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(self.sandbox.elude(script_path))
run_tag = tree.getroot().find('./run')
run_tag.attrib['dt'] = '0.1'
tree.write(self.sandbox(script_name))
fdm = CreateFDM(self.sandbox)
fdm.set_aircraft_path('aircraft')
fdm.load_script(script_name)
# Switch the accel on
fdm.set_property_value('fcs/accelerometer/on', 1.0)
fdm.run_ic()
while fdm.run():
self.assertAlmostEqual(fdm.get_property_value('fcs/accelerometer/X'),
0.0, delta=1E-8)
self.assertAlmostEqual(fdm.get_property_value('fcs/accelerometer/Y'),
0.0, delta=1E-8)
self.assertAlmostEqual(fdm.get_property_value('fcs/accelerometer/Z'),
0.0, delta=1E-8)
self.assertAlmostEqual(fdm.get_property_value('accelerations/a-pilot-x-ft_sec2'),
0.0, delta=1E-8)
self.assertAlmostEqual(fdm.get_property_value('accelerations/a-pilot-y-ft_sec2'),
0.0, delta=1E-8)
self.assertAlmostEqual(fdm.get_property_value('accelerations/a-pilot-z-ft_sec2'),
0.0, delta=1E-8)
del fdm
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 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 CheckRateLimit(script_path, input_prop, output_prop, incr_limit, decr_limit):
fdm = CreateFDM(sandbox)
fdm.set_aircraft_path('aircraft')
ScriptExecution(fdm, script_path, 1.0)
fdm.set_property_value(input_prop, 1.0)
CheckRateValue(fdm, output_prop, incr_limit)
fdm.set_property_value(input_prop, 0.0)
CheckRateValue(fdm, output_prop, decr_limit)
def testSpinningBodyOnOrbit(self):
script_name = 'ball_orbit.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_model('ball')
# Offset the CG along Y (by 30")
fdm.set_property_value('inertia/pointmass-weight-lbs[1]', 50.0)
aircraft_path = self.sandbox.elude(
self.sandbox.path_to_jsbsim_file('aircraft', 'ball'))
fdm.load_ic(os.path.join(aircraft_path, 'reset00.xml'), False)
# Switch the accel on
fdm.set_property_value('fcs/accelerometer/on', 1.0)
# Set the orientation such that the spinning axis is Z.
fdm.set_property_value('ic/phi-rad', 0.5 * math.pi)
# Set the angular velocities to 0.0 in the ECEF frame. The angular
# velocity R_{inertial} will therefore be equal to the Earth rotation
# rate 7.292115E-5 rad/sec
fdm.set_property_value('ic/p-rad_sec', 0.0)
fdm.set_property_value('ic/q-rad_sec', 0.0)
fdm.set_property_value('ic/r-rad_sec', 0.0)
fdm.run_ic()
fax = fdm.get_property_value('fcs/accelerometer/X')
fay = fdm.get_property_value('fcs/accelerometer/Y')
faz = fdm.get_property_value('fcs/accelerometer/Z')
cgy_ft = fdm.get_property_value('inertia/cg-y-in') / 12.
omega = 0.00007292115 # Earth rotation rate in rad/sec
self.assertAlmostEqual(
fdm.get_property_value('accelerations/a-pilot-x-ft_sec2'),
fax,
delta=1E-8)
self.assertAlmostEqual(
fdm.get_property_value('accelerations/a-pilot-y-ft_sec2'),
fay,
delta=1E-8)
self.assertAlmostEqual(
fdm.get_property_value('accelerations/a-pilot-z-ft_sec2'),
faz,
delta=1E-8)
# Acceleration along X should be zero
self.assertAlmostEqual(fax, 0.0, delta=1E-8)
# Acceleration along Y should be equal to r*omega^2
self.assertAlmostEqual(fay / (cgy_ft * omega * omega), 1.0, delta=1E-7)
# Acceleration along Z should be zero
self.assertAlmostEqual(faz, 0.0, delta=1E-8)
def test_static_hold_down(self):
fdm = CreateFDM(self.sandbox)
fdm.load_model('J246')
aircraft_path = self.sandbox.elude(self.sandbox.path_to_jsbsim_file('aircraft'))
fdm.load_ic(os.path.join(aircraft_path, 'J246', 'LC39'), False)
fdm.set_property_value('forces/hold-down', 1.0)
fdm.run_ic()
h0 = fdm.get_property_value('position/h-sl-ft')
t = 0.0
while t < 420.0:
fdm.run()
t = fdm.get_property_value('simulation/sim-time-sec')
self.assertAlmostEqual(fdm.get_property_value('position/h-sl-ft'),
h0, 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 CheckRateLimit(self, input_prop, output_prop, incr_limit, decr_limit):
fdm = CreateFDM(self.sandbox)
fdm.set_aircraft_path("aircraft")
self.ScriptExecution(fdm, 1.0)
fdm.set_property_value(input_prop, 1.0)
self.CheckRateValue(fdm, output_prop, incr_limit)
fdm.set_property_value(input_prop, 0.0)
self.CheckRateValue(fdm, output_prop, decr_limit)
