def test_generate_opm_with_defaults(self):
o = OpmParams({'epoch': 'foo', 'state_vector': [1, 2, 3, 4, 5, 6]})
expected_opm = """CCSDS_OPM_VERS = 2.0
ORIGINATOR = ADAM_User
COMMENT Cartesian coordinate system
OBJECT_NAME = dummy
OBJECT_ID = 001
CENTER_NAME = SUN
REF_FRAME = ITRF-97
TIME_SYSTEM = UTC
EPOCH = foo
X = 1
Y = 2
Z = 3
X_DOT = 4
Y_DOT = 5
Z_DOT = 6
MASS = 1000
SOLAR_RAD_AREA = 20
SOLAR_RAD_COEFF = 1
DRAG_AREA = 20
DRAG_COEFF = 2.2"""
# Remove the CREATION_DATE stamp since that varies.
opm = "\n".join([
line for line in o.generate_opm().splitlines()
if not line.startswith('CREATION_DATE')
])
self.maxDiff = None # Otherwise if the next line fails, we can't see the diff
self.assertEqual(expected_opm, opm)
def test_generate_opm_with_defaults(self):
o = OpmParams({'epoch': 'foo', 'state_vector': [1, 2, 3, 4, 5, 6]})
expected_opm = """CCSDS_OPM_VERS = 2.0
ORIGINATOR = ADAM_User
COMMENT Cartesian coordinate system
OBJECT_NAME = dummy
OBJECT_ID = 001
CENTER_NAME = SUN
REF_FRAME = ICRF
TIME_SYSTEM = UTC
EPOCH = foo
X = 1
Y = 2
Z = 3
X_DOT = 4
Y_DOT = 5
Z_DOT = 6
MASS = 1000.0
SOLAR_RAD_AREA = 20.0
SOLAR_RAD_COEFF = 1.0
DRAG_AREA = 20.0
DRAG_COEFF = 2.2"""
opm = OpmParamsTest.remove_non_static_fields(o.generate_opm())
self.maxDiff = None # Otherwise if the next line fails, we can't see the diff
self.assertEqual(expected_opm, opm)
def make_cartesian_and_keplerian_batches(self, start_time_str,
end_time_str):
keplerian_elements = {
'semi_major_axis_km': 3.1307289138037175E8,
'eccentricity': 0.5355029800000188,
'inclination_deg': 23.439676743246295,
'ra_of_asc_node_deg': 359.9942693176405,
'arg_of_pericenter_deg': 328.5584374618295,
'true_anomaly_deg': -127.01778914927144,
'gm': 1.327124400419394E11
}
cartesian_state_vector = [
-3.0653634150102222e8,
-1.1097955684640282e8,
-4.8129706422527283e7, # x, y, z
15.7598552764090590,
-10.5875673291958420,
-4.5896734328869746 # dx, dy, dZ
]
propagation_params = PropagationParams({
'start_time':
start_time_str,
'end_time':
end_time_str,
'project_uuid':
self.working_project.get_uuid(),
'description':
'Created by test at ' + start_time_str
})
opm_params_templ = {
'epoch': start_time_str,
# state_vector or keplerian_elements will be set later.
'mass': 500.5,
'solar_rad_area': 25.2,
'solar_rad_coeff': 1.2,
'drag_area': 33.3,
'drag_coeff': 2.5
}
cartesian_opm_params = opm_params_templ.copy()
cartesian_opm_params['state_vector'] = cartesian_state_vector
keplerian_opm_params = opm_params_templ.copy()
keplerian_opm_params['keplerian_elements'] = keplerian_elements
cartesian = Batch(propagation_params, OpmParams(cartesian_opm_params))
keplerian = Batch(propagation_params, OpmParams(keplerian_opm_params))
return cartesian, keplerian
def _new_batch_propagation(self):
now = datetime.datetime.utcnow()
later = now + datetime.timedelta(10 * 365)
propagation_params = PropagationParams({
'start_time':
now.isoformat() + 'Z',
'end_time':
later.isoformat() + 'Z',
'step_size':
60 * 60, # 1 hour.
'description':
'Created by test at ' + str(now) + 'Z'
})
state_vec = [
130347560.13690618, -74407287.6018632, -35247598.541470632,
23.935241263310683, 27.146279819258538, 10.346605942591514
]
opm_params = OpmParams({
'epoch': now.isoformat() + 'Z',
'state_vector': state_vec,
'mass': 500.5,
'solar_rad_area': 25.2,
'solar_rad_coeff': 1.2,
'drag_area': 33.3,
'drag_coeff': 2.5,
'originator': 'Test',
'object_name': 'TestObj',
'object_id': 'TestObjId',
})
return BatchPropagation(propagation_params, opm_params)
def new_targeted_propagation(self, initial_maneuver):
start = '2013-05-25T00:00:02.000000Z'
end = '2018-04-25T03:06:14.200000Z'
propagation_params = PropagationParams({
'start_time':
start,
'end_time':
end,
'project_uuid':
self.working_project.get_uuid(),
'description':
'Created by test at ' + start
})
state_vec = [
-1.4914794358536252e+8, 1.0582106861692128e+8,
6.0492834101479955e+7, -11.2528789273597756, -22.3258231726462242,
-9.7271222877710155
]
opm_params = OpmParams({
'epoch': start,
'state_vector': state_vec,
'initial_maneuver': initial_maneuver,
})
return TargetedPropagation(
propagation_params, opm_params,
TargetingParams({
'target_distance_from_earth': 1.0e4,
'tolerance': 1.0
}))
def make_batch(self, state_vec, start_time, end_time):
start_time_str = start_time.isoformat() + 'Z'
end_time_str = end_time.isoformat() + 'Z'
propagation_params = PropagationParams({
'start_time':
start_time_str,
'end_time':
end_time_str,
'step_size':
0,
'project_uuid':
self.working_project.get_uuid(),
'description':
'Created by test at ' + start_time_str
})
opm_params = OpmParams({
'epoch': start_time_str,
'state_vector': state_vec,
'mass': 500.5,
'solar_rad_area': 25.2,
'solar_rad_coeff': 1.2,
'drag_area': 33.3,
'drag_coeff': 2.5,
'originator': 'Test',
'object_name': 'TestObj',
'object_id': 'TestObjId',
})
return Batch(propagation_params, opm_params)
def test_access(self):
projects_module = self.service.get_projects_module()
permissions_module = self.service.get_permissions_module()
groups_module = self.service.get_groups_module()
# Only prod has a public project.
projects = projects_module.get_projects()
if self.config.get_environment() == "prod":
self.assertEqual(1, len(projects))
self.assertEqual("public", projects[0].get_name())
else:
self.assertEqual(0, len(projects))
print("Skipping check for public objects.")
# Can't add a project to public project.
public_project = "00000000-0000-0000-0000-000000000001"
with (self.assertRaises(RuntimeError)):
projects_module.new_project(public_project, "", "")
# Can't run a batch in the public project.
batches_module = self.service.get_batches_module()
dummy_propagation_params = PropagationParams({
'start_time': 'AAA',
'end_time': 'BBB',
'project_uuid': 'CCC'
})
dummy_opm_params = OpmParams({
'epoch': 'DDD',
'state_vector': [1, 2, 3, 4, 5, 6]
})
with (self.assertRaises(RuntimeError)):
batches_module.new_batch(dummy_propagation_params,
dummy_opm_params)
# Anon should have no permissions.
permissions = permissions_module.get_my_permissions()
self.assertEqual(1, len(permissions))
self.assertEqual(0, len(permissions[""]))
# And anon is in no groups.
groups = groups_module.get_my_memberships()
self.assertEqual(0, len(groups))
# Therefore anon can grant no permissions.
with (self.assertRaises(RuntimeError)):
permissions_module.grant_user_permission(
"*****@*****.**", Permission("READ", "PROJECT",
public_project))
