Abstract: The multi-degree-of-freedom solar panel of spacecraft is susceptible to elastic vibrations under the perturbation of the attitude control engine, which may lead to failure of the locking motor at the joint. In this paper, the FEM and dynamic model of the solar panel is established, for the analysis of the rigid and elastic loads. Taking a specific mode case as an example, the rigid and elastic loads at the joint of the solar panel are analyzed and compared. The input can thus be provided for the design of the joint and the locking motor.