Kepleriean orbital elements
- class satkit.kepler(*args, **kwargs)
Bases:
objectRepresent 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
- a
Semi-major axis, meters
- eccen
Eccentricity, unitless
- eccentric_anomaly
Eccentric anomaly, radians
- static from_pv(r, v)
Create Keplerian element set from input position and velocity vectors
Args:
pos (npt.ArrayLike[np.float64])3-element array representing position vector
vel (npt.ArrayLike[np.float64])3-element array representing velocity vector
Returns:
satkit.keplerKeplerian element set object
- inclination
Inclination, radians
- mean_anomaly
Mean anomaly, radians
- mean_motion
Mean motion, radians / second
- nu
True anomaly, radians
- period
Orbital period, seconds
- raan
Right ascension of ascending node, radians
- to_pv()
Convert Keplerian element set to position and velocity vectors
Returns:
tuple[npt.ArrayLike[np.float64], npt.ArrayLike[np.float64]]Tuple with two elements representing the position and velocity vectors
- true_anomaly
True anomaly, radians
- w
Argument of perigee, radians
- kepler.propagate(dt)
Propagate Keplerian element set by input duration
Args:
dt (duration | float)Duration by which to propagate the Keplerian element set If float, value is seconds
Returns:
satkit.keplerKeplerian element set object after propagation