# And can add/modify no groups.
with (self.assertRaises(RuntimeError)):
groups_module.new_group("", "")
all_group = "00000000-0000-0000-0000-000000000001"
with (self.assertRaises(RuntimeError)):
groups_module.add_user_to_group("*****@*****.**", all_group)
# Not even allowed to see the members of the magic all group.
with (self.assertRaises(RuntimeError)):
groups_module.get_group_members(all_group)
def test_submit_batch(self, service):
keplerian_elements = {
'semi_major_axis_km': 448793612,
'eccentricity': 0.1,
'inclination_deg': 90,
'ra_of_asc_node_deg': 91,
'arg_of_pericenter_deg': 92,
'true_anomaly_deg': 93,
'gm': 132712440041.9394
}
keplerian_sigma = {
'semi_major_axis': 100,
'eccentricity': 0.001,
'inclination': 1,
'ra_of_asc_node': 2,
'arg_of_pericenter': 3,
'true_anomaly': 4,
}
# state_vec = [130347560.13690618,
# -74407287.6018632,
# -35247598.541470632,
# 23.935241263310683,
# 27.146279819258538,
# 10.346605942591514]
# sigma_vec = {'x': 1000,
# 'y': 1001,
# 'z': 1002,
# 'x_dot': 10,
# 'y_dot': 11,
# 'z_dot': 12}
draws = 5
propagation_params = PropagationParams({
'start_time': '2017-10-04T00:00:00Z', # propagation start time in ISO format
'end_time': '2017-10-11T00:00:00Z', # propagation end time in ISO format
'project_uuid': service.workspace,
'keplerianSigma': keplerian_sigma,
'monteCarloDraws': draws,
'propagationType': 'MONTE_CARLO',
'description': 'Integration Test Run',
'stopOnImpact': True,
'step_size': 86400,
'stopOnCloseApproach': False,
'stopOnImpactDistanceMeters': 500000,
'closeApproachRadiusFromTargetMeters': 7000000000
})
opm_params = OpmParams({
'epoch': '2017-10-04T00:00:00Z',
'keplerian_elements': keplerian_elements,
})
response = service.processing_service.execute_batch_propagation(
service.workspace, propagation_params, opm_params)
assert response.job_id() is not None
def new_batch_propagation(self):
now = datetime.datetime.utcnow()
later = now + datetime.timedelta(10 * 365)
propagation_params = PropagationParams({
'start_time':
now.isoformat() + 'Z',
'end_time':
later.isoformat() + 'Z',
'step_size':
60 * 60, # 1 hour.
'description':
'Created by test at ' + str(now) + 'Z'
})
state_vec = [
130347560.13690618, -74407287.6018632, -35247598.541470632,
23.935241263310683, 27.146279819258538, 10.346605942591514
]
opm_params = OpmParams({
'epoch': now.isoformat() + 'Z',
'state_vector': state_vec,
# Comment out state_vector and uncomment this to try with keplerian elements instead.
# 'keplerian_elements': {
# 'semi_major_axis_km': 3.1307289138037175E8,
# 'eccentricity': 0.5355029800000188,
# 'inclination_deg': 23.439676743246295,
# 'ra_of_asc_node_deg': 359.9942693176405,
# 'arg_of_pericenter_deg': 328.5584374618295,
# 'true_anomaly_deg': -127.01778914927144,
# 'gm': 1.327124400419394E11
# },
'mass': 500.5,
'solar_rad_area': 25.2,
'solar_rad_coeff': 1.2,
'drag_area': 33.3,
'drag_coeff': 2.5,
'originator': 'Test',
'object_name': 'TestObj',
'object_id': 'TestObjId',
# Uncomment this to try a hypercube propagation.
# Lower triangular covariance matrix (21 elements in a list)
# 'covariance': [
# 3.331349476038534e-04,
# 4.618927349220216e-04, 6.782421679971363e-04,
# -3.070007847730449e-04, -4.221234189514228e-04, 3.231931992380369e-04,
# -3.349365033922630e-07, -4.686084221046758e-07, 2.484949578400095e-07, 4.296022805587290e-10, # NOQA (we want to keep the visual triangle)
# -2.211832501084875e-07, -2.864186892102733e-07, 1.798098699846038e-07, 2.608899201686016e-10, 1.767514756338532e-10, # NOQA
# -3.041346050686871e-07, -4.989496988610662e-07, 3.540310904497689e-07, 1.869263192954590e-10, 1.008862586240695e-10, 6.224444338635500e-10], # NOQA
# 'perturbation': 3,
# 'hypercube': 'FACES',
})
return BatchPropagation(propagation_params, opm_params)
def test_sun_ememe(self, service, working_project):
start_time_str = "2000-01-01T11:58:55.816Z"
end_time_str = "2009-07-21T21:55:08.813Z"
sun_ememe_state_vec = [
-306536346.18024945, -120966638.54521248, -12981.069369263947,
15.759854830195243, -11.539570959741736, 0.0005481049628786039
]
propagation_params = PropagationParams({
'start_time':
start_time_str,
'end_time':
end_time_str,
'step_size':
86400,
'project_uuid':
working_project.get_uuid(),
'description':
'Created by test at ' + start_time_str
})
opm_params = OpmParams({
'epoch': start_time_str,
'state_vector': sun_ememe_state_vec,
'center_name': 'SUN',
'ref_frame': 'EMEME2000',
})
batch = Batch(propagation_params, opm_params)
runner = BatchRunManager(service.get_batches_module(), [batch])
runner.run()
end_state = batch.get_results().get_end_state_vector()
# The output state is expected to be in ICRF.
expected_end_state = [
73978163.61069362, -121822760.05571477, -52811158.83249758,
31.71000343989318, 29.9657246374751, .6754531613947713
]
# These values are in EMEME. The resulting ephemeris is not expected to match these values.
# expected_end_state = [73978158.47632701, -132777272.5255892, 5015.073123970032,
# 31.710003506237434, 27.761693311026138, -11.299967713192564]
difference = np.subtract(expected_end_state, end_state)
print("Difference is %s" % difference)
print("End state: %s" % end_state)
npt.assert_allclose(difference[0:3], [0, 0, 0], rtol=0, atol=.02)
npt.assert_allclose(difference[3:6], [0, 0, 0], rtol=0, atol=.00002)
# The returned ephemeris will be in Sun-centered ICRF, not EMEME. My best guess is that
# the ephemeris file doesn't support all reference frames, so if it encounters one that
# isn't supported, it'll choose a similar one.
ephem = batch.get_results().get_parts()[-1].get_ephemeris()
assert "ICRF" in ephem
assert "EMEME" not in ephem
def propagate_states(state_vectors, epoch_time, end_time):
"""Propagate states from one time to another
Assume state epoch is the same as integration start time
Args:
sate_vectors (list of lists) - list of lists with 6 elements
[rx, ry, rz, vx, vy, vz] [km, km/s]
epoch_time (datetime.datetime) - epoch of state (UTC datetime)
end_time (datetime.datetime) - time at which to end the simulation
(UTC datetime)
Returns:
end_state_vectors (list of lists) - states at end of integration
[rx, ry, rz, vx, vy, vz] [km, km/s]
"""
# Convert times to strings
epoch_time_str = batch_time_string_from_datetime(epoch_time)
start_time_str = epoch_time_str
end_time_str = batch_time_string_from_datetime(end_time)
print("Propagating %i states to propagate from %s to %s" %
(len(state_vectors), start_time_str, end_time_str))
url = "https://pro-equinox-162418.appspot.com/_ah/api/adam/v1"
rest = RestRequests(url)
batches_module = Batches(rest)
# Create batches from statevectors
batches = []
propagation_params = PropagationParams({
'start_time':
start_time_str,
'end_time':
end_time_str,
'project_uuid':
'ffffffff-ffff-ffff-ffff-ffffffffffff'
})
for state_vector in state_vectors:
opm_params = OpmParams({
'epoch': start_time_str,
'state_vector': state_vector
})
batches.append(Batch(propagation_params, opm_params))
# submit batches and wait till they finish running
BatchRunManager(batches_module, batches).run()
# Get final states
end_state_vectors = []
for batch in batches:
end_state_vectors.append(batch.get_results().get_end_state_vector())
return end_state_vectors
def test_config_in_use_pins_project(self):
