Details
| Original language | English |
|---|---|
| Title of host publication | AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials |
| Publisher | American Institute of Aeronautics and Astronautics Inc. (AIAA) |
| ISBN (print) | 9781624105326 |
| Publication status | Published - 7 Jan 2018 |
| Event | AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2018 - Kissimmee, United States Duration: 8 Jan 2018 → 12 Jan 2018 |
Publication series
| Name | AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2018 |
|---|---|
| Number | 210049 |
Abstract
Composite laminate stiffened panels are often used in aircraft design for fuselage structures because of their favourable properties such as high strength to weight ratio and high stiffness to weight ratio. In order to assess the failure load of these thin-walled structures and to exploit their reserves, a reliable simulation capability for their postbuckling behaviour required. To perform a realistic failure analysis and to accurately detect the final collapse, material degradation should be taken into account. Global-local approaches are a computationally efficient technique to perform a progressive failure analysis and to examine localized damaged areas in detail. In this paper, an existing two-way coupling global-local approach is extended. The enhanced method allows for consideration of a combination of different damage modes, matrix cracking, fibre damage and debonding between skin and stringer. An accurate exchange of information concerning the damage state between global model and refined local model is performed. From the global to the local model, the displacements are transferred through a submodeling procedure. Afterwards, the degraded material properties obtained from the local model analysis are returned to the global model with the help of a special mapping technique. This mapping tool accounts for the different mesh sizes at both levels. The two-way coupling procedure is illustrated on the basis of 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)
- Civil and Structural Engineering
- Engineering(all)
- Building and Construction
- Engineering(all)
- Mechanics of Materials
- Engineering(all)
- Architecture
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AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials. 210049. ed. American Institute of Aeronautics and Astronautics Inc. (AIAA), 2018. (AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2018; No. 210049).
Research output: Chapter in book/report/conference proceeding › Conference contribution › Research › peer review
}
TY - GEN
T1 - Progressive Failure Analysis of Stiffened Composite Panels Using a Two-Way Loose Coupling Approach Including Intralaminar Failure and Debonding
AU - Akterskaia, Margarita
AU - Jansen, Eelco
AU - Rolfes, Raimund
PY - 2018/1/7
Y1 - 2018/1/7
N2 - Composite laminate stiffened panels are often used in aircraft design for fuselage structures because of their favourable properties such as high strength to weight ratio and high stiffness to weight ratio. In order to assess the failure load of these thin-walled structures and to exploit their reserves, a reliable simulation capability for their postbuckling behaviour required. To perform a realistic failure analysis and to accurately detect the final collapse, material degradation should be taken into account. Global-local approaches are a computationally efficient technique to perform a progressive failure analysis and to examine localized damaged areas in detail. In this paper, an existing two-way coupling global-local approach is extended. The enhanced method allows for consideration of a combination of different damage modes, matrix cracking, fibre damage and debonding between skin and stringer. An accurate exchange of information concerning the damage state between global model and refined local model is performed. From the global to the local model, the displacements are transferred through a submodeling procedure. Afterwards, the degraded material properties obtained from the local model analysis are returned to the global model with the help of a special mapping technique. This mapping tool accounts for the different mesh sizes at both levels. The two-way coupling procedure is illustrated on the basis of 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 design for fuselage structures because of their favourable properties such as high strength to weight ratio and high stiffness to weight ratio. In order to assess the failure load of these thin-walled structures and to exploit their reserves, a reliable simulation capability for their postbuckling behaviour required. To perform a realistic failure analysis and to accurately detect the final collapse, material degradation should be taken into account. Global-local approaches are a computationally efficient technique to perform a progressive failure analysis and to examine localized damaged areas in detail. In this paper, an existing two-way coupling global-local approach is extended. The enhanced method allows for consideration of a combination of different damage modes, matrix cracking, fibre damage and debonding between skin and stringer. An accurate exchange of information concerning the damage state between global model and refined local model is performed. From the global to the local model, the displacements are transferred through a submodeling procedure. Afterwards, the degraded material properties obtained from the local model analysis are returned to the global model with the help of a special mapping technique. This mapping tool accounts for the different mesh sizes at both levels. The two-way coupling procedure is illustrated on the basis of 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=85044570910&partnerID=8YFLogxK
U2 - 10.2514/6.2018-0735
DO - 10.2514/6.2018-0735
M3 - Conference contribution
SN - 9781624105326
T3 - AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2018
BT - AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials
PB - American Institute of Aeronautics and Astronautics Inc. (AIAA)
T2 - AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2018
Y2 - 8 January 2018 through 12 January 2018
ER -