WOLFRAM SYSTEM MODELER
AircraftBaseInterface for a complete aircraft model |
 |
Diagram
Wolfram Language
In[1]:=
SystemModel["Aircraft.Physical.FixedWing.Interfaces.AircraftBase"]
Out[1]:=
Information
This base model compiles a complete fixed-wing aircraft model with a conventional wing configuration from the propulsion, surface and body components in the Parts package and takes input commands for the control actuator, i.e. commands for throttle position(s) as well as for the ailerons, rudder and elevator deflections. Additionally, all parameters of the aircraft other than the propulsion-specific parameters (except for the number of engines) are declared in this model. However, if the weight estimation method is used and any mass property is to be entered directly for any component instead of using the estimated value, it can be done in the corresponding component model in its Estimated Mass Properties parameter tab.
This base model is extended by the complete aircraft models found in the FixedWing package and can also be extended by the user's own fixed-wing aircraft designs with conventional wing configuration.
Parameters
Due to many couplings between the characteristics of different components of the aircraft, most of the aircraft parameters are declared on this top-level aircraft model instead of declaring them lower at the component models. The parameters declared here are propagated down to the components where they are needed.
Mass and Inertia
The first parameter in this tab, namely the weightEst parameter, declares whether the weight estimation method is used to estimate the mass properties of the aircraft component by component or if the known mass properties of the entire aircraft are entered directly. Depending on its value, the editing of the relevant mass property or design variable parameters is enabled. The theory behind the weight estimation method is described in the documentation of the corresponding components. The suggested workflow to be followed when using the weight estimation method in aircraft sizing is presented in GettingStarted.
If no weight estimation is used, the known mass properties to be entered are without the contribution of fuel (except for electric aircraft and gliders, for which they are the mass properties with the total mass), which all remain constant during a simulation. The mass of the initial fuel is defined separately with the initialMfuel parameter, and the consequent center of mass location and variable inertia tensor of the fuel system are estimated in the TankSystem component regardless of whether the weight estimation method is used or not. When the weight estimation method is used, the initial fuel mass is adjusted as a fraction of the estimated maximum fuel capacity in the Fuel System parameter tab of the propulsion component.
Propulsion
All parameters concerning propulsion and fuel or battery system are declared in the propulsion component, with the exception of the number of engines (nEng), which is declared in this base model. However, the choice of the propulsion type is done in this model by redeclaring the propulsion component into TurbofanPropulsion, TurbojetPropulsion, TurbopropPropulsion, PistonPropulsion, ElectricPropulsion or into a custom propulsion, as in Hawker Siddeley HS-121 Trident 3B.
Geometry
In this parameter tab, the coordinates of the wings with respect to the fuselage reference point, the dimensions of the fuselage and wings and the incidence, sweep and dihedral angles of the wings are to be entered. The fuselage reference point is defined at the half-length of all given maximum fuselage dimensions, as shown in Figure 1.
Figure 1: Definition of the fuselage reference point location. [1]
Aerodynamic Properties
The required aerodynamic properties to be entered to the aircraft model are the properties of the two-dimensional airfoils used in the main wing, horizontal tail and vertical tail and the surface roughness height on different surfaces. By default, the given surface roughness height for the entire aircraft (kSkinAC) is propagated to be used on the surfaces of all components, including the surface of the nacelles in the turbofan, turbojet and turboprop engines.
The derivation of the lift and drag coefficients of the wings and the fuselage from the given Aerodynamic Properties and Geometry parameters is described in the documentation for WingBody, HorizontalTail and VerticalTail components, and the derivation of the drag coefficients of the nacelles in the turbofan, turbojet and turboprop engines is described in their respective documentation.
Controls
The maximum control surface deflections given here are propagated to be used in the limiters in the Ailerons, HorizontalTail and VerticalTail components.
Derived Properties
This tab includes the parameters that are derived based on the parameters given on the previous tabs. The equations used to derive and estimate these values may be bypassed by entering a known value in the parameter input field.
Initialization
The parameters to define the initial position, orientation, and translational and rotational velocities are entered here. The initialization for the translational velocity is performed in this model from the Start Flight Conditions parameters, whereas the initialization for the position, orientation and angular velocity is performed in the Body model from the propagated Start Position and Start Orientation and Angular Velocities parameters.
