def test_class_one(self):
print '==================== Main start ==================== ' + time.strftime(
"%c")
t0 = time.clock()
print "time start= {0}".format(t0)
atmosphere = Atmosphere()
t1 = time.clock()
print "simulation time= {0} - simulation duration= {1:3.10f} seconds".format(
t1, (t1 - t0))
print '==================== load airports ==================== ' + time.strftime(
"%c")
airportsDB = AirportsDatabase()
assert airportsDB.read()
print '==================== air density at airports field elevation ==================== ' + time.strftime(
"%c")
for airport in airportsDB.getAirports():
print '=======================' + airport.getName(
) + '===================='
print 'field elevation= ' + str(
airport.getFieldElevationAboveSeaLevelMeters()) + ' meters'
altitudeMeters = airport.getFieldElevationAboveSeaLevelMeters()
print 'air density= ' + str(
atmosphere.getAirDensityKilogramsPerCubicMeters(
altitudeMeters)) + ' kg / meters ^^ 3'
def test_class_two(self):
print '==================== Main start ==================== ' + time.strftime(
"%c")
t0 = time.clock()
print "time start= {0}".format(t0)
atmosphere = Atmosphere()
t1 = time.clock()
print "simulation time= {0} - simulation duration= {1:3.10f} seconds".format(
t1, (t1 - t0))
altitudeMeters = 10.0
print 'air density= ' + str(
atmosphere.getAirDensityKilogramsPerCubicMeters(
altitudeMeters)) + ' kg / meters ^^ 3'
print '==================== air density at given altitudes ==================== ' + time.strftime(
"%c")
for altitudeMeters in ['10.0', '1000.0', '2000.0', '3000.0', '4000.0']:
strMsg = 'altitude= ' + str(
altitudeMeters) + ' meters ... air density= '
strMsg += str(
atmosphere.getAirDensityKilogramsPerCubicMeters(
float(altitudeMeters)))
strMsg += ' kg / cubic meters'
print strMsg
def getAircraft(self, aircraftICAOcode):
print(self.className +
': ================ get aircraft =================')
atmosphere = Atmosphere()
earth = Earth()
acBd = BadaAircraftDatabase()
assert acBd.read()
if (acBd.aircraftExists(aircraftICAOcode)
and acBd.aircraftPerformanceFileExists(aircraftICAOcode)):
print(self.className + ': performance file= {0}'.format(
acBd.getAircraftPerformanceFile(aircraftICAOcode)))
self.aircraft = BadaAircraft(
ICAOcode=aircraftICAOcode,
aircraftFullName=acBd.getAircraftFullName(aircraftICAOcode),
badaPerformanceFilePath=acBd.getAircraftPerformanceFile(
aircraftICAOcode),
atmosphere=atmosphere,
earth=earth,
windSpeedMetersPerSecond=None,
windDirectionDegrees=None)
self.aircraft.dump()
else:
raise ValueError(self.className + ': aircraft not found= ' +
self.aircraftICAOcode)
def test_Class_Two(self):
print('================ test Two ====================')
acBd = BadaAircraftDatabase()
assert acBd.read()
atmosphere = Atmosphere()
earth = Earth()
aircraftICAOcode = 'A320'
if ( acBd.aircraftExists(aircraftICAOcode) and
acBd.aircraftPerformanceFileExists(aircraftICAOcode)):
print(acBd.getAircraftFullName(aircraftICAOcode))
aircraftPerformance = AircraftPerformance(acBd.getAircraftPerformanceFile(aircraftICAOcode))
aeroDynamics = AeroDynamics(aircraftPerformance, atmosphere, earth)
print(aeroDynamics)
phase = 'XX'
try:
print(aeroDynamics.getDragCoeff(phase))
except Exception as e:
print('test two = {0}'.format(e))
self.assertTrue(isinstance(e, AssertionError))
def setUp(self) -> None:
self.deltaTimeSeconds = 1.0
atmosphere = Atmosphere()
earth = Earth()
print('==================== Aircraft ==================== ' +
time.strftime("%c"))
acBd = BadaAircraftDatabase()
aircraftICAOcode = 'A320'
if acBd.read():
if (acBd.aircraftExists(aircraftICAOcode)
and acBd.aircraftPerformanceFileExists(aircraftICAOcode)):
print(
'==================== aircraft found ==================== '
+ time.strftime("%c"))
self.aircraft = BadaAircraft(
ICAOcode=aircraftICAOcode,
aircraftFullName=acBd.getAircraftFullName(
aircraftICAOcode),
badaPerformanceFilePath=acBd.getAircraftPerformanceFile(
aircraftICAOcode),
atmosphere=atmosphere,
earth=earth,
windSpeedMetersPerSecond=None,
