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from astropy import units as u
import numpy as np
from numpy.testing import assert_allclose
from boinor.bodies import Earth
# lots of functions are already checked somewhere else
# unfortunately mee2rv is missing
from boinor.core.elements import coe2mee, coe2rv, mee2coe, mee2rv, rv2coe
def test_conversions():
# taken from the rv2coe() example
# this is a bad example as it results in 90 < i <180, which is a retrograde orbit
# and coe2mee() can not handle this
# k = Earth.k.to_value(u.km**3 / u.s**2)
# r = np.array([-6045.0, -3490.0, 2500.0])
# v = np.array([-3.457, 6.618, 2.533])
# this values are better
k = Earth.k.to_value(u.km**3 / u.s**2)
r = np.array([-6045.0, -3490.0, 2500.0])
v = np.array([-3.457, -6.618, -2.533])
p_coe, ecc_coe, inc_coe, raan_coe, argp_coe, nu_coe = rv2coe(k, r, v)
p_mee, f_mee, g_mee, h_mee, k_mee, L_mee = coe2mee(
p_coe, ecc_coe, inc_coe, raan_coe, argp_coe, nu_coe
)
p_coe2, ecc_coe2, inc_coe2, raan_coe2, argp_coe2, nu_coe2 = mee2coe(
p_mee, f_mee, g_mee, h_mee, k_mee, L_mee
)
assert_allclose(p_coe, p_coe2)
assert_allclose(ecc_coe, ecc_coe2)
assert_allclose(inc_coe, inc_coe2)
assert_allclose(raan_coe, raan_coe2)
assert_allclose(argp_coe, argp_coe2)
assert_allclose(nu_coe, nu_coe2)
r_rv, v_rv = mee2rv(k, p_mee, f_mee, g_mee, h_mee, k_mee, L_mee)
# print("r:", r, " <-> ", r_rv)
# print("v:", v, " <-> ", v_rv)
assert_allclose(r, r_rv)
assert_allclose(v, v_rv)
r_new, v_new = coe2rv(
k, p_coe, ecc_coe, inc_coe, raan_coe, argp_coe, nu_coe
)
assert_allclose(r, r_new)
assert_allclose(v, v_new)
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