基于捷联导引头的比例导引制导律设计

Strapdown Seeker Based PN Guidance Law Design

捷联导引头不能直接测量视线角速率信号,进而无法直接利用比例导引进行制导。采取两级发动机助推模式并结合坐标变换得到比例导引所需的惯性视线角速度来进行制导。建立带重力补偿的战术导弹数学模型,两级发动机分别给予不同的约束。通过坐标变换将能够直接测量到的弹体视线角以及姿态信息转换成惯性视线角速度信号。仿真结果验证,通过该方法实现捷联方式下的比例导引是可行的。

Strapdown seeker cannot directly measure the inertial line-of-sight（LOS） rate,such that proportional guidance is not able to be used directly to control the missile.A method using two-stage engine based on coordinate transformation was applied to obtain the inertial LOS rate required by precise proportional guidance.Gravity compensation signal was introduced into the proportional guidance system to establish the tactical missile mathematical model,and two-stage engine was endowed the different constraints respectively.Then the directly obtained line-of-view angle on body combined with the measured attitude information was converted to the inertial LOS rate for proportional guidance system utilizing coordinate transformation formulas.The feasibility of the proposed approach for strapdown seeker based proportional guidance system was validated through practical simulation analysis.