# Because JSBSim internals use static pointers, we cannot rely on Python
# garbage collector to decide when the FDM is destroyed otherwise we can
# get dangling pointers.
del fdm
def CheckRateLimit(self, input_prop, output_prop, incr_limit, decr_limit):
fdm = CreateFDM(self.sandbox)
fdm.set_aircraft_path('aircraft')
self.ScriptExecution(fdm, 1.0)
fdm.set_property_value(input_prop, 1.0)
self.CheckRateValue(fdm, output_prop, incr_limit)
fdm.set_property_value(input_prop, 0.0)
self.CheckRateValue(fdm, output_prop, decr_limit)
# Because JSBSim internals use static pointers, we cannot rely on Python
# garbage collector to decide when the FDM is destroyed otherwise we can
# get dangling pointers.
del fdm
def test_static_hold_down(self):
fdm = CreateFDM(self.sandbox)
fdm.load_model('J246')
aircraft_path = self.sandbox.elude(
self.sandbox.path_to_jsbsim_file('aircraft'))
fdm.load_ic(os.path.join(aircraft_path, 'J246', 'LC39'), False)
fdm.set_property_value('forces/hold-down', 1.0)
fdm.run_ic()
h0 = fdm.get_property_value('position/h-sl-ft')
t = 0.0
while t < 420.0:
fdm.run()
t = fdm.get_property_value('simulation/sim-time-sec')
self.assertAlmostEqual(fdm.get_property_value('position/h-sl-ft'),
h0,
delta=1E-5)
def testSpinningBodyOnOrbit(self):
script_name = 'ball_orbit.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_model('ball')
# Offset the CG along Y (by 30")
fdm.set_property_value('inertia/pointmass-weight-lbs[1]', 50.0)
aircraft_path = self.sandbox.elude(self.sandbox.path_to_jsbsim_file('aircraft', 'ball'))
fdm.load_ic(os.path.join(aircraft_path, 'reset00.xml'), False)
# Switch the accel on
fdm.set_property_value('fcs/accelerometer/on', 1.0)
# Set the orientation such that the spinning axis is Z.
fdm.set_property_value('ic/phi-rad', 0.5*math.pi)
# Set the angular velocities to 0.0 in the ECEF frame. The angular
# velocity R_{inertial} will therefore be equal to the Earth rotation
# rate 7.292115E-5 rad/sec
fdm.set_property_value('ic/p-rad_sec', 0.0)
fdm.set_property_value('ic/q-rad_sec', 0.0)
fdm.set_property_value('ic/r-rad_sec', 0.0)
fdm.run_ic()
fax = fdm.get_property_value('fcs/accelerometer/X')
fay = fdm.get_property_value('fcs/accelerometer/Y')
faz = fdm.get_property_value('fcs/accelerometer/Z')
cgy_ft = fdm.get_property_value('inertia/cg-y-in') / 12.
omega = 0.00007292115 # Earth rotation rate in rad/sec
self.assertAlmostEqual(fdm.get_property_value('accelerations/a-pilot-x-ft_sec2'),
fax, delta=1E-8)
self.assertAlmostEqual(fdm.get_property_value('accelerations/a-pilot-y-ft_sec2'),
fay, delta=1E-8)
self.assertAlmostEqual(fdm.get_property_value('accelerations/a-pilot-z-ft_sec2'),
faz, delta=1E-8)
# Acceleration along X should be zero
self.assertAlmostEqual(fax, 0.0, delta=1E-8)
# Acceleration along Y should be equal to r*omega^2
self.assertAlmostEqual(fay / (cgy_ft * omega * omega), 1.0, delta=1E-7)
# Acceleration along Z should be zero
self.assertAlmostEqual(faz, 0.0, delta=1E-8)
def test_gust_reset(self):
fdm = CreateFDM(self.sandbox)
fdm.load_script(self.sandbox.path_to_jsbsim_file('scripts', 'c172_cruise_8K.xml'))
fdm.set_property_value('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, current = Table(), Table()
ref.ReadCSV(self.sandbox('output.csv'))
fdm.set_property_value('simulation/randomseed', 0.0)
fdm.reset_to_initial_conditions(1)
ExecuteUntil(fdm, 15.5)
current.ReadCSV(self.sandbox('output_0.csv'))
diff = ref.compare(current)
self.longMessage = True
self.assertTrue(diff.empty(), msg='\n'+repr(diff))
def test_no_script(self):
fdm = CreateFDM(self.sandbox)
aircraft_path = self.sandbox.path_to_jsbsim_file('aircraft')
fdm.set_aircraft_path(aircraft_path)
fdm.load_model('c172x')
aircraft_path = os.path.join(self.sandbox.elude(aircraft_path), 'c172x')
fdm.load_ic(os.path.join(aircraft_path, 'reset01.xml'), False)
fdm.run_ic()
self.assertEqual(fdm.get_property_value('simulation/sim-time-sec'), 0.0)
ExecuteUntil(fdm, 5.0)
t = fdm.get_property_value('simulation/sim-time-sec')
fdm.set_property_value('simulation/do_simple_trim', 1)
