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()
pitot_angle_deg = 5.0
self.addPitotTube(root, 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 = pitot_angle_deg * math.pi / 180.
weight = fdm['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['ic/h-sl-ft'] = weight / spring_coeff
fdm['forces/hold-down'] = 1.0
fdm.run_ic()
ExecuteUntil(fdm, 10.)
for i in range(36):
for j in range(-9, 10):
angle = math.pi * i / 18.0
angle2 = math.pi * j / 18.0
ca2 = math.cos(angle2)
fdm['atmosphere/wind-north-fps'] = 10. * math.cos(angle) * ca2
fdm['atmosphere/wind-east-fps'] = 10. * math.sin(angle) * ca2
fdm['atmosphere/wind-down-fps'] = 10. * math.sin(angle2)
fdm.run()
vg = fdm['velocities/vg-fps']
self.assertAlmostEqual(vg, 0.0, delta=1E-7)
vt = fdm['velocities/vt-fps']
self.assertAlmostEqual(vt, 10., delta=1E-7)
mach = vt / fdm['atmosphere/a-fps']
P = fdm['atmosphere/P-psf']
pt = P * math.pow(1 + 0.2 * mach * mach, 3.5)
psl = fdm['atmosphere/P-sl-psf']
rhosl = fdm['atmosphere/rho-sl-slugs_ft3']
A = math.pow((pt - P) / psl + 1.0, 1.0 / 3.5)
alpha = fdm['aero/alpha-rad']
beta = fdm['aero/beta-rad']
vc = math.sqrt(
7.0 * psl / rhosl *
(A - 1.0)) * math.cos(alpha + pitot_angle) * math.cos(beta)
self.assertAlmostEqual(fdm['velocities/vc-kts'],
max(0.0, vc) / 1.68781,
delta=1E-7)
def setUp(self):
self.sandbox = SandBox()
script_path = self.sandbox.path_to_jsbsim_file('scripts', 'c1722.xml')
# The aircraft c172x does not contain an <input> tag so we need
# to add one.
tree, aircraft_name, b = CopyAircraftDef(script_path, self.sandbox)
self.root = tree.getroot()
input_tag = et.SubElement(self.root, 'input')
input_tag.attrib['port']='1137'
tree.write(self.sandbox('aircraft', aircraft_name, aircraft_name+'.xml'))
self.fdm = CreateFDM(self.sandbox)
self.fdm.set_aircraft_path('aircraft')
self.fdm.load_script(script_path)
self.fdm.run_ic()
self.fdm.hold()
# Execute JSBSim in a separate thread
self.cond = threading.Condition()
self.thread = JSBSimThread(self.fdm, self.cond, 5., time.time())
self.thread.start()
# Wait for the thread to be started before connecting a telnet session
self.cond.acquire()
self.cond.wait()
self.tn = telnetlib.Telnet("localhost", 1137)
self.cond.release()
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 setUp(self):
JSBSimTestCase.setUp(self)
self.script_path = self.sandbox.path_to_jsbsim_file('scripts',
'c1724.xml')
# Since we will alter the aircraft definition file, we need make a copy
# of it and of all the files it is refering to.
self.tree, self.aircraft_name, self.path_to_jsbsim_aircrafts = CopyAircraftDef(self.script_path, self.sandbox)
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 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_steer_type(self):
self.script_path = self.sandbox.path_to_jsbsim_file(
'scripts', 'c1721.xml')
self.tree, self.aircraft_name, b = CopyAircraftDef(
self.script_path, self.sandbox)
root = self.tree.getroot()
self.max_steer_tag = root.find('ground_reactions/contact/max_steer')
# Check the fixed type
self.max_steer_tag.text = '0.0'
fdm = self.steerType(False, False, False)
del fdm
# Check the castered type
self.max_steer_tag.text = '360.0'
self.isCastered()
# Check the steered type
self.max_steer_tag.text = '10.0'
fdm = self.steerType(True, False, False)
fdm['fcs/steer-cmd-norm'] = 0.5
fdm.run()
self.assertAlmostEqual(fdm['fcs/steer-pos-deg'], 5.0)
del fdm
bogey_tag = root.find('ground_reactions/contact//max_steer/..')
