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doi:10.16579/j.issn.1001.9669.2021.01.009

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更新时间：2022-09-22

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- Journal of Mechanical Strength Issue 1, Pages: 63-70(2021)
- 作者机构：
  
  1. 中国民航大学航空工程学院
  2. 北京航空航天大学航空科学与工程学院
- 作者简介：
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- DOI：10.16579/j.issn.1001.9669.2021.01.009
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[J]. Journal of Mechanical Strength (1):63-70(2021)
DOI：

[J]. Journal of Mechanical Strength (1):63-70(2021) DOI： 10.16579/j.issn.1001.9669.2021.01.009.

摘要

为研究不同修理方法以及不同损伤尺寸对复合材料层合板拉伸性能的影响,针对复合材料飞机蒙皮,设计了无损板、60 mm与30 mm损伤孔径的胶接修理板和胶铆混合修理板五组试验件,并对这五组结构件进行静强度拉伸试验及失效机理分析。建立试验件的三维有限元仿真模型,分析无损板和四组修理件的破坏强度、破坏模式、应力分布、应力大小和危险部位。结果证明,胶铆混合修理可以改变复合材料修理结构件的应力分布,并有效降低危险部位的应力集中,改善结构的强度恢复率。

Abstract

In order to study the influence of different repair methods and different damage sizes on the tensile properties of composite laminates,experimental investigation on static tensile strength was designed and carried out in this paper with five groups of test specimens,including no-damage specimens,adhesive repair specimens and adhesive-rivet hybrid repair specimens with 60 mm and 30 mm circular hole damage for composite aircraft skin.The three-dimensional finite element simulation models of the test specimens were established,to analyze the difference between the five groups of specimens in terms of failure strength,failure mode,stress values and distribution,and critical sites.The results show that the adhesive-rivet hybrid repair method is a better choice which changes the stress distribution of composite repaired parts,reduces the stress concentration effectively in the critical sites,and improves the strength recovery rate of the structure.

关键词

复合材料胶铆混合修理拉伸强度有限元法应力分布

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DOI：10.16579/j.issn.1001.9669.2021.01.009

摘要

Abstract

关键词

Keywords

references