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Effects of peripheral visual cues in simulator-based training of multimodal control skills

Effects of peripheral visual cues in simulator-based trainin...

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aiaa modeling and simulation technologies conference, 2017

作者： Mendes, M.F.S. Pool, D.M. van Paassen, M.M. Control and Simulation Section Faculty of Aerospace Engineering P.O. Box 5058 Delft2600 GB Netherlands

ISBN: (纸本)9781624104510

This paper describes a training experiment performed in the SIMONA Research Simulator at Delft University of Technology to evaluate the effectiveness of peripheral visual cues as a substitute for physical motion feedback during the development of multimodal control skills. Twenty task-naive participants were divided in two experimental groups and performed a skill-based compensatory roll tracking task. Both groups were trained in a fixed-base setting, but one group was provided with additional out-of-the-window peripheral visual (roll rate) cues. After training, participants were transferred to a moving-base condition where pure roll motion cues were provided. The development of skills in both groups throughout the experiment was studied and compared using fits of a multimodal human operator model with an error and a roll feedback response, to explicitly quantify operators’ use of all supplied feedbacks. As expected, the group that had access to peripheral visual cues attained better tracking performance during training and showed the development of multimodal control behavior. However, no evident transfer of this developed multimodal control strategy to a motion setting was observed. This suggests that training with peripheral visual cues is not an effective substitute for training the multimodal skills human operators use when motion feedback is available. © 2017 by Delft University of Technology.

关键词： Personnel training

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Refinement of objectivemotion cueing criteria based on three flight tasks

Refinement of objectivemotion cueing criteria based on three...

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aiaa modeling and simulation technologies conference, 2017

作者： Zaal, Peter M. T. Schroeder, Jeffery A. Chung, William W. Human Systems Integration Division San Jose State University NASA Ames Research Center Moffett Field CA94035 United States Federal Aviation Administration Moffett Field CA94035 United States Simulation Laboratories Science Applications International Corporation NASA Ames Research Center Moffett Field CA94035 United States

ISBN: (数字)9781624104510

ISBN: (纸本)9781624104510

This paper aims to refine objective motion cueing criteria developed in a previous experiment for the simulator motion system diagnostic test specified by the International Civil Aviation Organization. Fifteen airline transport pilots flew the same three tasks as in the previous experiment in the NASA Vertical Motion Simulator under six different motion configurations. The six different motion configurations covered the motion region between the motion fidelity uncertainty boundary found in the previous experiment and the mean motion response of a statistical sample of eight representative hexapod motion simulators. The motion condition significantly affected 1) roll deviations in the approach to a stall and maximum pitch rate in a stall recovery, and 2) heading deviation and pedal reaction time after an engine failure in the takeoff task. Significant differences in pilot-vehicle performance were used to develop new objective motion cueing criteria boundaries for the main motion responses. In addition, perception thresholds of false motion cues were used to develop motion cueing criteria for the cross-coupling motion responses. The fidelity boundaries of the current experiment should be used with caution when reducing the uncertainty of the initial fidelity boundaries developed in the previous experiment, as they do not fully overlap. Data collected in the current study will add to data from the next experiment, which aims to further refine and optimize the objective motion criteria found to date. © 2017, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： NASA

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One-way Navier-stokes and resolvent analysis for modeling coherent structures in a supersonic turbulent jet 23

One-way Navier-stokes and resolvent analysis for modeling co...

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23rd aiaa/CEAS Aeroacoustics conference, 2017

作者： Rigas, Georgios Schmidt, Oliver T. Colonius, Tim Brès, Guillaume A. California Institute of Technology PasadenaCA United States CASCADE Technologies Palo AltoCA United States

ISBN: (数字)9781624105043

ISBN: (纸本)9781624105043

A linear analysis of the mean flow of a turbulent Mach 1.5 high Reynolds number jet is conducted. Optimal response modes describing the fluctuating hydrodynamic and acoustic fields are obtained in a computationally efficient way by spatially marching the linearized One-Way Navier-Stokes equations. For this purpose, an adjoint-based optimization framework is proposed and demonstrated for calculating optimal boundary conditions and optimal volumetric forcing. These optimal modes are validated against modes obtained in terms of global resolvent analysis. Two scenarios are considered in the present analysis. In the first case, no restrictions are applied to the spatial forcing distribution. In the second scenario, the forcing is restricted to the nozzle plane. The resulting optimal and suboptimal modes are compared to spectral proper orthogonal modes obtained from a high-fidelity large eddy simulation. 1 The implications of these observations are discussed in detail. © 2017, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Large eddy simulation

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Mass-driver-and scramjet-assisted surface-to-orbit modeling and simulation 21st

Mass-driver-and scramjet-assisted surface-to-orbit modeling ...

