def test_get_keplerian_parameters(self):
"""
get_keplerian_parameters test
"""
parameters = {
"eccentricity": 0.0008641,
"semimajor_axis": 6801395.04,
"inclination": radians(87.0),
"perigee_argument": radians(20.0),
"right_ascension_of_ascending_node": radians(10.0),
"anomaly": radians(0.0),
"anomaly_type": "TRUE",
"orbit_update_date":'2021-12-02T00:00:00.000',
"frame": "EME"}
propagator_1 = analytical_propagator(parameters)
orbit = keplerian_orbit(parameters)
new_state = SpacecraftState(orbit)
new_parameters = orekit_utils.get_keplerian_parameters(new_state)
propagator_2 = keplerian_orbit(new_parameters)
new_time = absolute_time_converter_utc_string('2021-12-05T00:00:00.000')
distance = orekit_utils.find_sat_distance(propagator_1, propagator_2, new_time)
# parameters value change but define same orbit
self.assertTrue(distance <= 0.000001)
def test_analytical_propagator(self):
"""
analytical_propagator test
"""
parameters = {
"eccentricity": 0.0008641,
"semimajor_axis": 6801395.04,
"inclination": radians(87.0),
"perigee_argument": radians(20.0),
"right_ascension_of_ascending_node": radians(10.0),
"anomaly": radians(0.0),
"anomaly_type": "TRUE",
"orbit_update_date": '2021-12-02T00:00:00.000',
"frame": "EME"
}
k_orbit = keplerian_orbit(parameters)
test1 = analytical_propagator(parameters)
test2 = KeplerianPropagator(keplerian_orbit(parameters),
Constants.WGS84_EARTH_MU)
time1 = orekit_utils.absolute_time_converter_utc_string(
'2022-01-02T00:00:00.000')
self.assertTrue(
test1.getPVCoordinates(time1, FramesFactory.getEME2000()).toString(
) == test2.getPVCoordinates(time1,
FramesFactory.getEME2000()).toString())
def test_keplerian_orbit(self):
"""
keplerian_orbit test
"""
parameters = {
"eccentricity": 0.0008641,
"semimajor_axis": 6801395.04,
"inclination": radians(87.0),
"perigee_argument": radians(20.0),
"right_ascension_of_ascending_node":radians(10.0),
"anomaly": radians(0.0),
"anomaly_type": "TRUE",
"orbit_update_date":'2021-12-02T00:00:00.000',
"frame": "EME"}
k_orbit = keplerian_orbit(parameters)
eccentricity = parameters["eccentricity"]
semimajor_axis = parameters["semimajor_axis"]
inclination = parameters["inclination"]
perigee_argument = parameters["perigee_argument"]
right_ascension_of_ascending_node = parameters["right_ascension_of_ascending_node"]
true_anomaly = parameters["anomaly"]
orbit_update_date = parameters["orbit_update_date"]
epochDate = absolute_time_converter_utc_string(orbit_update_date)
frame = orekit_utils.string_to_frame(parameters["frame"])
self.assertTrue(KeplerianOrbit(semimajor_axis, eccentricity, inclination, perigee_argument,
right_ascension_of_ascending_node,
true_anomaly, PositionAngle.TRUE,
frame, epochDate,
Constants.WGS84_EARTH_MU).toString() == k_orbit.toString())