self.assertEqual(fdm.get_property_value('simulation/sim-time-sec'), t)
fdm.reset_to_initial_conditions(1)
self.assertEqual(fdm.get_property_value('simulation/sim-time-sec'), 0.0)
del fdm
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(self.sandbox.elude(script_path))
run_tag = tree.getroot().find('./run')
run_tag.attrib['dt'] = '0.1'
tree.write(self.sandbox(script_name))
fdm = CreateFDM(self.sandbox)
fdm.set_aircraft_path('aircraft')
fdm.load_script(script_name)
# Switch the accel on
fdm.set_property_value('fcs/accelerometer/on', 1.0)
fdm.run_ic()
while fdm.run():
self.assertAlmostEqual(
fdm.get_property_value('fcs/accelerometer/X'), 0.0, delta=1E-8)
self.assertAlmostEqual(
fdm.get_property_value('fcs/accelerometer/Y'), 0.0, delta=1E-8)
self.assertAlmostEqual(
fdm.get_property_value('fcs/accelerometer/Z'), 0.0, delta=1E-8)
self.assertAlmostEqual(
fdm.get_property_value('accelerations/a-pilot-x-ft_sec2'),
0.0,
delta=1E-8)
self.assertAlmostEqual(
fdm.get_property_value('accelerations/a-pilot-y-ft_sec2'),
0.0,
delta=1E-8)
self.assertAlmostEqual(
fdm.get_property_value('accelerations/a-pilot-z-ft_sec2'),
0.0,
delta=1E-8)
del 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 BuildReference(self, script_name):
# Run the script
self.script = self.sandbox.path_to_jsbsim_file(os.path.join('scripts',
script_name))
self.sandbox.delete_csv_files()
fdm = CreateFDM(self.sandbox)
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)
self.ref = Table()
self.ref.ReadCSV(self.sandbox("output.csv"))
# Since the script will work with modified versions of the aircraft XML
# definition file, we need to make a copy of the directory that contains
# all the input data of that aircraft
tree, self.aircraft_name, self.path_to_jsbsim_aircrafts = CopyAircraftDef(self.script, self.sandbox)
self.aircraft_path = self.sandbox('aircraft', self.aircraft_name)
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 test_gust_reset(self):
fdm = CreateFDM(self.sandbox)
fdm.load_script(
self.sandbox.path_to_jsbsim_file('scripts', 'c172_cruise_8K.xml'))
fdm.set_property_value('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, current = Table(), Table()
ref.ReadCSV(self.sandbox('output.csv'))
fdm.set_property_value('simulation/randomseed', 0.0)
fdm.reset_to_initial_conditions(1)
ExecuteUntil(fdm, 15.5)
current.ReadCSV(self.sandbox('output_0.csv'))
diff = ref.compare(current)
self.longMessage = True
self.assertTrue(diff.empty(), msg='\n' + repr(diff))
def BuildReference(self, script_name):
# Run the script
self.script = self.sandbox.path_to_jsbsim_file(
os.path.join('scripts', script_name))
self.sandbox.delete_csv_files()
fdm = CreateFDM(self.sandbox)
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)
self.ref = Table()
self.ref.ReadCSV(self.sandbox("output.csv"))
# Since the script will work with modified versions of the aircraft XML
# definition file, we need to make a copy of the directory that contains
# all the input data of that aircraft
tree, self.aircraft_name, self.path_to_jsbsim_aircrafts = CopyAircraftDef(
self.script, self.sandbox)
self.aircraft_path = self.sandbox('aircraft', self.aircraft_name)
def test_no_script(self):
fdm = CreateFDM(self.sandbox)
aircraft_path = self.sandbox.path_to_jsbsim_file('aircraft')
fdm.set_aircraft_path(aircraft_path)
fdm.load_model('c172x')
aircraft_path = os.path.join(self.sandbox.elude(aircraft_path),
'c172x')
fdm.load_ic(os.path.join(aircraft_path, 'reset01.xml'), False)
fdm.run_ic()
self.assertEqual(fdm.get_property_value('simulation/sim-time-sec'),
0.0)
ExecuteUntil(fdm, 5.0)
t = fdm.get_property_value('simulation/sim-time-sec')
fdm.set_property_value('simulation/do_simple_trim', 1)
self.assertEqual(fdm.get_property_value('simulation/sim-time-sec'), t)
fdm.reset_to_initial_conditions(1)
self.assertEqual(fdm.get_property_value('simulation/sim-time-sec'),
0.0)
del 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 testOnGround(self):
script_name = 'c1721.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()
