Thermal-mechanical buckling of composite plates for aerospace applications

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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.
Original languageEnglish
Title of host publicationProceedings of the 18th European Conference on Composite Materials
Subtitle of host publication24-28th June 2018, Athens, Greece
Number of pages6
Publication statusPublished - 2018
EventECCM18: 18th European Conference on Composite Materials - Athens, Greece
Duration: 24 Jun 201828 Jun 2018
Conference number: 18


ConferenceECCM18: 18th European Conference on Composite Materials
Abbreviated titleECCM18
Internet address


  • thermal-mechanical buckling
  • composite materials
  • analytical formulation
  • supersonic aircraft


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