def test_fuel_tanks_content(self):
script_path = self.sandbox.path_to_jsbsim_file('scripts', 'J2460.xml')
fdm = CreateFDM(self.sandbox)
fdm.load_script(script_path)
fdm.run_ic()
tree = et.parse(script_path)
use_tag = tree.getroot().find('use')
aircraft_name = use_tag.attrib['aircraft']
aircraft_path = self.sandbox.path_to_jsbsim_file('aircraft',
aircraft_name)
aircraft_tree = et.parse(os.path.join(aircraft_path,
aircraft_name+'.xml'))
total_fuel_quantity = 0.0
total_oxidizer_quantity = 0.0
for tank in aircraft_tree.findall('propulsion/tank'):
contents = float(tank.find('contents').text)
if tank.attrib['type'] == "FUEL":
total_fuel_quantity += contents
elif tank.attrib['type'] == 'OXIDIZER':
total_oxidizer_quantity += contents
self.assertAlmostEqual(fdm['propulsion/total-fuel-lbs'],
total_fuel_quantity)
self.assertAlmostEqual(fdm['propulsion/total-oxidizer-lbs'],
total_oxidizer_quantity)
def test_wind_frame(self):
script_path = self.sandbox.path_to_jsbsim_file('scripts',
'ball_chute.xml')
fdm = CreateFDM(self.sandbox)
fdm.load_script(script_path)
fdm.run_ic()
self.assertAlmostEqual(
fdm['external_reactions/parachute/location-x-in'], 12.0)
self.assertAlmostEqual(
fdm['external_reactions/parachute/location-y-in'], 0.0)
self.assertAlmostEqual(
fdm['external_reactions/parachute/location-z-in'], 0.0)
self.assertAlmostEqual(fdm['external_reactions/parachute/x'], -1.0)
self.assertAlmostEqual(fdm['external_reactions/parachute/y'], 0.0)
self.assertAlmostEqual(fdm['external_reactions/parachute/z'], 0.0)
while fdm.run():
Tw2b = fdm.get_auxiliary().get_Tw2b()
mag = fdm['aero/qbar-psf'] * fdm[
'fcs/parachute_reef_pos_norm'] * 20.0
f = Tw2b * np.mat([-1.0, 0.0, 0.0]).T * mag
self.assertAlmostEqual(fdm['forces/fbx-external-lbs'], f[0, 0])
self.assertAlmostEqual(fdm['forces/fby-external-lbs'], f[1, 0])
self.assertAlmostEqual(fdm['forces/fbz-external-lbs'], f[2, 0])
m = np.cross(self.getLeverArm(fdm, 'parachute'),
np.array([f[0, 0], f[1, 0], f[2, 0]]))
self.assertAlmostEqual(fdm['moments/l-external-lbsft'], m[0])
self.assertAlmostEqual(fdm['moments/m-external-lbsft'], m[1])
self.assertAlmostEqual(fdm['moments/n-external-lbsft'], m[2])
def testDebugLvl(self):
fdm = CreateFDM(self.sandbox)
fdm.load_script(
self.sandbox.path_to_jsbsim_file('scripts', 'ball_orbit.xml'))
fdm.run_ic()
ExecuteUntil(fdm, 1000.)
ref, current = Table(), Table()
ref.ReadCSV(self.sandbox('BallOut.csv'))
del fdm
os.environ["JSBSIM_DEBUG"] = str(0)
fdm = CreateFDM(self.sandbox)
fdm.load_script(
self.sandbox.path_to_jsbsim_file('scripts', 'ball_orbit.xml'))
fdm.run_ic()
ExecuteUntil(fdm, 1000.)
current.ReadCSV(self.sandbox('BallOut.csv'))
diff = ref.compare(current)
self.longMessage = True
self.assertTrue(diff.empty(), msg='\n' + repr(diff))
def test_CAS_ic(self):
script_name = 'Short_S23_3.xml'
script_path = self.sandbox.path_to_jsbsim_file('scripts', script_name)
# Add a Pitot angle to the Short S23
tree, aircraft_name, path_to_jsbsim_aircrafts = CopyAircraftDef(script_path, self.sandbox)
self.addPitotTube(tree.getroot(), 5.0)
tree.write(self.sandbox('aircraft', aircraft_name,
aircraft_name+'.xml'))
# Read the CAS specified in the IC file
tree = et.parse(script_path)
use_element = tree.getroot().find('use')
IC_file = use_element.attrib['initialize']
tree = et.parse(os.path.join(path_to_jsbsim_aircrafts,
append_xml(IC_file)))
vc_tag = tree.getroot().find('./vc')
VCAS = float(vc_tag.text)
if 'unit' in vc_tag.attrib and vc_tag.attrib['unit'] == 'FT/SEC':
VCAS /= 1.68781 # Converts in kts
# Run the IC and check that the model is initialized correctly
fdm = CreateFDM(self.sandbox)
fdm.set_aircraft_path('aircraft')
fdm.load_script(script_path)
fdm.run_ic()
self.assertAlmostEqual(fdm['ic/vc-kts'], VCAS, delta=1E-7)
self.assertAlmostEqual(fdm['velocities/vc-kts'], VCAS, delta=1E-7)
def testOrbit(self):
script_name = 'ball_orbit.xml'
script_path = self.sandbox.path_to_jsbsim_file('scripts', script_name)
self.AddAccelerometersToAircraft(script_path)
# The time step is too small in ball_orbit so let's increase it to 0.1s
# for a quicker run
tree = et.parse(script_path)
run_tag = tree.getroot().find('./run')
run_tag.attrib['dt'] = '0.1'
tree.write(script_name)
fdm = CreateFDM(self.sandbox)
fdm.set_aircraft_path('aircraft')
fdm.load_script(script_name)
# Switch the accel on
fdm['fcs/accelerometer/on'] = 1.0
fdm.run_ic()
while fdm.run():
self.assertAlmostEqual(fdm['fcs/accelerometer/X'], 0.0, delta=1E-8)
self.assertAlmostEqual(fdm['fcs/accelerometer/Y'], 0.0, delta=1E-8)
self.assertAlmostEqual(fdm['fcs/accelerometer/Z'], 0.0, delta=1E-8)
self.assertAlmostEqual(fdm['accelerations/a-pilot-x-ft_sec2'],
0.0,
delta=1E-8)
self.assertAlmostEqual(fdm['accelerations/a-pilot-y-ft_sec2'],
0.0,
delta=1E-8)
self.assertAlmostEqual(fdm['accelerations/a-pilot-z-ft_sec2'],
0.0,
delta=1E-8)
del fdm
def testDebugLvl(self):
fdm = CreateFDM(self.sandbox)
fdm.load_script(
self.sandbox.path_to_jsbsim_file('scripts', 'ball_orbit.xml'))
fdm.run_ic()
ExecuteUntil(fdm, 1000.)
ref = pd.read_csv('BallOut.csv', index_col=0)
del fdm
os.environ["JSBSIM_DEBUG"] = str(0)
fdm = CreateFDM(self.sandbox)
fdm.load_script(
self.sandbox.path_to_jsbsim_file('scripts', 'ball_orbit.xml'))
fdm.run_ic()
ExecuteUntil(fdm, 1000.)
current = pd.read_csv('BallOut.csv', index_col=0)
# Check the data are matching i.e. the time steps are the same between
# the two data sets and that the output data are also the same.
self.assertTrue(isDataMatching(ref, current))
# Find all the data that are differing by more than 1E-8 between the
# two data sets.
diff = FindDifferences(ref, current, 1E-8)
self.longMessage = True
self.assertEqual(len(diff), 0, msg='\n' + diff.to_string())
def test_hold_down_with_gnd_reactions(self):
fdm = CreateFDM(self.sandbox)
fdm.load_script(self.sandbox.path_to_jsbsim_file('scripts',
'c1721.xml'))
fdm.run_ic()
ExecuteUntil(fdm, 0.25)
fdm['forces/hold-down'] = 1.0
h0 = fdm['position/h-sl-ft']
pitch = fdm['attitude/pitch-rad']
roll = fdm['attitude/roll-rad']
heading = fdm['attitude/heading-true-rad']
while fdm['simulation/sim-time-sec'] < 2.0:
fdm.run()
self.assertAlmostEqual(fdm['accelerations/pdot-rad_sec2'], 0.0)
self.assertAlmostEqual(fdm['accelerations/qdot-rad_sec2'], 0.0)
self.assertAlmostEqual(fdm['accelerations/rdot-rad_sec2'], 0.0)
self.assertAlmostEqual(fdm['accelerations/udot-ft_sec2'], 0.0)
self.assertAlmostEqual(fdm['accelerations/vdot-ft_sec2'], 0.0)
self.assertAlmostEqual(fdm['accelerations/wdot-ft_sec2'], 0.0)
self.assertAlmostEqual(fdm['position/h-sl-ft'], h0, delta=1E-6)
self.assertAlmostEqual(fdm['attitude/pitch-rad'], pitch)
self.assertAlmostEqual(fdm['attitude/roll-rad'], roll)
self.assertAlmostEqual(fdm['attitude/heading-true-rad'], heading)
def test_output(self):
tree = et.parse(self.script_path)
output_tag = et.SubElement(tree.getroot(), 'output')
output_tag.attrib['name'] = 'test.csv'
output_tag.attrib['type'] = 'CSV'
output_tag.attrib['rate'] = '10'
property_tag = et.SubElement(output_tag, 'property')
property_tag.text = 'position/vrp-radius-ft'
tree.write('c1722_0.xml')
fdm = CreateFDM(self.sandbox)
fdm.load_script('c1722_0.xml')
fdm.run_ic()
ExecuteUntil(fdm, 10.)
