Abstract
In medium or small-sized spacecrafts’ docking process, it’s feasible to adopt a flexible probe for the probe-cone docking mechanism instead a buffer to reduce the docking impact force. The governing equations of kinematics and dynamics are derived from Lagrange analytical method. The influence parameters of the impact force are separated by simplifying the impact mathematical modeling. The effects of the influence parameters in the impact force, such as the length of docking beam, and the material of the docking mechanism, are discussed by finite element method. The varation amplitude and varation frequency are obtained by docking experiment, and reliability and correctness of the analysis reuslts are verified.
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