def __init__(self, aircraftPerformance, ICAOcode, atmosphere, earth):
self.className = self.__class__.__name__
''' init mother class '''
AeroDynamics.__init__(self, aircraftPerformance, atmosphere, earth)
assert isinstance(atmosphere, Atmosphere)
self.atmosphere = atmosphere
assert isinstance(aircraftPerformance, AircraftPerformance)
self.MaxOpSpeedCasKnots = aircraftPerformance.getVmoCasKnots()
self.MaxOpMachNumber = aircraftPerformance.getMaxOpMachNumber()
self.MaxOpAltitudeFeet = aircraftPerformance.getMaxOpAltitudeFeet()
self.targetCruiseAltitudeMslMeters = self.MaxOpAltitudeFeet / Meter2Feet
self.targetCruiseMachNumber = self.MaxOpMachNumber
self.arrivalAirportFieldElevationMeters = 0.0
self.StateVector = StateVector(ICAOcode, atmosphere)
self.departureAirportAltitudeMSLmeters = 0.0
self.approachWayPoint = None
self.arrivalRunWayTouchDownWayPoint = None
def __init__(self, aircraftPerformance, ICAOcode, atmosphere, earth):
self.className = self.__class__.__name__
''' init mother class '''
AeroDynamics.__init__(self, aircraftPerformance, atmosphere, earth)
assert isinstance(atmosphere, Atmosphere)
self.atmosphere = atmosphere
assert isinstance(aircraftPerformance, AircraftPerformance)
self.MaxOpSpeedCasKnots = aircraftPerformance.getVmoCasKnots()
self.MaxOpMachNumber = aircraftPerformance.getMaxOpMachNumber()
self.MaxOpAltitudeFeet = aircraftPerformance.getMaxOpAltitudeFeet()
self.targetCruiseAltitudeMslMeters = self.MaxOpAltitudeFeet / Meter2Feet
self.targetCruiseMachNumber = self.MaxOpMachNumber
self.arrivalAirportFieldElevationMeters = 0.0
self.StateVector = StateVector(ICAOcode, atmosphere)
self.departureAirportAltitudeMSLmeters = 0.0
self.approachWayPoint = None
self.arrivalRunWayTouchDownWayPoint = None
class FlightEnvelope(AeroDynamics):
'''
design issue = TAS + altitude (and ISA temperature) => compute CAS
Definition
Calibrated airspeed (CAS) is indicated airspeed corrected for instrument errors and position error
(due to incorrect pressure at the static port caused by airflow disruption).
Description
CAS has two primary applications in aviation:
for navigation, CAS is traditionally calculated as one of the steps between indicated airspeed (IAS) and true airspeed (TAS);
for aircraft control, CAS is one of the primary reference points, as it describes the dynamic pressure acting on aircraft surfaces
regardless of the existing conditions of temperature, pressure altitude or wind.
The first application has rapidly decreased in importance due to the widespread use of GPS and inertial navigation systems.
With these systems, pilots are able to read TAS and ground-speed directly from cockpit displays.
This negates the requirement to calculate TAS from IAS with calibrated airspeed as an intermediate step.
The second application, however, remains critical.
As an example, at a given weight, an aircraft will rotate and climb, stall or fly an approach to a landing at approximately the same calibrated airspeeds,
regardless of the elevation, even though the true airspeed and ground speed may differ significantly.
These V (vertical) speeds are normally published as IAS rather than CAS so they can be read directly from the airspeed indicator.
