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共 1485 条记录，以下是121-130 订阅

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Human-in-the-loop simulation of trajectory based operation concept for remotely piloted aircraft system integration

Human-in-the-loop simulation of trajectory based operation c...

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aiaa modeling and simulation technologies conference, 2017

作者： Kang, Jisoo Kang, Seonyoung Oh, Hyeju Choi, Keeyoung Lee, Hak-Tae Jung, Hyun-Tae Moon, Woo-Choon Department of Aerospace Engineering Inha University Incheon22212 Korea Republic of School of Air Transport Transportation and Logistics Korea Aerospace University Goyang-SiGyeonggi-Do10540 Korea Republic of

ISBN: (数字)9781624104510

ISBN: (纸本)9781624104510

Trajectory Based Operations (TBO) is one of the concepts of the next generation air traffic management (ATM) system to maximize throughput by planning and sharing 4-D trajectories between pilots and controllers. Given the current circumstances where many countries put efforts to establish rules and regulations for Remotely Piloted Aircraft System (RPAS) integration, it is essential to analyze the impact of RPAS on the next generation ATM environment. In this research, a Human-in-The-Loop (HiTL) simulation system capable of TBO is developed. HiTL simulations were performed by a licensed air traffic controller assuming integrated operation with Remotely Piloted Aircraft (RPA) with communication delays. The results were analyzed using three evaluation metrics, which are efficiency, safety, and controller workload. It shows that, compared to the conventional radar vectoring, TBO reduced both the arrival delay and the controller workload. However, in terms of the two safety metrics employed for this research, TBO showed slightly reduced level of safety. © 2017, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Controllers

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aiaa modeling and simulation technologies conference and exhibit

AIAA Modeling and Simulation Technologies Conference and Exh...

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aiaa modeling and simulation technologies conference and exhibit

ISBN: (纸本)9781563479458

The proceedings contain 121 papers. The topics discussed include: performance measurements on the MPI stewart platform;Cal Poly's motion flight simulator and motion algorithms;piloted simulator evaluation of new fault-tolerant flight control algorithms for reconstructed accident scenarios;development of a model-based safety analysis technique from the ETF flight simulator;airframe and trajectory pursuit modeling for simulation assisted air race planning;pilots' use of pitch and heave motion cues in a pitch control task;model verification and validation of a mobile robot system for 6-DOF motion emulation;evaluating an objective method for motion cueing fidelity;nonlinear ground dynamics of aircraft: bifurcation analysis of turning solutions;measuring and modeling neuromuscular system dynamics for haptic interface design;HORIZON 2.1: A space system simulation framework;and mobile robotic system for ground testing of multi-spacecraft proximity operations.

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Development and validation of a flight-identified full-envelope business jet simulation model using a stitching architecture

Development and validation of a flight-identified full-envel...

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aiaa modeling and simulation technologies conference, 2017

作者： Berger, Tom Tischler, Mark B. Hagerott, Steven G. Cotting, M. Christopher Gray, William R. Gresham, James L. George, Justin E. Krogh, Kyle J. D’Argenio, Alessandro Howland, Justin D. U.S. Army Aviation Development Directorate Moffett Field CA United States Textron Aviation WichitaKS United States USAF Test Pilot School Edwards AFB CA United States

ISBN: (数字)9781624104510

ISBN: (纸本)9781624104510

A full flight-envelope simulation model of the Calspan Variable Stability Learjet-25 was developed from flight data. The model is based on a stitched model architecture, which falls into the class of quasi-Linear-Parameter-Varying models, and was developed using a series of discrete linear point models and trim data. Point models were identified from flight data at five different flight and loading conditions. A scaling method was used and validated to convert all identified point models to the same loading configuration. The quasi-linear aerodynamics from the models were then combined with trim data and the full nonlinear equations of motion to develop the stitched model. Through validation with flight data, the model was shown to accurately represent the aircraft dynamics within the normal flight envelope and be able to estimate the effects of weight and center of gravity variations. The paper provides a brief background of model stitching, lists the steps required to develop a stitched model from flight data, and then demonstrates how the steps are applied to the Learjet. © 2017, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Equations of motion

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Interaction of a robotic servicing vehicle with satellite flexible modes during capture

Interaction of a robotic servicing vehicle with satellite fl...

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aiaa modeling and simulation technologies conference, 2017

作者： Brannan, Justin C. Carignany, Craig R. Dynamics and Controls Department Emergent Space Technologies Inc LaurelMD20707 United States Aerospace Engineering Department University of Maryland College ParkMD20740 United States

