Delamination behavior of L-shaped composite beam with manufacturing defects
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DOI 10.1007/s12206-020-0823-y
Journal of Mechanical Science and Technology 34 (9) 2020 Original Article DOI 10.1007/s12206-020-0823-y Keywords: · Composite L-shaped beam · Delamination · Manufacturing defects · Pre-crack · Wavy ply
Correspondence to: Kyeongsik Woo [email protected]
Citation: Woo, K., Nega, B. F., Cairns, D. S., Lua, J. (2020). Delamination behavior of Lshaped composite beam with manufacturing defects. Journal of Mechanical Science and Technology 34 (9) (2020) ?~?. http://doi.org/10.1007/s12206-020-0823-y
Received March 17th, 2020 Revised
June 23rd, 2020
Accepted July 13th, 2020 † Recommended by Editor Seungjae Min
Delamination behavior of L-shaped composite beam with manufacturing defects Kyeongsik Woo1, Biruk F. Nega2, Douglas S. Cairns3 and Jim Lua4 1
2
School of Civil Engineering, Chungbuk National University, Cheongju, Korea, Department of Mechani3 cal, Materials and Manufacturing Engineering, University of Nottingham, Ningbo, China, Department of 4 Mechanical & Industrial Engineering, Montana State University, Bozeman, MT, USA, Global Engineering and Materials, Inc., Princeton, NJ, USA
Abstract
Composite structures are more susceptible to manufacturing defects than conventional materials. Fiber misalignment, cracks, and voids are typical types of manufacturing defects in laminated composites. Defects can greatly reduce structural integrity and load carrying capacity, so their effects on material and structural strengths must be understood. In this paper, the effect of manufacturing defects on the progressive delamination behavior was studied for carbon/epoxy composite laminated L-beam under four-point bending test conditions. The defects of wavy plies and pure resin that had flowed out were characterized from surface photography and then transformed into finite element modeling using semi-automatic approach to which pre-delamination and void were included. Next, progressive failure analyses were performed with the interface delamination and matrix direction failure accounted for by cohesive zone modeling. Numerical results were examined focusing on the effects of defects on the peak load reduction and the variation of delamination pattern. The stacking sequence effect was also investigated.
1. Introduction
© The Korean Society of Mechanical Engineers and Springer-Verlag GmbH Germany, part of Springer Nature 2020
In recent years, advanced composite materials have been extensively used in the aerospace, military, and automotive industries to replace large portions of metallic parts. They are favored over conventional metallic materials for their high strength-to-weight ratio, which is the primary criterion of concern for weight reduction. Even though composite materials offer superior performance, they are also susceptible to defects induced by the manufacturing process. The current practice in the design of composite structures adopts the metallic part design philosophy of using the same safety factor despite the fact that composite materials are far more prone to uncertaintie
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