Abstract: On the basis of analysis of the deployment motion of satellite solar array, a whole satellite model was established by UG and was imported to MSC. ADAMS. Then, the deployment of solar array was simulated in ADAMS. A jointing structure consisting of revolute joints, torsion springs and closed cable loops was built in ADAMS/View. Moreover, the impacting process was simulated by contact functions, the closed cable loops was simulated by couplers, and the dynamics characteristic was emulated in ADAMS/Solver. After analysis on the simulation, the relations between deployment angles of linker and solar panels with time were obtained, and the movement of satellite′ attitude influenced by deployment motion was calculated. Analysis results indicate that the deployment process of solar array is 15 s. The deployment motion is stabilization and smoothness, and has a little effect on satellite attitude. These results reported here show that designed solar array is reasonable.