Python Orbit.from_vectors方法代码示例

# 需要导入模块: from poliastro.twobody.orbit import Orbit [as 别名]
# 或者: from poliastro.twobody.orbit.Orbit import from_vectors [as 别名]
def test_orbit_wrong_dimensions_fails():
    bad_r = [[1000, 0, 0]] * u.km
    bad_v = [[[0, 10, 0]]] * u.km / u.s

    with pytest.raises(ValueError) as excinfo:
        Orbit.from_vectors(Earth, bad_r, bad_v)
    assert "ValueError: Vectors must have dimension 1, got 2 and 3" in excinfo.exconly()

# 需要导入模块: from poliastro.twobody.orbit import Orbit [as 别名]
# 或者: from poliastro.twobody.orbit.Orbit import from_vectors [as 别名]
def test_state_raises_unitserror_if_rv_units_are_wrong():
    _d = [1.0, 0.0, 0.0] * u.AU
    wrong_v = [0.0, 1.0e-6, 0.0] * u.AU
    with pytest.raises(u.UnitsError) as excinfo:
        Orbit.from_vectors(Sun, _d, wrong_v)
    assert (
        "UnitsError: Argument 'v' to function 'from_vectors' must be in units convertible to 'm / s'."
        in excinfo.exconly()
    )

# 需要导入模块: from poliastro.twobody.orbit import Orbit [as 别名]
# 或者: from poliastro.twobody.orbit.Orbit import from_vectors [as 别名]
def test_orbit_accepts_ecliptic_plane():
    r = [1e09, -4e09, -1e09] * u.km
    v = [5e00, -1e01, -4e00] * u.km / u.s

    ss = Orbit.from_vectors(Sun, r, v, plane=Planes.EARTH_ECLIPTIC)

    assert ss.frame.is_equivalent_frame(HeliocentricEclipticJ2000(obstime=J2000))

# 需要导入模块: from poliastro.twobody.orbit import Orbit [as 别名]
# 或者: from poliastro.twobody.orbit.Orbit import from_vectors [as 别名]
def transform(orbit, frame_orig, frame_dest):
    """Transforms Orbit from one frame to another.

    Parameters
    ----------
    orbit : ~poliastro.bodies.Orbit
        Orbit to transform
    frame_orig : ~astropy.coordinates.BaseCoordinateFrame
        Initial frame
    frame_dest : ~astropy.coordinates.BaseCoordinateFrame
        Final frame

    Returns
    -------
    orbit: ~poliastro.bodies.Orbit
        Orbit in the new frame

    """

    orbit_orig = frame_orig(x=orbit.r[0], y=orbit.r[1], z=orbit.r[2],
                            v_x=orbit.v[0], v_y=orbit.v[1], v_z=orbit.v[2],
                            representation=CartesianRepresentation,
                            differential_type=CartesianDifferential)

    orbit_dest = orbit_orig.transform_to(frame_dest(obstime=orbit.epoch))
    orbit_dest.representation = CartesianRepresentation

    return Orbit.from_vectors(orbit.attractor,
                              orbit_dest.data.xyz,
                              orbit_dest.data.differentials['s'].d_xyz,
                              epoch=orbit.epoch)

# 需要导入模块: from poliastro.twobody.orbit import Orbit [as 别名]
# 或者: from poliastro.twobody.orbit.Orbit import from_vectors [as 别名]
def test_inertial_body_centered_to_pqw():
    molniya_r_peri, molniya_v_peri = coordinates.inertial_body_centered_to_pqw(molniya.r, molniya.v, bodies.Earth)

    molniya_peri = Orbit.from_vectors(bodies.Earth, molniya_r_peri, molniya_v_peri, molniya.epoch)

    assert_quantity_allclose(molniya_peri.e_vec[-2:], [0, 0], atol=1e-12)
    assert_quantity_allclose(norm(molniya_peri.e_vec), norm(molniya.e_vec))

# 需要导入模块: from poliastro.twobody.orbit import Orbit [as 别名]
# 或者: from poliastro.twobody.orbit.Orbit import from_vectors [as 别名]
def test_orbit_plot_static_3d():
    # Data from Curtis, example 4.3
    r = [-6045, -3490, 2500] * u.km
    v = [-3.457, 6.618, 2.533] * u.km / u.s
    ss = Orbit.from_vectors(Earth, r, v)
    with pytest.raises(ValueError, match="static and use_3d cannot be true"):
        ss.plot(static=True, use_3d=True)