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

作者： Wittal, M.M. Benavides, J.C. Clithero, A.O. Reksoatmodjo, R. Schmidt, E. Aerospace Engineering Department College of Engineering & Physics Department College of Arts and Sciences Embry-Riddle Aeronautical University 3700 Willow Creek Rd PrescottAZ86301 United States Aerospace Engineering Department College of Engineering Embry-Riddle Aronautical University 3700 Willow Creek Rd PrescottAZ86301 United States Physics Department College of Arts and Sciences Embry-Riddle Aeronautical University 3700 Willow Creek Rd PrescottAZ86301 United States

ISBN: (纸本)9781624104633

In an effort to explore the potential benefits of alternate surface-to-orbit propulsion techniques, model-based and measured values were used to create a simulation of a mass-driver-and SCRamjetassisted surface-to-orbit system. This simulated pseudo-single-stage-to-orbit vehicle is launched from a mass driver at the threshold of supersonic flight at which point the SCRamjet is activated and rapidly ascends. Heating and performance limitations are assessed using models on SCRamjet behavior as a function of altitude and speed, and is compared with real behavior of the X-43 and X-51 SCRamjet vehicles. Additionally, speed limitations at higher altitudes are examined in order to minimize the use of liquid boosters needed to circularize at Low Earth Orbit (LEO) altitudes. © 2017, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Orbits

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Spread of Chaotic Behavior in Scale-free and Random Networks

Spread of Chaotic Behavior in Scale-free and Random Networks

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IEEE Asia Pacific conference on Postgraduate Research in Microelectronics and Electronics (PrimeAsia)

作者： Chikazawa, Takahiro Uwate, Yoko Nishio, Yoshifumi Tokushima Univ Dept Elect & Elect Engn 2-1 Minami Josanjima Tokushima 7708506 Japan

ISBN: (纸本)9781538605240

In this study, we investigate the spread of chaotic behavior to complex network. We propose three types random network models with different network topology. In each network model, the proposed network is composed of coupled chaotic circuits when one circuit is set to generate chaotic attractor and the other circuits are set to generate three-periodic attractors. By using computer simulations, we investigate ratio of propagation and spread of chaotic behavior by changing the initial chaos position. We compare their differences of simulation results in scale-free and random networks. From the simulation result, in scale-free network, the ratio of propagation is effected by clustering coefficient and path length.

关键词： Integrated circuit modeling Chaotic communication Couplings simulation Asia conferences

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Grid convergence in LES of bluff body stabilized flames 55

Grid convergence in LES of bluff body stabilized flames

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55th aiaa Aerospace Sciences Meeting

作者： Sankaran, Vaidyanathan Gallagher, Timothy P. United Technologies Research Center East HartfordCT06108 United States Georgia Institute of Technology AtlantaGA30332 United States

ISBN: (数字)9781624104473

ISBN: (纸本)9781624104473

This paper investigates the influence of mesh resolution on the solution obtained from large eddy simulations of a bluff body stabilized flame. A sequence of coarse, medium, and fine meshes are used to simulate stable combustion conditions observed in the Volvo experimental rig. Two different combustion models using finite-rate kinetics are employed to understand the nature of convergence between different models and these are the dynamically thickened flame (DTF) model and a Turbulent Batch Reactor (TBR) model. Solutions from both models are qualitatively and quantitatively in reasonable agreement with experimental data. Mean velocities and temperature exhibit very good grid convergence everywhere in the flow-field. The RMS statistics indicate some mesh dependency. The dependency is weak for the DTF model and more pronounced for the turbulent batch reactor model. Good convergence of the DTF approach is attributed to the artificial flame thickening feature of the model that suppresses flame wrinkling due to scales finer than the flame, which in turn suppresses the flame-induced turbulence at scales near and below the grid resolution. Frequency spectra of the resolved kinetic energy obtained at several locations in the flow-field for the three meshes also exhibit better convergence, indicating a stronger measure of grid independence. © 2017 by Vaidyanathan Sankaran, Timothy Gallagher.

关键词： Large Eddy simulation Kinetic Energy Air Mass Flow Rates Combustors Numerical modeling Non Reacting Flow Velocity Profiles Shear Layers Partially Premixed Combustion Vortex Shedding Phenomena

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Frustrated Coupled Oscillators with Anomalous Coupling Method

Frustrated Coupled Oscillators with Anomalous Coupling Metho...

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IEEE Asia Pacific conference on Postgraduate Research in Microelectronics and Electronics (PrimeAsia)

作者： Ueta, Kazuki Uwate, Yoko Nishio, Yoshifumi Tokushima Univ Dept Elect & Elect Engn 2-1 Minami Josanjima Tokushima 7708506 Japan

ISBN: (纸本)9781538605240

Synchronization phenomena of frustration network by coupled oscillators has been studied in a wide range of fields, such as medicine and engineering. It is investigated towards various systems up to now. However, analysis of regarding more complex systems are little. In our study, we developed the system model so that a basic minimum unit even in more complex systems. In addition, we observed synchronization phenomena about the system. In this paper, we show the result of circuit experiment with oscilloscope. Finally, we state the conclusion accompanying the experiment results.

关键词： Synchronization Oscillators Couplings Integrated circuit modeling Resistors simulation Asia

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Numerical modeling and simulation of supersonic flows in propulsion systems by open-source solvers 21

Numerical modeling and simulation of supersonic flows in pro...

