General Instability of Orthotropically Stiffened Cylinders. Part 2. Bending and Combined Compression and Bending.

Item

Title
General Instability of Orthotropically Stiffened Cylinders. Part 2. Bending and Combined Compression and Bending.
Date
1965
Index Abstract
Coming Soon
Photo Quality
Complete
Report Number
AFFDL TR 65-161 Part 2
Creator
Lakshmikantham, C.
Gerard, George
Milligan, Roger
Corporate Author
Air Force Flight Dynamics Laboratory
Laboratory
Air Force Flight Dynamics Laboratory
Extent
41
Identifier
AD0623810
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
As part of a general program to determine the applicability of linear orthotropic theory to the design of cylindrical shells under various loading conditions, a theoretical and experimental investigation was performed on the general instability of orthotropic cylinders under bending and combined axial compression and bending loading. Based on a simple approximation for the asymmetric buckling pattern, theoretical results suitable for design use were obtained for the buckling of orthotropic cylinders for both bending and combined loading conditions. It was shown that the buckling stress for orthotropic cylinders under bending or axial compression loading are equal which agrees with previous results for isotropic cylinders. Theoretical results were evaluated by means of a series of careful experiments performed on orthotropically stiffened cylinders designed to fail in the elastic general instability mode. For both bending loading and the combined axial and bending loading condition, experimental results were in good agreement with the theory.
Report Availability
Full text available
Date Issued
1965-08
Provenance
Lockheed Martin Missiles & Fire Control
Type
report
Format
1 online resource
Media
AFFDLTR65-161part02.pdf