CDM MODEL FOR INTRALAMINAR PROGRESSIVE DAMAGE ANALYSIS OF COMPOSITE LAMINATES

Wu Yitao; Yao Weixing; Wu Fuqiang

doi:10.6052/0459-1879-13-106

Volume 46 Issue 1

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Chinese Journal of Theoretical and Applied Mechanics > 2014 > 46(1): 94-104. > DOI: 10.6052/0459-1879-13-106 CSTR: 32045.14.0459-1879-13-106

Wu Yitao, Yao Weixing, Wu Fuqiang. CDM MODEL FOR INTRALAMINAR PROGRESSIVE DAMAGE ANALYSIS OF COMPOSITE LAMINATES[J]. Chinese Journal of Theoretical and Applied Mechanics, 2014, 46(1): 94-104. DOI: 10.6052/0459-1879-13-106

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CDM MODEL FOR INTRALAMINAR PROGRESSIVE DAMAGE ANALYSIS OF COMPOSITE LAMINATES

1.
Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2. State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Funds: The project was supported by the National Natural Science Foundation of China(11202098) and the Priority Academic Program Development of Jiangsu Higher Education Institutions.

Received Date: April 02, 2013
Revised Date: June 30, 2013

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Abstract

Abstract

Based on continuum damage mechanics (CDM), a model was proposed for predicting intralaminar progressive damage of composite laminates, including damage description, damage model judgment and damage evolution. Four different damage modes existent within lamina, namely, fiber tension fracture (FFT), fiber compression fracture (FFC), inter fiber tension fracture (IFFT) and inter fiber compression fracture (IFFC), were considered, and damage state variables corresponding to these four modes were also defined. Material constitutive relationship being in the damaged states in the material principal axes was derived compared to that of undamaged states. The onset of the damage was estimated with Puck's criteria and the evolution of the damage was controlled by the strain energy release density within the characteristic length. Assuming that the material was exhibited linear strain-softening behavior, a new damage evolution law associating damage state variables with equivalent strain on fracture plane was established in this paper. The proposed model can predict damage initiation, damage evolution and final failure of composite laminates. Failure analyses of [45/0/-45/90]_2S notched laminates under tension and compression were performed with the present model and showed that it is capable to predict the strength of the composite laminate and analyze the failure process.
- composite laminate,
- material constitutive relation,
- progressive damage evolution,
- puck criteria

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