为了减小某顺序离轨导弹的初始扰动,根据拉格朗日方程和赫兹接触理论,基于虚拟样机技术,建立了某型导弹顺序离轨的弹-架系统动力学模型。综合考虑弹轨间隙、推力偏心角、推力偏心距、质量偏心、初始加速度冲击、定位块位置尺寸等因素,对动力学模型进行参数化设计,对导弹离轨姿态的影响进行了数值计算分析。结果表明,以上因素控制在合理范围内可有效减小初始扰动。弹轨间隙上下、左右应控制在0.4~0.6mm和0.4~0.8mm之间;发动机推力偏心和质量偏心越小越好;初始加速度冲击对导弹姿态扰动较小;定位块位置尺寸对导弹姿态角有影响。

In order to reduce the initial disturbance of a missile which leave the rail sequence, based on Lagrange equation, Hertz contact theory and virtual prototyping technology, a dynamic model of a missile system which leave the rail sequence is established. Considering the factors such as clearance, thrust misalignment angle, thrust misalignment distance, mass eccentricity, initial acceleration impact, position and size of positioning block, the parametric design of the dynamic model and the numerical analysis of the influence of the missile's attitude are carried out. The results show that the initial disturbance can be effectively reduced by controlling the above factors within a reasonable range, the clearance should be controlled between 0.4~0.6mm, 0.4~0.8mm; the smaller the thrust eccentricity of the engine and mass eccentricity of the missile, the better; the initial acceleration impact has less disturbance to the attitude of the missile; the position and size of positioning block has influence on the attitude angle of the missile.