pylupnt.Satellite

class pylupnt.Satellite

Keplerian satellite propagated with Earth two-body dynamics (km units).

property GM_

Gravitational parameter [km^3/s^2].

property coe_

Classical orbital elements (a, e, i, Omega, w, M).

property epoch_utc_

Epoch [s UTC past J2000].

get_pos(self: pylupnt._pylupnt.Satellite) → Annotated[numpy.typing.NDArray[numpy.float64], '[3, 1]']

Position in ECI coordinates [km].

get_pos_epoch(self: pylupnt._pylupnt.Satellite, dt: SupportsFloat | SupportsIndex) → Annotated[numpy.typing.NDArray[numpy.float64], '[3, 1]']

Position [km] propagated forward by dt [s] from the current epoch.

property id_

Satellite ID (PRN).

property posvel_

Position/velocity state [km, km/s].

propagate(self: pylupnt._pylupnt.Satellite, epoch_utc_new: SupportsFloat | SupportsIndex) → None

Propagate the satellite state to a new UTC epoch [s past J2000].