windDirectionDegrees=None)
print(self.aircraft)
assert not (self.aircraft is None)
def getAircraft(self):
print(self.className +
': ================ get aircraft =================')
atmosphere = Atmosphere()
earth = Earth()
acBd = BadaAircraftDatabase()
assert acBd.read()
if (acBd.aircraftExists(self.aircraftICAOcode)
and acBd.aircraftPerformanceFileExists(self.aircraftICAOcode)):
print(self.className + ': performance file= {0}'.format(
acBd.getAircraftPerformanceFile(self.aircraftICAOcode)))
self.aircraft = BadaAircraft(
ICAOcode=self.aircraftICAOcode,
aircraftFullName=acBd.getAircraftFullName(
self.aircraftICAOcode),
badaPerformanceFilePath=acBd.getAircraftPerformanceFile(
self.aircraftICAOcode),
atmosphere=atmosphere,
earth=earth)
self.aircraft.dump()
else:
raise ValueError(self.className + ': aircraft not found= ' +
self.aircraftICAOcode)
def test_Class_One(self):
print('================ test one ====================')
acBd = BadaAircraftDatabase()
assert acBd.read()
atmosphere = Atmosphere()
earth = Earth()
aircraftICAOcode = 'A320'
if ( acBd.aircraftExists(aircraftICAOcode) and
acBd.aircraftPerformanceFileExists(aircraftICAOcode)):
print(acBd.getAircraftFullName(aircraftICAOcode))
aircraftPerformance = AircraftPerformance(acBd.getAircraftPerformanceFile(aircraftICAOcode))
aeroDynamics = AeroDynamics(aircraftPerformance, atmosphere, earth)
print(aeroDynamics)
for phase in ['CR', 'IC', 'TO', 'AP', 'LD']:
print('phase= {0} - Vstall CAS= {1} knots'.format(phase, aeroDynamics.getVstallKcas(phase)))
for phase in ['CR', 'IC', 'TO', 'AP', 'LD']:
print('phase= {0} - Drag Coeff= {1}'.format(phase, aeroDynamics.getDragCoeff(phase)))
print('Wing Area Surface={0} Square-meters'.format(aeroDynamics.getWingAreaSurfaceSquareMeters()))
def test_Vstall(self):
t0 = time.clock()
print("time start= ", t0)
atmosphere = Atmosphere()
earth = Earth()
print(
'==================== Stall Speed according to airport field elevation ==================== '
+ time.strftime("%c"))
acBd = BadaAircraftDatabase()
aircraftICAOcode = 'B743'
if acBd.read():
if (acBd.aircraftExists(aircraftICAOcode)
and acBd.aircraftPerformanceFileExists(
acBd.getAircraftPerformanceFile(aircraftICAOcode))):
print(
'==================== aircraft found ==================== '
+ time.strftime("%c"))
aircraft = BadaAircraft(
ICAOcode=aircraftICAOcode,
aircraftFullName=acBd.getAircraftFullName(
aircraftICAOcode),
badaPerformanceFilePath=acBd.getAircraftPerformanceFile(
aircraftICAOcode),
atmosphere=atmosphere,
earth=earth)
aircraft.dump()
print('==================== Airport database ==================== ' +
time.strftime("%c"))
airportsDB = AirportsDatabase()
assert airportsDB.read()
for airport in airportsDB.getAirports():
print('============' + airport.getName() + ' ============')
#print airport
aircraft = BadaAircraft(
ICAOcode=aircraftICAOcode,
aircraftFullName=acBd.getAircraftFullName(aircraftICAOcode),
badaPerformanceFilePath=acBd.getAircraftPerformanceFile(
aircraftICAOcode),
atmosphere=atmosphere,
earth=earth)
print('airport field elevation= {0:.2f} meters'.format(
airport.getFieldElevationAboveSeaLevelMeters()))
CAS = aircraft.computeStallSpeedCasKnots()
print('V stall Calibrated AirSpeed= {0:.2f} knots'.format(CAS))
TAS = cas2tas(
cas=CAS,
altitude=airport.getFieldElevationAboveSeaLevelMeters(),
temp='std',
speed_units='kt',
alt_units='m',
temp_units=default_temp_units,
)
print('V stall True AirSpeed= {0:.2f} knots'.format(TAS))
def test_class_one(self):
print '==================== Main start ==================== '+ time.strftime("%c")
t0 = time.clock()
print "time start= {0}".format( t0)
atmosphere = Atmosphere()
t1 = time.clock()
print "simulation time= {0} - simulation duration= {1:3.10f} seconds".format(t1 , (t1-t0))
print '==================== load airports ==================== '+ time.strftime("%c")
airportsDB = AirportsDatabase()
assert airportsDB.read()
print '==================== air density at airports field elevation ==================== '+ time.strftime("%c")
