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)