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Monday, November 30, 2020 | History

2 edition of Numerical modeling of on-orbit propellant motion resulting from an impulsive acceleration found in the catalog.

Numerical modeling of on-orbit propellant motion resulting from an impulsive acceleration

Numerical modeling of on-orbit propellant motion resulting from an impulsive acceleration

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Published by National Aeronautics and Space Administration, For sale by the National Technical Information Service in [Washington, DC], [Springfield, Va .
Written in English

    Subjects:
  • Fluid dynamics.

  • Edition Notes

    Other titlesNumerical modeling of on orbit propellant motion resulting from an impulsive acceleration.
    StatementJohn C. Aydelott ... [et al.].
    SeriesNASA technical memorandum -- 89873.
    ContributionsAydelott, John C., United States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL18033374M

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Numerical modeling of on-orbit propellant motion resulting from an impulsive acceleration Download PDF EPUB FB2

Get this from a library. Numerical modeling of on-orbit propellant motion resulting from an impulsive acceleration. [John C Aydelott; United States. National Aeronautics and Space Administration.;]. Numerical modeling of on-orbit propellant motion resulting from an impulsive acceleration. JOHN AYDELOTT, RAYMOND MJOLSNESS, A multidomain and multidimensional numerical analysis of flow in fuelside preburner, high pressure turbine, hot gas manifold and main injector assembly of the Space Shuttle main engine Modeling shock/boundary.

Although the shuttle/Centaur development activity has been suspended, the numerical modeling techniques are available to predict on-orbit liquid motion resulting from impulsive accelerations for.

Phase field modeling of liquid jets in low gravity Numerical modeling of on-orbit propellant motion resulting from an impulsive acceleration to predict on-orbit liquid motion resulting Author: David Chato. Section 3 presents a single impulsive control law to correct relative angular momentum and energy for formation design.

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RCS thrusters, engines common to both the SM and the LSAM ascent stage, are used for on-orbit maneuvering. The SM propellant tanks are sized to perform up to 1, m/s of service propulsion system and 50 m/s of RCS delta-V with the CEV CM attached and 15 m/s of RCS delta-V after separation.

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The impulsive transfer case, even including flybys, is thus a parameter optimization problem with the parameters being such quantities as the timing, magnitude, and direction of the impulsive V’s and the timing and altitude.

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