of distributed simulation capabilities together with the availability of a suite of models that represent key components of the air traffic system that can be integrated into a gate-to-gate modeling tool. In particular, the Airspace Concept Evaluation System prototype utilizes the High-Level Architecture together with agent-based software to create the large-scale, distributed simulation framework necessary to support system-wide evaluations. The complete simulation system will contain the run-time simulation engine together with scenario generation utilities, databases and post-processing tools. The prototype that is presented in this paper focuses on development of t

关键词： Air traffic control

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The aircraft simulation role in improving flight safety through control room training

The aircraft simulation role in improving flight safety thro...

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aiaa modeling and simulation technologies conference and exhibit 2002

作者： Shy, Karla S. Hageman, Jacob J. Le, Jeanette H. NASA Dryden Flight Research Center Edwards CA United States

ISBN: (纸本)9781624101212

NASA Dryden Flight Research Center uses its six-degrees-of-freedom (6-DOF) fixed-base simulations for mission control room training to improve flight safety and operations. This concept is applied to numerous flight projects such as the F-18 High Alpha Research Vehicle (HARV), the F-15 Intelligent Flight Control System (IFCS), the X-38 Actuator Control Test (XACT), and X-43A (Hyper-X). The Dryden 6-DOF simulations are typically used through various stages of a project, from design to ground tests. The roles of these simulations have expanded to support control room training, reinforcing flight safety by building control room staff proficiency. Real-time telemetry, radar, and video data are generated from flight vehicle simulation models. These data are used to drive the control room displays. Nominal static values are used to complete information where appropriate. Audio communication is also an integral part of training sessions. This simulation capability is used to train control room personnel and flight crew for nominal missions and emergency situations. Such training sessions are also opportunities to refine flight cards and control room display pages, exercise emergency procedures, and practice control room setup for the day of flight. This paper describes this technology as it is used in the X-43A and F-15 IFCS and XACT projects.

关键词： NASA

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aiaa modeling and simulation technologies conference and exhibit 2001

AIAA Modeling and Simulation Technologies Conference and Exh...

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aiaa modeling and simulation technologies conference and exhibit 2001

ISBN: (纸本)9781563479458

The proceedings contain 73 papers. The special focus in this conference is on modeling and simulation technologies. The topics include: MASTER- project overview for the development of a modular vehicle simulator;a unique software system for simulation-to-flight research;simulation of an affordable fly-by-wire system for small commercial aircraft;use of flight simulation to complement flight testing of low-cost UAVs;determining fidelity standards for the shipboard launch and recovery task;investigation of effectiveness of the dynamic seat in a black hawk flight simulation;an integrated time-varying airwake in a UH-60 black hawk shipboard landing simulation;system architecture for a multipurpose flight simulator;an integrated modeling and simulation capability for weapon engagement analysis;integration of the CASTLE simulation executive with SIMULINK;a missile system simulation benchmark using the ACSL graphic modeller;an object-oriented sensor and sensor system design;the preparation of target radar signatures for hardware-in-the-loop;a comparative assessment of RF clutter models for use in missile simulation studies;eSim software for web-enabled distributed analysis and simulation;tailored solutions for networking legacy flight simulators - an HLA based approach;from a theater-wide, distributed, high fidelity, virtual simulation exercise;using java applets/servlets for web-based distributed flight simulation;a COTS solution for the distributed flight simulation of an F-14 squadron;GCS/Langley coordinate conversion;a scalable modeling and simulation infrastructure for fast-time airport simulation;PC based configurable aircraft simulation environment for dynamics and control analysis;real-time simulation using Linux;real-time system simulation using COTS for flight control integration;on the dependence of pilot task and pilot workload;the opto-kinetic cervical reflex in flight simulation;human operator issues for uninhabited aerial vehicles;glider aerotow training - f

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Missile operational simulation using commercial-off-the-shelf software

Missile operational simulation using commercial-off-the-shel...

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aiaa modeling and simulation technologies conference and exhibit 2002

作者： Pollini, Lorenzo Baralli, Francesco Innocenti, Mario Giordanello, Carlo Italy

