A New Design of the 3D Deployable Solar Array in the Aerospace Field and Kinematic Analysis during Deployment

Abstract

Abstract The paper focuses on a new design of the 3D deployable solar array for spacecraft and landers. Compared with existing solar array designs, the main advantage of this new design is the further increase in the area of the solar array. The principles of spatial rings and domes are used for this new design. This design consists of a large dome and four smaller rings. The model is constructed using Solidworks, and different configurations during the deployment are shown. The kinematic analysis shows that the length ratios of elements are independent of the input angle θ. It proves that this deployable structure has only one mobility. The configuration can be determined by a specific input angle. When the input angle θ increases, the top-view area of the structure increases, while the maximum height of the structure decreases. The volume of the increases and then decreases with the increasing θ. The maximum volume occurs at θ = 110°. In addition, the shape of the top-view geometry for a particular design is determined by two design parameters. It is found that the length ratios of elements increase with the increasing value of two design parameters.