Animation
By default, the Modelica Standard Library FixedShape primitives are used to visualize different components with simple box and cylinder shapes with the dimensions given in the Geometry parameters and by estimating them for certain components. However, if a CAD model of the complete aircraft model exists as an .obj file, it can be used by setting CADshapes as true and entering the path of the .obj file to CADpath field. This automatically disables the default animation in every component. The rotation and translation between the CAD object origin and the fuselage reference point can be entered to the translCADshape in the Body model.
Connectors
This model contains real inputs for the control actuators, a frame connected to the fuselage reference point (aircraftRP), and a FlightDataOut connector for forwarding the variables of the flight data as a feedback to the autopilots. The aircraftRP frame can be used, for example, to create physical connection to other aircraft, as is done in the GliderTow example.
The numbered real inputs for the throttle position commands (deltaThrot1Cmd - deltaThrot5Cmd) follow the numbering of the engines presented in the ConventionalPropulsion model. If a CustomPropulsion model is used, the unnumbered deltaThrotCmd real input adjusts its dimension to the now unconstrained number of engines defined as nEng.
Variables
The variables of the complete aircraft that are solved for in this model by fetching the required variables from the subcomponents include:
- Flight data variables, which are to be stored in the FlightData record and outputted through the FlightDataOut connector
- Drag coefficient and the lift-to-drag ratio (CDac and LDratio; aircraft lift coefficient is solved in the surfaces component)
- Kinetic energy (Ekin), potential energy (Epot), rotational energy (Erot) and their sum, the total energy (Etot)
- Total net power output (Pnet, derivative of total energy) and energy dissipation rate (Pdiss, total net power output subtracted by gross power used by engines)
- Mass properties
As the mass properties of a rigid multi-body system are not automatically solved, first the center of mass location for the entire aircraft including the contribution from the variable fuel mass (xCM, yCM, zCM) is calculated. Then, the moments of inertia around this center of mass (Ixx, Iyy, Izz) are solved by using the parallel axis theorem, and the total products of inertia (Ixy, Ixz, Iyz) are solved by summing the products of component masses and their coordinates with respect to the solved aircraft center of mass.
This method, however, is a minor simplification, as it considers the local frames of the main wing and horizontal tail surfaces to be parallel with the fuselage reference plane. In fact, the moments of inertia of the main wing and horizontal tail are solved in a frame parallel to their surfaces by considering the rotations around their incidence and dihedral angles.
References
[1] 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.
Parameters (151)
| weightEst |
Value: Type: Boolean Description: true, if weight estimation method is used for masses, center of mass location and inertia tensor |
|---|---|
| mDry |
Value: Type: Mass (kg) Description: Aircraft dry mass (total mass for electric aircraft and gliders) |
| initialMfuel |
Value: Type: Mass (kg) Description: Initial fuel mass |
| 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) |
| yCMdry |
Value: Type: Length (m) Description: Aircraft center of mass y-coordinate w.r.t. fuselage reference point (with total mass for electric aircraft and gliders, positive y-axis towards right) |
| zCMdry |
Value: Type: Length (m) Description: Aircraft center of mass z-coordinate w.r.t. fuselage reference point (with total mass for electric aircraft and gliders, positive z-axis towards ground) |
| IxxDry |
