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  • 1
    Electronic Resource
    Electronic Resource
    Postbuckling behavior of composite-stiffened-curved panels loaded in compression (1982)
    Springer
    Experimental mechanics 22 (1982), S. 231-236 
    Details
    ISSN: 1741-2765
    Source: Springer Online Journal Archives 1860-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: Abstract In this paper, a methodology is developed for the design of a weight-efficient, composite, curved-stiffened panel, loaded in compression well beyond the initial buckling load. A stiffened fuselage panel is designed to satisfy typical design load criteria for the moderately loaded sections of a typical fighter aircraft. Several stiffened panels are fabricated. Some panels are tested to determine experimentally the static strength and the remaining panels are subjected first to severe fatigue loading and then tested statically to determine the effect of fatigue loading on the postbuckling strengh. The experimentally observed behavior is compared with analytical predictions. The weight efficiencies of buckled and unbuckled construction are also compared.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF02326363
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    Paper (German National Licenses)
    Fulltext
  • 2
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    Postbuckling behavior of composite-stiffened-curved panels loaded in compression (1982)
    Springer
    Details
    Publication Date: 1982-06-01
    Print ISSN: 0014-4851
    Electronic ISSN: 1741-2765
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Springer
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    PAPER CURRENT
  • 3
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    Buckling of Cylindrical Panels Under Axial Compression (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper investigates the effects of boundary conditions and panel width on the axially compressive buckling behavior of unstiffened, isotropic, circular cylindrical panels. Numerical results are presented for eight different sets of boundary conditions along the straight edges of the panels. For all sets of boundary conditions except one (SSI), the results show that the panel buckling loads monotonically approach the complete cylinder buckling load from above as the panel width is increased. Low buckling loads, sometimes less than half the complete cylinder buckling load, are found for simply supported panels with free in-plane edge displacements (SSI). The SSI buckling loads are below the complete cylinder load even for '360deg panels'. It is also observed that the prevention of circumferential edge displacement is the most important in-plane boundary condition from the point of view of increasing the buckling load, and that the prevention of edge rotation (i.e. clamping) in the circumferential direction also significantly increases the buckling load. Parametric studies are also performed to determine the effects of variations in panel length and thickness on the buckling loads.
    Keywords: Structural Mechanics
    Type: Computers and Structures; 6; 1; 29-35
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Optimization of a corrugated stiffened composite panel under uniaxial compression (1973)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An approach of structural optimization has been used to optimize the weight of a simply supported, corrugated hat stiffened composite panel under uniaxial compression. The approach consists of the employment of nonlinear mathematical programming techniques to reach an optimum solution. Some simplifying assumptions are made in the stress analysis to obtain faster convergence to an optimum solution. With these simplifying assumptions the number of unknown design parameters is reduced to twelve.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-132314
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Buckling of eccentrically stringer-stiffened cylindrical panels under axial compression (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The paper presents numerical results, based on Donnell shell theory, for the axial compressive buckling loads for eccentrically stringer-stiffened circular cylindrical panels, in a study of the effect of boundary conditions and panel width on the buckling load. The two cases of inside and outside stiffeners were considered. The complete cylinder buckling load was reached only for panels under classical simply supported boundary conditions. The prevention of circumferential displacement is found to be the most important in-plane boundary condition from the point of view of increasing the buckling load. Clamping is found more effective in increasing the buckling loads of panels with free circumferential edge displacement than of panels with zero edge displacement. When panel width is equal to or greater than 180 deg, the panel buckling loads are within 10% of the complete cylinder load for all cases except one simply supported panel with outside stringers. Buckling loads were higher for outside stringers, except for very narrow panels that are restrained against circumferential edge displacement. Eccentricity effects are generally similar for clamped and simply supported panels with the same in-plane boundary conditions.
    Keywords: STRUCTURAL MECHANICS
    Type: Computers and Structures; 6; June 197
    Format: text
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  • 6
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    Stress tests on cylinders and aluminum panels (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An optimization study of composite stiffened cylinders is discussed. The mathematical model for the buckling has been coupled successfully with the optimization program AESOP. The buckling analysis is based on the use of the smeared theory for the buckling of stiffened orthotropic cylindrical shells. The loading, radius, and length of the cylinder are assumed to be known parameters. An optimum solution gives the value of cross-sectional dimensions and laminate orientations. The different types of buckling modes are identified. Mathematical models are developed to show the relationships of the parameters.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-139215
    Format: application/pdf
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  • 7
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    Weight comparisons of optimized stiffened, unstiffened, and sandwich cylindrical shells made from composite or aluminum materials (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This work presents optimum designs for unstiffened, hat stringer-stiffened and honeycomb sandwich cylinders under axial compression. Optimization results for graphite-epoxy cylinders show about a 50 percent weight savings over corresponding optimized aluminum cylinders for a wide loading range. The inclusion of minimum gage considerations results in a significant weight penalty, especially for a lightly loaded cylinder. Effects of employing a smeared stiffener buckling theory in the optimization program are investigated through comparison of results obtained from a more accurate branched shell buckling computer code. It was found that the stiffener cross-sectional deformations, which are usually ignored in smeared stiffener theory, result in about a 30 percent lower buckling load for the graphite-epoxy hat stiffened cylinder.
    Keywords: STRUCTURAL MECHANICS
    Type: Structures, Structural Dynamics, and Materials Conference; May 05, 1976 - May 07, 1976; King of Prussia, PA
    Format: text
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    NASA TECHNICAL REPORTS
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