self.assertTrue(self.sandbox.exists(output_tag.attrib['name']),
msg="The file 'output.csv' has not been created")
orig = pd.read_csv('JSBout172B.csv', index_col=0)
test = pd.read_csv('test.csv', index_col=0)
pname = '/fdm/jsbsim/' + property_tag.text
ref = orig[pname]
mod = test[pname]
# Check the data are matching i.e. the time steps are the same between
# the two data sets.
self.assertTrue(isDataMatching(ref, mod))
# Find all the data that are differing by more than 1E-8 between the
# two data sets.
delta = pd.concat([np.abs(ref - mod), ref, mod], axis=1)
delta.columns = ['delta', 'ref value', 'value']
diff = delta[delta['delta'] > 1E-8]
self.longMessage = True
self.assertEqual(len(diff), 0, msg='\n'+diff.to_string())
def SubProcessScriptExecution(sandbox, script_path):
fdm = CreateFDM(sandbox)
fdm.load_script(script_path)
fdm.run_ic()
while fdm.run():
pass
def test_hold_down_with_gnd_reactions(self):
fdm = CreateFDM(self.sandbox)
fdm.load_script(
self.sandbox.path_to_jsbsim_file('scripts', 'c1721.xml'))
fdm.run_ic()
ExecuteUntil(fdm, 0.25)
fdm['forces/hold-down'] = 1.0
h0 = fdm['position/h-sl-ft']
pitch = fdm['attitude/pitch-rad']
roll = fdm['attitude/roll-rad']
heading = fdm['attitude/heading-true-rad']
while fdm['simulation/sim-time-sec'] < 2.0:
fdm.run()
self.assertAlmostEqual(fdm['accelerations/pdot-rad_sec2'], 0.0)
self.assertAlmostEqual(fdm['accelerations/qdot-rad_sec2'], 0.0)
self.assertAlmostEqual(fdm['accelerations/rdot-rad_sec2'], 0.0)
self.assertAlmostEqual(fdm['accelerations/udot-ft_sec2'], 0.0)
self.assertAlmostEqual(fdm['accelerations/vdot-ft_sec2'], 0.0)
self.assertAlmostEqual(fdm['accelerations/wdot-ft_sec2'], 0.0)
self.assertAlmostEqual(fdm['position/h-sl-ft'], h0, delta=1E-6)
self.assertAlmostEqual(fdm['attitude/pitch-rad'], pitch)
self.assertAlmostEqual(fdm['attitude/roll-rad'], roll)
self.assertAlmostEqual(fdm['attitude/heading-true-rad'], heading)
def Compare(self, section):
# Rerun the script with the modified aircraft definition
self.sandbox.delete_csv_files()
fdm = CreateFDM(self.sandbox)
# We need to tell JSBSim that the aircraft definition is located in the
# directory build/.../aircraft
fdm.set_aircraft_path('aircraft')
fdm.set_output_directive(
self.sandbox.path_to_jsbsim_file('tests', 'output.xml'))
fdm.load_script(self.script)
fdm['simulation/randomseed'] = 0.0
fdm.run_ic()
ExecuteUntil(fdm, 50.0)
mod = pd.read_csv('output.csv', index_col=0)
# Check the data are matching i.e. the time steps are the same between
# the two data sets and that the output data are also the same.
self.assertTrue(isDataMatching(self.ref, mod))
# Whether the data is read from the aircraft definition file or from an
# external file, the results shall be exactly identical. Hence the
# precision set to 0.0.
diff = FindDifferences(self.ref, mod, 0.0)
self.assertEqual(len(diff),
0,
msg='\nTesting section "' + section + '"\n' +
diff.to_string())
def Compare(self, section):
# Rerun the script with the modified aircraft definition
self.sandbox.delete_csv_files()
fdm = CreateFDM(self.sandbox)
# We need to tell JSBSim that the aircraft definition is located in the
# directory build/.../aircraft
fdm.set_aircraft_path('aircraft')
fdm.set_output_directive(
self.sandbox.path_to_jsbsim_file('tests', 'output.xml'))
fdm.load_script(self.script)
fdm.set_property_value('simulation/randomseed', 0.0)
fdm.run_ic()
ExecuteUntil(fdm, 50.0)
mod = Table()
mod.ReadCSV(self.sandbox('output.csv'))
# Whether the data is read from the aircraft definition file or from an
# external file, the results shall be exactly identical. Hence the
# precision set to 0.0.
diff = self.ref.compare(mod, 0.0)
self.assertTrue(diff.empty(),
msg='\nTesting section "' + section + '"\n' +
repr(diff))
def testFunctionWithIndexedProps(self):
tree = et.parse(self.sandbox.path_to_jsbsim_file('engine',
'eng_PegasusXc.xml'))
# Define the function starter-max-power-W as a 'post' function
root = tree.getroot()
startPowFunc_tag = root.find("function/[@name='propulsion/engine[#]/starter-max-power-W']")
startPowFunc_tag.attrib['type']='post'
tree.write('eng_PegasusXc.xml')
# Copy the propeller file.
shutil.copy(self.sandbox.path_to_jsbsim_file('engine', 'prop_deHavilland5000.xml'),
'.')
fdm = CreateFDM(self.sandbox)
fdm.set_engine_path('.')
fdm.load_script(self.sandbox.path_to_jsbsim_file('scripts',
'Short_S23_1.xml'))
fdm.run_ic()
pm = fdm.get_property_manager()
self.assertTrue(pm.hasNode('propulsion/engine[0]/starter-max-power-W'))
self.assertTrue(pm.hasNode('propulsion/engine[1]/starter-max-power-W'))
self.assertTrue(pm.hasNode('propulsion/engine[2]/starter-max-power-W'))
self.assertTrue(pm.hasNode('propulsion/engine[3]/starter-max-power-W'))
while fdm.run():
rpm = [fdm['propulsion/engine[0]/engine-rpm'],
fdm['propulsion/engine[1]/engine-rpm'],
fdm['propulsion/engine[2]/engine-rpm'],
fdm['propulsion/engine[3]/engine-rpm']]
for i in range(4):
maxPower = max(0.0, 1.0-rpm[i]/400)*498.941*0.10471976*rpm[i]
self.assertAlmostEqual(fdm['propulsion/engine[%d]/starter-max-power-W' % (i,)],
maxPower)
def testOrbit(self):
script_name = 'ball_orbit.xml'
script_path = self.sandbox.path_to_jsbsim_file('scripts', script_name)
self.AddAccelerometersToAircraft(script_path)
# The time step is too small in ball_orbit so let's increase it to 0.1s
# for a quicker run
tree = et.parse(script_path)
run_tag = tree.getroot().find('./run')
run_tag.attrib['dt'] = '0.1'
tree.write(script_name)
fdm = CreateFDM(self.sandbox)
fdm.set_aircraft_path('aircraft')
fdm.load_script(script_name)
# Switch the accel on
fdm['fcs/accelerometer/on'] = 1.0
fdm.run_ic()
while fdm.run():
self.assertAlmostEqual(fdm['fcs/accelerometer/X'], 0.0, delta=1E-8)
self.assertAlmostEqual(fdm['fcs/accelerometer/Y'], 0.0, delta=1E-8)
self.assertAlmostEqual(fdm['fcs/accelerometer/Z'], 0.0, delta=1E-8)
self.assertAlmostEqual(fdm['accelerations/a-pilot-x-ft_sec2'], 0.0,
delta=1E-8)
self.assertAlmostEqual(fdm['accelerations/a-pilot-y-ft_sec2'], 0.0,
delta=1E-8)
self.assertAlmostEqual(fdm['accelerations/a-pilot-z-ft_sec2'], 0.0,
delta=1E-8)
del fdm
def test_output(self):
tree = et.parse(self.script_path)
output_tag = et.SubElement(tree.getroot(), 'output')
output_tag.attrib['name'] = 'test.csv'
output_tag.attrib['type'] = 'CSV'
output_tag.attrib['rate'] = '10'
property_tag = et.SubElement(output_tag, 'property')
property_tag.text = 'position/vrp-radius-ft'
tree.write('c1722_0.xml')
fdm = CreateFDM(self.sandbox)
fdm.load_script('c1722_0.xml')
fdm.run_ic()
ExecuteUntil(fdm, 10.)
