Abstract: The existing docking mechanism for on-orbit service cannot provide strong support for our country's follow-up lunar exploration project due to its large size, complex structure and single docking target. Lightweight docking mechanism is also an essential link due to the limit of carrying capacity. In order to study the docking mechanism that can serve the high-orbit missions such as future Moon Space Station and manned lunar landing, a new claw-type docking mechanism was designed, which adopted androgynous configuration and can realize the interchange between active vehicle and passive vehicle, the V-shaped slot and claw hook and other structural components are used to realize the capture and energy consumption functions in the docking process of aircraft, so as to realize the stable connection between two vehicles. The docking mechanism has the advantages of small size, light weight, simple structure and easy realization of functions. The dynamic analysis of the capture buffer system was carried out, and the influence of the parameters of buffer components on its capture performance was calculated, the establishment of the digital virtual prototype was completed in ADAMS software, and the simulation research was carried out in combination with the actual two typical initial docking conditions. The results show that the energy consumption in the docking process under the two working conditions meets the design requirements, and the capture can be completed with a smaller impact force of the V-shaped slot. The results prove the feasibility of the capture buffer system, and verify the capability of the docking mechanism with this configuration has better ability to complete tasks.