for i in xrange(500):
fdm.run()
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
faz -= az
self.assertAlmostEqual(fay, 0.0, delta=1E-6)
self.assertAlmostEqual(fax / (g * math.sin(theta)), 1.0, delta=1E-5)
self.assertAlmostEqual(faz / (g * math.cos(theta)), -1.0, delta=1E-7)
del fdm
def testOnGround(self):
script_name = 'c1721.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()
for i in xrange(500):
fdm.run()
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
faz -= az
self.assertAlmostEqual(fay, 0.0, delta=1E-6)
self.assertAlmostEqual(fax / (g * math.sin(theta)), 1.0, delta=1E-5)
self.assertAlmostEqual(faz / (g * math.cos(theta)), -1.0, delta=1E-7)
del fdm
class CheckMomentsUpdate(unittest.TestCase):
def setUp(self):
self.sandbox = SandBox()
def tearDown(self):
self.sandbox.erase()
def CheckCGPosition(self):
weight = self.fdm.get_property_value('inertia/weight-lbs')
empty_weight = self.fdm.get_property_value('inertia/empty-weight-lbs')
contents = self.fdm.get_property_value(
'buoyant_forces/gas-cell/contents-mol')
radiosonde_weight = weight - empty_weight - contents * mol2lbs
CGx = self.fdm.get_property_value('inertia/cg-x-in')
CGy = self.fdm.get_property_value('inertia/cg-y-in')
CGz = self.fdm.get_property_value('inertia/cg-z-in')
X = self.fdm.get_property_value('inertia/pointmass-location-X-inches')
Y = self.fdm.get_property_value('inertia/pointmass-location-Y-inches')
Z = self.fdm.get_property_value('inertia/pointmass-location-Z-inches')
self.assertAlmostEqual(CGx, X * radiosonde_weight / weight, delta=1E-7)
self.assertAlmostEqual(CGy, Y * radiosonde_weight / weight, delta=1E-7)
self.assertAlmostEqual(CGz, Z * radiosonde_weight / weight, delta=1E-7)
def test_moments_update(self):
script_path = self.sandbox.path_to_jsbsim_file('scripts',
'weather-balloon.xml')
self.fdm = CreateFDM(self.sandbox)
self.fdm.load_script(script_path)
self.fdm.set_output_directive(
self.sandbox.path_to_jsbsim_file('tests', 'output.xml'))
self.fdm.run_ic()
self.CheckCGPosition()
dt = self.fdm.get_property_value('simulation/dt')
ExecuteUntil(self.fdm, 1.0 - 2.0 * dt)
self.CheckCGPosition()
# Moves the radio sonde to modify the CG location
self.fdm.set_property_value('inertia/pointmass-location-X-inches', 5.0)
# Check that the moment is immediately updated accordingly
self.fdm.run()
self.CheckCGPosition()
Fbx = self.fdm.get_property_value('forces/fbx-buoyancy-lbs')
Fbz = self.fdm.get_property_value('forces/fbz-buoyancy-lbs')
CGx = self.fdm.get_property_value(
'inertia/cg-x-in') / 12.0 # Converts from in to ft
CGz = self.fdm.get_property_value('inertia/cg-z-in') / 12.0
Mby = self.fdm.get_property_value('moments/m-buoyancy-lbsft')
self.assertAlmostEqual(
Fbx * CGz - Fbz * CGx,
Mby,
delta=1E-7,
msg="Fbx*CGz-Fbz*CGx = %f and Mby = %f do not match" %
(Fbx * CGz - Fbz * CGx, Mby))
# One further step to log the same results in the output file
self.fdm.run()
self.CheckCGPosition()
csv = Table()
csv.ReadCSV(self.sandbox('output.csv'))
Mby = csv.get_column('M_{Buoyant} (ft-lbs)')[-1]
Fbx = csv.get_column('F_{Buoyant x} (lbs)')[-1]
Fbz = csv.get_column('F_{Buoyant z} (lbs)')[-1]
self.assertAlmostEqual(
Fbx * CGz - Fbz * CGx,
Mby,
delta=1E-7,
msg="Fbx*CGz-Fbz*CGx = %f and Mby = %f do not match" %
(Fbx * CGz - Fbz * CGx, Mby))
def test_pitot_angle(self):
script_name = 'ball_chute.xml'
script_path = self.sandbox.path_to_jsbsim_file('scripts', script_name)
# Add a Pitot angle to the Cessna 172
tree, aircraft_name, path_to_jsbsim_aircrafts = CopyAircraftDef(script_path, self.sandbox)
root = tree.getroot()
metrics_tag = root.find('./metrics')
pitot_tag = et.SubElement(metrics_tag, 'pitot_angle')
pitot_tag.attrib['unit'] = 'DEG'
pitot_tag.text = '5.0'
contact_tag = root.find('./ground_reactions/contact')
contact_tag.attrib['type'] = 'STRUCTURE'
tree.write(self.sandbox('aircraft', aircraft_name,
aircraft_name+'.xml'))
fdm = CreateFDM(self.sandbox)
fdm.set_aircraft_path('aircraft')
fdm.load_model('ball')
pitot_angle = float(pitot_tag.text) * math.pi / 180.
