摘要
组合飞行器分离前后,主机焦点和重心会发生突变,其姿态受分离影响亦会发生剧烈变化,这对飞行控制律的设计提出了较大的挑战。研究适用于组合飞行器的飞行控制方法,建立包含跟踪信号的被控对象模型,采用鲁棒伺服思想发展适用于组合飞行器的纵向/横航向飞行控制律,该控制律由制导回路、角度外回路和角速率内回路组成,通过在角速率内回路中引入积分环节来提高系统对外界扰动的鲁棒性。通过频域法分析闭环系统特性,并在考虑多种误差源的情况下通过时域蒙特卡洛仿真验证控制律的有效性和鲁棒性。开展组合飞行器验证性飞行试验,结果表明:飞行过程中主机与子机安全分离、全程姿态可控,进一步验证了本文鲁棒伺服飞行控制律的可行性。
The neutral point,center of gravity and flight attitude of the carrier aircraft will change dramatically after the separation of the combined aircraft.This poses a significant challenge to the design of flight control rate.In this paper,a flight control method suitable for combined aircraft is studied.The controlled model including tracking signal is established,and the longitudinal/lateral heading flight control law suitable for the combined aircraft is developed by using the robust servo idea.The control law is composed of guidance loop/angular outer loop and angular rate inner loop,and the robustness of the system to external disturbances is improved by integrating in the inner loop of the angular rate.The closed-loop system characteristics are analyzed using the frequency domain method,and the validity and robustness of the control law are verified by Monte-Carlo simulation in time-domain under consideration of various error sources.Finally,a verification flight test of the combined aircraft is carried out.During the flight,the carrier aircraft and the child aircraft are separated safely,and the attitude is controllable throughout the flight,and further verifies the reliability of the robust servo flight control law proposed in this paper.
作者
胡芳芳
章胜
朱喆
黄江涛
杜昕
HU Fangfang;ZHANG Sheng;ZHU Zhe;HUANG Jiangtao;DU Xin(Aerospace Technology Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China)
出处
《航空工程进展》
2025年第4期93-99,124,共8页
Advances in Aeronautical Science and Engineering
关键词
组合飞行器
鲁棒伺服控制
频域分析
蒙特卡洛仿真
飞行试验
combined aircraft
robust servo control
frequency-domain analysis
Monte-Carlo simulation
flight test
作者简介
通信作者:杜昕(1985-),男,博士,高级工程师。E-mail:duxin_cardc@foxmail.com。
