中国科技核心期刊

中文核心期刊

CSCD来源期刊

空间控制技术与应用

• 短文 • 上一篇    下一篇

基于指数趋近律的高超声速飞行器
滑模控制器设计

李惠峰,孙文冲   

  1. 北京航空航天大学, 北京 100191
  • 收稿日期:1900-01-01 修回日期:1900-01-01 出版日期:2009-08-26 发布日期:2009-08-26

Index Approach Law Based Sliding Control for A Hypersonic Vehicle
LI Huifeng,SUN Wenchong

LI Huifeng,SUN Wenchong   

  1. Beijing University of Aeronautics and Astronautics, Beijing 100191
  • Received:1900-01-01 Revised:1900-01-01 Online:2009-08-26 Published:2009-08-26

摘要: 采用NASA兰利实验室开发的一种通用高超声速飞行器的改良非线性纵向模型,针对输入/输出线性化模型,以指数趋近律作为到达条件设计滑模变结构控制器,该方法能够较好地处理不确定性问题,而且对外界干扰不敏感。仿真在高超声速巡航条件下进行,通过对跟踪高度和速度阶跃指令的仿真验证,并与符号函数作为到达条件设计的滑模控制器进行对比,发现前者在速度阶跃和高度阶跃响应速度上较后者分别提高了50%和70%左右,并且以符号函数设计的滑模控制器存在稳态误差,而以指数趋近律作为到达条件设计的滑模控制器可以达到0误差的跟踪精度。

关键词: 高超声速飞行器, 滑模控制, 趋近律, 鲁棒性

Abstract: A universal improved nonlinear longitudinal model of a hypersonic vehicle developed by the Langley lab is adopted. For its I/O linearized model, a sliding mode controller is designed. This method can solve the uncertainty problem and it is insensitive to disturbances. The index approach law used to drive the sliding mode to reach the sliding surface is adopted to eliminate the quiver. The simulation results for tracking the height step and velocity step order at cruise condition show that the sliding mode controller with index approach law acquires satisfying tracking ability and strong robustness. The controller can not only track the single height step order or velocity step order accurately, but track the height step order and velocity step order together fleetly with zero error. In addition, the sliding controller with index law is better than the one with sign function in tracking speed and precision. Another result is also proved that the index approach law can eliminate the quiver perfectly.

Key words: hypersonic vehicle, sliding mode control, approach law, robustness

中图分类号: 

  • V4