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Minimum weight design of fuselage type stiffened circular cylindrical shells subject to uniform axial compression

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1. http://hdl.handle.net/1853/16880
2. 253775

Identifer	oai:union.ndltd.org:GATECH/oai:smartech.gatech.edu:1853/16880
Date	08 1900
Creators	Ungbhakorn, Variddhi
Publisher	Georgia Institute of Technology
Source Sets	Georgia Tech Electronic Thesis and Dissertation Archive
Detected Language	English
Type	Dissertation
Rights	Access restricted to authorized Georgia Tech users only.