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In order to solve the problems of the existing solar wing, such as complex process and obvious structural vibration. a new space deployable solar wing mechanism composed of single DOF modularization was designed. The structure and working principle of the space deployable solar wing are described, and the driving system is briefly introduced. The single module of the solar wing is divided into two parts and the kinematics equations of the kite-shaped mechanism and origami mechanism are established respectively. Secondly, the output motion rule of the bar at the end was solved when the special driving is applied to the kite-shaped mechanism. And based on this output, changed the angle of the origami mechanism’ plates and the change curve of the centre of mass and the angle between the plates is obtained. The study results show that, synthesize considering the shrinkage and the ratio of folding to span, the optimal solution is the angle of plates  φ =4°. Through the above research that provide the theoretical basis for the optimization and improvement of the mechanism.

Design and development characteristics research of modular space deployable solar wing