The ignition pressurization load of low temperature and high speed loading at the moment of low temperature ignition of solid rocket propellant may lead to the destruction of propellant structural integrity. In view of the lack of reasonable test scheme design in the current low temperature ignition impact test, this paper used Abaqus finite element analysis software to carry out numerical simulation research on a low temperature ignition impact test specimen in the form of Ф25～37 mm inner hole charge. The maximum internal pressure limited of the hydroxyl terminated polybutadiene(HTPB) solid propellant specimen whose structural integrity was not destroyed and the influence of thickness coefficient on the distribution of equivalent stress and strain of the propellant were quantitatively obtained. The results show that the structural integrity of the solid propellant will not be destroyed under the low temperature ignition test conditions of -40 °C and 10 MPa, which is consistent with the test conclusion. When the internal pressure increases to 42.2 MPa, the surface equivalent stress of the propellant exceeds its tensile strength, and the structural integrity of the propellant is damaged. Under the same typical working condition, the equivalent stress and strain of propellant surface increase with the increase of thickness coefficient. When thickness coefficient is 2.6, the equivalent stress of propellant surface is damaged due to exceeding its tensile strength and structural integrity. The research methods and results in this paper can provide guidance for the optimization design of related test schemes.