火星表面热环境对航天器热控影响分析

火星大气对太阳辐射产生吸收和散射作用,同时还将与火星表面航天器发生对流换热.热设计时难以直接评估对流、辐射和导热三种换热对航天器的影响,从而确定主要的控温途径.在调研火星表面辐射、大气等热环境的基础上,从线性化传热系数和对流辐射比的角度对比分析了辐射、对流和导热对航天器的影响.器表辐射传热系数随光学属性和温度的变化范围...

Analysis of the influence of Mars surface thermal environment on spacecraft thermal control

For the Mars surface exploration, the Martian atmosphere absorbs and scatters the incident solar radiation, while causing convective heat transfer between itself and the spacecraft on the surface of Mars. In the thermal design, it is difficult to directly assess the impact of the three heat transfer types (convection, radiation and heat conduction) on the spacecraft and determine the main transmission ways. Based on the investigation into the thermal environment such as Mars surface radiation and the atmosphere, the effects of radiation, convection and heat conduction on the spacecraft were compared and analyzed from the perspective of linearized heat transfer coefficient and convection-radiation ratio. The radiation heat transfer coefficient of the spacecraft surface varies with optical properties and temperature in the range of 0.3W/(m²·℃) to 1.4W/(m²·℃), and the convective heat transfer coefficient varies with the wind speed from 0.2W/(m²·℃) to 1.5W/(m²·℃). The conduction heat transfer coefficient can be controlled below 0.25W/(m²·℃). The results show that solar radiation is the main external heat source compared to Mars surface and sky radiation. Radiation and convective heat transfer on the surface of the spacecraft are two parallel transmission paths, both of which may become the main path. The heat conduction in the spacecraft is the main controllable factor of its thermal control.