Dynamics Modeling and Performance Analysis for a Spacecraft Collision Buffer System

The in-orbit collision safety and reliability of a spacecraft are directly influenced by the dynamic characteristics of its collision buffer system. A rigid-flexible coupling dynamics model of the collision buffer system was established based on the multibody systems transfer matrix method. The overall transfer equation, characteristic equation, and dynamics response equation of the system were derived according to the topological graph of the dynamics model describing the transfer relationships of each component. Additionally, the vibration characteristics of the system were analyzed through numerical simulations. Modal tests of the collision buffer system were conducted to validate the accuracy of the proposed model. The effects of physical parameters, such as stiffness coefficients on the dynamic characteristics of the collision buffer system were analyzed and the regulatory mechanisms of key parameters on the system’s natural frequencies and vibration responses were revealed. The method established in this study was demonstrated to significantly enhance the efficiency of system vibration characteristic analysis, providing a novel technical approach for the dynamic characteristic analysis and optimal design of spacecraft collision buffering systems.