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Multimodal pilot control Behavior in Combined Target-Following Disturbance-Rejection Tasks

JOURNAL OF GUIDANCE control AND DYNAMICS 2009年第5期32卷 1418-1428页

作者： Zaal, P. M. T. Pool, D. M. Mulder, M. van Paassen, M. M. Delft Univ Technol Fac Aerosp Engn Control & Simulat Div NL-2600 GB Delft Netherlands

Investigating how humans use their perceptual modalities while controlling a vehicle is important for the design of new control systems and the optimization of simulator motion cueing. For the identification of separate pilot response functions to the different perceived cues, multiple forcing functions need to be inserted into the manual control loop. An example of a task with multiple forcing functions is a combined target-following disturbance-rejection task, where a target and disturbance signal are used to separate the human visual and vestibular motion responses. The use of multiple forcing functions, however, also affects the nature of the control task and how the motion cues are used by the pilot to form a proper control action. This paper presents the results of an experiment where possible effects of using multiple forcing functions on pilot control behavior in an aircraft pitch control task are investigated. The results indicate that pilot performance and control activity are significantly lower when the relative power of the target forcing function is increased. This is caused by a significant change in multimodal pilot control behavior. With an increase in relative target power, the visual-perception gain is reduced and the visual time delay becomes higher. The motion-perception gain reduces if both forcing functions have significant power. It is also found that multimodal pilot control behavior in a pure target or disturbance task can be analyzed by adding a small additional disturbance or target signal, respectively. In this case, the effects on control behavior are found to be minimal, while still being able to accurately estimate the parameters of the multichannel pilot model.

关键词： pilot control pilot Aerospace Engineering Aircraft Pitch control control Systems State Space Representation Optimal control Frequency Response Functions SIMONA Research Simulator Analysis of Variance

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HANDLING QUALITIES FOR pilot control OF APOLLO LUNAR-LANDING SPACECRAFT

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JOURNAL OF SPACECRAFT AND ROCKETS 1966年第5期3卷 632-&页

作者： CHEATHAM, DC HACKLER, CT NASA Manned Spacecraft Center Houston Texas

piloted simulations of the lunar-landing maneuver were conducted at the Manned Spacecraft Center to determine control problems and required handling qualities of lunar-landing spacecraft. The studies examined control problems and handling qualities required to complete the final approach to landing starting from ranges of 2000 to 3000 ft from the desired landing site. Results of the simulation studies indicated that satisfactory handling qualities could be obtained with control powers of the order of 10 deg/sec²for the rate command control using proportional firing thrusters, and that control powers of the order of 5 deg/sec²provided satisfactory handling qualities for the rate command control system employing on-off thruster firing logic. Within a satisfactory range of maximum rate command and control power available, the pilots tolerated equivalent time constants up to 1 sec in the proportional system and equivalent time constants of the order of 3 sec in the on-off thruster logic control system. In addition, the simulation studies showed that the direct on-off logic control system (no rate feed-back) would probably not provide satisfactory control handling qualities for the lunar landing. © 1966 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.

关键词： Handling Qualities Lunar Landing Spacecrafts pilot control control System Design Manned Spacecraft Command and control Systems pilot Attitude control System Flight Vehicle

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Influences of Simulator Motion System Characteristics on pilot control Behavior

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JOURNAL OF GUIDANCE control AND DYNAMICS 2013年第3期36卷 667-676页

作者： Nieuwenhuizen, F. M. Mulder, M. van Paassen, M. M. Buelthoff, H. H. Max Planck Inst Biol Cybernet D-72012 Tubingen Germany Delft Univ Technol Fac Aerosp Engn Control & Simulat Div NL-2600 GB Delft Netherlands

Low-cost motion systems have been proposed for certain training tasks that would otherwise be performed on high-performance full-flight simulators. These systems usually have lower bandwidth and lower smoothness. The influence of these characteristics on pilot perception and control behavior is unknown and needs to be investigated. In this paper, this is done by simulating a model of a simulator with limited capabilities on a high-end simulator. The platform limitations, which consist of a platform filter, time delay, and noise characteristics, can then be removed one by one, and their effect on control behavior is studied in isolation. An experiment was conducted to identify pilot perception and control behavior in a closed-loop control task. The time delay and noise characteristics of the simulators did not have an effect. However, it was found that the bandwidth of the motion system had a significant effect on performance and control behavior. Results indicate that the motion cues were barely used at all in conditions with a low bandwidth, and that participants relied on the visual cues to generate lead to perform the control task.

