Following the method of the rendezvous technique used in Reference [1] and Chapter 2 to generate the motion of a spacecraft in near-circular orbit perturbed by Earth’s J2 and J3 zonals, and described in the rotating Euler-Hill frame, the same approach is used in this chapter and based on Reference [2] to obtain analytic expression for the spacecraft motion perturbed by the luni-solar gravity.


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    Titel :

    Analytic Solutions for the Perturbed Motion of a Spacecraft in Near-Circular Orbit, Under the Influence of the Luni-Solar Gravity, in Rotating and Inertial Cartesian Reference Frames


    Weitere Titelangaben:

    Space Technology Library


    Beteiligte:


    Erscheinungsdatum :

    2021-04-13


    Format / Umfang :

    55 pages




    Medientyp :

    Aufsatz/Kapitel (Buch)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch