Failure Analysis of Composite Laminates with Free Edge

Zhou, Si-Ming; Sun, C.T.

doi:10.1007/978-94-009-2544-1_49

Cited by 4 publications

(6 citation statements)

References 1 publication

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“…Evaluating Equation (24) yields the following expression for G: (25) Finally, G can be used in the Griffith fracture criterion to determine whether edge delamination will occur under the given load.…”

Section: Damage Predictionmentioning

confidence: 99%

Characterization of Matrix Crack-Induced Laminate Failure—Part II: Analysis and Verifications

Johnson

Chang

2001

Journal of Composite Materials

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A two-part investigation was performed to study the stiffness response and strength of composite laminates subjected to uniaxial tension. In Part I, experimental testing was performed to characterize the matrix crack-induced damage progression and failure modes in composite laminates under uniaxial tension loading conditions.In Part II, analytical models were developed to account for the damage modes observed in the experimental investigation. Models for matrix crack-induced delamination, matrix crack-induced microcracking, and matrix crack-induced edge delamination were developed. Model predictions were compared with experimental data.The proposed models were integrated and implemented in the computer code, PDCell. The code was then used to predict the stiffness response and failure of composite laminates subjected to tensile loading. Code predictions were used to evaluate the effects of ply orientation, ply group thickness, loading direction, and stacking sequence on laminate tensile strength. The predictions from the code were compared with available test data in the literature.ized through uniaxial tensile testing of finite-width laminate specimens. In

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Section: Damage Predictionmentioning

confidence: 99%

Characterization of Matrix Crack-Induced Laminate Failure—Part II: Analysis and Verifications

Johnson

Chang

2001

Journal of Composite Materials

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“…Clearly, there are some inconsistencies in these proposed mechanisms of failures in composite materials. It is important to note that the high stresses near free edges can easily trigger failure in a laminate 10 . Fractographic analysis of polymer composite materials has been subject of considerable interest in the recent years.…”

Section: Introductionmentioning

confidence: 99%

Fractographic analysis of tensile failures of aerospace grade composites

et al. 2012

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This paper describes fractographic features observed in aerospace composites failed under tensile loads. Unidirectional Carbon Fibre Reinforced Plastic (UD CFRP) and Unidirectional Glass Fibre Reinforced Plastic (UD GFRP) composite specimens were fabricated and tested in tension. The morphology of fractured surfaces was studied at various locations to identify failure mechanism and characteristic fractographic features. CFRP composites displayed transverse crack propagation and the fracture surface showed three distinct regions, viz., crack origin, propagation and final failure. Significant variations in the fractographic features were noticed in crack propagation and final failure regions. Crack propagation region exhibited brittle fracture with chevron lines emanating from the crack origin. The entire crack propagation region exhibited radial marks on the individual fibre broken ends. On the other hand, the final fracture region revealed longitudinal matrix splitting and radial marks in majority of locations, and chop marks at some locations. The change in fracture mode in the final fracture was attributed to superimposition of bending loads. GFRP composites exhibited broom like fracture with extensive longitudinal splitting with radial marks present on individual fibre broken ends. Transverse fracture was observed at a few locations. These fracture features were analyzed and correlated with the loading conditions.

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“…Zhou and Sun [9] observed that the free edge interlaminar shear stress Tn dominates the failure in angle ply [ t 6]ZS laminates of T300/5208 graphite/epoxy composite for angles smaller than 30°. Figure 7 shows the predicted failure stresses by the Tsai-Hill criterion and the present method for the [ t 6]2S AS4/3501-6 graphite/epoxy laminate.…”

Section: Resultsmentioning

confidence: 99%

“…Many researchers have concentrated their efforts on opening mode delamination that is dominated by interlaminar normal stress. Experimental results indicate that if free edge delamination is caused by interlaminar normal stress, the laminate can withstand loads beyond the onset of delamination [9]. On the other hand, the free edge failure caused by the interlaminar shear stresses often results in immediate laminate failure [10].…”

Section: Introductionmentioning

confidence: 98%

A Failure Criterion for Laminates Governed by Free Edge Interlaminar Shear Stress

Joo

Sun

1992

Journal of Composite Materials

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Interlaminar shear stresses in balanced and symmetric laminates with free edges and failure due to these stresses were studied. It was shown that the average interlaminar shear stress τ xz near the free edge is linearly related to the mismatch of the extension-shear coupling of the top and bottom sublaminates separated by the interface of interest. A simple failure criterion based on the mismatch of the extension shear coupling was introduced to predict laminate failure stress and strain. The validity of this criterion was verified by experiments using AS4/3501-6 graphite/epoxy composite laminates.

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Failure Analysis of Composite Laminates with Free Edge

Cited by 4 publications

References 1 publication

Characterization of Matrix Crack-Induced Laminate Failure—Part II: Analysis and Verifications

Characterization of Matrix Crack-Induced Laminate Failure—Part II: Analysis and Verifications

Fractographic analysis of tensile failures of aerospace grade composites

A Failure Criterion for Laminates Governed by Free Edge Interlaminar Shear Stress

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