for airport in airportsDB.getAirports():
print '=======================' + airport.getName() + '===================='
print 'field elevation= ' + str(airport.getFieldElevationAboveSeaLevelMeters()) + ' meters'
altitudeMeters = airport.getFieldElevationAboveSeaLevelMeters()
print 'air density= ' + str(atmosphere.getAirDensityKilogramsPerCubicMeters(altitudeMeters)) + ' kg / meters ^^ 3'
def test_class_two(self):
print '==================== Main start ==================== '+ time.strftime("%c")
t0 = time.clock()
print "time start= {0}".format( t0)
atmosphere = Atmosphere()
t1 = time.clock()
print "simulation time= {0} - simulation duration= {1:3.10f} seconds".format(t1 , (t1-t0))
altitudeMeters = 10.0
print 'air density= ' + str(atmosphere.getAirDensityKilogramsPerCubicMeters(altitudeMeters)) + ' kg / meters ^^ 3'
print '==================== air density at given altitudes ==================== '+ time.strftime("%c")
for altitudeMeters in ['10.0', '1000.0', '2000.0', '3000.0', '4000.0']:
strMsg = 'altitude= ' + str(altitudeMeters) + ' meters ... air density= '
strMsg += str(atmosphere.getAirDensityKilogramsPerCubicMeters(float(altitudeMeters)))
strMsg += ' kg / cubic meters'
print strMsg
def setUp(self) -> None:
self.atmosphere = Atmosphere()
self.earth = Earth()
self.acBd = BadaAircraftDatabase()
self.aircraftICAOcode = 'A320'
self.deltaTimeSeconds = 1.0
assert self.acBd.read()
assert self.acBd.aircraftExists(self.aircraftICAOcode)
assert self.acBd.aircraftPerformanceFileExists(self.aircraftICAOcode)
self.aircraft = BadaAircraft(
ICAOcode=self.aircraftICAOcode,
aircraftFullName=self.acBd.getAircraftFullName(
self.aircraftICAOcode),
badaPerformanceFilePath=self.acBd.getAircraftPerformanceFile(
self.aircraftICAOcode),
atmosphere=self.atmosphere,
earth=self.earth,
windSpeedMetersPerSecond=None,
windDirectionDegrees=None)
def test_Class_One(self):
print('================ test one ====================')
acBd = BadaAircraftDatabase()
assert acBd.read()
atmosphere = Atmosphere()
earth = Earth()
aircraftICAOcode = 'A320'
if (acBd.aircraftExists(aircraftICAOcode)
and acBd.aircraftPerformanceFileExists(aircraftICAOcode)):
print(acBd.getAircraftFullName(aircraftICAOcode))
aircraftPerformance = AircraftPerformance(
acBd.getAircraftPerformanceFile(aircraftICAOcode))
flightEnvelope = FlightEnvelope(
aircraftPerformance=aircraftPerformance,
ICAOcode=aircraftICAOcode,
atmosphere=atmosphere,
earth=earth)
print(flightEnvelope)
from Home.Guidance.GroundRunLegFile import GroundRunLeg
from Home.Guidance.DescentGlideSlopeFile import DescentGlideSlope
from Home.BadaAircraftPerformance.BadaAircraftDatabaseFile import BadaAircraftDatabase
from Home.BadaAircraftPerformance.BadaAircraftFile import BadaAircraft
Knots2MetersPerSecond = 0.514444444
if __name__ == '__main__':
t0 = time.clock()
print("time start= ", t0)
print('================ get aircraft =================')
aircraftIcaoCode = 'A320'
atmosphere = Atmosphere()
earth = Earth()
acBd = BadaAircraftDatabase()
assert acBd.read()
if (acBd.aircraftExists(aircraftIcaoCode)
and acBd.aircraftPerformanceFileExists(
acBd.getAircraftPerformanceFile(aircraftIcaoCode))):
aircraft = BadaAircraft(
aircraftIcaoCode,
acBd.getAircraftPerformanceFile(aircraftIcaoCode), atmosphere,
earth)
aircraft.dump()
else:
def test_DescentGlideSlope(self):
atmosphere = Atmosphere()
earth = Earth()
print '==================== three degrees Descent Slope Start ==================== ' + time.strftime(
"%c")
acBd = BadaAircraftDatabase()
aircraftICAOcode = 'A320'
if acBd.read():
if (acBd.aircraftExists(aircraftICAOcode)
and acBd.aircraftPerformanceFileExists(aircraftICAOcode)):
print '==================== aircraft found ==================== ' + time.strftime(
"%c")
aircraft = BadaAircraft(
ICAOcode=aircraftICAOcode,
aircraftFullName=acBd.getAircraftFullName(
aircraftICAOcode),
badaPerformanceFilePath=acBd.getAircraftPerformanceFile(
aircraftICAOcode),
atmosphere=atmosphere,
earth=earth)
