基于ADAMS的减振系统仿真

Simulation of A Vibration Isolation System Based on ADAMS

采用减振方式减小运载火箭在发射状态对空间飞行器产生的过载是一种理想形式,但通常减振设计必须进行详细计算与实际验证,周期长,准确性差,费用高。因此,文中提出了一种新的采用减振措施来减小发射段振动的影响的方法;又采用虚拟样机技术,利用ADAMS动力学仿真软件对其横向振动特性进行了仿真研究,表明该方法可以有效的减小发射状态下的过载对空间飞行器的影响;并提出用ADAMS软件建模对该系统进行参数优化设计的具体方法。同时表明,用ADAMS软件建立减振系统三维实体模型进行仿真设计,具有速度快、分析方便、便于实施和结果准确等特点,是理想的一种设计方法。

During launch, launch vehicles impart high loads into sensitive components of spacecraft. Each component and subsystem of spacecraft must be designed to withstand these launch loads. To make components strong enough to withstand these loads requires additional weight, which increases costs and reduces overall performance. A better option is to reduce the magnitude of the vibrations into the sensitive components by carefully designing the structure of the launch vehicle adapter. In this paper, to solve the problem, an isolation mount of the launch vehicle adapter is designed such that the launch vibrations into sensitive components are minimized over a defined frequency range. The simulation results show that the model leads to satisfactory vibration isolation performance. In addition, some simple modified designs are utilized to further improve the vibration isolation performance of the system.