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

作　　者：邱欣[1] 李高春[2] 张春龙[1] 杨明[1] 

机构地区：[1]海军航空工程学院研究生管理大队,烟台264001 [2]海军航空工程学院飞行器工程系,烟台264001

出　　处：《固体火箭技术》2014年第3期346-351,375,共7页Journal of Solid Rocket Technology

基　　金：武器装备预研基金(9140A280102)

摘　　要：为获得固体火箭发动机推进剂/衬层粘接系统在温度载荷下的累积损伤分布及其变化规律,设计了一种多角度拉伸夹具,进行了以载荷大小和载荷角度为变量的粘接试件定载试验,获得了界面承载时间随载荷大小和角度的变化规律。通过添加载荷角度项,对线性累积损伤模型进行了修改。采用有限元法计算了药柱不同温度下的热应力分布,获得了界面处主应力在垂直于界面平面内合力的大小及其与界面的夹角。结果表明,根据主应力及修改后的线性累积损伤公式计算的发动机界面累积损伤程度明显大于根据Mises应力的计算结果,认为发动机头部及其与圆柱段连接处、人工脱粘根部是容易脱粘的部位。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 finite 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 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]