Closed-form solutions for thermomechanical buckling of orthotropic composite plates

Journal article (2020)

Authors

J. Gutierrez Alvarez Aerospace Structures & Computational Mechanics - Aerospace Engineering
C. Bisagni Aerospace Structures & Computational Mechanics - Aerospace Engineering
Research Group
Aerospace Structures & Computational Mechanics (Aerospace Engineering) (TU Delft)
Thermomechanical buckling Thermal stresses Closed formula Preliminar design
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Published Date

01-02-2020

Language

English

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Faculty

Aerospace Engineering

Department

Aerospace Structures & Materials

Research Group

Aerospace Structures & Computational Mechanics

Abstract

A closed-form solution is derived for the buckling of orthotropic composite plates under the effect of thermal and mechanical loads. The plates are subjected to constant temperature increment and length variation while the width expansion is constrained. The problem is formulated in terms of displacement components, studied using classical plate theory in combination with classical lamination theory. An analytical formula that relates critical temperatures to applied plate displacements is obtained. The buckling of heated, fully restrained plates is also derived as a particular case. Examples of plates made of different materials and lay-ups are presented in graphical form, and are verified by finite element analysis. The obtained formula can be used during initial design, for sensitivity analysis and also for obtaining desired buckling shapes.