拦截器姿态控制系统的滑动模态设计法  

SLIDING MODE SYNTHESIS OF INTERCEPTOR ATTITUDE CONTROL SYSTEM

作　　者：姚立强[1] 徐松源[1] 

机构地区：[1]哈尔滨工程大学,哈尔滨电工学院

出　　处：《宇航学报》1995年第3期18-24,共7页Journal of Astronautics

摘　　要：拦截器姿态控制系统是一个非线性控制系统。系统的技术要求比较高，除了动静态性能外，还要有较强的鲁棒性，这就对系统的设计带来较大的困难。本文介绍一种以时间最佳和变结构理论中滑动模态为基础的设计法，它的特点是设计方法简单，考虑非线性因素方便，系统除具有良好的动静态性能外，还具有很强的鲁棒性。文中介绍了基本设计原理，拦截器姿态控制系统的设计方法和仿真结果。Interceptor attitude Control system is a nonlinear control system. The performance tequirements for the system are very high. Besides the transient and steady-state response performances, the control system must have robustness. So there are many difficulties in the design of the system.In this thesis, a design method which based on time --optimal and sliding mode in variable structure theory is introduced. There are many characteristics in this method,Such as its simplicity in design and its Convenience in introducing nonlinear factor, moreover,the system designed according to this method not only has fine performance in transient and steady--state response but also has strong robustness.Furthermore, The basic synthesis principle, synthesis of interceptor attitude Contnol system and the simulation results are recommended in this thesis.

关 键 词：拦截器姿态控制系统 时间最佳控制 滑动模态控制 

分 类 号：V448.222[航空宇航科学与技术—飞行器设计]