Value: Type: MomentOfInertia (kg·m²) Description: Aircraft moment of inertia about x-axis (with total mass for electric aircraft and gliders) |
| IyyDry |
Value: Type: MomentOfInertia (kg·m²) Description: Aircraft moment of inertia about y-axis (with total mass for electric aircraft and gliders) |
| IzzDry |
Value: Type: MomentOfInertia (kg·m²) Description: Aircraft moment of inertia about z-axis (with total mass for electric aircraft and gliders) |
| IxyDry |
Value: Type: MomentOfInertia (kg·m²) Description: Aircraft xy-product of moment of inertia (with total mass for electric aircraft and gliders) |
| IxzDry |
Value: Type: MomentOfInertia (kg·m²) Description: Aircraft xz-product of moment of inertia (with total mass for electric aircraft and gliders) |
| IyzDry |
Value: Type: MomentOfInertia (kg·m²) Description: Aircraft yz-product of moment of inertia (with total mass for electric aircraft and gliders) |
| MTOMdes |
Value: Type: Mass (kg) Description: Design maximum take-off mass |
| nPax |
Value: Type: Integer Description: Design number of passengers |
| mPLdes |
Value: Type: Mass (kg) Description: Design payload mass |
| machDes |
Value: Type: Real Description: Design Mach number |
| compMat |
Value: Type: Boolean Description: true, if composite materials are used in structures |
| qMax |
Value: Type: Pressure (Pa) Description: Maximum dynamic pressure |
| nMax |
Value: Type: Real Description: Maximum load factor |
| nEng |
Value: Type: Integer Description: Number of engines |
| wingMounted |
Value: if nEng == 0 then false else propulsion.wingMounted Type: Boolean |
| engineType |
Value: if nEng == 0 then 4 else propulsion.engineType Type: Integer |
| lFus |
Value: Type: Length (m) Description: Fuselage length |
| wFus |
Value: Type: Length (m) Description: Fuselage maximum width |
| hFus |
Value: Type: Length (m) Description: Fuselage maximum height |
| dFusHT |
Value: Type: Length (m) Description: Fuselage diameter at horizontal tail 1/4 chord |
| bWing |
Value: Type: Length (m) Description: Main wing span |
| 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 |
| cAil |
Value: Type: Length (m) Description: Aileron average chord |
| yAilRoot |
Value: Type: Length (m) Description: Aileron root y-coordinate w.r.t. fuselage centerline |
| yAilTip |
Value: Type: Length (m) Description: Aileron tip y-coordinate w.r.t. fuselage centerline |
| bHT |
Value: Type: Length (m) Description: Horizontal tail span |
| cHTroot |
Value: Type: Length (m) Description: Horizontal tail root chord |
| cHTtip |
Value: Type: Length (m) Description: Horizontal tail tip chord |
| tHTroot |
Value: Type: Length (m) Description: Horizontal tail root thickness |
| tHTtip |
Value: Type: Length (m) Description: Horizontal tail tip thickness |
| xHTrootLE |
Value: Type: Length (m) Description: Horizontal tail root leading edge x-coordinate w.r.t. fuselage reference point (positive x-axis towards nose) |
| zHTrootLE |
Value: Type: Length (m) Description: Horizontal tail root leading edge z-coordinate w.r.t. fuselage reference point (positive z-axis towards ground) |
| lambdaHT |
Value: Type: Angle (rad) Description: Horizontal tail sweep angle at 1/4 chord |
| iHT |
Value: Type: Angle (rad) Description: Horizontal tail incidence angle |
| Selv |
Value: Type: Area (m²) Description: Elevator area |
| bVT |
Value: Type: Length (m) Description: Vertical tail span |
| cVTroot |
Value: Type: Length (m) Description: Vertical tail root chord |
| cVTtip |
Value: Type: Length (m) Description: Vertical tail tip chord |
| tVTroot |
Value: Type: Length (m) Description: Vertical tail root thickness |
| tVTtip |
Value: Type: Length (m) Description: Vertical tail tip thickness |
| xVTrootLE |
Value: Type: Length (m) Description: Vertical tail root leading edge x-coordinate w.r.t. fuselage reference point (positive x-axis towards nose) |
| zVTroot |
Value: Type: Length (m) Description: Vertical tail root z-coordinate w.r.t fuselage reference point |
