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.
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
Space Technology Library
2021-04-13
55 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch