The sail area of the solar sail spacecraft significantly impacts the propulsion efficiency of the satellite based on solar electric propulsion (SEP). And the folding ratio of the solar sail can be effectively enhanced using origami principles, which are adept at leveraging crease characteristics. This paper proposes a novel solar sail spacecraft design approach based on the origami principle. An origami-based solar sail is given from the design point of view. The folding and unfolding motion of the solar sail is simulated using the Origami Simulator, and a ground deployment test is conducted with a physical prototype to validate the feasibility of the origami-inspired design. Based on this, it proves that the type of crease has a significant impact on the orbit control of solar sail spacecraft. This paper examines the impact of different folding patterns on the orbit control ability of solar sail spacecraft during Earth-Mars transfer from a control perspective. Accordingly, four commonly used folding patterns are selected to analyze their performance parameters, such as folding ratio and characteristic acceleration, to calculate the transfer trajectory. The results indicate that the solar sail designed based on the origami principle has a large folding ratio, which benefits the orbit control ability and reduces the transfer time.