self.assertTrue(self.sandbox.exists(output_tag.attrib['name']),
msg="The file 'output.csv' has not been created")
orig = pd.read_csv('JSBout172B.csv', index_col=0)
test = pd.read_csv('test.csv', index_col=0)
pname = '/fdm/jsbsim/' + property_tag.text
ref = orig[pname]
mod = test[pname]
# Check the data are matching i.e. the time steps are the same between
# the two data sets.
self.assertTrue(isDataMatching(ref, mod))
# Find all the data that are differing by more than 1E-8 between the
# two data sets.
delta = pd.concat([np.abs(ref - mod), ref, mod], axis=1)
delta.columns = ['delta', 'ref value', 'value']
diff = delta[delta['delta'] > 1E-8]
self.longMessage = True
self.assertEqual(len(diff), 0, msg='\n' + diff.to_string())
def test_fuel_tanks_content(self):
script_path = self.sandbox.path_to_jsbsim_file('scripts', 'J2460.xml')
fdm = CreateFDM(self.sandbox)
fdm.load_script(script_path)
fdm.run_ic()
tree = et.parse(script_path)
use_tag = tree.getroot().find('use')
aircraft_name = use_tag.attrib['aircraft']
aircraft_path = self.sandbox.path_to_jsbsim_file(
'aircraft', aircraft_name)
aircraft_tree = et.parse(
os.path.join(aircraft_path, aircraft_name + '.xml'))
total_fuel_quantity = 0.0
total_oxidizer_quantity = 0.0
for tank in aircraft_tree.findall('propulsion/tank'):
contents = float(tank.find('contents').text)
if tank.attrib['type'] == "FUEL":
total_fuel_quantity += contents
elif tank.attrib['type'] == 'OXIDIZER':
total_oxidizer_quantity += contents
self.assertAlmostEqual(fdm['propulsion/total-fuel-lbs'],
total_fuel_quantity)
self.assertAlmostEqual(fdm['propulsion/total-oxidizer-lbs'],
total_oxidizer_quantity)
def test_gust_reset(self):
fdm = CreateFDM(self.sandbox)
fdm.load_script(self.sandbox.path_to_jsbsim_file('scripts',
'c172_cruise_8K.xml'))
fdm['simulation/randomseed'] = 0.0
fdm.set_output_directive(self.sandbox.path_to_jsbsim_file('tests', 'output.xml'))
fdm.run_ic()
ExecuteUntil(fdm, 15.5)
ref = pd.read_csv('output.csv', index_col=0)
fdm['simulation/randomseed'] = 0.0
fdm.reset_to_initial_conditions(1)
ExecuteUntil(fdm, 15.5)
current = pd.read_csv('output_0.csv', index_col=0)
# Check the data are matching i.e. the time steps are the same between
# the two data sets and that the output data are also the same.
self.assertTrue(isDataMatching(ref, current))
# Find all the data that are differing by more than 1E-8 between the
# two data sets.
diff = FindDifferences(ref, current, 1E-8)
self.longMessage = True
self.assertEqual(len(diff), 0, msg='\n'+diff.to_string())
def testDebugLvl(self):
fdm = CreateFDM(self.sandbox)
fdm.load_script(self.sandbox.path_to_jsbsim_file('scripts',
'ball_orbit.xml'))
fdm.run_ic()
ExecuteUntil(fdm, 1000.)
ref = pd.read_csv('BallOut.csv', index_col=0)
del fdm
os.environ["JSBSIM_DEBUG"] = str(0)
fdm = CreateFDM(self.sandbox)
fdm.load_script(self.sandbox.path_to_jsbsim_file('scripts',
'ball_orbit.xml'))
fdm.run_ic()
ExecuteUntil(fdm, 1000.)
current = pd.read_csv('BallOut.csv', index_col=0)
# Check the data are matching i.e. the time steps are the same between
# the two data sets and that the output data are also the same.
self.assertTrue(isDataMatching(ref, current))
# Find all the data that are differing by more than 1E-8 between the
# two data sets.
diff = FindDifferences(ref, current, 1E-8)
self.longMessage = True
self.assertEqual(len(diff), 0, msg='\n'+diff.to_string())
def Compare(self, section):
# Rerun the script with the modified aircraft definition
self.sandbox.delete_csv_files()
fdm = CreateFDM(self.sandbox)
# We need to tell JSBSim that the aircraft definition is located in the
# directory build/.../aircraft
fdm.set_aircraft_path('aircraft')
fdm.set_output_directive(self.sandbox.path_to_jsbsim_file('tests',
'output.xml'))
fdm.load_script(self.script)
fdm['simulation/randomseed'] = 0.0
fdm.run_ic()
ExecuteUntil(fdm, 50.0)
mod = pd.read_csv('output.csv', index_col=0)
# Check the data are matching i.e. the time steps are the same between
# the two data sets and that the output data are also the same.
self.assertTrue(isDataMatching(self.ref, mod))
# Whether the data is read from the aircraft definition file or from an
# external file, the results shall be exactly identical. Hence the
# precision set to 0.0.
diff = FindDifferences(self.ref, mod, 0.0)
self.assertEqual(len(diff), 0,
msg='\nTesting section "'+section+'"\n'+diff.to_string())
def test_wind_frame(self):
script_path = self.sandbox.path_to_jsbsim_file('scripts',
'ball_chute.xml')
fdm = CreateFDM(self.sandbox)
fdm.load_script(script_path)
fdm.run_ic()
self.assertAlmostEqual(fdm['external_reactions/parachute/location-x-in'],
12.0)
self.assertAlmostEqual(fdm['external_reactions/parachute/location-y-in'],
0.0)
self.assertAlmostEqual(fdm['external_reactions/parachute/location-z-in'],
0.0)
self.assertAlmostEqual(fdm['external_reactions/parachute/x'], -1.0)
self.assertAlmostEqual(fdm['external_reactions/parachute/y'], 0.0)
self.assertAlmostEqual(fdm['external_reactions/parachute/z'], 0.0)
while fdm.run():
Tw2b = fdm.get_auxiliary().get_Tw2b()
mag = fdm['aero/qbar-psf'] * fdm['fcs/parachute_reef_pos_norm']*20.0
f = Tw2b * np.mat([-1.0, 0.0, 0.0]).T * mag
self.assertAlmostEqual(fdm['forces/fbx-external-lbs'], f[0, 0])
self.assertAlmostEqual(fdm['forces/fby-external-lbs'], f[1, 0])
self.assertAlmostEqual(fdm['forces/fbz-external-lbs'], f[2, 0])
m = np.cross(self.getLeverArm(fdm,'parachute'),
np.array([f[0,0], f[1,0], f[2, 0]]))
self.assertAlmostEqual(fdm['moments/l-external-lbsft'], m[0])
self.assertAlmostEqual(fdm['moments/m-external-lbsft'], m[1])
self.assertAlmostEqual(fdm['moments/n-external-lbsft'], m[2])
def test_fuel_tanks_inertia(self):
script_path = self.sandbox.path_to_jsbsim_file('scripts', 'c1722.xml')
# The aircraft c172x does not contain an <inertia_factor> tag so we
# need to add one.
tree, aircraft_name, b = CopyAircraftDef(script_path, self.sandbox)
tank_tag = tree.getroot().find('propulsion/tank')
inertia_factor = et.SubElement(tank_tag, 'inertia_factor')
inertia_factor.text = '1.0'
tree.write(self.sandbox('aircraft', aircraft_name,
aircraft_name+'.xml'))
fdm = CreateFDM(self.sandbox)
fdm.set_aircraft_path('aircraft')
fdm.load_script(script_path)
fdm.run_ic()
contents0 = fdm['propulsion/tank/contents-lbs']
ixx0 = fdm['propulsion/tank/local-ixx-slug_ft2']
iyy0 = fdm['propulsion/tank/local-iyy-slug_ft2']
izz0 = fdm['propulsion/tank/local-izz-slug_ft2']
# Remove half of the tank contents and check that the inertias are
# updated accordingly
fdm['propulsion/tank/contents-lbs'] = 0.5*contents0
contents = fdm['propulsion/tank/contents-lbs']
ixx = fdm['propulsion/tank/local-ixx-slug_ft2']
iyy = fdm['propulsion/tank/local-iyy-slug_ft2']
izz = fdm['propulsion/tank/local-izz-slug_ft2']
self.assertAlmostEqual(contents, 0.5*contents0, delta=1E-7,
msg="The tank content (%f lbs) should be %f lbs" % (contents, 0.5*contents0))
self.assertAlmostEqual(ixx, 0.5*ixx0, delta=1E-7,
msg="The tank inertia Ixx (%f slug*ft^2) should be %f slug*ft^2" % (ixx, 0.5*ixx0))
self.assertAlmostEqual(iyy, 0.5*iyy0, delta=1E-7,
msg="The tank inertia Iyy (%f slug*ft^2) should be %f slug*ft^2" % (iyy, 0.5*iyy0))
self.assertAlmostEqual(izz, 0.5*izz0, delta=1E-7,
msg="The tank inertia Izz (%f slug*ft^2) should be %f slug*ft^2" % (izz, 0.5*izz0))
# Execute the script and check that the fuel inertias have been updated
# along with the consumption.
ExecuteUntil(fdm, 200.0)
contents = fdm['propulsion/tank/contents-lbs']
ixx = fdm['propulsion/tank/local-ixx-slug_ft2']
iyy = fdm['propulsion/tank/local-iyy-slug_ft2']
izz = fdm['propulsion/tank/local-izz-slug_ft2']
contents_ratio = contents / contents0
ixx_ratio = ixx / ixx0
iyy_ratio = iyy / iyy0
izz_ratio = izz / izz0
self.assertAlmostEqual(contents_ratio, ixx_ratio, delta=1E-7,
msg="Ixx does not vary as the tank content does\nIxx ratio=%f\nContents ratio=%f" % (ixx_ratio, contents_ratio))
self.assertAlmostEqual(contents_ratio, iyy_ratio, delta=1E-7,
msg="Iyy does not vary as the tank content does\nIyy ratio=%f\nContents ratio=%f" % (iyy_ratio, contents_ratio))
self.assertAlmostEqual(contents_ratio, izz_ratio, delta=1E-7,
msg="Izz does not vary as the tank content does\nIzz ratio=%f\nContents ratio=%f" % (izz_ratio, contents_ratio))
def test_no_input(self):
fdm = CreateFDM(self.sandbox)
fdm.load_script(self.script_path)
fdm.run_ic()
fdm.hold()
with self.assertRaises(socket.error):
TelnetInterface(fdm, 5., 1137)
def test_no_output(self):
fdm = CreateFDM(self.sandbox)
fdm.load_script(self.script_path)
fdm.run_ic()
ExecuteUntil(fdm, 10.)
