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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Orbit adjustment of sun-synchronous satellites with electric propulsion


    Additional title:

    J Spacecraft Rockets


    Contributors:

    Published in:

    Publication date :

    1968


    Size :

    4 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :