WOLFRAM SYSTEM MODELER
PipistrelPEM60MVLCElectric engine: Pipistrel PEM 60MVLC |
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Diagram
Wolfram Language
In[1]:=
SystemModel["Aircraft.Physical.FixedWing.Parts.Propulsions.Engines.ElectricEngines.PipistrelPEM60MVLC"]
Out[1]:=
Information
This model extends the ElectricEngine model and contains the parameters of the Pipistrel PEM 60MVLC engine.
References for Engine Parameter Values
[1] PIPISTREL d.o.o. (2022). "Technical data PIPISTREL Alpha Electro." [online]
Available at: https://www.pipistrel-aircraft.com/products/light-sport-microlight/alpha-electro/#tab-id-2 [Accessed 27 Oct. 2022].
Parameters (18)
| weightEst |
Value: Type: Boolean Description: true, if weight estimation method is used for masses, center of mass location and inertia tensor |
|---|---|
| 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: 0 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: 60000 Type: Power (W) Description: Engine power at sea level |
| dProp |
Value: 1.64 Type: Length (m) Description: Propeller diameter |
| etaProp |
Value: 0.8 Type: Real Description: Propeller efficiency |
| etaEng |
Value: 0.8 Type: Real Description: Power transmission efficiency |
| mProp |
Value: 0 Type: Mass (kg) Description: Propeller mass |
| mEngDry |
Value: Psealevel * W2kg / 3200 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 |
Inputs (1)
| flightData |
Type: FlightData Description: Global flight data variables |
|---|
Connectors (3)
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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 |
Components (15)
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flightData |
Type: FlightData Description: Global flight data variables |
|---|---|---|
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energySystem |
Type: ElectricSystem 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 |
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onGround |
Type: BooleanExpression Description: Boolean expression for indicating aircraft being on ground |