aircraft.dump()
assert not (aircraft is None)
print '==================== runways database ==================== ' + time.strftime(
"%c")
runWaysDatabase = RunWayDataBase()
assert runWaysDatabase.read()
runway = runWaysDatabase.getFilteredRunWays(airportICAOcode='LFML',
runwayName='')
print runway
print "=========== arrival airport =========== " + time.strftime("%c")
airportsDB = AirportsDatabase()
assert (airportsDB.read())
MarseilleMarignane = airportsDB.getAirportFromICAOCode('LFML')
print MarseilleMarignane
print "=========== descent glide slope =========== " + time.strftime(
"%c")
threeDegreesGlideSlope = DescentGlideSlope(
runway=runway,
aircraft=aircraft,
arrivalAirport=MarseilleMarignane)
initialWayPoint = WayPoint(Name='startOfDescentGlideSlope', )
print "=========== DescentGlideSlope build the glide slope =========== " + time.strftime(
"%c")
# threeDegreesGlideSlope.buildGlideSlope(deltaTimeSeconds = 0.1,
# elapsedTimeSeconds = 0.0,
# initialWayPoint = None,
# flownDistanceMeters = 0.0,
# distanceStillToFlyMeters = 100000.0,
# distanceToLastFixMeters = 100000.0)
threeDegreesGlideSlope.buildSimulatedGlideSlope(
descentGlideSlopeSizeNautics=5.0)
print "=========== DescentGlideSlope =========== " + time.strftime(
"%c")
for node in threeDegreesGlideSlope.getVertices():
print node
print "=========== DescentGlideSlope length =========== " + time.strftime(
"%c")
print "get number of vertices= {0}".format(
threeDegreesGlideSlope.getNumberOfVertices())
print "get number of edges= {0}".format(
threeDegreesGlideSlope.getNumberOfEdges())
print 'Glide Slope overall length= {0} meters'.format(
threeDegreesGlideSlope.computeLengthMeters())
threeDegreesGlideSlope.createKmlOutputFile()
threeDegreesGlideSlope.createXlsxOutputFile()
print '==================== three degrees Descent Slope End ==================== ' + time.strftime(
"%c")
def test_One(self):
print('=========== main start ==================')
aircraftICAOcode = 'A320'
atmosphere = Atmosphere()
assert (not (atmosphere is None))
earth = Earth()
assert (not (earth is None))
acBd = BadaAircraftDatabase()
assert acBd.read()
if (acBd.aircraftExists(aircraftICAOcode)
and acBd.aircraftPerformanceFileExists(aircraftICAOcode)):
aircraft = BadaAircraft(
ICAOcode=aircraftICAOcode,
aircraftFullName=acBd.getAircraftFullName(aircraftICAOcode),
badaPerformanceFilePath=acBd.getAircraftPerformanceFile(
aircraftICAOcode),
atmosphere=atmosphere,
earth=earth)
aircraft.dump()
else:
raise ValueError(': aircraft not found= ' + aircraftICAOcode)
assert not (aircraft is None)
print('================ load airports =================')
airportsDB = AirportsDatabase()
assert (airportsDB.read())
adepIcaoCode = 'LFML'
departureAirport = airportsDB.getAirportFromICAOCode(adepIcaoCode)
print(': departure airport= ' + str(departureAirport))
assert not (departureAirport is None)
print('================ load runways =================')
runWaysDatabase = RunWayDataBase()
assert (runWaysDatabase.read())
print('==================== take off run-way ==================== ')
departureRunway = runWaysDatabase.getFilteredRunWays(adepIcaoCode)
print(
'=========== minimum and maximum aircraft mass ==================')
minMassKg = aircraft.getMinimumMassKilograms()
print('aircraft minimum mass: ' + str(minMassKg) + ' kilograms')
maxMassKg = aircraft.getMaximumMassKilograms()
print('aircraft maximum mass: ' + str(maxMassKg) + ' kilograms')
deltaMass = maxMassKg - minMassKg
massKg = 39000.0
while (massKg < maxMassKg):
massKg += 1000.0
print(
'==================== set aircraft reference mass ==================== '
)
aircraft = BadaAircraft(
ICAOcode=aircraftICAOcode,
aircraftFullName=acBd.getAircraftFullName(aircraftICAOcode),
badaPerformanceFilePath=acBd.getAircraftPerformanceFile(
aircraftICAOcode),
atmosphere=atmosphere,
earth=earth)
aircraft.setTargetCruiseFlightLevel(
310, departureAirport.getFieldElevationAboveSeaLevelMeters())
print(
'==================== aircraft reference mass ==================== '
