On failure mechanisms of composite laminates with an open hole subjected to compressive load

Suemasu, Hiroshi; Takahashi, Hisao; Ishikawa, Takashi

doi:10.1016/j.compscitech.2005.07.042

Cited by 86 publications

(44 citation statements)

References 22 publications

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“…Independently of the laminate, the first damage was fibre micro-buckling in the 0º layer. Some accumulation of damage, such as further fibre micro-buckling in the 0º layers and interlaminar delaminations in several interfaces, was observed before the final unstable fracture in the laminate with high interlaminar toughness, while sudden failure occurred in the laminate with low interlaminar toughness [12].…”

Section: Introductionmentioning

confidence: 99%

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Effects of external patch configuration on repaired composite laminates subjected to multi-impacts

Coelho

Reis

Ferreira

et al. 2017

Composite Structures

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Please cite this article as: Santos, R.A.M., Reis, P.N.B., Santos, M.J., Coelho, C.A.C.P., Effect of distance between impact point and hole position on the impact fatigue strength of composite laminates, Composite Structures (2017), doi: http://dx.doi.org/10. 1016/j.compstruct.2017.02.045 This is a PDF file of an unedited manuscript that has been accepted for publication. As a service to our customers we are providing this early version of the manuscript. The manuscript will undergo copyediting, typesetting, and review of the resulting proof before it is published in its final form. Please note that during the production process errors may be discovered which could affect the content, and all legal disclaimers that apply to the journal pertain. In terms of multi-impacts, the damage severity is also very influenced by the distance. For small distances the damage progresses quickly, while three stages can be found for the control samples and for the distance of 20 mm. Effect of distance between impact

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Section: Introductionmentioning

confidence: 99%

“…laminates with an open hole was studied by Suemasu et al [12]. Two types of composite systems were investigated to examine the dependence of failure behaviour on the material properties (such as interlaminar toughness).…”

Section: Introductionmentioning

confidence: 99%

Effects of external patch configuration on repaired composite laminates subjected to multi-impacts

Coelho

Reis

Ferreira

et al. 2017

Composite Structures

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“…Previous experimental results by Suemasu et al [20] serve as a validation for a laminate with an open hole under compression. The experimental results by Chang and Chang [8] and previous predictions by Sleight [21], and Gunel and Kayral [22] are considered in the validation of predictions for a laminate with a hole under tension.…”

Section: Numerical Resultsmentioning

confidence: 99%

“…The validity of this approach is established by considering the published test data and predictions for (1) strength of laminates under various off-axis loading [18,19], (2) strength of laminates with a hole under compression [20], and (3) strength of laminate with a hole under tension, [8,[21][22].…”

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confidence: 99%

Prediction of Composite Laminate Strength Properties Using a Refined Zigzag Plate Element

Barut

Madenci

Tessler

2013

54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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This study presents an approach that uses the refined zigzag element, {2,2} RZE in conjunction with progressive failure criteria to predict the ultimate strength of composite laminates based on only ply-level strength properties. The methodology involves four major steps: (1) Determination of accurate stress and strain fields under complex loading conditions using {2,2} RZE -based finite element analysis, (2) Determination of failure locations and failure modes using the commonly accepted Hashin's failure criteria, (3) Recursive degradation of the material stiffness, and (4) Non-linear incremental finite element analysis to obtain stress redistribution until global failure. The validity of this approach is established by considering the published test data and predictions for (1) strength of laminates under various off-axis loading, (2) strength of laminates with a hole under compression, and (3) strength of laminates with a hole under tension.

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“…Apart from interlaminar toughness, there are other mechanical properties than can benefit from interlaminar reinforcement. Bolt-bearing and open-hole compression failure mechanisms can be caused by interlaminar delamination, fiber microbuckling, etc 1,6 . Complex shapes, including L-shape cured laminates (which is a typical element in aerospace structural components such as angle brackets, co-cured webs, or frames [7]) usually fail by interlaminar delamination via a tensile interlaminar mode.…”

Section: Introductionmentioning

confidence: 99%

Aligned Carbon Nanotube Reinforcement of Aerospace Carbon Fiber Composites: Substructural Strength Evaluation for Aerostructure Applications

Villoria¹,

Ydrefors²,

Hallander³

et al. 2012

53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

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The mechanism of reinforcement is not compliant interlayer creation, but rather is a fiberstitching mechanism, as no increase in interlayer thickness occurs with the nanostitches. Unlike traditional (large-fiber/tow/pin) stitching or z-pinning techniques that damage inplane fibers and reduce laminate in-plane strengths, the nano-scale CNT-based 'stitches' improve in-plane strength, demonstrating the potential of such an architecture for aerospace structural applications. The quality of VACNT transfer to the prepreg laminates has not been optimized and therefore the noted enhancement to strength may be considered conservative. Ongoing work has been undertaken to both improve VACNT transfer and expand the data set. Nomenclature AE= Acoustic Emission CNTs = Carbon Nanotubes

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On failure mechanisms of composite laminates with an open hole subjected to compressive load

Cited by 86 publications

References 22 publications

Effects of external patch configuration on repaired composite laminates subjected to multi-impacts

Effects of external patch configuration on repaired composite laminates subjected to multi-impacts

Prediction of Composite Laminate Strength Properties Using a Refined Zigzag Plate Element

Aligned Carbon Nanotube Reinforcement of Aerospace Carbon Fiber Composites: Substructural Strength Evaluation for Aerostructure Applications

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