弹道式飞行器再入攻角引起的落点误差分析

ANALYSES OF REENTRY VEHICLE DISPERSION FROM INITIAL ATTACK ANGLE

由于干扰因素的影响,飞行器再入时会产生±5°的初始攻角,这种攻角产生的升力不仅随攻角的收敛而变小,而且随飞行器的自旋而改变方向,从而使飞行器沿螺旋状弹道再入,最终造成落点误差,文中将转子动力学理论用于旋转飞行器的再入运动分析,通过对进动角与升力的耦合计算,得出了飞行器的平均落点误差,并以算例进行了验证,最后,给出了若干重要结论。

The Reentry vehicle can produce initial attack of angle that is about ± 5 ° when the Reentry vehicle separates from the body due to disturbances. The lift from the angle not only gets little when the angle convergence, but also makes the Reentry vehicle reentry in spiral ballistic. This results in impact point errors finally. This thesis makes use of rotor dynamic theory in reentry movement analyses to spiral Reentry vehicle. The dispersion means are obtained by the computation of the coupling about rotation and lift, and these also are illustrated through an example. Several important conclusions are presented at last.