Abstract: Considering the difficulty in comprehensively simulating the complex and changeable thermal environment of the Martian surface with a thermal balance test，a thermal balance test method based on the correlation verification of the thermal model is established.In addition，vacuum，low-pressure variable-temperature natural convection and low-pressure constant-temperature forced convection are combined to verify the convection，heat conduction，radiation network coefficient and thermal capacity of the analysis model under high- and low-temperature conditions，and the correctness of the design is verified using the thermal analysis model after correlation verification.The results show that the natural convection heat transfer coefficient under the condition that the plate temperature is 11.86℃ higher than the air temperature（-91℃） was 0.19-0.57W/（m²·K），and the forced convection heat transfer coefficient under the wind speed of 4.15m/s is 1.24-2.4W/（m²·K）.The deviation between the modified thermal analysis model and the test results is within ±3.5℃.This method realizes the thermal design verification of spacecraft under incompletely simulating the thermal environment，provides an effective thermal analysis model，and has been successfully applied to the thermal balance test of the Zhu Rong Mars rover.

Key words: Martian surface, thermal test, thermal model, convective heat