Details
| Original language | English |
|---|---|
| Pages (from-to) | 683-703 |
| Journal | International Journal of Structural Stability and Dynamics |
| Volume | 2010 |
| Issue number | 10 (4) |
| Publication status | Published - 2010 |
| Externally published | Yes |
Abstract
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In: International Journal of Structural Stability and Dynamics, Vol. 2010, No. 10 (4), 2010, p. 683-703.
Research output: Contribution to journal › Article › Research › peer review
}
TY - JOUR
T1 - Numerical treatment of damage propagation in axially compressed composite airframe panels
AU - Balzani, C.
AU - Wagner, W.
N1 - Funding information: This work is supported by the European Commission, Priority Aeronautics and Space, Contract AST3-CT-2003-502723. The ¯nancial support is greatefully
PY - 2010
Y1 - 2010
N2 - In the design phase of stringer-stiffened composite airframe panels, it is a key issue to exploit material reserves as far as possible to create lighter and safer aircraft. A recent approach is to apply postbuckling design – standard for metallic panels – also to composite parts. This work focusses on the development of a simulation procedure which accurately predicts the postbuckling response of composite panels while accounting for damage propagation. For this purpose we employ a robust shell element formulation which allows for arbitrary stacking sequences as well as a variable location of the reference plane. A ply discount model is incorporated to account for intralaminar damage growth. The cohesive zone approach is implemented in a so-called interface element to predict interlaminar damage growth, respective skinstringer separation. The numerical model is validated via a numerical example with experimental evidence.
AB - In the design phase of stringer-stiffened composite airframe panels, it is a key issue to exploit material reserves as far as possible to create lighter and safer aircraft. A recent approach is to apply postbuckling design – standard for metallic panels – also to composite parts. This work focusses on the development of a simulation procedure which accurately predicts the postbuckling response of composite panels while accounting for damage propagation. For this purpose we employ a robust shell element formulation which allows for arbitrary stacking sequences as well as a variable location of the reference plane. A ply discount model is incorporated to account for intralaminar damage growth. The cohesive zone approach is implemented in a so-called interface element to predict interlaminar damage growth, respective skinstringer separation. The numerical model is validated via a numerical example with experimental evidence.
KW - composite panel
KW - damage growth
KW - postbuckling design
UR - http://www.scopus.com/inward/record.url?eid=2-s2.0-77955668120&partnerID=MN8TOARS
U2 - 10.1142/S0219455410003683
DO - 10.1142/S0219455410003683
M3 - Article
VL - 2010
SP - 683
EP - 703
JO - International Journal of Structural Stability and Dynamics
JF - International Journal of Structural Stability and Dynamics
SN - 0219-4554
IS - 10 (4)
ER -