某大型制导火箭弹发射动力学仿真与试验分析

Launching Dynamics Simulation and Test Analysis of a Large Guided Rocket

针对某大型制导火箭弹弹体初始扰动、发射安全性及弹架系统动态响应未知等问题,采用多体动力学方法和子结构模态综合法建立发射动力学刚柔耦合数学模型。利用动力学仿真软件求解耦合的非线性微分代数方程,获得了弹体初始扰动、质心下沉量、发射导轨动态响应等参数。仿真结果表明:弹体初始扰动符合设计要求,火箭弹质心下沉在指定范围内,可以安全发射。最后通过地面发射试验,对仿真结果进行了验证。

Aiming to the problems of initial disturbance, launch safety and dynamic response unknown of large guided rocket system, the rigid flexible coupling mathematical model of launch dynamics is established by using multi-body dynamics method and substructure mode synthesis method. By using the dynamic simulation software to solve the coupled nonlinear differential algebraic equation, the parameters of the initial disturbance of the rocket, the center of mass subsidence and dynamic response of the launching guide rail are obtained. The simulation results show that the initial disturbance of the rocket body conforms to the design requirements, the rocket′s center of mass subsidence within the specified range, and it can be launched safely, the simulation results are verified by the ground launch tests.