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

作者： Hoste, Jimmy-John O. E. Casseau, Vincent Fossati, Marco Taylor, Ian J. Gollan, Rowan J. Centre for Future Air-Space Transportation Technology Department of Mechanical and Aerospace Engineering University of Strathclyde GlasgowG1 1XJ United Kingdom Division of Aerospace Sciences School of Engineering University of Glasgow GlasgowG12 8QQ United Kingdom Centre for Hypersonics School of Mechanical & Mining Engineering The University of Queensland BrisbaneQLD4072 Australia

ISBN: (数字)9781624104633

ISBN: (纸本)9781624104633

Two open-source solvers, Eilmer and hyFoam, are here considered for their performance in simulating high-speed flows in different flow conditions and geometric configurations typical of propulsive systems at supersonic speeds. The goal is to identify the open-source platform providing the best compromise between accuracy, flexibility and computational cost to eventually simulate the flow fields inside ramjet and scramjet engines. The differences in terms of discretization and solution methods of the selected solvers are discussed in terms of their impact on solution accuracy and computational efficiency and in view of the aerothermodynamic analysis and design of future trans-atmospheric propulsive systems. In this work steady state problems are considered. Numerical results of two scramjet type engines demonstrated a similar predictive capability of both codes in non-reacting conditions. These results highlight their potential to be considered for further characterization of overall engine performance. © 2017, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Computational efficiency

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A comparative study of elliptic and round scramjet combustors by improved delayed detached Eddy simulation 21st

A comparative study of elliptic and round scramjet combustor...

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

作者： Yao, Wei Yuan, Yueming Li, Xiaopeng Wang, Jing Fan, Xuejun Key Laboratory of High Temperature Gas Dynamics Institute of Mechanics CAS No.15 Beisihuanxi Road Beijing100190 China School of Engineering Science University of Chinese Academy of Science Beijing100049 China Institute of Engineering Thermophysics CAS No.11 Beisihuanxi Road Beijing100190 China

ISBN: (纸本)9781624104633

To explore the combustion performance of non-rectangular type supersonic combustors, the flow and combustion characteristics in round and round-to-elliptic shape-transition (RdEST) supersonic combustors under the same configurations of flight Mach number and fuel equivalence ratio were compared based on modeling results. The fuel equivalence ratio is maintained the same as 0.8, while two inlet Mach numbers of 2.5 and 3.0 both corresponding to a real flight Mach number of 6.5 are tested. To alleviate the strict requirements on wall-normal and -parallel grid spacing, Improved Delayed Detached Eddy simulation (IDDES) is employed in this study to enable an automatic choice of RANS or LES mode depending on the local boundary layer thickness and turbulent viscosity. To reduce the computational cost of stiff kerosene oxidation chemistry, a total of four versions of skeletal mechanisms (respectively 48s/197r, 39s/153r, 28s/92r and current 19s/54r) have been developed based on the detailed 2815s/8217r Dagaut mechanism by using a highly efficient and reliable directed relation graph with error propagation and sensitivity analysis (DRGEPSA) method together with manual path analysis. Although the mechanism size has been significantly reduced, key kinetic properties such as adiabatic flame temperature, heat release rate, ignition delay and laminar flame speed all agree well with the original detailed mechanism. The static pressure along streamwise direction is compared with the measurement to validate the modeling results. Two key aspects are well predicted, i.e. the pressure ratio and the initial pressure rise location, indicating that the flame anchoring location and the distribution of wave structures inside the combustor are close to the actual situation. Then the aerodynamic fields are analyzed for the round and elliptic combustors to compare their flow, mixing and combustion related flow structures. The three-dimensional wave structures inside the elliptic combustor are fi

关键词： Mach number

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Autoignition characteristics of selected alternative fuels at high OPR conditions 53

Autoignition characteristics of selected alternative fuels a...

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

作者： Zeppieri, Stephen Smith, Lance Colket, Med United Technologies Research Center East HartfordCT06108 United States Combustion Science Group TFS MS 129-29 United States Propulsion Technology TFS MS 129-29 United States Thermo-Fluid Sciences Department United States

ISBN: (数字)9781624105111

ISBN: (纸本)9781624105111

As aircraft engines are operated at higher operating pressures for efficiency improvements, the associated increased combustor air inlet temperature will lead to reduced autoignition times upon mixing with the fuel leaving less time for the fuel-air premixing that is required to achieve ultra-low NOx emissions. Thus, experiments exploring the impact of various fuel physical and chemical properties were performed on autoignition time using a premixing aeroengine fuel injector at realistic combustor inlet conditions. Two testing methods were used to explore the impact of these various fuel properties on the autoignition characteristics of six different fuels. The experimental results and subsequent analysis revealed that the fuel Cetane number was the primary property that influenced the fuel-air autoignition characteristics for the tested fuels. A single kinetic mechanism, in conjunction with characteristic time scale analysis, generated simulation results that were both qualitatively and quantitatively consistent with the experimental findings. This modeling technique allowed for the extension of the analysis to more severe operating conditions for assessment of the six fuels' autoignition characteristics under a representative high OPR cycle condition, for the reference fuel injector system.

关键词： Combustors

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