poliastro.twobody.states

Module Contents

Classes

BaseState

Base State class, meant to be subclassed.

ClassicalState

State defined by its classical orbital elements.

RVState

State defined by its position and velocity vectors.

ModifiedEquinoctialState

State defined by modified equinoctial elements representation.

class poliastro.twobody.states.BaseState(attractor, elements, plane)

Base State class, meant to be subclassed.

property plane

Fundamental plane of the frame.

property attractor

Main attractor.

n()

Mean motion.

period()

Period of the orbit.

r_p()

Radius of pericenter.

r_a()

Radius of apocenter.

t_p()

Elapsed time since latest perifocal passage.

to_tuple()
abstract to_value()

Converts to raw values with appropriate units.

abstract to_vectors()

Converts to position and velocity vector representation.

Return type

RVState

abstract to_classical()

Converts to classical orbital elements representation.

Return type

ClassicalState

abstract to_equinoctial()

Converts to modified equinoctial elements representation.

Return type

ModifiedEquinoctialState

class poliastro.twobody.states.ClassicalState(attractor, elements, plane)

Bases: BaseState

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 p

Semilatus rectum.

property a

Semimajor axis.

property ecc

Eccentricity.

property inc

Inclination.

property raan

Right ascension of the ascending node.

property argp

Argument of the perigee.

property nu

True anomaly.

to_value()

Converts to raw values with appropriate units.

to_vectors()

Converts to position and velocity vector representation.

to_classical()

Converts to classical orbital elements representation.

to_equinoctial()

Converts to modified equinoctial elements representation.

property plane

Fundamental plane of the frame.

property attractor

Main attractor.

n()

Mean motion.

period()

Period of the orbit.

r_p()

Radius of pericenter.

r_a()

Radius of apocenter.

t_p()

Elapsed time since latest perifocal passage.

to_tuple()
class poliastro.twobody.states.RVState(attractor, elements, plane)

Bases: BaseState

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.

property v

Velocity vector.

to_value()

Converts to raw values with appropriate units.

to_vectors()

Converts to position and velocity vector representation.

to_classical()

Converts to classical orbital elements representation.

property plane

Fundamental plane of the frame.

property attractor

Main attractor.

n()

Mean motion.

period()

Period of the orbit.

r_p()

Radius of pericenter.

r_a()

Radius of apocenter.

t_p()

Elapsed time since latest perifocal passage.

to_tuple()
abstract to_equinoctial()

Converts to modified equinoctial elements representation.

Return type

ModifiedEquinoctialState

class poliastro.twobody.states.ModifiedEquinoctialState(attractor, elements, plane)

Bases: BaseState

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 p

Semilatus rectum.

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 L

True longitude.

to_value()

Converts to raw values with appropriate units.

to_classical()

Converts to classical orbital elements representation.

to_vectors()

Converts to position and velocity vector representation.

property plane

Fundamental plane of the frame.

property attractor

Main attractor.

n()

Mean motion.

period()

Period of the orbit.

r_p()

Radius of pericenter.

r_a()

Radius of apocenter.

t_p()

Elapsed time since latest perifocal passage.

to_tuple()
abstract to_equinoctial()

Converts to modified equinoctial elements representation.

Return type

ModifiedEquinoctialState