Experiment research on heat-transfer capability of the multi-layer insulation blankets under different vacuum degrees

Abstract

The high-speed reentry capsule of lunar spacecraft will face a weak vacuum environment long-term on orbit, thus the difference of heat-transfer capability of the multi-layer insulation blankets under different vacuum degrees should be evaluated in thermal design. In this article, an one-dimensional method of mesurement with adiabatic boundary condition was constucted to test the heat tranfer performance of multi-layer insulation blankets with 5, 10, 15 and 20 under 0.001-10000 Pa. Based on the test data, equivalent thermal conductivities of different vacuum degrees were calculated. The proper equivalent thermal conductivity is selected in the entire spacecraft thermal analyses, and this method is proved to be correct through thermal balance test and on orbit temperature telemetry. This work achieves not only basic data for reentry capsule, but also important fundation of thermal design and thermal analyse with multi-layer insultaion blankets in different vacuum degree.