A semi-analytical approach for linear and non-linear analysis of unstiffened laminated composite cylinders and cones under axial, torsion and pressure loads

Castro, Saullo G.P.; Mittelstedt, Christian Mittelstedt; Monteiro, Francisco A.C. Monteiro; Arbelo, Mariano A. Arbelo; Degenhardt, Richard Degenhardt; Ziegmann, Gerhard Ziegmann

A semi-analytical approach for linear and non-linear analysis of unstiffened laminated composite cylinders and cones under axial, torsion and pressure loads

Journal article (2015)

Authors

Saullo G.P. Castro Private University of Applied Sciences, Clausthal University of Technology, EMBRAER

Christian Mittelstedt Mittelstedt SOGETI High Tech GmbH

Francisco A.C. Monteiro Monteiro Division of Fundamental Science

Mariano A. Arbelo Arbelo Private University of Applied Sciences

Richard Degenhardt Degenhardt Private University of Applied Sciences, Deutsches Zentrum für Luft- und Raumfahrt (DLR)

Gerhard Ziegmann Ziegmann Clausthal University of Technology

Research Group

Aerospace Structures & Computational Mechanics (Aerospace Engineering) (TU Delft)

Cylinders Ritz method Cones Linear buckling Linear static Non-linear analysis

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Published Date

01-01-2015

Language

English

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Faculty

Aerospace Engineering

Department

Aerospace Structures & Materials

Research Group

Aerospace Structures & Computational Mechanics

Abstract

A semi-analytical model for the non-linear analysis of simply supported, unstiffened laminated composite cylinders and cones using the Ritz method and the Classical Laminated Plate Theory is proposed. A matrix notation is used to formulate the problem using Donnell's and Sanders' non-linear equations. The approximation functions proposed are capable to simulate the elephant's foot effect, a common phenomenon and a common failure mode for cylindrical and conical structures under axial compression. Axial, torsion and pressure loads can be applied individually or combined, and solutions for linear static, linear buckling and non-linear buckling analyses are presented and verified using a commercial finite element software. The presented non-linear buckling analyses used perturbation loads to create the initial geometric imperfections, showing the capability of the method for arbitrary imperfection patterns. The linear stiffness matrices are integrated analytically and for the conical structures an approximation is proposed to overcome the non-integrable expressions.