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On the influence of laminate stacking on buckling of composite cylindrical shells subjected to axial compresssion

Geier, B. and Meyer-Piening, H.-R. and Zimmermann, R. (2002) On the influence of laminate stacking on buckling of composite cylindrical shells subjected to axial compresssion. Composite Structures, 55 (4), pp. 467-474.

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Abstract

The buckling loads of laminated cylinders can strongly depend on the position of the differently oriented layers within the shell. This paper deals with two different laminated orthotropic cylinders with opposite stacking sequence of the laminate layers. Cylinders of this construction had been thoroughly tested within a BRITE EURAM project. Analytical and semi-analytical methods have been used to predict the buckling loads, and the results are reported in this paper as well as test results for comparison. An explanation of the striking influence of stacking sequence is given. With some more examples the findings are verified. It is suggested that the presented results can be used for benchmarking purpose.

Document Type:Article
Additional Information: LIDO-Berichtsjahr=2002,
Title:On the influence of laminate stacking on buckling of composite cylindrical shells subjected to axial compresssion
Authors:
AuthorsInstitution or Email of Authors
Geier, B.UNSPECIFIED
Meyer-Piening, H.-R.ETH Zürich
Zimmermann, R.UNSPECIFIED
Date:2002
Journal or Publication Title:Composite Structures
Refereed publication:Yes
In ISI Web of Science:Yes
Volume:55
Page Range:pp. 467-474
Status:Published
Keywords:Composites; Buckling analysis; Shells
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Aeronautics
HGF - Program Themes:other
DLR - Research area:Aeronautics
DLR - Program:L ST - Starrflüglertechnologien
DLR - Research theme (Project):UNSPECIFIED
Location: Braunschweig
Institutes and Institutions:Institute of Composite Structures and Adaptive Systems > Institut für Strukturmechanik
Deposited By: elib DLR-Beauftragter
Deposited On:16 Sep 2005
Last Modified:14 Jan 2010 16:20

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