Abstract: Based on the analysis of the space heat environment, the received heat flux and its angle factor of the solar array are calculated. The time points when the spacecraft enters and leaves the Earth’s shadow in orbit are calculated under the LEO and GEO conditions, respectively. The finite element analysis model is built for the solar array components such as the yoke, the panels and the hinge based on the simplified model of the spacecraft solar array. The periodic variation of the heat flux on the solar array is analyzed under different orbit conditions.