# Config management isn't very common, doesn't merit direct addition to service.
configs = PropagatorConfigs(self.service.rest)
projects = self.service.get_projects_module()
project = self.service.new_working_project()
project1 = projects.new_project(project.get_uuid(), "", "")
self.assertIsNotNone(project1)
project2 = projects.new_project(project.get_uuid(), "", "")
self.assertIsNotNone(project2)
print("Added child projects to working project: " + "[" +
project1.get_uuid() + ", " + project2.get_uuid() + "]")
config = configs.new_config({
'project': project1.get_uuid(),
'description': 'test config'
})
self.assertEqual(project1.get_uuid(), config.get_project())
batch = Batch(
PropagationParams({
'start_time': '2017-10-04T00:00:00Z',
'end_time': '2017-10-05T00:00:00Z',
'project_uuid': project2.get_uuid(),
'propagator_uuid': config.get_uuid()
}),
OpmParams({
'epoch':
'2017-10-04T00:00:00Z',
'state_vector': [
130347560.13690618, -74407287.6018632, -35247598.541470632,
23.935241263310683, 27.146279819258538, 10.346605942591514
]
}))
BatchRunManager(self.service.get_batches_module(), [batch]).run()
# Attempt to delete the project with the config in it. It should refuse because the
# config is still in use by the batch.
with self.assertRaises(RuntimeError):
projects.delete_project(project1.get_uuid())
# Then delete the batch. After that, the project with the config in it should
# delete no problem.
self.service.batches.delete_batch(batch.get_uuid())
projects.delete_project(project1.get_uuid())
# Clean up the batch holder project.
projects.delete_project(project2.get_uuid())
def new_hypercube_batch(self, hypercube):
now = datetime.datetime.utcnow()
later = now + datetime.timedelta(365 * 10) # 10 years
propagation_params = PropagationParams({
'start_time': now.isoformat() + 'Z',
'end_time': later.isoformat() + 'Z',
'step_size': 0,
'project_uuid': self.working_project.get_uuid(),
'description': 'Created by test at ' + str(now) + 'Z'
})
state_vec = [130347560.13690618,
-74407287.6018632,
-35247598.541470632,
23.935241263310683,
27.146279819258538,
10.346605942591514]
opm_params = OpmParams({
'epoch': now.isoformat() + 'Z',
'state_vector': state_vec,
'mass': 500.5,
'solar_rad_area': 25.2,
'solar_rad_coeff': 1.2,
'drag_area': 33.3,
'drag_coeff': 2.5,
'originator': 'Test',
'object_name': 'TestObj',
'object_id': 'TestObjId',
# Lower triangular covariance matrix (21 elements in a list)
'covariance': [
3.331349476038534e-04,
4.618927349220216e-04, 6.782421679971363e-04,
-3.070007847730449e-04, -4.221234189514228e-04, 3.231931992380369e-04,
-3.349365033922630e-07, -4.686084221046758e-07, 2.484949578400095e-07, 4.296022805587290e-10, # NOQA (we want to keep the visual triangle)
-2.211832501084875e-07, -2.864186892102733e-07, 1.798098699846038e-07, 2.608899201686016e-10, 1.767514756338532e-10, # NOQA
-3.041346050686871e-07, -4.989496988610662e-07, 3.540310904497689e-07, 1.869263192954590e-10, 1.008862586240695e-10, 6.224444338635500e-10], # NOQA
'perturbation': 3,
'hypercube': hypercube,
})
return Batch(propagation_params, opm_params)
def test_icrf(self, service, working_project):
start_time_str = "2000-01-01T11:58:55.816Z"
end_time_str = "2009-07-21T21:55:08.813Z"
sun_icrf_state_vec = [
-306536341.5010222, -110979556.84640282, -48129706.42252728,
15.75985527640906, -10.587567329195842, -4.589673432886975
]
propagation_params = PropagationParams({
'start_time':
start_time_str,
'end_time':
end_time_str,
'step_size':
86400,
'project_uuid':
working_project.get_uuid(),
'description':
'Created by test at ' + start_time_str
})
opm_params = OpmParams({
'epoch': start_time_str,
'state_vector': sun_icrf_state_vec,
'center_name': 'SUN',
'ref_frame': 'ICRF',
})
batch = Batch(propagation_params, opm_params)
runner = BatchRunManager(service.get_batches_module(), [batch])
runner.run()
end_state = batch.get_results().get_end_state_vector()
expected_end_state = [
73978163.61069362, -121822760.05571477, -52811158.83249758,
31.71000343989318, 29.9657246374751, .6754531613947713
]
difference = np.subtract(expected_end_state, end_state)
print("Difference is %s" % difference)
print("End state: %s" % end_state)
npt.assert_allclose(difference[0:3], [0, 0, 0], rtol=0, atol=.02)
npt.assert_allclose(difference[3:6], [0, 0, 0], rtol=0, atol=.00002)
ephem = batch.get_results().get_parts()[-1].get_ephemeris()
assert "ICRF" in ephem
def new_dummy_batch(self, days_to_propagate):
if (days_to_propagate > 36500):
print(
"Server has trouble handling propagation durations longer than 100 years. "
+ "Try something smaller.")
return
now = datetime.datetime.utcnow()
later = now + datetime.timedelta(days_to_propagate)
propagation_params = PropagationParams({
'start_time':
now.isoformat() + 'Z',
'end_time':
later.isoformat() + 'Z',
'step_size':
60 * 60, # 1 hour.
'project_uuid':
self.working_project.get_uuid(),
'description':
'Created by test at ' + str(now) + 'Z'
})
state_vec = [
130347560.13690618, -74407287.6018632, -35247598.541470632,
23.935241263310683, 27.146279819258538, 10.346605942591514
]
opm_params = OpmParams({
'epoch': now.isoformat() + 'Z',
'state_vector': state_vec,
'mass': 500.5,
'solar_rad_area': 25.2,
'solar_rad_coeff': 1.2,
'drag_area': 33.3,
'drag_coeff': 2.5,
'originator': 'Test',
'object_name': 'TestObj',
'object_id': 'TestObjId',
})
return Batch(propagation_params, opm_params)
def test_generate_opm(self):
o = OpmParams({
'epoch':
'foo',
'state_vector': [1, 2, 3, 4, 5, 6],
'keplerian_elements': {
'semi_major_axis_km': 1,
'eccentricity': 2,
'inclination_deg': 3,
'ra_of_asc_node_deg': 4,
'arg_of_pericenter_deg': 5,
'true_anomaly_deg': 6,
'gm': 7
},
'originator':
'a',
'object_name':
'b',
'object_id':
'c',
'center_name':
'EARTH',
'ref_frame':
'EMEME2000',
'mass':
1,
'solar_rad_area':
2,
'solar_rad_coeff':
3,
'drag_area':
4,
'drag_coeff':
5,
'covariance': [
0, 1, 2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17,
18, 19, 20
],
'perturbation':
7,
'hypercube':
'CORNERS',
})
expected_opm = """CCSDS_OPM_VERS = 2.0
ORIGINATOR = a
COMMENT Cartesian coordinate system
OBJECT_NAME = b
OBJECT_ID = c
CENTER_NAME = EARTH
REF_FRAME = EMEME2000
TIME_SYSTEM = UTC
EPOCH = foo
X = 1
Y = 2
Z = 3
X_DOT = 4
Y_DOT = 5
Z_DOT = 6
SEMI_MAJOR_AXIS = 1
ECCENTRICITY = 2
INCLINATION = 3
RA_OF_ASC_NODE = 4
ARG_OF_PERICENTER = 5
TRUE_ANOMALY = 6
GM = 7
MASS = 1
SOLAR_RAD_AREA = 2
SOLAR_RAD_COEFF = 3
DRAG_AREA = 4
DRAG_COEFF = 5
CX_X = 0
CY_X = 1
CY_Y = 2
CZ_X = 3
CZ_Y = 4
CZ_Z = 5
CX_DOT_X = 6
CX_DOT_Y = 7
CX_DOT_Z = 8
CX_DOT_X_DOT = 9
CY_DOT_X = 10
CY_DOT_Y = 11
CY_DOT_Z = 12
CY_DOT_X_DOT = 13
CY_DOT_Y_DOT = 14
CZ_DOT_X = 15
CZ_DOT_Y = 16
CZ_DOT_Z = 17
CZ_DOT_X_DOT = 18
CZ_DOT_Y_DOT = 19
CZ_DOT_Z_DOT = 20
USER_DEFINED_ADAM_INITIAL_PERTURBATION = 7 [sigma]
USER_DEFINED_ADAM_HYPERCUBE = CORNERS"""