self.assertFalse(self.sandbox.exists('output.csv'),
msg="Results have unexpectedly been written to 'output.csv'")
def test_no_input(self):
fdm = CreateFDM(self.sandbox)
fdm.load_script(self.script_path)
fdm.run_ic()
fdm.hold()
with self.assertRaises(socket.error):
TelnetInterface(fdm, 5., 1137)
def test_fuel_tanks_inertia(self):
script_path = self.sandbox.path_to_jsbsim_file('scripts', 'c1722.xml')
# The aircraft c172x does not contain an <inertia_factor> tag so we need
# to add one.
tree, aircraft_name, b = CopyAircraftDef(script_path, self.sandbox)
tank_tag = tree.getroot().find('./propulsion/tank')
inertia_factor = et.SubElement(tank_tag, 'inertia_factor')
inertia_factor.text = '1.0'
tree.write(self.sandbox('aircraft', aircraft_name, aircraft_name+'.xml'))
fdm = CreateFDM(self.sandbox)
fdm.set_aircraft_path('aircraft')
fdm.load_script(script_path)
fdm.run_ic()
contents0 = fdm.get_property_value('propulsion/tank/contents-lbs')
ixx0 = fdm.get_property_value('propulsion/tank/local-ixx-slug_ft2')
iyy0 = fdm.get_property_value('propulsion/tank/local-iyy-slug_ft2')
izz0 = fdm.get_property_value('propulsion/tank/local-izz-slug_ft2')
# Remove half of the tank contents and check that the inertias are
# updated accordingly
fdm.set_property_value('propulsion/tank/contents-lbs', 0.5*contents0)
contents = fdm.get_property_value('propulsion/tank/contents-lbs')
ixx = fdm.get_property_value('propulsion/tank/local-ixx-slug_ft2')
iyy = fdm.get_property_value('propulsion/tank/local-iyy-slug_ft2')
izz = fdm.get_property_value('propulsion/tank/local-izz-slug_ft2')
self.assertTrue(abs(contents-0.5*contents0) < 1E-7,
msg="The tank content (%f lbs) should be %f lbs" % (contents, 0.5*contents0))
self.assertTrue(abs(ixx-0.5*ixx0) < 1E-7,
msg="The tank inertia Ixx (%f slug*ft^2) should be %f slug*ft^2" % (ixx, 0.5*ixx0))
self.assertTrue(abs(iyy-0.5*iyy0) < 1E-7,
msg="The tank inertia Iyy (%f slug*ft^2) should be %f slug*ft^2" % (iyy, 0.5*iyy0))
self.assertTrue(abs(izz-0.5*izz0) < 1E-7,
msg="The tank inertia Izz (%f slug*ft^2) should be %f slug*ft^2" % (izz, 0.5*izz0))
# Execute the script and check that the fuel inertias have been updated
# along with the consumption.
ExecuteUntil(fdm, 200.0)
contents = fdm.get_property_value('propulsion/tank/contents-lbs')
ixx = fdm.get_property_value('propulsion/tank/local-ixx-slug_ft2')
iyy = fdm.get_property_value('propulsion/tank/local-iyy-slug_ft2')
izz = fdm.get_property_value('propulsion/tank/local-izz-slug_ft2')
contents_ratio = contents / contents0
ixx_ratio = ixx / ixx0
iyy_ratio = iyy / iyy0
izz_ratio = izz / izz0
self.assertTrue(abs(contents_ratio - ixx_ratio) < 1E-7,
msg="Ixx does not vary as the tank content does\nIxx ratio=%f\nContents ratio=%f" % (ixx_ratio, contents_ratio))
self.assertTrue(abs(contents_ratio - iyy_ratio) < 1E-7,
msg="Iyy does not vary as the tank content does\nIyy ratio=%f\nContents ratio=%f" % (iyy_ratio, contents_ratio))
self.assertTrue(abs(contents_ratio - izz_ratio) < 1E-7,
msg="Izz does not vary as the tank content does\nIzz ratio=%f\nContents ratio=%f" % (izz_ratio, contents_ratio))
def testChannelRate(self):
os.environ['JSBSIM_DEBUG'] = str(0)
fdm = CreateFDM(self.sandbox)
fdm.load_script(
self.sandbox.path_to_jsbsim_file('scripts',
'systems-rate-test-0.xml'))
fdm.run_ic()
while fdm['simulation/sim-time-sec'] < 30:
fdm.run()
self.assertEqual(fdm['simulation/frame'], fdm['tests/rate-1'])
self.assertEqual(int(fdm['simulation/frame'] / 4),
fdm['tests/rate-4'])
self.assertEqual(fdm['simulation/sim-time-sec'],
fdm['tests/rate-1-dt-sum'])
self.assertAlmostEqual(
fdm['simulation/dt'] * fdm['tests/rate-4'] * 4,
fdm['tests/rate-4-dt-sum'])
self.assertEqual(fdm['simulation/dt'], fdm['tests/rate-1-dt'])
self.assertEqual(fdm['simulation/dt'] * 4, fdm['tests/rate-4-dt'])
try:
fdm['simulation/do_simple_trim'] = 1
except RuntimeError as e:
# The trim cannot succeed. Just make sure that the raised exception
# is due to the trim failure otherwise rethrow.
if e.args[0] != 'Trim Failed':
raise
while fdm['simulation/sim-time-sec'] < 40:
self.assertEqual(fdm['simulation/frame'], fdm['tests/rate-1'])
self.assertEqual(int(fdm['simulation/frame'] / 4),
fdm['tests/rate-4'])
self.assertEqual(fdm['simulation/sim-time-sec'],
fdm['tests/rate-1-dt-sum'])
self.assertAlmostEqual(
fdm['simulation/dt'] * fdm['tests/rate-4'] * 4,
fdm['tests/rate-4-dt-sum'])
fdm.run()
fdm.reset_to_initial_conditions(1)
tf = fdm['tests/rate-1-dt-sum']
xtraFrames = fdm['simulation/frame'] % 4
while fdm['simulation/sim-time-sec'] < 30:
fdm.run()
self.assertEqual(fdm['simulation/frame'], fdm['tests/rate-1'])
self.assertEqual(int((fdm['simulation/frame'] - xtraFrames) / 4),
fdm['tests/rate-4'])
self.assertAlmostEqual(fdm['simulation/sim-time-sec'],
fdm['tests/rate-1-dt-sum'] - tf)
self.assertAlmostEqual(
fdm['simulation/dt'] * fdm['tests/rate-4'] * 4,
fdm['tests/rate-4-dt-sum'])
def testSteadyFlight(self):
script_name = 'c1722.xml'
script_path = self.sandbox.path_to_jsbsim_file('scripts', script_name)
self.AddAccelerometersToAircraft(script_path)
fdm = CreateFDM(self.sandbox)
fdm.set_aircraft_path('aircraft')
fdm.load_script(script_path)
# Switch the accel on
fdm['fcs/accelerometer/on'] = 1.0
# Use the standard gravity (i.e. GM/r^2)
fdm['simulation/gravity-model'] = 0
# Select an orientation such that frame transformations simplify
fdm['ic/psi-true-rad'] = 0.0
fdm.run_ic()
ExecuteUntil(fdm, 0.1)
fdm['simulation/do_simple_trim'] = 1
r = fdm['position/radius-to-vehicle-ft']
pitch = fdm['attitude/theta-rad']
roll = fdm['attitude/phi-rad']
latitude = fdm['position/lat-gc-rad']
g = fdm['accelerations/gravity-ft_sec2']
omega = 0.00007292115 # Earth rotation rate in rad/sec
fc = r * math.cos(latitude) * omega * omega # Centrifugal force
uvw = np.array(fdm.get_propagate().get_uvw().T)[0]
Omega = omega * np.array([
math.cos(pitch - latitude),
math.sin(pitch - latitude) * math.sin(roll),
math.sin(pitch - latitude) * math.cos(roll)
])
