反舰导弹大前置角下三维剩余飞行时间估计方法  

Time-to-go Estimation Method for Anti-ship Missiles with Large Lead Angle in Three-dimensional Space

作　　者：吴浩 李东光 王泳安[1] WU Hao;LI Dongguang;WANG Yong an(School of Mechanical and Electrical Engineering,Central North University,Taiyuan 030051,Shanxi,China;School of Mechanical and Electrical Engineering,Beijing Institute of Technology,Beijing 100081,China)

机构地区：[1]中北大学机电工程学院,山西太原030051 [2]北京理工大学机电学院,北京100081

出　　处：《兵工学报》2024年第5期1449-1459,共11页Acta Armamentarii

摘　　要：为解决导弹开启末制导时初始前置角过大或前置角变化幅度较大的问题,设计适用于多种导弹制导律的前置角三维剩余飞行时间估计方法。将导弹速度和目标速度投影分解,在地面坐标系的Oxy面和Oxz面上建立弹目相对运动关系方程,以此为基础建立三维弹目相对运动模型。利用弹目相对运动关系方程和比例导引控制方程,建立1阶非线性微分方程,解析弹目距离与前置角的关系,并利用麦克劳林展开式求解方程。根据视线角速度变化选择合适的内框角,对前置角进行补偿,同时使用中位值平均滤波法降低前置角波动造成的误差。利用已建立的三维弹目相对运动模型进行仿真实验。仿真结果表明,在小角度假设不能成立时,尤其是因制导律进行角度控制而导致前置角变化较大时,前置角剩余飞行时间(Time-to-go,TGO)估计方法的估计值误差收敛时间和最大误差值要小于其他TGO估计方法,估计效果最佳。To solve the problem of large initial lead angle or significant change in lead angle when missile terminal guidance starts,a 3D time-to-go(TGO)estimation method for lead angle is designed for various missile guidance laws.The missile velocity and target velocity projections are decomposed to establish the relationship equations of relative motion between missile and target on Oxy and Oxz surfaces of ground coordinate system.Based on this,a three-dimensional missile-target relative motion model is established.A first-order nonlinear differential equation is established by using the relative motion equation and proportional navigation control equation of missile and target.The relationship between missile-target distance and lead angle is analyzed.The first-order nonlinear differential equation is solved by using McLaughlin formula.An appropriate inner frame angle is selected based on the change in line-of-sight angular velocity to compensate for the lead angle,and the median average filtering method is used to reduce the error caused by the fluctuation of lead angle.The simulation experiments are conducted by using the proposed three-dimensional missile-target relative motion model.The simulated results show that,when the small angle assumption cannot be established,especially when the angle control of guidance law results in significant changes in the lead angle,the convergence time and maximum error value of estimated error of the lead angle TGO estimation method are smaller than those of other TGO estimation methods.

关 键 词：反舰导弹 前置角 制导律 剩余飞行时间估计 机动目标 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程] TJ761.7