基于数据驱动的攻击时间和攻击角度控制导引律

为了提高导弹突防能力并有效打击目标, 对同时实现攻击时间和攻击角度控制的导引律进行了研究。基于一种以数据驱动为核心的方法, 将导引过程分为第一阶段攻击时间控制和第二阶段攻击角度控制。根据攻击角度控制导引律生成驱动数据, 采用人工神经网络技术建立了剩余飞行时间映射网络, 据此求得攻击时间控制阶段的攻击时间误差。基于比例导引法, 利用攻击时间误差设计出攻击时间控制导引律, 从而使导弹同时实现攻击时间和攻击角度控制。仿真结果表明, 所提出的导引律在不同条件下均能有效实现攻击时间和攻击角度控制, 与现有文献相比, 最大过载减少约43%, 需用控制总能量减少约46%。

Data-driven method based impact time and impact angle control guidance law

In order to improve the penetration ability of missile and attack the target effectively, the guidance law realizing the control of both impact time and impact angle is studied. Based on a data-driven method, the guidance process is divided into the first stage of impact time control and the second stage of impact angle control. The driving data is generated according to the guidance law of impact angle control, and the mapping network of time to go is established by using artificial neural network technology to obtain the error of impact time in the impact time control stage. Based on the proportional guidance method, the impact time control guidance law is designed with the error of impact time, so that the missile can control the impact time and the impact angle simultaneously. The simulation results show that the proposed guidance law can effectively control the impact time and impact angle under different conditions. Compared with existing literature, the maximum overload is reduced by about 43%, and the total control energy required is reduced by about 46%.