多弹协同最优制导律研究  

Research on the Optimal Guidance Law for Cooperative Attack of Multiple Missiles

作　　者：邓海鹏 刘梦焱 马季容 栗金平 DENG Hai-peng;LIU Meng-yan;MA Ji-rong;LI Jin-ping(Xi'an Institute of Modern Control Technology,Xi'an Shanxi 710065,China)

机构地区：[1]西安现代控制技术研究所,陕西西安710065

出　　处：《计算机仿真》2022年第12期23-27,共5页Computer Simulation

摘　　要：为了提高导弹突防及精确打击能力,针对攻击时间约束和攻击角度约束以及控制能量消耗最少的性能指标要求,提出一种多弹协同最优制导律。选取一枚导弹作为领弹,其余导弹为从弹,估计领弹剩余飞行时间,并将估计值传送给从弹,作为从弹的攻击时间约束;从弹根据攻击时间约束、理想的攻击角度约束,以及控制能量最省的指标要求,应用最优控制原理解算出最优飞行轨迹;应用设计好的最优轨迹控制各从弹飞向目标。通过matlab中的simulink进行了仿真,结果证明,所有导弹都能精确地按照给定的攻击时间和攻击角度击中目标。To enhance the penetration ability and target-hitting capacity, and in order to meet the requirements of attack time, attack angle, and lower energy consumption constraints, an optimal guidance law for the cooperative attack of multiple missiles was proposed. First, one of the missiles was regarded as the leader, and the others were followers. The time to go of the leader was estimated and was sent to the followers as an attack time constraint. Then, according to the constraints of attack time, attack angle, and lower energy consumption, the guidance law of the followers was got using the theory of optimal control. Finally, each follower flew to the target in the light of the optimal guidance law. The Simulation results show that adopting the proposed method can realize the cooperation of position, impact angle, and impact time effectively when multiple-missiles combat cooperatively.

关 键 词：多弹协同攻击 最优控制 剩余飞行时间 饱和攻击 

分 类 号：TJ765.4[兵器科学与技术—武器系统与运用工程]