Abstract
It has been found that load state plays an important role in crack growth rates in fibre/metal laminates. It is expected that material anisotropy is a major cause, and that residual strength of reinforced panels may be affected. Accordingly, an extension of the displacement compatibility method of damage tolerance analysis is presented. The present work accounts for material anisotropy and panel load condition. Comparisons with finite element results show that the extended displacement compatibility method gives accurate stress intensity results for anisotropic panels under tension and under shear loading. The stress intensities obtained using the displacement compatibility method have been used in conjunction with material R-curves to calculate residual strength curves of stiffened panels.
| Original language | English (US) |
|---|---|
| Pages (from-to) | 2809-2818 |
| Number of pages | 10 |
| Journal | Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference |
| Volume | 4 |
| State | Published - Jan 1 1997 |
| Event | Proceedings of the 1997 38th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Part 4 (of 4) - Kissimmee, FL, USA Duration: Apr 7 1997 → Apr 10 1997 |
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All Science Journal Classification (ASJC) codes
- Architecture
- Materials Science(all)
- Aerospace Engineering
- Mechanics of Materials
- Mechanical Engineering
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Damage tolerance modelling of fibre/metal laminate fuselage structures. / Langelaan, Jack W.; Kok, Leo J.J.
In: Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, Vol. 4, 01.01.1997, p. 2809-2818.Research output: Contribution to journal › Conference article
TY - JOUR
T1 - Damage tolerance modelling of fibre/metal laminate fuselage structures
AU - Langelaan, Jack W.
AU - Kok, Leo J.J.
PY - 1997/1/1
Y1 - 1997/1/1
N2 - It has been found that load state plays an important role in crack growth rates in fibre/metal laminates. It is expected that material anisotropy is a major cause, and that residual strength of reinforced panels may be affected. Accordingly, an extension of the displacement compatibility method of damage tolerance analysis is presented. The present work accounts for material anisotropy and panel load condition. Comparisons with finite element results show that the extended displacement compatibility method gives accurate stress intensity results for anisotropic panels under tension and under shear loading. The stress intensities obtained using the displacement compatibility method have been used in conjunction with material R-curves to calculate residual strength curves of stiffened panels.
AB - It has been found that load state plays an important role in crack growth rates in fibre/metal laminates. It is expected that material anisotropy is a major cause, and that residual strength of reinforced panels may be affected. Accordingly, an extension of the displacement compatibility method of damage tolerance analysis is presented. The present work accounts for material anisotropy and panel load condition. Comparisons with finite element results show that the extended displacement compatibility method gives accurate stress intensity results for anisotropic panels under tension and under shear loading. The stress intensities obtained using the displacement compatibility method have been used in conjunction with material R-curves to calculate residual strength curves of stiffened panels.
UR - http://www.scopus.com/inward/record.url?scp=0030694899&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=0030694899&partnerID=8YFLogxK
M3 - Conference article
AN - SCOPUS:0030694899
VL - 4
SP - 2809
EP - 2818
JO - Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
JF - Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
SN - 0273-4508
ER -