Research on Mechanical and Thermal Design and Analysis of Quasi-2D Microsatellites

Quasi-2D microsatellites possess the characteristics of high launch efficiency, low development cost, and low-drag flight capability, and are suitable for future low earth orbit (LEO) and very low earth orbit (VLEO) space missions. In order to adapt to the stacked launch mode, the quasi-2D microsatellite adopts a new high-functional density design, which leads to a new mechanical and thermal environment problem. Taking the specific platelike configuration as an example, the structure and thermal control design of the quasi-2D microsatellite are firstly carried out, and the mechanical/thermal modeling and simulation of the satellite are carried out, and the fundamental frequency and temperature distribution characteristics of the structure are obtained, which provides a data reference for the subsequent design. Secondly, the satellite structure was rapidly developed through aerospace additive manufacturing, and the preliminary thermal design scheme of passive heat dissipation of high thermal conductivity silicone rubber sheet was adopted. Through thermal simulation modeling and physical testing, it has been proven that the new quasi-2D satellite has uniform transient heat distribution and controllable temperature during continuous operation. The new method meets the requirements of fast response and low cost of low-orbit missions, and provides a new solution for the efficient completion of future LEO and VLEO space missions.