Abstract: Taking the independently developed repeatedly deployable solar array of lunar rover as the research object, the influence of the extreme temperature of the lunar surface on the reliability of the end position of the deployed solar array is analyzed. The relationship function between the extreme temperature and solar array materials and hinge structure is constructed. Based on the kinetic elastic dynamics, the gap flexible coupling dynamic model under extreme temperature is established. Taking the end position error of the solar array as the evaluation index, combining the BP neural network algorithm with the first order second moment method, the stress strength theory is used to establish the reliability model of the end position of the solar array. The calculation of the classical MC method is compared and verified to determine the feasibility and efficiency of the neural network method. The results show that under the extreme temperature conditions, the hinge clearance has a significant effect on the position reliability. Within the temperature range of -30-20 ℃, the reliability of the end position of the deployed mechanism is optimal.

Key words: Deployable solar array, Extreme temperature, Gap flexible coupling model, End position reliability