关键词: 固体火箭发动机;结构完整性;粘弹性;有限元法

Abstract: A computer program to analyze thermal stresses/strains of a viscoe-lastic constructure with finite element technique is presented in this paper.The stresses/strains in this program are fully coupled with the temperature. Since the frontal technique used in the program is modified, the computation is improved in the efficiency and can be carried out with a microcomputer. In addition, the stresses of a grain in a solid rocket motor in aeroheating or curecooling processing are analyzed. The computation results on thermal stresses are reasonable and the temperature from the computation is in good accordance with the test results, which prove out the reliability and the applicability of the program presented in the paper.

Key words: Solid rocket engine;Structural integrity;Viscoelasticity;Finite element method