基于脉冲发动机特性的多弹协同制导律设计  

Design of Multi-Missile Cooperative Guidance Law Based on Pulse Engine Characteristics

作　　者：潘辉[1] 张振林 郭超 Pan Hui;Zhang Zhenlin;Guo Chao(China Airborne Missile Academy,Luoyang 471009,China;School of Astronautics,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]中国空空导弹研究院,河南洛阳471009 [2]西北工业大学航天学院,西安710072

出　　处：《航空兵器》2022年第1期41-46,共6页Aero Weaponry

摘　　要：针对攻击高速目标的多弹协同制导律设计问题,提出一种基于脉冲发动机工作特性的多弹协同制导律设计方法。首先,求解视线系下的弹-目相对运动方程;其次,在视线方向上采用有限时间一致性理论进行协同制导律设计,视线法向采用滑模变结构控制理论进行视线角度约束制导律设计;然后,对于视线方向上过载指令,考虑脉冲发动机工作特性,将视线系下的连续制导指令转换为离散制导指令,进而实现多弹协同制导;最后,通过数值仿真验证了所设计协同制导律的可行性和有效性。Aiming at the design problem of multi-missile cooperative guidance law for attacking high-speed targets,a design method of multi-missile cooperative guidance law based on the working characteristics of pulse engine is proposed.Firstly,the relative motion equation of missile and target is solved.Secondly,the finite-time consistency theory is used to design the cooperative guidance law in the line-of-sight direction,and the sliding mode variable structure control theory is used to design the line-of-sight angle constrained guidance law in the line-of-sight normal direction.Then,for the overload command in the line-of-sight direction,considering the working characteristics of the pulse engine,the continuous guidance command in the line-of-sight system is transformed into discrete guidance command,and then the multi-missile cooperative guidance is realized.Finally,the feasibility and effectiveness of the designed multi-missile cooperative guidance law are verified by numerical simulation.

关 键 词：协同制导 一致性理论 角度约束 脉冲发动机特性 滑模变结构控制 离散制导 导弹 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程] V249.1[航空宇航科学与技术—飞行器设计]