It has been a traditional regulation to turn over the missiles every half or one year to avoid possible large deformation, crack or debond. Finite element method (FEM) was employed in this article to analyze the feasibility of long-term non-turnover storage. Based on time-temperature shift principle and thermorheologically simple material assumption, several loads including assumptive aging, cooldown and long-term gravity were considered for a solid rocket motor model with a finocyl grain. Results showed that the structural integrity of the grain was fine and the long-term non-turnover storage was feasible. In order to insure the feasibility, the method of artificial internal pressure was put forward and validated.
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