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This document discusses elliptical orbits, which have an eccentricity between 0 and 1. It provides the key equations for calculating parameters of an elliptical orbit such as the semi-major axis, semi-minor axis, apoapsis distance, and cartesian coordinates as a function of true anomaly. The semi-major axis is equal to the sum of the periapsis and apoapsis distances. The semi-minor axis can be calculated from the semi-major axis and eccentricity. Cartesian coordinates of a point on the elliptical orbit are

Author

Anush Saini

Language

EN