关键词： pilot control pilot Closed Loop control Full Flight Simulator Stewart Platform SIMONA Research Simulator Aeroplane pilot Modeling Variance Decomposition Analysis of Variance

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Simulation of a pilot control Valve Using Pseudo Bond Graph Approach 7

Simulation of a Pilot Control Valve Using Pseudo Bond Graph ...

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International Conference on Fluid Power and Mechatronics FPM

作者： Wang Zhiwen Xiong Wei Wang Haitao Wang Zuwen Dalian Maritime Univ Inst Ship Electromech Equipment Dalian Peoples R China

ISBN: (纸本)9781479987702

The dynamic behaviors of a pilot control valve have been studied using the pseudo bond graph approach. The pseudo bond graph model can synchronously retain the mathematical structure and the physical structure of the research object. State equations are deduced from the pseudo bond graph model and been numerically solved with MATLAB-SIMULINK. The simulation results show that the pilot control valve can work well in despite of an unexpected response. The profiles of the gas pressure in different chambers and the displacement of the valve spool are obtained. The pseudo bond graph model can predict the dynamic behaviors of the pilot control valve, thereby providing reference for further optimization.

关键词： pseudo bond graph pneumatic dynamic analysis line-thrower pilot control

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A Simulator Comparison Study into the Effects of Motion Filter Order on pilot control Behavior

A Simulator Comparison Study into the Effects of Motion Filt...

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AIAA Science and Technology (SciTech) Forum and Exposition

作者： Pieters, Marc A. Zaal, Peter M. T. Pool, Daan M. Stroosin, Olaf Mulder, Max San Jose State Univ San Jose CA 95192 USA NASA Ames Res Ctr Human Syst Integrat Div Moffett Field CA 94035 USA Delft Univ Technol Control & Simulat Div Fac Aerosp Engn POB 5058 NL-2600 GB Delft Netherlands

ISBN: (数字)9781624105784

ISBN: (纸本)9781624105784

This paper describes an experiment investigating the effects of motion filter order on human manual control tracking behavior and performance. The experiment was performed on two simulators: the Vertical Motion Simulator at NASA Ames Research Center and the SIMONA Research Simulator at Delft University of Technology. Eighteen pilots in the Vertical Motion Simulator and twenty pilots in the SIMONA Research Simulator performed the experiment with a full factorial variation of three motion filter orders and two motion filter frequencies, in addition to a reference no-motion and full-motion condition. Motion shaping filters derived from Objective Motion Cueing Test measurements on the Vertical Motion Simulator were included in the SIMONA Research Simulator motion logic to match the motion cues between both simulators. Furthermore, the side sticks were set to matching characteristics and the visual cues were matched in terms of time delay, graphics size and screen characteristics. With increased motion filter order, pilots showed worse performance and a lowered contribution of motion feedback in their control strategy. Increasing the motion filter break frequency had similar effects, which were stronger than the effects of increasing the motion filter order, for the eight experimental conditions that were considered in this experiment. For the same motion condition the simulators showed offsets in the results. However, the trends between the motion conditions were similar, leading to the conclusion that for simulator comparisons relative trends are easier to replicate between simulators than absolute results within one condition.

关键词： pilot control SIMONA Research Simulator NASA Ames Research Center pilot pilot Modeling Tracking control Statistical Analysis Flight Simulation Analysis of Variance Primary Flight Display

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Neural Network Modeling of Lateral pilot Landing control

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JOURNAL OF AIRCRAFT 2009年第5期46卷 1721-1726页

作者： Mori, Ryota Suzuki, Shinji Univ Tokyo Dept Aeronaut & Astronaut Bunkyo Ku Tokyo 1140023 Japan

Human pilot landing control has been analyzed by the authors using neural network modeling. Although the previous research considered only longitudinal control, analysis of the lateral control is the focus of this paper. The lateral control can be quite difficult under crosswind conditions, because the combination of two lateral control methodologies (crab method and wing-low method) is needed for a successful landing. To analyze lateral control, this paper makes a first step: a lateral pilot control model is established. The necessary visual cues for lateral control are defined, and neural network models for aileron and rudder controls are constructed. The adequacy of the proposed neural network model is checked by Monte Carlo simulations.

