一种用于导弹末制导的线性化控制方法  

A Linearized Method for Missile Flight Control in Terminal Guidance

作　　者：金勇俊[1] 杜永军[1] 张科[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072

出　　处：《上海航天》2006年第5期24-27,共4页Aerospace Shanghai

基　　金：国家自然科学基金(60575013)

摘　　要：针对包含未知参数的导弹运动非线性模型,提出了一种用于末制导的线性化反馈简化控制方法。在模型中引入附加加速度输出,通过消除内反馈和零极点以输入-输出的近似线性控制导弹的非线性运动。给出了控制模型及其构成。仿真结果表明,该方法的反应速度快、稳定性好,控制精度满足要求,可用于导弹跟踪飞行控制。A simplified linearized feedback control method of terminal guidance was put forward for a nonlinearized model including unknown parameters of missile in this paper, The additional acceleration was induced to the model, The nonlinearized motion for missile which the input and output were approximated as linear relation was controlled by eliminating the inner feedback and zero pole. The control model and its composition were given, The simulation result showed that the method had characteristics of fast response, good stability, which accuracy could meet the reqirement. The method would be used to track flight control of missile.

关 键 词：导弹 飞行控制 末制导 非线性控制 反馈线性化 附加加速度 

分 类 号：TJ765.1[兵器科学与技术—武器系统与运用工程]