poliastro2.core.twobody.states

Classes

BaseState(attractor, elements, plane)	Base State class, meant to be subclassed.
ClassicalState(attractor, elements, plane)	State defined by its classical orbital elements.
ModifiedEquinoctialState(attractor, ...)	State defined by modified equinoctial elements representation.
RVState(attractor, elements, plane)	State defined by its position and velocity vectors.

class poliastro2.core.twobody.states.BaseState(attractor, elements, plane)

Base State class, meant to be subclassed.

property attractor

Main attractor.

property n

Mean motion.

property period

Period of the orbit.

property plane

Fundamental plane of the frame.

property r_a

Radius of apocenter.

property r_p

Radius of pericenter.

property t_p

Elapsed time since latest perifocal passage.

to_classical()

Converts to classical orbital elements representation.

Return type:

ClassicalState

to_equinoctial()

Converts to modified equinoctial elements representation.

Return type:

ModifiedEquinoctialState

to_tuple()

to_value()

Converts to raw values with appropriate units.

to_vectors()

Converts to position and velocity vector representation.

Return type:

RVState

class poliastro2.core.twobody.states.ClassicalState(attractor, elements, plane)

State defined by its classical orbital elements.

Orbital elements:

p~astropy.units.Quantity

Semilatus rectum.

ecc~astropy.units.Quantity

Eccentricity.

inc~astropy.units.Quantity

Inclination.

raan~astropy.units.Quantity

Right ascension of the ascending node.

argp~astropy.units.Quantity

Argument of the perigee.

nu~astropy.units.Quantity

True anomaly.

property a

Semimajor axis.

property argp

Argument of the perigee.

property ecc

Eccentricity.

property inc

Inclination.

property nu

True anomaly.

property p

Semilatus rectum.

property raan

Right ascension of the ascending node.

to_classical()

Converts to classical orbital elements representation.

to_equinoctial()

Converts to modified equinoctial elements representation.

to_value()

Converts to raw values with appropriate units.

to_vectors()

Converts to position and velocity vector representation.

class poliastro2.core.twobody.states.ModifiedEquinoctialState(attractor, elements, plane)

State defined by modified equinoctial elements representation.

Orbital elements:

p~astropy.units.Quantity

Semilatus rectum.

f~astropy.units.Quantity

Second modified equinoctial element.

g~astropy.units.Quantity

Third modified equinoctial element.

h~astropy.units.Quantity

Fourth modified equinoctial element.

k~astropy.units.Quantity

Fifth modified equinoctial element.

L~astropy.units.Quantity

True longitude.

property L

True longitude.

property f

Second modified equinoctial element.

property g

Third modified equinoctial element.

property h

Fourth modified equinoctial element.

property k

Fifth modified equinoctial element.

property p

Semilatus rectum.

to_classical()

Converts to classical orbital elements representation.

to_value()

Converts to raw values with appropriate units.

to_vectors()

Converts to position and velocity vector representation.

class poliastro2.core.twobody.states.RVState(attractor, elements, plane)

State defined by its position and velocity vectors.

Orbital elements:

r~astropy.units.Quantity

Position vector wrt attractor center.

v~astropy.units.Quantity

Velocity vector.

property r

Position vector.

to_classical()

Converts to classical orbital elements representation.

to_value()

Converts to raw values with appropriate units.

to_vectors()

Converts to position and velocity vector representation.

property v

Velocity vector.