基 于 最 优 误 差 动 力 学 的 变 速 导 弹 飞 行 路 程控 制 制 导 律

To solve the problem of performance degradation of current impact time control guidance based on con⁃ stant speed assumption in practical application，a feasible flying range control guidance scheme with time-varying speed is proposed in this paper. The relative motion equation of the missile against the stationary target in the arc-length domain is derived based on the classical differential geometric curve principle，which reduces the influence of time-varying speed on the relative motion of missile and target. Furthermore，the exact solution for the range-to-go guided by pure proportional navigation is derived using the Gaussian hypergeometric function. On this basis，a flying range control guidance law is designed with the optimal error dynamics method，and the effectiveness of the proposed guidance is verified by simulation.