def test_DeltaOmega(t_max=160):
time, r0, v0 = integrate_orbits(t_max=t_max, coupled=False)
time, r, v = integrate_orbits(t_max=160, coupled=True)
DeltaOmegaU = omega(v0[:, 0], r0[:, 0]) - omega(v[:, 0], r[:, 0])
result = [DeltaOmegaU.min(), DeltaOmegaU.max()]
assert_array_almost_equal(result,
[-1.0492366485e-05, 7.84639028908e-05],
err_msg="DeltaOmega incorrect")
def test_uranus_initial_conditions(t_max=10, dt=0.01):
time, r, v = integrate_orbits(t_max=t_max, dt=dt)
assert_equal(len(r), int(t_max/dt))
assert_array_almost_equal(r[0, 0], np.array([-17.30163539, -8.30441128]),
err_msg="Uranus initial position wrong")
assert_array_almost_equal(v[0, 0], np.array([-0.62108718, 1.29398985]),
err_msg="Uranus initinal velocity wrong")
def test_neptune_initial_conditions(t_max=10, dt=0.01):
time, r, v = integrate_orbits(t_max=t_max, dt=dt)
assert_equal(len(r), int(t_max/dt))
assert_array_almost_equal(r[0, 1], np.array([ 9.47879984, -28.52756714]),
err_msg="Neptune initial position wrong")
assert_array_almost_equal(v[0, 1], np.array([-1.08771092, -0.36141161]),
err_msg="Neptune initinal velocity wrong")
