Solar Array Mechanism Based on Deployable Structure

Spacecrafts such as satellites consume large amounts of electrical energy to carry out their missions in space. Due to the limited weight and space constraints, solar arrays become a top priority to meet the long-term operation of high-power loads. The widespread use of solar arrays is one of the necessary tools for sustainable development, which is not only related to the study of materials but also to explore more possibilities of utilization in conjunction with deployable structures. Based on the theoretical kinematic analysis and the scissor structure, this study puts forward a solar array mechanism of the scissor structure and revolute joints in the several regular polygons that connected each other. It comprises a sizeable octagonal loop and four medium-sized hexagonal rings. Because the simplified structure uses fewer rods, the failure rate is lower. A specific input angle can determine the configuration. A powerful and efficient solar array mechanism based on deployable structure was designed.