def test_correct_pericenter_J2_exception():
ss0 = Orbit.from_classical(
Mercury,
1000 * u.km,
0 * u.one,
0 * u.deg,
0 * u.deg,
0 * u.deg,
0 * u.deg,
)
max_delta_r = 30 * u.km
with pytest.raises(NotImplementedError) as excinfo:
Maneuver.correct_pericenter(ss0, max_delta_r)
assert excinfo.type == NotImplementedError
assert (str(
excinfo.value
) == f"The correction maneuver is not yet supported for {ss0.attractor}")
def test_correct_pericenter_ecc_exception():
ss0 = Orbit.from_classical(
Earth,
1000 * u.km,
0.5 * u.one,
0 * u.deg,
0 * u.deg,
0 * u.deg,
0 * u.deg,
)
max_delta_r = 30 * u.km
with pytest.raises(NotImplementedError) as excinfo:
Maneuver.correct_pericenter(ss0, max_delta_r)
assert excinfo.type == NotImplementedError
assert (
str(excinfo.value) ==
f"The correction maneuver is not yet supported with {ss0.ecc},it should be less than or equal to 0.001"
)
def test_correct_pericenter(attractor, max_delta_r, a, ecc, inc, expected_t,
expected_v):
ss0 = Orbit.from_classical(
attractor,
a,
ecc,
inc,
0 * u.deg,
0 * u.deg,
0 * u.deg,
)
maneuver = Maneuver.correct_pericenter(ss0, max_delta_r)
assert_quantity_allclose(maneuver[0][0], expected_t)
assert_quantity_allclose(maneuver[0][1].value.tolist(),
expected_v.value.tolist())
