Postbuckling strength of stiffened composite plates with impact damage

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The buckling and postbuckling strengths for unstiffened and stiffened composite plates with various impact damages were studied numerically and experimentally. To predict the residual strength, a progressive failure model with the degradation of elastic moduli in the damaged regions was adopted in a nonlinear finite element method. The progressive failure analysis used the maximum stress criterion and the complete unloading model. The degradation ratio in each sublaminate was determined by delamination distributions through the thickness of laminates. The ply-by-ply delamination was detected by an improved ultrasonic technique. The predicted buckling and postbuckling strength showed good agreement with experimental results. The correlation between the impact damage and the postbuckling strength is discussed. The delamination growth was also observed for I-stiffened composite plates under the cyclic compressive load.
Publisher
AMER INST AERONAUT ASTRONAUT
Issue Date
2000-10
Language
English
Article Type
Article
Keywords

COMPRESSIVE STRENGTH; RESIDUAL STRENGTH; BEHAVIOR; PANELS; DELAMINATION; PREDICTION; FAILURE; TESTS

Citation

AIAA JOURNAL, v.38, no.10, pp.1956 - 1964

ISSN
0001-1452
DOI
10.2514/2.851
URI
http://hdl.handle.net/10203/70578
Appears in Collection
AE-Journal Papers(저널논문)
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