'''
# VMO - maximum operating speed (CAS), in knots
MaxOpSpeedCasKnots = 0.0
# MMO - maximum operational Mach number
MaxOpMachNumber = 0.0
# hMO - maximum operating altitude, in feet, above standard MSL
MaxOpAltitudeFeet = 0.0
'''
hmax - maximum altitude, in feet, above standard MSL at Max Take-Off Weight under ISA
conditions (allowing about 300 fpm of residual Rate Of Climb),
'''
MaxAltitudeMslFeet = 0.0
# Gw - mass gradient on hmax , in feet/kg
# Gt - temperature gradient on hmax in feet/degree Celsius
''' speed history - check that speed stays within the flight envelope '''
StateVector = None
def __init__(self, aircraftPerformance, ICAOcode, atmosphere, earth):
self.className = self.__class__.__name__
''' init mother class '''
AeroDynamics.__init__(self, aircraftPerformance, atmosphere, earth)
assert isinstance(atmosphere, Atmosphere)
self.atmosphere = atmosphere
assert isinstance(aircraftPerformance, AircraftPerformance)
self.MaxOpSpeedCasKnots = aircraftPerformance.getVmoCasKnots()
self.MaxOpMachNumber = aircraftPerformance.getMaxOpMachNumber()
self.MaxOpAltitudeFeet = aircraftPerformance.getMaxOpAltitudeFeet()
self.targetCruiseAltitudeMslMeters = self.MaxOpAltitudeFeet / Meter2Feet
self.targetCruiseMachNumber = self.MaxOpMachNumber
self.arrivalAirportFieldElevationMeters = 0.0
self.StateVector = StateVector(ICAOcode, atmosphere)
self.departureAirportAltitudeMSLmeters = 0.0
self.approachWayPoint = None
self.arrivalRunWayTouchDownWayPoint = None
def setTargetCruiseFlightLevel(self,
RequestedFlightLevel,
departureAirportAltitudeMSLmeters):
self.departureAirportAltitudeMSLmeters = departureAirportAltitudeMSLmeters
QNHhectoPascals = 1013.25 - (departureAirportAltitudeMSLmeters / 8.5344)
''' flight level is expressed in hundreds of feet '''
assert RequestedFlightLevel >= 15.0 and RequestedFlightLevel <= 450.0
self.targetCruiseFlightLevel = RequestedFlightLevel
''' pression de reference MSL = 1013,25 hecto Pascals '''
''' delta meter for each hecto pascal = 8,5344 meter '''
''' compute Mean Sea Level altitude expressed in meters '''
self.targetCruiseAltitudeMslMeters = ( RequestedFlightLevel * 100.0 * Feet2Meter ) + (1013.25 - QNHhectoPascals) * 8.5344
self.targetCruiseAltitudeMslMeters = ( RequestedFlightLevel * 100.0 * Feet2Meter )
print self.className + ': set Cruise FL= {0} - QNH= {1:.2f} hecto Pascals - computed Altitude MSL= {2:.2f} meters'.format(RequestedFlightLevel , QNHhectoPascals, self.targetCruiseAltitudeMslMeters)
def getTargetCruiseFlightLevelMeters(self):
return self.targetCruiseAltitudeMslMeters
def setTargetApproachWayPoint(self, approachWayPoint):
self.approachWayPoint = approachWayPoint
def getTargetApproachWayPoint(self):
return self.approachWayPoint
def getMaxOperationalMach(self):
return self.MaxOpMachNumber
def setTargetCruiseMach(self, cruiseMachNumber):
''' check that target mach is always lower or equal to Max Operational Mach '''
if isinstance(cruiseMachNumber, str) and (cruiseMachNumber == 'use-default'):
cruiseMachNumber = self.MaxOpMachNumber
assert (cruiseMachNumber <= self.MaxOpMachNumber)
print self.className + ' ===================================================='
print self.className + ': set target cruise Mach= {0}'.format(cruiseMachNumber)
self.targetCruiseMachNumber = cruiseMachNumber
print self.className + ' ===================================================='
def getTargetCruiseMach(self):
return self.targetCruiseMachNumber
def setArrivalRunwayTouchDownWayPoint(self, arrivalRunWayTouchDownWayPoint):
''' target runway touch down way point '''
self.arrivalRunWayTouchDownWayPoint = arrivalRunWayTouchDownWayPoint
def getArrivalRunwayTouchDownWayPoint(self):
return self.arrivalRunWayTouchDownWayPoint
def dump(self):
print self.className + ': VMO CAS= ' + str(self.MaxOpSpeedCasKnots) + ' knots'
print self.className + ': Max Operational Mach Number= ' + str(self.MaxOpMachNumber)
print self.className + ': Max Operational Altitude= ' + str(self.MaxOpAltitudeFeet) + ' feet'
def __str__(self):
strMsg = self.className + ': VMO CAS= {0} knots'.format(self.MaxOpSpeedCasKnots)
strMsg += ' - Max Operational Mach Number= {0}'.format(self.MaxOpMachNumber)
strMsg += ' - Max Operational Altitude= {0} feet'.format(self.MaxOpAltitudeFeet)
return strMsg
def getMaxAltitudeMslMtowFeet(self):
