def interpolate(self,
step_size: float,
num_points: int = 5) -> OrbitEphemerisMessage:
"""Interpolates the ephemeris data to the desired time step size.
:param step_size: The interpolated step size in seconds.
:param num_points: The number of states to use for interpolation.
"""
epochs, state_vects = [], []
for emph_line in self.ephemeris_lines:
epochs.append(emph_line.epoch)
# Convert components from m and m\s to km and km\s
state_vect = [i * 1000.0 for i in emph_line.state_vector]
state_vects.append(state_vect)
offset_epochs = conv.get_J2000_epoch_offset(epochs)
interpolation = interpolate_ephemeris(self.ref_frame, offset_epochs,
state_vects, num_points,
self.ref_frame, offset_epochs[0],
offset_epochs[-1], step_size)
interp_ephem_lines = []
for proto_buf in interpolation:
epoch = conv.get_UTC_string(proto_buf.time)
state_vector = [i / 1000.0 for i in list(proto_buf.true_state)]
interp_ephem_line = EphemerisLine(epoch=epoch,
state_vector=state_vector)
interp_ephem_lines.append(interp_ephem_line)
interp_oem_data = self.copy()
interp_oem_data.ephemeris_lines = interp_ephem_lines
return interp_oem_data
def predict(self):
self.predict["state"] = "disabled"
start = get_J2000_epoch_offset(self.start_time.get())
end = get_J2000_epoch_offset(self.end_time.get())
data, tle = {}, [
l for l in self.tle.get("0.0", "end-1c").splitlines()
if l.startswith("1") or l.startswith("2")
]
for f in [
"latitude", "longitude", "altitude", "fov_azimuth",
"fov_elevation", "fov_aperture", "step_size"
]:
data[f] = [
float(t.strip()) for t in getattr(self, f).get().split(",")
]
if (f not in ["altitude", "step_size"]):
data[f] = [d * Constant.DEGREE_TO_RAD for d in data[f]]
cfg_list = []
sim_meas = len(data["latitude"]) <= 2 or len(data["latitude"]) != len(
data["longitude"])
for i in range(0, len(tle), 2):
cfg_list.append(
configure(prop_start=start,
prop_initial_TLE=tle[i:i + 2],
prop_end=end,
prop_step=data["step_size"][0],
sim_measurements=sim_meas,
gravity_degree=-1,
gravity_order=-1,
ocean_tides_degree=-1,
ocean_tides_order=-1,
third_body_sun=False,
third_body_moon=False,
solid_tides_sun=False,
solid_tides_moon=False,
drag_model=DragModel.UNDEFINED,
rp_sun=False))
cfg_list[-1].output_flags |= OutputFlag.OUTPUT_ECLIPSE
if (sim_meas):
add_station(cfg_list[-1], "Sensor", data["latitude"][0],
data["longitude"][0], data["altitude"][0],
data["fov_azimuth"][0], data["fov_elevation"][0],
data["fov_aperture"][0])
cfg_list[-1].measurements[MeasurementType.AZIMUTH].error[:] = [
0.0
]
cfg_list[-1].measurements[
MeasurementType.ELEVATION].error[:] = [0.0]
else:
cfg_list[-1].geo_zone_lat_lon[:] = [
l for ll in zip(data["latitude"], data["longitude"])
for l in ll
]
if (len(cfg_list)):
i = 0
lookup = {0.0: "Sunlit", 0.5: "Penumbra", 1.0: "Umbra"}
self.output.delete("0.0", tk.END)
if (sim_meas):
self.output_label[
"text"] = "UTC, Azimuth [deg], Elevation [deg]"
else:
self.output_label[
"text"] = "UTC, Latitude [deg], Longitude [deg], Altitude [m]"
for o in propagate_orbits(cfg_list):
self.output.insert(tk.END, f"\nObject {tle[i][2:7]}:\n")
i += 2
for m in o.array:
if (sim_meas):
self.output.insert(
tk.END, "{}: {:.5f}, {:.5f} ({})\n".format(
get_UTC_string(m.time),
(m.values[0] / Constant.DEGREE_TO_RAD + 360) %
360, m.values[1] / Constant.DEGREE_TO_RAD,
lookup[m.true_state[-1]]))
else:
lla = pos_to_lla(Frame.GCRF, m.time, m.true_state)
self.output.insert(
tk.END, "{}: {:.5f}, {:.5f}, {:.2f} ({})\n".format(
get_UTC_string(m.time),
lla[0] / Constant.DEGREE_TO_RAD,
lla[1] / Constant.DEGREE_TO_RAD, lla[2],
lookup[m.true_state[-1]]))
self.predict["state"] = "normal"
default=datetime(day1.year, day1.month,
day1.day).strftime(timefmt))
parser.add_argument("--step-size",
help="step size [sec]",
type=float,
default=900.0)
parser.add_argument("--export-oem",
help="Export output to CCSDS OEM files",
action="store_true",
default=False)
