# Buggy code
def farnocchia(k, r0, v0, tof):
    r"""Propagates orbit using mean motion.

    This algorithm depends on the geometric shape of the orbit.
    For the case of the strong elliptic or strong hyperbolic orbits:

    ..  math::

        M = M_{0} + \frac{\mu^{2}}{h^{3}}\left ( 1 -e^{2}\right )^{\frac{3}{2}}t

    .. versionadded:: 0.9.0

    Parameters
    ----------
    k : float
        Standar Gravitational parameter
    r0 : ~astropy.units.Quantity
        Initial position vector wrt attractor center.
    v0 : ~astropy.units.Quantity
        Initial velocity vector.
    tof : float
        Time of flight (s).

    Note
    ----
    This method takes initial :math:`\vec{r}, \vec{v}`, calculates classical orbit parameters,
    increases mean anomaly and performs inverse transformation to get final :math:`\vec{r}, \vec{v}`
    The logic is based on formulae (4), (6) and (7) from http://dx.doi.org/10.1007/s10569-013-9476-9

    """

    # get the initial true anomaly and orbit parameters that are constant over time
    p, ecc, inc, raan, argp, nu0 = rv2coe(k, r0, v0)

    # get the initial mean anomaly
    M0 = nu_to_M(nu0, ecc)
    if np.abs(ecc - 1.0) > 1e-2:
        # strong elliptic or strong hyperbolic orbits
        a = p / (1.0 - ecc**2)
        n = np.sqrt(k / np.abs(a**3))
    else:
        # near-parabolic orbit
        q = p / np.abs(1.0 + ecc)
        n = np.sqrt(k / 2.0 / (q**3))

    M = M0 + tof * n
    nu = M_to_nu(M, ecc)

    return coe2rv(k, p, ecc, inc, raan, argp, nu)


# Traceback (FloatingPointError)
$ NUMBA_DISABLE_JIT=1 ipython --no-banner

In [1]: import numpy as np

In [2]: np.seterr(all="raise")
Out[2]: {'divide': 'warn', 'over': 'warn', 'under': 'ignore', 'invalid': 'warn'}

In [3]: import numpy as np
...: import math
...: from astropy import units as u
...: from poliastro.bodies import Earth, Moon
...: from poliastro.twobody import Orbit
...:
...: r=[8.e3, 1.e3, 0.]*u.km
...: v=[-0.5, -0.5, 0.]*u.km/u.s
...: orbit1=Orbit.from_vectors(Earth,r,v)
...: orbit2=orbit1.propagate(1.*u.h)
...:
...:
---------------------------------------------------------------------------
FloatingPointError                        Traceback (most recent call last)
<ipython-input-3-08d7b74965c9> in <module>()
8 v=[-0.5, -0.5, 0.]*u.km/u.s
9 orbit1=Orbit.from_vectors(Earth,r,v)
---> 10 orbit2=orbit1.propagate(1.*u.h)

~/.miniconda36/envs/poliastro37/lib/python3.7/site-packages/poliastro/twobody/orbit.py in propagate(self, value, method, rtol, **kwargs)
403                 time_of_flight = time.TimeDelta(value)
404
--> 405             return propagate(self, time_of_flight, method=method, rtol=rtol, **kwargs)
406
407     def sample(self, values=None, method=mean_motion):

~/.miniconda36/envs/poliastro37/lib/python3.7/site-packages/poliastro/twobody/propagation.py in propagate(orbit, time_of_flight, method, rtol, **kwargs)
177
178     """
--> 179     r, v = method(orbit, time_of_flight.to(u.s).value, rtol=rtol, **kwargs)
180     return orbit.from_vectors(orbit.attractor, r * u.km, v * u.km / u.s, orbit.epoch + time_of_flight, orbit.plane)

~/.miniconda36/envs/poliastro37/lib/python3.7/site-packages/poliastro/twobody/propagation.py in mean_motion(orbit, tofs, **kwargs)
118
119     if not hasattr(tofs, '__len__'):
--> 120         return mean_motion_fast(k, r0, v0, tofs)
121
122     results = [mean_motion_fast(k, r0, v0, tof) for tof in tofs]

~/.miniconda36/envs/poliastro37/lib/python3.7/site-packages/poliastro/core/propagation.py in mean_motion(k, r0, v0, tof)
33
34     # get the initial mean anomaly
---> 35     M0 = nu_to_M(nu0, ecc)
36     # strong elliptic or strong hyperbolic orbits
37     if np.abs(ecc - 1.0) > 1e-2:

~/.miniconda36/envs/poliastro37/lib/python3.7/site-packages/poliastro/core/angles.py in nu_to_M(nu, ecc, delta)
183     else:
184         D = nu_to_D(nu)
--> 185         M = D_to_M(D, ecc)
186     return M
187

~/.miniconda36/envs/poliastro37/lib/python3.7/site-packages/poliastro/core/angles.py in D_to_M(D, ecc)
155 @jit
156 def D_to_M(D, ecc):
--> 157     M = _kepler_equation_parabolic(D, 0.0, ecc)
158     return M
159

~/.miniconda36/envs/poliastro37/lib/python3.7/site-packages/poliastro/core/angles.py in _kepler_equation_parabolic(D, M, ecc)
26 @jit
27 def _kepler_equation_parabolic(D, M, ecc):
---> 28     return M_parabolic(ecc, D) - M
29
30

~/.miniconda36/envs/poliastro37/lib/python3.7/site-packages/poliastro/core/angles.py in M_parabolic(ecc, D, tolerance)
41     k = 0
42     while not small_term:
---> 43         term = (ecc - 1.0 / (2.0 * k + 3.0)) * (x ** k)
44         small_term = np.abs(term) < tolerance
45         S += term

FloatingPointError: overflow encountered in double_scalars

# Fixed code
def farnocchia(k, r0, v0, tof):
    r"""Propagates orbit using mean motion.

    This algorithm depends on the geometric shape of the orbit.
    For the case of the strong elliptic or strong hyperbolic orbits:

    ..  math::

        M = M_{0} + \frac{\mu^{2}}{h^{3}}\left ( 1 -e^{2}\right )^{\frac{3}{2}}t

    .. versionadded:: 0.9.0

    Parameters
    ----------
    k : float
        Standar Gravitational parameter
    r0 : ~astropy.units.Quantity
        Initial position vector wrt attractor center.
    v0 : ~astropy.units.Quantity
        Initial velocity vector.
    tof : float
        Time of flight (s).

    Note
    ----
    This method takes initial :math:`\vec{r}, \vec{v}`, calculates classical orbit parameters,
    increases mean anomaly and performs inverse transformation to get final :math:`\vec{r}, \vec{v}`
    The logic is based on formulae (4), (6) and (7) from http://dx.doi.org/10.1007/s10569-013-9476-9

    """

    # get the initial true anomaly and orbit parameters that are constant over time
    p, ecc, inc, raan, argp, nu0 = rv2coe(k, r0, v0)
    q = p / (1 + ecc)

    delta_t0 = delta_t_from_nu(nu0, ecc, k, q)
    delta_t = delta_t0 + tof

    nu = nu_from_delta_t(delta_t, ecc, k, q)

    return coe2rv(k, p, ecc, inc, raan, argp, nu)