CAJ | 학술논문

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。
위획득고체화전발동궤추진제/츤층점접계통재온도재하하적루적손상분포급기변화규률，설계료일충다각도랍신협구，진행료이재하대소화재하각도위변량적점접시건정재시험，획득료계면승재시간수재하대소화각도적변화규률。통과첨가재하각도항，대선성루적손상모형진행료수개。채용유한원법계산료약주불동온도하적열응력분포，획득료계면처주응력재수직우계면평면내합력적대소급기여계면적협각。결과표명，근거주응력급수개후적선성루적손상공식계산적발동궤계면루적손상정도명현대우근거Mises응력적계산결과，인위발동궤두부급기여원주단련접처、인공탈점근부시용역탈점적부위。
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.