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Influence of Shim Layers on Progressive Failure of a composite Componentin composite-aluminum Bolted Joint in Aerospace Structural Assembly

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Transactions of Nanjing University of Aeronautics and Astronautics 2018年第1期35卷 188-202页

作者： Cephas Yaw Attahu An Luling Li Zhaoqing Gao Guoqiang Department of Aerospace Manufacturing Engineering Jiangsu Key Laboratory of Precision and Micro-Manufacturing TechnologyNanjing University of Aeronautics and AstronauticsNanjing 210016P.R.China AVIC Xi′an Aircraft Industry(Group)Company LTD Xi′an 710089P.R.China

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(3 D)structural solid elements assembled model of a carbon fiber-reinforced polymer(CFRP)-aluminum single-lap joint with a titanium(Ti-6 Al-4 V)fastener and a washer generated with the commercial finite element(FE)software package,ABAQUS/Standard.A progressive failure algorithm written in Fortran code with a set of appropriate 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 *** assembled 3 DFE 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 fastener,and a *** 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 investigated by both numerical simulations and experimental *** simulated model and test specimens conformed to the standard test configurations for both civil and military *** numerical simulations correlated 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 b

关键词： composite-aluminum progressive failure modeling finite element modeling single-lap bolted joint shimming aerospace structures

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