WOLFRAM SYSTEM MODELER
PistonPropulsionPiston propulsion (model specific parameters not set) |
SystemModel["Aircraft.Physical.FixedWing.Parts.Propulsions.PistonPropulsion"]
This piston engine propulsion model extends the ConventionalPropulsion model and models the propulsion for an aircraft using piston engines.
Essentially, what this model does on top of the ConventionalPropulsion model, is to:
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.
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: 0 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 |
flightData |
Type: FlightData Description: Global flight data variables |
---|
aircraftRP |
Type: Frame_b Description: Connector to aircraft reference point |
|
---|---|---|
deltaThrotCmd |
Type: RealInput[nEng] Description: Engine throttle commands |
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: PistonEngine Description: Model for engine 1 |
|
engineD |
Type: PistonEngine Description: Piston engine: unparameterized |
|
engineB |
Type: PistonEngine Description: Piston engine: unparameterized |
|
engineE |
Type: PistonEngine Description: Piston engine: unparameterized |
|
engineA |
Type: PistonEngine Description: Piston engine: unparameterized |
|
sumConsumption |
Type: Sum Description: Summing of fuel / battery energy consumption |
|
rotEng1 |
Type: FixedRotation Description: Engine 1 thrust line angle |