目标机动对扩展弹道成型制导系统脱靶量影响分析

Analysis of miss distance due to target maneuver for extended trajectory shaping guidance systems

构造了基于剩余飞行时间指数函数的扩展目标罚函数,给出了对常值机动目标最优的扩展弹道成型制导律簇。利用无量纲化方法和伴随技术,研究了含有一阶动力学滞后的制导系统在目标常值机动、随机机动和终端落角约束作用下的无量纲位置和角度脱靶量随无量纲末导时间变化特性。采用直接法对伴随法仿真结果进行了验证。研究结果表明,当末导时间分别为制导系统动力学滞后时间常数的15倍、20倍左右时,落角约束和目标常值机动引起的位置和角度脱靶量均趋近于零;随着指数n的增大,导航系数也越大,无量纲位置和角度脱靶量振荡加剧,收敛时间也加长。目标随机机动引起的位置和角度脱靶量随着末导时间的增大维持在某个稳定的值,并不趋近于零,而且指数n越大,其脱靶量的稳定值也越大。

The extended object cost function was proposed based on the time-to-go exponential function and for constant target maneuver, a family of extended optimal trajectory shaping guidance law was deduced. The missile non-dimensional position and angle miss distance vs non-dimensional terminal guidance time was studied using the non-dimensional method and adjoint technique when the constant/random maneuver target was introduced into the one single lag system. The adjoint simulation results were validated by the direct simulation results. The results show that the position and angle miss distance produced by the final impact angle approaches to zero when the missile terminal guidance time is about 15 times of the system lag time while the constant target maneuver is about 20 times. If the exponential number n and the system navigation ratio increase, the non-dimensional position and angle miss distance is oscillatory more worse and the convergence time of the miss distance is larger than before. With the increasing of the terminal guidance time, the position and angle miss distance of the random target maneuver approaches to a stable value but not near zero and also, the miss of which is larger when the exponential number n increases.