castered_tag = et.SubElement(bogey_tag, 'castered')
castered_tag.text = '1.0'
# Check that the bogey is castered no matter what is the value
# of <max_steer>
self.max_steer_tag.text = '10.0'
self.isCastered()
self.max_steer_tag.text = '0.0'
self.isCastered()
self.max_steer_tag.text = '360.0'
self.isCastered()
# Check the fixed type
castered_tag.text = '0.0'
self.max_steer_tag.text = '0.0'
fdm = self.steerType(False, False, False)
del fdm
# Check the steered type
self.max_steer_tag.text = '10.0'
self.isSteered()
# Check the steered type with 360.0
self.max_steer_tag.text = '360.0'
self.isSteered()
def setUp(self):
JSBSimTestCase.setUp(self)
self.fdm = CreateFDM(self.sandbox)
self.script_path = self.sandbox.path_to_jsbsim_file(
'scripts', 'x153.xml')
self.tree, self.aircraft_name, b = CopyAircraftDef(
self.script_path, self.sandbox)
self.aero2wind = np.mat(np.identity(3))
self.aero2wind[0, 0] *= -1.0
self.aero2wind[2, 2] *= -1.0
self.auxilliary = self.fdm.get_auxiliary()
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 testIndependenceOfInitialLocation(self):
script_path = self.sandbox.path_to_jsbsim_file('scripts/ball.xml')
tree, aircraft_name, _ = CopyAircraftDef(script_path, self.sandbox)
tree.write(
self.sandbox('aircraft', aircraft_name, aircraft_name + '.xml'))
# Alter the initial conditions XML file to force the initial latitude
# to 90 degrees.
_, IC_tree, IC_file = self.getElementTrees(script_path)
IC_root = IC_tree.getroot()
lat_tag = IC_root.find('latitude')
psi_tag = IC_root.find('psi')
alt_tag = IC_root.find('altitude')
psi_tag.text = '90.0' # Heading East
lat_tag.text = '89.9' # Above the North Pole
h0 = float(alt_tag.text)
IC_tree.write(os.path.join('aircraft', aircraft_name, IC_file))
fdm = self.create_fdm()
fdm.set_aircraft_path('aircraft')
self.load_script('ball.xml')
fdm.run_ic()
p = fdm['ic/p-rad_sec']
q = fdm['ic/q-rad_sec']
r = fdm['ic/r-rad_sec']
self.delete_fdm()
# Since the equatorial radius is 70159 ft larger than the polar radius
# we need to decrease the altitude by the same amount in order to
# initialize the vehicle at the same radius.
alt_tag.text = str(h0 - 70159)
psi_tag.text = '0.0' # Heading North
lat_tag.text = '0.0' # Above equator
# Longitude at which the polar orbit tested above would cross the equator
lon_tag = IC_root.find('longitude')
lon_tag.text = '90.0'
IC_tree.write(os.path.join('aircraft', aircraft_name, IC_file))
fdm = self.create_fdm()
fdm.set_aircraft_path('aircraft')
self.load_script('ball.xml')
fdm.run_ic()
self.assertAlmostEqual(fdm['ic/p-rad_sec'], p)
self.assertAlmostEqual(fdm['ic/q-rad_sec'], q)
self.assertAlmostEqual(fdm['ic/r-rad_sec'], r)
def testKinematicNoScale(self):
# Test the <nocale/> feature
script_path = self.sandbox.path_to_jsbsim_file('scripts', 'c1721.xml')
tree, aircraft_name, b = CopyAircraftDef(script_path, self.sandbox)
kinematic_tag = tree.getroot().find('flight_control/channel/kinematic')
et.SubElement(kinematic_tag, 'noscale')
tree.write(
self.sandbox('aircraft', aircraft_name, aircraft_name + '.xml'))
fdm = CreateFDM(self.sandbox)
fdm.set_aircraft_path('aircraft')
fdm.load_model(aircraft_name)
fdm.load_ic('reset00', True)
fdm.run_ic()
fdm['fcs/flap-cmd-norm'] = 12.
ExecuteUntil(fdm, 2.2)
self.assertAlmostEqual(fdm['fcs/flap-pos-deg'], 12.)
def test_alt_mod_vs_CAS(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, b = CopyAircraftDef(script_path, self.sandbox)
self.addPitotTube(tree.getroot(), 10.0)
tree.write(self.sandbox('aircraft', aircraft_name,
aircraft_name+'.xml'))
fdm = CreateFDM(self.sandbox)
fdm.set_aircraft_path('aircraft')
fdm.load_model('Short_S23')
fdm['ic/beta-deg'] = 15.0 # Add some sideslip
fdm['ic/vc-kts'] = 172.0
fdm['ic/h-sl-ft'] = 15000.
