在建立尾翼式火箭被动控制器力学模型的基础上,导出了分析被动控制器发射过程的动力学方程,并对某火箭被动控制器进行了计算。计算结果表明,对这种尾翼式火箭弹,当被动控制器的支承点位于定向管重心处、定向管固有频率为5Hz,且火箭弹出管转角为0.567π弧度时,能减小推力偏心引起的弹道偏差80%左右。 Based on the establishment of the mechanical model of the passive rocket controller, the dynamic equations of the passive controller were derived and the passive rocket controller was calculated. The calculation results show that for such a tail-mounted rocket, when the support point of the passive controller is located at the center of gravity of the directional tube, the natural frequency of the directional tube is 5 Hz, and the rocket ejector angle is 0.567π radians, the eccentricity of the thrust can be reduced Ballistic deviation of about 80%.