Simulation analysis and tests of rotating damper for spacecraft deployment mechanism
WANG Jiadeng1,2, LIU Chong3, XUE Jingsai1,2, DENG Zehua1,2, YANG Mingbo1,2, LIU Xingtian1,2
1. Space Mechanical-Thermal Integrative Technology Lab, Shanghai Institute of Satellite Engineering, Shanghai 201109, China;
2. Shanghai Engineering Technology Research Center for Aerospace Equipment Micro-vibration Environment Simulation, Shanghai 201109, China;
3. Shanghai Composite Material Technology Co., Ltd., Shanghai 201112, China
Abstract：With the increasing demand for the driving torque of large antennas of spacecraft, the problem of shock load control when the antenna is deployed in place has gradually attracted the attention of the engineering community. This paper introduces a large-stroke, large-damping rotational damper for spacecraft deployment mechanism, which can effectively suppress the impact load when the deployment mechanism is deployed. Firstly, the working principle of the rotary damper is briefly introduced, the mechanical model of the rotary damper is established, and the damping characteristics of the rotary damper are analyzed. Then, MSC.ADAMS software was used to simulate the dynamic numerical simulation of the expansion process of the antenna from the closed state to the fully expanded state, and the influence of the rotating damper on the unfolding speed and the locking impact force when it was deployed in place was analyzed. Finally, the damping performance test platform of the rotary damper was built and the damping performance test was carried out. The results show that the error between the simulated value of damping torque and the experimental value is within 2%, and the amplitude of the locking shock load decreases by 91% when the antenna is deployed in place after the rotating damper is installed, and the unfolding speed at the end of the deployment decreases by 81%, which verifies the effectiveness of the rotating damper for impact load control.
王嘉登1，2，刘冲3，薛景赛1，2，邓泽华1，2，杨铭波1，2，刘兴天1，2. 航天器展开机构转动阻尼器仿真分析与实验研究[J]. 振动与冲击, 2023, 42(13): 310-315.
WANG Jiadeng1,2, LIU Chong3, XUE Jingsai1,2, DENG Zehua1,2, YANG Mingbo1,2, LIU Xingtian1,2. Simulation analysis and tests of rotating damper for spacecraft deployment mechanism. JOURNAL OF VIBRATION AND SHOCK, 2023, 42(13): 310-315.
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