ISBN: (纸本)9781624101212

The present paper shows how COTS (commercial-off-the-shelf) software like Mathworks' Matlab©, Simulink© and Stateflow© can be used to design and realize an operational environment simulator for generic missiles. Every agent in the chosen scenario was modeled with the accuracy needed: enemy vehicles, detection radars, guns, missiles, jammers, chaffs, inter-vehicle communications/coordination. Agents have their own dynamics and logic behavior in response to attacks, i.e. the deploy of countermeasures and counter-attack against the missile. Simulink was used as the simulation platform, while stateflow is responsible for the specification of most of the logic behavior of simulator's agents. The simulator is completely modular: a new agent with its own behavior can be developed and tested separately and then integrated into the environment simulator. The simulator was build from the standpoint of missile design;the missile and its launcher are the primary focus: missile dynamics, seeker's head, land clutter and missile attack logic are modeled accurately. Missile dynamics can be chosen ranging from the simple point-mass model, valid with good accuracy in cruise and final on-target guidance, to the complete 6-dof model used by analysts for the guidance and control laws design. Particular care was posed on seeker head simulation incorporating very complex head-sensor and target models. In particular, the pipeline of target detection, acquisition and selection through sensor fusion was modeled using the same logic schemes, build with stateflow, developed duringthe design, simulation and analysis cycle of missile and seeker head logic. This enlarges dramatically the in-simulation missile logic validation possibilities and permits to highlight possible hidden weaknesses of missile logic behavior longb efore early prototype tests. This simulator allows to run a single simulation or a batch of simulations for Montecarlo analysis. The paper will present the techniques used for s

关键词： MATLAB

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Modelling and simulation of flapping wing control for a micromechanical flying insect (entomopter)

Modelling and simulation of flapping wing control for a micr...

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aiaa modeling and simulation technologies conference and exhibit 2002

作者： Lasek, Maciej Sibilski, Krzysztof Warsaw University of Technology Poland Technological University of Radom Poland

ISBN: (纸本)9781624101212

Very recently, it has been recognized that flapping wing propulsion can be more efficient than conventional propellers if applied to very small-scale vehicles, so-called MAVs (micro air vehicles or microflyer - μAV). These vehicles should be thought of as aerial robots whose mobility can deploy a useful micro payload to a hazardous location where it may perform a variety of missions, including reconnaissance and surveillance, targeting, tagging and biochemical sensing. Flapping flight is more complicated than flight with fixed or rotating wings. The key to understand the mechanisms of flapping flight is the adequate physical and mathematical modeling. The current research on flying insect-like MAV resulted in the new term entomopter, describing similarity of MAV to real insect 13. An insect wing is a multifunctional device providing lift, propulsion and flight control and performing complex motion relative to the aircraft body, which shows the analogy to helicopter rotor. Transferring ideas from the more matured discipline like rotorcraft technology to emerging entomopter technology should be beneficial for the later one (and may be vice-versa). The key problem is to construct the proper computational models for the simulation of controlled entomopter motion. The following assumptions are made: the wings motion may be decomposed into flapping, lagging, and feathering;aerodynamic forces coming from airfoils have periodical character;the wing vortices are generated at the trailing edge only;the shape of the wake is determined from calculations via a time-stepping procedure. The modified strip theory and modified panel method are used for computing the unsteady flows of entomopter flight. In the proposed model the control of the motion is performed by feathering, flapping, and lagging amplitudes. Synthesis of control has been conducted on the basis of inverse simula- tion3, 16 This paper presents the design of software simulation for entomopter flight (SSEF). In partic

关键词： Micro air vehicle (MAV)

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Characterization of a gas/gas, hydrogen/oxygen engine

Characterization of a gas/gas, hydrogen/oxygen engine

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38th aiaa/ASME/SAE/ASEE Joint Propulsion conference and exhibit 2002

作者： Archambault, Mark R. Peroomian, Oshin Air Force Research Laboratory Space and Missile Propulsion Division Edwards AFB CA 93524 United States Metacomp Technologies Inc Westlake Village CA 91361 United States

ISBN: (纸本)9781624101151

As part of an ongoing program to develop a computational methodology to obtain high-fidelity rocket engine flow solutions, computations were performed on a single-element, gadgas, H2/02 combustion engine. The present work examines the influence of modeling experimental features often neglected in a simulation, specifically a nitrogen curtain purge used to cool optical access. It is shown that the influence is significant and better agreement with the data can be obtained by including the nitrogen purge. Additional solutions are presented to investigate the impact of using various turbulence models on this class of problems. A linear, realizable k-epsilon model best represented the experimental data, however, it should be recognized that RANS-type turbulence models are best suited to steady, isotropic flows, which the present flowfield is not.

关键词： Turbulence models

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An application using an open systems architecture for avionics development, testing, and real time manned simulation

An application using an open systems architecture for avioni...

