基于变结构鲁棒控制的导弹再入解耦控制  

Missile Reentry Decoupling Control Based on the Variable Structure Robust Control

作　　者：周军[1] 刘玉玺[1] 周凤岐[1] 

机构地区：[1]西北工业大学精确制导与控制研究所,陕西西安710072

出　　处：《飞行力学》2008年第2期29-32,共4页Flight Dynamics

摘　　要：根据时标分离的原则,分成快慢两个回路采用动态逆对导弹大迎角再入系统进行了设计。针对快回路受到的参数不确定性和外来干扰引起的不确定性的影响,提出了采用变结构控制和鲁棒控制的方法,使系统受到的不确定影响衰减到一个给定的水平,并获得一个H∞跟踪性能指标。理论分析和仿真结果表明,采用这种方法系统具有良好的鲁棒性和跟踪特性。According to the principle of timescale separation, the system is separated into fast loop and slow loop to design the missile reentry in large attack angle with the method of the dynamic inversion. For the parameter uncertainty and external disturbance of the fast loop, we propose the method of the variable structure control and robust control, which attenuate the uncertainty to a prescribed level, and achieve a H∞tracking performance index. The theory analysis and simulation results denote the control method has a better robustness and tracing characteristic.

关 键 词：导弹大迎角再入 时标分离 动态逆 变结构 鲁棒控制 

分 类 号：V448.222[航空宇航科学与技术—飞行器设计]