Design and driving optimization of a space-towed deployable arm

Due to the mass and volume of the driving mechanism, the traditional deployable arm mechanism has difficulty meeting the deployment ratio and mass requirements of ultra large-scale spacecraft, and it is urgent to develop new deployable configurations and more efficient driving modes. This study proposes a new driving method and a new towed deployable arm to meet the requirements of a large deployment ratio and light mass. First, the optimal configuration of the deployable arm with an axial load cable and telescopic inclined bar is proposed in this paper. The rapid response hinge is designed, and the layout of the hinge is optimized to further improve the stiffness and tolerance of the deployable arm. Second, the dynamic characteristics of the deployable arm under different driving forces are analysed, and the correctness of the theoretical model is verified by ADAMS software. Based on the response surface method, driving strategies are optimized. Finally, a 4-metre prototype is developed. The towing expansion test is carried out to verify the correctness of the theoretical analysis in this paper.