Influence of the Fatigue Load Level and the Hole Diameter on the Laminate Structure’s Fatigue Performance

Q4 Engineering

Fatigue of Aircraft Structures Pub Date : 2018-12-01 DOI:10.2478/fas-2018-0002

M. Zalewska

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引用次数: 0

Abstract

Abstract Damage tolerance of composite aircraft structure is one of the main areas of research, important when a new product is being developed. There are a number of variables, such as damage characteristics (dent depth, delamination area) and loading parameters (load type, amplitude of cyclic loading, load sequence) that need to be investigated experimentally [1]. These tests of composite materials are usually performed at an element level and are carried out in order to validate the analytical model, developed to predict the full-scale component’s behaviour. The paper presents the results of compression testing of the [36/55/9] carbon fibre/epoxy laminate, manufactured with the Automated Fibre Placement technology (AFP) and subjected to static and fatigue loads. The laminate compression loading mode was achieved through sandwich 4-point flexure. At the stage of fatigue testing, two parameters were investigated: the damage size, simulated by the hole diameter and the fatigue load level. Based on the test results, the laminate fatigue load limit equal to 75% of the OHC failure load was evaluated. By collating the static and fatigue tests results, the damage tolerance characteristic of the considered laminate was created.

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疲劳载荷水平和孔直径对层压结构疲劳性能的影响

摘要复合材料飞机结构损伤容限是复合材料飞机结构损伤容限研究的主要领域之一，在新产品开发中具有重要意义。有许多变量，如损伤特征(凹痕深度，分层面积)和加载参数(加载类型，循环加载振幅，加载顺序)需要进行实验研究[1]。这些复合材料的测试通常在元件水平上进行，目的是验证用于预测全尺寸部件行为的分析模型。本文介绍了采用自动纤维放置技术(AFP)制造的[36/55/9]碳纤维/环氧层压板在静态和疲劳载荷下的压缩测试结果。层压板压缩加载方式是通过夹心四点弯曲实现的。在疲劳试验阶段，研究了两个参数:损伤尺寸、孔直径模拟和疲劳载荷水平。在试验结果的基础上，评估了层压疲劳载荷极限为热热破坏载荷的75%。通过对比静力和疲劳试验结果，建立了所考虑的层合板的损伤容限特性。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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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.