# Remove the CREATION_DATE stamp since that varies.
opm = "\n".join([
line for line in o.generate_opm().splitlines()
if not line.startswith('CREATION_DATE')
])
self.maxDiff = None # Otherwise if the next line fails, we can't see the diff
self.assertEqual(expected_opm, opm)
def test_generate_opm(self):
o = OpmParams({
'epoch':
'foo',
'state_vector': [1, 2, 3, 4, 5, 6],
'originator':
'a',
'object_name':
'b',
'object_id':
'c',
'mass':
1,
'solar_rad_area':
2,
'solar_rad_coeff':
3,
'drag_area':
4,
'drag_coeff':
5,
'covariance': [
0, 1, 2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17,
18, 19, 20
],
'perturbation':
7,
'hypercube':
'CORNERS',
})
expected_opm = """CCSDS_OPM_VERS = 2.0
ORIGINATOR = a
COMMENT Cartesian coordinate system
OBJECT_NAME = b
OBJECT_ID = c
CENTER_NAME = SUN
REF_FRAME = ITRF-97
TIME_SYSTEM = UTC
EPOCH = foo
X = 1
Y = 2
Z = 3
X_DOT = 4
Y_DOT = 5
Z_DOT = 6
MASS = 1
SOLAR_RAD_AREA = 2
SOLAR_RAD_COEFF = 3
DRAG_AREA = 4
DRAG_COEFF = 5
CX_X = 0
CY_X = 1
CY_Y = 2
CZ_X = 3
CZ_Y = 4
CZ_Z = 5
CX_DOT_X = 6
CX_DOT_Y = 7
CX_DOT_Z = 8
CX_DOT_X_DOT = 9
CY_DOT_X = 10
CY_DOT_Y = 11
CY_DOT_Z = 12
CY_DOT_X_DOT = 13
CY_DOT_Y_DOT = 14
CZ_DOT_X = 15
CZ_DOT_Y = 16
CZ_DOT_Z = 17
CZ_DOT_X_DOT = 18
CZ_DOT_Y_DOT = 19
CZ_DOT_Z_DOT = 20
USER_DEFINED_ADAM_INITIAL_PERTURBATION = 7 [sigma]
USER_DEFINED_ADAM_HYPERCUBE = CORNERS"""
# Remove the CREATION_DATE stamp since that varies.
opm = "\n".join([
line for line in o.generate_opm().splitlines()
if not line.startswith('CREATION_DATE')
])
self.maxDiff = None # Otherwise if the next line fails, we can't see the diff
self.assertEqual(expected_opm, opm)
def test_invalid_keys(self):
with self.assertRaises(KeyError):
OpmParams({'unrecognized': 0})
def test_required_keys(self):
with self.assertRaises(KeyError):
OpmParams({'epoch': 'foo'})
with self.assertRaises(KeyError):
OpmParams({'state_vector': []})
def test_access_state_vector(self):
o = OpmParams({'epoch': 'foo', 'state_vector': [1, 2, 3, 4, 5, 6]})
self.assertEqual([1, 2, 3, 4, 5, 6], o.get_state_vector())
o.set_state_vector([6, 5, 4, 3, 2, 1])
self.assertEqual([6, 5, 4, 3, 2, 1], o.get_state_vector())
def test_required_keys(self):
with self.assertRaises(KeyError):
OpmParams({'epoch': 'foo'})
with self.assertRaises(KeyError):
OpmParams({'state_vector': []})
with self.assertRaises(KeyError):
OpmParams({
'keplerian_elements': {
'semi_major_axis_km': 1,
'eccentricity': 2,
'inclination_deg': 3,
'ra_of_asc_node_deg': 4,
'arg_of_pericenter_deg': 5,
'true_anomaly_deg': 6,
'gm': 7
}
})
with self.assertRaises(KeyError):
OpmParams({
'epoch': 'foo',
'keplerian_elements': {
'semi_major_axis_km': 1,
'eccentricity': 2,
'inclination_deg': 3,
'ra_of_asc_node_deg': 4,
'arg_of_pericenter_deg': 5,
'true_anomaly_deg': 6,
# Missing gm.
}
})
with self.assertRaises(KeyError):
OpmParams({
'epoch': 'foo',
'keplerian_elements': {
'semi_major_axis_km': 1,
'eccentricity': 2,
'inclination_deg': 3,
'ra_of_asc_node_deg': 4,
'arg_of_pericenter_deg': 5,
'true_anomaly_deg': 6,
'gm': 7,
'extra what is this': 8
}
})
# No KeyError with no state vector.
OpmParams({
'epoch': 'foo',
'keplerian_elements': {
'semi_major_axis_km': 1,
'eccentricity': 2,
'inclination_deg': 3,
'ra_of_asc_node_deg': 4,
'arg_of_pericenter_deg': 5,
'true_anomaly_deg': 6,
'gm': 7
}
})
class BatchesTest(unittest.TestCase):
"""Unit tests for batches module
"""
dummy_propagation_params = PropagationParams({
'start_time': 'AAA',
'end_time': 'BBB',
'project_uuid': 'CCC'
})
dummy_opm_params = OpmParams({
'epoch': 'DDD',
'state_vector': [1, 2, 3, 4, 5, 6]
})
def _check_input(self, data_dict):
"""Check input data
Checks input data by asserting the following:
- start time = 'AAA'
- end time = 'BBB'
- step size = 86400 (default)
- opm string in data dictionary is not None
- originator = 'ADAM_User'
- object name = 'dummy'
- object ID = '001'
- epoch and state vector are 'CCC' and [1, 2, 3, 4, 5, 6], respectively
- object mass = 1000 (default)
- object solar radiation area = 20 (default)
- object solar radiation coefficient = 1 (default)
- object drag area = 20 (default)
- object drag coefficient = 2.2 (default)
- propagator ID is default (none specified)
Args:
data_dict (dict) - input data for POST
Returns:
True
"""
self.assertEqual(data_dict['start_time'],
self.dummy_propagation_params.get_start_time())
self.assertEqual(data_dict['end_time'],
self.dummy_propagation_params.get_end_time())
self.assertEqual(data_dict['project'],
self.dummy_propagation_params.get_project_uuid())
self.assertEqual(data_dict['step_duration_sec'], 86400)
self.assertEqual(data_dict['propagator_uuid'],
"00000000-0000-0000-0000-000000000001")
opm = data_dict['opm_string']
self.assertIsNotNone(opm)
self.assertIn('ORIGINATOR = ADAM_User', opm)
self.assertIn('OBJECT_NAME = dummy', opm)
self.assertIn('OBJECT_ID = 001', opm)
self.assertIn('EPOCH = DDD', opm)
self.assertIn('X = 1', opm)
self.assertIn('Y = 2', opm)
self.assertIn('Z = 3', opm)
self.assertIn('X_DOT = 4', opm)
self.assertIn('Y_DOT = 5', opm)
self.assertIn('Z_DOT = 6', opm)
self.assertIn('MASS = 1000', opm)
self.assertIn('SOLAR_RAD_AREA = 20', opm)
self.assertIn('SOLAR_RAD_COEFF = 1', opm)
self.assertIn('DRAG_AREA = 20', opm)
self.assertIn('DRAG_COEFF = 2.2', opm)
return True
def _check_inputs(self, inputs):
for data_dict in inputs['requests']:
self._check_input(data_dict)
return True
def test_new_batch(self):
rest = _RestProxyForTest()
batches = Batches(rest)
