Equivalent simulation test method of engine plume thermal environment in aerobic environment

Abstract The deep space probe is generally composed of the lander and the lander. During the take-off and landing of the extraterrestrial body, the engine jet flows through the top surface of the lander or the surface of the extraterrestrial body to reflect on the bottom surface of the lander, which will produce strong aerodynamic and thermal effects in a small space, thus affecting the stability and surface thermal protection of the lander. The plume heat effect refers to the impact of the flyover engine gas flow movement or heat radiation on the lander surface on the flyover bottom, tank, lander top surface, buffer mechanism, and key equipment. This paper calculates from the probe plume thermal environment equivalent simulation method, and heat flow simulation loading system design until the test verifies that the affected product surface temperature rises. It can provide necessary technical support for the selection of thermal control protection materials (conventional thermal control, flexible thermal protection materials, high-temperature thermal protection materials).