In order to evaluate the performances of an over-storage solid rocket motor(SRM)

the solid rocket motor already stored for 14 years was disassembled.The mechanical property and deflagration performances of the solid propellant were measured.The three-dimensional interior ballistic model for igniting process of the SRM was analyzed by numerical simulation.The finite element model(FEM) of the SRM was developed.Based on the grid face of computational fluid dynamics(CFD) mesh and FEM element

the data transfer method from CFD pressure to FEM load was studied.The structural integrity analysis of the SRM was carried out with the fluid-structural coupling technique.It shows that the modulus of the hydroxyl terminated polybutadiene(HTPB) composite propellant after 14 years has been increased

and ε_m decreased.According to the results of interior ballistic simulation and structural integrity analysis

the structural integrity of the grain could be maintained

and the SRM that had been stored for 14 years is applicable for use.