带时间控制的落角约束制导律

Guidance law with time control and falling angle constraints

针对多弹饱和协同攻击的任务场景,为满足时间控制和落角约束要求,提出了一种基于改进比例导引法的时间落角控制制导律。通过哈密顿原理求解最优控制问题得到落角控制项,利用小前置角假设得到预估剩余飞行时间的解析表达式,引入最佳误差动态使时间控制误差快速收敛,构造带有可调整时间控制增益系数的时间控制项。通过数值仿真模拟了单弹攻击以及多弹协同作战场景。仿真结果表明,增大时间控制增益系数能够提升时间误差收敛速度,但会增加控制资源消耗;与现有时间落角控制制导律相比,所提出的方法有效提升了命中位置、落角和时间控制的精度,能够满足不同约束条件下的导弹命中时间和落角控制要求。

In order to meet the requirements of time control and falling angle constraint,a time falling angle control guidance law based on the improved proportional guidance method is proposed for the mission scenario of multiple missile salvo attack.The falling angle control term is derived by solving the optimal control problem based on Hamilton's principle,and an analytical expression for predicting the time-to-go estimation is obtained by using the small leading angle hypothesis.An optimal error dynamics is introduced to expedite convergence of time control error,and a time control term with adjustable time control gain coefficient is constructed.Simulation results demonstrate that increasing the time control gain coefficient can improve convergence speed of time error,but also increase the consumption of control resources.Compared with existing time falling angle control guidance laws,this proposed method can effectively improve the accuracy in hit position,falling angle and time control to achieve missile hit time and falling angle under different constraints.