ASSESSMENT METHOD OF THE REPAIRED AIRCRAFT COMPOSITE WING PANEL WITH DISCRETE-SOURCE DAMAGE

CHEN XiangMing; ZHANG AYing; CHAI YaNan; LIU HongWu; WANG LiLi; YU Fei

doi:10.16579/j.issn.1001.9669.2017.02.036

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ASSESSMENT METHOD OF THE REPAIRED AIRCRAFT COMPOSITE WING PANEL WITH DISCRETE-SOURCE DAMAGE

更新时间：2022-09-22

- ASSESSMENT METHOD OF THE REPAIRED AIRCRAFT COMPOSITE WING PANEL WITH DISCRETE-SOURCE DAMAGE
- Journal of Mechanical Strength Vol. 39, Issue 2, Pages: 457-462(2017)
- 作者机构：
  
  1. 中国飞机强度研究所全尺寸飞机结构静力/疲劳航空科技重点实验室
  2. 中航工业第一飞机设计研究院
- 作者简介：
- 基金信息：
- DOI：10.16579/j.issn.1001.9669.2017.02.036
  CLC：
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CHEN XiangMing, ZHANG AYing, CHAI YaNan, et al. ASSESSMENT METHOD OF THE REPAIRED AIRCRAFT COMPOSITE WING PANEL WITH DISCRETE-SOURCE DAMAGE. [J]. 39(2):457-462(2017)
DOI：

CHEN XiangMing, ZHANG AYing, CHAI YaNan, et al. ASSESSMENT METHOD OF THE REPAIRED AIRCRAFT COMPOSITE WING PANEL WITH DISCRETE-SOURCE DAMAGE. [J]. 39(2):457-462(2017) DOI： 10.16579/j.issn.1001.9669.2017.02.036.

摘要

针对含离散源损伤复合材料机翼壁板机械连接修理结构,开展了机械连接修理结构渐进式破坏有限元分析技术的研究和验证。建立了利用梁元耦合解析刚性面模拟螺钉,采用适用于平面应力状态的LaRC05强度准则和B-K准则作为复合材料层板和胶接界面失效判据的机械连接修理结构有限元分析模型。在此基础上,通过编写用户自定义材料子程序(UMAT),实现了材料失效准则与刚度退化方案在商用软件Abaqus中的应用和机械连接修理结构承载能力的求解。计算结果表明,对于大规模螺钉连接的复杂修理结构,所采用的有限元建模和分析方法有效可行。与试验结果相比,结构承载能力数值分析与试验值吻合良好,误差在5%以内,预测的失效模式也与试验结果一致。

Abstract

The progressive damage analysis technique was studied by using finite element method and test validation of the repaired aircraft wing composite panel with discrete-source damage. Firstly,an analysis model adopting the two dimensional LaRC05 and B-K failure criteria was established to indentify the initial damage of composite ply and interface. Then,a user defined subroutine UMAT of material failure criteria and degradation rule based on commercial software ABAQUS was programmed and the load carrying capacity of the repaired aircraft wing composite panel was analyzed. The numerical results indicated that: the FEM analysis method presented in this paper was viable for the large-scale bolted repair structure. The comparison between analysis and test indicates that the load carrying capacity and failure mode of numerical results agree well with test results. The errors of predicted load carrying capacity are within 5%.

关键词

复合材料机翼加筋壁板离散源损伤修理评估方法

Keywords

Composite wingStiffened panelDiscrete-source damageRepairAssessment method

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The First Aircraft Institute of AVIC

Shenyang Aircraft Design ＆ Research Institute

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