# A successful run.
rest.expect_post("/batch", self._check_input, 200, {
'calc_state': 'PENDING',
'uuid': '1'
})
state = batches.new_batch(self.dummy_propagation_params,
self.dummy_opm_params)
self.assertEqual('1', state.get_uuid())
self.assertEqual('PENDING', state.get_calc_state())
# Unsuccessful run.
rest.expect_post("/batch", self._check_input, 400, {
'calc_state': 'PENDING',
'uuid': '1'
})
with self.assertRaises(RuntimeError):
batches.new_batch(self.dummy_propagation_params,
self.dummy_opm_params)
def test_new_batches(self):
rest = _RestProxyForTest()
batches = Batches(rest)
# Successful run.
rest.expect_post(
"/batches", self._check_inputs, 200, {
'requests': [{
'calc_state': 'PENDING',
'uuid': '1'
}, {
'calc_state': 'RUNNING',
'uuid': '2'
}]
})
states = batches.new_batches(
[[self.dummy_propagation_params, self.dummy_opm_params],
[self.dummy_propagation_params, self.dummy_opm_params]])
self.assertEqual(2, len(states))
self.assertEqual('1', states[0].get_uuid())
self.assertEqual('PENDING', states[0].get_calc_state())
self.assertEqual('2', states[1].get_uuid())
self.assertEqual('RUNNING', states[1].get_calc_state())
# Unsuccessful run.
rest.expect_post("/batches", self._check_inputs, 400, {})
with self.assertRaises(RuntimeError):
batches.new_batches(
[[self.dummy_propagation_params, self.dummy_opm_params],
[self.dummy_propagation_params, self.dummy_opm_params]])
def test_delete_batch(self):
rest = _RestProxyForTest()
batches = Batches(rest)
# Successful request.
rest.expect_delete("/batch/aaa", 204)
batches.delete_batch('aaa')
# 200 isn't a valid return value for delete calls right now
rest.expect_delete("/batch/aaa", 200)
with self.assertRaises(RuntimeError):
batches.delete_batch('aaa')
def test_get_summary(self):
rest = _RestProxyForTest()
batches = Batches(rest)
# Successful request.
rest.expect_get('/batch/aaa', 200, {
'uuid': 'aaa',
'calc_state': 'RUNNING'
})
summary = batches.get_summary('aaa')
self.assertEqual('aaa', summary.get_uuid())
self.assertEqual('RUNNING', summary.get_calc_state())
# Successfully found missing.
rest.expect_get('/batch/aaa', 404, 'Not JSON wat')
self.assertIsNone(batches.get_summary('aaa'))
# Unsuccessful request.
rest.expect_get('/batch/aaa', 503, 'Also not JSON wat')
with self.assertRaises(RuntimeError):
batches.get_summary('aaa')
def test_get_summaries(self):
rest = _RestProxyForTest()
batches = Batches(rest)
# Successful request.
rest.expect_get(
'/batch?project_uuid=' +
self.dummy_propagation_params.get_project_uuid(), 200, {
'items': [{
'uuid': 'aaa',
'calc_state': 'RUNNING'
}, {
'uuid': 'bbb',
'calc_state': 'COMPLETED'
}, {
'uuid': 'ccc',
'calc_state': 'FAILED'
}]
})
summaries = batches.get_summaries(
self.dummy_propagation_params.get_project_uuid())
self.assertEqual(3, len(summaries))
self.assertEqual('aaa', summaries['aaa'].get_uuid())
self.assertEqual('RUNNING', summaries['aaa'].get_calc_state())
self.assertEqual('bbb', summaries['bbb'].get_uuid())
self.assertEqual('COMPLETED', summaries['bbb'].get_calc_state())
self.assertEqual('ccc', summaries['ccc'].get_uuid())
self.assertEqual('FAILED', summaries['ccc'].get_calc_state())
# Unsuccessful request.
rest.expect_get(
'/batch?project_uuid=' +
self.dummy_propagation_params.get_project_uuid(), 403, {})
with self.assertRaises(RuntimeError):
batches.get_summaries(
self.dummy_propagation_params.get_project_uuid())
def test_get_propagation_results(self):
rest = _RestProxyForTest()
batches = Batches(rest)
# Parts count not specified. No result retrieval is attempted.
state = StateSummary({
'uuid': 'aaa',
'calc_state': 'COMPLETED',
})
self.assertIsNone(batches.get_propagation_results(state))
# Parts count is 0. No result retrieval is attempted.
state = StateSummary({
'uuid': 'aaa',
'calc_state': 'COMPLETED',
'parts_count': 0,
})
self.assertIsNone(batches.get_propagation_results(state))
# Normal retrieval.
state = StateSummary({
'uuid': 'aaa',
'calc_state': 'COMPLETED',
'parts_count': 2,
})
rest.expect_get('/batch/aaa/1', 200, {
'part_index': 'a',
'calc_state': 'RUNNING'
})
rest.expect_get('/batch/aaa/2', 200, {
'part_index': 'z',
'calc_state': 'COMPLETED'
})
results = batches.get_propagation_results(state)
self.assertEqual(2, len(results.get_parts()))
self.assertEqual('a', results.get_parts()[0].get_part_index())
self.assertEqual('z', results.get_parts()[1].get_part_index())
# Some parts could not be found.
state = StateSummary({
'uuid': 'aaa',
'calc_state': 'FAILED',
'parts_count': 3,
})
rest.expect_get('/batch/aaa/1', 404, 'Not json')
rest.expect_get('/batch/aaa/2', 200, {
'part_index': 'z',
'calc_state': 'COMPLETED'
})
rest.expect_get('/batch/aaa/3', 404, 'Not json')
results = batches.get_propagation_results(state)
self.assertEqual(3, len(results.get_parts()))
self.assertIsNone(results.get_parts()[0])
self.assertEqual('z', results.get_parts()[1].get_part_index())
self.assertIsNone(results.get_parts()[2])
