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Mean anomaly
Appendix a Orbits
Perturbation Theory in Celestial Mechanics
New Closed-Form Solutions for Optimal Impulsive Control of Spacecraft Relative Motion
SATELLITES ORBIT ELEMENTS : EPHEMERIS, Keplerian ELEMENTS, STATE VECTORS
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Arxiv:2010.00559V2 [Astro-Ph.EP] 3 Jan 2021 E-Mail:
[email protected]
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[email protected]
2 Jackson Kulik
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