Numerical Prediction of Damage Interaction during L-Shaped Laminated Composite Structures Unfolding

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The Low through-the-Thickness Strengths of Composites make them Prone to Delamination and Brutal Rupture. for Primary Aircraft Structural Components, it is Necessary to Predict Failure with Adequate Criteria for any Structure of Various Thicknesses and in Zones of Material or Geometric Discontinuities. the Purpose of the Present Work is to Evaluate the Ability of our Continuous Damage Model to Predict at which Interface Delamination will Occur in any Geometrical or Material Configuration. Numerical Predictions of Delamination Onset Computed by our CDM Model Show a Good Agreement with Theoretical Estimations and Experimental Results of an L-Shape Structure Reference Case. Comparisons between 2D and 3D Models Show no Effect of Free Boundaries on Delamination Onset and Growth.

Info:

Periodical:

Key Engineering Materials (Volumes 577-578)

Edited by:

A. Milazzo and M.H. Aliabadi

Pages:

461-464

DOI:

10.4028/www.scientific.net/KEM.577-578.461

Citation:

C. Espinosa et al., "Numerical Prediction of Damage Interaction during L-Shaped Laminated Composite Structures Unfolding", Key Engineering Materials, Vols. 577-578, pp. 461-464, 2014

Online since:

September 2013

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$35.00

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