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Bending of Bonded Composite Repairs for Aluminum Aircraft Structures: A Design Study

机译：铝制飞机结构的粘结复合材料修理的弯曲：一项设计研究

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This paper describes an experimental and finite element study of a bonded composite repair applied to a metallic aircraft structure. The experimental study involves the fatigue testing and fractographic examination of 2024-T3 aluminum plates repaired with boron/epoxy composite patches. The two plates are tested simultaneously in a sandwich panel configuration with and without an aluminum honeycomb spacer to provide bending restraint. The specimen was heavily instrumented, with strains being measured on the surface of the patch at many locations, thus allowing the validation of a three-dimensional finite element model and an assessment of the effects of geometrically nonlinear bending, buckling, and crack closure on the mechanical response and strength of the repair. The experimental and finite element results illustrate the important influence of bending and composite failure modes on the life and strength of the repair. The authors use the experimental results and the validated finite element analysis to evaluate the effectiveness of the methods and data currently available in the open literature for damage-tolerance substantiation, and then, by applying probabilistic methods and the principle of compounded conservatism to the findings, propose a new process for classifying bonded repairs and assigning requirements for testing and inspections.
机译：本文描述了一种应用于金属飞机结构的粘结复合材料修复的实验和有限元研究。实验研究涉及用硼/环氧复合材料修补剂修复的2024-T3铝板的疲劳测试和分形检查。在带有和不带有铝蜂窝隔圈的夹心板配置中同时测试这两个板，以提供弯曲限制。标本经过大量仪器测试，在许多位置的贴片表面上测量了应变，因此可以验证三维有限元模型，并可以评估几何非线性弯曲，屈曲和裂纹闭合对裂纹的影响。机械响应和修复强度。实验和有限元结果说明了弯曲和复合破坏模式对修复寿命和强度的重要影响。作者使用实验结果和经过验证的有限元分析来评估开放文献中目前可用于损伤容限化的方法和数据的有效性，然后将概率方法和复合保守性原理应用于研究结果，提出一种对保税维修进行分类并分配测试和检查要求的新流程。

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