Launch Separation Simulation and Sensitivity Analysis in Space Environment

Given the mission requirements of the spacecraft and the satellite's limited attitude control capabilities, specific criteria are in place for the attitude angular velocities of both entities at the moment of separation. This study, grounded in multi-body dynamics, employs ADAMS software to fabricate a virtual prototype model of the spacecraft, separation mechanism, and satellite. It scrutinizes the impact of rail gaps, discrepancies in rail gaps, and thrust eccentricity on the spacecraft's separation attitude. The analysis suggests that thrust eccentricity primarily drives changes in spacecraft attitude angular velocity. Moreover, the number of collisions between the spacecraft and the satellite is influenced by rail gaps, whereas inconsistencies in rail gaps result in spacecraft roll during separation. The simulation results can provide theoretical support for the subsequent design of separation mechanisms