Details
| Original language | English |
|---|---|
| Pages (from-to) | 3078-3089 |
| Number of pages | 12 |
| Journal | AIAA journal |
| Volume | 57 |
| Issue number | 7 |
| Early online date | 21 Apr 2019 |
| Publication status | Published - Jul 2019 |
Abstract
Composite laminate stiffened panels are often used in aircraft fuselage design because of their favorable properties. To assess the failure load of these thin-walled structures and to exploit their reserves, a reliable simulation capability for their postbuckling behavior is often necessary. To perform a realistic failure analysis and to accurately detect final collapse, material degradation should be considered. Global-local approaches are computationally efficient techniques to perform a progressive failure analysis and to examine localized damaged areas in detail. In this paper, a two-way coupling global-local approach is presented, including a combination of different damage modes, such as matrix cracking, fiber damage, and skin-stringer debonding. An accurate exchange of information concerning the damage state between global and refined local models is performed. From the global to the local model, the displacements are transferred through a submodeling procedure. Afterward, the degraded material properties obtained from the local model analysis are returned to the global model with a special mapping technique that accounts for the different mesh sizes at the two levels. The two-way coupling procedure is applied to the progressive failure analysis of a one-stringer composite panel loaded in compression. Finally, the numerical results of the procedure are compared with experimental results.
ASJC Scopus subject areas
- Engineering(all)
- Aerospace Engineering
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In: AIAA journal, Vol. 57, No. 7, 07.2019, p. 3078-3089.
Research output: Contribution to journal › Article › Research › peer review
}
TY - JOUR
T1 - Progressive Failure Analysis Using Global-Local CouplingIncluding Intralaminar Failure and Debonding
AU - Akterskaia, Margarita
AU - Jansen, Eelco
AU - Hallett, Stephen R.
AU - Weaver, Paul M.
AU - Rolfes, Raimund
N1 - Funding information: The research leading to these results has received funding from European Union’s Horizon 2020 research and innovation program (FULLCOMP/2015-2019) under Marie Sklodowska-Curie actions grant agreement number 642121. The provided financial support is gratefully acknowledged by the authors. Paul M. Weaver would like to thank Science Foundation Ireland for funding VARICOMP (15/RP/ 2773) under its Research Professor scheme.
PY - 2019/7
Y1 - 2019/7
N2 - Composite laminate stiffened panels are often used in aircraft fuselage design because of their favorable properties. To assess the failure load of these thin-walled structures and to exploit their reserves, a reliable simulation capability for their postbuckling behavior is often necessary. To perform a realistic failure analysis and to accurately detect final collapse, material degradation should be considered. Global-local approaches are computationally efficient techniques to perform a progressive failure analysis and to examine localized damaged areas in detail. In this paper, a two-way coupling global-local approach is presented, including a combination of different damage modes, such as matrix cracking, fiber damage, and skin-stringer debonding. An accurate exchange of information concerning the damage state between global and refined local models is performed. From the global to the local model, the displacements are transferred through a submodeling procedure. Afterward, the degraded material properties obtained from the local model analysis are returned to the global model with a special mapping technique that accounts for the different mesh sizes at the two levels. The two-way coupling procedure is applied to the progressive failure analysis of a one-stringer composite panel loaded in compression. Finally, the numerical results of the procedure are compared with experimental results.
AB - Composite laminate stiffened panels are often used in aircraft fuselage design because of their favorable properties. To assess the failure load of these thin-walled structures and to exploit their reserves, a reliable simulation capability for their postbuckling behavior is often necessary. To perform a realistic failure analysis and to accurately detect final collapse, material degradation should be considered. Global-local approaches are computationally efficient techniques to perform a progressive failure analysis and to examine localized damaged areas in detail. In this paper, a two-way coupling global-local approach is presented, including a combination of different damage modes, such as matrix cracking, fiber damage, and skin-stringer debonding. An accurate exchange of information concerning the damage state between global and refined local models is performed. From the global to the local model, the displacements are transferred through a submodeling procedure. Afterward, the degraded material properties obtained from the local model analysis are returned to the global model with a special mapping technique that accounts for the different mesh sizes at the two levels. The two-way coupling procedure is applied to the progressive failure analysis of a one-stringer composite panel loaded in compression. Finally, the numerical results of the procedure are compared with experimental results.
UR - http://www.scopus.com/inward/record.url?scp=85065562886&partnerID=8YFLogxK
U2 - 10.2514/1.J057677
DO - 10.2514/1.J057677
M3 - Article
AN - SCOPUS:85065562886
VL - 57
SP - 3078
EP - 3089
JO - AIAA journal
JF - AIAA journal
SN - 0001-1452
IS - 7
ER -