ISBN: (数字)9781624104510

ISBN: (纸本)9781624104510

On-orbit failures that typically lead to satellite end-of-life may soon be repaired using robotic servicing platforms. Such a design mission would require a robotic servicing spacecraft to rendezvous, grasp, refuel, and release a client satellite in an effort to extend its life. This paper will focus on the interaction dynamics between the robotic servicing spacecraft and client satellite while a grapple maneuver is being performed by the ser-vicer's robotic arm. A robotic testbed platform will be used to perform this investigation, enabling hardware-in-the-loop simulations of the on-orbit rigid and flexible-body dynamics in a 1-g setting. The grapple sequence between servicer and client satellite is one of the most critical maneuvers since any unintentional energy transfer during contact could po-tentially damage the client satellite. If certain flexible modes are excited, it could damage the satellite's appendages and lead to unstable interaction with the servicer spacecraft. Such induced oscillations could make it difficult to maintain stable interaction between the two vehicles, jeopardizing the entire servicing mission. The results of this research include a discussion regarding the impact of flexible-body dynamics on an end-to-end servicing mission including the interaction forces during a grapple maneuver and a time-history of the simulated pose and rates for the client satellite body and attached flexible appendages. © 2017, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Satellites

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Comparison of flamelet and transported species-based modeling of scramjet combustor 53

Comparison of flamelet and transported species-based modelin...

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53rd aiaa/SAE/ASEE Joint Propulsion conference, 2017

作者： Li, Wenhai Lou, Zhipeng Ladeinde, Foluso TTC Technologies Inc. CentereachNY11720 United States Department of Mechanical Engineering Stony Brook University Stony BrookNY11794 United States

ISBN: (数字)9781624105111

ISBN: (纸本)9781624105111

In this study, two classes of turbulence-combustion interaction models - compressible flamelet/progress variable (CFPV) model and various finite-rate transported-species models - are compared for supersonic combustion modeling within the framework of Large-Eddy simulation. The models are tested by simulating combustion in scramjets. The simulations show that CFPV gives results which are closer to those of the finite-rate models when compared with the original flamelet/progress variable model. It has also been found that the CFPV model tends to under-predict the chemical reaction rate compared to the models based on the eddy dissipation concept and the partially-stirred reactor, while the quasilaminar model tends to over-predict the reaction rate for the supersonic combustion investigated in this work.

关键词： Combustion

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The influence of discrimination strategy on the JND in human haptic perception of manipulator stiffness

The influence of discrimination strategy on the JND in human...

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aiaa modeling and simulation technologies conference, 2017

作者： Fu, W. van Paassen, M.M. Mulder, M. Section of Control and Simulation Faculty of Aerospace Engineering Delft University of Technology P.O. Box 5058 Delft2600 GB Netherlands

ISBN: (数字)9781624104916

ISBN: (纸本)9781624104510

To better design and evaluate simulator control loading systems, humans’ JND in the haptic perception of manipulator stiffness was investigated. To assess changes in such a mechanical property, humans must infer the change through changes in perceived contact force and/or manipulator displacement. To study the relative roles of these two perceptions, we measured stiffness JNDs of seven participants through a forced-choice stiffness discrimination procedure, on three conditions which we referred to as the force, displacement and free conditions. In the force condition, the manipulator displacement was fixed and subjects could only base their stiffness discrimination on changes in the contact force, and likewise in the displacement condition, discrimination was on the basis of changes in the manipulator displacement while the contact force was fixed. In the free condition subjects could uses either or both force and displacement cues to discriminate between different stiffness settings. The lowest stiffness JND was observed in the force condition, followed by a similar results from the free condition. The highest JND level and a poor consistency of results among individuals were obtained in the displacement condition. Subjects indicated that their stiffness discrimination in the free condition was based on the force comparison. To validate this finding, we used two models, one assumed force differences as a criterion for detection and the other assumed the displacement, to estimate the experimental results. Model comparisons indicated that subject’s stiffness discrimination is largely based on detection of force differences. © 2017 by Delft University of Technology.

关键词： Stiffness

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Quantifying the effects of added dynamics with human operator control behavior measurements and simulations

Quantifying the effects of added dynamics with human operato...

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aiaa modeling and simulation technologies conference, 2017

作者： Lu, T. Pool, D.M. van Paassen, M.M. Mulder, M. Control and Simulation Section Faculty of Aerospace Engineering Delft University of Technology P.O. Box 5058 DelftHolland2629HS Netherlands

ISBN: (纸本)9781624104510

Maximum Unnoticeable Added Dynamics (MUAD) envelopes define the region where the subjective handling qualities of the modified aircraft dynamics have no degradation compared with the baseline aircraft dynamics. However, it is unknown whether human operator control behavior also remains unchanged within this region. This paper is part of research project that aims to develop a new "objective" MUAD envelope that explicitly quantifies the sensitivity of the human operator control behavior due to changes in the controlled aircraft dynamics from objective control behavior measures. As a preliminary study, this paper describes an compensatory pitch attitude tracking experiment that was performed to study the adaptation of human operator control behavior to different added dipole dynamics on a baseline controlled element. In addition, a computer-based grid search simulation was developed for predicting these control behavior adaptations, thus without having to determine them experimentally. Overall, the experiment results indicate that for all tested added dipole dynamics (both "up" and "down" dipoles, centered on 1, 3, or 7 rad/s frequencies) at least part of the considered dependent variables (e.g., task performance, control activity, crossover frequency, phase margin, and human operator model parameters) reflected changes in human operator behavior. With clear inconsistencies in which metrics were affected by different added dynamics, it is concluded that the development of an "objective" MUAD envelope should not be done based on a single dependent measure. Furthermore, the computer simulation predictions matched very well with the collected experiment data. Thus such simulation data will be relied on to add to collected experimental human control data in the further development of the objective MUAD envelope. © 2017 by Delft University of Technology.

