Structural Design and Dynamic Analysis of Microsatellite

This paper focuses on the structural design and mechanical environment test of a micro-satellite carried on a large satellite. Firstly, the structure of the micro-satellite is designed according to the requirements, and the finite element model is established for preliminary analysis, and the fundamental frequency of the satellite is obtained. Secondly, the design and implementation of simulation mechanical environment test prove the reliability of satellite structure design during launch process. The test results show that the fundamental frequency of satellite is 35.2 Hz, which is 6% different from the simulation analysis results. Meanwhile, the response of satellite in subsystem test is much larger than that in coupled system test, which indicates that the design method for mechanical environment experimental conditions still needs improvement.