Bases: object
Performs conversions between Cartesian state vectors and classical orbital elements.
Provides static methods to convert between position/velocity vectors
(r, v) and Keplerian orbital elements (p, e, i, Ω, ω, ν), as
well as related quantities such as mean motion, period, and eccentric
anomaly.
Methods
-
rv2coe(grav_param: float, r: ndarray[tuple[Any, ...], dtype[_ScalarT]], v: ndarray[tuple[Any, ...], dtype[_ScalarT]], threshHold: float = 1e-08)
Convert state vector to classical orbital elements.
- Parameters:
grav_param (float) – Standard gravitational parameter in \(\frac{km^3}{s^2}\).
r (np.ndarray) – Position vector in kilometers.
v (np.ndarray) – Velocity vector in kilometers per second.
tol (float, optional) – Tolerance for eccentricity and inclination checks. Defaults to 1e-8.
- Returns:
p (float) – Semi-latus rectum of parameter in kilometers.
ecc (float) – Eccentricity.
inc (float) – Inclination in radians.
raan (float) – Right ascension of the ascending node in radians.
argp (float) – Argument of Perigee in radians.
nu (float) – True Anomaly in radians.
Notes
All angles are in radians; distances in km; velocities in km/s
