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An Approximate Method for Buckling Analysis and Optimization of Composite Lattice Conical Panels Considering Geometric Parameters

An Approximate Method for Buckling Analysis and Optimization of Composite Lattice Conical Panels... This paper proposes an approximate method for calculating the critical buckling load of conical composite lattice panels. The conical composite lattice panel consists of helical and hoop ribs and can be described by geometrical parameters. Using these geometric parameters, the critical buckling load of conical composite lattice panels under uniform compression is predicted. The present method is validated by comparing the critical buckling loads obtained under a simply supported boundary condition with those obtained by the finite element method. The results of the critical buckling load show good agreement between the present method and finite element analysis. A parametric study is performed using the present method to investigate the influence of the number of hoop and helical ribs on the critical buckling load. In the parametric study, the number of helical and hoop ribs is defined as design variables, and the critical buckling load is defined as the response. In addition, the present method is applied to the optimization of composite lattice conical panels using a genetic algorithm. The optimization of the panels is defined by minimizing the mass, while defining the critical load as the boundary condition. Therefore, the approximation method using geometric functions provides not only analysis of critical buckling loads for composite lattice panels but also a useful tool for optimal design. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png International Journal of Aeronautical and Space Sciences Springer Journals

An Approximate Method for Buckling Analysis and Optimization of Composite Lattice Conical Panels Considering Geometric Parameters

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Publisher
Springer Journals
Copyright
Copyright © The Author(s), under exclusive licence to The Korean Society for Aeronautical & Space Sciences 2023. Springer Nature or its licensor (e.g. a society or other partner) holds exclusive rights to this article under a publishing agreement with the author(s) or other rightsholder(s); author self-archiving of the accepted manuscript version of this article is solely governed by the terms of such publishing agreement and applicable law.
ISSN
2093-274X
eISSN
2093-2480
DOI
10.1007/s42405-023-00589-1
Publisher site
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Abstract

This paper proposes an approximate method for calculating the critical buckling load of conical composite lattice panels. The conical composite lattice panel consists of helical and hoop ribs and can be described by geometrical parameters. Using these geometric parameters, the critical buckling load of conical composite lattice panels under uniform compression is predicted. The present method is validated by comparing the critical buckling loads obtained under a simply supported boundary condition with those obtained by the finite element method. The results of the critical buckling load show good agreement between the present method and finite element analysis. A parametric study is performed using the present method to investigate the influence of the number of hoop and helical ribs on the critical buckling load. In the parametric study, the number of helical and hoop ribs is defined as design variables, and the critical buckling load is defined as the response. In addition, the present method is applied to the optimization of composite lattice conical panels using a genetic algorithm. The optimization of the panels is defined by minimizing the mass, while defining the critical load as the boundary condition. Therefore, the approximation method using geometric functions provides not only analysis of critical buckling loads for composite lattice panels but also a useful tool for optimal design.

Journal

International Journal of Aeronautical and Space Sciences – Springer Journals

Published: May 13, 2023

Keywords: Composite lattice structure; Buckling analysis; Conical panel; Finite element analysis; Ritz method

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