寻的制导旋转导弹比例导引

导弹的旋转会引起俯仰和偏航通道的交叉耦合作用,因此旋转导弹比例导引参数设计不当将引起弹体以锥形运动形式发散,导致脱靶量增大。针对一种寻的制导的单通道控制旋转导弹,推导了包含耦合作用的制导、控制和动力学方程,分析了比例导引视线角速度收敛条件、最优导航比以及导引关系对脱靶量的影响。指出在旋转条件下,导引头相位延迟导致更大的比例导引系数才能使得视线角速度收敛,同时最优导航比增大。视线角速度提前发散使得弹体成锥摆状态飞行,进而导致脱靶量增大。案例数值仿真表明,随着转速增加,脱靶量呈指数形式增大,因此,必须限制最大转速,并根据转速选择合理的导航比。

Proportional Navigation of Homing Spinning Missiles

The irrelevant parameters of proportional navigation(PN)for spinning missiles may result in a divergent coning motion due to the cross-coupling between the pitch and yaw induced by spinning,which can cause large miss distance. Aiming at homing spinning missile guided by one pair of control fins,the guidance equations,control equations and dynamics equations were derived,which included cross-coupling elements. The convergence condition of angular rate of line of sight(LOS)was analyzed,as well as the optimal navigation ratio and the effect on miss distance. The phase-delay of the seeker leads to a larger navigation ratio for angular rate of LOS convergence,and the optimal navigation ratio increases at the same time. The missiles fly in form of coning motion with the divergent angular rate of LOS,and a large miss distance generates. Numerical simulation of a case shows that the miss distance increases exponentially with the increase of the spinning rate. The upper limit of spinning rate and navigation ratio should be designed in justified range.