# Complete failure.
state = StateSummary({
'uuid': 'aaa',
'calc_state': 'COMPLETED',
'parts_count': 2,
})
rest.expect_get('/batch/aaa/1', 403, 'irrelevant')
with self.assertRaises(RuntimeError):
batches.get_propagation_results(state)
'project_uuid': config.get_workspace(),
# 'step_size': 60 * 60, # step size (seconds)
# 'propagator_uuid': '00000000-0000-0000-0000-000000000002', # force model
# 'description': 'some description' # description of run
})
opm_params = OpmParams({
'epoch': '2017-10-04T00:00:00Z',
'state_vector': state_vec,
# 'mass': 500.5, # object mass
# 'solar_rad_area': 25.2, # object solar radiation area (m^2)
# 'solar_rad_coeff': 1.2, # object solar radiation coefficient
# 'drag_area': 33.3, # object drag area (m^2)
# 'drag_coeff': 2.5, # object drag coefficient
# 'covariance': covariance, # object covariance
# 'perturbation': 3, # sigma perturbation on state vector
# 'hypercube': 'FACES', # hypercube propagation type
# 'originator': 'Robot', # originator of run
# 'object_name': 'TestObj', # object name
# 'object_id': 'test1234', # object ID
})
batch = Batch(propagation_params, opm_params)
print("Submitting OPM:")
print(batch.get_opm_params().generate_opm())
# Submit and wait until batch run is ready
batches_module = Batches(auth_rest)
BatchRunManager(batches_module, [batch]).run()
def test_from_json(self):
self.maxDiff = None
json1 = {
"header": {
"originator": "Test",
"creation_date": "2018-06-21 16:22:20.550672"
},
"metadata": {
"comments": ["Cartesian coordinate system"],
"object_name": "TestObj",
"object_id": "TestObjId",
"center_name": "SUN",
"ref_frame": "ICRF",
"time_system": "UTC"
},
"spacecraft": {
"mass": 500.5,
"solar_rad_area": 25.2,
"solar_rad_coeff": 1.2,
"drag_area": 33.3,
"drag_coeff": 2.5
},
"ccsds_opm_vers": "2.0",
"state_vector": {
"epoch": "2018-06-21T16:22:20.550561Z",
"x": 130347560.13690618,
"y": -74407287.6018632,
"z": -35247598.54147063,
"x_dot": 23.935241263310683,
"y_dot": 27.146279819258538,
"z_dot": 10.346605942591514
}
}
expected_opm1 = """CCSDS_OPM_VERS = 2.0
CREATION_DATE = 2018-06-21 16:25:33.374936
ORIGINATOR = Test
COMMENT Cartesian coordinate system
OBJECT_NAME = TestObj
OBJECT_ID = TestObjId
CENTER_NAME = SUN
REF_FRAME = ICRF
TIME_SYSTEM = UTC
EPOCH = 2018-06-21T16:22:20.550561Z
X = 130347560.13690618
Y = -74407287.6018632
Z = -35247598.54147063
X_DOT = 23.935241263310683
Y_DOT = 27.146279819258538
Z_DOT = 10.346605942591514
MASS = 500.5
SOLAR_RAD_AREA = 25.2
SOLAR_RAD_COEFF = 1.2
DRAG_AREA = 33.3
DRAG_COEFF = 2.5"""
expected_opm1 = OpmParamsTest.remove_non_static_fields(expected_opm1)
opm_params1 = OpmParams.fromJsonResponse(json1)
actual_opm1 = OpmParamsTest.remove_non_static_fields(
opm_params1.generate_opm())
self.assertEqual(expected_opm1, actual_opm1)
json2 = {
"header": {
"originator": "Test",
"creation_date": "2018-06-21 17:43:20.984533"
},
"metadata": {
"comments": ["Cartesian coordinate system"],
"object_name": "TestObj",
"object_id": "TestObjId",
"center_name": "SUN",
"ref_frame": "ICRF",
"time_system": "UTC"
},
"spacecraft": {
"mass": 500.5,
"solar_rad_area": 25.2,
"solar_rad_coeff": 1.2,
"drag_area": 33.3,
"drag_coeff": 2.5
},
"maneuvers": [{
"duration": 0.0,
"man_epoch_ignition": "2018-06-21T17:43:20.984304Z",
"delta_mass": 0.0,
"man_ref_frame": "TNW",
"man_dv_1": 1.0,
"man_dv_2": 2.0,
"man_dv_3": 3.0,
}],
"covariance": {
"cx_x": 0.0003331349476038534,
"cy_x": 0.0004618927349220216,
"cy_y": 0.0006782421679971363,
"cz_x": -0.0003070007847730449,
"cz_y": -0.0004221234189514228,
"cz_z": 0.0003231931992380369,
"cx_dot_x": -3.34936503392263e-07,
"cx_dot_y": -4.686084221046758e-07,
"cx_dot_z": 2.484949578400095e-07,
"cx_dot_x_dot": 4.29602280558729e-10,
"cy_dot_x": -2.211832501084875e-07,
"cy_dot_y": -2.864186892102733e-07,
"cy_dot_z": 1.798098699846038e-07,
"cy_dot_x_dot": 2.608899201686016e-10,
"cy_dot_y_dot": 1.767514756338532e-10,
"cz_dot_x": -3.041346050686871e-07,
"cz_dot_y": -4.989496988610662e-07,
"cz_dot_z": 3.540310904497689e-07,
"cz_dot_x_dot": 1.86926319295459e-10,
"cz_dot_y_dot": 1.008862586240695e-10,
"cz_dot_z_dot": 6.2244443386355e-10
},
"adam_fields": [{
"key": "INITIAL_PERTURBATION",
"value": "3"
}, {
"key": "HYPERCUBE",
"value": "FACES"
}],
"ccsds_opm_vers":
"2.0",
"state_vector": {
"epoch": "2018-06-21T17:43:20.984304Z",
"x": 130347560.13690618,
"y": -74407287.6018632,
"z": -35247598.54147063,
"x_dot": 23.935241263310683,
"y_dot": 27.146279819258538,
"z_dot": 10.346605942591514
}
}
expected_opm2 = """CCSDS_OPM_VERS = 2.0
CREATION_DATE = 2018-06-21 17:43:20.984372
ORIGINATOR = Test
COMMENT Cartesian coordinate system
OBJECT_NAME = TestObj
OBJECT_ID = TestObjId
CENTER_NAME = SUN
REF_FRAME = ICRF
TIME_SYSTEM = UTC
EPOCH = 2018-06-21T17:43:20.984304Z
X = 130347560.13690618
Y = -74407287.6018632
Z = -35247598.54147063
X_DOT = 23.935241263310683
Y_DOT = 27.146279819258538
Z_DOT = 10.346605942591514
MASS = 500.5
SOLAR_RAD_AREA = 25.2
SOLAR_RAD_COEFF = 1.2
DRAG_AREA = 33.3
DRAG_COEFF = 2.5
CX_X = 0.0003331349476038534
CY_X = 0.0004618927349220216
CY_Y = 0.0006782421679971363
CZ_X = -0.0003070007847730449
CZ_Y = -0.0004221234189514228
CZ_Z = 0.0003231931992380369
CX_DOT_X = -3.34936503392263e-07
CX_DOT_Y = -4.686084221046758e-07
CX_DOT_Z = 2.484949578400095e-07
CX_DOT_X_DOT = 4.29602280558729e-10
CY_DOT_X = -2.211832501084875e-07
CY_DOT_Y = -2.864186892102733e-07
CY_DOT_Z = 1.798098699846038e-07
CY_DOT_X_DOT = 2.608899201686016e-10
CY_DOT_Y_DOT = 1.767514756338532e-10
CZ_DOT_X = -3.041346050686871e-07
CZ_DOT_Y = -4.989496988610662e-07
CZ_DOT_Z = 3.540310904497689e-07
CZ_DOT_X_DOT = 1.86926319295459e-10
CZ_DOT_Y_DOT = 1.008862586240695e-10
CZ_DOT_Z_DOT = 6.2244443386355e-10
USER_DEFINED_ADAM_INITIAL_PERTURBATION = 3 [sigma]
USER_DEFINED_ADAM_HYPERCUBE = FACES
MAN_EPOCH_IGNITION = 2018-06-21T17:43:20.984304Z
MAN_DURATION = 0.0
MAN_DELTA_MASS = 0.0
MAN_REF_FRAME = TNW
MAN_DV_1 = 1.0
MAN_DV_2 = 2.0
MAN_DV_3 = 3.0"""
expected_opm2 = OpmParamsTest.remove_non_static_fields(expected_opm2)
opm_params2 = OpmParams.fromJsonResponse(json2)
actual_opm2 = OpmParamsTest.remove_non_static_fields(
opm_params2.generate_opm())
self.assertEqual(expected_opm2, actual_opm2)
json3 = {
"header": {
"originator": "Test",
"creation_date": "2018-06-21 17:56:58.406867"
},
"metadata": {
"comments": ["Cartesian coordinate system"],
"object_name": "TestObj",
"object_id": "TestObjId",
"center_name": "SUN",
"ref_frame": "ICRF",
"time_system": "UTC"
},
"keplerian": {
"eccentricity": 0.5355029800000188,
"inclination": 23.439676743246295,
"gm": 132712440041.9394,
"semi_major_axis": 313072891.38037175,
"mean_motion": 0.0,
"ra_of_asc_node": 359.9942693176405,
"arg_of_pericenter": 328.5584374618295,
"true_anomaly": -127.01778914927144,
"mean_anomaly": 0.0
},
"spacecraft": {
"mass": 500.5,
"solar_rad_area": 25.2,
"solar_rad_coeff": 1.2,
"drag_area": 33.3,
"drag_coeff": 2.5
},
"ccsds_opm_vers": "2.0",
"state_vector": {
"epoch": "2018-06-21T17:56:58.406556Z",
"x": 0.0,
"y": 0.0,
"z": 0.0,
"x_dot": 0.0,
"y_dot": 0.0,
"z_dot": 0.0
}
}
expected_opm3 = """CCSDS_OPM_VERS = 2.0
CREATION_DATE = 2018-06-21 17:56:58.406717
ORIGINATOR = Test
COMMENT Cartesian coordinate system
OBJECT_NAME = TestObj
OBJECT_ID = TestObjId
CENTER_NAME = SUN
REF_FRAME = ICRF
TIME_SYSTEM = UTC
EPOCH = 2018-06-21T17:56:58.406556Z
X = 0.0
Y = 0.0
Z = 0.0
X_DOT = 0.0
Y_DOT = 0.0
Z_DOT = 0.0
SEMI_MAJOR_AXIS = 313072891.38037175
ECCENTRICITY = 0.5355029800000188
INCLINATION = 23.439676743246295
RA_OF_ASC_NODE = 359.9942693176405
ARG_OF_PERICENTER = 328.5584374618295
TRUE_ANOMALY = -127.01778914927144
GM = 132712440041.9394
MASS = 500.5
SOLAR_RAD_AREA = 25.2
SOLAR_RAD_COEFF = 1.2
DRAG_AREA = 33.3
DRAG_COEFF = 2.5"""
expected_opm3 = OpmParamsTest.remove_non_static_fields(expected_opm3)
opm_params3 = OpmParams.fromJsonResponse(json3)
actual_opm3 = OpmParamsTest.remove_non_static_fields(
opm_params3.generate_opm())
self.assertEqual(expected_opm3, actual_opm3)
class TargetedPropagationsTest(unittest.TestCase):
"""Unit tests for TargetedPropagations module
"""
@classmethod
def remove_non_static_fields(cls, opm_string):
