Configuration design and crease topology of origami-inspired spinning space deployable structures

Abstract

Origami-inspired space deployable structures can be transformed from the folded states into the deployed states in orbit, which satisfied the demands of complex space missions and had been widely used in the space field. It remains to be investigated how the space deployable structures realized a large deployable ratio in the crease design process of origami patterns for the storage space limitation of spacecraft structures. Origami-inspired Regular Polygons Deployable Structures (RPDS) were proposed by designing the origami configurations and analyzing the deployable mechanism from existing space deployable structures, and a novel crease topology with three different approaches was presented in repeating origami modules to enhance the deployable ratio. The topology results indicated that the deployable ratio of RPDS can be increased effectively by shortening the storage height or performing multi-stage deployment, and the flexibility of RPDS can be verified by changing the shape of the central body. The configuration rationality and deployable reliability of RPDS are confirmed by kinematic modeling and numerical simulation. This study provides new insights into extraordinary geometrical and folding properties of origami-inspired deployable structures via configuration design and crease topology, which can be extended to other origami patterns in various origami-inspired applications.