if (len(sys.argv) == 1):
parser.print_help()
exit(1)
args = parser.parse_args()
start = get_J2000_epoch_offset(args.start_time)
end = get_J2000_epoch_offset(args.end_time)
config, elements = [], [
l for l in getattr(args, "tle-file").read().splitlines()
if l.startswith("1") or l.startswith("2")
]
for i in range(0, len(elements), 2):
config.append(
configure(prop_start=start,
prop_initial_TLE=elements[i:i + 2],
prop_end=end,
prop_step=args.step_size,
gravity_degree=-1,
gravity_order=-1,
ocean_tides_degree=-1,
ocean_tides_order=-1,
["2020-07-24T03:22:03.679Z", 5.711479, 0.636510],
["2020-07-24T03:22:08.283Z", 5.706017, 0.608080],
["2020-07-24T03:22:12.904Z", 5.701007, 0.580095],
["2020-07-24T03:22:17.432Z", 5.696508, 0.553190],
["2020-07-24T03:22:22.073Z", 5.692283, 0.526236],
["2020-07-24T03:22:26.745Z", 5.688394, 0.499645],
["2020-07-24T03:22:31.417Z", 5.684841, 0.473698],
["2020-07-24T03:22:35.997Z", 5.681670, 0.448829],
["2020-07-24T03:22:40.696Z", 5.678703, 0.423978],
["2020-07-24T03:22:45.390Z", 5.675990, 0.399725],
["2020-07-24T03:22:49.930Z", 5.673622, 0.376921]]
# Use Laplace IOD to estimate an initial state from 3 RA/dec
times, ra, dec = [], [], []
for i in range(3):
times.append(get_J2000_epoch_offset(real_obs[i][0]))
ra.append(real_obs[i][1])
dec.append(real_obs[i][2])
initial_epoch = times[1]
initial_state = iod_laplace(Frame.EME2000, lat, lon, alt, times, ra, dec)
# Configure orbit determination
config = configure(prop_start=initial_epoch,
prop_initial_state=initial_state,
prop_end=get_J2000_epoch_offset(real_obs[-1][0]))
# Define ground station(s)
add_station(config, "UTA-ASTRIA-NMSkies", lat, lon, alt)
# Define measurement types; RA/dec used here
config.measurements[MeasurementType.RIGHT_ASCENSION].error[:] = [
# along with this program. If not, see <http://www.gnu.org/licenses/>.
from numpy import diag
from numpy.random import multivariate_normal
from orbdetpy import (configure, add_facet, add_maneuver, add_station,
build_measurement, AttitudeType, Filter, ManeuverTrigger,
ManeuverType, MeasurementType, Constant)
from orbdetpy.ccsds import export_OEM, export_TDM
from orbdetpy.conversion import get_J2000_epoch_offset, get_UTC_string
from orbdetpy.estimation import determine_orbit
from orbdetpy.propagation import propagate_orbits
from orbdetpy.plotting.estimation import plot as estimation_plot
from orbdetpy.plotting.simulation import plot as simulation_plot
# Set up configuration for measurement generation
cfg = configure(prop_start=get_J2000_epoch_offset("2019-05-01T00:00:00Z"),
prop_initial_state=[
-23183898.259, 35170229.755, 43425.075, -2566.938,
-1692.19, 138.948
],
prop_end=get_J2000_epoch_offset("2019-05-01T01:00:00Z"),
prop_step=300.0,
sim_measurements=True)
# Uncomment to define box-wing model
#add_facet(cfg, Constant.PLUS_I, 3.0)
#add_facet(cfg, Constant.PLUS_J, 3.0)
#add_facet(cfg, Constant.PLUS_K, 3.0)
#add_facet(cfg, Constant.MINUS_I, 3.0)
#add_facet(cfg, Constant.MINUS_J, 3.0)
#add_facet(cfg, Constant.MINUS_K, 3.0)
now = datetime.utcnow().strftime("%Y-%m-%dT%H:%M:%S.%fZ")
print(f"J2000_EPOCH = {conv.get_UTC_string(0.0)}")
print(
f"""J2000_EPOCH => 2000-01-01T12:00:00Z = {conv.get_J2000_epoch_offset("2000-01-01T12:00:00Z")}s"""
)
print(f"""J2000_EPOCH => {now} (now) = {conv.get_J2000_epoch_offset(now)}s""")
# Time difference between pairs of epochs
for key, val in vars(Epoch).items():
if (key.endswith("_EPOCH") and key != "J2000_EPOCH"):
print(
f"J2000_EPOCH => {key} = {conv.get_epoch_difference(Epoch.J2000_EPOCH, val)}s"
)
print()
time = conv.get_J2000_epoch_offset("1998-08-10T23:10:00Z")
# Inertial GCRF state vector
gcrf_pv = [-6045E3, -3490E3, 2500E3, -3.457E3, 6.618E3, 2.533E3]
# Frame transformations
itrf_pv = conv.transform_frame(Frame.GCRF, time, gcrf_pv,
Frame.ITRF_CIO_CONV_2010_ACCURATE_EOP)
print("GCRF=>ITRF: {:.2f}m, {:.2f}m, {:.2f}m, {:.2f}m/s, {:.2f}m/s, {:.2f}m/s".
