opihiexarata.orbit.custom module

This is a class which defines a custom orbit. A user supplies the orbital elements to this engine and the vehicle function.

class opihiexarata.orbit.custom.CustomOrbitEngine(semimajor_axis: float, eccentricity: float, inclination: float, longitude_ascending_node: float, argument_perihelion: float, mean_anomaly: float, epoch_julian_day: float, semimajor_axis_error: float = None, eccentricity_error: float = None, inclination_error: float = None, longitude_ascending_node_error: float = None, argument_perihelion_error: float = None, mean_anomaly_error: float = None)[source]

Bases: OrbitEngine

This engine is just a wrapper for when a custom orbit is desired to be specified.

semimajor_axis

The semi-major axis of the orbit provided, in AU.

Type:: float

semimajor_axis_error

The error on the semi-major axis of the orbit provided, in AU.

Type:: float

eccentricity

The eccentricity of the orbit provided.

Type:: float

eccentricity_error

The error on the eccentricity of the orbit provided.

Type:: float

inclination

The angle of inclination of the orbit provided, in degrees.

Type:: float

inclination_error

The error on the angle of inclination of the orbit provided, in degrees.

Type:: float

longitude_ascending_node

The longitude of the ascending node of the orbit provided, in degrees.

Type:: float

longitude_ascending_node_error

The error on the longitude of the ascending node of the orbit provided, in degrees.

Type:: float

argument_perihelion

The argument of perihelion of the orbit provided, in degrees.

Type:: float

argument_perihelion_error

The error on the argument of perihelion of the orbit provided, in degrees.

Type:: float

mean_anomaly

The mean anomaly of the orbit provided, in degrees.

Type:: float

mean_anomaly_error

The error on the mean anomaly of the orbit provided, in degrees.

Type:: float

epoch_julian_day

The epoch where for these osculating orbital elements. This value is in Julian days.

Type:: float

__init__(semimajor_axis: float, eccentricity: float, inclination: float, longitude_ascending_node: float, argument_perihelion: float, mean_anomaly: float, epoch_julian_day: float, semimajor_axis_error: float = None, eccentricity_error: float = None, inclination_error: float = None, longitude_ascending_node_error: float = None, argument_perihelion_error: float = None, mean_anomaly_error: float = None) → None[source]

The orbital elements are already provided for this custom solution. If errors may optionally be provided.

Parameters:

semimajor_axis (float) – The semi-major axis of the orbit provided, in AU.
eccentricity (float) – The eccentricity of the orbit provided.
inclination (float) – The angle of inclination of the orbit provided, in degrees.
longitude_ascending_node (float) – The longitude of the ascending node of the orbit provided, in degrees.
argument_perihelion (float) – The argument of perihelion of the orbit provided, in degrees.
mean_anomaly (float) – The mean anomaly of the orbit provided, in degrees.
epoch_julian_day (float) – The epoch where for these osculating orbital elements. This value is in Julian days.
semimajor_axis_error (float, default = None) – The error on the semi-major axis of the orbit provided, in AU.
eccentricity_error (float, default = None) – The error on the eccentricity of the orbit provided.
inclination_error (float, default = None) – The error on the angle of inclination of the orbit provided, in degrees.
longitude_ascending_node_error (float, default = None) – The error on the longitude of the ascending node of the orbit provided, in degrees.
argument_perihelion_error (float, default = None) – The error on the argument of perihelion of the orbit provided, in degrees.
mean_anomaly_error (float, default = None) – The error on the mean anomaly of the orbit provided, in degrees.

Return type:

None