一种改进的带角度约束最优制导律

An Improved Optimal Guidance Law with Angle Constraint

为了实现拦截任务需求,考虑拦截弹的角度约束以及能量过早损失而不能满足后续拦截需求,推导了一种改进的最优制导律。基于能量最小目标函数结构,提出一种使初始段需用过载尽量小且终端视线角能收敛到期望值的控制权函数;基于小角度假设,采用最优控制理论,推导了带视线角约束的最优制导律;基于制导律能使终端视线角收敛的特点,将带终端视线角问题转换为终端交会角问题,得到带终端交会角约束的最优制导律。仿真结果表明,所设计的制导律能实现终端交会角控制,同时能保证制导初始段能量消耗较小,且命中精度较高。所设计的方法对拦截弹的最优制导律研究具有一定参考和应用价值。

In order to achieve the intercept mission requirements,an improved optimal guidance law is derived considering the angle constraint of the interceptor and the premature loss of energy that cannot satisfy the subsequent interception requirements.Based on the structure of energy minimum objective function,a control weighted function is proposed to minimize the required overload in the initial phase and the terminal line of sight(LOS)angle can converge to the excepted value.An angle constraint optimal guidance law is derived in view of small angle assumption and optimal control theory.Based on the characteristics that the guidance law can make the terminal LOS angle converge,the problem of terminal LOS angle is converted into the problem of terminal encounter angle,and the optimal guidance law with terminal-intersection angle constraint is obtained.The simulation results show that the designed guidance law can not only realize terminal encounter angle control,and also ensure low energy consumption in the initial stage of guidance,as well as achieve high hit accuracy.The designed approach has certain reference and application values for the study on the optimal guidance law of interception missile.