# 需要导入模块: from poliastro.twobody.orbit import Orbit [as 别名]
# 或者: from poliastro.twobody.orbit.Orbit import from_vectors [as 别名]
def test_orbit_no_frame_representation():
    date_launch = Time("2011-11-26 15:02", scale="utc")
    r = [61445.76498656, 24827.93010168, 0.0] * u.km
    v = [-0.42581645, -0.18867869, 0.0] * u.km / u.s
    ss = Orbit.from_vectors(Moon, r, v, date_launch)
    expected_str = "106 x -142299 km x 180.0 deg orbit around Moon (\u263E) at epoch 2011-11-26 15:02:00.000 (UTC)"

    assert str(ss) == repr(ss) == expected_str

# 需要导入模块: from poliastro.twobody.orbit import Orbit [as 别名]
# 或者: from poliastro.twobody.orbit.Orbit import from_vectors [as 别名]
def test_sample_big_orbits(method):
    # See https://github.com/poliastro/poliastro/issues/265
    ss = Orbit.from_vectors(
        Sun,
        [-9018878.6, -94116055, 22619059] * u.km,
        [-49.950923, -12.948431, -4.2925158] * u.km / u.s,
    )
    positions = ss.sample(15, method=method)
    assert len(positions) == 15

# 需要导入模块: from poliastro.twobody.orbit import Orbit [as 别名]
# 或者: from poliastro.twobody.orbit.Orbit import from_vectors [as 别名]
def hyperbolic():
    r = [1.197659243752796e09, -4.443716685978071e09, -1.747610548576734e09] * u.km
    v = (
        [5.540549267188614e00, -1.251544669134140e01, -4.848892572767733e00]
        * u.km
        / u.s
    )
    epoch = Time("2015-07-14 07:59", scale="tdb")
    return Orbit.from_vectors(Sun, r, v, epoch)

# 需要导入模块: from poliastro.twobody.orbit import Orbit [as 别名]
# 或者: from poliastro.twobody.orbit.Orbit import from_vectors [as 别名]
def test_orbit_plot_is_not_static(use_3d):
    from plotly.graph_objs import FigureWidget

    # Data from Curtis, example 4.3
    r = [-6045, -3490, 2500] * u.km
    v = [-3.457, 6.618, 2.533] * u.km / u.s
    ss = Orbit.from_vectors(Earth, r, v)
    plot = ss.plot(static=False, use_3d=use_3d)
    assert isinstance(plot, FigureWidget)

# 需要导入模块: from poliastro.twobody.orbit import Orbit [as 别名]
# 或者: from poliastro.twobody.orbit.Orbit import from_vectors [as 别名]
def test_orbit_plot_is_static():

    # Data from Curtis, example 4.3
    r = [-6045, -3490, 2500] * u.km
    v = [-3.457, 6.618, 2.533] * u.km / u.s
    ss = Orbit.from_vectors(Earth, r, v)
    plot = ss.plot(static=True)
    assert isinstance(plot[0], matplotlib.lines.Line2D)
    assert isinstance(plot[1], matplotlib.lines.Line2D)

# 需要导入模块: from poliastro.twobody.orbit import Orbit [as 别名]
# 或者: from poliastro.twobody.orbit.Orbit import from_vectors [as 别名]
def test_pqw_returns_dimensionless():
    r_0 = ([1, 0, 0] * u.au).to(u.km)
    v_0 = ([0, 6, 0] * u.au / u.year).to(u.km / u.day)
    ss = Orbit.from_vectors(Sun, r_0, v_0)

    p, q, w = ss.pqw()

    assert p.unit == u.one
    assert q.unit == u.one
    assert w.unit == u.one

# 需要导入模块: from poliastro.twobody.orbit import Orbit [as 别名]
# 或者: from poliastro.twobody.orbit.Orbit import from_vectors [as 别名]
def test_orbit_has_proper_frame(attractor, expected_frame_class):
    # Dummy data
    r = [1e09, -4e09, -1e09] * u.km
    v = [5e00, -1e01, -4e00] * u.km / u.s
    epoch = Time("2015-07-14 07:59", scale="tdb")

    ss = Orbit.from_vectors(attractor, r, v, epoch)

    assert ss.frame.is_equivalent_frame(expected_frame_class(obstime=epoch))
    assert ss.frame.obstime == epoch

# 需要导入模块: from poliastro.twobody.orbit import Orbit [as 别名]
# 或者: from poliastro.twobody.orbit.Orbit import from_vectors [as 别名]
def test_hyperbolic_modulus_wrapped_nu():
    ss = Orbit.from_vectors(
        Sun,
        [-9.77441841e07, 1.01000539e08, 4.37584668e07] * u.km,
        [23.75936985, -43.09599568, -8.7084724] * u.km / u.s,
    )
    num_values = 3

    positions = ss.sample(num_values)

    assert_quantity_allclose(positions[0].data.xyz, ss.r)

# 需要导入模块: from poliastro.twobody.orbit import Orbit [as 别名]
# 或者: from poliastro.twobody.orbit.Orbit import from_vectors [as 别名]
def test_sample_num_points(num_points):
    # Data from Vallado, example 2.4
    r0 = [1131.340, -2282.343, 6672.423] * u.km
    v0 = [-5.64305, 4.30333, 2.42879] * u.km / u.s
    ss0 = Orbit.from_vectors(Earth, r0, v0)

    # TODO: Test against the perigee and apogee
    # expected_ss = ss0.propagate(ss0.period / 2)

    rr = ss0.sample(num_points)

    assert len(rr) == num_points