poliastro.twobody.elements

Module Contents

Functions

circular_velocity(k, a)

Circular velocity for a given body (k) and semimajor axis (a).

mean_motion(k, a)

Mean motion given body (k) and semimajor axis (a).

period(k, a)

Period given body (k) and semimajor axis (a).

hyp_nu_limit(ecc, r_max_ratio=np.inf)

Limit true anomaly for hyperbolic orbits.

get_eccentricity_critical_argp(R, J2, J3, a, inc)

Cccentricity for frozen orbits when the argument of perigee is critical.

get_inclination_critical_argp(R, J2, J3, a, ecc)

Inclination for frozen orbits

get_eccentricity_critical_inc(ecc=None)

Eccentricity for frozen orbits when the inclination is critical.

poliastro.twobody.elements.u_kms
poliastro.twobody.elements.u_km3s2
poliastro.twobody.elements.circular_velocity(k, a)

Circular velocity for a given body (k) and semimajor axis (a).

poliastro.twobody.elements.mean_motion(k, a)

Mean motion given body (k) and semimajor axis (a).

poliastro.twobody.elements.period(k, a)

Period given body (k) and semimajor axis (a).

poliastro.twobody.elements.hyp_nu_limit(ecc, r_max_ratio=np.inf)

Limit true anomaly for hyperbolic orbits.

Parameters
  • ecc (Quantity) – Eccentricity, should be larger than 1.

  • r_max_ratio (float, optional) – Value of \(r_{\text{max}} / p\) for this angle, default to infinity.

poliastro.twobody.elements.get_eccentricity_critical_argp(R, J2, J3, a, inc)

Cccentricity for frozen orbits when the argument of perigee is critical.

Parameters
poliastro.twobody.elements.get_inclination_critical_argp(R, J2, J3, a, ecc)

Inclination for frozen orbits when the argument of perigee is critical and the eccentricity is given.

Parameters
poliastro.twobody.elements.get_eccentricity_critical_inc(ecc=None)

Eccentricity for frozen orbits when the inclination is critical.

If ecc is None we set an arbitrary value which is the Moon eccentricity because it seems reasonable.

Parameters

ecc (Quantity, optional) – Eccentricity, default to None.