def test_true_anom():
r""" Test for True Anomaly Function
"""
r_vector = [1, 2, 3]
h_vector = [-3, 6, -3]
e_vector = [2, 3, 4]
actual_out = RV2COE.true_anom(r_vector, h_vector, e_vector)
expected_out = -0.12186756768575521
np.testing.assert_allclose(actual_out, expected_out)
r_input = [r_i, r_j, r_k]
v_input = [v_i, v_j, v_k]
Line_1 = ("The mu Constant: \n\t", str(mu), "\n", 'Radius {} (km)\n\t{}\n'.format(count+1,r_input))
Line_2 = ('Velocity {} (km/s)\n\t{}\n'.format(count+1,v_input))
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)