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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    Title :

    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


    Additional title:

    Space Technology Library


    Contributors:


    Publication date :

    2021-04-13


    Size :

    55 pages




    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English