Abstract：Here, aiming at influences of flexible effect on separation process of a satellite cabin shell, a rigid-flexible coupled dynamic model for horizontal throwing separation of a composite satellite cabin shell was established based on the flexible multi-body dynamic method. The thrust-displacement relationship of a thruster was used to realize the thrust equivalence of the thruster from ground tests to arbitrary conditions. Simulation and contrastive analysis for the flexible body model and the rigid body model were performed. The results showed that elastic deformation of the shell is dominated by the second-order “breathing motion” mode to absorb about 15% of work done by the thruster, and the separation speed decreases; the respiratory motion at the lower corner point of the separation surface is the most severe, and the influence of the first time inward breathing movement of the half hood on the inner envelope is the greatest; the flexibility effect can also affect the thrust action time history of the thruster. Satellite cabin separation ground tests were conducted. A high-speed photography was used to measure the half hood’s motion to contrastively verify the correctness of the simulation method. It was shown that the simulation error is less than 13%; the study results are helpful to ensure the effectiveness of the separation scheme, release the design margin of the satellite cabin inner envelope space, and provide a reference for separation optimization design.
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GE Yue, WANG Hongbo, GONG Min, LUO Bo, ZHAO Junfeng, GAO Feng. Simulation and tests for horizontal throwing separation of satellite cabin shell based on rigid-flexible coupling. JOURNAL OF VIBRATION AND SHOCK, 2021, 40(7): 19-28.
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