# Compute the acceleration measured by the accelerometer as the sum of
# the gravity and the centrifugal and Coriolis forces.
fa_yz = (fc * math.cos(latitude - pitch) - g * math.cos(pitch))
fa = np.array([(fc * math.sin(latitude - pitch) + g * math.sin(pitch)),
fa_yz * math.sin(roll), fa_yz * math.cos(roll)
]) + np.cross(2.0 * Omega, uvw)
# After the trim we are close to the equilibrium but there remains a
# small residual that we have to take the bias into account
fax = fa[0] + fdm['accelerations/udot-ft_sec2']
fay = fa[1] + fdm['accelerations/vdot-ft_sec2']
faz = fa[2] + fdm['accelerations/wdot-ft_sec2']
# Deltas are relaxed because the tolerances of the trimming algorithm
# are quite relaxed themselves.
self.assertAlmostEqual(fdm['fcs/accelerometer/X'], fax, delta=1E-6)
self.assertAlmostEqual(fdm['fcs/accelerometer/Y'], fay, delta=1E-4)
self.assertAlmostEqual(fdm['fcs/accelerometer/Z'], faz, delta=1E-5)
del fdm
def test_grain_tanks_content(self):
script_path = self.sandbox.path_to_jsbsim_file('scripts', 'J2460.xml')
tree, aircraft_name, b = CopyAircraftDef(script_path, self.sandbox)
id = 0
for tank in tree.getroot().findall('propulsion/tank'):
grain_config = tank.find('grain_config')
if grain_config and grain_config.attrib['type'] == 'CYLINDRICAL':
break
++id
capacity = float(tank.find('capacity').text)
tank.find('contents').text = str(0.5 * capacity)
tree.write(
self.sandbox('aircraft', aircraft_name, aircraft_name + '.xml'))
radius_tag = tank.find('radius')
radius = float(radius_tag.text)
if 'unit' in radius_tag.attrib and radius_tag.attrib['unit'] == 'IN':
radius /= 12.0
bore_diameter_tag = tank.find('grain_config/bore_diameter')
bore_radius = 0.5 * float(bore_diameter_tag.text)
if 'unit' in bore_diameter_tag.attrib and bore_diameter_tag.attrib[
'unit'] == 'IN':
bore_radius /= 12.0
fdm = CreateFDM(self.sandbox)
fdm.set_aircraft_path('aircraft')
fdm.load_script(script_path)
fdm.run_ic()
tank_name = 'propulsion/tank[%g]' % (id, )
self.assertAlmostEqual(fdm[tank_name + '/contents-lbs'],
0.5 * capacity)
fdm['propulsion/tank/contents-lbs'] = capacity
mass = capacity / 32.174049 # Converting lbs to slugs
ixx = 0.5 * mass * (radius * radius + bore_radius * bore_radius)
self.assertAlmostEqual(fdm[tank_name + 'local-ixx-slug_ft2'], ixx)
del fdm
tank.find('contents').text = '0.0'
tree.write(
self.sandbox('aircraft', aircraft_name, aircraft_name + '.xml'))
fdm = CreateFDM(self.sandbox)
fdm.set_aircraft_path('aircraft')
fdm.load_script(script_path)
fdm.run_ic()
self.assertAlmostEqual(fdm[tank_name + '/contents-lbs'], 0.0)
fdm['propulsion/tank/contents-lbs'] = capacity
def testEnginePowerVC(self):
fdm = CreateFDM(self.sandbox)
fdm.load_script(
self.sandbox.path_to_jsbsim_file('scripts', 'L4102.xml'))
fdm.run_ic()
pm = fdm.get_property_manager()
self.assertTrue(pm.hasNode('propulsion/engine[0]/EnginePowerVC'))
self.assertTrue(pm.hasNode('propulsion/engine[1]/EnginePowerVC'))
while fdm.run():
self.assertAlmostEqual(fdm['propulsion/engine[0]/EnginePowerVC'],
fdm['propulsion/engine[1]/EnginePowerVC'])
def testSteadyFlight(self):
script_name = 'c1722.xml'
script_path = self.sandbox.path_to_jsbsim_file('scripts', script_name)
self.AddAccelerometersToAircraft(script_path)
fdm = CreateFDM(self.sandbox)
fdm.set_aircraft_path('aircraft')
fdm.load_script(script_path)
# Switch the accel on
fdm['fcs/accelerometer/on'] = 1.0
# Use the standard gravity (i.e. GM/r^2)
fdm['simulation/gravity-model'] = 0
# Select an orientation such that frame transformations simplify
fdm['ic/psi-true-rad'] = 0.0
fdm.run_ic()
ExecuteUntil(fdm, 0.1)
fdm['simulation/do_simple_trim'] = 1
r = fdm['position/radius-to-vehicle-ft']
pitch = fdm['attitude/theta-rad']
roll = fdm['attitude/phi-rad']
latitude = fdm['position/lat-gc-rad']
g = fdm['accelerations/gravity-ft_sec2']
omega = 0.00007292115 # Earth rotation rate in rad/sec
fc = r * math.cos(latitude) * omega * omega # Centrifugal force
uvw = np.array(fdm.get_propagate().get_uvw().T)[0]
Omega = omega * np.array([math.cos(pitch - latitude),
math.sin(pitch - latitude) * math.sin(roll),
math.sin(pitch - latitude) * math.cos(roll)])
# Compute the acceleration measured by the accelerometer as the sum of
# the gravity and the centrifugal and Coriolis forces.
fa_yz = (fc * math.cos(latitude - pitch) - g * math.cos(pitch))
fa = np.array([(fc * math.sin(latitude - pitch) + g * math.sin(pitch)),
fa_yz * math.sin(roll),
fa_yz * math.cos(roll)]) + np.cross(2.0*Omega, uvw)
# After the trim we are close to the equilibrium but there remains a
# small residual that we have to take the bias into account
fax = fa[0] + fdm['accelerations/udot-ft_sec2']
fay = fa[1] + fdm['accelerations/vdot-ft_sec2']
faz = fa[2] + fdm['accelerations/wdot-ft_sec2']
# Deltas are relaxed because the tolerances of the trimming algorithm
# are quite relaxed themselves.
self.assertAlmostEqual(fdm['fcs/accelerometer/X'], fax, delta=1E-6)
self.assertAlmostEqual(fdm['fcs/accelerometer/Y'], fay, delta=1E-4)
self.assertAlmostEqual(fdm['fcs/accelerometer/Z'], faz, delta=1E-5)
del fdm
def testEnginePowerVC(self):
fdm = CreateFDM(self.sandbox)
fdm.load_script(self.sandbox.path_to_jsbsim_file('scripts',
'L4102.xml'))
fdm.run_ic()
pm = fdm.get_property_manager()
self.assertTrue(pm.hasNode('propulsion/engine[0]/EnginePowerVC'))
self.assertTrue(pm.hasNode('propulsion/engine[1]/EnginePowerVC'))
while fdm.run():
self.assertAlmostEqual(fdm['propulsion/engine[0]/EnginePowerVC'],
fdm['propulsion/engine[1]/EnginePowerVC'])
def initFDM(self):
fdm = CreateFDM(self.sandbox)
script_path = self.sandbox.path_to_jsbsim_file('scripts',
'cannonball.xml')
fdm.load_script(script_path)
fdm['simulation/integrator/rate/rotational'] = 5
fdm['simulation/integrator/rate/translational'] = 5
fdm['simulation/integrator/position/rotational'] = 5
fdm['simulation/integrator/position/translational'] = 5
fdm.run_ic()
fdm.set_dt(0.05)
return fdm
def testEnginePowerVC(self):
# Check that the same results are obtained whether the engine power
# velocity correction is given in a <table> or <function>
fdm = CreateFDM(self.sandbox)
fdm.load_script(self.sandbox.path_to_jsbsim_file('scripts',
'L4102.xml'))
fdm.run_ic()
while fdm.run():
pass
del fdm
ref = pd.read_csv('L410.csv', index_col=0)
tree = et.parse(self.sandbox.path_to_jsbsim_file('engine',
'engtm601.xml'))
# Modify the engine definition to use a <function> rather than a
# <table> component.
root = tree.getroot()
engPowVC_tag = root.find("table/[@name='EnginePowerVC']")
root.remove(engPowVC_tag)
del engPowVC_tag.attrib['name']
func_engPowVC = et.SubElement(root, 'function')
func_engPowVC.attrib['name'] = 'EnginePowerVC'
func_engPowVC.append(engPowVC_tag)
tree.write('engtm601.xml')
# Copy the propeller file.
shutil.copy(self.sandbox.path_to_jsbsim_file('engine', 'vrtule2.xml'),
'.')
self.sandbox.delete_csv_files()
fdm = CreateFDM(self.sandbox)
fdm.set_engine_path('.')