关键词： Dynamics

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SimPADS: A domain specific modeling framework for model-based PADS DT&E 24

SimPADS: A domain specific modeling framework for model-base...

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24th aiaa Aerodynamic Decelerator Systems Technology conference, 2017

作者： Moore, James E. Yakimenko, Oleg A. JM Technologies LLC 1408 W. Giaconda Place TucsonAZ85704 United States Naval Postgraduate School Department of Systems Engineering 777 Dyer Rd MontereyCA93943 United States

ISBN: (数字)9781624105036

ISBN: (纸本)9781624105036

This paper describes SimPADS, an integrated development environment for a PADS (Precision Aerial Delivery System) Flight Management System (FMS) framework providing high-fidelity Guidance, Navigation and Control (GNC) simulation and test support. Specifically, SimPADS is being developed and integrated within the Snowflake PADS. SimPADS is leveraging the extensive capabilities developed by JM technologies under the ORION program (the original GPADS system developed for the U.S. Army in the late 1990’s) and aids at making them more accessible using modern software tools and techniques. SimPADS relies on an end-to-end development tool chain including Rational Rose Unified modeling Language (UML), Visual Studio C/C++, Rowley CrossWorks for ARM(C/C++), and MATLAB/Simulink using a consistent Object-Oriented Design (OOD) strategy. The simulation environment uses MATLAB as an underlying platform and features an open architecture to support a variety of GNC developers. © 2017, American Institute of Aeronautics and Astronautics. All rflights reserved.

关键词： C++ (programming language)

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Large eddy simulation of compressibility effects on supersonic boundary layer transition and turbulence 21

Large eddy simulation of compressibility effects on superson...

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21st aiaa International Space Planes and Hypersonics technologies conference, Hypersonics 2017

作者： Wang, Suozhu Chen, Gang Zhen, Huaping Zhao, Zhenping Li, Xiaoxuan Yang, Yifeng Xue, Pu Beijing Institute of Space Long March Vehicle Beijing100076 China

ISBN: (数字)9781624104633

ISBN: (纸本)9781624104633

The present paper addresses the numerical investigation of supersonic flat-plate boundary layer transition at three different Mach numbers. simulations are performed with a spatial large eddy simulation method. For the Favre-filtered Navier-Stokes equations, the convection terms are discretized with a 5th-order upwind compact scheme, and a 6th-order central compact scheme is applied to the viscous terms. The similarity solutions of the compressible laminar boundary layer are used as the initial mean flow, and unstable perturbations are imposed on the inflow boundary to make the transition occur. The main objectives are to assess the compressibility effects on the spatial transition process and turbulence characteristics. The results show that, the compressibility effects inhibit the spatial transition process. The mean streamwise velocity profiles with van Driest transformation are consistent with the incompressible law of the wall up to Mach number 5. According to the analysis of the turbulent Mach number and rms density fluctuations, the Morkovin’s hypothesis no longer holds for Mach number 4.5 and 6.0. The distributions of the turbulent Mach number, rms fluctuation quantities and Reynolds stresses along the wall-normal direction at different streamwise locations exhibit similarity in fully developed turbulent region for all three Mach numbers. The compressibility effects tend to suppress the mainstream velocity fluctuations and Reynolds normal stress. © 2017, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Mach number

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simulation of kerosene fueled RBCC engine based on skeletal mechanism 21

Simulation of kerosene fueled RBCC engine based on skeletal ...

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21st aiaa International Space Planes and Hypersonics technologies conference, Hypersonics 2017

作者： Liu, Bing He, Guoqiang Qin, Fei Cao, Donggang Shi, Lei Science and Technology on Combustion Internal Flow and Thermal-structure Laboratory Northwestern Polytechnical University Xi’an710072 China

ISBN: (数字)9781624104633

ISBN: (纸本)9781624104633

The detailed kerosene high temperature mechanism of C10H22 consisting of 121 species 866 elemental reactions is reduced by DRG method and CSP importance index. A skeletal chemical mechanism of kerosene containing 41 species and 132 elemental reactions is finally obtained. The comparisons of flame temperature, ignition delay time, ignition process and extinction predicted by the skeletal mechanism show an overall good accordance with the detailed reaction mechanism. Moreover, a three-dimensional RANS modeling based on the skeletal kerosene mechanism and a global reaction with the single compound C11H21 is employed for the numerical analysis of a full-scale RBCC engine, which has been experimentally tested in a direct connect supersonic combustion test platform assembled in Science and Technology on Combustion, Internal Flow and Thermal-structure Laboratory (Northwestern Polytechnical University, Xi’an, China). Both the skeletal mechanism and C11H21 global reaction can demonstrate appropriate accuracy with the experiment result. © 2017, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Ignition

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