)
print('aircraft reference mass= ' + str(massKg) + ' Kilograms')
aircraft.setAircraftMassKilograms(massKg)
print(
'==================== begin of ground run ==================== '
)
groundRunLeg = GroundRunLeg(runway=departureRunway,
aircraft=aircraft,
airport=departureAirport)
groundRunLeg.buildDepartureGroundRun(
deltaTimeSeconds=0.1,
elapsedTimeSeconds=0.0,
distanceStillToFlyMeters=500000.0,
distanceToLastFixMeters=500000.0)
groundRunLeg.computeLengthMeters()
#groundRunLeg.createXlsxOutputFile()
print(
'==================== end of ground run ==================== ')
initialWayPoint = groundRunLeg.getLastVertex().getWeight()
print(
'==================== dump aircraft speed profile ==================== '
)
aircraft.createStateVectorOutputFile(aircraftICAOcode + "-Mass-" +
str(massKg))
print('=========== main end ==================')
def test_TurnLeg(self):
print '==================== Turn Leg ==================== ' + time.strftime(
"%c")
atmosphere = Atmosphere()
earth = Earth()
acBd = BadaAircraftDatabase()
aircraftICAOcode = 'A320'
assert acBd.read()
assert acBd.aircraftExists(aircraftICAOcode)
assert acBd.aircraftPerformanceFileExists(aircraftICAOcode)
print '==================== aircraft found ==================== ' + time.strftime(
"%c")
aircraft = BadaAircraft(
ICAOcode=aircraftICAOcode,
aircraftFullName=acBd.getAircraftFullName(aircraftICAOcode),
badaPerformanceFilePath=acBd.getAircraftPerformanceFile(
aircraftICAOcode),
atmosphere=atmosphere,
earth=earth)
aircraft.dump()
print '==================== Get Airport ==================== ' + time.strftime(
"%c")
airportsDB = AirportsDatabase()
assert airportsDB.read()
print '==================== Get Arrival Airport ==================== ' + time.strftime(
"%c")
Lisbonne = airportsDB.getAirportFromICAOCode('LPPT')
print Lisbonne
print '==================== find the run-ways ==================== ' + time.strftime(
"%c")
runWaysDatabase = RunWayDataBase()
if runWaysDatabase.read():
print 'runways DB correctly read'
print '==================== take off run-way ==================== ' + time.strftime(
"%c")
arrivalRunway = runWaysDatabase.getFilteredRunWays(
airportICAOcode='LPPT', runwayName='')
print arrivalRunway
print '==================== Ground run ==================== ' + time.strftime(
"%c")
groundRun = GroundRunLeg(runway=arrivalRunway,
aircraft=aircraft,
airport=Lisbonne)
touchDownWayPoint = groundRun.computeTouchDownWayPoint()
print touchDownWayPoint
groundRun.buildDepartureGroundRun(deltaTimeSeconds=1.0,
elapsedTimeSeconds=0.0,
distanceStillToFlyMeters=0.0,
distanceToLastFixMeters=0.0)
print '==================== Climb Ramp ==================== ' + time.strftime(
"%c")
initialWayPoint = groundRun.getLastVertex().getWeight()
descentGlideSlope = DescentGlideSlope(runway=arrivalRunway,
aircraft=aircraft,
arrivalAirport=Lisbonne,
descentGlideSlopeDegrees=3.0)
''' if there is a fix nearer to 5 nautics of the touch-down then limit size of simulated glide slope '''
descentGlideSlope.buildSimulatedGlideSlope(
descentGlideSlopeSizeNautics=5.0)
descentGlideSlope.createKmlOutputFile()
firstGlideSlopeWayPoint = descentGlideSlope.getVertex(v=0).getWeight()
print '==================== Climb Ramp ==================== ' + time.strftime(
"%c")
initialWayPoint = groundRun.getLastVertex().getWeight()
print ' ================== turn leg end =============== '
wayPointsDb = WayPointsDatabase()
assert (wayPointsDb.read())
Exona = wayPointsDb.getWayPoint('EXONA')
Rosal = wayPointsDb.getWayPoint('ROSAL')
print Rosal.getBearingDegreesTo(Exona)
initialHeadingDegrees = arrivalRunway.getTrueHeadingDegrees()
lastTurnLeg = TurnLeg(initialWayPoint=firstGlideSlopeWayPoint,
finalWayPoint=Exona,
initialHeadingDegrees=initialHeadingDegrees,
aircraft=aircraft,
reverse=True)
deltaTimeSeconds = 1.0
lastTurnLeg.buildNewSimulatedArrivalTurnLeg(
deltaTimeSeconds=deltaTimeSeconds,
elapsedTimeSeconds=0.0,
distanceStillToFlyMeters=0.0,
simulatedAltitudeSeaLevelMeters=firstGlideSlopeWayPoint.
