Abstract:A key device inside a spacecraft has high power density, fast heating rate, lacks heat dissipation channels, and is prone to overheating. Considering factors such as spatial layout and economic cost comprehensively, phase change heat storage technology is one of the heat dissipation solutions with the lowest cost and the weakest overall impact. In view of the thermal design characteristics of a certain over-temperature equipment on spacecraft, the surrounding structural layout and other factors, a thermal design scheme based on phase change heat storage measures is presented. Using finite element numerical analysis methods, thermal balance equations and thermal analysis computational models were established. The transient simulation analysis was carried out under the given temperature boundary conditions using the thermal analysis software NX/TMG. The relevant parameters were optimized, and the thermal response performance of the components was presented. Subsequently, based on actual equipment thermal characteristic parameters, thermal simulation components and phase change thermal storage modules were designed and manufactured. Based on this, the construction of the test platform and the ground principle test are completed. The test and simulation results are in good agreement. After adopting the phase change heat storage device, the requirement that the continuous working temperature of the equipment does not exceed 45℃ for the 2000s can be met, and the influence of convective heat transfer on the test results can be ignored.
