基于飞行时间估计带时间约束的末制导律设计

针对某些导弹要求限制末端攻击时间的作战要求,本文提出一种带末端攻击时间约束的新型制导律。所提出的制导律是通过线性最优控制方法的解而得到的,该制导律是比例导引律和攻击时间误差反馈的组合,此攻击时间误差有别于通过比例导引律所设定的攻击时间。本文用到飞行时间估算方法来完善所提出的制导律。所得制导律形式简单、实用。数字仿真结果证明所提出的制导律能够导引多枚导弹在期望的攻击时间同时命中固定目标。

Terminal Guidance Design for Missile with Impact Time Constraint Based on Time-to-go Estimation

According to the requirements of some types of missile which attack target with terminal desired impact time at the terminal point,a new guidance law with terminal constraint of impact time is presented.The proposed guidance law is obtained as the solution of a linear optimal control method.The solution is the combination of the PNG law and the feedback of the impact time error,it is different between the designated impact times by PNG.Time-to-go estimation method is proposed for implementation of the proposed law.The proposed guidance law is practicality.Numerical simulation results demonstrate that the proposed guidance law can guide multiple missiles to hit a stationary target with desired impact time simultaneously.