astrodynx

Kepler Equations

kepler_equ_elps	Returns the Kepler's equation for elliptical orbits in the form f(E) = 0.
kepler_equ_hypb	Returns the Kepler's equation for hyperbolic orbits in the form f(H) = 0.
kepler_equ_uni	Returns the universal Kepler's equation in the form f(chi) = 0.
generalized_anomaly	Returns the generalized anomaly.
mean_anomaly_elps	Returns the mean anomaly for an elliptical orbit.
mean_anomaly_hypb	Returns the mean anomaly for a hyperbolic orbit.
solve_kepler_elps	Returns the eccentric anomaly for an elliptical orbit.
solve_kepler_hypb	Returns the hyperbolic eccentric anomaly for a hyperbolic orbit.
solve_kepler_uni	Returns the generalized anomaly for a universal orbit equation.
dE	Returns the derivative of Kepler's equation for elliptical orbits with respect to the eccentric anomaly.
dH	Returns the derivative of Kepler's equation for hyperbolic orbits with respect to the hyperbolic eccentric anomaly.

Orbit Integrals

orb_period	Returns the orbital period of a two-body system.
a_from_period	Returns the semimajor axis of a two-body system from its orbital period.
angular_momentum	Returns the specific angular momentum of a two-body system.
semimajor_axis	Returns the semimajor axis of a two-body orbit.
eccentricity_vector	Returns the eccentricity vector of a two-body orbit.
semiparameter	Returns the semiparameter of a two-body orbit.
mean_motion	Returns the mean motion of a two-body orbit.
equ_of_orbit	Returns the equation of the orbit in the two-body system.
equ_of_orb_uvi	The equation of orbit using universal functions
radius_periapsis	Returns the radius of periapsis of the orbit.
radius_apoapsis	Returns the radius of apoapsis of the orbit.
semipara_from_ae	Returns the semiparameter of the orbit from the semimajor axis and eccentricity.
a_from_pe	Returns the semimajor axis of the orbit from the semiparameter and eccentricity.

Orbit State Conversions

rv2coe	Transfer position and velocity vectors to classical orbital elements.
coe2rv	Transfer classical orbital elements to position and velocity vectors.
inclination	Returns the inclination of a two-body orbit.
true_anomaly	Returns the true anomaly of a two-body orbit.
right_ascension	Returns the right ascension of the ascending node of a two-body orbit.
argument_of_periapsis	Returns the argument of periapsis of a two-body orbit.

Module Information

Full name: astrodynx

Source: View source on GitHub