Design and analysis of test coupons for composite blade repairs
Design and analysis of test coupons for composite blade repairs
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DOI：
10.1016/s0263-8223(97)80011-6
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发表时间：
1997-02-01
影响因子：
6.3
通讯作者：
Sem, K
中科院分区：
文献类型：
--
作者：
Oztelcan, C;Ochoa, OO;Sem, K
复合材料技术的进步刺激了复合材料在现代旋翼飞机结构中的使用增加。除了这些材料系统理想的高强度、低重量特性之外，增强的疲劳强度和损伤容限使复合材料对于先进结构应用特别有吸引力。尽管这些结构在使用过程中经常损坏并需要修复，但复合材料可以持续修复。为了确保成功修复，至关重要的是能够预测修复部件的强度、寿命和可能的损坏模式，以解决可靠性和设计问题。本文重点关注复合材料修复方法开发计划的第一阶段，其目标是开发适当的测试样本，以通过计算和实验评估静态和循环载荷对修复部位复合材料叶片的影响。第一阶段涉及代表重叠和围接预固化补丁修复的测试附片的设计及其静态加载条件的分析。全局叶片模型用于确定给定负载组的应变分布。然后使用适当的边界条件创建代表测试试样几何形状的局部有限元模型。根据该局部模型，生成重叠和围巾补丁模型。这些模型在单轴压缩和拉伸载荷下进行分析。基于允许的极限应力的用户子程序被纳入分析中，以检测粘合剂损坏的开始和进展。 (C) 1997 爱思唯尔科学有限公司。
Advancements in composite material technology have spurred an increase in the use of composites in modem rotorcraft structures. In addition to the desirable high strength, low-weight features of these material systems, the enhanced fatigue strength and damage tolerance has made composites particularly attractive for advanced structural applications. Even though these structures are often damaged during service and need repair, composites can be repaired consistently. In order to assure successful repair, it is crucial to be able to predict the strength, life and possible damage modes of a repaired component for reliability and design issues.This paper focuses on the first phase of a composite repair methodology development program where the goal is to develop appropriate test specimens to evaluate computationally and experimentally the effects of static and cyclic loads on a composite blade with a repair site. The first phase addresses the design of the test coupons representative of overlap and scarf precured-patch repairs and their analysis for static loading conditions. A global blade model is used to determine the strain distribution for a given set of loads. A local finite element model which represents the test coupon geometry, is then created with the appropriate boundary conditions. From this local model, overlap and scarf patch models are generated. These models are analyzed under uniaxial compressive and tensile loads. A user subroutine, based on the ultimate stress allowable is incorporated into the analysis to detect the initiation and progression of damage in the adhesive. (C) 1997 Elsevier Science Ltd.