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Effects of Stiffening and Mechanical Load on Thermal Buckling of Stiffened Cylindrical ShellsA study of thermal buckling of stiffened cylindrical shells with the proportions of a preliminary supersonic transport fuselage design (1970) is presented. The buckling analysis is performed using an axisymmetric shell-of-revolution code, BOSOR4. The effects of combined mechanical (axial loading) and thermal loading (heated skins) are investigated. Results indicate that the location of longitudinal eccentric stiffening has a very large effect on the thermal buckling strength of longitudinally stiffened shells, and on longitudinally stiffened shells with rings.
Document ID
19970012889
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Johnson, Theodore F. (NASA Langley Research Center Hampton, VA United States)
Card, Michael F. (NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 6, 2013
Publication Date
April 12, 1995
Publication Information
Publisher: American Inst. of Aeronautics and Astronautics
Subject Category
Structural Mechanics
Report/Patent Number
NASA-TM-112006
NAS 1.15:112006
AIAA Paper 95-1317
Report Number: NASA-TM-112006
Report Number: NAS 1.15:112006
Report Number: AIAA Paper 95-1317
Meeting Information
Meeting: Structures, Structural Dynamics and Materials Conference
Location: New Orleans, LA
Country: United States
Start Date: April 10, 1995
End Date: April 12, 1995
Sponsors: American Helicopter Society, Inc., American Inst. of Aeronautics and Astronautics, American Society of Mechanical Engineers, American Society for Composites, American Society of Civil Engineers
Accession Number
97N17020
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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