WOLFRAM SYSTEM MODELER

ElectricEngine

Electric engine: unparameterized

Diagram

Wolfram Language

In[1]:=
SystemModel["Aircraft.Physical.FixedWing.Parts.Propulsions.Engines.ElectricEngines.ElectricEngine"]
Out[1]:=

Information

This electric engine model extends the EngineBase model and models the thrust and mass (if weight estimation method is used) of an electric engine.

Parameters

The required parameters for the electric engine model are listed in the Propulsion tab, as shown in Figure 1.


Figure 1: Required input parameters for electric 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 ElectricPropulsion, and thus they can and should be left unchanged.

Thrust Available

The thrust available (Tavail) for electric 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 electric engines, the power available is invariable with flight conditions, and thus it always equals the engine power at sea level (P0).

Energy Consumption

The calculations for energy consumption are performed in the energySystem component.

Drag

The electric engine is considered to be installed completely inside the fuselage, and the drag due to propeller is omitted. Thus, the electric engine model currently has no drag.

Mass

If the weight estimation method is used and no engine mass is entered by the user, the engine mass is solved by using an empirical relationship based on the given P0 parameter value, as presented by Erä-Esko [1]

.

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.

References

[1]  Erä-Esko, N. (2022). "Development and Use of System Modeler 6DOF Flight Mechanics Model in Aircraft Conceptual Design."
      Available atmodelica://Aircraft/Resources/Documents/EraeEskoThesis.pdf.

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:

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

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: 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)

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: ElectricSystem

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

Extended by (1)

PipistrelPEM60MVLC

Aircraft.Physical.FixedWing.Parts.Propulsions.Engines.ElectricEngines

Electric engine: Pipistrel PEM 60MVLC