Abstract
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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References
Kechichian, J. A. (1989). Analytic solution for the perturbed motion in near-circular orbit due to J2, J3 earth zonal harmonics in rotating and inertial Cartesian reference frames, AIAA Paper 89-0352, AIAA 27th aerospace sciences meeting, Reno.
Kechichian, J. A. (1988). Analytic solution of perturbed motion in near-circular orbit due to luni-solar gravity in rotating and inertial Cartesian frames, AIAA Paper 88-4295, AIAA/AAS astrodynamics conference, Minneapolis.
Brouwer, D., & Clemence, G. M. (1961). Methods of celestial mechanics, Academic.
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Kéchichian, J.A. (2021). 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. In: Orbital Relative Motion and Terminal Rendezvous. Space Technology Library, vol 39. Springer, Cham. https://doi.org/10.1007/978-3-030-64657-8_3
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DOI: https://doi.org/10.1007/978-3-030-64657-8_3
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