拦截不同机动目标的最优制导律设计与仿真  

Design and simulation of optimal guidance law for intercepting different maneuvering targets

作　　者：张欧 肖沿海 陆海英 ZHANG Ou;XIAO Yanhai;LU Haiying(Jiangnan Design&Research Institute of Machinery&Electricity,Guiyang 550009,China)

机构地区：[1]江南机电设计研究所,贵阳550009

出　　处：《航天控制》2025年第1期54-61,共8页Aerospace Control

摘　　要：针对防空导弹迎击拦截不同方式的机动目标,基于最优控制方法提出了一种控制量权重可变的制导律。建立了纵向平面弹目相对运动的状态方程,设计了控制量权重可变和带视线角速度约束的指标函数,利用极小值原理数值推导了带有权重系数的最优制导律。针对不同方式的机动目标开展了仿真试验,结果表明本文所提出的最优导引方法的性能优于传统比例导引,视线角速度收敛较快,能够较好地形成逆轨态势;此外,针对机动方式不同的目标,可以通过调整最优导引律的权重,匹配到各机动目标的最优控制参数。A guidance law with variable control weight is proposed,which is based on the optimal con⁃trol method for intercept different types of maneuvering targets by using air-defense missile.A state equa⁃tion of relative motion between missile and target in the longitudinal plane is set up,and an indicator function based on variable control weight and line of sight angular velocity constraint is designed,further⁃more,the optimal guidance law related to weight coefficients is derived by using the minimum numerical principle.Simulation experiments are implemented for different types of maneuvering targets,and the results indicate that the performance of the optimal guidance approach proposed in this paper is superior to traditional proportional guidance method.The line-of-sight angular velocity convergence is fairly quick,which can form preferable reverse orbit situation.Furthermore,regarding targets under different maneuvering modes,the weight of the optimal guidance law can be adjusted to match the optimal control parameters of each maneuvering target.

关 键 词：防空导弹 机动目标 极小值原理 最优导引律 可变权重 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程]