Mechanical Response Analysis Of Cylindrical Shell With Visco-elastic Liner

During the curing process of the solid propellant rocket motor, because of thedifferent material properties, the deformations of the propellant, liner, inhibitor andthe motor-case are also different. Due to the different material properties, the cracksor other imperfections will occur which will provide additional burning surfaces,resulting in possible engine failure. This paper deals with the propellant curingprocess, and analyzes the reaction of the liner structure with finite element method.The material properties of the liner and inhibitor will be changed to optimize therocket motor.An introduction of the solid propellant rocket motor was made. The progressand achievements of the structure integrity of the solid motor was summarized andthe main factors affecting the bonding strength was analyzed.Based on the basic equations of the visco-elastic theory, the applications to thefinite element software ABAQUS was intruduced. The heat analysis was studied andthe method to solve the steady thermal analysis and transient thermal analysis wasderived.A simplification of the classic solid propellant rocket motor was made, and aone-half axis-symmetrical finite element model was built. The temperature field,stress field and the strain field were analyzed, and the dangerous point on the linerwas found out. A comparison of the reaction to the change of the properties of theliner material was made.Based on an actual model of a solid propellant rocket motor, the transientthermal analysis was simulated. The temperature field and stress field were analyzed,and the dangerous point on the liner was found out. Comparing the results of themodels with artificial debonding and which without it, the artificial debonding layerwas verified that it could release the stress. The stress on the interface was decreasedby optimizing the liner structure.