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Composite laminates

About: Composite laminates is a research topic. Over the lifetime, 10087 publications have been published within this topic receiving 208227 citations.


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Journal ArticleDOI
TL;DR: In this paper, the strength of anisotropic composite materials subjected to any state of combined stress, predicted from basic strength characteristics of unidirectional layer, is estimated from the basic strength of composite materials.
Abstract: Strength of anisotropic composite materials subjected to any state of combined stress, predicted from basic strength characteristics of unidirectional layer

503 citations

Journal ArticleDOI
TL;DR: In this article, a three-dimensional finite element model is developed to predict damage progression and strength of mechanically fastened joints in carbon fiber-reinforced plastics that fail in the bearing, tension and shear-out modes.
Abstract: A three-dimensional finite element model is developed to predict damage progression and strength of mechanically fastened joints in carbon fibre-reinforced plastics that fail in the bearing, tension and shear-out modes. The model is based on a three-dimensional finite element model, on a three-dimensional failure criterion and on a constitutive equation that takes into account the effects of damage on the material elastic properties. This is accomplished using internal state variables that are functions of the type of damage. This formulation is used together with a global failure criterion to predict the ultimate strength of the joint. Experimental results concerning damage progression, joint stiffness and strength are obtained and compared with the predictions. A good agreement between experimental results and numerical predictions is obtained.

480 citations

Journal ArticleDOI
TL;DR: In this paper, the authors investigate the low velocity impact load level at which a composite laminate will delaminate and find that a sudden load drop occurs due to specimen stiffness loss as a result of laminate level damage.
Abstract: An investigation of the low velocity impact load level at which a composite laminate will delaminate is presented. The delamination threshold load is described as the load level, obtained from the load–time history or load–displacement plot, at which a sudden load drop occurs due to specimen stiffness loss as a result of laminate level damage. Approximately 500 low velocity impact load–time histories from the Air Force Research Laboratory (AFRL) Low Velocity Impact Database are used to investigate the delamination threshold load. The database contains laminate impact test data for graphite/epoxy (AS4/3501-6), graphite/PEEK (AS4/APC-2), and graphite/BMI (IM7/5260) material systems. The delamination threshold load observations are compared to C-scan damage measurements of impacted specimens to determine if the sudden load drop corresponds to delamination development.

477 citations

Journal ArticleDOI
TL;DR: In this article, the impact damage of composite laminates in the form of intra-and inter-laminar cracking was modelled using stress-based criteria for damage initiation, and fracture mechanics techniques to capture its evolution.

476 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
2023240
2022527
2021532
2020477
2019479
2018496