fdm.load_script(self.sandbox.path_to_jsbsim_file('scripts',
'L4102.xml'))
fdm.run_ic()
while fdm.run():
pass
current = pd.read_csv('L410.csv', index_col=0)
# Check the data are matching i.e. the time steps are the same between
# the two data sets and that the output data are also the same.
self.assertTrue(isDataMatching(ref, current))
# Find all the data that are differing by more than 1E-5 between the
# two data sets.
diff = FindDifferences(ref, current, 0.0)
self.longMessage = True
self.assertEqual(len(diff), 0, msg='\n'+diff.to_string())
def initFDM(self):
fdm = CreateFDM(self.sandbox)
script_path = self.sandbox.path_to_jsbsim_file('scripts',
'cannonball.xml')
fdm.load_script(script_path)
fdm['simulation/integrator/rate/rotational'] = 5
fdm['simulation/integrator/rate/translational'] = 5
fdm['simulation/integrator/position/rotational'] = 5
fdm['simulation/integrator/position/translational'] = 5
fdm.run_ic()
fdm.set_dt(0.05)
return fdm
def testChannelRate(self):
os.environ['JSBSIM_DEBUG'] = str(0)
fdm = CreateFDM(self.sandbox)
fdm.load_script(
self.sandbox.path_to_jsbsim_file('scripts',
'systems-rate-test-0.xml'))
fdm.run_ic()
while fdm['simulation/sim-time-sec'] < 30:
fdm.run()
self.assertEqual(fdm['simulation/frame'], fdm['tests/rate-1'])
self.assertEqual(int(fdm['simulation/frame'] / 4),
fdm['tests/rate-4'])
self.assertEqual(fdm['simulation/sim-time-sec'],
fdm['tests/rate-1-dt-sum'])
self.assertAlmostEqual(
fdm['simulation/dt'] * fdm['tests/rate-4'] * 4,
fdm['tests/rate-4-dt-sum'])
self.assertEqual(fdm['simulation/dt'], fdm['tests/rate-1-dt'])
self.assertEqual(fdm['simulation/dt'] * 4, fdm['tests/rate-4-dt'])
# Trigger the trimming and check that it fails (i.e. it raises an
# exception TrimFailureError)
with self.assertRaises(TrimFailureError):
fdm['simulation/do_simple_trim'] = 1
while fdm['simulation/sim-time-sec'] < 40:
self.assertEqual(fdm['simulation/frame'], fdm['tests/rate-1'])
self.assertEqual(int(fdm['simulation/frame'] / 4),
fdm['tests/rate-4'])
self.assertEqual(fdm['simulation/sim-time-sec'],
fdm['tests/rate-1-dt-sum'])
self.assertAlmostEqual(
fdm['simulation/dt'] * fdm['tests/rate-4'] * 4,
fdm['tests/rate-4-dt-sum'])
fdm.run()
fdm.reset_to_initial_conditions(1)
tf = fdm['tests/rate-1-dt-sum']
xtraFrames = fdm['simulation/frame'] % 4
while fdm['simulation/sim-time-sec'] < 30:
fdm.run()
self.assertEqual(fdm['simulation/frame'], fdm['tests/rate-1'])
self.assertEqual(int((fdm['simulation/frame'] - xtraFrames) / 4),
fdm['tests/rate-4'])
self.assertAlmostEqual(fdm['simulation/sim-time-sec'],
fdm['tests/rate-1-dt-sum'] - tf)
self.assertAlmostEqual(
fdm['simulation/dt'] * fdm['tests/rate-4'] * 4,
fdm['tests/rate-4-dt-sum'])
def test_grain_tanks_content(self):
script_path = self.sandbox.path_to_jsbsim_file('scripts', 'J2460.xml')
tree, aircraft_name, b = CopyAircraftDef(script_path, self.sandbox)
id = 0
for tank in tree.getroot().findall('propulsion/tank'):
grain_config = tank.find('grain_config')
if grain_config and grain_config.attrib['type'] == 'CYLINDRICAL':
break
++id
capacity = float(tank.find('capacity').text)
tank.find('contents').text = str(0.5*capacity)
tree.write(self.sandbox('aircraft', aircraft_name,
aircraft_name+'.xml'))
radius_tag = tank.find('radius')
radius = float(radius_tag.text)
if 'unit' in radius_tag.attrib and radius_tag.attrib['unit'] == 'IN':
radius /= 12.0
bore_diameter_tag = tank.find('grain_config/bore_diameter')
bore_radius = 0.5*float(bore_diameter_tag.text)
if 'unit' in bore_diameter_tag.attrib and bore_diameter_tag.attrib['unit'] == 'IN':
bore_radius /= 12.0
fdm = CreateFDM(self.sandbox)
fdm.set_aircraft_path('aircraft')
fdm.load_script(script_path)
fdm.run_ic()
tank_name = 'propulsion/tank[%g]' % (id,)
self.assertAlmostEqual(fdm[tank_name+'/contents-lbs'], 0.5*capacity)
fdm['propulsion/tank/contents-lbs'] = capacity
mass = capacity / 32.174049 # Converting lbs to slugs
ixx = 0.5 * mass * (radius * radius + bore_radius*bore_radius)
self.assertAlmostEqual(fdm[tank_name+'local-ixx-slug_ft2'], ixx)
del fdm
tank.find('contents').text = '0.0'
tree.write(self.sandbox('aircraft', aircraft_name,
aircraft_name+'.xml'))
fdm = CreateFDM(self.sandbox)
fdm.set_aircraft_path('aircraft')
fdm.load_script(script_path)
fdm.run_ic()
self.assertAlmostEqual(fdm[tank_name+'/contents-lbs'], 0.0)
fdm['propulsion/tank/contents-lbs'] = capacity
def test_script_input(self):
tree = et.parse(self.sandbox.elude(self.script_path))
input_tag = et.SubElement(tree.getroot(), 'input')
input_tag.attrib['port'] = '1138'
tree.write(self.sandbox('c1722_1.xml'))
fdm = CreateFDM(self.sandbox)
fdm.load_script('c1722_1.xml')
fdm.run_ic()
fdm.hold()
tn = TelnetInterface(fdm, 5., 1138)
self.sanityCheck(tn)
def test_script_input(self):
tree = et.parse(self.script_path)
input_tag = et.SubElement(tree.getroot(), 'input')
input_tag.attrib['port'] = '1138'
tree.write('c1722_1.xml')
fdm = CreateFDM(self.sandbox)
fdm.load_script('c1722_1.xml')
fdm.run_ic()
fdm.hold()
tn = TelnetInterface(fdm, 5., 1138)
self.sanityCheck(tn)
def test_output_from_file(self):
tree = et.parse(self.sandbox.elude(self.script_path))
output_tag = et.SubElement(tree.getroot(), 'output')
output_tag.attrib['file'] = self.sandbox.elude(self.sandbox.path_to_jsbsim_file('tests', 'output.xml'))
tree.write(self.sandbox('c1722_0.xml'))
fdm = CreateFDM(self.sandbox)
fdm.load_script('c1722_0.xml')
fdm.run_ic()
ExecuteUntil(fdm, 10.)
self.assertTrue(self.sandbox.exists('output.csv'),
msg="The file 'output.csv' has not been created")
def test_moment(self):
script_path = self.sandbox.path_to_jsbsim_file('scripts',
'ball_chute.xml')
tree, aircraft_name, aircraft_path = CopyAircraftDef(
script_path, self.sandbox)
extReact_element = tree.getroot().find('external_reactions')
moment_element = et.SubElement(extReact_element, 'moment')
moment_element.attrib['name'] = 'parachute'
moment_element.attrib['frame'] = 'WIND'
direction_element = et.SubElement(moment_element, 'direction')
x_element = et.SubElement(direction_element, 'x')
x_element.text = '0.2'
y_element = et.SubElement(direction_element, 'y')
y_element.text = '0.0'
z_element = et.SubElement(direction_element, 'z')
z_element.text = '-1.5'
tree.write(
self.sandbox('aircraft', aircraft_name, aircraft_name + '.xml'))
fdm = CreateFDM(self.sandbox)
fdm.set_aircraft_path('aircraft')
fdm.load_script(script_path)
fdm.run_ic()
mDir = np.array([0.2, 0.0, -1.5])
mDir /= np.linalg.norm(mDir)
self.assertAlmostEqual(fdm['external_reactions/parachute/l'], mDir[0])
self.assertAlmostEqual(fdm['external_reactions/parachute/m'], mDir[1])
self.assertAlmostEqual(fdm['external_reactions/parachute/n'], mDir[2])
fdm['external_reactions/parachute/magnitude-lbsft'] = -3.5
while fdm.run():
Tw2b = fdm.get_auxiliary().get_Tw2b()
mag = fdm['aero/qbar-psf'] * fdm[
'fcs/parachute_reef_pos_norm'] * 20.0
f = Tw2b * np.mat([-1.0, 0.0, 0.0]).T * mag
self.assertAlmostEqual(fdm['forces/fbx-external-lbs'], f[0, 0])
self.assertAlmostEqual(fdm['forces/fby-external-lbs'], f[1, 0])
self.assertAlmostEqual(fdm['forces/fbz-external-lbs'], f[2, 0])
m = -3.5 * Tw2b * np.mat(mDir).T
fm = np.cross(self.getLeverArm(fdm, 'parachute'),
np.array([f[0, 0], f[1, 0], f[2, 0]]))
self.assertAlmostEqual(fdm['moments/l-external-lbsft'],
m[0, 0] + fm[0])
self.assertAlmostEqual(fdm['moments/m-external-lbsft'],
m[1, 0] + fm[1])
self.assertAlmostEqual(fdm['moments/n-external-lbsft'],
m[2, 0] + fm[2])
def testChannelRate(self):
os.environ['JSBSIM_DEBUG'] = str(0)
fdm = CreateFDM(self.sandbox)
fdm.load_script(self.sandbox.path_to_jsbsim_file('scripts',
'systems-rate-test-0.xml'))
fdm.run_ic()
while fdm['simulation/sim-time-sec'] < 30:
fdm.run()
self.assertEqual(fdm['simulation/frame'], fdm['tests/rate-1'])
self.assertEqual(int(fdm['simulation/frame']/4),
fdm['tests/rate-4'])
self.assertEqual(fdm['simulation/sim-time-sec'],
fdm['tests/rate-1-dt-sum'])
self.assertAlmostEqual(fdm['simulation/dt']*fdm['tests/rate-4']*4,
fdm['tests/rate-4-dt-sum'])
self.assertEqual(fdm['simulation/dt'], fdm['tests/rate-1-dt'])
self.assertEqual(fdm['simulation/dt']*4, fdm['tests/rate-4-dt'])
try:
fdm['simulation/do_simple_trim'] = 1
except RuntimeError as e:
