Abstract: In order to study the shock-combustion performance of the solid rocket motor, the sled platform as loading device was used to apply shock load to the high energy solid rocket motor, regulated the velocity of the sled to obtain the macroscopic reactive characteristics of the high energy rocket shock combustion. The experiment process was simulated by means of the thermo-mechanical coupling calculation mode, which considering the propellant self-heated reaction heat source aroused by temperature rised under stress effection. Through calculating temperature change of the propellant when the motor struck target board, the action severe degree of the propellant was analysed, the reactive characteristics of solid rocket motor was judged and the reaction mechanism was obtained. The result shows that the propellant will be ignited when the striking velocity larger then 100 m/s, the ignition position occurs on the bore of the motor, the ignition delay time reduces with the increase of the striking velocity.