Origami principle in space deployable membrane structures: Mechanism, application and prospects

The accelerated evolution of space technology has elevated the importance of high power and lightweight attributes in satellite design. In response to the conflict between the demand for large-scale, high-power payloads and the need for lightweight, compact platforms, flexible space origami membrane structures have emerged as a potential solution. These structures possess the ability to overcome the limitations of traditional deployable mechanisms. Their geometric reconfiguration capabilities, characterized by high folding ratios, effectively satisfy the high-power performance demands. Thus, this paper begins with an overview of the design and application of space origami membranes before investigating the design of creases, deployable mechanisms, and the close connection between the two, focusing on the origami principle. This section introduces various crease types with different motion dimensions, folding characteristics, advantages, disadvantages, and optimization methods. Then, the deployable mechanisms’ structures, principles, and performance characteristics in three unfolding spatial dimensions are presented comprehensively. Based on the preceding sections, this paper reviews the application of the origami principle to spacecraft solar arrays, antennas, solar sails, drag sails, and light shade structures, considering the current status, application purpose, and effect. Finally, the development trend of space origami membrane structures is analyzed.