注：国家自然科学基金项目（NO. 11472058）；国家自然科学基金重点项目资助（NO. 11732005）

作者：和志伟，管萍

单位：北京信息科技大学 自动化学院，北京100192

中图分类号：V 249.122+.2        

文献标识码：A        

文章编号：1006-883X(2019)04-0007-05

收稿日期：2019-03-21

 

摘要：针对高超声速飞行器运行环境中气动参数大范围变化可能导致失稳现象，构建高超声速飞行器姿态的滑模变结构控制器。通过多时间尺度理论将飞行器姿态控制系统分为内外双闭环子系统，分别为内外环设计滑模姿态控制律，保证控制系统对气动参数变化不敏感，能稳定准确地跟踪期望姿态角指令。仿真结果表明所提滑模变结构姿态控制算法性能良好，对气动参数变化有一定的鲁棒性。

关键词：高超声速飞行器；气动参数；姿态控制；滑模控制

 

Variable Structure Control of Attitude for Hypersonic Vehicle 

HE Zhi-wei, GUAN Ping

School of Automation, Beijing Information Science and Technology University, Beijing 100192, China

Abstract: A sliding mode variable structure controller for the attitude of hypersonic vehicle is designed, aiming at the flight instability caused by the wide range variation of aerodynamic parameters during flight. The attitude control system is divided into internal and external closed-loop subsystems based on the multi-time scale theory, and then the sliding mode attitude control laws are built for them respectively, which makes the control system insensitive to the aerodynamic parameters and track the desired attitude angles stably and accurately. The simulation results show that the proposed sliding mode control method is effective and robust to aerodynamic parameters.

Key words: hypersonic vehicle; aerodynamic parameters; attitude control; sliding mode control

 

 

备注：2019年 第25卷 第04期