The low-eccentricity earth satellite orbit at the critical inclination

descriptionPublicationkeyboard_double_arrow_right Article 01 Oct 1978 English Publisher:Springer Science and Business Media LLCJournal:Celestial Mechanics, volume 18, pages 233-236 (issn: 0008-8714, eissn: 1572-9478,

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Authors: Lyddane, R. H.; Cohen, Charles J.;

doi: 10.1007/bf01230163

The low-eccentricity earth satellite orbit at the critical inclination

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Abstract

A solution to the orbital motion of an Earth satellite at the critical inclination and with near-zero eccentricity is developed by the von Zeipel method to the first order in the eccentricity, and to the first order in the higher gravitational harmonics, using elements which do not degenerate at zero eccentricity.

Related Organizations

Naval Air Systems Command
United States
Naval Air Warfare Center Weapons Division
United States

Keywords

Delaunay Variables, Celestial mechanics, Orbital mechanics, Critical Inclination, Satellite Orbit, Orbital Mechanics, Earth Potential, Eccentricity, Perturbation, Poincare Variables

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