getAltitudeMeanSeaLevelMeters(),
flightPathAngleDegrees=3.0)
lastTurnLeg.createKmlOutputFile()
descentGlideSlope.addGraph(lastTurnLeg)
#descentGlideSlope.createXlsxOutputFile()
descentGlideSlope.createKmlOutputFile()
print ' ================== turn leg end =============== '
@author: rjdverbeek <*****@*****.**>
'''
from Home.aerocalc.airspeed import tas2cas, cas2tas
from Home.Environment.Atmosphere import Atmosphere
from Home.Environment.Earth import Earth
from Home.BadaAircraftPerformance.BadaAircraftDatabaseFile import BadaAircraftDatabase
from Home.BadaAircraftPerformance.BadaAircraftFile import BadaAircraft
if __name__ == '__main__':
atmosphere = Atmosphere()
print ( '=========== main start ==================' )
for tas in range(0,100,1):
cas1 = tas2cas(tas = tas , altitude = 100.0, temp='std', speed_units = 'm/s', alt_units='m')
cas2 = atmosphere.tas2cas(tas, altitude = 100.0, speed_units = 'm/s', alt_units = 'm')
print ( tas, cas1, cas2 )
print ( '=========== main start ==================' )
for altitude in range(0, 10000, 100):
cas = 100.0 # 100 m/s
tas1 = cas2tas(cas = cas, altitude = altitude, temp='std', speed_units = 'm/s', alt_units='m')
tas2 = atmosphere.cas2tas(cas = cas, altitudeMeters = altitude, speed_units = 'm/s', altitude_units = 'm')
print ( 'altitude= {0} meters ... cas= {1} m/s constant ... tas1= {2} m/s ... tas2= {3} m/s'.format(altitude, cas, tas1, tas2) )
from Home.Environment.Earth import Earth
from Home.OutputFiles.XlsxOutputFile import XlsxOutput
Meter2Feet = 3.2808
Knots2MetersPerSecond = 0.514444444
#============================================
if __name__ == '__main__':
FileName = "FlightEnvelope.xlsx"
print("=================== Flight Envelope start======================")
aircraftIcaoCode = 'A320'
atmosphere = Atmosphere()
assert not (atmosphere is None)
earth = Earth()
assert not (earth is None)
acBd = BadaAircraftDatabase()
assert acBd.read()
assert acBd.aircraftExists(aircraftIcaoCode)
assert acBd.aircraftPerformanceFileExists(aircraftIcaoCode)
aircraft = BadaAircraft(aircraftIcaoCode,
acBd.getAircraftFullName(aircraftIcaoCode),
acBd.getAircraftPerformanceFile(aircraftIcaoCode),
atmosphere, earth)
def test_DescentGlideSlope_Two(self):
atmosphere = Atmosphere()
earth = Earth()
print(
'==================== three degrees Descent Slope Start ==================== '
+ time.strftime("%c"))
acBd = BadaAircraftDatabase()
aircraftICAOcode = 'A320'
aircraft = None
if acBd.read():
if (acBd.aircraftExists(aircraftICAOcode)
and acBd.aircraftPerformanceFileExists(aircraftICAOcode)):
print(
'==================== aircraft found ==================== '
+ time.strftime("%c"))
aircraft = BadaAircraft(
ICAOcode=aircraftICAOcode,
