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WOLFRAM SYSTEM MODELER

TurbopropPropulsion

Turboprop propulsion (model specific parameters not set)

Diagram

Wolfram Language

In[1]:=

SystemModel["Aircraft.Physical.FixedWing.Parts.Propulsions.TurbopropPropulsion"]

Out[1]:=

Information

This turboprop propulsion model extends the ConventionalPropulsion model and models the propulsion for an aircraft using turboprop engines.

Essentially, what this model does on top of the ConventionalPropulsion model, is to:

Redeclare the EngineBase models as TurbopropEngine models
Redeclare the EnergyStorageBase model as TankSystem
Propagate the relevant parameters from the aircraft top level into the turboprop engine and the tank system models
Declare the tank parameters and propagate their values further into the tank system model

The engine model to be used for all engines in the propulsion system can be selected by choosing the value for the Engine parameter in the General tab.

Parameters (49)

kSkinNac	Value: Type: Length (m) Description: Nacelle surface roughness height
CADshapes	Value: Type: Boolean Description: true, if external CAD files are used for animation
convProp	Value: true Type: Boolean Description: =true, if conventional propulsion
weightEst	Value: Type: Boolean Description: true, if weight estimation method is used for masses, center of mass location and inertia tensor
SrefWing	Value: Type: Area (m²) Description: Main wing reference area
nEng	Value: 5 Type: Integer Description: Number of engines
T0	Value: Type: Temperature (K) Description: Temperature at sea-level
rho0	Value: Type: Density (kg/m³) Description: Air density at sea-level
p0	Value: Type: Pressure (Pa) Description: Static pressure at sea-level
gammaAir	Value: Type: Real Description: Adiabatic index for air
bWing	Value: Type: Length (m) Description: Main wing span
engineType	Value: 1 Type: Integer Description: Type of engine (0 = piston, 1 = turboprop, 2 = turbojet, 3 = turbofan, 4 = electric)
wingMounted	Value: Type: Boolean Description: true, if engines are mounted on the main wing
xEng	Value: Type: Length (m) Description: Fuselage mounted engine / Single engine rear end x-location from fuselage reference point (positive x-axis towards nose)
yEngInner	Value: if nEng == 2 then bWing / 4 else bWing / 3 Type: Length (m) Description: Inner engines y-coordinate w.r.t. fuselage centerline
yEngOuter	Value: bWing / 6 Type: Length (m) Description: Outer engines y-coordinate w.r.t. fuselage centerline
zTau	Value: 0 Type: Length (m) Description: Thrust line z-coordinate w.r.t. fuselage reference point for side (#2-5) engines and single engine
zTauMid	Value: zTau Type: Length (m) Description: Thrust line z-coordinate w.r.t. fuselage reference point for middle (#1) engine
kappa	Value: 0 Type: Angle (rad) Description: Engine thrust line angle for side (#2-5) engines and single engine
kappaMid	Value: 0 Type: Angle (rad) Description: Engine thrust line angle for middle (#1) engine
kappaEng1	Value: if nEng == 1 then kappa else if nEng == 3 then kappaMid else 0 Type: Angle (rad) Description: Engine thrust line angle for Engine 1
tauWing	Value: Type: Real Description: Ratio of thickness-to-chord ratios at the main wing tip and root
xCMdry	Value: Type: Length (m) Description: Aircraft center of mass x-coordinate w.r.t. fuselage reference point (with total mass for electric aircraft and gliders, positive x-axis towards nose)
wFus	Value: Type: Length (m) Description: Fuselage maximum width
hFus	Value: Type: Length (m) Description: Fuselage maximum height
cWingRoot	Value: Type: Length (m) Description: Main wing root chord (where wing intersects with fuselage)
cWingTip	Value: Type: Length (m) Description: Main wing tip chord
tWingRoot	Value: Type: Length (m) Description: Main wing root thickness
tWingTip	Value: Type: Length (m) Description: Main wing tip thickness
xWingRootLE	Value: Type: Length (m) Description: Main wing root leading edge x-coordinate w.r.t. fuselage reference point (positive x-axis towards nose)
zWingRootLE	Value: Type: Length (m) Description: Main wing root leading edge z-coordinate w.r.t. fuselage reference point (positive z-axis towards ground)
lambdaWing	Value: Type: Angle (rad) Description: Main wing sweep angle at 1/4 chord
gammaWing	Value: Type: Angle (rad) Description: Main wing dihedral angle
iWing	Value: Type: Angle (rad) Description: Main wing incidence angle
TRwing	Value: Type: Real Description: Main wing taper ratio
xWingAC	Value: Type: Length (m) Description: Main wing aerodynamic center from wing leading edge at mean chord (positive x-axis towards nose)
yWingAC	Value: Type: Length (m) Description: Main wing aerodynamic center from fuselage centerline (y-coordinate w.r.t. fuselage centerline of mean chord)
lambdaWingLE	Value: Type: Angle (rad) Description: Main wing leading edge sweep angle
lambdaWingHC	Value: Type: Angle (rad) Description: Main wing half-chord sweep angle
bVT	Value: Type: Length (m) Description: Vertical tail span
lVTcm	Value: Type: Length (m) Description: Vertical tail arm length (from aircraft center of mass to vertical tail 1/4 chord)
rEng1	Value: if nEng == 3 then {xCMdry - lVTcm - bVT * (3 / 4), 0, zTauMid} else if nEng == 1 then {xEng, 0, zTau} else {0, 0, 0} Type: Length[3] (m) Description: Location of engine 1 rear end w.r.t. fuselage reference point
initialMfuel	Value: Type: Mass (kg) Description: Initial fuel mass
rhoFuel	Value: 804 Type: Density (kg/m³) Description: Fuel density
eFuel	Value: 43000000 Type: SpecificEnergy (J/kg) Description: Fuel energy density
tankFudgeFactor	Value: 0.9 Type: Real Description: Fudge factor to shrink the tank size from the maximum possible tank volume
initialFuel	Value: 0.5 Type: Real Description: Initial fuel volume as a fraction of the fuel capacity
ctrTank	Value: true Type: Boolean Description: true, if aircraft is fitted with center tank
wingTank	Value: true Type: Boolean Description: true, if aircraft is fitted with wing tanks

