DAMAGE TOLERANCE EXPERIMENT AND ANALYSIS OF STIFFENED FUSELAGE PANEL WITH LONGITUDINAL CRACK

CHEN An; WEI YuLong; LIAO JiangHai; DONG DengKe

doi:10.16579/j.issn.1001.9669.2017.06.034

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DAMAGE TOLERANCE EXPERIMENT AND ANALYSIS OF STIFFENED FUSELAGE PANEL WITH LONGITUDINAL CRACK

更新时间：2022-09-22

- DAMAGE TOLERANCE EXPERIMENT AND ANALYSIS OF STIFFENED FUSELAGE PANEL WITH LONGITUDINAL CRACK
- Journal of Mechanical Strength Vol. 39, Issue 6, Pages: 1463-1467(2017)
- 作者机构：
  
  1. 中国飞机强度研究所
- 作者简介：
- 基金信息：
- DOI：10.16579/j.issn.1001.9669.2017.06.034
  CLC：
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CHEN An, WEI YuLong, LIAO JiangHai, et al. DAMAGE TOLERANCE EXPERIMENT AND ANALYSIS OF STIFFENED FUSELAGE PANEL WITH LONGITUDINAL CRACK. [J]. 39(6):1463-1467(2017)
DOI：

CHEN An, WEI YuLong, LIAO JiangHai, et al. DAMAGE TOLERANCE EXPERIMENT AND ANALYSIS OF STIFFENED FUSELAGE PANEL WITH LONGITUDINAL CRACK. [J]. 39(6):1463-1467(2017) DOI： 10.16579/j.issn.1001.9669.2017.06.034.

摘要

对民用飞机含纵向裂纹机身加筋壁板在增压和轴向拉伸联合载荷作用下进行损伤容限试验和数值仿真分析。通过试验深入研究了机身壁板的裂纹扩展规律和剩余强度特性,借助Ansys有限元软件计算了不同裂纹长度下的应力强度因子,对裂纹扩展寿命进行了预测,基于线弹性断裂力学给出了剩余强度特征曲线,并进行了试验结果和计算分析的对比。研究结果表明:数值分析与试验结果吻合良好,可为机身壁板损伤容限设计及评定提供依据。

Abstract

Results from an experimental and analytical study of a curved stiffened aluminum panel subjected to combined internal pressure and axial tension loads are presented. The behaviors of the crack propagation and characteristics of the residual strength for fuselage panel are investigated. Stress intensity factors associated with different crack lengths are analyzed by using ANSYS software,and the crack propagation cycles are predicted. The residual strength curves are calculated based on the linear elastic fracture mechanics by comparison of experimental results. Analysis results agree well with the test results. Both results can provide the bases for the damage tolerance design and assessment of fuselage structure.

关键词

机身壁板纵向裂纹损伤容限试验裂纹扩展剩余强度应力强度因子

Keywords

Fuselage panelLongitudinal crackDamage tolerance experimentCrack propagationResidual strengthStress intensify factor

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