# Remove the CREATION_DATE stamp since that varies.
return "\n".join([line for line in opm_string.splitlines()
if not line.startswith('CREATION_DATE')])
dummy_propagation_params = PropagationParams({
'start_time': 'AAA',
'end_time': 'BBB',
})
dummy_opm_params = OpmParams({
'epoch': 'DDD',
'state_vector': [1.0, 2.0, 3.0, 4.0, 5.0, 6.0]
})
dummy_targeting_params = TargetingParams({
'target_distance_from_earth': 123
})
dummy_opm_params_as_api_response = {
"header": {
"originator": "ADAM_User",
"creation_date": "2018-06-21 19:13:27.261813"
},
"metadata": {
"comments": [
"Cartesian coordinate system"
],
"object_name": "dummy",
"object_id": "001",
"center_name": "SUN",
"ref_frame": "ICRF",
"time_system": "UTC"
},
"spacecraft": {
"mass": 1000.0,
"solar_rad_area": 20.0,
"solar_rad_coeff": 1.0,
"drag_area": 20.0,
"drag_coeff": 2.2
},
"ccsds_opm_vers": "2.0",
"state_vector": {
"epoch": "DDD",
"x": 1.0,
"y": 2.0,
"z": 3.0,
"x_dot": 4.0,
"y_dot": 5.0,
"z_dot": 6.0
}
}
def test_insert_targeted_propagation(self):
dummy_rest = {'not': 'used'}
targeted_props = TargetedPropagations(dummy_rest)
# Override AdamObjects._insert to just dump out a copy of the data passed.
passed_data = []
def store_data(self, data, passed_data=passed_data):
passed_data.append(data)
return 'uuid'
tmp_insert = AdamObjects._insert
AdamObjects._insert = store_data
prop = TargetedPropagation(
self.dummy_propagation_params,
self.dummy_opm_params,
self.dummy_targeting_params)
targeted_props.insert(prop, 'project_uuid')
uuid = prop.get_uuid()
self.assertEqual('uuid', uuid)
self.assertEqual(
self.dummy_propagation_params.get_description(),
passed_data[0]['description'])
passed_prop_params = passed_data[0]['initialPropagationParameters']
self.assertEqual(
self.dummy_propagation_params.get_start_time(),
passed_prop_params['start_time'])
self.assertEqual(
self.dummy_propagation_params.get_end_time(),
passed_prop_params['end_time'])
self.assertEqual(
self.dummy_propagation_params.get_propagator_uuid(),
passed_prop_params['propagator_uuid'])
self.assertEqual(
self.dummy_propagation_params.get_step_size(),
passed_prop_params['step_duration_sec'])
self.assertEqual(
TargetedPropagationsTest.remove_non_static_fields(
self.dummy_opm_params.generate_opm()),
TargetedPropagationsTest.remove_non_static_fields(
passed_prop_params['opmFromString']))
passed_targeting_params = passed_data[0]['targetingParameters']
self.assertEqual(self.dummy_targeting_params.get_target_distance_from_earth(),
passed_targeting_params['targetDistanceFromEarth'])
self.assertEqual(self.dummy_targeting_params.get_tolerance(),
passed_targeting_params['tolerance'])
self.assertEqual(self.dummy_targeting_params.get_run_nominal_only(),
passed_targeting_params['runNominalOnly'])
self.assertEqual('project_uuid', passed_data[0]['project'])
AdamObjects._insert = tmp_insert
def test_get_targeted_propagation(self):
dummy_rest = {'not': 'used'}
targeted_props = TargetedPropagations(dummy_rest)
return_data = {
"uuid": "uuid",
"initialPropagationParameters": {
"start_time": "AAA",
"end_time": "BBB",
"step_duration_sec": "0",
"propagator_uuid": "00000000-0000-0000-0000-000000000001",
"executor": "stk",
"opm": {
"header": {
"originator": "ADAM_User",
"creation_date": "2018-06-21 19:28:47.304102"
},
"metadata": {
"comments": [
"Cartesian coordinate system"
],
"object_name": "dummy",
"object_id": "001",
"center_name": "SUN",
"ref_frame": "ICRF",
"time_system": "UTC"
},
"spacecraft": {
"mass": 1000.0,
"solar_rad_area": 20.0,
"solar_rad_coeff": 1.0,
"drag_area": 20.0,
"drag_coeff": 2.2
},
"ccsds_opm_vers": "2.0",
"state_vector": {
"epoch": "DDD",
"x": 1.0,
"y": 2.0,
"z": 3.0,
"x_dot": 4.0,
"y_dot": 5.0,
"z_dot": 6.0
}
}
},
"targetingParameters": {
"targetDistanceFromEarth": 123.0,
"tolerance": 1.0,
"runNominalOnly": False
},
"description": "Created by test at 2018-06-21 19:28:47.303980Z",
"maneuverX": 0.0,
"maneuverY": 0.0,
"maneuverZ": 0.0
}
def return_data(self, uuid, return_data=return_data):
return return_data
tmp_get_json = AdamObjects._get_json
AdamObjects._get_json = return_data
targeted_prop = targeted_props.get('uuid')
self.assertEqual('uuid', targeted_prop.get_uuid())
self.assertEqual(self.dummy_propagation_params.get_start_time(),
targeted_prop.get_propagation_params().get_start_time())
self.assertEqual(self.dummy_propagation_params.get_end_time(),
targeted_prop.get_propagation_params().get_end_time())
self.assertEqual(
TargetedPropagationsTest.remove_non_static_fields(
self.dummy_opm_params.generate_opm()),
TargetedPropagationsTest.remove_non_static_fields(
targeted_prop.get_opm_params().generate_opm()))
self.assertEqual(self.dummy_targeting_params.get_target_distance_from_earth(),
targeted_prop.get_targeting_params().get_target_distance_from_earth())
self.assertIsNone(targeted_prop.get_ephemeris())
self.assertEqual([0, 0, 0], targeted_prop.get_maneuver())
AdamObjects._get_json = tmp_get_json
class BatchPropagationsTest(unittest.TestCase):
"""Unit tests for BatchPropagations module
"""
@classmethod
def remove_non_static_fields(cls, opm_string):
