ABSTRACT
There is an increasing demand for large spacecraft components with the development of the large spacecraft industry. However, the launcher’s capability is a major constraint in spacecraft design. Designs based on large rigid and foldable structures are constrained in size by the fairings’ dimensions [1]. Deployable mechanism has the advantages of less mass, smaller volume, and convenience of storage and transportation. Deployable structures have won widespread attention for their expensive application prospects in fields such as solar panels, antennas, radars, and satellite masts [2].
