The Buckling Strength of Filament-wound Cylinders Under Axial Compression PDF Download

Author: J. Tasi
Publisher:
ISBN:
Category : Buckling (Mechanics)
Languages : en
Pages : 76

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Author: A. Holston (Jr.)
Publisher:
ISBN:
Category : Bending
Languages : en
Pages : 164

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Book Description
A combined analytical and experimental investigation of the stability of composite cylindrical shells is presented. Forty-five fiber-glass filament wound cylinders were fabricated, buckled, and analyzed. The number 45 stems from considering three diameters (6 in, 12 in, 24 in), three filament configurations, and five loadings. All cylinders had essentially the same wall thickness, .035 in, and each cylinder length was nearly equal to its diameter. The five loadings were: (1) uniform axial compression, (2) torsion, (3) bending, (4)combined torsion and uniform axial compression, (5) combined bending and uniform axial compression. The analysis was based on linear anisotropic shell theory and the effects of boundary conditions were not considered. Preliminary tests were conducted to determine the in-plane stiffnesses and individual layer elastic properties. The experimental buckling loads were from 67 to 90% of predicted values for loading without torsion. The bending buckling stress was, for all practical purposes, equal to the axial buckling stress and the combined bending with uniform axial load interaction was essentially linear. The experimental torsion buckling loads were greater than the predicted values but the boundary conditions were not considered in the analysis. Buckling loads were computed for boron filament wound cylinders of the same size and winding configurations. These computations show that the buckling loads of boron and aluminum cylinders, of the same size, are nearly equal. A similar comparison on a weight basis would produce the same result since their densities are essentially equal.

Author: James P. Peterson
Publisher:
ISBN:
Category : Axial compression and bending
Languages : en
Pages : 36

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Book Description
Buckling data review for stiffened cylinder failures during axial compression and bending.

Author: D. Bushnell
Publisher: Springer Science & Business Media
ISBN: 9789024730995
Category : Science
Languages : en
Pages : 456

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Book Description
This report describes the work performed by Lockheed Palo Alto Research Labora tory, Palo Alto, California 94304. The work was sponsored by Air Force Office of Scientific Research, Bolling AFB, Washington, D. C. under Grant F49620-77-C-0l22 and by the Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Wright-Patterson AFB, Ohio under Contract F3361S-76-C-31OS. The work was completed under Task 2307Nl, "Basic Research in Behavior of Metallic and Composite Components of Airframe Structures". The work was admini stered by Lt. Col. J. D. Morgan (AFOSR) and Dr. N. S. Khot (AFWAL/FIBRA). The contract work was performed between October 1977 and December 1980. The technical report was released by the Author in December 1981. Preface Many structures are assembled from parts which are thin. For example, a stiffened plate or cylindrical panel is composed of a sheet the thickness of which is small com pared to its length, breadth, and stiffener- spacing, and stiffeners the thickness of which is small compared to their _ heights and lengths. These assembled structures, loaded in compression, can buckle overall, that is sheet and stiffeners can collapse together in a general instability mode; the sheet can buckle locally between stiffeners; the stiffeners can cripple; and a variety of complex buckling interactions can occur involving local and overall deformations of both sheet and stiffeners. More complex, built-up structures can buckle in more complex and subtle ways.

Author: Josef Singer
Publisher: John Wiley & Sons
ISBN: 0471974501
Category : Technology & Engineering
Languages : en
Pages : 1140

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* Edited by Josef Singer, the world's foremost authority on structural buckling. * Time-saving and cost-effective design data for all structural, mechanical, and aerospace engineering researchers.

Author: David Bushnell
Publisher:
ISBN:
Category : Buckling (Mechanics)
Languages : en
Pages : 810

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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 912

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Author: L. David Wall (Jr.)
Publisher:
ISBN:
Category : Fibrous composites
Languages : en
Pages : 52

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Results are presented from torsion tests conducted on 36 multilayered, filament-wound, glass-epoxy tubes. Configurations with helical windings and with alternating helical and circumferential windings were investigated for various winding angles. Under small loadings, shear moduli deduced from linear shear stress-strain curves were found to be in reasonable agreement with analytical predictions. Under larger loadings, various degrees of nonlinearity in shear stress-strain curves were encountered, depending on the helical winding angle. Experimental torsional strengths were defined by a 0.2 -percent offset yield stress or by maximum stress when large nonlinearities did not exist. These strengths were compared with torsional buckling predictions for orthotropic cylinders, and with material strength predictions based on orthotropic yield criteria and elastic stress analysis. Computed elastic buckling stresses were considerably higher than the experimental strengths for most of the test specimens except for those with only 30° and 45 [degree] windings. Experimental torsional strengths- were found to correlate with conventional yield predictions if predicted yielding in certain layers were ignored or if unrealistically large transverse tensile and shear strengths of unidirectional laminae were employed in the analysis.

Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1080

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Author: United States. National Aeronautics and Space Administration. Technology Utilization Division
Publisher:
ISBN:
Category :
Languages : en
Pages : 570

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