In order to study the effect of dynamic shock on solid propellant during the ignition process of solid rocket motor, a simulation setup based on quenched combustion was designed. The setup is composed of an ignition bolt, a combustion chamber, and a releasing pressure bolt. The metal burst disk is installed in the shear hole of the releasing pressure bolt and controls the ignition pressure precisely during the ignition shock process. Poly(BAMO-THF)/AP/Al solid propellant samples,molded into hollow cylinder, were used to evaluate the simulation shock process in setup. The p-t curves show that the blow-out pressure of burst disk is corresponding to the measured blow-out pressure in strong ignition mode and the pressure deviation is less than ±6%. The calculated pressurization rate according to the collected p-t curves can reach 7000 MPa·s^-1 at 10 MPa ignition and 12000 MPa·s^-1 at 15 MPa ignition, which are much more than the pressurization rate for actual ignition process of solid rocket. After simulation ignition shock experiment, filler particles implanted in the end face of propellant samples are damaged, while the inside surface basically keeps an intact condition. Compressive strength generally increases after ignition shock process, while the strain value at the point decreases when the compressive strength begins to rise. It is included that propellants with unstable structure are easier to be damaged and the mechanical properties would be changed during simulation ignition shock process.