def test_moving_body_pointing_law(self):
"""
moving_body_pointing_law test
"""
parameters = {
"eccentricity": 0.0008641,
"semimajor_axis": 6801395.04,
"inclination": 87.0,
"perigee_argument": 20.0,
"right_ascension_of_ascending_node": 10.0,
"anomaly": radians(0.0),
"anomaly_type": "TRUE",
"orbit_update_date":'2021-12-02T00:00:00.000',
"frame": "EME"}
parameters1 = {
"eccentricity": 0.0008641,
"semimajor_axis": 6801395.04,
"inclination": 87.0,
"perigee_argument": 10.0,
"right_ascension_of_ascending_node": 10.0,
"anomaly": radians(0.0),
"anomaly_type": "TRUE",
"orbit_update_date":'2021-12-02T00:00:00.000',
"frame": "EME"}
orbit_propagator_1 = analytical_propagator(parameters1)
orbit_propagator_2 = analytical_propagator(parameters1)
parameters["frame"] = orekit_utils.frame_to_string(orbit_propagator_1.getFrame())
time_to_propagate = orekit_utils.absolute_time_converter_utc_string('2022-05-02T00:00:00.000')
orbit_to_track_propagator = analytical_propagator(parameters)
test1 = CelestialBodyPointed(FramesFactory.getEME2000(), orbit_to_track_propagator,
Vector3D.PLUS_K, Vector3D.PLUS_K,
Vector3D.MINUS_J)
test2 = moving_body_pointing_law(orbit_to_track_propagator, parameters)
orbit_propagator_1.setAttitudeProvider(test1)
orbit_propagator_2.setAttitudeProvider(test2)
state_1 = orbit_propagator_1.propagate(time_to_propagate)
state_2 = orbit_propagator_2.propagate(time_to_propagate)
self.assertTrue((state_1.getAttitude().getSpin().toString() == state_2.getAttitude().getSpin().toString()))
def test_ground_pointing_law(self):
"""
ground_pointing_law test
"""
parameters = {"latitude": 12.0, "altitude": 2343.0, "longitude": 12.0}
parameters1 = {
"eccentricity": 0.0008641,
"semimajor_axis": 6801395.04,
"inclination": 87.0,
"perigee_argument": 10.0,
"right_ascension_of_ascending_node": 10.0,
"anomaly": radians(0.0),
"anomaly_type": "TRUE",
"orbit_update_date": '2021-12-02T00:00:00.000',
"frame": "EME"
}
orbit_propagator_1 = analytical_propagator(parameters1)
orbit_propagator_2 = analytical_propagator(parameters1)
parameters["frame"] = orekit_utils.frame_to_string(
orbit_propagator_1.getFrame())
ITRF = FramesFactory.getITRF(IERSConventions.IERS_2010, True)
target = GeodeticPoint(parameters["latitude"], parameters["longitude"],
parameters["altitude"])
attitude_provider = ground_pointing_law(parameters)
attitude_provider_1 = TargetPointing(
FramesFactory.getEME2000(), target,
OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS,
Constants.WGS84_EARTH_FLATTENING, ITRF))
orbit_propagator_1.setAttitudeProvider(attitude_provider)
orbit_propagator_2.setAttitudeProvider(attitude_provider_1)
time_to_propagate = orekit_utils.absolute_time_converter_utc_string(
'2022-05-02T00:00:00.000')
state_1 = orbit_propagator_1.propagate(time_to_propagate)
state_2 = orbit_propagator_2.propagate(time_to_propagate)
self.assertTrue((state_1.getAttitude().getSpin().toString() ==
state_2.getAttitude().getSpin().toString()))
def test_attitude_provider_constructor(self):
"""
attitude_provider_constructor test
"""
moving_body = "moving_body_tracking"
moving_body_param = {
"eccentricity": 0.0008641,
"semimajor_axis": 6801395.04,
"inclination": 87.0,
"perigee_argument": 10.0,
"right_ascension_of_ascending_node": 10.0,
"anomaly": 0.0,
"anomaly_type": "TRUE",
"orbit_update_date":"2021-12-02T00:00:00.000",
"frame": "EME"}
orbit_params = {
"eccentricity": 0.0008641,
"semimajor_axis": 6801395.04,
"inclination": 87.0,
"perigee_argument": 20.0,
"right_ascension_of_ascending_node": 10.0,
"anomaly": 0.0,
"anomaly_type": "TRUE",
"orbit_update_date":'2021-12-02T00:00:00.000',
"frame": "EME"}
orbit_propagator_1 = analytical_propagator(orbit_params)
orbit_propagator_2 = analytical_propagator(orbit_params)
attitude_m_body = attitude_provider_constructor(moving_body, moving_body_param)
attitude_m_body_1 = moving_body_pointing_law(analytical_propagator(moving_body_param),moving_body_param)
orbit_propagator_1.setAttitudeProvider(attitude_m_body)
orbit_propagator_2.setAttitudeProvider(attitude_m_body_1)
time_to_propagate = orekit_utils.absolute_time_converter_utc_string('2022-05-02T00:00:00.000')
state_1 = orbit_propagator_1.propagate(time_to_propagate)
state_2 = orbit_propagator_2.propagate(time_to_propagate)
self.assertTrue((state_1.getAttitude().getSpin().toString() == state_2.getAttitude().getSpin().toString()))
ground = "ground_tracking"
ground_param = {
"latitude": 12.0,
"altitude": 2343.0,
"longitude":12.0
}
parameters = {
"eccentricity": 0.0008641,
"semimajor_axis": 6801395.04,
"inclination": 87.0,
"perigee_argument": 10.0,
"right_ascension_of_ascending_node": 10.0,
"anomaly": radians(0.0),
"anomaly_type": "TRUE",
"orbit_update_date":'2021-12-02T00:00:00.000',
"frame": "EME"}
orbit_propagator_1 = analytical_propagator(parameters)
orbit_propagator_2 = analytical_propagator(parameters)
ground_param["frame"] = orekit_utils.frame_to_string(orbit_propagator_1.getFrame())
attitude_provider_1 = attitude_provider_constructor(ground, ground_param)
attitude_provider_2 = ground_pointing_law(ground_param)
orbit_propagator_1.setAttitudeProvider(attitude_provider_1)
orbit_propagator_2.setAttitudeProvider(attitude_provider_2)
time_to_propagate = orekit_utils.absolute_time_converter_utc_string('2022-05-02T00:00:00.000')
state_1 = orbit_propagator_1.propagate(time_to_propagate)
state_2 = orbit_propagator_2.propagate(time_to_propagate)
self.assertTrue((state_1.getAttitude().getSpin().toString() == state_2.getAttitude().getSpin().toString()))