SIMULATION OF THE INITIAL DEPLOYMENT KINETICS OF A SPACECRAFT SOLAR-ARRAY

This paper presents a mathematical simulation of the initial deploymen t kinetics of a spacecraft solar array panel stack and its primary dep loyment mechanism. Two methods for achieving initial deployment are co nsidered. The first deployment method involves the motorized deploymen t of a single hinge. The second deployment method involves the spring actuated deployment of two hinges. In the motorized deployment case, t he solar array is predicted to slide against the spacecraft sidewall b efore separation. In the spring actuated deployment case, the solar ar ray is predicted to separate from the spacecraft sidewall without slid ing.