A Computational Model for Predicting Damage Evolution in Laminated Composite Plates

[+] Author and Article Information
M. L. Phillips, C. Yoon, D. H. Allen

Aerospace Engineering Department, Texas A&M University, College Station, TX 77843

J. Eng. Mater. Technol 121(4), 436-444 (Oct 01, 1999) (9 pages) doi:10.1115/1.2812399 History: Received January 14, 1999; Revised June 01, 1999; Online November 27, 2007


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.

Copyright © 1999 by The American Society of Mechanical Engineers
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