Ritz method for the analysis of unstiffened laminated composite cylinders and cones under axial compression

Conference paper (2014)

Authors

Saullo G.P. Castro Private University of Applied Sciences, EMBRAER
Christian Mittelstedt SOGETI High Tech GmbH
Francisco A.C. Monteiro Division of Fundamental Science
Mariano A. Arbelo Private University of Applied Sciences
Regina Khakimova Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR)
Richard Degenhardt Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR)
Research Group
Aerospace Structures & Computational Mechanics (Aerospace Engineering) (TU Delft)
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Published Date

01-01-2014

Language

English

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Faculty

Aerospace Engineering

Department

Aerospace Structures & Materials

Research Group

Aerospace Structures & Computational Mechanics

Abstract

This paper presents the application of the Ritz method for the analysis of laminated composite cylinders and cones using the classical laminated plate theory (CLPT) and the first shear deformation theory (FSDT). The Donnell and Sander kinematic approximations are investigated for the CLPT. It is shown that the equations proposed by Sanders when applied with the CLPT increase the range of applicability of the CLPT in comparison with the Donnell kinematics. The developed models are suitable to obtain linear and non-linear responses of conical and cylindrical shells under displacement or load controlled axial compression and geometric imperfections. This paper brings the investigation of static and buckling responses and the commercial finite element solver Abaqus was used to validate all the linear and non-linear results.