| lambdaVT |
Value: Type: Angle (rad) Description: Vertical tail sweep angle at 1/4 chord |
| Srdr |
Value: Type: Area (m²) Description: Rudder area |
| kSkinAC |
Value: Type: Length (m) Description: Surface roughness height (same value to be used for all components) |
| kSkinFus |
Value: kSkinAC Type: Length (m) Description: Fuselage surface roughness height |
| kSkinWing |
Value: kSkinAC Type: Length (m) Description: Main Wing surface roughness height |
| ClAlphaWing2D |
Value: Type: CurveSlope (rad⁻¹) Description: Change in the section lift coefficient of the main wing airfoil (2D) due to alpha |
| alpha0Wing2D |
Value: Type: Angle (rad) Description: Zero-lift angle of attack of the main wing airfoil (2D) |
| ClMaxWing2D |
Value: Type: Real Description: Maximum section lift coefficient of the main wing airfoil (2D) |
| kSkinHT |
Value: kSkinAC Type: Length (m) Description: Horizontal tail surface roughness height |
| ClAlphaHT2D |
Value: Type: CurveSlope (rad⁻¹) Description: Change in the section lift coefficient of the horizontal tail airfoil (2D) due to alpha |
| alpha0HT2D |
Value: Type: Angle (rad) Description: Zero-lift angle of attack of the horizontal tail airfoil (2D) |
| ClMaxHT2D |
Value: Type: Real Description: Maximum section lift coefficient of the horizontal tail airfoil (2D) |
| kSkinVT |
Value: kSkinAC Type: Length (m) Description: Vertical tail surface roughness height |
| ClAlphaVT2D |
Value: Type: CurveSlope (rad⁻¹) Description: Change in the section lift coefficient of the vertical tail airfoil (2D) due to alpha |
| deltaElvMax |
Value: Type: Angle (rad) Description: Maximum elevator deflection |
| deltaAilMax |
Value: Type: Angle (rad) Description: Maximum aileron deflection |
| deltaRdrMax |
Value: Type: Angle (rad) Description: Maximum rudder deflection |
| sigmaBeta |
Value: max(3.06 * (SrefVT / SrefWing) / (1 + cos(lambdaWing)) + 0.4 * (-tan(gammaWing) * (yWingAC - wFus / 2) + zWingRootLE) / wFus + 0.009 * (bWing ^ 2 / SrefWing) - 0.276, 0) Type: Real Description: Change in sidewash due to beta |
| rACcm |
Value: if weightEst then {xWingRootLE - lambdaWingLE * (yWingAC - wFus / 2) - 0.15 * cWingMean, 0, 0} else {xCMdry, yCMdry, zCMdry} Type: Length[3] (m) Description: Aircraft dry center of mass w.r.t. fuselage reference point (estimated to be at 15% of MAC if weight estimation method is used) |
| Cfus |
Value: Modelica.Constants.pi * (3 * (hFus / 2 + wFus / 2) - sqrt(10 * hFus / 2 * wFus / 2 + 3 * ((hFus / 2) ^ 2 + (wFus / 2) ^ 2))) Type: Length (m) Description: Fuselage circumference |
| SwetFus |
Value: Cfus * lFus * (1 - 2 / (lFus / (Cfus / Modelica.Constants.pi))) ^ (2 / 3) * (1 + 1 / (lFus / (Cfus / Modelica.Constants.pi)) ^ 2) Type: Area (m²) Description: Fuselage wetted area |
| FFfus |
Value: 1 + 0.0025 * (lFus / hFus) + 60 * (hFus / lFus) ^ 3 Type: Real Description: Fuselage form factor |
| CDmaxFus |
Value: 0.8 * lFus * hFus / SrefWing Type: Real Description: Maximum drag coefficient of the fuselage |
| nSeatAbs |
Value: if nPax > 180 then floor(0.9 * wFus / 0.5588) - 1 else floor(0.9 * wFus / 0.5588) Type: Real Description: Number of seats abreast |
| SrefWing |
Value: (cWingRoot + cWingTip) * (bWing - wFus) / 2 + cWingRoot * wFus Type: Area (m²) Description: Main wing reference area |
| ARwing |
Value: bWing ^ 2 / SrefWing Type: Real Description: Main wing aspect ratio |
| TRwing |
Value: cWingTip / cWingRoot Type: Real Description: Main wing taper ratio |
| cWingMean |
Value: 2 / 3 * cWingRoot * ((1 + TRwing + TRwing ^ 2) / (1 + TRwing)) Type: Length (m) Description: Main wing mean chord length |
| tWingMean |
Value: (yWingAC - wFus / 2) * (tWingTip - tWingRoot) / (bWing / 2 - wFus / 2) + tWingRoot Type: Length (m) Description: Main wing mean thickness |
| tauWing |
Value: tWingTip / cWingTip / (tWingRoot / cWingRoot) Type: Real Description: Ratio of thickness-to-chord ratios at the main wing tip and root |
