Kepleriean orbital elements
Represent Keplerian element sets and convert between cartesian
Notes
This class is used to represent Keplerian elements and convert between Cartesian coordinates
The class uses the semi-major axis (a), not the semiparameter
All angle units are radians
All length units are meters
All velocity units are meters / second
- property satkit.kepler.eccentric_anomaly
Eccentric anomaly, radians
- satkit.kepler.from_pv(vel: numpy.typing.ArrayLike[numpy.float64])
Create Keplerian element set from input position and velocity vectors
- Parameters:
pos (npt.ArrayLike[np.float64]) – 3-element array representing position vector
vel (npt.ArrayLike[np.float64]) – 3-element array representing velocity vector
- Returns:
Keplerian element set object
- Return type:
satkit.kepler
- property satkit.kepler.mean_anomaly
Mean anomaly, radians
- property satkit.kepler.mean_motion
Mean motion, radians / second
- property satkit.kepler.period
Orbital period, seconds
- satkit.kepler.propagate(dt: duration | float)
Propagate Keplerian element set by input duration
- Parameters:
dt (duration | float) – Duration by which to propagate the Keplerian element set If float, value is seconds
- Returns:
Keplerian element set object after propagation
- Return type:
satkit.kepler
- satkit.kepler.to_pv()
Convert Keplerian element set to position and velocity vectors
- Returns:
Tuple with two elements representing the position and velocity vectors
- Return type:
tuple[npt.ArrayLike[np.float64], npt.ArrayLike[np.float64]]
- property satkit.kepler.true_anomaly
True anomaly, radians