Item Details

The Effect of Angle of Attack on the Buckling of Mars Entry Aeroshells

by Gerald A. Cohen
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 [distributor], 1973.
Language
English
Series
NASA Contractor Report
Summary
The buckling modes of four optimized Mars entry aeroshell configurations at angle-of-attack loadings have been calculated. The analysis is based on experimental pressure distributions and was performed with the aid of a buckling digital computer program which treats general asymmetric linearized prebuckling states of branched shells of revolution. Only zero and first harmonic pressure components are treated, these being constructed from windward and leeward meridian pressure data at a mach number of 4.63. The results showed a rather small effect of the unsymmetrical pressure component on buckling for angles of attack up to 15 deg. Comparison of the results for the 120 deg cones to previous results indicates that the common procedure of basing the design on a symmetrized pressure distribution of the windward meridian is a conservative approach.
Description
iii, 18 p. : ill. ; 27 cm.
Mode of access: Internet.
Notes
  • "NASA CR-2087."
  • "February 1973."
  • Cover title.
  • Includes bibliographical references (p. 6).
Series Statement
NASA contractor report ; NASA CR-2087
Logo for No Copyright - United StatesNo Copyright - United States
Technical Details

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    a| TL521.3.C6 b| A3 no. 2087
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    a| Cohen, Gerald A.
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    1
    4
    a| The effect of angle of attack on the buckling of Mars entry aeroshells / c| by Gerald A. Cohen.
    260
      
      
    a| Washington, D.C. : b| National Aeronautics and Space Administration ; a| Springfield, Va. : b| For sale by the National Technical Information Service [distributor], c| 1973.
    300
      
      
    a| iii, 18 p. : b| ill. ; c| 27 cm.
    490
      
    0
    a| NASA contractor report ; v| NASA CR-2087
    500
      
      
    a| "NASA CR-2087."
    500
      
      
    a| "February 1973."
    500
      
      
    a| Cover title.
    504
      
      
    a| Includes bibliographical references (p. 6).
    520
      
      
    a| The buckling modes of four optimized Mars entry aeroshell configurations at angle-of-attack loadings have been calculated. The analysis is based on experimental pressure distributions and was performed with the aid of a buckling digital computer program which treats general asymmetric linearized prebuckling states of branched shells of revolution. Only zero and first harmonic pressure components are treated, these being constructed from windward and leeward meridian pressure data at a mach number of 4.63. The results showed a rather small effect of the unsymmetrical pressure component on buckling for angles of attack up to 15 deg. Comparison of the results for the 120 deg cones to previous results indicates that the common procedure of basing the design on a symmetrized pressure distribution of the windward meridian is a conservative approach.
    536
      
      
    a| Prepared by Structures Research Associates, Laguna Beach, Calif. for Langley Research Center b| NAS1-10091 v| 124-08-20-04-00
    538
      
      
    a| Mode of access: Internet.
    650
      
    0
    a| Mars probes x| Aerodynamics x| Computer simulation.
    650
      
    0
    a| Buckling (Mechanics) x| Computer simulation.
    650
      
    0
    a| Elastic plates and shells x| Computer simulation.
    650
      
    7
    a| Stress analysis. 2| nasat
    650
      
    7
    a| Mechanical properties. 2| nasat
    650
      
    7
    a| Deformation. 2| nasat
    650
      
    7
    a| Conical bodies. 2| nasat
    650
      
    7
    a| Buckling. 2| nasat
    650
      
    7
    a| Reentry vehicles. 2| nasat
    650
      
    7
    a| Pressure distribution. 2| nasat
    650
      
    7
    a| Mars (planet). 2| nasat
    650
      
    7
    a| Dynamic structural analysis. 2| nasat
    650
      
    7
    a| Angle of attack. 2| nasat
    650
      
    7
    a| Aerospace vehicles. 2| nasat
    710
    2
      
    a| Langley Research Center.
    710
    2
      
    a| Structures Research Associates.
    974
      
      
    b| UIU c| UIUC d| 20141113 s| google u| uiug.30112106860205 y| 1973 r| pd q| bib

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