An analysis and simulation of launch vehicle separation dynamics including thrust transients

An analysis of the stage separation of a launch vehicle and potential for re-contact is conducted. The launch vehicle with thrust transient and mass offset in the spent stage is assumed; the engine lies recessed at the time of separation within the spent-stage's forward skirt. The potential for and effects of re-contact during separation are investigated. Coordinate systems and the equations of motion are developed. Closed-form analyses are performed for simplified cases. Furthermore, simulations are performed to verify the closed-form solutions, and the differences between simulation results and analytical solutions are discussed.