Scaling methodology for buckling of sandwich composite cylindrical structures

Conference paper (2018)

Authors

I. Uriol Balbin Aerospace Structures & Computational Mechanics - Aerospace Engineering
C. Bisagni Aerospace Structures & Computational Mechanics - Aerospace Engineering
Marc R. Schultz NASA Langley Research Center
Mark W. Hilburger NASA Langley Research Center
Research Group
Aerospace Structures & Computational Mechanics (Aerospace Engineering) (TU Delft)
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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

The study of the buckling behavior of large shell structures through full-size tests can be complex and expensive. Therefore, scaled structures are often preferred to investigate the buckling behavior efficiently. However, it can be difficult to design scaled structures that are representative of the full-scale structures. Herein, an analytical scaling methodology for compression-loaded sandwich composite cylinders based on the nondimensionalization of the buckling equations is presented. The methodology is used to develop scaled configurations that show a similar buckling response. Both the baseline and the scaled configurations are verified by finite-element analysis. Limitations of the methodology are discussed and are a result of neglecting the flexural anisotropy and the transverse shear compliance.

Files

6.2018_1988.pdf
(.pdf | 1.19 Mb)