tasMetersPerSecond = atmosphere.cas2tas(casMetersPerSecond,
950.0,
speed_units='m/s',
altitude_units='m')
elapsedTimeSeconds = 0.0
aircraft.initStateVector(
elapsedTimeSeconds=elapsedTimeSeconds,
trueAirSpeedMetersSecond=tasMetersPerSecond,
altitudeMeanSeaLevelMeters=firstGlideSlopeWayPoint.
getAltitudeMeanSeaLevelMeters(),
deltaDistanceFlownMeters=0.0)
aircraft.setApproachConfiguration(0.0)
aircraftMassKilograms = 49000.0
aircraft.setAircraftMassKilograms(aircraftMassKilograms)
print(
'===================== final 3 degrees descending glide slope ================'
)
descentGlideSlope = DescentGlideSlope(runway=arrivalRunway,
aircraft=aircraft,
arrivalAirport=arrivalAirport,
descentGlideSlopeDegrees=3.0)
descentGlideSlope.buildGlideSlope(elapsedTimeSeconds=0.0,
initialWayPoint=firstGlideSlopeWayPoint,
flownDistanceMeters=300000.0,
distanceStillToFlyMeters=10000.0)
print('================= create output files =========================')
aircraftIcaoCode,
acBd.getAircraftPerformanceFile(aircraftIcaoCode), atmosphere,
earth)
aircraft.dump()
assert not (aircraft is None)
elapsedTimeSeconds = 0.0
deltaTimeSeconds = 1.0
aircraft.initStateVector(elapsedTimeSeconds=0.0,
trueAirSpeedMetersSecond=0.0,
altitudeMeanSeaLevelMeters=0.0)
aircraft.setTargetCruiseFlightLevel(RequestedFlightLevel=310.0,
departureAirportAltitudeMSLmeters=0.0)
aircraft.setAircraftMassKilograms(aircraftMassKilograms=64000.0)
aircraft.setTargetCruiseMach(cruiseMach=0.8)
tas = aircraft.getCurrentTrueAirSpeedMetersSecond()
previousAltitudeMSLmeters = 0.0
t0 = time.clock()
print('simulation start= {0} seconds'.format(t0))
print('=========== simulation start ==================')
endOfSimulation = False
currentPosition = departureAirport
arrivalGroundRun = GroundRunLeg(runway=arrivalRunway,
aircraft=aircraft,
airport=arrivalAirport)
touchDownWayPoint = arrivalGroundRun.computeTouchDownWayPoint()
print(touchDownWayPoint)
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 ==================')
aircraftIcaoCode,
acBd.getAircraftPerformanceFile(aircraftIcaoCode), atmosphere,
earth)
aircraft.dump()
assert not (aircraft is None)
elapsedTimeSeconds = 0.0
deltaTimeSeconds = 1.0
aircraft.initStateVector(elapsedTimeSeconds=0.0,
trueAirSpeedMetersSecond=0.0,
airportFieldElevationAboveSeaLevelMeters=0.0)
aircraft.setTargetCruiseFlightLevel(RequestedFlightLevel=310.0,
departureAirportAltitudeMSLmeters=0.0)
aircraft.setAircraftMassKilograms(aircraftMassKilograms=285700.0)
aircraft.setTargetCruiseMach(cruiseMachNumber=0.8)
tas = aircraft.getCurrentTrueAirSpeedMetersSecond()
previousAltitudeMSLmeters = 0.0
t0 = time.clock()
print('simulation start= {0} seconds'.format(t0))
print('=========== simulation start ==================')
endOfSimulation = False
currentPosition = departureAirport
arrivalGroundRun = GroundRunLeg(runway=arrivalRunway,
aircraft=aircraft,
airport=arrivalAirport)
touchDownWayPoint = arrivalGroundRun.computeTouchDownWayPoint()
acBd = BadaAircraftDatabase()
assert acBd.read()
aircraftIcaoCode = 'A320'
if ( acBd.aircraftExists(aircraftIcaoCode)
and acBd.aircraftPerformanceFileExists(acBd.getAircraftPerformanceFile(aircraftIcaoCode))):
tasKnots = 480.0
print ( '--------------- tas= {0:.2f} knots ----------------------'.format(tasKnots) )
aircraft = BadaAircraft(aircraftIcaoCode,
acBd.getAircraftPerformanceFile(aircraftIcaoCode),
atmosphere,
earth)
aircraft.dump()
takeOffMassKilograms = 64000.0
aircraft.setAircraftMassKilograms(takeOffMassKilograms)
RequestedFlightLevel = 310.0
fieldElevationAboveSeaLevelMeters = 150.0
aircraft.setTargetCruiseFlightLevel(RequestedFlightLevel, fieldElevationAboveSeaLevelMeters)
tasMetersPerSecond = tasKnots * Knots2MetersPerSecond
aircraft.initStateVector(elapsedTimeSeconds = 0.0,
trueAirSpeedMetersSecond = tasMetersPerSecond,
altitudeMeanSeaLevelMeters = 3000.0 * Meter2Feet,
deltaDistanceFlownMeters = 0.0)
aircraft.setCruiseConfiguration(elapsedTimeSeconds = 0.0)
turnLeg = TurnLeg( initialWayPoint = departureAirport,
finalWayPoint = arrivalAirport,
initialHeadingDegrees = 215.0,
finalHeadingDegrees = 180.0,