# The trim cannot succeed. Just make sure that the raised exception
# is due to the trim failure otherwise rethrow.
if e.args[0] != 'Trim Failed':
raise
while fdm['simulation/sim-time-sec'] < 40:
self.assertEqual(fdm['simulation/frame'], fdm['tests/rate-1'])
self.assertEqual(int(fdm['simulation/frame']/4),
fdm['tests/rate-4'])
self.assertEqual(fdm['simulation/sim-time-sec'],
fdm['tests/rate-1-dt-sum'])
self.assertAlmostEqual(fdm['simulation/dt']*fdm['tests/rate-4']*4,
fdm['tests/rate-4-dt-sum'])
fdm.run()
fdm.reset_to_initial_conditions(1)
tf = fdm['tests/rate-1-dt-sum']
xtraFrames = fdm['simulation/frame'] % 4
while fdm['simulation/sim-time-sec'] < 30:
fdm.run()
self.assertEqual(fdm['simulation/frame'], fdm['tests/rate-1'])
self.assertEqual(int((fdm['simulation/frame']-xtraFrames)/4),
fdm['tests/rate-4'])
self.assertAlmostEqual(fdm['simulation/sim-time-sec'],
fdm['tests/rate-1-dt-sum']-tf)
self.assertAlmostEqual(fdm['simulation/dt']*fdm['tests/rate-4']*4,
fdm['tests/rate-4-dt-sum'])
def testTableWithIndexedVars(self):
tree = et.parse(
self.sandbox.path_to_jsbsim_file('engine', 'eng_PegasusXc.xml'))
# Define the function starter-max-power-W as a 'post' function
root = tree.getroot()
startPowFunc_tag = root.find(
"function/[@name='propulsion/engine[#]/starter-max-power-W']")
startPowFunc_tag.attrib['type'] = 'post'
max_tag = startPowFunc_tag.find('product/max')
diff_tag = max_tag.find('difference')
max_tag.remove(diff_tag)
table_tag = et.SubElement(max_tag, 'table')
table_tag.attrib['name'] = 'propulsion/engine[#]/starter-tabular-data'
indepVar_tag = et.SubElement(table_tag, 'independentVar')
indepVar_tag.attrib['lookup'] = 'row'
indepVar_tag.text = 'propulsion/engine[#]/engine-rpm'
tData_tag = et.SubElement(table_tag, 'tableData')
tData_tag.text = '0.0 1.0\n400.0 0.0'
tree.write('eng_PegasusXc.xml')
# Copy the propeller file.
shutil.copy(
self.sandbox.path_to_jsbsim_file('engine',
'prop_deHavilland5000.xml'), '.')
fdm = CreateFDM(self.sandbox)
fdm.set_engine_path('.')
fdm.load_script(
self.sandbox.path_to_jsbsim_file('scripts', 'Short_S23_1.xml'))
fdm.run_ic()
pm = fdm.get_property_manager()
self.assertTrue(pm.hasNode('propulsion/engine[0]/starter-max-power-W'))
self.assertTrue(pm.hasNode('propulsion/engine[1]/starter-max-power-W'))
self.assertTrue(pm.hasNode('propulsion/engine[2]/starter-max-power-W'))
self.assertTrue(pm.hasNode('propulsion/engine[3]/starter-max-power-W'))
while fdm.run():
rpm = [
fdm['propulsion/engine[0]/engine-rpm'],
fdm['propulsion/engine[1]/engine-rpm'],
fdm['propulsion/engine[2]/engine-rpm'],
fdm['propulsion/engine[3]/engine-rpm']
]
for i in xrange(4):
tabularData = max(0.0, 1.0 - rpm[i] / 400)
maxPower = tabularData * 498.941 * 0.10471976 * rpm[i]
self.assertAlmostEqual(
fdm['propulsion/engine[%d]/starter-max-power-W' % (i, )],
maxPower)
self.assertAlmostEqual(
fdm['propulsion/engine[%d]/starter-tabular-data' % (i, )],
tabularData)
def test_script_start_time_0(self):
script_name = 'ball_orbit.xml'
script_path = self.sandbox.path_to_jsbsim_file('scripts', script_name)
fdm = CreateFDM(self.sandbox)
fdm.load_script(script_path)
fdm.run_ic()
self.assertEqual(fdm['simulation/sim-time-sec'], 0.0)
ExecuteUntil(fdm, 5.0)
fdm.reset_to_initial_conditions(1)
self.assertEqual(fdm['simulation/sim-time-sec'], 0.0)
del fdm
def test_script_start_time_0(self):
script_name = 'ball_orbit.xml'
script_path = self.sandbox.path_to_jsbsim_file('scripts', script_name)
fdm = CreateFDM(self.sandbox)
fdm.load_script(script_path)
fdm.run_ic()
self.assertEqual(fdm.get_property_value('simulation/sim-time-sec'), 0.0)
ExecuteUntil(fdm, 5.0)
fdm.reset_to_initial_conditions(1)
self.assertEqual(fdm.get_property_value('simulation/sim-time-sec'), 0.0)
del fdm
def steerType(self, hasSteerPosDeg, hasSteeringAngle, hasCastered):
self.tree.write(self.sandbox('aircraft', self.aircraft_name,
self.aircraft_name+'.xml'))
fdm = CreateFDM(self.sandbox)
fdm.set_aircraft_path('aircraft')
fdm.load_script(self.script_path)
fdm.run_ic()
pm = fdm.get_property_manager()
self.assertTrue(pm.hasNode('fcs/steer-pos-deg') == hasSteerPosDeg)
self.assertTrue(pm.hasNode('gear/unit/steering-angle-deg')
== hasSteeringAngle)
self.assertTrue(pm.hasNode('gear/unit/castered') == hasCastered)
return fdm
def steerType(self, hasSteerPosDeg, hasSteeringAngle, hasCastered):
self.tree.write(self.sandbox('aircraft', self.aircraft_name,
self.aircraft_name+'.xml'))
fdm = CreateFDM(self.sandbox)
fdm.set_aircraft_path('aircraft')
fdm.load_script(self.script_path)
fdm.run_ic()
pm = fdm.get_property_manager()
self.assertTrue(pm.hasNode('fcs/steer-pos-deg') == hasSteerPosDeg)
self.assertTrue(pm.hasNode('gear/unit/steering-angle-deg')
== hasSteeringAngle)
self.assertTrue(pm.hasNode('gear/unit/castered') == hasCastered)
return fdm
def testSteadyFlight(self):
script_name = 'c1722.xml'
script_path = self.sandbox.path_to_jsbsim_file('scripts', script_name)
self.AddAccelerometersToAircraft(script_path)
fdm = CreateFDM(self.sandbox)
fdm.set_aircraft_path('aircraft')
fdm.load_script(script_path)
# Switch the accel on
fdm.set_property_value('fcs/accelerometer/on', 1.0)
# Use the standard gravity (i.e. GM/r^2)
fdm.set_property_value('simulation/gravity-model', 0)
# Simplifies the transformation to compare the accelerometer with the
# gravity
fdm.set_property_value('ic/psi-true-rad', 0.0)
fdm.run_ic()
while fdm.get_property_value('simulation/sim-time-sec') <= 0.5:
fdm.run()
fdm.set_property_value('simulation/do_simple_trim', 1)
ax = fdm.get_property_value('accelerations/udot-ft_sec2')
ay = fdm.get_property_value('accelerations/vdot-ft_sec2')
az = fdm.get_property_value('accelerations/wdot-ft_sec2')
g = fdm.get_property_value('accelerations/gravity-ft_sec2')
theta = fdm.get_property_value('attitude/theta-rad')
# There is a lag of one time step between the computations of the
# accelerations and the update of the accelerometer
fdm.run()
fax = fdm.get_property_value('fcs/accelerometer/X')
fay = fdm.get_property_value('fcs/accelerometer/Y')
faz = fdm.get_property_value('fcs/accelerometer/Z')
fax -= ax
fay -= ay
faz -= az
# Deltas are relaxed because the tolerances of the trimming algorithm
# are quite relaxed themselves.
self.assertAlmostEqual(faz / (g * math.cos(theta)), -1.0, delta=1E-5)
self.assertAlmostEqual(fax / (g * math.sin(theta)), 1.0, delta=1E-5)
self.assertAlmostEqual(math.sqrt(fax * fax + fay * fay + faz * faz) /
g,
1.0,
delta=1E-6)
del fdm
def test_output_from_file(self):
tree = et.parse(self.script_path)
output_tag = et.SubElement(tree.getroot(), 'output')
# Relative path from the aircraft directory to the output directive
# file
output_tag.attrib['file'] = os.path.join('..', '..', 'tests',
'output.xml')
tree.write('c1722_0.xml')
fdm = CreateFDM(self.sandbox)
fdm.load_script('c1722_0.xml')
fdm.run_ic()
ExecuteUntil(fdm, 10.)
