Design and parameter optimization of the box-panel satellite primary load-bearing structure

Abstract

To meet the demand for the rapid development of commercial satellites, we introduce parameter optimization technology in the early design phase of the satellites to establish an optimization design scheme, where the thickness of the primary load-bearing cabin panel skin and honeycomb core are defined as design variables, satellite stiffness and skin strength as constraints, and the minimum total mass of the satellite as the objective function, and revise the design parameters according to the manufacturing constraints. Optimized satellite mass is 129 kg, with only a 1 kg increase compared to the previous optimization. The fundamental frequency has increased by approximately 19%, reaching 63.41 Hz. The skin strength has decreased by about 30%, to 156 MPa. The optimization results meet the launch requirements and have successfully passed tests and flight verification. This scheme can effectively improve the design efficiency of the satellite’s main load-bearing structure, providing a reference for the rapid development of commercial box-type satellites.