Abstract
In this paper, the failure modes of T-shaped composite stiffened panels under uniaxial compression are analyzed through experiments and Finite Element Method(FEM). The composite stiffened panels' buckling and post-buckling behaviors with different pre-damage locations and sizes are studied. Three pre-damage locations and four damage sizes are considered. Comparing the critical buckling loads and the maximum failure loads of these pre-damaged composite stiffened panels, three conclusions are obtained: there are a few influences on the critical buckling loads and the maximum failure loads, when the pre-damages are located at the skin between the stringers; the critical buckling loads obviously decreased by 50% at maximum when the damages are located at the skin under the stringer; the maximum failure loads decrease due to the damage size increasing when the pre-damages are located at the skin under the stringer's edge, and the maximal decreasing value is 25%. Finally maps about the critical buckling and the maximum failure loads' ratios with respect to the pre-damage locations and sizes are shown.
Original language | English |
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Pages (from-to) | 115-119 |
Number of pages | 5 |
Journal | Yingyong Lixue Xuebao/Chinese Journal of Applied Mechanics |
Volume | 30 |
Issue number | 1 |
State | Published - Feb 2013 |
Keywords
- Critical buckling load
- Linear buckling
- Maximum failure load
- Non-linear buckling
- Stiffened panel