return self.MaxOpAltitudeFeet
def getMaxOpSpeedCasKnots(self):
return self.MaxOpSpeedCasKnots
def initStateVector(self,
elapsedTimeSeconds,
trueAirSpeedMetersSecond,
airportFieldElevationAboveSeaLevelMeters,
aircraftMassKilograms):
'''
altitude and speed changes are modifying the configuration of the aircraft
'''
lastAltitudeMeanSeaLevelMeters = self.StateVector.getCurrentAltitudeSeaLevelMeters()
targetCruiseAltitudeMeanSeaLevelMeters = self.getTargetCruiseFlightLevelMeters()
# self.setCurrentAltitudeSeaLevelMeters(elapsedTimeSeconds,
# airportFieldElevationAboveSeaLevelMeters,
# lastAltitudeMeanSeaLevelMeters,
# targetCruiseAltitudeMeanSeaLevelMeters)
self.StateVector.initStateVector(elapsedTimeSeconds,
trueAirSpeedMetersSecond,
airportFieldElevationAboveSeaLevelMeters,
aircraftMassKilograms)
def updateAircraftStateVector(self,
elapsedTimeSeconds ,
trueAirSpeedMetersPerSecond ,
altitudeMeanSeaLevelMeters ,
currentDistanceFlownMeters ,
distanceStillToFlyMeters ,
aircraftMassKilograms ,
flightPathAngleDegrees ,
thrustNewtons ,
dragNewtons ,
liftNewtons ,
endOfSimulation):
self.StateVector.updateAircraftStateVector(elapsedTimeSeconds ,
trueAirSpeedMetersPerSecond ,
altitudeMeanSeaLevelMeters ,
currentDistanceFlownMeters ,
distanceStillToFlyMeters ,
aircraftMassKilograms ,
flightPathAngleDegrees ,
thrustNewtons ,
dragNewtons ,
liftNewtons ,
endOfSimulation)
calibratedAirSpeedKnots = self.atmosphere.tas2cas(tas = trueAirSpeedMetersPerSecond ,
altitude = altitudeMeanSeaLevelMeters,
temp='std',
speed_units = 'm/s',
alt_units='m'
) * MeterSecond2Knots
if (calibratedAirSpeedKnots > self.MaxOpSpeedCasKnots):
print self.className + ': CAS= {0:.2f} knots >> higher than Max Op CAS= {1:.2f} knots'.format(calibratedAirSpeedKnots, self.MaxOpSpeedCasKnots)
endOfSimulation = True
if (altitudeMeanSeaLevelMeters * Meter2Feet) > self.MaxOpAltitudeFeet:
print self.className + ': current altitude= {0:.2f} feet >> higher than Max Operational Altitude= {1:.2f} feet'.format((altitudeMeanSeaLevelMeters * Meter2Feet), self.MaxOpAltitudeFeet)
endOfSimulation = True
if altitudeMeanSeaLevelMeters < 0.0:
print self.className + ': altitude MSL= {0:.2f} meters is negative => end of simulation'.format(altitudeMeanSeaLevelMeters)
endOfSimulation = True
if trueAirSpeedMetersPerSecond < 0.0:
print self.className + ': tas= {0:.2f} m/s is negative => end of simulation'.format(trueAirSpeedMetersPerSecond)
endOfSimulation = True
return endOfSimulation
def createStateVectorHistoryFile(self):
self.StateVector.createStateVectorHistoryFile()
def getCurrentAltitudeSeaLevelMeters(self):
return self.StateVector.getCurrentAltitudeSeaLevelMeters()
def getCurrentTrueAirSpeedMetersSecond(self):
return self.StateVector.getCurrentTrueAirSpeedMetersSecond()
def getCurrentDistanceFlownMeters(self):
return self.StateVector.getCurrentDistanceFlownMeters()
def getFlightPathAngleDegrees(self):
return self.StateVector.getFlightPathAngleDegrees()
class FlightEnvelope(AeroDynamics):
'''
design issue = TAS + altitude (and ISA temperature) => compute CAS
Definition
Calibrated airspeed (CAS) is indicated airspeed corrected for instrument errors and position error
(due to incorrect pressure at the static port caused by airflow disruption).
Description
CAS has two primary applications in aviation:
for navigation, CAS is traditionally calculated as one of the steps between indicated airspeed (IAS) and true airspeed (TAS);
for aircraft control, CAS is one of the primary reference points, as it describes the dynamic pressure acting on aircraft surfaces
regardless of the existing conditions of temperature, pressure altitude or wind.
The first application has rapidly decreased in importance due to the widespread use of GPS and inertial navigation systems.
With these systems, pilots are able to read TAS and ground-speed directly from cockpit displays.
This negates the requirement to calculate TAS from IAS with calibrated airspeed as an intermediate step.
The second application, however, remains critical.
As an example, at a given weight, an aircraft will rotate and climb, stall or fly an approach to a landing at approximately the same calibrated airspeeds,
regardless of the elevation, even though the true airspeed and ground speed may differ significantly.
