Details
| Original language | English |
|---|---|
| Pages (from-to) | 240-248 |
| Journal | Composites science and technology |
| Volume | 2010 |
| Issue number | 70 |
| Publication status | Published - 2010 |
| Externally published | Yes |
Abstract
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In: Composites science and technology, Vol. 2010, No. 70, 2010, p. 240-248.
Research output: Contribution to journal › Article › Research › peer review
}
TY - JOUR
T1 - Damage sensitivity of axially loaded stringer-stiffened curved CFRP panels
AU - Lauterbach, S.
AU - Orifici, A.C.
AU - Wagner, W.
AU - Balzani, C.
AU - Abramovich, H.
AU - Thomson, R.
N1 - Funding information: The authors kindly acknowledge the financial support of the European Commission, Priority Aeronautics and Space, Contract AST3-CT-2003-502723, and the Australian Government under both the “Innovation Access Programme – International Science and Technology” and “International Science Linkages” established under the Australian Government’s innovation statement, “Backing Australia’s Ability”. This research is part of the Research Program of the Cooperative Research Centre for Advanced Composite Structures (CRC-ACS) Ltd.
PY - 2010
Y1 - 2010
N2 - A fuselage representative carbon fibre-reinforced multi-stiffener panel is analysed under compressive loading. An intact and pre-damaged configuration is loaded into the postbuckling region and further on until collapse occurs. An analysis tool is applied that includes an approach for predicting interlaminar damage initiation and degradation models for capturing interlaminar damage growth as well as inplane damage mechanisms. Analysis of the intact panel configuration predicts collapse due to fibre fracture in the stiffeners close to the panel clamps, which agrees well with the results from experimental testing. The pre-damaged configuration was proposed containing Teflon-coated layers to generate the initial debonds in the skin-stiffener interface. The outcome of the simulation of this configuration shows that crack growth is not predicted to occur, which agrees with the observations of the experiment. A parametric study is conducted to investigate the effect of the skin-stiffener debond parameters such as length, width and location on crack growth and the collapse behaviour of the panel. It is found that the sensitivity of the panel design to the damage parameters is highly dependent on the postbuckling mode shape or displacement pattern, and particularly the extent to which this influences the conditions at the crack front. More broadly, the analysis tool is shown to be capable of capturing the critical damage mechanisms leading to structural collapse of stiffened composite structures in the postbuckling region.
AB - A fuselage representative carbon fibre-reinforced multi-stiffener panel is analysed under compressive loading. An intact and pre-damaged configuration is loaded into the postbuckling region and further on until collapse occurs. An analysis tool is applied that includes an approach for predicting interlaminar damage initiation and degradation models for capturing interlaminar damage growth as well as inplane damage mechanisms. Analysis of the intact panel configuration predicts collapse due to fibre fracture in the stiffeners close to the panel clamps, which agrees well with the results from experimental testing. The pre-damaged configuration was proposed containing Teflon-coated layers to generate the initial debonds in the skin-stiffener interface. The outcome of the simulation of this configuration shows that crack growth is not predicted to occur, which agrees with the observations of the experiment. A parametric study is conducted to investigate the effect of the skin-stiffener debond parameters such as length, width and location on crack growth and the collapse behaviour of the panel. It is found that the sensitivity of the panel design to the damage parameters is highly dependent on the postbuckling mode shape or displacement pattern, and particularly the extent to which this influences the conditions at the crack front. More broadly, the analysis tool is shown to be capable of capturing the critical damage mechanisms leading to structural collapse of stiffened composite structures in the postbuckling region.
UR - http://www.scopus.com/inward/record.url?eid=2-s2.0-72949118076&partnerID=MN8TOARS
U2 - 10.1016/j.compscitech.2009.10.013
DO - 10.1016/j.compscitech.2009.10.013
M3 - Article
VL - 2010
SP - 240
EP - 248
JO - Composites science and technology
JF - Composites science and technology
SN - 0266-3538
IS - 70
ER -