4. OrbitalElements#

class OrbitalElements#

Bases: object

Provides methods for converting between state vectors and orbital elements.

Methods

rv2coe(grav_param, r, v[, threshHold])

Converts from vectors to classical orbital elements.
rv2coe(grav_param: float, r: ndarray[tuple[int, ...], dtype[_ScalarType_co]], v: ndarray[tuple[int, ...], dtype[_ScalarType_co]], threshHold: float = 1e-08)#

Converts from vectors 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.

Examples

# initial setup
import scarabaeus as scb