摘要: Due to the unique configuration of the stealth satellite，the spatial utilization of the carrying space is very low. The need of re‐ search on on-orbit assembly technology for stealth satellites is urgent. Based on the parameters and design requirements of in-orbit assembly for stealth satellites, the on-orbit assembly interface between stealth satellite modules is designed. In a microgravity environment where loads are not easily dissipated, excessive contact forces for on-orbit assembly affect the attitude stability of the spacecraft with the on-orbit assembly platform. Based on the geometric shapes of the components in contact during the assembly process, classify contact phases and cal‐ culate the Hertz contact force. Three feed paths are set, then the trend of the contact force magnitude and the location where the maximum contact force occurs for three paths are analyzed. The contact force experiment is carried out and results are compared with analyzed results. The correctness of the trend of the magnitude of the contact forces, the maximum contact forces and the location where the maximum con‐ tact forces occurs are verified.