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aiaa modeling and simulation technologies conference and exhibit 2002

作者： Bezdek, William J. Bankhead, Janet E. Kolta, Jessica Trapp, Theresa The Boeing Company St. Louis MO United States Aviant St. Louis MO United States

ISBN: (纸本)9781624101212

The current generation of aircraft has many specialized computer systems for control of the aircraft and the onboard systems to support the mission. Typically, many of these computer systems are very specialized along with the software that operates on them. The trend is to transition to more general-purpose hardware, open system architectures, and higher order computer languages. The objective of this paper is to investigate the ability to use embedded avionics code and displays directly on different types of general-purpose computers and integrate them with traditional real time manned simulators to prototype new concepts. New weapon system concepts are often developed using rapid prototyping techniques and tested by flight crews using real time simulation. The computer code written for those activities is often done in C++, FORTRAN, or other languages and uses OpenGL or other software for the displays. The cockpit used for this research represents many low-cost engineering development simulators and is called the Reconfigurable Manned Interactive Crew Station (RMICS) simulator. The RMICS consists of flight hardware grips, a display surface showing the virtual cockpit layout with embedded avionics displays, and a separate out-thewindow display with an embedded Head-Up Display (HUD). The proposed avionics and weapon system changes are rapidly prototyped and flown by operational pilots in the simulator to help develop, evaluate, and refine the requirements using representative mission scenarios. At the conclusion of the rapid prototyping phase, the requirements are passed along to the embedded avionics software designers, which develop and test the embedded avionics software and displays. Recently, this development has transitioned from a few workstations to smaller systems on the engineer's desk to develop and test the code. In addition, the trend is to develop displays using a high level graphical tool, such as the Virtual Avionics Prototyping System (VAPS). By us

关键词： Codes (symbols)

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The DG/VMS method for unified turbulence simulation

The DG/VMS method for unified turbulence simulation

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32nd aiaa Fluid Dynamics conference and exhibit 2002

作者： Scott Collis, S. Department of Mechanical Engineering and Materials Science Rice University Houston TX 77005-1892 United States

ISBN: (纸本)9781624101137

The high cost of wind tunnel testing and the ongoing reduction in national wind tunnel facilities are forcing the aerospace engineering community to increasingly rely on computational fluid dynamics (CFD) to predict the performance of new aircraft designs. However, most aerospace applications are characterized by flows that exhibit large-scale unsteady turbulence and the accurate prediction of these flows is often critical to predicting overall performance. Unfortunately, the turbulence modeling approaches used in existing industrial CFD simulation tools often do not accurately predict large-scale turbulent flows which limits their utility. This paper introduces a new paradigm, called the DG/VMS method, for CFD that is specifically designed to accurately and efficiently predict complex flows dominated by large-scale turbulence. Here, the DG/VMS formulation is presented along with results for several laminar validation tests. Our future work will apply the DG/VMS to turbulent flows. © 2002 by the author. Published by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Computational fluid dynamics

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Unsteady simulation of a landing-gear flow field

Unsteady simulation of a landing-gear flow field

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8th aiaa/CEAS Aeroacoustics conference and exhibit, 2002

作者： Li, Fei Khorrami, Mehdi R. Malik, Mujeeb R. High Technology Corporation Hampton VA 23666 United States Computational Modeling and Simulation Branch NASA Langley Research Center Hampton VA 23681 United States

ISBN: (纸本)9781624101199

This paper presents results of an unsteady Reynoldsaveraged Navier-Stokes simulation of a landing-gear flow field. The geometry of the four-wheel landinggear assembly consists of several of the fine details including the oleo-strut, two diagonal struts, a door, yokes/pin and a flat-plate simulating the wing surface. The computational results, obtained by using 13.3 million grid points, are presented with an emphasis on the characteristics of the unsteadiness ensuing from different parts of the landing-gear assembly, including vortex shedding patterns and frequencies of dominant oscillations. The results show that the presence of the diagonal struts and the door significantly influence the flow field. Owing to the induced asymmetry, vortices are shed only from one of the rear wheels and not the other. Present computations also capture streamwise vortices originating from the upstream corners of the door. © 2002 by the author(s). Published by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Struts

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Finite-element based large-eddy simulation of the near-nozzle region of a compressible round jet

Finite-element based large-eddy simulation of the near-nozzl...

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8th aiaa/CEAS Aeroacoustics conference and exhibit, 2002

作者： Jansen, K. Maeder, T. Reba, R. Rensselaer Polytechnic Institute Troy NY 12180 United States United Technologies Research Center East Hartford CT 06018 United States

ISBN: (纸本)9781624101199

The near-nozzle region of a compressible high Reynolds number (Re {all equal to} 106) turbulent cold round jet has been numerically simulated. A finiteelement based large-eddy simulation technique has been used on a fully unstructured mesh. The computational domain has been restricted to a 20- degree azimuthal sector that includes the end part of a converging nozzle. Results for the flow in the first diameter downstream of the nozzle lip are in qualitative agreement with experimental data. A frequency-domain formulation of the Lighthill analogy has been used to compute the far-field pressure spectrum. Sources of discrepancy with experimental data have been identified and improvement strategies are addressed. © 2002 by the author(s). Published by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Nozzles

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