摘要
利用最优控制理论及非线性控制理论中的精确线性化方法,将再入机动弹头方向控制方案设计问题转化为线性系统综合问题,无需作任何简化假设,推导方式更为简单,为再入弹头的机动方式提供了一种新方法,仿真表明推导出的制导律可行。
The reentry maneuverable warhead end angle is constraint and traditional proportion guidance can not meet the demand. With the optimal control theory and precise linearlzation method of the nonlinear control systems theory, the reentry maneuverable warhead guidance scheme design problem is transformed to linear system synthesis problem. The guidance law derivation is very simple without any simplify hypothesis. A very efficient method of studying time varying system is provided.
出处
《弹箭与制导学报》
CSCD
北大核心
2007年第2期8-10,共3页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
再入机动弹头
最优制导
黎卡提方程
reentry maneuvering warhead
optimal guidance
Riccati equation