aircraftFullName=acBd.getAircraftFullName(
aircraftICAOcode),
badaPerformanceFilePath=acBd.getAircraftPerformanceFile(
aircraftICAOcode),
atmosphere=atmosphere,
earth=earth)
aircraft.dump()
assert not (aircraft is None)
print('==================== runways database ==================== ' +
time.strftime("%c"))
runWaysDatabase = RunWayDataBase()
assert runWaysDatabase.read()
runway = runWaysDatabase.getFilteredRunWays(airportICAOcode='LFPG',
runwayName='08L')
print(runway)
print("=========== airports =========== " + time.strftime("%c"))
airportsDB = AirportsDatabase()
assert (airportsDB.read())
CharlesDeGaulle = airportsDB.getAirportFromICAOCode('LFPG')
print(CharlesDeGaulle)
print("=========== descent glide slope =========== " +
time.strftime("%c"))
threeDegreesGlideSlope = DescentGlideSlope(
runway=runway, aircraft=aircraft, arrivalAirport=CharlesDeGaulle)
threeDegreesGlideSlope.buildSimulatedGlideSlope(
descentGlideSlopeSizeNautics=5.0)
print("=========== DescentGlideSlope =========== " +
time.strftime("%c"))
for node in threeDegreesGlideSlope.getVertices():
print(node)
print("=========== DescentGlideSlope length =========== " +
time.strftime("%c"))
print("get number of vertices= {0}".format(
threeDegreesGlideSlope.getNumberOfVertices()))
print("get number of edges= {0}".format(
threeDegreesGlideSlope.getNumberOfEdges()))
print('Glide Slope overall length= {0} meters'.format(
threeDegreesGlideSlope.computeLengthMeters()))
threeDegreesGlideSlope.createKmlOutputFile()
threeDegreesGlideSlope.createXlsxOutputFile()
print(
'==================== three degrees Descent Slope End ==================== '
+ time.strftime("%c"))
def test_ClimbRamp(self):
atmosphere = Atmosphere()
earth = Earth()
print '==================== Three Degrees climb slope ==================== ' + time.strftime(
"%c")
acBd = BadaAircraftDatabase()
aircraftICAOcode = 'A320'
if acBd.read():
if (acBd.aircraftExists(aircraftICAOcode)
and acBd.aircraftPerformanceFileExists(aircraftICAOcode)):
print '==================== aircraft found ==================== ' + time.strftime(
"%c")
aircraft = BadaAircraft(
ICAOcode=aircraftICAOcode,
aircraftFullName=acBd.getAircraftFullName(
aircraftICAOcode),
badaPerformanceFilePath=acBd.getAircraftPerformanceFile(
aircraftICAOcode),
atmosphere=atmosphere,
earth=earth)
aircraft.dump()
assert not (aircraft is None)
print '==================== get Charles Gaulle airport ==================== ' + time.strftime(
"%c")
airportsDB = AirportsDatabase()
assert (airportsDB.read())
CharlesDeGaulle = airportsDB.getAirportFromICAOCode('LFPG')
print CharlesDeGaulle
assert not (aircraft is None)
aircraft.setTargetCruiseFlightLevel(
RequestedFlightLevel=390,
departureAirportAltitudeMSLmeters=CharlesDeGaulle.
