Albouy, W.

Hirsekorn, M.

Laurin, F.

Maire, J.-F.

Nicol, M.

Treutenaere, S.

Scipedia

8th ECCOMAS Thematic Conference on the Mechanical Response of Composites: COMPOSITES 2021M. Fagerström & G. Catalanotti (Editors)MODELLING THE INFLUENCE OF THE STACKING ORDER ONDAMAGE IN LAMINATED COMPOSITESM. Nicol1,2∗, F. Laurin1, M. Hirsekorn1, J.-F. Maire1, W. Albouy2, S. Treutenaere21 ONERA, DMAS, Université Paris-Saclay F-92320 Châtillon, France2 Safran Composites, a technology platform of Safran Tech, 33 avenue de la gare, Itteville, France∗ matthieu.nicol@safrangroup.comComposite materials, especially unidirectional carbon fiber reinforced polymers, are massivelyused in primary aircraft structures as a lightweight alternative to metal alloys. In industrialapplications, a composite laminate layup must comply with numerous design guidelines [1]which restrict the possible stacking sequences at the cost of possibly better layups. Thus, a cur-rent challenge is the development of damage models that take into account the influence of thestacking sequence on the mechanical performance of the composite. Currently, models at theply scale are the most suitable for an industrial use due to their good predictive capabilities at arelatively low computational cost. Yet, they are not able to predict the damage coupling betweenadjacent plies and the influence of the laminate stacking order on the tensile strength [2, 3]. Tounderstand the underlying mechanisms, a discrete damage model is proposed: an automaticcrack insertion method is built to obtain complete freedom on the location and orientation ofthe cracks inserted in a finite element mesh (Figure 1). A method based on finite fracture me-chanics, is used to compare damaged configurations for different stacking orders and concludeon the more energetically favorable one. The approach is first validated on well known results(e.g. ply thickness effect on damage). It is then used to study the damage coupling betweenplies and analyze the effect of the stacking order on laminate damage and failure.(a)(b)(c)-132233σ22002−602−602006060Figure 1: Discrete crack insertion in order to compare two laminates: (a) mesh (transparent: inserted cracks);resulting σ22 field for (b) laminate [02/−602/60]s and (c) laminate [0/−602/0/60]s.References[1] Composite Materials Handbook - Volume 3: Polymer matrix composites, materials usage,design and analysis. Military Handbook MIL-HDBK-17-3F, U.S. Department of Defense,2002.[2] T. Yokozeki, T. Aoki, and T. Ishikawa. Transverse cracking in CFRP laminates with an-gled plies. In Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures,Structural Dynamics and Materials Conference, volume 1, 2002.[3] C. Huchette. Analyse multiéchelle des interactions entre fissurations intralaminaire et in-terlaminaire dans les matériaux composites stratifiés. Doctorate thesis, Université Paris VI,2005.

Modelling the Influence of The Stacking Order on Damage in Laminated Composites

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Modelling the Influence of The Stacking Order on Damage in Laminated Composites

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