format(*itrf_pv))
print(
"ITRF=>GCRF: {:.2f}m, {:.2f}m, {:.2f}m, {:.2f}m/s, {:.2f}m/s, {:.2f}m/s\n".
format(*conv.transform_frame(Frame.ITRF_CIO_CONV_2010_ACCURATE_EOP, time,
itrf_pv, Frame.GCRF)))
# Position => Lat/Lon/Alt
lla = conv.pos_to_lla(Frame.GCRF, time, gcrf_pv[:3])
def predict(self):
self.predict["state"] = "disabled"
start = get_J2000_epoch_offset(self.start_time.get())
end = get_J2000_epoch_offset(self.end_time.get())
data, tle = {}, [
l for l in self.tle.get("0.0", "end-1c").splitlines()
if l.startswith("1") or l.startswith("2")
]
for f in [
"latitude", "longitude", "altitude", "fov_azimuth",
"fov_elevation", "fov_aperture", "step_size"
]:
data[f] = [
float(t.strip()) for t in getattr(self, f).get().split(",")
]
if (f not in ["altitude", "step_size"]):
data[f] = [d * Constant.DEGREE_TO_RAD for d in data[f]]
cfg_list = []
sim_meas = len(data["latitude"]) <= 2 or len(data["latitude"]) != len(
data["longitude"])
for i in range(0, len(tle), 2):
cfg_list.append(
configure(prop_start=start,
prop_initial_TLE=tle[i:i + 2],
prop_end=end,
prop_step=data["step_size"][0],
sim_measurements=sim_meas))
if (not sim_meas):
cfg_list[-1].geo_zone_lat_lon[:] = [
l for ll in zip(data["latitude"], data["longitude"])
for l in ll
]
continue
add_station(cfg_list[-1], "Sensor", data["latitude"][0],
data["longitude"][0], data["altitude"][0],
data["fov_azimuth"][0], data["fov_elevation"][0],
data["fov_aperture"][0])
cfg_list[-1].measurements[MeasurementType.AZIMUTH].error[:] = [0.0]
cfg_list[-1].measurements[MeasurementType.ELEVATION].error[:] = [
0.0
]
if (len(cfg_list)):
i = 0
self.output.delete("0.0", tk.END)
if (sim_meas):
self.output_label[
"text"] = "UTC, Azimuth [deg], Elevation [deg]"
else:
self.output_label[
"text"] = "UTC, Latitude [deg], Longitude [deg], Altitude [m]"
for o in propagate_orbits(cfg_list):
self.output.insert(tk.END,
"\nObject {}:\n".format(tle[i][2:7]))
i += 2
for m in o.array:
if (sim_meas):
self.output.insert(
tk.END, "{}: {:.5f}, {:.5f}\n".format(
get_UTC_string(m.time),
(m.values[0] / Constant.DEGREE_TO_RAD + 360) %
360, m.values[1] / Constant.DEGREE_TO_RAD))
else:
lla = pos_to_lla(Frame.GCRF, m.time, m.true_state)
self.output.insert(
tk.END, "{}: {:.5f}, {:.5f}, {:.2f}\n".format(
get_UTC_string(m.time),
lla[0] / Constant.DEGREE_TO_RAD,
lla[1] / Constant.DEGREE_TO_RAD, lla[2]))
self.predict["state"] = "normal"
