Lightweight design and analysis on thermal door of remote sensing satellite camera in low earth orbit

Remote sensing satellite in low earth orbit is a kind of spacecraft developed to meet the needs of high-resolution imaging observation, rapid response to emergency earth observation and disaster image monitoring. In this paper, a finite element model of a remote sensing satellite camera with a diameter of 800mm thermal protection door (thermal door for short) was established. The topological optimization design technology is used to design the thermal door structures with high-reliability, high-strength and ultra-light. After optimization, the weight of thermal door is 4.5Kg. The finite element simulation analysis is carried out on the thermal door, and the analysis results show that the thermal door meets the harsh mechanical conditions of a satellite platform. The mechanical test of thermal door was carried out, and the test results match the simulation analysis results. After the mechanical test, the thermal boundary and vacuum conditions in orbit were simulated in the thermal vacuum experiment tank, and the thermal door’s opening and closing tests were carried out. The thermal door’s opening/closing time, opening/closing speed, structural stability and positioning accuracy meet the index requirements. This thermal door has been developed and delivered to the satellite. The research results of this paper have a certain reference value for the design of thermal door for remote sensing satellite cameras with low power consumption and high temperature control requirements..