boinor.twobody.states

classes of different states defined by their elements

classical orbital elements.

p : Semilatus rectum. ecc : Eccentricity. inc : Inclination. raan : Right ascension of the ascending node. argp : Argument of the perigee. nu : True anomaly.

position and velocity vectors.

r : Position vector wrt attractor center. v : Velocity vector.

modified equinoctial elements representation.

p : Semilatus rectum. f : Second modified equinoctial element. g : Third modified equinoctial element. h : Fourth modified equinoctial element. k : Fifth modified equinoctial element. L : True longitude.

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.

Module Contents

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

Base State class, meant to be subclassed.

property plane

Fundamental plane of the frame.

property attractor

Main attractor.

property n

Mean motion.

property period

Period of the orbit.

property r_p

Radius of pericenter.

property r_a

Radius of apocenter.

property t_p

Elapsed time since latest perifocal passage.

to_tuple()

Converts to Six-tuple of orbital elements.

abstractmethod to_value()

Converts to raw values with appropriate units.

abstractmethod to_vectors()

Converts to position and velocity vector representation.

Return type:

RVState

abstractmethod to_classical()

Converts to classical orbital elements representation.

Return type:

ClassicalState

abstractmethod to_equinoctial()

Converts to modified equinoctial elements representation.

Return type:

ModifiedEquinoctialState

class boinor.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.

property n

Mean motion.

property period

Period of the orbit.

property r_p

Radius of pericenter.

property r_a

Radius of apocenter.

property t_p

Elapsed time since latest perifocal passage.

to_tuple()

Converts to Six-tuple of orbital elements.

class boinor.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.

to_equinoctial()

Converts to modified equinoctial elements representation.

property plane

Fundamental plane of the frame.

property attractor

Main attractor.

property n

Mean motion.

property period

Period of the orbit.

property r_p

Radius of pericenter.

property r_a

Radius of apocenter.

property t_p

Elapsed time since latest perifocal passage.

to_tuple()

Converts to Six-tuple of orbital elements.

class boinor.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.

to_equinoctial()

Converts to modified equinoctial elements representation.

property plane

Fundamental plane of the frame.

property attractor

Main attractor.

property n

Mean motion.

property period

Period of the orbit.

property r_p

Radius of pericenter.

property r_a

Radius of apocenter.

property t_p

Elapsed time since latest perifocal passage.

to_tuple()

Converts to Six-tuple of orbital elements.