getAltitudeMeanSeaLevelMeters())
print '==================== Three Degrees climb slope==================== ' + time.strftime(
"%c")
runWaysDatabase = RunWayDataBase()
if runWaysDatabase.read():
print 'runways DB correctly read'
runway = runWaysDatabase.getFilteredRunWays('LFPG')
print runway
print '==================== Ground Run ==================== ' + time.strftime(
"%c")
groundRun = GroundRunLeg(runway=runway,
aircraft=aircraft,
airport=CharlesDeGaulle)
groundRun.buildDepartureGroundRun(deltaTimeSeconds=0.1,
elapsedTimeSeconds=0.0,
distanceStillToFlyMeters=100000.0,
distanceToLastFixMeters=100000.0)
print '==================== Three Degrees climb slope==================== ' + time.strftime(
"%c")
initialVertex = groundRun.getVertex(groundRun.getNumberOfVertices() -
1)
initialWayPoint = initialVertex.getWeight()
climbRamp = ClimbRamp(initialWayPoint=initialWayPoint,
runway=runway,
aircraft=aircraft,
departureAirport=CharlesDeGaulle)
climbRamp.buildClimbRamp(deltaTimeSeconds=0.1,
elapsedTimeSeconds=0.0,
distanceStillToFlyMeters=100000.0,
distanceToLastFixMeters=100000.0,
climbRampLengthNautics=5.0)
groundRun.addGraph(climbRamp)
groundRun.createKmlOutputFile()
print "=========== ThreeDegreesGlideSlope end =========== " + time.strftime(
"%c")
def test_Two(self):
t0 = time.clock()
print ( " ========== Great Circle ======= time start= ", t0 )
atmosphere = Atmosphere()
earth = Earth()
print ( '==================== Great Circle ==================== '+ time.strftime("%c") )
acBd = BadaAircraftDatabase()
aircraftICAOcode = 'A320'
if acBd.read():
if ( acBd.aircraftExists(aircraftICAOcode)
and acBd.aircraftPerformanceFileExists(aircraftICAOcode)):
print ( '==================== aircraft found ==================== '+ time.strftime("%c") )
aircraft = BadaAircraft(ICAOcode = aircraftICAOcode,
aircraftFullName = acBd.getAircraftFullName(aircraftICAOcode),
badaPerformanceFilePath = acBd.getAircraftPerformanceFile(aircraftICAOcode),
atmosphere = atmosphere,
earth = earth)
print ( aircraft )
else:
print ( '==================== airport database ==================== '+ time.strftime("%c") )
airportsDB = AirportsDatabase()
assert not(airportsDB is None)
wayPointsDb = WayPointsDatabase()
assert (wayPointsDb.read())
initialWayPoint = wayPointsDb.getWayPoint('TOU')
finalWayPoint = wayPointsDb.getWayPoint('ALIVA')
print ( initialWayPoint.getBearingDegreesTo(finalWayPoint) )
print ( finalWayPoint.getBearingDegreesTo(initialWayPoint) )
''' departure ground run => initial speed is null '''
trueAirSpeedMetersSecond = 70.0
elapsedTimeSeconds = 0.0
aircraft.setCurrentAltitudeSeaLevelMeters(
elapsedTimeSeconds = 0.0 ,
altitudeMeanSeaLevelMeters = 0.0,
lastAltitudeMeanSeaLevelMeters = 0.0,
targetCruiseAltitudeMslMeters = 10000.0)
aircraft.initStateVector(
elapsedTimeSeconds = 0.0,
trueAirSpeedMetersSecond = 70.0,
airportFieldElevationAboveSeaLevelMeters = 152.0)
aircraft.setTargetCruiseFlightLevel(RequestedFlightLevel = 310,
departureAirportAltitudeMSLmeters = 152.0)
print ( "=========== simulated descent glide slope =========== " + time.strftime("%c") )
MarseilleMarignane = airportsDB.getAirportFromICAOCode('LFML')
print ( '==================== runways database ==================== '+ time.strftime("%c") )
runWaysDatabase = RunWayDataBase()
assert runWaysDatabase.read()
runway = runWaysDatabase.getFilteredRunWays(airportICAOcode = 'LFML', runwayName = '')
arrivalGroundRun = GroundRunLeg( runway = runway,
aircraft = aircraft,
airport = MarseilleMarignane )
touchDownWayPoint = arrivalGroundRun.computeTouchDownWayPoint()
aircraft.setArrivalRunwayTouchDownWayPoint(touchDownWayPoint)
threeDegreesGlideSlope = DescentGlideSlope(runway = runway,
aircraft = aircraft,
arrivalAirport = MarseilleMarignane )
threeDegreesGlideSlope.buildSimulatedGlideSlope(descentGlideSlopeSizeNautics = 5.0)
approachWayPoint = threeDegreesGlideSlope.getLastVertex().getWeight()
aircraft.setTargetApproachWayPoint(approachWayPoint)
''' =================================='''
greatCircle = GreatCircleRoute(initialWayPoint = initialWayPoint,
finalWayPoint = finalWayPoint,
aircraft = aircraft)
distanceStillToFlyMeters = initialWayPoint.getDistanceMetersTo(approachWayPoint)
greatCircle.computeGreatCircle(
deltaTimeSeconds = 0.1,
elapsedTimeSeconds = 0.0,
distanceStillToFlyMeters = distanceStillToFlyMeters,
distanceToLastFixMeters = distanceStillToFlyMeters)
print ( 'main great circle length= ' + str(greatCircle.computeLengthMeters()) + ' meters' )
greatCircle.createKmlOutputFile()
greatCircle.createXlsxOutputFile()
