Thermal-mechanical buckling of composite plates for aerospace applications

Conference paper (2018)

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)
Copyright: © 2018 J. Gutierrez Alvarez, C. Bisagni
Composite materials Supersonic aircraft Thermal-mechanical buckling Analytical formulation
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Published Date

2018

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 proposed for determining the buckling of composite plates under combined thermal-mechanical loading. The plates are subjected to a constant temperature increment, combined with applied displacement, while transversal in-plane expansion is restricted. The plates are studied using Von Kármán equations in combination with classical lamination theory, being the study limited to symmetric and balanced laminates. The problem is formulated in terms of in-plane displacement fields and solved using the Galerkin method. An analytical formula is obtained that relates critical temperatures to applied plate displacement. An example of a possible application is presented in the form of graph and is verified by finite element analysis. The obtained formula can be used during initial design for sensitivity analysis and optimization, and also for deriving specific buckling shapes.