对箱装导弹顺序离轨的3个阶段进行了受力分析,通过ADAMS动力学仿真软件对某导弹出箱离轨过程的运动姿态进行了仿真计算,并将计算结果与飞行试验数据进行了对比,发现导弹在飞行试验中出箱时刻俯仰方向离轨扰动与仿真计算结果基本一致,证明了该仿真模型的正确性。研究表明,通过动力学仿真计算导弹离轨时弹体的初始扰动结果可信,为导弹飞行性能分析提供一定的参考依据。

In this paper, the forces that act on the coffin-type launch of missile during its launch from orbit by order are analyzed by divided into three stages. The motion attitude of a missile out-of-orbit process is analyzed by ADAMS. Compared with the results of flight test, the velocity of pitch angle is consistent with each other at the time of departure from orbit. It is proved that the simulation model is reasonable. The results of the initial disturbance of the missile when it is out of orbit can be calculated by dynamic simulation, which provide significant reference for launching of missile.