Dynamic Optimal Simulation and Analysis of the Load Chassis of Fly-Around Satellite

Abstract

The load chassis is the main component of the installation of fly-around satellite and repressurization system of spacecraft. Its stiffness and strength take the important role for the normal work of the fly-around satellite and repressurization system of spacecraft. The initial design is not good in the mechanical performance test of the chassis. Based on the existing structure, several optimization designs for the dynamic performance are proposed, The final design scheme is determined by comparing the results of finite element analysis and operability, which was verified through the product test and the whole spacecraft vibration test. The fundamental frequency of the structure is increased by nearly 8 Hz, Although the response value does not decrease largely. The successful launch of the spacecraft and the satisfactory shooting of the fly-around satellite indicate that the optimization design of the loading chassis is correct and reasonable. The optimization design method also provides experience for other spacecraft structure design.