On the Stability of Eccentrically Stiffened Cylindrical Shells Under Axial Compression PDF Download
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Author: Josef Singer Publisher: ISBN: Category : Languages : en Pages : 55
Book Description
The eccentricity effect of stiffeners is studied for stiffened cylindrical shells under axial compression. Classical simple supports and classical clamped ends are considered. A detailed physical explanation of the causes of the eccentricity effect and its behavior is proposed and verified by computations for 350 typical shells. As for buckling under hydrostatic pressure and torsion studied earlier, the behavior of the eccentricity effect in the case of axial compression also depends very strongly on the geometry of the shell, represented by the Batdorf parameter, while the geometry of the stiffeners only influences its magnitude. Inversion of eccentricity effect occurs at very low Z, but for practical dimensions outside stringers always stiffen the shell more than inside ones. The eccentricity effect has a pronounced maximum at practical values of Z, and the behavior of the eccentricity effect is very similar for clamped and simply supported shells. Rings, which are much less effective stiffeners than stringers under axial compression, are also considered. Results are compared with those of other investigators. (Author).
Author: Josef Singer Publisher: ISBN: Category : Languages : en Pages : 55
Book Description
The eccentricity effect of stiffeners is studied for stiffened cylindrical shells under axial compression. Classical simple supports and classical clamped ends are considered. A detailed physical explanation of the causes of the eccentricity effect and its behavior is proposed and verified by computations for 350 typical shells. As for buckling under hydrostatic pressure and torsion studied earlier, the behavior of the eccentricity effect in the case of axial compression also depends very strongly on the geometry of the shell, represented by the Batdorf parameter, while the geometry of the stiffeners only influences its magnitude. Inversion of eccentricity effect occurs at very low Z, but for practical dimensions outside stringers always stiffen the shell more than inside ones. The eccentricity effect has a pronounced maximum at practical values of Z, and the behavior of the eccentricity effect is very similar for clamped and simply supported shells. Rings, which are much less effective stiffeners than stringers under axial compression, are also considered. Results are compared with those of other investigators. (Author).
Author: Tien-Yu Tsui Publisher: ISBN: Category : Languages : en Pages : 33
Book Description
Linear stability of eccentrically stiffened cylindrical shells under axial compression has been investigated in the paper with an aim to establish the parameter ranges for the prevailing buckling modes. Charts delineating the zones of prevailing modes are presented in a parameter plane. Useful approximate relations are given for the bounds on parameters to predict a buckling mode for a shell in the moderate length range. (Author).
Author: L.A. Samuelson Publisher: CRC Press ISBN: 1482296713 Category : Architecture Languages : en Pages : 299
Book Description
This book provides engineering tools for the design of shells against buckling. A simplified approach is given in a number of cases which are not addressed in current design codes.
Author: D. Bushnell Publisher: Springer Science & Business Media ISBN: 9789024730995 Category : Science Languages : en Pages : 456
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: George J. Simitses Publisher: ISBN: Category : Structural stability Languages : en Pages : 208
Book Description
This report deals primarily with extension of the energy-based concepts of dynamic stability, developed earlier for finite-degree-of-freedom systems, to continuous systems. Moreover, the related criteria for dynamic stability are demonstrated through several structural configurations, such as eccentrically loaded simple two-bar frames, geometrically imperfect, thin, cylindrical shells (of stiffened and unstiffened construction) and subjected to uniform axial compression and lateral pressure, and a pinnted, half-sine, shallow arch loaded transversely. All of these systems are subject to violent buckling under static application of the loads. Moreover, the developed concepts are extended, so as to apply to structural systems, which are either subject to smooth buckling or are not subject to buckling at all under static loading.
Author: Robert M. Jones Publisher: ISBN: Category : Languages : en Pages : 49
Book Description
A solution for the plastic buckling of eccentrically stiffened cylinders is derived by use of the J2 deformation theory of plasticity for a set of simply supported edge boundary conditions. The uniaxial character of the stiffeners and the stiffener eccentricity (asymmetry about the cylinder middle surface) ae explicitly accounted for as is a variable Poisson's ratio in the plastic region. A closed-form stability criterion is obtained for axial compression, lateral pressure, and hydrostatic pressure loadings. The present results are more realistic for most practical stiffened cylinders than an existing solution in which an orthotropic shell model is used. A numerical example is given to illustrate the effect of plastic action on the buckling load of a typical aerospace structure. The FORTRAN IV computer program is described and listed. (Author).
Author: Josef Singer
Author: Josef Singer
Author: Tien-Yu Tsui
Author: John N. Dickson
Author: Ru-Lin Lee
Author: Yu-jyi Lin
Author: L.A. Samuelson
Author: D. Bushnell
Author: George J. Simitses
Author: Robert M. Jones
Author: