Planet¶
Base class of planets.
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class
pyplanets.planets.planet.Planet(epoch: pyplanets.core.epoch.Epoch, VSOP87_L, VSOP87_B, VSOP87_R, ORBITAL_ELEM, ORBITAL_ELEM_J2000)[source]¶ Abstract base class for planets.
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__init__(epoch: pyplanets.core.epoch.Epoch, VSOP87_L, VSOP87_B, VSOP87_R, ORBITAL_ELEM, ORBITAL_ELEM_J2000)[source]¶ - Initializes an object of type planet for a given date (epoch) with
its orbital parameters (ephemeredes) given by VSOP87.
- Parameters
epoch (
Epoch) – Epoch to which all computations of this instance refer, as an Epoch object- Raises
TypeError if epoch is of wrong type.
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__weakref__¶ list of weak references to the object (if defined)
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abstract
aphelion() → pyplanets.core.epoch.Epoch[source]¶ This method computes the time of Aphelion closest to the epoch of initialization. Subclasses are required to implement this method.
- Returns
The epoch of the desired Aphelion
- Return type
Epoch
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apparent_heliocentric_position(nutation=True)[source]¶ This method computes the apparent heliocentric position of a planet for a given epoch, using the VSOP87 theory.
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apparent_planetcentric_sun_position(nutation=True)[source]¶ Generalization of coordinate transformation applicable to all planets. For Planet Earth, this method returns Sun’s apparent geocentric position, i.e. Sun.apparent_geocentric_position(…) in PyMeeus-Classic. Basically a simple transformation!
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geometric_heliocentric_position(tofk5=True)[source]¶ This method computes the geometric heliocentric position of a planet for a given epoch, using the VSOP87 theory.
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orbital_elements_j2000()[source]¶ This method computes the orbital elements of Mars for the standard equinox J2000.0 for a given epoch.
- Returns
A tuple containing the following six orbital elements: - Mean longitude of the planet (Angle) - Semimajor axis of the orbit (float, astronomical units) - eccentricity of the orbit (float) - inclination on the plane of the ecliptic (Angle) - longitude of the ascending node (Angle) - argument of the perihelion (Angle)
- Return type
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orbital_elements_mean_equinox()[source]¶ This method computes the orbital elements of Mars for the mean equinox of the date for a given epoch.
- Returns
A tuple containing the following six orbital elements: - Mean longitude of the planet (Angle) - Semimajor axis of the orbit (float, astronomical units) - eccentricity of the orbit (float) - inclination on the plane of the ecliptic (Angle) - longitude of the ascending node (Angle) - argument of the perihelion (Angle)
- Return type
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passage_nodes(ascending=True) -> (<class 'pyplanets.core.epoch.Epoch'>, <class 'float'>)[source]¶ This function computes the time of passage by the nodes (ascending or descending) of the planet, nearest to the given epoch.
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abstract
perihelion() → pyplanets.core.epoch.Epoch[source]¶ This method computes the time of Perihelion closest to the epoch of initialization. Subclasses are required to implement this method.
- Returns
The epoch of the desired Perihelion
- Return type
Epoch
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