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From M.Eng. René Schwarz, Bremen/Merseburg
M001: Keplerian Orbit Elements to Cartesian State Vectors
This Memorandum contains an algorithm for converting a traditional set of Keplerian Orbit Elements (semi-major axis, eccentricity, argument of periapsis, longitude of ascending node, inclination, and mean anomaly) to cartesian state vectors (position and velocity vector).
Keywords:
Kepler, Orbit, Elements, Cartesian, State, Vector, Rotation, Matrix
M002: Cartesian State Vectors to Keplerian Orbit Elements
This Memorandum contains an algorithm for converting cartesian state vectors (position and velocity vector) to a traditional set of Keplerian Orbit Elements (semi-major axis, eccentricity, argument of periapsis, longitude of ascending node, inclination, and mean anomaly).
Keywords:
Kepler, Orbit, Elements, Cartesian, State, Vector
