CAJ | 학술논문

为采用试件模拟固体火箭发动机燃烧室壳体／绝热层／衬层／推进剂粘接系统同时承受拉伸和剪切载荷的受载状态，设计了符合航天行业标准 QJ 2038．1A－2004规定的矩形粘接试件的多角度拉伸夹具。实现了对试件的单纯拉伸、单纯剪切以及拉伸、剪切结合的多种载荷状态。随着拉伸角度由0°增至90°，界面失效时刻对应的载荷由1166 N 降至420 N，最大主应力由0．945 MPa降至0．461 MPa，上界面最大主应力集中系数由1．1 上升至2．7，下界面最大主应力集中系数则变化较小。试验中试件起裂部位与界面最大应力位置的计算结果一致性较好，可为发动机粘接系统结构完整性分析提供参考。
위채용시건모의고체화전발동궤연소실각체／절열층／츤층／추진제점접계통동시승수랍신화전절재하적수재상태，설계료부합항천행업표준 QJ 2038．1A－2004규정적구형점접시건적다각도랍신협구。실현료대시건적단순랍신、단순전절이급랍신、전절결합적다충재하상태。수착랍신각도유0°증지90°，계면실효시각대응적재하유1166 N 강지420 N，최대주응력유0．945 MPa강지0．461 MPa，상계면최대주응력집중계수유1．1 상승지2．7，하계면최대주응력집중계수칙변화교소。시험중시건기렬부위여계면최대응력위치적계산결과일치성교호，가위발동궤점접계통결구완정성분석제공삼고。
In order to simulate the loading condition of shell/ insulation / liner/ propellant bonding system in solid rocket motor combustion chambers,a multi-angle tensile clamp was designed for rectangular adhesive specimen according to QJ 2038. 1A-2004,and the pure tensile,pure shear and tensile-shear mixed stress on the specimen interface were realized. Results show that the tensile angle(the angle between tensile direction and normal direction of interface)increases from 0° to 90°,and the critical load decreases from 1166 N to 420 N,and the critical maximal principal stress decreases from 0. 945 MPa to 0. 461 MPa. The crit-ical maximal principal stress ratio of upper interface increases from 1. 1 to 2. 7 and little change in lower interface,indicating the fracture initiation locations of the specimen are consistent with the calculated.