def test_R_A_A_N():
r""" Test for RAAN Function
"""
n_vector = [.25, .5, .75]
actual_out = RV2COE.R_A_A_N(n_vector)
expected_out = 1.1071487177940904
np.testing.assert_allclose(actual_out, expected_out)
r"""Inner Workings, Pulling outside functions"""
h_input = RV2COE.ang_momentum(r_input, v_input)
e_vector = RV2COE.eccentricity(mu, r_input, v_input, h_input)
n_vector = RV2COE.line_of_nodes(RV2COE.unit_vector(h_input))
p = RV2COE.semi_latus_rectum(mu, h_input)
theta = RV2COE.true_anom(r_input, h_input, e_vector)
i = RV2COE.inclination(RV2COE.unit_vector(h_input))
a = RV2COE.semi_major_axis(p, np.linalg.norm(e_vector))
raan = RV2COE.R_A_A_N(n_vector)
w = RV2COE.arg_of_periapsis(n_vector, e_vector, h_input)
r_p = RV2COE.rad_peri(p, np.linalg.norm(e_vector))
r_a = RV2COE.rad_apo(p, np.linalg.norm(e_vector))
gamma = RV2COE.flight_ang(np.linalg.norm(e_vector), theta)
period = RV2COE.Orbit_Period(mu, a)
if (theta < 0):
theta = 2 * np.pi + theta
else:
theta = theta