某卫星整流罩分离仿真分析

Simulation Analysis of Separation for Some Satellite Fairing

基于多体动力学用MSC/Adams软件建立了卫星整流罩分离模型。仿真获得了卫星整流罩分离角速度、旋转角和旋转铰链力载荷;分析了不同弹射筒峰值压力和不同铰链构型的分离。结果发现:铰链构型对卫星整流罩两半罩分离脱钩角的影响较大,而峰值压力几无作用。另发现,若适当加大弹簧推力器蓄能,可在运载火箭关机时用轴向过载的骤降效应实现卫星整流罩分离,提高卫星整流罩分离可靠性。

The model of the fairing separated from the rocket was established using MSC/Adams software based on multi-body dynamics in this paper.The profile of angular velocity,rotate angle and force on the hinge were gotten through the simulation,and the separations with different pressure of the ejection ram and different structure of the hinge were discussed.The results showed that the structure of the hinge had a greater impact on the separation angle of the two fairings,and the influence of the maximum pressure of the ejection ram could be ignored.It was also found that if the energy of the spring was increased,the axial overloading would be used to separate the faring when the engine was cut down,which increasing the reliability of the separation course.