摘要：Space deployable mast is an important device or system, which can deploy and support spacecraft fittings on orbit, such as payload, solar array, antenna, and etc. In order to achieve the pre-function of spacecraft fittings and attitude control of spacecraft, space deployable mast of high stiffness is required. Therefore, it is necessary to analyze the stiffness of the mast to ensure the capability. STDM consisting of longerons, rigid frames, flex-battens, hinge joints, and etc has higher stiffness than coil or articulated deployable mast. The design of STDM is presented, under the demand of future large-scale spacecraft. The theory analysis of stiffness is achieved and the impact factor are found, which establish the theoretical baseline for the optimization design and application of the mechanism product.
