采用运动伪装理论的冲压动力导弹制导律

Terminal Guidance Law for Scramjet Missile with Motion Camouflage Theory

在视线旋转坐标系内设计制导律是一种不通过双平面解耦处理三维制导问题的途径。针对高速机动目标的三维末制导拦截问题,基于运动伪装理论的运动伪装条件,在视线瞬时旋转坐标系内推导出一种适用于冲压动力导弹的运动伪装制导律。动力学仿真结果表明,与经典比例导引律相比,该制导律在考虑冲压动力导弹最大可用攻角、侧滑角及余气系数限制下,可以有效降低导引头的视线转速率及命中点需用过载,具有良好的制导特性。

Designing guidance law in the rotary line-of-sight frame is a way to avoid using decoupling method in dealing with 3 D guidance problem. Aiming at the 3 D guidance problem of maneuvering target interception,based on the condition of motion camouflage strategy,a motion camouflage strategy guidance law in the rotary line-of-sight frame is derived. The kinetic simulation results demonstrate that the motion camouflage strategy guidance law shows a good performance with the available attack angle,sideslip angle and excess coefficient of the ramjet missile compared with the pure navigation guidance. The seeker＇s rotary rate of line-of-sight and the required overload for the hit point are reduced,and it has good guidance characteristics.