self.assertTrue(self.sandbox.exists('output.csv'),
msg="The file 'output.csv' has not been created")
def LoadScript(self, tree, script_path, prop_output_to_CSV=[]):
# Make a local copy of files referenced by the script.
for element in list(tree.getroot()):
if 'file' in element.keys():
name = append_xml(element.attrib['file'])
name_with_path = os.path.join(os.path.dirname(script_path),
name)
if os.path.exists(name_with_path):
shutil.copy(name_with_path, name)
# Generate a CSV file to check that it is correctly initialized
# with the initial values
output_tag = et.SubElement(tree.getroot(), 'output')
output_tag.attrib['name'] = 'check_csv_values.csv'
output_tag.attrib['type'] = 'CSV'
output_tag.attrib['rate'] = '10'
position_tag = et.SubElement(output_tag, 'position')
position_tag.text = 'ON'
velocities_tag = et.SubElement(output_tag, 'velocities')
velocities_tag.text = 'ON'
for props in prop_output_to_CSV:
property_tag = et.SubElement(output_tag, 'property')
property_tag.text = props
f = os.path.split(script_path)[-1] # Script name
tree.write(f)
# Initialize the script
fdm = CreateFDM(self.sandbox)
self.assertTrue(fdm.load_script(f),
msg="Failed to load script %s" % (f,))
fdm.run_ic()
return (f, fdm)
def testOrbitCheckCase(self):
os.environ['JSBSIM_DEBUG'] = str(0)
fdm = CreateFDM(self.sandbox)
fdm.load_script(self.sandbox.path_to_jsbsim_file('scripts', 'ball_orbit.xml'))
fdm.run_ic()
while fdm.run():
pass
ref, current = Table(), Table()
ref.ReadCSV(self.sandbox.elude(self.sandbox.path_to_jsbsim_file('logged_data', 'BallOut.csv')))
current.ReadCSV(self.sandbox('BallOut.csv'))
diff = ref.compare(current)
self.longMessage = True
self.assertTrue(diff.empty(), msg='\n'+repr(diff))
def test_moment(self):
script_path = self.sandbox.path_to_jsbsim_file('scripts',
'ball_chute.xml')
tree, aircraft_name, aircraft_path = CopyAircraftDef(script_path,
self.sandbox)
extReact_element = tree.getroot().find('external_reactions')
moment_element = et.SubElement(extReact_element, 'moment')
moment_element.attrib['name'] = 'parachute'
moment_element.attrib['frame'] = 'WIND'
direction_element = et.SubElement(moment_element, 'direction')
x_element = et.SubElement(direction_element, 'x')
x_element.text = '0.2'
y_element = et.SubElement(direction_element, 'y')
y_element.text = '0.0'
z_element = et.SubElement(direction_element, 'z')
z_element.text = '-1.5'
tree.write(self.sandbox('aircraft', aircraft_name,
aircraft_name+'.xml'))
fdm = CreateFDM(self.sandbox)
fdm.set_aircraft_path('aircraft')
fdm.load_script(script_path)
fdm.run_ic()
mDir = np.array([0.2, 0.0, -1.5])
mDir /= np.linalg.norm(mDir)
self.assertAlmostEqual(fdm['external_reactions/parachute/l'], mDir[0])
self.assertAlmostEqual(fdm['external_reactions/parachute/m'], mDir[1])
self.assertAlmostEqual(fdm['external_reactions/parachute/n'], mDir[2])
fdm['external_reactions/parachute/magnitude-lbsft'] = -3.5
while fdm.run():
Tw2b = fdm.get_auxiliary().get_Tw2b()
mag = fdm['aero/qbar-psf'] * fdm['fcs/parachute_reef_pos_norm']*20.0
f = Tw2b * np.mat([-1.0, 0.0, 0.0]).T * mag
self.assertAlmostEqual(fdm['forces/fbx-external-lbs'], f[0, 0])
self.assertAlmostEqual(fdm['forces/fby-external-lbs'], f[1, 0])
self.assertAlmostEqual(fdm['forces/fbz-external-lbs'], f[2, 0])
m = -3.5 * Tw2b * np.mat(mDir).T
fm = np.cross(self.getLeverArm(fdm,'parachute'),
np.array([f[0,0], f[1,0], f[2, 0]]))
self.assertAlmostEqual(fdm['moments/l-external-lbsft'], m[0, 0] + fm[0])
self.assertAlmostEqual(fdm['moments/m-external-lbsft'], m[1, 0] + fm[1])
self.assertAlmostEqual(fdm['moments/n-external-lbsft'], m[2, 0] + fm[2])
def testDragFunctions(self):
fdm = CreateFDM(self.sandbox)
self.script_path = self.sandbox.path_to_jsbsim_file('scripts',
'x153.xml')
fdm.load_script(self.script_path)
fdm.set_output_directive(self.sandbox.path_to_jsbsim_file('tests',
'output.xml'))
fdm.run_ic()
while fdm.run():
pass
results = pd.read_csv('output.csv', index_col=0)
Fdrag = results['F_{Drag} (lbs)']
CDmin = results['aero/coefficient/CDmin']
CDi = results['aero/coefficient/CDi']
self.assertAlmostEqual(abs(Fdrag/(CDmin+CDi)).max(), 1.0, delta=1E-5)
def test_moments_update(self):
script_path = self.sandbox.path_to_jsbsim_file('scripts', 'weather-balloon.xml')
fdm = CreateFDM(self.sandbox)
fdm.load_script(script_path)
fdm.run_ic()
# Moves the radio sonde to modify the CG location
fdm.set_property_value('inertia/pointmass-location-X-inches', 5.0)
# Check that the moment is immediately updated accordingly
fdm.run()
Fbz = fdm.get_property_value('forces/fbz-buoyancy-lbs')
CGx = fdm.get_property_value('inertia/cg-x-in') / 12.0 # Converts from in to ft
Mby = fdm.get_property_value('moments/m-buoyancy-lbsft')
self.assertTrue(abs(Fbz * CGx + Mby) < 1E-7,
msg="Fbz*CGx = %f and Mby = %f do not match" % (-Fbz*CGx, Mby))
def testTableWithIndexedVars(self):
tree = et.parse(self.sandbox.path_to_jsbsim_file('engine',
'eng_PegasusXc.xml'))
# Define the function starter-max-power-W as a 'post' function
root = tree.getroot()
startPowFunc_tag = root.find("function/[@name='propulsion/engine[#]/starter-max-power-W']")
startPowFunc_tag.attrib['type']='post'
max_tag = startPowFunc_tag.find('product/max')
diff_tag = max_tag.find('difference')
max_tag.remove(diff_tag)
table_tag = et.SubElement(max_tag,'table')
table_tag.attrib['name']='propulsion/engine[#]/starter-tabular-data'
indepVar_tag = et.SubElement(table_tag, 'independentVar')
indepVar_tag.attrib['lookup']='row'
indepVar_tag.text = 'propulsion/engine[#]/engine-rpm'
tData_tag = et.SubElement(table_tag, 'tableData')
tData_tag.text ='0.0 1.0\n400.0 0.0'
tree.write('eng_PegasusXc.xml')
# Copy the propeller file.
shutil.copy(self.sandbox.path_to_jsbsim_file('engine', 'prop_deHavilland5000.xml'),
'.')
fdm = CreateFDM(self.sandbox)
fdm.set_engine_path('.')
fdm.load_script(self.sandbox.path_to_jsbsim_file('scripts',
'Short_S23_1.xml'))
fdm.run_ic()
pm = fdm.get_property_manager()
self.assertTrue(pm.hasNode('propulsion/engine[0]/starter-max-power-W'))
self.assertTrue(pm.hasNode('propulsion/engine[1]/starter-max-power-W'))
self.assertTrue(pm.hasNode('propulsion/engine[2]/starter-max-power-W'))
self.assertTrue(pm.hasNode('propulsion/engine[3]/starter-max-power-W'))
while fdm.run():
rpm = [fdm['propulsion/engine[0]/engine-rpm'],
fdm['propulsion/engine[1]/engine-rpm'],
fdm['propulsion/engine[2]/engine-rpm'],
fdm['propulsion/engine[3]/engine-rpm']]
for i in range(4):
tabularData = max(0.0, 1.0-rpm[i]/400)
maxPower = tabularData*498.941*0.10471976*rpm[i]
self.assertAlmostEqual(fdm['propulsion/engine[%d]/starter-max-power-W' % (i,)],
maxPower)
self.assertAlmostEqual(fdm['propulsion/engine[%d]/starter-tabular-data' % (i,)],
tabularData)
