复合材料修补后金属薄板损伤临界裂纹张开位移模型研究

Q4 Engineering

Fatigue of Aircraft Structures Pub Date : 2016-06-01 DOI:10.1515/fas-2016-0009

Michał Sałaciński, A. Leski, M. Stefaniuk

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引用次数: 1

摘要

提出了一种计算CPBR(粘结复合材料补片修复)修复后飞机金属结构最大位移的方法。这些计算是根据标本进行的。试样是按照现行航空要求制备的。2024-T3合金金属板为结构。采用硼-环氧复合材料补片预浸技术修复结构。将金属结构建模为各向同性弹性体。采用正交各向异性结构对涂覆复合贴片的金属结构进行建模。在此基础上，确定了金属结构中的应力。基于平面应力状态下的线弹性断裂力学模型，确定了金属结构的开口位移大小。通过实验室条件下的位移测量，验证了计算结果。实验室试验证明了所提出方法的准确性。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

查看原文本刊更多论文

Approach to Critical Crack Opening Displacement Modeling of Damage in Metal Sheets after Composite Patch Bonded Repair

Abstract The paper proposes a method of calculating the maximum displacement in the aircraft metal structure repaired by CPBR (bonded composite patch repair). The calculations were made based on specimens. The specimens were prepared according to the current requirements used in aviation. The 2024-T3 alloy metal sheet was a structure. To repair the structure used the boron-epoxy composite patch in prepreg technology was used. The metal structure was modeled as an isotropic elastic body. The metal structure coated with the composite patch was modeled as an orthotropic structure. Based on this, the stress was determined in the metal structure. The size opening displacement in the metal structure was determined based on the model of linear elastic fracture mechanics for the plane stress state. The calculation results were verified by measuring the displacement in laboratory conditions. The laboratory tests made it possible to demonstrate the accuracy of the proposed approach.

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来源期刊

Fatigue of Aircraft Structures Engineering-Safety, Risk, Reliability and Quality

CiteScore

0.40

自引率

0.00%

发文量

期刊介绍： The publication focuses on problems of aeronautical fatigue and structural integrity. The preferred topics include: full-scale fatigue testing of aircraft and aircraft structural components, fatigue of materials and structures, advanced materials and innovative structural concepts, damage tolerant design of aircraft structure, life extension and management of ageing fleets, structural health monitoring and loads, fatigue crack growth and life prediction methods, NDT inspections, airworthiness considerations.