摘要
将发射瞬时所确定的平行接近弹道作为基准弹道,由于各种干拢所引起的相对于基准弹道的偏离作为偏差来处理;用最优控制理论导出空-空导弹进行全向攻击的最优制导律,此制导律包含目标加速度反馈。当目标作非机动飞行时,最优制导律是一种变比例系数的比例制导。数字仿真结果表明:在相同条件下,最优制导弹道需用过载、终端脱靶量均小于比例制导,特别是从目标前方攻击时,其制导精度大大优于比例制导。
A missile flight path of parallel approaching method decided by launching parameters is used as a reference trajectory and the change produced by all kinds of disturbance is treated as deviation. An optimal guidance law of air-to-air missiles attacking in all-direction is obtained by the theory of optimal control. The loop of missile control systems includes the feed back of maneuvering acceleration of target. When targets fly with non-maneuvering, the optimal guidance law is the proportional guidance law with a changeable factor. The numerical computation confirms that the load-factor needed and the terminal error are much smaller than that produced by initial conditions and the same target. Especially when a missile attacks a target in the front of it, the guidance precision is much higher than that of the other guidance law.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1991年第3期A119-A127,共9页
Acta Aeronautica et Astronautica Sinica
关键词
空对空导弹
制导
机动目标
attacking in all-directional, maneuvering target, optimal guidance law.
