poliastro.earth

Earth focused orbital mechanics routines

Subpackages

Submodules

Package Contents

Classes

EarthSatellite

Position and velocity of a body with respect to Earth

class poliastro.earth.EarthSatellite(orbit, spacecraft)

Position and velocity of a body with respect to Earth at a given time

property orbit

Orbit of the EarthSatellite.

property spacecraft

Spacecraft of the EarthSatellite.

propagate(tof, atmosphere=None, gravity=None, *args)

Propagates an ‘EarthSatellite Orbit’ at a specified time.

If value is true anomaly, propagate orbit to this anomaly and return the result. Otherwise, if time is provided, propagate this EarthSatellite Orbit some time and return the result.

Parameters
  • tof (Quantity, Time, TimeDelta) – Scalar time to propagate.

  • atmosphere – a callable model from poliastro.earth.atmosphere

  • gravity (EarthGravity) – There are two possible values, SPHERICAL and J2. Only J2 is implemented at the moment. Default value is None.

  • *args – parameters used in perturbation models.

Returns

A new EarthSatellite with the propagated Orbit

Return type

EarthSatellite