航空工程进展2025，Vol.16Issue(4)：93-99,124,8.DOI:10.16615/j.cnki.1674-8190.2025.04.09
组合飞行器飞行控制律设计分析与试飞验证
Design,analysis and verification flight test of control law for combined aircraft
胡芳芳 1章胜 1朱喆 1黄江涛 1杜昕1
作者信息
- 1. 中国空气动力研究与发展中心 空天技术研究所,绵阳 621000
- 折叠
摘要
Abstract
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 sig-nal is established,and the longitudinal/lateral heading flight control law suitable for the combined aircraft is devel-oped 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 con-sideration 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.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Key words
combined aircraft/robust servo control/frequency-domain analysis/Monte-Carlo simulation/flight test分类
航空航天引用本文复制引用
胡芳芳,章胜,朱喆,黄江涛,杜昕..组合飞行器飞行控制律设计分析与试飞验证[J].航空工程进展,2025,16(4):93-99,124,8.
