Dissertation > Aviation, aerospace > Aviation > Aerospace materials > Metal and non-metallic composite materials

Investigation of Glass Reinforced Aluminum (GLARE) Laminates Bolted Joint

Author CaoZiZhen
Tutor ZhangJiFeng
School Harbin Engineering University
Course Aircraft design
Keywords GLARE laminates bolt joints progressive damage failure modes strength prediction
CLC V257
Type Master's thesis
Year 2013
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Glass reinforced aluminum (GLARE) laminates are hybrid composite structures basedon thin sheets of aluminum alloys and plies of glass-fibre reinforced polymeric materials. Thefibre/metal composite technology combines the advantages of metallic materials and fibrereinforced matrix systems. The fatigue and low strength of metals and weak impact resistanceand reparability of composites can be overcome by the combination. The good properties ofGLARE laminates are attracting more and more attention. To make good use of GLARElaminates in aircraft structures, study of GLARE mechanical joint should be focused on.This paper carried out research on the follows.(1) Experimental design and producingGLARE laminates. To enhance the bonding strength, aluminum layers and glass-reinforcedlayers were bonded together with J133adhesive and the aluminum sheet got a pre-treatmentof phosphoric acid anodizing.(2) An experimental investigation was performed to determinethe failure mode and bearing strength of mechanically fastened bolted single-lap joints underquasi-static tension in Glare laminates. Specimens were divided into four groups, influence ofedge distance to hole diameter (E/D) ratio, width to hole diameter (W/D) ratio, ply orientationand tightening torque on the performances of GLARE bolted single-lap joint were studied.(3)The numerical study was performed by using finite element software ABAQUS. Plasticity inthe aluminum layers, asymmetrical lateral constraint and preload in the bolt were allimplemented in the model. For the glass fibre reinforced epoxy the user subroutine UMATwas employed for description of the progressive damage. Behavior of the delaminationbetween plies of the laminate was described using cohesive interface and the user subroutineUINTER was employed. Very good agreement was achieved between experimental resultsand simulated results.(4) Failure of GLARE laminates with two parallel pin-loaded holes wasanalyzed, and effects of geometric parameters on joint strength were predicted.

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