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 -