Inputs (1)

flightData	Type: FlightData Description: Global flight data variables

flightData

Type: FlightData

Description: Global flight data variables

Connectors (2)

	aircraftRP	Type: Frame_b Description: Connector to aircraft reference point
	deltaThrotCmd	Type: RealInput[nEng] Description: Engine throttle commands

aircraftRP

Type: Frame_b

Description: Connector to aircraft reference point

deltaThrotCmd

Type: RealInput[nEng]

Description: Engine throttle commands

Components (18)

	flightData	Type: FlightData Description: Global flight data variables
	energyStorage	Type: TankSystem Description: Model for energy storage
	rotEng2	Type: FixedRotation Description: Engine 2 thrust line angle (enabled if number of engines = 2 or 3 or 4)
	rotEng3	Type: FixedRotation Description: Engine 3 thrust line angle (enabled if number of engines = 2 or 3 or 4)
	rotEng4	Type: FixedRotation Description: Engine 4 thrust line angle (enabled if number of engines = 4)
	rotEng5	Type: FixedRotation Description: Engine 5 thrust line angle (enabled if number of engines = 4)
	translEng1	Type: FixedTranslation Description: Location of engine 1 rear end w.r.t. fuselage reference point
	translEng2	Type: FixedTranslation Description: Location of engine 2 rear end w.r.t. fuselage reference point
	translEng3	Type: FixedTranslation Description: Location of engine 3 rear end w.r.t. fuselage reference point
	translEng4	Type: FixedTranslation Description: Location of engine 4 rear end w.r.t. fuselage reference point
	translEng5	Type: FixedTranslation Description: Location of engine 5 rear end w.r.t. fuselage reference point
	engineC	Type: TurbopropEngine Description: Model for engine 1
	engineD	Type: TurbopropEngine Description: Turboprop engine: unparameterized
	engineB	Type: TurbopropEngine Description: Turboprop engine: unparameterized
	engineE	Type: TurbopropEngine Description: Turboprop engine: unparameterized
	engineA	Type: TurbopropEngine Description: Turboprop engine: unparameterized
	sumConsumption	Type: Sum Description: Summing of fuel / battery energy consumption
	rotEng1	Type: FixedRotation Description: Engine 1 thrust line angle