# Remove the CREATION_DATE stamp since that varies.
return "\n".join([
line for line in opm_string.splitlines()
if not line.startswith('CREATION_DATE')
])
dummy_propagation_params = PropagationParams({
'start_time': 'AAA',
'end_time': 'BBB',
})
dummy_opm_params = OpmParams({
'epoch': 'DDD',
'state_vector': [1.0, 2.0, 3.0, 4.0, 5.0, 6.0]
})
dummy_opm_params_as_api_response = {
"header": {
"originator": "ADAM_User",
"creation_date": "2018-06-21 19:13:27.261813"
},
"metadata": {
"comments": ["Cartesian coordinate system"],
"object_name": "dummy",
"object_id": "001",
"center_name": "SUN",
"ref_frame": "ICRF",
"time_system": "UTC"
},
"spacecraft": {
"mass": 1000.0,
"solar_rad_area": 20.0,
"solar_rad_coeff": 1.0,
"drag_area": 20.0,
"drag_coeff": 2.2
},
"ccsds_opm_vers": "2.0",
"state_vector": {
"epoch": "DDD",
"x": 1.0,
"y": 2.0,
"z": 3.0,
"x_dot": 4.0,
"y_dot": 5.0,
"z_dot": 6.0
}
}
def test_create_batch_propagation(self):
dummy_rest = {'not': 'used'}
batch_props = BatchPropagations(dummy_rest)
# Override AdamObjects._insert to just dump out a copy of the data passed.
passed_data = []
def store_data(self, data, passed_data=passed_data):
passed_data.append(data)
return 'uuid'
tmp_insert = AdamObjects._insert
AdamObjects._insert = store_data
batch_prop = BatchPropagation(self.dummy_propagation_params,
self.dummy_opm_params)
batch_props.insert(batch_prop, 'project_uuid')
uuid = batch_prop.get_uuid()
self.assertEqual('uuid', uuid)
self.assertEqual(self.dummy_propagation_params.get_description(),
passed_data[0]['description'])
passed_prop_params = passed_data[0]['templatePropagationParameters']
self.assertEqual(self.dummy_propagation_params.get_start_time(),
passed_prop_params['start_time'])
self.assertEqual(self.dummy_propagation_params.get_end_time(),
passed_prop_params['end_time'])
self.assertEqual(self.dummy_propagation_params.get_propagator_uuid(),
passed_prop_params['propagator_uuid'])
self.assertEqual(self.dummy_propagation_params.get_step_size(),
passed_prop_params['step_duration_sec'])
self.assertEqual(
BatchPropagationsTest.remove_non_static_fields(
self.dummy_opm_params.generate_opm()),
BatchPropagationsTest.remove_non_static_fields(
passed_prop_params['opmFromString']))
self.assertEqual('project_uuid', passed_data[0]['project'])
AdamObjects._insert = tmp_insert
def test_get_batch_propagation(self):
dummy_rest = {'not': 'used'}
batch_props = BatchPropagations(dummy_rest)
return_data = {
"uuid":
"uuid",
"templatePropagationParameters": {
"start_time": "AAA",
"end_time": "BBB",
"step_duration_sec": "0",
"propagator_uuid": "00000000-0000-0000-0000-000000000001",
"executor": "stk",
"opm": {
"header": {
"originator": "ADAM_User",
"creation_date": "2018-06-21 19:28:47.304102"
},
"metadata": {
"comments": ["Cartesian coordinate system"],
"object_name": "dummy",
"object_id": "001",
"center_name": "SUN",
"ref_frame": "ICRF",
"time_system": "UTC"
},
"spacecraft": {
"mass": 1000.0,
"solar_rad_area": 20.0,
"solar_rad_coeff": 1.0,
"drag_area": 20.0,
"drag_coeff": 2.2
},
"ccsds_opm_vers": "2.0",
"state_vector": {
"epoch": "DDD",
"x": 1.0,
"y": 2.0,
"z": 3.0,
"x_dot": 4.0,
"y_dot": 5.0,
"z_dot": 6.0
}
}
},
"summary":
"1000 2000 3000 4000 5000 6000 7000\n7000 6000 5000 4000 3000 2000 1000"
}
def return_data(self, uuid, return_data=return_data):
return return_data
tmp_get_json = AdamObjects._get_json
AdamObjects._get_json = return_data
batch_prop = batch_props.get('uuid')
self.assertEqual('uuid', batch_prop.get_uuid())
self.assertEqual(self.dummy_propagation_params.get_start_time(),
batch_prop.get_propagation_params().get_start_time())
self.assertEqual(self.dummy_propagation_params.get_end_time(),
batch_prop.get_propagation_params().get_end_time())
self.assertEqual(
BatchPropagationsTest.remove_non_static_fields(
self.dummy_opm_params.generate_opm()),
BatchPropagationsTest.remove_non_static_fields(
batch_prop.get_opm_params().generate_opm()))
self.assertEqual(
'1000 2000 3000 4000 5000 6000 7000\n7000 6000 5000 4000 3000 2000 1000',
batch_prop.get_summary())
self.assertEqual([[1, 2, 3, 4, 5, 6, 7], [7, 6, 5, 4, 3, 2, 1]],
batch_prop.get_final_state_vectors())
AdamObjects._get_json = tmp_get_json
def test_basic_stm(self):
state_vec = [
130347560.13690618, -74407287.6018632, -35247598.541470632,
23.935241263310683, 27.146279819258538, 10.346605942591514
]
start_time = datetime.datetime(2017, 10, 4, 0, 0, 0, 123456)
end_time = datetime.datetime(2018, 10, 4, 0, 0, 0, 123456)
propagation_params = PropagationParams({
'start_time':
start_time.isoformat() + 'Z',
'end_time':
end_time.isoformat() + 'Z',
'project_uuid':
self.working_project.get_uuid(),
'description':
'Created by test at ' + start_time.isoformat() + 'Z'
})
opm_params = OpmParams({
'epoch': start_time.isoformat() + 'Z',
'state_vector': state_vec,
})
end_state, stm = self.stm_module.run_stm_propagation(
propagation_params, opm_params)
# Taken from printed output of ../state_stm_propagation.py
expected_end_state = np.array([
-37523497.931654416, 492950622.8491298, 204482176.63445434,
-11.336957217854795, 7.18499733419028, 3.3597496059480085
])
expected_stm = np.matrix(
[[
9.70874844e+00, -1.21563565e+00, -9.26967637e-01,
5.34214567e+07, 1.64329953e+07, 5.30094892e+06
],
[
7.11171945e+00, -3.24202476e+00, -5.93038128e-01,
3.90278376e+07, 3.82420496e+07, 9.62761631e+06
],
[
2.50503331e+00, -3.00334152e-01, -2.62144498e+00,
1.46131045e+07, 1.04218322e+07, 1.53347450e+07
],
[
2.14264136e-07, -2.82295666e-08, -2.23357566e-08,
1.33259336e+00, 6.98930318e-01, 2.41824966e-01
],
[
4.69172199e-07, -2.03571494e-07, -6.32223023e-08,
2.52995851e+00, 2.04570983e+00, 7.47014439e-01
],
[
1.82661672e-07, -4.57388872e-08, -1.15455121e-07,
9.96459361e-01, 8.11376173e-01, 3.16765622e-01
]])
npt.assert_allclose(expected_end_state,
np.array(end_state),
rtol=1e-8,
atol=0)
npt.assert_allclose(expected_stm.getA(), stm.getA(), rtol=1e-8, atol=0)
