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Bending Tests of Metal Monocoque Fuselage ConstructionThis thesis presents a study of the bending stress in smooth skin, aluminum alloy, true monocoque fuselage sections of varying ratio of diameters to thickness. The test specimens - circular, thin-walled cylinder were loaded to give a large bending stress in proportion to the shearing stress, in order to represent the critical section of a fuselage.
Document ID
19930081125
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Mossman, Ralph W (Stanford University)
Robinson, Russell G (Stanford University)
Date Acquired
September 6, 2013
Publication Date
November 1, 1930
Report/Patent Number
NACA-TN-357
Report Number: NACA-TN-357
Accession Number
93R10415
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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