Prediction of Transverse Cracking and Stiffness Reduction in Cross-Ply Laminated Composites

Lim, Sg; Hong, Chang Sun

doi:10.1177/002199838902300704

Cited by 153 publications

(56 citation statements)

References 21 publications

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“…A number of factors such as the constraining effect of neighboring plies, ply thickness, inadequacy of the failure criteria, inaccuracies in the estimation of residual stress, insufficient data on transverse strengths and stress for the onset of transverse crack initiation may contribute to the discrepancy between prediction and experiment. A fracture mechanics approach, which accounts for some of the above factors, is currently being explored using analytical models [8][9] in conjunction with additional experimental data.…”

Section: Onset Of Transverse Crackingmentioning

confidence: 99%

Polymer Matrix Composite (PMC) Damage Tolerance and Repair Technology

Kim¹

2001

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The public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. The application of composites in space structures such as reusable launch vehicles requires a detailed understanding of their mechanical behavior and damage resistance in the service environment. Experimental and analytical studies were conducted on IM7/977-3, a graphite-toughened epoxy, to characterize the influence of cryogenic service temperatures on the strength, modulus, and fracture of this material system, and on transverse crack initiation in cross-ply laminates at 23, -129, and -196 °C. Transverse tensile and shear strengths and moduli increased at the cryogenic test temperatures while strain to failure decreased, denoting increased brittleness. The stress for the onset of transverse cracking decreased substantially at cryogenic temperatures, due primarily to an increase in the curing residual stresses. Laminated plate theory, in conjunction with maximum stress criteria, appears to overestimate the onset of the transverse cracking in this laminate. REPORT DATE (DD-MM-YY) EXECUTIVE SUMMARYThe application of composites in space structures, such as reusable launch vehicles (RLVs), requires a detailed understanding of their mechanical behavior and damage resistance in the service environment. Experimental and analytical studies were conducted on IM7/977-3, a toughened graphite/epoxy, to characterize the influence of cryogenic service temperatures on the strength, modulus, and fracture of this material system, and on transverse crack initiation in cross-ply laminates at 23, -129, and -196°C. Transverse tensile and shear strengths and moduli increased at the cryogenic test temperatures while strain to failure decreased, denoting increased brittleness. The stress for the onset of transverse cracking decreased substantially at cryogenic temperatures, due primarily to an increase in the curing residual stresses. Laminated plate theory, in conjunction with maximum stress criteria, appears to overestimate the onset of the transverse cracking in this laminate.

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Section: Onset Of Transverse Crackingmentioning

confidence: 99%

Polymer Matrix Composite (PMC) Damage Tolerance and Repair Technology

Kim¹

2001

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“…There are several models to describe the matrix crack [9][10][11][12][13][14][15][16][17][18], in which the shear-lag model [9,[12][13][14][15][16][17][18] is one of the effective approaches to solve the stress and strain fields in the interior of composites with matrix crack uniformly distributed throughout the length of beam. Highsmith and Reifsnider [9] proposed a one-dimensional (1-D) shear-lag model based on the assumption that the shear stain acted only in a thin resin-rich region.…”

Section: Introductionmentioning

confidence: 99%

Nonlinear vibration of matrix cracked laminated beams containing carbon nanotube reinforced composite layers in thermal environments

Fan

Wang

2015

Composite Structures

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“…[1][2][3] O'Brien et al 4 and Charewicz and Daniel 5 have examined the fatigue behavior of laminates and proposed lifetime prediction models based on fatigue factors such as increased matrix cracking, delamination growth, and stiffness loss. Ogin et al 6,7 and Lim and Hong 8 have modeled the stiffness reduction in composites due to the effects of matrix cracking. Laws and Dvorak 9 have investigated the progression of matrix cracking as well as stiffness loss due to transverse cracking.…”

Section: Introductionmentioning

confidence: 99%

Lamb wave assessment of fatigue and thermal damage in composites

Michael

Barry

Prosser

1998

The Journal of the Acoustical Society of America

102

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Among the various techniques available, ultrasonic Lamb waves offer a convenient method of evaluating composite materials. Since the Lamb wave velocity depends on the elastic properties of a structure, an effective tool exists to monitor damage in composites by measuring the velocity of these waves. Lamb wave measurements can propagate over long distances and are sensitive to the desired in-plane elastic properties of the material. This paper describes two studies which monitor fatigue damage and two studies which monitor thermal damage in composites using Lamb waves. In the fatigue studies, the Lamb wave velocity is compared to modulus measurements obtained using strain gage measurements in the first experiment and the velocity is monitored along with the crack density in the second. In the thermal damage studies, one examines samples which were exposed to varying temperatures for a three minute duration and the second includes rapid thermal damage in composites by intense laser beams. In all studies, the Lamb wave velocity is demonstrated to be an excellent method to monitor damage in composites.

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Prediction of Transverse Cracking and Stiffness Reduction in Cross-Ply Laminated Composites

Cited by 153 publications

References 21 publications

Polymer Matrix Composite (PMC) Damage Tolerance and Repair Technology

Polymer Matrix Composite (PMC) Damage Tolerance and Repair Technology

Nonlinear vibration of matrix cracked laminated beams containing carbon nanotube reinforced composite layers in thermal environments

Lamb wave assessment of fatigue and thermal damage in composites

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