Bonded composite repair of fatigue-cracked primary aircraft structure
Bonded composite repair of fatigue-cracked primary aircraft structure
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DOI：
10.1016/s0263-8223(00)00011-8
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发表时间：
1999-12-01
影响因子：
6.3
通讯作者：
Baker, A
中科院分区：
文献类型：
--
作者：
Baker, A
与基于机械紧固金属补片的标准修复相比，基于粘合纤维复合材料补片或增强材料的修复在结构上更加高效，并且对母体结构的损坏要小得多。由于粘合补片的高补强效率，可以成功修复“活”疲劳裂纹。然而，当此类修复应用于主体结构时，通常会采取保守的认证方法，其中国际劳工组织对修补系统给予减缓裂缝增长或恢复残余强度的认可。因此，接近临界尺寸的裂纹无法修复，检查间隔必须基于未修补裂纹的预测增长行为。为了让补丁获得认可，需要证明 (a) 补丁丢失的可能性低得可以接受，或者 (b) 可以立即检测到其丢失。讨论了两种方法：解决（a）的第一种方法基于预测补片系统疲劳行为并确保其环境耐久性的已证明能力。解决 (b) 问题的第二种方法基于“智能补丁”概念，其中补丁系统监控其自身的运行状况。 Crown 版权所有 (C) 2000 由 Elsevier Science Ltd 出版。保留所有权利。
Repairs based on adhesively bonded fibre-composite patches or reinforcements are more structurally efficient and much less damaging to the parent structure than standard repairs based on mechanically fastened metallic patches. As a result of the high reinforcing efficiency of bonded patches "live" fatigue cracks can be successfully repaired. However, when such repairs are applied to primary structure a conservative certification approach is often taken in which Ilo credit is given to the patch system for slowing crack growth or restoring residual strength. Thus, cracks approaching critical size cannot be repaired and inspection intervals must be based on the predicted growth behaviour of the unpatched crack. To allow credit to be given to the patch the need is to demonstrate either (a) that the likelihood of patch loss is acceptably low or (b) that its loss can be immediately detected. Two approaches are discussed: the first approach which addresses (a) is based on a demonstrated ability to predict the patch system's fatigue behaviour and to assure its environmental durability. The second approach that addresses (b) is based on the "smart patch" concept in which the patch system monitors its own health. Crown Copyright (C) 2000 Published by Elsevier Science Ltd. All rights reserved.