# You should have received a copy of the GNU General Public License
# along with this program. If not, see <http://www.gnu.org/licenses/>.
from numpy import diag
from numpy.random import multivariate_normal
from orbdetpy import (configure, add_facet, add_maneuver, add_station, build_measurement, AttitudeType,
Filter, ManeuverTrigger, ManeuverType, MeasurementType, Constant)
from orbdetpy.ccsds import export_OEM, export_TDM
from orbdetpy.conversion import get_J2000_epoch_offset, get_UTC_string
from orbdetpy.estimation import determine_orbit
from orbdetpy.propagation import propagate_orbits
from orbdetpy.plotting.estimation import plot as estimation_plot
from orbdetpy.plotting.simulation import plot as simulation_plot
# Set up configuration for measurement generation
cfg = configure(prop_start=get_J2000_epoch_offset("2019-05-01T00:00:00Z"),
prop_initial_state=[-23183898.259, 35170229.755, 43425.075, -2566.938, -1692.19, 138.948],
prop_end=get_J2000_epoch_offset("2019-05-01T01:00:00Z"), prop_step=300.0, sim_measurements=True)
# Uncomment to define box-wing model
#add_facet(cfg, Constant.PLUS_I, 3.0)
#add_facet(cfg, Constant.PLUS_J, 3.0)
#add_facet(cfg, Constant.PLUS_K, 3.0)
#add_facet(cfg, Constant.MINUS_I, 3.0)
#add_facet(cfg, Constant.MINUS_J, 3.0)
#add_facet(cfg, Constant.MINUS_K, 3.0)
#cfg.rso_solar_array_area = 20.0
#cfg.rso_solar_array_axis[:] = Constant.PLUS_J
# Uncomment to define initial attitude
#cfg.rso_attitude_provider = AttitudeType.FIXED_RATE
#
# This program is distributed in the hope that it will be useful,
# but WITHOUT ANY WARRANTY; without even the implied warranty of
# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
# GNU General Public License for more details.
#
# You should have received a copy of the GNU General Public License
# along with this program. If not, see <http://www.gnu.org/licenses/>.
from orbdetpy import configure, Frame
from orbdetpy.conversion import get_J2000_epoch_offset, get_UTC_string
from orbdetpy.propagation import propagate_orbits
from orbdetpy.utilities import interpolate_ephemeris
# Propagate for 1 hour at 5 minute intervals with default settings
cfg = configure(prop_start=get_J2000_epoch_offset("2020-03-09T22:00:02.000Z"),
prop_initial_state=[
-152408.166, -958234.785, 6908448.381, -7545.691, 285.553,
-126.766
],
prop_end=get_J2000_epoch_offset("2020-03-09T23:00:02.000Z"),
prop_step=300.0)
times, states = [], []
for o in propagate_orbits([cfg])[0].array:
times.append(o.time)
states.append(o.true_state)
# Interpolate over the same period at 1 minute intervals
for i in interpolate_ephemeris(Frame.GCRF, times, states, 5, Frame.GCRF,
cfg.prop_start, cfg.prop_end, 60.0):
from orbdetpy.conversion import get_J2000_epoch_offset
from orbdetpy.propagation import propagate_orbits
with open(path.join(path.dirname(path.realpath(__file__)), "tle_tests.txt"), "r") as fp:
test_cases = [[]]
for l in fp.read().splitlines():
if (l.strip()):
test_cases[-1].append(l)
else:
test_cases.append([])
config = [configure(prop_step=60.0, prop_inertial_frame=Frame.TEME, gravity_degree=-1, gravity_order=-1, ocean_tides_degree=-1,
ocean_tides_order=-1, third_body_sun=False, third_body_moon=False, solid_tides_sun=False,
solid_tides_moon=False, drag_model=DragModel.UNDEFINED, rp_sun=False)]
diff_norm = lambda x, y: math.sqrt((x[0]-y[0])**2 + (x[1]-y[1])**2 + (x[2]-y[2])**2)
for test in test_cases:
epstr = "19" + test[0][18:32] if (test[0][18:20] >= "57") else "20" + test[0][18:32]
eputc = (datetime.strptime(epstr[:7], "%Y%j") + timedelta(days=float(epstr[7:]))).strftime("%Y-%m-%dT%H:%M:%S.%f")
eptdt = get_J2000_epoch_offset(eputc)
config[0].prop_initial_TLE[:] = test[:2]
for line in test[2:]:
truth = [float(t)*1000.0 for t in line.split()[:7]]
truth[0] = truth[0]*60.0/1000.0
config[0].prop_start = eptdt + truth[0]
config[0].prop_end = config[0].prop_start
prop = propagate_orbits(config)[0].array[0]
assert(diff_norm(truth[1:4], prop.true_state[:3]) < 2.0E-3) # 2.0 mm position error tolerance
assert(diff_norm(truth[4:7], prop.true_state[3:6]) < 0.003E-3) # 0.003 mm/s velocity error tolerance