self.assertAlmostEqual(fdm['ic/vc-kts'], 172.0, delta=1E-7)
self.assertAlmostEqual(fdm['ic/beta-deg'], 15.0, delta=1E-7)
fdm.run_ic()
self.assertAlmostEqual(fdm['velocities/vc-kts'], 172.0, delta=1E-7)
self.assertAlmostEqual(fdm['aero/beta-deg'], 15.0, delta=1E-7)
def test_trim_with_actuator_delay(self):
# This is a regression test that checks that actuators delays are
# disabled when the trim takes place (GitHub issue #293).
script_path = self.sandbox.path_to_jsbsim_file('scripts', 'c1722.xml')
aircraft_tree, aircraft_name, _ = CopyAircraftDef(
script_path, self.sandbox)
root = aircraft_tree.getroot()
elevator_actuator = root.find(
"flight_control/channel/actuator[@name='fcs/elevator-actuator']")
delay = et.SubElement(elevator_actuator, 'delay')
delay.text = '0.1'
aircraft_tree.write(
self.sandbox('aircraft', aircraft_name, aircraft_name + '.xml'))
fdm = self.create_fdm()
fdm.set_aircraft_path(self.sandbox('aircraft'))
fdm.load_script(script_path)
fdm.run_ic()
while fdm.run():
if fdm['simulation/trim-completed'] == 1:
break
def BuildReference(self, script_name):
# Run the script
self.script = self.sandbox.path_to_jsbsim_file('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['simulation/randomseed'] = 0.0
fdm.run_ic()
ExecuteUntil(fdm, 50.0)
self.ref = pd.read_csv("output.csv", index_col=0)
# 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 = os.path.join('aircraft', self.aircraft_name)
def test_trim_westward(self):
# This is a regression test after the bug reported in GitHub issue #163
# which reports a trim failure when the heading is set to 270 degrees or
# -90 degrees i.e. westward.
script_path = self.sandbox.path_to_jsbsim_file('scripts',
'737_cruise.xml')
aircraft_tree, aircraft_name, b = CopyAircraftDef(
script_path, self.sandbox)
aircraft_tree.write(
self.sandbox('aircraft', aircraft_name, aircraft_name + '.xml'))
IC_file = self.sandbox('aircraft', aircraft_name, 'cruise_init.xml')
tree = et.parse(IC_file)
heading_el = tree.find('psi')
heading_el.text = '270.0'
tree.write(IC_file)
fdm = self.create_fdm()
fdm.set_aircraft_path(self.sandbox('aircraft'))
fdm.load_script(script_path)
fdm.run_ic()
while fdm['simulation/sim-time-sec'] < 6.0:
fdm.run()
def testNorthPoleInitialization(self):
script_path = self.sandbox.path_to_jsbsim_file('scripts/ball.xml')
tree, aircraft_name, _ = CopyAircraftDef(script_path, self.sandbox)
tree.write(
self.sandbox('aircraft', aircraft_name, aircraft_name + '.xml'))
# Alter the initial conditions XML file to force the initial latitude
# to 90 degrees.
_, IC_tree, IC_file = self.getElementTrees(script_path)
IC_root = IC_tree.getroot()
lat_tag = IC_root.find('latitude')
lat_tag.text = '90.0'
IC_tree.write(os.path.join('aircraft', aircraft_name, IC_file))
fdm = self.create_fdm()
fdm.set_aircraft_path('aircraft')
fpectl.turnon_sigfpe()
self.load_script('ball.xml')
fdm.run_ic()
self.assertAlmostEqual(fdm['ic/lat-gc-deg'], 90.)
while fdm['simulation/sim-time-sec'] < 1.:
fdm.run()
fpectl.turnoff_sigfpe()
def AddAccelerometersToAircraft(self, script_path):
tree, aircraft_name, b = CopyAircraftDef(script_path, self.sandbox)
system_tag = et.SubElement(tree.getroot(), 'system')
system_tag.attrib['file'] = 'accelerometers'
tree.write(
self.sandbox('aircraft', aircraft_name, aircraft_name + '.xml'))
def test_input_socket(self):