These V (vertical) speeds are normally published as IAS rather than CAS so they can be read directly from the airspeed indicator.
'''
# VMO - maximum operating speed (CAS), in knots
MaxOpSpeedCasKnots = 0.0
# MMO - maximum operational Mach number
MaxOpMachNumber = 0.0
# hMO - maximum operating altitude, in feet, above standard MSL
MaxOpAltitudeFeet = 0.0
'''
hmax - maximum altitude, in feet, above standard MSL at Max Take-Off Weight under ISA
conditions (allowing about 300 fpm of residual Rate Of Climb),
'''
MaxAltitudeMslFeet = 0.0
# Gw - mass gradient on hmax , in feet/kg
# Gt - temperature gradient on hmax in feet/degree Celsius
''' speed history - check that speed stays within the flight envelope '''
StateVector = None
def __init__(self, aircraftPerformance, ICAOcode, atmosphere, earth):
self.className = self.__class__.__name__
''' init mother class '''
AeroDynamics.__init__(self, aircraftPerformance, atmosphere, earth)
assert isinstance(atmosphere, Atmosphere)
self.atmosphere = atmosphere
assert isinstance(aircraftPerformance, AircraftPerformance)
self.MaxOpSpeedCasKnots = aircraftPerformance.getVmoCasKnots()
self.MaxOpMachNumber = aircraftPerformance.getMaxOpMachNumber()
self.MaxOpAltitudeFeet = aircraftPerformance.getMaxOpAltitudeFeet()
self.targetCruiseAltitudeMslMeters = self.MaxOpAltitudeFeet / Meter2Feet
self.targetCruiseMachNumber = self.MaxOpMachNumber
self.arrivalAirportFieldElevationMeters = 0.0
self.StateVector = StateVector(ICAOcode, atmosphere)
self.departureAirportAltitudeMSLmeters = 0.0
self.approachWayPoint = None
self.arrivalRunWayTouchDownWayPoint = None
def setTargetCruiseFlightLevel(self, RequestedFlightLevel,
departureAirportAltitudeMSLmeters):
self.departureAirportAltitudeMSLmeters = departureAirportAltitudeMSLmeters
QNHhectoPascals = 1013.25 - (departureAirportAltitudeMSLmeters /
8.5344)
''' flight level is expressed in hundreds of feet '''
assert RequestedFlightLevel >= 15.0 and RequestedFlightLevel <= 450.0
self.targetCruiseFlightLevel = RequestedFlightLevel
''' pression de reference MSL = 1013,25 hecto Pascals '''
''' delta meter for each hecto pascal = 8,5344 meter '''
''' compute Mean Sea Level altitude expressed in meters '''
self.targetCruiseAltitudeMslMeters = (
RequestedFlightLevel * 100.0 *
Feet2Meter) + (1013.25 - QNHhectoPascals) * 8.5344
self.targetCruiseAltitudeMslMeters = (RequestedFlightLevel * 100.0 *
Feet2Meter)
print(self.className +
': set Cruise FL= {0} - QNH= {1:.2f} hecto Pascals - '
'computed Altitude MSL= {2:.2f} meters'.format(
RequestedFlightLevel, QNHhectoPascals,
self.targetCruiseAltitudeMslMeters))
def getTargetCruiseFlightLevelMeters(self):
return self.targetCruiseAltitudeMslMeters
def setTargetApproachWayPoint(self, approachWayPoint):
self.approachWayPoint = approachWayPoint
def getTargetApproachWayPoint(self):
return self.approachWayPoint
def getMaxOperationalMach(self):
return self.MaxOpMachNumber
def setTargetCruiseMach(self, cruiseMachNumber):
''' check that target mach is always lower or equal to Max Operational Mach '''
if isinstance(cruiseMachNumber, str) and (cruiseMachNumber
== 'use-default'):
cruiseMachNumber = self.MaxOpMachNumber
assert (cruiseMachNumber <= self.MaxOpMachNumber)
print(self.className +
'====================================================')
print(self.className +
': set target cruise Mach= {0}'.format(cruiseMachNumber))
self.targetCruiseMachNumber = cruiseMachNumber
print(self.className +
'====================================================')
def getTargetCruiseMach(self):
return self.targetCruiseMachNumber
def setArrivalRunwayTouchDownWayPoint(self,
arrivalRunWayTouchDownWayPoint):
''' target runway touch down way point '''
