[SA1-2-10-1] Keplerian elements (Two-Body Problem)

The Keplerian orbit of the satellite is defined by the following six orbital parameters: the right ascension of ascending node, the inclination of the orbital plane, the argument of perigee, the semi-major axis of the orbital ellipse, the numerical eccentricity of the orbit and the perigee passing time.

External resources

• Sanz Subirana, J., Juan Zornoza, J.M. and Hernández-Pajares, M. (2013) GNSS Data Processing, Vol. 1: Fundamentals and Algorithms (ESA TM-23/1, May 2013) ESA Communications, Noordwijk, The Netherlands.

Outgoing relations

• [SA1-2-10-1] Keplerian elements (Two-Body Problem) is subconcept of [SA1-2-10] Orbital elements