# The aircraft c172x does not contain an <input> tag so we need
# to add one.
tree, aircraft_name, b = CopyAircraftDef(self.script_path,
self.sandbox)
self.root = tree.getroot()
input_tag = et.SubElement(self.root, 'input')
input_tag.attrib['port'] = '1137'
tree.write(
self.sandbox('aircraft', aircraft_name, aircraft_name + '.xml'))
fdm = CreateFDM(self.sandbox)
fdm.set_aircraft_path('aircraft')
fdm.load_script(self.script_path)
fdm.run_ic()
fdm.hold()
tn = TelnetInterface(fdm, 5., 1137)
self.sanityCheck(tn)
# Check the aircraft name and its version
msg = string.split(tn.sendCommand("info"), '\n')
self.assertEqual(string.strip(string.split(msg[2], ':')[1]),
string.strip(self.root.attrib['name']))
self.assertEqual(string.strip(string.split(msg[1], ':')[1]),
string.strip(self.root.attrib['version']))
# Check that the simulation time is 0.0
self.assertEqual(float(string.strip(string.split(msg[3], ':')[1])),
0.0)
self.assertEqual(tn.getSimTime(), 0.0)
self.assertEqual(tn.getPropertyValue("simulation/sim-time-sec"), 0.0)
# Check that 'iterate' iterates the correct number of times
tn.sendCommand("iterate 19")
self.assertEqual(tn.getSimTime(), 19. * tn.getDeltaT())
self.assertAlmostEqual(tn.getPropertyValue("simulation/sim-time-sec"),
tn.getSimTime(),
delta=1E-5)
# Wait a little bit and make sure that the simulation time has not
# changed meanwhile thus confirming that the simulation is on hold.
tn.wait(0.1)
self.assertEqual(tn.getSimTime(), 19. * tn.getDeltaT())
self.assertAlmostEqual(tn.getPropertyValue("simulation/sim-time-sec"),
tn.getSimTime(),
delta=1E-5)
# Modify the tank[0] contents via the "send" command
half_contents = 0.5 * tn.getPropertyValue(
"propulsion/tank/contents-lbs")
tn.sendCommand("set propulsion/tank/contents-lbs " +
str(half_contents))
self.assertEqual(tn.getPropertyValue("propulsion/tank/contents-lbs"),
half_contents)
# Check the resume/hold commands
tn.setRealTime(True)
t = tn.getSimTime()
tn.sendCommand("resume")
tn.wait(0.5)
self.assertNotEqual(tn.getSimTime(), t)
tn.wait(0.5)
tn.sendCommand("hold")
tn.setRealTime(False)
t = tn.getSimTime()
self.assertAlmostEqual(tn.getPropertyValue("simulation/sim-time-sec"),
t,
delta=1E-5)
# Wait a little bit and make sure that the simulation time has not
# changed meanwhile thus confirming that the simulation is on hold.
tn.wait(0.1)
self.assertEqual(tn.getSimTime(), t)
self.assertAlmostEqual(tn.getPropertyValue("simulation/sim-time-sec"),
t,
delta=1E-5)
def test_point_mass_inertia(self):
script_path = self.sandbox.path_to_jsbsim_file('scripts', 'J2460.xml')
fdm = CreateFDM(self.sandbox)
fdm.set_output_directive(
self.sandbox.path_to_jsbsim_file('tests', 'output.xml'))
fdm.load_script(script_path)
fdm.run_ic()
ExecuteUntil(fdm, 50.0)
ref = pd.read_csv("output.csv", index_col=0)
tree, aircraft_name, path_to_jsbsim_aircrafts = CopyAircraftDef(
script_path, self.sandbox)
pointmass_element = tree.getroot().find(
'mass_balance/pointmass//form/..')
weight_element = pointmass_element.find('weight')
weight = float(weight_element.text)
form_element = pointmass_element.find('form')
radius_element = form_element.find('radius')
radius, length = (0.0, 0.0)
if radius_element is not None:
radius = float(radius_element.text)
length_element = form_element.find('length')
if length_element is not None:
length = float(length_element.text)
shape = form_element.attrib['shape']
pointmass_element.remove(form_element)
inertia = np.zeros((3, 3))
if string.strip(shape) == 'tube':
inertia[0, 0] = radius * radius
inertia[1, 1] = (6.0 * inertia[0, 0] + length * length) / 12.0
inertia[2, 2] = inertia[1, 1]
inertia = inertia * weight / 32.174049 # converting slugs to lbs
ixx_element = et.SubElement(pointmass_element, 'ixx')
ixx_element.text = str(inertia[0, 0])
iyy_element = et.SubElement(pointmass_element, 'iyy')
iyy_element.text = str(inertia[1, 1])
izz_element = et.SubElement(pointmass_element, 'izz')
izz_element.text = str(inertia[2, 2])
tree.write(
self.sandbox('aircraft', aircraft_name, aircraft_name + '.xml'))
# 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
fdm = CreateFDM(self.sandbox)
fdm.set_aircraft_path('aircraft')
fdm.set_output_directive(
self.sandbox.path_to_jsbsim_file('tests', 'output.xml'))
fdm.load_script(script_path)
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(ref, mod))
# Find all the data that are differing by more than 1E-8 between the
# two data sets.
diff = FindDifferences(ref, mod, 1E-8)
self.longMessage = True
self.assertEqual(len(diff), 0, msg='\n' + diff.to_string())
