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Influence of Shim Layers on Progressive Failure of a Composite Component in Composite-Aluminum Bolted Joint in Aerospace Structural Assembly

机译:垫片层对航空结构装配中铝复合螺栓连接中复合部件渐进破坏的影响

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摘要

The influence of varying shim layers on the progressive damage/failure of a composite component in a bolted composite-aluminum aerospace structural assembly was investigated using a non-linear three-dimensional (3D)structural solid elements assembled model of a carbon fiber-reinforced polymer(CFRP)-aluminum single-lap joint with a titanium(Ti-6Al-4V)fastener and a washer generated with the commercial finite element(FE)soft-ware package,ABAQUS /Standard.A progressive failure algorithm written in Fortran code with a set of appropri-ate degradation rules was incorporated as a user subroutine in ABAQUS to simulate the non-linear damage behavior of the composite component in the composite-aluminum bolted aerospace structure.The assembled 3D FE model simulated,as well as the specimen for the experimental testing consisted of a carbon-epoxy IMS-977-2 substrate, aluminum alloy 7075-T651 substrate,liquid shim(Hysol EA 9394),solid peelable fiberglass shim,a titanium fas-tener,and a washer.In distinction to previous investigations,the influence of shim layers(liquid shim and solid peelable fiberglass shim)inserted in-between the faying surfaces(CFRP and aluminum alloy substrates)were in-vestigated by both numerical simulations and experimental work.The simulated model and test specimens con-formed to the standard test configurations for both civil and military standards.The numerical simulations correla-ted well with the experimental results and it has been found that:(1)The shimming procedure as agreed upon by the aerospace industry for the resolution of assembly gaps in bolted joints for composite materials is the same for a composite-aluminum structure;liquid shim series(0.3,0.5 and 0.7 mm thicknesses)prolonged the service life of the composite component whereas a solid peelable fiberglass shim most definitely had a better influence on the 0.9 assembly gap compared with the liquid shim;(2)The shim layers considerably influenced the structural strength of the composite component by delaying its ultimate failure thereby increasing its service life;and(3)Increasing the shim layer′s thickness led to a significant corresponding effect on the stiffness but with minimal effect on the ultimate load.
机译:使用非线性三维(3D)结构固体元件组装模型,研究了改变垫片层对螺栓复合 - 铝航空航天枢纽结构组件中复合材料组件中复合部件的渐进式损伤/失效的影响(CFRP) - 用钛(Ti-6Al-4V)紧固件和用商业有限元(Fe)软件包产生的垫圈,ABAQUS / BADYADT.A与商业有限元(FE)软件包,用铝合金,ABAQUS / BROFT.A的储存器一组拟申请者降解规则被用作ABAQUS中的用户子程序,以模拟复合铝螺栓航空航天结构中复合部件的非线性损伤行为。模拟的组装3D FE模型,以及样品实验测试由碳环氧IMS-977-2基板,铝合金7075-T651基板,液体垫片(Hysol EA 9394),固体可剥离玻璃纤维垫片,钛Fas-Tener和垫圈组成。通过数值模拟和实验工作,椎间垫层(液体垫片和固体可剥离玻璃纤维垫片)中插入的垫片层(液体垫片和固体可剥离玻璃纤维垫)的影响。模拟模型和试验标本形成为民事和军事标准的标准测试配置。数值模拟与实验结果相得益彰,有人发现:(1)航空航天行业达成决议案的散发程序复合材料的螺栓接头中的组装间隙对于复合材料 - 铝结构是相同的;液体垫片系列(0.3,0.5和0.7毫米厚度)延长了复合部件的使用寿命,而固体可剥离的玻璃纤维垫绝对有更好与液体垫片相比对0.9装配间隙的影响;(2)垫片层显着影响了复合康科的结构强度通过延迟其最终失败,从而提高其使用寿命;(3)增加垫片层的厚度导致对刚度的显着影响,但对最终负荷影响最小。

著录项

  • 来源
    《南京航空航天大学学报(英文版)》 |2018年第1期|188-202|共15页
  • 作者单位

    Department of Aerospace Manufacturing Engineering,Jiangsu Key Laboratory of Precision and Micro-Manufacturing Technology,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,P.R.China;

    Department of Aerospace Manufacturing Engineering,Jiangsu Key Laboratory of Precision and Micro-Manufacturing Technology,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,P.R.China;

    AVIC Xi'an Aircraft Industry(Group)Company LTD,Xi'an 710089,P.R.China;

    Department of Aerospace Manufacturing Engineering,Jiangsu Key Laboratory of Precision and Micro-Manufacturing Technology,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,P.R.China;

  • 收录信息 中国科学引文数据库(CSCD);中国科技论文与引文数据库(CSTPCD);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类 航空仪表、航空设备;
  • 关键词

  • 入库时间 2022-08-18 02:01:00
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