大气层外拦截器预测导引律设计及制导系统稳定性分析  

Design of Predictive Guidance Law and Stability Analysis of Guidance System for Exo-Atmospheric Interceptor

作　　者：章国江[1] 杨宝庆[1] 姚郁[1] 

机构地区：[1]哈尔滨工业大学航天学院,哈尔滨150080

出　　处：《弹道学报》2010年第2期10-14,共5页Journal of Ballistics

基　　金：自然科学基金项目(60674043);博士点基金项目(20060213040)

摘　　要：针对脉冲式发动机作为轨控执行机构的大气层外拦截器,考虑视线转率的测量噪声和弹-目相对距离的估计误差,推导了视线转率预测值与当前时刻状态、控制输入、视线转率测量噪声以及弹-目相对距离估计误差之间的关系;基于预测控制方法设计了开关式导引律,通过分析得到了开关式导引律对应的开关曲线;应用李雅普诺夫方法分析了制导系统的稳定性.数值仿真结果表明,视线转率和弹-目相对距离测量不准确情况下,应用该文提出的导引律设计方法仍然能够实现直接碰撞.To research exo-atmospheric interceptor with pulse-jet, considering the measurement noise of rotation rate of LOS （line of sight） and error of estimating relative distance between missile and target, the LOS rate was predicted by state, control input, measurement noise of LOS and estimation error of relative distance. The switching guidance law was designed on the basis of predictive control, and switching curve was derived by analysis. Stabilization of the guidance sys- tem with switching guidance law was analyzed by using Lyapunov method. The simulation result shows that the direct impact can be realized by the guidance law proposed in this paper while the LOS rate and the relative distance between missile and target measured unexactly.

关 键 词：拦截器 导引律 开关曲线 预测控制 

分 类 号：V448[航空宇航科学与技术—飞行器设计]