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, plane)

Base State class, meant to be subclassed.

property plane(self)

Fundamental plane of the frame.

property attractor(self)

Main attractor.

property n(self)

Mean motion.

property period(self)

Period of the orbit.

abstract to_vectors(self)

Converts to position and velocity vector representation.

Return type

RVState

abstract to_classical(self)

Converts to classical orbital elements representation.

Return type

ClassicalState

abstract to_equinoctial(self)

Converts to modified equinoctial elements representation.

Return type

ModifiedEquinoctialState

class poliastro.twobody.states.ClassicalState(attractor, p, ecc, inc, raan, argp, nu, plane)

Bases: BaseState

State defined by its classical orbital elements.

property p(self)

Semilatus rectum.

property a(self)

Semimajor axis.

property ecc(self)

Eccentricity.

property inc(self)

Inclination.

property raan(self)

Right ascension of the ascending node.

property argp(self)

Argument of the perigee.

property nu(self)

True anomaly.

to_vectors(self)

Converts to position and velocity vector representation.

to_classical(self)

Converts to classical orbital elements representation.

to_equinoctial(self)

Converts to modified equinoctial elements representation.

class poliastro.twobody.states.RVState(attractor, r, v, plane)

Bases: BaseState

State defined by its position and velocity vectors.

property r(self)

Position vector.

property v(self)

Velocity vector.

to_vectors(self)

Converts to position and velocity vector representation.

to_classical(self)

Converts to classical orbital elements representation.

class poliastro.twobody.states.ModifiedEquinoctialState(attractor, p, f, g, h, k, L, plane)

Bases: BaseState

State defined by modified equinoctial elements representation.

property p(self)

Semilatus rectum.

property f(self)

Second modified equinoctial element.

property g(self)

Third modified equinoctial element.

property h(self)

Fourth modified equinoctial element.

property k(self)

Fifth modified equinoctial element.

property L(self)

True longitude.

to_classical(self)

Converts to classical orbital elements representation.