Item Details

Effects of Eccentricities and Lateral Pressure on the Design of Stiffened Compression Panels

by Gary L. Giles and Melvin S. Anderson
Format
Book; Government Document; Online; EBook
Published
Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972.
Language
English
Series
NASA Technical Note
Summary
An analysis for determining the effects of eccentricities and lateral pressure on the design of stiffened compression panels is presented. The four types of panel stiffeners considered are integral, zee, integral zee, and integral tee. Mass-strength curves, which give the mass of the panel necessary to carry a specified load, are given along with related design equations needed to calculate the cross-sectional dimensions of the minimum-mass-stiffened panel. The results of the study indicate that the proportions of the panels are geometrically similar to the proportions of panels designed for no eccentricity or lateral pressure, but no cross-sectional dimensions are greater, resulting in significantly increased mass. The analytical minimum-mass designs of zee-stiffened panels are compared with designs from experimentally derived charts. An assumed eccentricity of 0.001 times the length of the panel is used to correlate the analytical and experimental data. Good correlation between the experimentally derived and the analytical curves is obtained for the range of loading where materials yield governs the design. At lower loads the mass given by the analytical curve using this assumed eccentricity is greater than that given by the experimental results.
Description
33 p. : ill. ; 27 cm.
Mode of access: Internet.
Notes
  • Prepared at Langley Research Center.
  • Cover title.
  • Bibliography: p. 33.
Series Statement
NASA technical note ; NASA TN D-6784
Logo for Copyright Not EvaluatedCopyright Not Evaluated
Technical Details

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    a| Effects of eccentricities and lateral pressure on the design of stiffened compression panels c| by Gary L. Giles and Melvin S. Anderson.
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    a| Washington, D.C. : b| National Aeronautics and Space Administration ; a| [Springfield, Va. : b| For sale by the National Technical Information Service], c| 1972.
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    a| 33 p. : b| ill. ; c| 27 cm.
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    a| NASA technical note ; v| NASA TN D-6784
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    a| Prepared at Langley Research Center.
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    a| Cover title.
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    a| Bibliography: p. 33.
    520
      
      
    a| An analysis for determining the effects of eccentricities and lateral pressure on the design of stiffened compression panels is presented. The four types of panel stiffeners considered are integral, zee, integral zee, and integral tee. Mass-strength curves, which give the mass of the panel necessary to carry a specified load, are given along with related design equations needed to calculate the cross-sectional dimensions of the minimum-mass-stiffened panel. The results of the study indicate that the proportions of the panels are geometrically similar to the proportions of panels designed for no eccentricity or lateral pressure, but no cross-sectional dimensions are greater, resulting in significantly increased mass. The analytical minimum-mass designs of zee-stiffened panels are compared with designs from experimentally derived charts. An assumed eccentricity of 0.001 times the length of the panel is used to correlate the analytical and experimental data. Good correlation between the experimentally derived and the analytical curves is obtained for the range of loading where materials yield governs the design. At lower loads the mass given by the analytical curve using this assumed eccentricity is greater than that given by the experimental results.
    538
      
      
    a| Mode of access: Internet.
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    0
    a| Strains and stresses.
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    0
    a| Eccentric loads.
    650
      
    0
    a| Elastic plates and shells.
    650
      
    0
    a| Plates (Engineering)
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    1
      
    a| Anderson, Melvin S.
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    a| United States. b| National Aeronautics and Space Administration.
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    a| Langley Research Center.
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    b| UIU c| UIUC d| 20141113 s| google u| uiug.30112106883744 y| 1972 r| pd q| bib

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