weight = fdm.get_property_value('inertia/weight-lbs')
spring_tag = contact_tag.find('./spring_coeff')
spring_coeff = float(spring_tag.text)
print "Weight=%d Spring=%d" % (weight, spring_coeff)
fdm.set_property_value('ic/h-sl-ft', weight / spring_coeff)
fdm.set_property_value('forces/hold-down', 1.0)
fdm.run_ic()
ExecuteUntil(fdm, 10.)
for i in xrange(36):
for j in xrange(-9, 10):
angle = math.pi * i / 18.0
angle2 = math.pi * j / 18.0
ca2 = math.cos(angle2)
fdm.set_property_value('atmosphere/wind-north-fps',
10. * math.cos(angle) * ca2)
fdm.set_property_value('atmosphere/wind-east-fps',
10. * math.sin(angle) * ca2)
fdm.set_property_value('atmosphere/wind-down-fps',
10. * math.sin(angle2))
fdm.run()
vg = fdm.get_property_value('velocities/vg-fps')
self.assertAlmostEqual(vg, 0.0, delta=1E-7)
vt = fdm.get_property_value('velocities/vt-fps')
self.assertAlmostEqual(vt, 10., delta=1E-7)
mach = vt / fdm.get_property_value('atmosphere/a-fps')
P = fdm.get_property_value('atmosphere/P-psf')
pt = P * math.pow(1+0.2*mach*mach, 3.5)
psl = fdm.get_property_value('atmosphere/P-sl-psf')
rhosl = fdm.get_property_value('atmosphere/rho-sl-slugs_ft3')
A = math.pow((pt-P)/psl+1.0, 1.0/3.5)
alpha = fdm.get_property_value('aero/alpha-rad')
beta = fdm.get_property_value('aero/beta-rad')
vc = math.sqrt(7.0*psl/rhosl*(A-1.0))*math.cos(alpha+pitot_angle)*math.cos(beta)
self.assertAlmostEqual(fdm.get_property_value('velocities/vc-kts'),
max(0.0, vc) / 1.68781, delta=1E-7)
def test_pitot_angle(self):
script_name = 'ball_chute.xml'
script_path = self.sandbox.path_to_jsbsim_file('scripts', script_name)
# Add a Pitot angle to the Cessna 172
tree, aircraft_name, path_to_jsbsim_aircrafts = CopyAircraftDef(
script_path, self.sandbox)
root = tree.getroot()
metrics_tag = root.find('./metrics')
pitot_tag = et.SubElement(metrics_tag, 'pitot_angle')
pitot_tag.attrib['unit'] = 'DEG'
pitot_tag.text = '5.0'
contact_tag = root.find('./ground_reactions/contact')
contact_tag.attrib['type'] = 'STRUCTURE'
tree.write(
self.sandbox('aircraft', aircraft_name, aircraft_name + '.xml'))
fdm = CreateFDM(self.sandbox)
fdm.set_aircraft_path('aircraft')
fdm.load_model('ball')
pitot_angle = float(pitot_tag.text) * math.pi / 180.
weight = fdm.get_property_value('inertia/weight-lbs')
spring_tag = contact_tag.find('./spring_coeff')
spring_coeff = float(spring_tag.text)
print "Weight=%d Spring=%d" % (weight, spring_coeff)
fdm.set_property_value('ic/h-sl-ft', weight / spring_coeff)
fdm.set_property_value('forces/hold-down', 1.0)
fdm.run_ic()
ExecuteUntil(fdm, 10.)
