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

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

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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.

composite-aluminumprogressive failure modelingfinite element modelingsingle-lap bolted jointshimmingaerospace structures

Cephas Yaw Attahu、An Luling、Li Zhaoqing、Gao Guoqiang

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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

authors wish to acknowledge the Innovation Foun-dation of National Research Center for Commercial Aircraft Manufacturing EngJiangsu Key Laboratory of Preci-sion and Micro-Manufacturing Technology for the provision of financial support

SAMC13-JS-13-021

2018

南京航空航天大学学报(英文版)
南京航空航天大学

南京航空航天大学学报(英文版)

CSTPCDCSCDEI
影响因子：0.279
ISSN：1005-1120
年,卷(期)：2018.35(1)
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