Details
| Original language | English |
|---|---|
| Pages (from-to) | 3648-3657 |
| Journal | Engineering fracture mechanics |
| Volume | 2010 |
| Issue number | 77 |
| Publication status | Published - 2010 |
| Externally published | Yes |
Abstract
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In: Engineering fracture mechanics, Vol. 2010, No. 77, 2010, p. 3648-3657.
Research output: Contribution to journal › Article › Research › peer review
}
TY - JOUR
T1 - Prediction of the postbuckling response of composite airframe panels including ply failure
AU - Wagner, W.
AU - Balzani, C.
N1 - Funding information: COCOMAT. Specific targeted research project co-funded by the European Commission, priority aeronautics and space, 6th framework program, Contract No. AST3–CT–2003–502723. URL < http://www.cocomat.de >. The authors kindly acknowledge the financial support of the European Commission, Priority Aeronautics and Space, Contract AST3-CT-2003-502723. The authors further thank the DLR for providing test results, ARAMIS pictures, and photographs of the COCOMAT panel P29. The information in this paper is provided as is and no guarantee or warranty is given that the information is fit for any particular purpose. The user thereof uses the information at its sole risk and liability.
PY - 2010
Y1 - 2010
N2 - Future design scenarios aim to allow buckling in composite airframe panels. Reliable simulation procedures should be able to capture the postbuckling elastic as well as the inelastic response associated with damage. Damage in composite laminates in terms of ply failure may primarily occur as fiber fracture or matrix cracking. This paper presents a model which is able to capture both geometrical and material nonlinearity. It bases on the finite element formulation of a layered, iso-parametric, quadrilateral shell element which allows for an arbitrary reference surface as well as an arbitrary stacking sequence. Geometrical nonlinearity is accounted for by utilizing Green strains and second Piola–Kirchhoff stresses. Material nonlinearity is considered via a layerwise ideally brittle damage model. The model is applied to a buckling test of a stringer-stiffened composite airframe panel. The numerical results are compared with an experiment proving the applicability of the proposed concept.
AB - Future design scenarios aim to allow buckling in composite airframe panels. Reliable simulation procedures should be able to capture the postbuckling elastic as well as the inelastic response associated with damage. Damage in composite laminates in terms of ply failure may primarily occur as fiber fracture or matrix cracking. This paper presents a model which is able to capture both geometrical and material nonlinearity. It bases on the finite element formulation of a layered, iso-parametric, quadrilateral shell element which allows for an arbitrary reference surface as well as an arbitrary stacking sequence. Geometrical nonlinearity is accounted for by utilizing Green strains and second Piola–Kirchhoff stresses. Material nonlinearity is considered via a layerwise ideally brittle damage model. The model is applied to a buckling test of a stringer-stiffened composite airframe panel. The numerical results are compared with an experiment proving the applicability of the proposed concept.
KW - airframe panel
KW - composite
KW - failure analysis
KW - finite element method
KW - ply failure
KW - postbuckling
UR - http://www.scopus.com/inward/record.url?eid=2-s2.0-78649477256&partnerID=MN8TOARS
U2 - 10.1016/j.engfracmech.2010.05.009
DO - 10.1016/j.engfracmech.2010.05.009
M3 - Article
VL - 2010
SP - 3648
EP - 3657
JO - Engineering fracture mechanics
JF - Engineering fracture mechanics
SN - 0013-7944
IS - 77
ER -