self.arrivalRunWayTouchDownWayPoint = arrivalRunWayTouchDownWayPoint
def getArrivalRunwayTouchDownWayPoint(self):
return self.arrivalRunWayTouchDownWayPoint
def dump(self):
print(self.className + ': VMO CAS= ' + str(self.MaxOpSpeedCasKnots) +
' knots')
print(self.className + ': Max Operational Mach Number= ' +
str(self.MaxOpMachNumber))
print(self.className + ': Max Operational Altitude= ' +
str(self.MaxOpAltitudeFeet) + ' feet')
def __str__(self):
strMsg = self.className + ': VMO CAS= {0} knots'.format(
self.MaxOpSpeedCasKnots)
strMsg += ' - Max Operational Mach Number= {0}'.format(
self.MaxOpMachNumber)
strMsg += ' - Max Operational Altitude= {0} feet'.format(
self.MaxOpAltitudeFeet)
return strMsg
def getMaxAltitudeMslMtowFeet(self):
return self.MaxOpAltitudeFeet
def getMaxOpSpeedCasKnots(self):
return self.MaxOpSpeedCasKnots
def initStateVector(self, elapsedTimeSeconds, trueAirSpeedMetersSecond,
airportFieldElevationAboveSeaLevelMeters,
aircraftMassKilograms):
'''
altitude and speed changes are modifying the configuration of the aircraft
'''
lastAltitudeMeanSeaLevelMeters = self.StateVector.getCurrentAltitudeSeaLevelMeters(
)
targetCruiseAltitudeMeanSeaLevelMeters = self.getTargetCruiseFlightLevelMeters(
)
# self.setCurrentAltitudeSeaLevelMeters(elapsedTimeSeconds,
# airportFieldElevationAboveSeaLevelMeters,
# lastAltitudeMeanSeaLevelMeters,
# targetCruiseAltitudeMeanSeaLevelMeters)
self.StateVector.initStateVector(
elapsedTimeSeconds, trueAirSpeedMetersSecond,
airportFieldElevationAboveSeaLevelMeters, aircraftMassKilograms)
def updateAircraftStateVector(
self, elapsedTimeSeconds, trueAirSpeedMetersPerSecond,
altitudeMeanSeaLevelMeters, currentDistanceFlownMeters,
distanceStillToFlyMeters, aircraftMassKilograms,
flightPathAngleDegrees, thrustNewtons, dragNewtons, liftNewtons,
endOfSimulation):
self.StateVector.updateAircraftStateVector(
elapsedTimeSeconds, trueAirSpeedMetersPerSecond,
altitudeMeanSeaLevelMeters, currentDistanceFlownMeters,
distanceStillToFlyMeters, aircraftMassKilograms,
flightPathAngleDegrees, thrustNewtons, dragNewtons, liftNewtons,
endOfSimulation)
calibratedAirSpeedKnots = self.atmosphere.tas2cas(
tas=trueAirSpeedMetersPerSecond,
altitude=altitudeMeanSeaLevelMeters,
temp='std',
speed_units='m/s',
alt_units='m') * MeterSecond2Knots
if (calibratedAirSpeedKnots > self.MaxOpSpeedCasKnots):
print(
self.className +
': CAS= {0:.2f} knots >> higher than Max Op CAS= {1:.2f} knots'
.format(calibratedAirSpeedKnots, self.MaxOpSpeedCasKnots))
endOfSimulation = True
if (altitudeMeanSeaLevelMeters * Meter2Feet) > self.MaxOpAltitudeFeet:
print(
self.className +
': current altitude= {0:.2f} feet >> higher than Max Operational Altitude= {1:.2f} feet'
.format((altitudeMeanSeaLevelMeters *
Meter2Feet), self.MaxOpAltitudeFeet))
endOfSimulation = True
if altitudeMeanSeaLevelMeters < 0.0:
print(
self.className +
': altitude MSL= {0:.2f} meters is negative => end of simulation'
.format(altitudeMeanSeaLevelMeters))
endOfSimulation = True
if trueAirSpeedMetersPerSecond < 0.0:
print(self.className +
': tas= {0:.2f} m/s is negative => end of simulation'.format(
trueAirSpeedMetersPerSecond))
endOfSimulation = True
return endOfSimulation
def createStateVectorHistoryFile(self):
self.StateVector.createStateVectorHistoryFile()
def getCurrentAltitudeSeaLevelMeters(self):
return self.StateVector.getCurrentAltitudeSeaLevelMeters()
def getCurrentTrueAirSpeedMetersSecond(self):
return self.StateVector.getCurrentTrueAirSpeedMetersSecond()
def getCurrentDistanceFlownMeters(self):
return self.StateVector.getCurrentDistanceFlownMeters()
def getFlightPathAngleDegrees(self):
return self.StateVector.getFlightPathAngleDegrees()
