Adjustment can be accomplished by electric propulsion systems limited to thrust levels in millipounds; near polar 750-nautical-mi orbit with precession error of 0.029°/day is chosen; perturbation equations of motion are used to derive total impulse required to correct error; spiraling operation or altitude change can accomplish correction with 2050-lb-sec total impulse for 670-lb satellite; 5-mlb resistojet requires 11.3 days whereas 300- μlb ion engine requires 79.1 days for same correction; methods of inclination adjustment and providing constant precession bias require more total impulse and are therefore less efficient than spiraling approach.


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    Titel :

    Orbit adjustment of sun-synchronous satellites with electric propulsion


    Weitere Titelangaben:

    J Spacecraft Rockets


    Beteiligte:
    Barrett, C.C. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1968


    Format / Umfang :

    4 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :