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含能材料  2014 

固体推进剂矩形粘接试件的多角度拉伸试验

DOI: 10.11943/j.issn.1006-9941.2014.06.014

Keywords: 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

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Abstract:

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QJ2038.1A-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1166N降至420N,最大主应力由0.945MPa降至0.461MPa,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。

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