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Research On Parameter Identification And Control Of Flight Simulator Electric Control Load System

Posted on:2020-07-08Degree:MasterType:Thesis
Country:ChinaCandidate:X B WangFull Text:PDF
GTID:2392330575454825Subject:Mechanical engineering
Abstract/Summary:PDF Full Text Request
The maneuvering load system is one of the key subsystems of the flight simulator.The main function is based on the principle of aircraft maneuvering.The simulation technology is applied in real time to realistically reproduce various sensory forces when manipulating real aircraft.Accurately maneuvering the load system model is the basis for realizing the realistic simulation force.Using the relevant theory and method of system identification,the input and output data of the collection system is identified by the identification system,an accurate mathematical model is established,and the control algorithm is added based on the model.Research that enables control performance to meet expected goals.This paper introduces a set of electric control load system based on permanent magnet synchronous motor,ball screw pair and control device as PLC.The device has the characteristics of simple structure and flexible control.The mathematical modeling of permanent magnet synchronous motor,tension pressure sensor,ball screw drive and controller is established,and the mathematical model of electric control load system is given.The principle,process and method of system identification are introduced in detail.The identification experiment scheme is designed for the electric control load system of this research,including the determination of input and output signals,the selection of sampling interval,the calibration of the tension sensor,and the delay of the controller.Experimental analysis,etc.,using the recursive least squares method and correlation method to derive the model parameters of the system,and finally verify the validity of the identification model.In view of the problem that the steering rod jitter and the rod force output are unstable during the experiment,PID control is added to the system.In the experiment,it is found that the rod force output error becomes small,the steering column has no obvious jitter,and the systemtracking performance is improved to some extent.The prototype of the electric control load system designed this time has basically reached the expected goal,providing theoretical basis and practical experience for more in-depth research in the future.Some problems were also found in the experiment,such as the slow response of the system and the need for further improvement in the later stage.
Keywords/Search Tags:Flight simulator, Control load system, Mathematical model, System identification
PDF Full Text Request
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