Item Details

Dynamic Characteristics of a Two-Stage Variable-Mass Flexible Missile With Internal Flow

Leonard Meirovitch and John Bankovskis
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], 1972.
Language
English
Series
NASA Contractor Report
Summary
A general formulation of the dynamical problems associated with powered flight of a two stage flexible, variable-mass missile with internal flow, discrete masses, and aerodynamic forces is presented. The formulation comprises six ordinary differential equations for the rigid body motion, 3n ordinary differential equations for the n discrete masses and three partial differential equations with the appropriate boundary conditions for the elastic motion. This set of equations is modified to represent a single stage flexible, variable-mass missile with internal flow and aerodynamic forces. The rigid-body motion consists then of three translations and three rotations, whereas the elastic motion is defined by one longitudinal and two flexural displacements, the latter about two orthogonal transverse axes. The differential equations are nonlinear and, in addition, they possess time-dependent coefficients due to the mass variation.
Description
iii, 135 p. : ill. ; 27 cm.
Mode of access: Internet.
Notes
  • "NASA CR-2076."
  • "June 1972."
  • Cover title.
  • Bibliography: p. 118-120.
Series Statement
NASA contractor report ; NASA CR-2076
Other Forms
Also available via Internet from the NASA Technical Reports Server (http://ntrs.nasa.gov/). Address as of 6/22/06: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19720023267%5f1972023267.pdf.
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Technical Details

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    a| Dynamic characteristics of a two-stage variable-mass flexible missile with internal flow / c| Leonard Meirovitch and John Bankovskis.
    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| 1972.
    300
      
      
    a| iii, 135 p. : b| ill. ; c| 27 cm.
    490
      
    0
    a| NASA contractor report ; v| NASA CR-2076
    500
      
      
    a| "NASA CR-2076."
    500
      
      
    a| "June 1972."
    500
      
      
    a| Cover title.
    504
      
      
    a| Bibliography: p. 118-120.
    520
      
      
    a| A general formulation of the dynamical problems associated with powered flight of a two stage flexible, variable-mass missile with internal flow, discrete masses, and aerodynamic forces is presented. The formulation comprises six ordinary differential equations for the rigid body motion, 3n ordinary differential equations for the n discrete masses and three partial differential equations with the appropriate boundary conditions for the elastic motion. This set of equations is modified to represent a single stage flexible, variable-mass missile with internal flow and aerodynamic forces. The rigid-body motion consists then of three translations and three rotations, whereas the elastic motion is defined by one longitudinal and two flexural displacements, the latter about two orthogonal transverse axes. The differential equations are nonlinear and, in addition, they possess time-dependent coefficients due to the mass variation.
    530
      
      
    a| Also available via Internet from the NASA Technical Reports Server (http://ntrs.nasa.gov/). Address as of 6/22/06: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19720023267%5f1972023267.pdf.
    536
      
      
    a| Prepared by University of Cincinnati, Cincinnati, Ohio for Langley Research Center c| NGR 36-004-030
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    a| Mode of access: Internet.
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    0
    a| Rockets (Aeronautics) x| Aerodynamics x| Computer simulation.
    650
      
    7
    a| Variable mass systems . 2| nasat
    650
      
    7
    a| Transient response. 2| nasat
    650
      
    7
    a| Thrust loads. 2| nasat
    650
      
    7
    a| Internal combustion engines. 2| nasat
    650
      
    7
    a| Flexible bodies. 2| nasat
    650
      
    7
    a| Residual stress. 2| nasat
    650
      
    7
    a| Missile structures. 2| nasat
    650
      
    7
    a| Dynamic structural analysis. 2| nasat
    650
      
    7
    a| Aeroelasticity. 2| nasat
    700
    1
      
    a| Bankovskis, John.
    710
    2
      
    a| Langley Research Center.
    710
    2
      
    a| University of Cincinnati.
    974
      
      
    b| UIU c| UIUC d| 20141113 s| google u| uiug.30112106859934 y| 1972 r| pd q| bib

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