for i in xrange(36):
for j in xrange(-9, 10):
angle = math.pi * i / 18.0
angle2 = math.pi * j / 18.0
ca2 = math.cos(angle2)
fdm.set_property_value('atmosphere/wind-north-fps',
10. * math.cos(angle) * ca2)
fdm.set_property_value('atmosphere/wind-east-fps',
10. * math.sin(angle) * ca2)
fdm.set_property_value('atmosphere/wind-down-fps',
10. * math.sin(angle2))
fdm.run()
vg = fdm.get_property_value('velocities/vg-fps')
self.assertAlmostEqual(vg, 0.0, delta=1E-7)
vt = fdm.get_property_value('velocities/vt-fps')
self.assertAlmostEqual(vt, 10., delta=1E-7)
mach = vt / fdm.get_property_value('atmosphere/a-fps')
P = fdm.get_property_value('atmosphere/P-psf')
pt = P * math.pow(1 + 0.2 * mach * mach, 3.5)
psl = fdm.get_property_value('atmosphere/P-sl-psf')
rhosl = fdm.get_property_value('atmosphere/rho-sl-slugs_ft3')
A = math.pow((pt - P) / psl + 1.0, 1.0 / 3.5)
alpha = fdm.get_property_value('aero/alpha-rad')
beta = fdm.get_property_value('aero/beta-rad')
vc = math.sqrt(
7.0 * psl / rhosl *
(A - 1.0)) * math.cos(alpha + pitot_angle) * math.cos(beta)
self.assertAlmostEqual(
fdm.get_property_value('velocities/vc-kts'),
max(0.0, vc) / 1.68781,
delta=1E-7)
class CheckMomentsUpdate(unittest.TestCase):
def setUp(self):
self.sandbox = SandBox()
def tearDown(self):
self.sandbox.erase()
def CheckCGPosition(self):
weight = self.fdm.get_property_value('inertia/weight-lbs')
empty_weight = self.fdm.get_property_value('inertia/empty-weight-lbs')
contents = self.fdm.get_property_value('buoyant_forces/gas-cell/contents-mol')
radiosonde_weight = weight - empty_weight - contents * mol2lbs
CGx = self.fdm.get_property_value('inertia/cg-x-in')
CGy = self.fdm.get_property_value('inertia/cg-y-in')
CGz = self.fdm.get_property_value('inertia/cg-z-in')
X = self.fdm.get_property_value('inertia/pointmass-location-X-inches')
Y = self.fdm.get_property_value('inertia/pointmass-location-Y-inches')
Z = self.fdm.get_property_value('inertia/pointmass-location-Z-inches')
self.assertAlmostEqual(CGx, X * radiosonde_weight / weight, delta = 1E-7)
self.assertAlmostEqual(CGy, Y * radiosonde_weight / weight, delta = 1E-7)
self.assertAlmostEqual(CGz, Z * radiosonde_weight / weight, delta = 1E-7)
def test_moments_update(self):
script_path = self.sandbox.path_to_jsbsim_file('scripts', 'weather-balloon.xml')
self.fdm = CreateFDM(self.sandbox)
self.fdm.load_script(script_path)
self.fdm.set_output_directive(self.sandbox.path_to_jsbsim_file('tests', 'output.xml'))
self.fdm.run_ic()
self.CheckCGPosition()
dt = self.fdm.get_property_value('simulation/dt')
ExecuteUntil(self.fdm, 1.0-2.0*dt)
self.CheckCGPosition()
# Moves the radio sonde to modify the CG location
self.fdm.set_property_value('inertia/pointmass-location-X-inches', 5.0)
# Check that the moment is immediately updated accordingly
self.fdm.run()
self.CheckCGPosition()
Fbx = self.fdm.get_property_value('forces/fbx-buoyancy-lbs')
Fbz = self.fdm.get_property_value('forces/fbz-buoyancy-lbs')
CGx = self.fdm.get_property_value('inertia/cg-x-in') / 12.0 # Converts from in to ft
CGz = self.fdm.get_property_value('inertia/cg-z-in') / 12.0
Mby = self.fdm.get_property_value('moments/m-buoyancy-lbsft')
self.assertAlmostEqual(Fbx * CGz - Fbz * CGx, Mby, delta=1E-7,
msg="Fbx*CGz-Fbz*CGx = %f and Mby = %f do not match" % (Fbx*CGz-Fbz*CGx, Mby))
# One further step to log the same results in the output file
self.fdm.run()
self.CheckCGPosition()
csv = Table()
csv.ReadCSV(self.sandbox('output.csv'))
Mby = csv.get_column('M_{Buoyant} (ft-lbs)')[-1]
Fbx = csv.get_column('F_{Buoyant x} (lbs)')[-1]
Fbz = csv.get_column('F_{Buoyant z} (lbs)')[-1]
self.assertAlmostEqual(Fbx * CGz - Fbz * CGx, Mby, delta=1E-7,
msg="Fbx*CGz-Fbz*CGx = %f and Mby = %f do not match" % (Fbx*CGz-Fbz*CGx, Mby))
class CheckOutputRate(unittest.TestCase):
def setUp(self):
self.sandbox = SandBox()
self.fdm = CreateFDM(self.sandbox)
self.script_path = self.sandbox.path_to_jsbsim_file('scripts', 'c1722.xml')
# Read the time step 'dt' from the script file
self.tree = et.parse(self.sandbox.elude(self.script_path))
root = self.tree.getroot()
use_tag = root.find("./use")
aircraft_name = use_tag.attrib['aircraft']
self.run_tag = root.find("./run")
