General Instability of Orthotropically Stiffened Cylinders. Part 1. Axial Compression, Torsion and Hdyrostatic Pressure Loadings

Item

Title
General Instability of Orthotropically Stiffened Cylinders. Part 1. Axial Compression, Torsion and Hdyrostatic Pressure Loadings
Date
1965
Index Abstract
Coming Soon
Photo Quality
Complete
Report Number
AFFDL TR 65-161 Part 1
Creator
Milligan, Roger
Gerard, George
Lakshmikantham, C.
Becker, Herbert
Corporate Author
Air Force Flight Dynamics Laboratory
Laboratory
Air Force Flight Dynamics Laboratory
Extent
114
Identifier
AD0623801
Access Rights
Distribution of this document is unlimited
Distribution Classification
1
Contract
AF 33(615)-1228
DoD Project
1467
DoD Task
146703
DTIC Record Exists
No
Distribution Change Authority Correspondence
None
Abstract
The general applicability of orthotropic stability theory to aerospace shell structures was examined experimentally. For this purpose a series of careful experiments were performed on orthotropically stiffened cylinders designed to fail in the elastic general instability mode under three separate loading conditions: axial compression, torsion and hydrostatic pressure. Experimental results obtained during the program verified that for all loading conditions considered linear orthotropic theory results in accurate predictions of cylinder strength. As a result of observed discrepancies between experiment and previously existing theory for longitudinally stiffened cylinders under axial compression, theoretical studies were initiated which resulted in the discovery of a new asymmetric failure mode for this cylinder configuration. Based on this new failure mode, good correlation between experiment and theory was obtained except when the longitudinal stiffened cylinder configurations approached that corresponding to an isotropic cylinder. Other theoretical investigations performed during the program established that cylinder boundary conditions have a pronounced effect on the buckling strength of orthotropic cylinders under hydrostatic pressure loading.
Report Availability
Full text available
Date Issued
1965-07
Provenance
Lockheed Martin Missiles & Fire Control
Type
report
Format
1 online resource
Media
AFFDLTR65-161part01.pdf

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