A Progressive Damage Model for Predicting Permanent Indentation and Impact Damage in Composite Laminates

Author:

Ji Zhaojie,Guan Zhidong,Li Zengshan

Publisher

Springer Science and Business Media LLC

Subject

Ceramics and Composites

Reference38 articles.

1. AC20-107B. Composite Aircraft Structures. Federal Aviation Administration, 2009. 11–14

2. Pinho, S.T., Iannucci, L., Robinson, P.: Physically-based failure models and criteria for laminated fiber-reinforced composite with emphasis on fibre kinking. Part II: FE implementation. Comps Appl Sci Manuf 37, 767–777 (2006)

3. Falzon, B.G., Apruzzese, P.: Numerical analysis of intralaminar failure mechanisms in composite structures. Part I: FE implementation. Compos Struct 93, 1039–1046 (2011)

4. Falzon, B.G., Apruzzese, P.: Numerical analysis of intralaminar failure mechanisms in composite structures. Part II: Applications. Compos Struct 93, 1047–1053 (2011)

5. Maimí P, Camanho PP, Mayugo JA, Dávila CG. A thermodynamically consistent damage model for advanced composites. Hampton, Virginia: Langley Research Center, National Aeronautic and Space Administration (NASA); 2006. Report No: NASA/TM-2006-214282

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