self.dt = float(self.run_tag.attrib['dt'])
# Read the date at which the trim will be run
event_tags = root.findall('./run/event')
for event in event_tags:
if event.attrib['name'] == 'Trim':
cond_tag = event.find('./condition')
self.trim_date = float(string.split(cond_tag.text)[-1])
break
# Read the output rate and the output file from the aircraft file
aircraft_path = self.sandbox.path_to_jsbsim_file('aircraft', aircraft_name,
append_xml(aircraft_name))
tree = et.parse(self.sandbox.elude(aircraft_path))
output_tag = tree.getroot().find("./output")
self.output_file = self.sandbox(output_tag.attrib['name'])
self.rateHz = float(output_tag.attrib['rate'])
self.rate = int(1.0 / (self.rateHz * self.dt))
def tearDown(self):
del self.fdm
self.sandbox.erase()
def testOutputRate(self):
self.fdm.load_script(self.script_path)
# Check that the output is enabled by default
self.assertEqual(self.fdm.get_property_value("simulation/output/enabled"),
1.0)
# Check that the rate is consistent with the values extracted from the
# script and the aircraft definition
self.assertAlmostEqual(self.fdm.get_property_value("simulation/output/log_rate_hz"),
self.rateHz, delta=1E-5)
self.fdm.run_ic()
for i in xrange(self.rate):
self.fdm.run()
output = Table()
output.ReadCSV(self.output_file)
# According to the settings, the output file must contain 2 lines in
# addition to the headers :
# 1. The initial conditions
# 2. The output after 'rate' iterations
self.assertEqual(output.get_column(0)[1], 0.0)
self.assertEqual(output.get_column(0)[2], self.rate * self.dt)
self.assertEqual(output.get_column(0)[2],
self.fdm.get_property_value("simulation/sim-time-sec"))
def testDisablingOutput(self):
self.fdm.load_script(self.script_path)
# Disables the output during the initialization
self.fdm.set_property_value("simulation/output/enabled", 0.0)
self.fdm.run_ic()
self.fdm.set_property_value("simulation/output/enabled", 1.0)
for i in xrange(self.rate):
self.fdm.run()
output = Table()
output.ReadCSV(self.output_file)
# According to the settings, the output file must contain 1 line in
# addition to the headers :
# 1. The output after 'rate' iterations
self.assertEqual(output.get_column(0)[1],
self.fdm.get_property_value("simulation/sim-time-sec"))
def testTrimRestoresOutputSettings(self):
self.fdm.load_script(self.script_path)
# Disables the output during the initialization
self.fdm.set_property_value("simulation/output/enabled", 0.0)
self.fdm.run_ic()
# Check that the output remains disabled even after the trim is
# executed
while self.fdm.get_property_value("simulation/sim-time-sec") < self.trim_date + 2.0*self.dt:
self.fdm.run()
self.assertEqual(self.fdm.get_property_value("simulation/output/enabled"),
0.0)
# Re-enable the output and check that the output rate is unaffected by
# the previous operations
self.fdm.set_property_value("simulation/output/enabled", 1.0)
frame = int(self.fdm.get_property_value("simulation/frame"))
for i in xrange(self.rate):
self.fdm.run()
output = Table()
output.ReadCSV(self.output_file)
# The frame at which the data is logged must be the next multiple of
# the output rate
self.assertEqual(int(output.get_column(0)[1]/self.dt),
(1 + frame/self.rate)*self.rate)
def testDisablingOutputInScript(self):
property = et.SubElement(self.run_tag, 'property')
property.text = 'simulation/output/enabled'
property.attrib['value'] = "0.0"
self.tree.write(self.sandbox('c1722_0.xml'))
self.fdm.load_script('c1722_0.xml')
# Check that the output is disabled
self.assertEqual(self.fdm.get_property_value("simulation/output/enabled"),
0.0)
self.fdm.run_ic()
self.fdm.set_property_value("simulation/output/enabled", 1.0)
for i in xrange(self.rate):
self.fdm.run()
output = Table()
output.ReadCSV(self.output_file)
# According to the settings, the output file must contain 1 line in
# addition to the headers :
# 1. The output after 'rate' iterations
self.assertEqual(output.get_column(0)[1],
self.fdm.get_property_value("simulation/sim-time-sec"))
class CheckOutputRate(unittest.TestCase):
def setUp(self):
self.sandbox = SandBox()
self.fdm = CreateFDM(self.sandbox)
self.script_path = self.sandbox.path_to_jsbsim_file("scripts", "c1722.xml")
