固体推进剂矩形粘接试件的多角度拉伸试验  

Multi-angle Tensile Test for Solid Propellant Rectangular Adhesive Specimens

作　　者：邱欣[1] 李高春[1] 姜爱民[1] 赵大鹏 

机构地区：[1]海军航空工程学院飞行器工程系,山东烟台264001 [2]291049部队,山东青岛266102

出　　处：《含能材料》2014年第6期786-791,共6页Chinese Journal of Energetic Materials

基　　金：武器装备预研基金项目(9140A280102)

摘　　要：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。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.

关 键 词：航空宇航推进理论与工程 固体火箭发动机 粘接界面 多角度拉伸 失效准则 

分 类 号：V435.6[航空宇航科学与技术—航空宇航推进理论与工程]