飞行姿态控制系统半物理仿真平台开发

Development of Semi-physical Simulation Platform for Flight Attitude Control System

飞行姿态控制系统作为飞机姿态控制的重要组成部分,对飞机起降、空中姿态调整具有重要影响;为快速建立液压作动系统数值计算模型、飞行员操纵及控制单元、舵面及起落架演示单元等实验实物环节,基于Automation Studio液压设计及仿真专用软件,设计与开发了某型飞机飞行姿态控制系统的半物理仿真实验平台;给出了飞行姿态控制系统半物理仿真平台软总体方案、硬件组成、工作原理及开发和实验流程;最后,以飞机方向舵为例,开发了包括液压油油箱、液压马达、控制阀门、作动筒及管道、溢流阀、限位开关等装置的数值计算模型,液压阀位置数字PID调节器,结合舵面及其加载演示系统PLC控制程序,配合现场人员的实际操控动作,开展了方向舵液压作动随动控制系统半物理仿真实验研究,试验并分析了飞机机翼液压作动系统位置随动过程中的运行工况,并记录关键的实验数据曲线,为飞行姿态控制系统研究提供了一种直观的仿真及分析实验方法。

As an important part of aircraft attitude control,flight attitude control system has the important influence on aircraft takeoff and landing and air attitude adjustment.In order to quickly establish the numerical calculation model of hydraulic actuation system,pilot control and control unit,rudder and landing gear demonstration unit,and other experimental physical links,a semi physical simulation experimental platform of flight attitude control system of an aircraft is designed and developed based on the special software for hydraulic design and simulation of Automation Studio.The overall software scheme,hardware composition,working principle,development and experimental flow of the semi-physical simulation platform of a flight attitude control system are given.Finally,taking the aircraft rudder as an example,the numerical calculation model including a hydraulic oil tank,hydraulic motor,control valve,actuator and pipeline,overflow valve,limit switch and other devices is proposed,the digital PID regulator of hydraulic valve position is combined with the PLC control program of the rudder surface and its loading demonstration system,and combined with the actual control action of field personnel,the semi-physical simulation experiment of the rudder hydraulic actuation servo control system is carried out,The operating conditions in the position servo process of aircraft wing hydraulic actuator system are tested and analyzed,and the key experimental data curves are recorded,which provides an intuitive simulation and analysis experimental method for the research of the flight attitude control system.