# Read the time step 'dt' from the script file
self.tree = et.parse(self.sandbox.elude(self.script_path))
root = self.tree.getroot()
use_tag = root.find("./use")
aircraft_name = use_tag.attrib["aircraft"]
self.run_tag = root.find("./run")
self.dt = float(self.run_tag.attrib["dt"])
# Read the date at which the trim will be run
event_tags = root.findall("./run/event")
for event in event_tags:
if event.attrib["name"] == "Trim":
cond_tag = event.find("./condition")
self.trim_date = float(string.split(cond_tag.text)[-1])
break
# Read the output rate and the output file from the aircraft file
aircraft_path = self.sandbox.path_to_jsbsim_file("aircraft", aircraft_name, append_xml(aircraft_name))
tree = et.parse(self.sandbox.elude(aircraft_path))
output_tag = tree.getroot().find("./output")
self.output_file = self.sandbox(output_tag.attrib["name"])
self.rateHz = float(output_tag.attrib["rate"])
self.rate = int(1.0 / (self.rateHz * self.dt))
def tearDown(self):
del self.fdm
self.sandbox.erase()
def testOutputRate(self):
self.fdm.load_script(self.script_path)
# Check that the output is enabled by default
self.assertEqual(self.fdm.get_property_value("simulation/output/enabled"), 1.0)
# Check that the rate is consistent with the values extracted from the
# script and the aircraft definition
self.assertAlmostEqual(self.fdm.get_property_value("simulation/output/log_rate_hz"), self.rateHz, delta=1e-5)
self.fdm.run_ic()
for i in xrange(self.rate):
self.fdm.run()
output = Table()
output.ReadCSV(self.output_file)
# According to the settings, the output file must contain 2 lines in
# addition to the headers :
# 1. The initial conditions
# 2. The output after 'rate' iterations
self.assertEqual(output.get_column(0)[1], 0.0)
self.assertEqual(output.get_column(0)[2], self.rate * self.dt)
self.assertEqual(output.get_column(0)[2], self.fdm.get_property_value("simulation/sim-time-sec"))
def testDisablingOutput(self):
self.fdm.load_script(self.script_path)
# Disables the output during the initialization
self.fdm.set_property_value("simulation/output/enabled", 0.0)
self.fdm.run_ic()
self.fdm.set_property_value("simulation/output/enabled", 1.0)
for i in xrange(self.rate):
self.fdm.run()
output = Table()
output.ReadCSV(self.output_file)
# According to the settings, the output file must contain 1 line in
# addition to the headers :
# 1. The output after 'rate' iterations
self.assertEqual(output.get_column(0)[1], self.fdm.get_property_value("simulation/sim-time-sec"))
def testTrimRestoresOutputSettings(self):
self.fdm.load_script(self.script_path)
# Disables the output during the initialization
self.fdm.set_property_value("simulation/output/enabled", 0.0)
self.fdm.run_ic()
# Check that the output remains disabled even after the trim is
# executed
while self.fdm.get_property_value("simulation/sim-time-sec") < self.trim_date + 2.0 * self.dt:
self.fdm.run()
self.assertEqual(self.fdm.get_property_value("simulation/output/enabled"), 0.0)
# Re-enable the output and check that the output rate is unaffected by
# the previous operations
self.fdm.set_property_value("simulation/output/enabled", 1.0)
frame = int(self.fdm.get_property_value("simulation/frame"))
for i in xrange(self.rate):
self.fdm.run()
output = Table()
output.ReadCSV(self.output_file)
# The frame at which the data is logged must be the next multiple of
# the output rate
self.assertEqual(int(output.get_column(0)[1] / self.dt), (1 + frame / self.rate) * self.rate)
def testDisablingOutputInScript(self):
property = et.SubElement(self.run_tag, "property")
property.text = "simulation/output/enabled"
property.attrib["value"] = "0.0"
self.tree.write(self.sandbox("c1722_0.xml"))
self.fdm.load_script("c1722_0.xml")
# Check that the output is disabled
self.assertEqual(self.fdm.get_property_value("simulation/output/enabled"), 0.0)
self.fdm.run_ic()
self.fdm.set_property_value("simulation/output/enabled", 1.0)
for i in xrange(self.rate):
self.fdm.run()
output = Table()
output.ReadCSV(self.output_file)
# According to the settings, the output file must contain 1 line in
# addition to the headers :
# 1. The output after 'rate' iterations
self.assertEqual(output.get_column(0)[1], self.fdm.get_property_value("simulation/sim-time-sec"))
