在碳纤维增强的环氧聚合物复合材料的循环疲劳裂纹生长上
Silvain Michel1, Neal Murphy2, Anthony J Kinloch3
1Empa, Swiss Federal Laboratories for Material Science and Technology, Laboratory for Mechanical Systems Engineering, CH-8600 Dübendorf, Switzerland.
Polymers
|February 10, 2024
概括
本研究提出了分析复合材料飞机结构分层增长的方法. 它详细说明了如何计算疲劳裂增长率和值,这对于确保结构完整性和延长使用寿命至关重要.
科学领域:
- 材料科学 材料科学 材料科学
- 航空航天工程 航空航天工程
- 断裂力学 断裂力学 断裂力学
背景情况:
- 在周期性负荷下,复合材料飞机结构中的分层显著减少了使用寿命.
- 当前的"无增长"设计理念可能无法防止在运营中的飞机中进行分层,从而损害完整性.
- 准确评估分层增长对于结构安全至关重要.
研究的目的:
- 概述用于分析连续纤维聚合物矩阵复合材料中的分层的实验和数据减少程序.
- 建立确定疲劳裂增长 (FCG) 速率曲线和最坏情况情景的方法.
- 为了计算复合材料的疲劳值.
主要方法:
- 线性弹性断裂力学 (LEFM) 原则的应用.
- 开发了两种不同的数据缩小程序:哈特曼-斯基夫方法和一种新的简单缩放方法.
- 疲劳裂增长 (FCG) 速度和值的实验性确定.
主要成果:
- 成功计算了疲劳裂增长 (FCG) 速率,da/dN,曲线.
- 确定两种方法来建立最坏的FCG率曲线,这两种方法都为实验数据提供了上限.
- 疲劳值的计算显示了两种拟议的方法之间的良好一致性.
结论:
- 拟议的实验和数据减少程序有效地描述了复合材料中的分层疲劳行为.
- 开发的方法提供了可靠的方法来确定最坏的情况下FCG率和疲劳值.
- 这些发现有助于改进设计理念,以提高飞机组件的结构完整性和寿命.
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