Thermal Buckling of Circular Cylindrical and Conical Thin-walled Shells PDF Download
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Author: David Abir
Publisher:
ISBN:
Category : Elastic plates and shells
Languages : en
Pages : 170
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Book Description
Author: David Abir
Publisher:
ISBN:
Category : Elastic plates and shells
Languages : en
Pages : 170
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Book Description
Author: Stanford University. Department of Aeronautics and Astronautics
Publisher:
ISBN:
Category :
Languages : en
Pages : 86
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Book Description
Author: S. V. Nardo
Publisher:
ISBN:
Category :
Languages : en
Pages : 49
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Book Description
This paper presents the results of several theoretical and experimental investigations made in connection with the problem of thermal buckling of circular cylindrical shells. In the Introduction, a brief survey is made of thermal effects on aircraft and missile structures, which include creep, thermal stresses, thermal buckling, and design criteria. Some of the features characterizing problems of thermal buckling, and methods of solution are outlined. The solutions to two problems of the thermal buckling of thin-walled circular cylindrical shells are given. In the first of these problems the temperature is assumed to vary the circumferential direction, giving rise to axial thermal stresses which vary in the circumferential direction. The second problem treats the case of hoop stresses varying only in the axial direction which may be obtained for certain thermal inputs and boundary conditions. The results of an experimental investigation of the thermal buckling of thin-walled circular cylindrical shells are presented. (Author).
Author: Nicholas John Hoff
Publisher:
ISBN:
Category : Buckling (Mechanics)
Languages : en
Pages : 66
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Book Description
With the aid of a set of orthonormal functions the critical temperatures are calculated for thin-walled circular cylindrical shells rapidly heated along a narrow axial strip. The results obtained are compared with experimental data of an earlier investigation. (Author).
Author: David William Hill
Publisher:
ISBN:
Category : Buckling (Mechanics)
Languages : en
Pages : 106
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Book Description
Author: Nicholas John Hoff
Publisher:
ISBN:
Category : Buckling (Mechanics)
Languages : en
Pages : 54
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Book Description
Analysis of the simple model proposed yields equilibrium curves in agreement with those obtained by other investigators for axially compressed thin-walled circular cylindrical shells. A rigorous calculation of the stability of the equilibrium of the model indicates that the snap-through phenomenon can be entirely absent when an imperfect shell is heated in a perfectly rigid testing machine. When the testing machine is sufficiently elastic, snap through will occur. It may take place at a temperature smaller than, equal to, or greater than T = epsilon sub cr/alpha, where epsilon sub cr is the theoretical critical strain of the perfect shell and alpha is the coefficient of expansion of the material of the shell, but the maximum stress produced in the imperfect shell will always be less than epsilon sub cr E, where E is Young's modulus of the material. (Author).
Author: Bernard Ross
Publisher:
ISBN:
Category : Buckling (Mechanics)
Languages : en
Pages : 350
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Book Description
Author: Josef Singer
Publisher: John Wiley & Sons
ISBN: 0471974501
Category : Technology & Engineering
Languages : en
Pages : 1140
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Book Description
* 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: Y. S. Pan
Publisher:
ISBN:
Category : Shells (Engineering)
Languages : en
Pages : 8
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Book Description
Author: L. K. Chang
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 100
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Book Description
A theory for thermal buckling of an orthotropic, multilayered, stiffened cylindrical shell is presented. The theory includes the effects of eccentricity of layers and stiffening, and deformations prior to buckling. It is sufficiently general to account for discrete rings and averaged properties of longitudinal stiffening, as well as arbitrary temperature distributions through the thickness of the shell and depth of the stiffeners. Two computer programs are described corresponding to solutions for buckling obtained by using finite differences and determinant plotting or modal iteration. Computed results for thermal buckling of unstiffened and ring-stiffened shells are presented and are in reasonable agreement with published results. The interaction of thermal loading and axial compression in two large diameter stiffened shells representative of a launch vehicle interstage and a preliminary supersonic transport fuselage design is investigated. Results indicate that budding can occur in both structures at a realistic temperature under thermal loading alone.
