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Analysis and residual strength prediction for multiple site damage in aircraft structures by using weight function method

机译：重量函数法分析飞机结构多部位损伤及残余强度

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This paper presents a review of recent progress of the development of weight function method for analyzing multiple site damage in aircraft structural panels.An analytical method,the Weight Function Method (WFM),has been proposed and further developed to analyze the MSD problems and to determine the related various fracture mechanics parameters.The plastic zone sizes and crack opening displacements were extensively verified and validated by excellent agreement with available analytical and finite element method results.Combined with Crack Tip Opening Angle criterion (CTOA),the present WFM is employed to predict the stable crack growth and residual strength of aircraft aluminum sheets containing MSD.The predicted results compared very well with the corresponding experimental data.Thereby a novel analytical approach with high efficiency and reliability has been devised for MSD analyses in aircraft structures.

机译：本文概述了用于分析飞机结构板多部位损伤的权重函数方法的最新进展。提出了一种分析方法，即权重函数方法（WFM），以分析MSD问题并为确定相关的各种断裂力学参数。塑性区的大小和裂缝的开裂位移与现有的解析和有限元方法结果进行了很好的吻合，得到了广泛的验证和验证。结合裂缝尖端的张开角度准则（CTOA），本WFM用于预测含MSD的飞机铝板的稳定裂纹扩展和残余强度，并将预测结果与相应的实验数据进行了很好的比较，从而为飞机结构中的MSD分析设计了一种高效，可靠的新型分析方法。

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来源
《International conference on fracture》|2013年|1-10|共10页
会议地点 Beijing(CN)
作者
X.R. Wu; W. Xu; H. Wang;
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作者单位

AVIC Beijing Institute of Aeronautical Materials Beijing 100095 China;

School of Aeronautics and Astronautics Shanghai Jiao Tong University Shanghai 200240 China;

School of Naval Architecture Ocean and Civil Engineering Shanghai Jiao Tong University Shanghai 200240 China;

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Multiple site damage; Weight function method; Plastic zone size; Crack opening displacement; Residual strength;

机译：多处损坏；权重函数法；塑料区大小；裂纹开口位移；残余强度;

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专利

1. Residual strength prediction for aircraft panels with Multiple Site Damage, using the 'EPFEAM' for stable crack growth analysis [J] . C. R. Pyo, H. Okada, S. N. Atluri Computational Mechanics . 1995,第3期

机译：使用“ EPFEAM”进行稳定的裂纹扩展分析，以预测具有多个部位损坏的飞机面板的残余强度
2. Damage Tolerance Analysis Software (DATAS) for Crack Growth Life Prediction and Residual Strength Analysis of Aircraft Structures [J] . l.S. Putra Key Engineering Materials . 2000,第期

机译：飞机结构裂纹扩展寿命预测和残余强度分析的损伤容限分析软件（DATAS）
3. Advanced damage tolerance and risk analysis methodologies and tools for aircraft structures containing multiple-site and multiple-element fatigue damages [J] . M Liao, Y Bombardier, G Renaud, Proceedings of the Institution of Mechanical Engineers . 2012,第G11期

机译：包含多点和多元素疲劳损伤的飞机结构的高级损伤承受能力和风险分析方法和工具
4. Analysis and residual strength prediction for multiple site damage in aircraft structures by using weight function method [C] . X. R. Wu, W. Xu, H. Wang International Conference on Fracture . 2012

机译：使用重量函数法对飞机结构多网站损坏的分析和剩余强度预测
5. Crack linkup and residual strength of aircraft structure containing multiple site damage. [D] . Ma, Leong. 1999

机译：包含多个部位损坏的飞机结构的裂纹连接和残余强度。
6. Residual Strength Prediction of Aluminum Panels with Multiple Site Damage Using Artificial Neural Networks [O] . Ala Hijazi, Sameer Al-Dahidi, Safwan Altarazi 2020

机译：利用人工神经网络多区损伤铝板的剩余强度预测
7. Residual Strength of Aging Aircraft with Multiple Site Damage/Multiple Element Damage [O] . L. Wang 2015

机译：具有多点损伤/多元素损伤的老化飞机剩余强度

Analysis and residual strength prediction for multiple site damage in aircraft structures by using weight function method

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