A model is developed herein for predicting the evolution of interface degradation, matrix cracking, and delamination at multiple sites in laminated continuous fiber composite plates subjected to monotonic and/or cyclic mechanical loading. Due to the complicated nature of the many cracks and their interactions, a multi-scale micro-meso-local-global methodology is deployed in order to model all damage modes. Interface degradation is first modeled analytically on the microscale, and the results are homogenized to produce a cohesive zone model that is capable of predicting interface fracture. Subsequently, matrix cracking in the plies is modeled analytically on the meso-scale, and this result is homogenized to produce ply level damage dependent constitutive equations. The evolution of delaminations is considered on the local scale, and this effect is modeled using a three dimensional finite element algorithm. Results of this analysis are homogenized to produce damage dependent laminate equations. Finally, global response of the damaged plate is modeled using a plate finite element algorithm. Evolution of all three modes of damage is predicted via interfacing all four scales into a single multi-scale algorithm that is computationally tenable for use on a desktop computer. Results obtained herein suggest that this model may be capable of accurately predicting complex damage patterns such as that observed at open holes in laminated plates.
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October 1999
Technical Papers
A Computational Model for Predicting Damage Evolution in Laminated Composite Plates
M. L. Phillips,
M. L. Phillips
Aerospace Engineering Department, Texas A&M University, College Station, TX 77843
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C. Yoon,
C. Yoon
Aerospace Engineering Department, Texas A&M University, College Station, TX 77843
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D. H. Allen
D. H. Allen
Aerospace Engineering Department, Texas A&M University, College Station, TX 77843
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M. L. Phillips
Aerospace Engineering Department, Texas A&M University, College Station, TX 77843
C. Yoon
Aerospace Engineering Department, Texas A&M University, College Station, TX 77843
D. H. Allen
Aerospace Engineering Department, Texas A&M University, College Station, TX 77843
J. Eng. Mater. Technol. Oct 1999, 121(4): 436-444 (9 pages)
Published Online: October 1, 1999
Article history
Received:
January 14, 1999
Revised:
June 1, 1999
Online:
November 27, 2007
Citation
Phillips, M. L., Yoon, C., and Allen, D. H. (October 1, 1999). "A Computational Model for Predicting Damage Evolution in Laminated Composite Plates." ASME. J. Eng. Mater. Technol. October 1999; 121(4): 436–444. https://doi.org/10.1115/1.2812399
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