Orbital_motion module

Orbital_motion.kepler_equation(E, M, e)

Returns the Kepler equation: M = E - e sin(E)

Parameters:

• E (float) – the eccentric anomaly

• M (float) – the mean anomaly

• e (float) – the eccentricity

Returns:

E - e*np.sin(E) - M

Return type:

float

Orbital_motion.solve_kepler(M, e)

Solve the Kepler equation to find the eccentric anomaly E.

Parameters:

• E (float) – the eccentric anomaly

• M (float) – the mean anomaly

Returns:

E

Return type:

float

Orbital_motion.true_anomaly(E, e)

Computes the true anomaly from the eccentric anomaly and the eccentricity.

Parameters:

• E (float) – the eccentric anomaly

• e (float) – the eccentricity

Returns:

nu

Return type:

float

Orbital_motion.compute_true_anomaly(nu_0, e, T, t, t_0=0)

Computes the true anomaly with respect to time.

Parameters:

• nu_0 (float) – the initial true anomaly (in rad)

• e (float) – the eccentricity

• T (float) – the orbital period

• t (float) – the time passed

• t_0 (float) – the initial time (default value: 0)

Returns:

nu_t

Return type:

float

Orbital_motion.main()