针对反坦克导弹近距离顶攻存在的弹道落角不足问题,分析了在弹道初始段加入推力矢量控制对飞行弹道的影响,并对气动力/推力矢量控制的近距离顶攻飞行弹道进行分析,设计了一种基于弹目视线角速度和弹目视线角的制导律,保证在全射程内的落角要求。仿真结果表明,所提出的制导律充分利用了推力矢量特性,提高了导弹的机动性能,在导弹的全射程内都能保证较大的落角,是一种可行的方案。

Aiming at deficiency of impact angle in short range attack of an anti tank missile, the influence of adding thrust vector control in the initial phase of trajectory and short range top attack trajectory controlled by aerodynamic and thrust vector were analyzed. In this paper, a new guidance law based on line of sight angle and the line of sight angle rate was designed, which guarantees to meet the impact angle requirements in all range trajectory. The simulation results show that the guidance law proposed makes full use of thrust vector’s characteristic, improves the dynamic of missile, and guarantees high impact angle of the missile in all trajectory. It is a feasible method.