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。 Due to interference factors, the aircraft reentry will produce an initial angle of attack of ± 5 °, the angle of attack generated by the lift not only decreases with the angle of attack convergence, and with the aircraft’s spin and change direction, so that the aircraft The trajectory reentry along the helical trajectory will eventually lead to the landing error. In this paper, the rotor dynamics theory is applied to the reentry movement analysis of the rotary vehicle. Through the coupled calculation of the precession angle and lift, the average landing error of the aircraft is obtained, Finally, some important conclusions are given.