WOLFRAM SYSTEM MODELER
PistonEnginePiston engine: unparameterized |
SystemModel["Aircraft.Physical.FixedWing.Parts.Propulsions.Engines.PistonEngines.PistonEngine"]
This piston engine model extends the EngineBase model and models the thrust and mass (if weight estimation method is used) of a piston engine.
The required parameters for the piston engine model are listed in the Propulsion tab, as shown in Figure 1.
Figure 1: Required input parameters for piston engine model.
Should the value of any of the estimated properties listed in the Estimated Properties parameter tab be known (such as engine mass), the equations can be bypassed by entering the known value directly to the respective parameter input field.
The remaining parameters listed in the Propagated parameters tab are propagated from the AircraftBase as the propulsion system is compiled in PistonPropulsion, and thus they can and should be left unchanged.
The thrust available (Tavail) for piston engines is solved through dividing the power available (Pavail) by the total velocity (vtot), and the factors for representing the propeller (ηprop) and power transmission efficiencies (ηmech) are also added, thus
.
For solving the power available, a relation presented by Gudmundsson [1] is used
,
where P0 is the engine power at sea level, ρalt is air density at flight altitude and ρ0 is air density at sea level.
The parameter for brake-specific fuel consumption (BSFC) is propagated to the energySystem component, where fuel consumption calculations are performed.
The piston engine is considered to be installed completely inside the fuselage, and the drag due to propeller is omitted. Thus, the piston engine model currently has no drag.
If the weight estimation method is used and no engine mass is entered by the user, the engine mass is solved by using empirical relationship based on the given P0 parameter value, as presented by Erä-Esko [2]
.
The mass of the propeller is then added on top of this estimated engine mass.
The engine moments of inertia are estimated to be insignificantly small, and thus a default value of 0.001 kg/m2 is used, which, however, can be overwritten by entering another value in the Estimated Properties parameter tab.
[2] Erä-Esko, N. (2022). "Development and Use of System Modeler 6DOF Flight Mechanics Model in Aircraft Conceptual Design."
Available at: modelica://Aircraft/Resources/Documents/EraeEskoThesis.pdf.
weightEst |
Value: Type: Boolean Description: true, if weight estimation method is used for masses, center of mass location and inertia tensor |
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bWing |
Value: Type: Length (m) Description: Main wing span |
SrefWing |
Value: Type: Area (m²) Description: Main wing reference area |
CADshapes |
Value: Type: Boolean Description: true, if external CAD files are used for animation |
negThrust |
Value: Type: Real Description: Maximum negative thrust (0 to 1 of thrust available) |
rho0 |
Value: Type: Density (kg/m³) Description: Air density at sea-level |
Psealevel |
Value: Type: Power (W) Description: Engine power at sea level |
BSFC |
Value: Type: BrakeSpecificFuelConsumption (kg⋅W⁻¹⋅s⁻¹) Description: Brake-specific fuel consumption in cruise |
dProp |
Value: Type: Length (m) Description: Propeller diameter |
etaProp |
Value: Type: Real Description: Propeller efficiency |
etaEng |
Value: Type: Real Description: Power transmission efficiency |
mProp |
Value: 0 Type: Mass (kg) Description: Propeller mass |
mEngDry |
Value: 0.0045394 * (Psealevel - 16076.3) ^ 0.922 Type: Mass (kg) Description: Engine dry mass |
mEngInstalled |
Value: mEngDry + mProp Type: Mass (kg) Description: Installed engine mass |
xEngCM |
Value: 0 Type: Length (m) Description: Engine center of mass x-coordinate w.r.t. engine rear end |
IxxEng |
Value: 0.001 Type: MomentOfInertia (kg⋅m²) Description: Engine roll moment of inertia |
IyyEng |
Value: 0.001 Type: MomentOfInertia (kg⋅m²) Description: Engine pitch moment of inertia |
IzzEng |
Value: 0.001 Type: MomentOfInertia (kg⋅m²) Description: Engine yaw moment of inertia |
Tstatic |
Value: (Modelica.Constants.pi / 2 * rho0 * dProp ^ 2 * Psealevel ^ 2) ^ (1 / 3) Type: Force (N) Description: Static thrust of one engine at sea level |
flightData |
Type: FlightData Description: Global flight data variables |
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deltaThrotCmd |
Type: RealInput Description: Throttle position command |
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engineRP |
Type: Frame_b Description: Connector to engine reference point |
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yConsumption |
Type: RealOutput Description: Consumed electric energy or fuel in an engine |
flightData |
Type: FlightData Description: Global flight data variables |
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energySystem |
Type: FuelSystemBrakeSpecific Description: Model to calculate the consumed electric energy or fuel in an engine |
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thrustEngine |
Type: WorldForce Description: Engine net thrust |
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engShape |
Type: FixedShape Description: Engine visualization |
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thrustAvailable |
Type: RealExpression Description: Thrust available of one engine |
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engineThrustDmd |
Type: Product Description: Thrust demand for one engine |
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engineDynamics |
Type: CriticalDamping Description: Simplified model of the engine dynamics |
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throttleOnGround |
Type: Limiter Description: Limits the throttle from maximum negative thrust to 1 once on the ground |
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dragNacelle3D |
Type: RealExpression[3] Description: Drag due to one nacelle |
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dragNacelle |
Type: WorldForce Description: Drag of nacelle |
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translEng |
Type: FixedTranslation Description: Translation from engine rear end to the point where thrust and drag are acting on (currently no translation) |
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bodyEng |
Type: Body Description: Mass and inertia of engine |
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switch |
Type: Switch Description: Switch between two Real signals |
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throttleInAir |
Type: Limiter Description: Limits the throttle from 0 to 1 once airborne |
|
onGround |
Type: BooleanExpression Description: Boolean expression for indicating aircraft being on ground |
Aircraft.Physical.FixedWing.Parts.Propulsions.Engines.PistonEngines Piston engine: Rotax 912 UL |