def test_leo_geo_numerical(inc_0): f = 3.5e-7 # km / s2 a_0 = 7000.0 # km a_f = 42166.0 # km inc_f = 0.0 # rad k = Earth.k.to(u.km**3 / u.s**2).value a_d, _, t_f = change_a_inc(k, a_0, a_f, inc_0, inc_f, f) # Retrieve r and v from initial orbit s0 = Orbit.circular(Earth, a_0 * u.km - Earth.R, inc_0 * u.rad) # Propagate orbit def f_leo_geo(t0, u_, k): du_kep = func_twobody(t0, u_, k) ax, ay, az = a_d(t0, u_, k) du_ad = np.array([0, 0, 0, ax, ay, az]) return du_kep + du_ad sf = s0.propagate(t_f * u.s, method=cowell, f=f_leo_geo, rtol=1e-6) assert_allclose(sf.a.to(u.km).value, a_f, rtol=1e-3) assert_allclose(sf.ecc.value, 0.0, atol=1e-2) assert_allclose(sf.inc.to(u.rad).value, inc_f, atol=2e-3)
def test_leo_geo_time_and_delta_v(inc_0, expected_t_f, expected_delta_V, rtol): f = 3.5e-7 # km / s2 a_0 = 7000.0 # km a_f = 42166.0 # km inc_f = 0.0 # rad k = Earth.k.to(u.km**3 / u.s**2).value inc_0 = np.radians(inc_0) # rad _, delta_V, t_f = change_a_inc(k, a_0, a_f, inc_0, inc_f, f) assert_allclose(delta_V, expected_delta_V, rtol=rtol) assert_allclose((t_f * u.s).to(u.day).value, expected_t_f, rtol=rtol)
def test_leo_geo_time_and_delta_v(inc_0, expected_t_f, expected_delta_V, rtol): f = 3.5e-7 # km / s2 a_0 = 7000.0 # km a_f = 42166.0 # km inc_f = 0.0 # rad k = Earth.k.to(u.km**3 / u.s**2).value inc_0 = np.radians(inc_0) # rad _, delta_V, t_f = change_a_inc(k, a_0, a_f, inc_0, inc_f, f) assert_allclose(delta_V, expected_delta_V, rtol=rtol) assert_allclose((t_f * u.s).to(u.day).value, expected_t_f, rtol=rtol)
def test_leo_geo_numerical(inc_0): f = 3.5e-7 # km / s2 a_0 = 7000.0 # km a_f = 42166.0 # km inc_f = 0.0 # rad k = Earth.k.to(u.km**3 / u.s**2).value a_d, _, t_f = change_a_inc(k, a_0, a_f, inc_0, inc_f, f) # Retrieve r and v from initial orbit s0 = Orbit.circular(Earth, a_0 * u.km - Earth.R, inc_0 * u.rad) # Propagate orbit sf = s0.propagate(t_f * u.s, method=cowell, ad=a_d, rtol=1e-6) assert_allclose(sf.a.to(u.km).value, a_f, rtol=1e-3) assert_allclose(sf.ecc.value, 0.0, atol=1e-2) assert_allclose(sf.inc.to(u.rad).value, inc_f, atol=2e-3)
def test_leo_geo_numerical(inc_0): f = 3.5e-7 # km / s2 a_0 = 7000.0 # km a_f = 42166.0 # km inc_f = 0.0 # rad k = Earth.k.to(u.km**3 / u.s**2).value a_d, _, t_f = change_a_inc(k, a_0, a_f, inc_0, inc_f, f) # Retrieve r and v from initial orbit s0 = Orbit.circular(Earth, a_0 * u.km - Earth.R, inc_0 * u.rad) # Propagate orbit sf = s0.propagate(t_f * u.s, method=cowell, ad=a_d, rtol=1e-6) assert_allclose(sf.a.to(u.km).value, a_f, rtol=1e-3) assert_allclose(sf.ecc.value, 0.0, atol=1e-2) assert_allclose(sf.inc.to(u.rad).value, inc_f, atol=2e-3)