关键词： Landing control Neural Networks pilot Yaw control pilot control Longitudinal control Monte Carlo Simulation pilot Modeling Aircraft Landing Flight Data

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Intelligent Walking Excavator and pilot control Analysis

Intelligent Walking Excavator and Pilot Control Analysis

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The 2015 International Conference on Advances in Construction Machinery and Vehicle Engineering(ICACMVE’2015)

作者： Wang Chunhua Gu Xingbin Liu Hanlin Zhao Weimin College of mechanical science and technology Northeast Petroleum University

Based on its special lower vehicles moving device,and its operational capability in difficult topographicterrains(such as steep mountains,forest lands,river channels and tunnels),walking excavator could save precious time for the rescue and relief work,and play a significant role in the recovery work,which has become the focus construction machinery of research and development.

关键词： walking excavator pilot control intelligent rescue and relief

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Investigation into pilot Perception and control During Decrab Maneuvers in Simulated Flight

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JOURNAL OF GUIDANCE control AND DYNAMICS 2010年第4期33卷 1048-1063页

作者： Beukers, J. T. Stroosma, O. Pool, D. M. Mulder, M. van Paassen, M. M. Delft Univ Technol Fac Aerosp Engn Control & Simulat Div NL-2629 HS Delft Netherlands

An experiment was conducted in the SIMONA Research Simulator at Delft University of Technology to investigate the influence of sway, roll, and yaw motion cues on pilot performance, control, and motion perception during decrab maneuvers. In the experiment, six pilots were instructed to perform manual decrab maneuvers in heavy crosswind conditions with a Cessna Citation 500 model. The contributions of yaw, roll, and sway motion stimuli were varied such that their effects on objective measures and subjective ratings could be examined. The results of this experiment show that yaw motion had a positive influence on performance in terms of lateral touchdown distance from the runway centerline. Roll motion significantly decreased roll rate variations during decrab. High workload and the relatively low intensity of lateral motion cues led to the fact that pilots were unable to give consistent fidelity ratings. This result emphasizes the need for an objective and quantifiable method to determine motion fidelity for such maneuvers. pilot models can possibly be used to further investigate the influence Of different motion cues in these transient control tasks.

关键词： Aircraft pilot Yaw Damper Runways Cessna Citation II Aircraft Center of Gravity Sideslip Angle National Aerospace Laboratories pilot control Analysis of Variance Pearson Correlation Coefficient

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Simulation of a pilot control Valve Using Pseudo Bond Graph Approach

Simulation of a Pilot Control Valve Using Pseudo Bond Graph ...

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2015 International Conference on Fluid Power and Mechatronics

作者： WANG Zhiwen XIONG Wei WANG Haitao WANG Zuwen Institute of Ship Electromechanical Equipment Dalian Maritime University

关键词： pseudo bond graph pneumatic dynamic analysis line-thrower pilot control

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pilot behavior modeling and its application to manual control tasks

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IFAC-PapersOnLine 2016年第32期49卷 159-164页

作者： Efremov, A.V. Tjaglik, M.S. Tiumentzev, U.V. Wenqian, Tan Moscow aviation Institute Moscow Russia Beijing University of Aeronautics and Astronautics Beijing100191 China

The modified two pilot behavior models are discussed. One of them is the structural model. Its modification allowed to get better agreement in calculation of variance of error and to evaluate the influence of some new task variables (control element gain coefficient, requirements to the accuracy) on pilot – vehicle system parameters. The other model is the composite model of pilot behavior based on neural network approach. This model provides high agreement between the simulated and experimental pilot frequency response characteristics. The structural model is used for development of the criterion for the of flying qualities prediction in lateral channel with taking into account the influence of motion cues on pilot behavior and for the preliminary design of the predictive display. As for the composite model it was used for development of the flying qualities criterion for the pitch control task based on calculation of pilot and pilot aircraft system frequency response parameters. The additional procedure - the preliminary selection of dynamic configurations from the database was proposed what allowed to get high agreement between the predicted flying qualities level evaluated by the pilots in flight tests. © 2016

关键词： Quality control Aircraft Aircraft control Flight control systems Flight simulators Frequency response Aircraft systems Dynamic configuration Flying quality Frequency response characteristic pilot control Response parameters simulation Structural modeling

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