固体火箭技术Issue(3)：346-351,375,7.DOI:10.7673/j.issn.1006-2793.2014.03.012
基于主应力的固体火箭发动机界面累积损伤分布研究
Cumulative damage distribution analysis of solid rocket motor interface based on principal stress
摘要
Abstract
In order to obtain the distribution and changing characteristics of cumulative damage of interface between propellant and liner of solid rocket motor under environment temperature,a multi angle tensile clamp was designed,constant load experiment with different load magnitude and angle was performed,and the changing characteristics of time to failure was obtained.The linear cumulative damage law was improved by adding load angle parameter.The distribution of thermal stress of grain was computed by fi-nite element method,the distribution and changing characteristics of principal stress in the normal section to interface were obtained. The results indicate that the cumulative damage computed by improved cumulative damage law is larger than that computed by Mises stress.It is considered that the head and its joint part with cylinder stage,as well as the end of stress relief flap of solid rocket motor are probable interface debond location.关键词
固体火箭发动机/累积损伤/界面/寿命预估Key words
solid rocket motor/cumulative damage/interface/service life prediction分类
航空航天引用本文复制引用
邱欣,李高春,张春龙,杨明..基于主应力的固体火箭发动机界面累积损伤分布研究[J].固体火箭技术,2014,(3):346-351,375,7.基金项目
武器装备预研基金（9140A280102）。 （）
