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Scaling Methodology for Buckling of Sandwich Composite Cylindrical StructuresThe 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.
Document ID
20180006179
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Balbin, Ines Uriol
(Delft Univ. of Technology Delft, Netherlands)
Bisagni, Chiara
(Delft Univ. of Technology Delft, Netherlands)
Schultz, Marc R.
(NASA Langley Research Center Hampton, VA, United States)
Hilburger, Mark W.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
October 9, 2018
Publication Date
January 8, 2018
Subject Category
Composite Materials
Report/Patent Number
NF1676L-27360
Meeting Information
Meeting: AIAA SciTech
Location: Kissimmee, FL
Country: United States
Start Date: January 8, 2018
End Date: January 12, 2018
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 869021.04.07.01.13
Distribution Limits
Public
Copyright
Public Use Permitted.
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