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.



Key Engineering Materials (Volumes 577-578)

Edited by:

A. Milazzo and M.H. Aliabadi






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




[1] San Diego Composites, SDC fabricating stiffened fuselage test panels for research on blunt impact of commercial Aircraft, http: /www. sdcomposites. com/Media/newsarticle120511. html.

[2] Martin R.H., Delamination failure in a unidirectional curved composite laminate, Contract NASI-18599 (1990).

[3] Calomfirescu M., Hickethier H., Damage tolerance of composite structures in aircraft industry, EADS Defence and Security internal presentation (2010).

[4] Brewer J.C., Failure of graphite/epoxy induced by delamination, PhD Massachusetts Institute of Technology (1988).

[5] Ilyas M., Espinosa Ch., Lachaud F., Michel L., Salaün M., Modelling Aeronautical Composite Laminates Behaviour under Impact using a Saturation Damage and Delamination Continuous Material Model, Key Engineering Materials, Vol. 452-453 (2011).

DOI: 10.4028/

[6] Wimmer G., Kitzmüller W., Pinter G., Wettermann T., Pettermann, H.E., Computational and experimental investigation of delamination in L-shaped laminated composite components, Engineering Fracture Mechanics, Vol. 76 (2009), pp.2810-2820.

DOI: 10.1016/j.engfracmech.2009.06.007

[7] Ko W.L., Jackson R.H., Delamination Multilayer theory for delamination analysis of composite curved bar subjected to end forces and end moments, NASA TM 4139 (1989).

DOI: 10.1007/978-94-009-1125-3_7

[8] Hufenbach, W., Hornig, A., Zhou, B., Langkamp, A., Gude, M., Determination of StrainRate Dependent Through-Thickness Tensile Properties of Textile Reinforced Thermoplastic Composites using LShaped Beam Specimens, Composites Science and Technology (2011).

DOI: 10.1016/j.compscitech.2011.03.018

[9] LSTC, LS-DYNA theory manual, ISBN 0-9788540-0-0 (2006).

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