针对某型直升机载导弹方案设计阶段续航发动机点火时间的确定问题,搭建优化模型,考虑弹体稳定性及飞行时间约束,对其续航发动机点火时间进行优化,使导弹进入末制导段时可用机动过载最大。优化结果表明,Hooke-Jeeves、ASA两种优化算法得到的结果基本一致,在保证导弹稳定性及飞行时间约束下,将续航发动机点火时间优化至30.1 s左右,使导弹进入末制导时速度增大4.3%,增大了导弹末端的机动过载。

In order to maximize the available maneuvering overload when the missile enters the terminal phase, for a certain type of helicopter-borne missile, this paper builts a model to optimize the ignition time of its sustainer, considering the stability of the missile and the constraints of flight time. The results show that Hooke-Jeeves and ASA have reached a similar conclusion: the ignition time of sustainer is optimized to 30.1 s, ensuring the stability of the missile and the constraints of flight time, which increases the speed by 4.3% when the missile enters the terminal phase, thereby increasing the maneuvering overload in the terminal phase.