def test_Orbit_Period():
r""" Test for Orbital Period Function
"""
mu = 2
a = 2
actual_out = RV2COE.Orbit_Period(mu, a)
expected_out = 12.5663706144
np.testing.assert_allclose(actual_out, expected_out)
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
if (raan < 0):
raan = 2 * np.pi + raan
else:
raan = raan
if (w < 0):
w = 2 * np.pi + w
else:
w = w
if (i < 0):
i = 2 * np.pi + i