WOLFRAM SYSTEM MODELER
RollsRoyceAE2100Turboprop engine: Rolls-Royce AE 2100 |
 |
Diagram
Wolfram Language
In[1]:=
SystemModel["Aircraft.Physical.FixedWing.Parts.Propulsions.Engines.TurbopropEngines.RollsRoyceAE2100"]
Out[1]:=
Information
This model extends the TurbopropEngine model and contains the parameters of the Rolls-Royce AE 2100 engine.
References for Engine Parameter Values
[1] Wikipedia. (2022). "Rolls-Royce AE 2100". [online]
Available at: https://en.wikipedia.org/wiki/Rolls-Royce_AE_2100#Specifications_(AE_2100D3) [Accessed 26 Oct. 2022].
Parameters (25)
| 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: 3096000 Type: Power (W) Description: Engine power at sea level |
| BSFC |
Value: 7.77777777777778e-08 Type: BrakeSpecificFuelConsumption (kg⋅W⁻¹⋅s⁻¹) Description: Brake-specific fuel consumption in cruise |
| dProp |
Value: 3.81 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 |
| kSkinNac |
Value: Type: Length (m) Description: Nacelle surface roughness height |
| mNac |
Value: 0.345 * 0.47 * mEngDry Type: Mass (kg) Description: Nacelle mass |
| mProp |
Value: 6.13 * (Tstatic * N2kg) / 1000 Type: Mass (kg) Description: Propeller mass |
| mEngDry |
Value: 0.0117 * 1.2 * Tstatic ^ 1.0572 Type: Mass (kg) Description: Engine dry mass |
| mEngInstalled |
Value: mEngDry + mNac + mProp Type: Mass (kg) Description: Installed engine mass |
| xEngCM |
Value: lNac / 2 Type: Length (m) Description: Engine center of mass x-coordinate w.r.t. engine rear end |
| IxxEng |
Value: mEngInstalled * (dNac / 2) ^ 2 / 2 Type: MomentOfInertia (kg⋅m²) Description: Engine roll moment of inertia |
| IyyEng |
Value: mEngInstalled * (dNac / 2) ^ 2 / 4 + mEngInstalled * lNac ^ 2 / 12 Type: MomentOfInertia (kg⋅m²) Description: Engine pitch moment of inertia |
| IzzEng |
Value: mEngInstalled * (dNac / 2) ^ 2 / 4 + mEngInstalled * lNac ^ 2 / 12 Type: MomentOfInertia (kg⋅m²) Description: Engine yaw moment of inertia |
| dNac |
Value: 4 * (0.0625 + 1 / (4 * sqrt(2)) * max(1.730 * log(max(Tstatic / 1000, 1)) - Modelica.Constants.pi, 0) ^ 0.5) Type: Length (m) Description: Nacelle diameter |
| lNac |
Value: 5 * (Tstatic / 1000) ^ 0.9839 / (6 * Modelica.Constants.pi * (1.730 * log(max(Tstatic / 1000, 1)) - Modelica.Constants.pi)) Type: Length (m) Description: Nacelle length |
| SwetNac |
Value: 2 * Modelica.Constants.pi ^ 2 * 0.2028 * dNac * ((0.20571 * lNac ^ 2 + 0.04661 * dNac ^ 2) ^ 0.5 + (0.1853 * lNac ^ 2 + 0.07557 * dNac ^ 2) ^ 0.5 - (0.005077 * lNac ^ 2 + 0.01611 * dNac ^ 2) ^ 0.5 - (0.01651 * lNac ^ 2 + 0.03666 * dNac ^ 2) ^ 0.5) Type: Area (m²) Description: Nacelle wetted area |
| FFnac |
Value: 1.17 * (1 + 0.35 * (dNac / max(lNac, 0.01))) Type: Real Description: Nacelle form factor |
| 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)
 |
deltaThrotCmd |
Type: RealInput Description: Throttle position command |
|---|---|---|
 |
engineRP |
Type: Frame_b Description: Connector to engine reference point |
 |
yConsumption |
Type: RealOutput Description: Consumed electric energy or fuel in an engine |
Components (15)
 |
flightData |
Type: FlightData Description: Global flight data variables |
|---|---|---|
 |
energySystem |
Type: FuelSystemBrakeSpecific Description: Model to calculate the consumed electric energy or fuel in an engine |
 |
thrustEngine |
Type: WorldForce Description: Engine net thrust |
 |
engShape |
Type: FixedShape Description: Engine visualization |
 |
thrustAvailable |
Type: RealExpression Description: Thrust available of one engine |
 |
engineThrustDmd |
Type: Product Description: Thrust demand for one engine |
 |
engineDynamics |
Type: CriticalDamping Description: Simplified model of the engine dynamics |
 |
throttleOnGround |
Type: Limiter Description: Limits the throttle from maximum negative thrust to 1 once on the ground |
|
dragNacelle3D |
Type: RealExpression[3] Description: Drag due to one nacelle |
|
dragNacelle |
Type: WorldForce Description: Drag of nacelle |
 |
translEng |
Type: FixedTranslation Description: Translation from engine rear end to the point where thrust and drag are acting on (currently no translation) |
 |
bodyEng |
Type: Body Description: Mass and inertia of engine |
 |
switch |
Type: Switch Description: Switch between two Real signals |
|
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 |