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Author:
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Category :
Languages : en
Pages : 524
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Author:
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Category :
Languages : en
Pages : 524
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Author: Richard F. Hartung
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ISBN:
Category : Numerical analysis
Languages : en
Pages : 1316
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Author: United States. National Aeronautics and Space Administration Scientific and Technical Information Division
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Category : Aeronautics
Languages : en
Pages : 478
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Author: L. K. Chang
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Category : Airplanes
Languages : en
Pages : 100
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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.
Author: United States. National Aeronautics and Space Administration. Scientific and Technical Information Division
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Category : Aeronautics
Languages : en
Pages : 470
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 1282
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Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author: Sidney C. Dixon
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Category : Buckling (Mechanics)
Languages : en
Pages : 44
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The effect of ring size on the buckling of truncated isotropic conical shells supported at the ends by rings and subjected to hydrostatic- or lateral pressure loadings has been studied. Results were obtained from an approximate theory based on Donnell-type shell theory and a membrane prestress state. For a given shell geometry, the ring properties were varied to determine the smallest ring required to provide the equivalent of essentially clamped support. For a particular application, this procedure yielded the minimum mass of the shell-ring configuration. A nondimensional stiffness parameter was determined which correlated, in general, the results for the entire range of ring and shell geometries considered. Approximate formulas are presented for the preliminary design of rings with both closed (circular and square) and open (I and Z) cross sections.
Author:
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Category : Government publications
Languages : en
Pages :
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Author:
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Category : Aeronautics
Languages : en
Pages : 1016
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Author:
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Category : Mechanics, Applied
Languages : en
Pages : 772
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