| xWingAC |
Value: -0.25 * cWingMean Type: Length (m) Description: Main wing aerodynamic center from wing leading edge at mean chord (positive x-axis towards nose) |
| yWingAC |
Value: (cWingRoot - cWingMean) / (cWingRoot - cWingTip) * (bWing - wFus) / 2 + wFus / 2 Type: Length (m) Description: Main wing aerodynamic center from fuselage centerline (y-coordinate w.r.t. fuselage centerline of mean chord) |
| SwetWing |
Value: 2 * (SrefWing / cos(gammaWing) - cWingRoot * wFus) * (1 + 0.25 * (tWingRoot / cWingRoot) * (1 + tWingTip / cWingTip / (tWingRoot / cWingRoot) * TRwing) / (1 + TRwing)) Type: Area (m²) Description: Main wing wetted area |
| lambdaWingLE |
Value: atan((cWingRoot / 4 - cWingTip / 4 + tan(lambdaWing) * bWing / 2) / (bWing / 2)) Type: Angle (rad) Description: Main wing leading edge sweep angle |
| lambdaWingHC |
Value: atan((cWingTip / 4 - cWingRoot / 4 + tan(lambdaWing) * bWing / 2) / (bWing / 2)) Type: Angle (rad) Description: Main wing half-chord sweep angle |
| lambdaWingTE |
Value: atan((lambdaWingLE * ((bWing - wFus) / 2) + cWingTip - cWingRoot) / ((bWing - wFus) / 2)) Type: Angle (rad) Description: Main wing trailing edge sweep angle (at ailerons location) |
| CLmaxWing3D |
Value: 0.9 * ClMaxWing2D * cos(lambdaWing) Type: Real Description: Maximum lift coefficient of the main wing (3D) |
| CDmaxWing3D |
Value: 1.98 - 0.81 * (1 - Modelica.Constants.e ^ (-20 / ARwing)) Type: Real Description: Maximum drag coefficient of the main wing (3D) |
| FFwing |
Value: 0.421 * (2 + 4 * tWingMean / cWingMean + 240 * (tWingMean / cWingMean) ^ 4) Type: Real Description: Main wing form factor |
| sdWing |
Value: 0.9998 + 0.0421 * (wFus / bWing) - 2.6286 * (wFus / bWing) ^ 2 + 2 * (wFus / bWing) ^ 3 Type: Real Description: Fuselage drag factor for main wing |
| kdWing |
Value: -3.333 * 10 ^ (-4) * lambdaWing ^ 2 + 6.667 * 10 ^ (-5) * lambdaWing + 0.38 Type: Real Description: Empirical constant for Oswald efficiency factor for main wing |
| Sail |
Value: cAil * (yAilTip - yAilRoot) * 2 Type: Area (m²) Description: Aileron area (of both wings) |
| xAilAC |
Value: -(xCMdry - (xWingRootLE - lambdaWingLE * (yWingAC - wFus / 2))) - 0.25 * cWingMean - tan(lambdaWing) * ((yAilRoot + yAilTip) / 2 - yWingAC) - (cAilWingRoot + cAilWingTip) / 2 * 0.75 + cAil / 4 Type: Length (m) Description: Aileron aerodynamic center x-coordinate w.r.t. aircraft center of mass |
| yAilAC |
Value: (yAilRoot + yAilTip) / 2 Type: Length (m) Description: Aileron aerodynamic center y-coordinate w.r.t. fuselage centerline |
| cAilWingRoot |
Value: cWingRoot - (yAilRoot - wFus / 2) * 2 / (bWing - wFus) * (cWingRoot - cWingTip) Type: Length (m) Description: Local main wing chord at aileron root |
| cAilWingTip |
Value: cWingRoot - (yAilTip - wFus / 2) * 2 / (bWing - wFus) * (cWingRoot - cWingTip) Type: Length (m) Description: Local main wing chord at aileron tip |
| kCnDeltaAil |
Value: -0.350894 - 0.066355 * (yAilRoot / (bWing / 2)) ^ 4.15179 + 0.029308 * (bWing ^ 2 / SrefWing) Type: Real Description: Empirical factor for the yaw moment derivative due to ailerons |
| tauAil |
Value: 1.129 * (Sail / SrefWing) ^ 0.4044 - 0.1772 Type: Real Description: Aileron effectiveness parameter |
| SrefHT |
Value: (cHTroot + cHTtip) * (bHT - dFusHT) / 2 + cHTroot * dFusHT Type: Area (m²) Description: Horizontal tail reference area |
| ARht |
Value: bHT ^ 2 / SrefHT Type: Real Description: Aspect ratio of horizontal tail |
| TRht |
Value: cHTtip / cHTroot Type: Real Description: Taper ratio of horizontal tail |
| cHTmean |
Value: 2 / 3 * cHTroot * (1 + TRht + TRht ^ 2) / (1 + TRht) Type: Length (m) Description: Horizontal tail mean chord |
| tHTmean |
Value: bHT / 2 * (1 + 2 * TRht) / (3 + 3 * TRht) * (tHTtip - tHTroot) / (bHT / 2 - dFusHT / 2) + tHTroot Type: Length (m) Description: Horizontal tail mean thickness |
| lHTcm |
Value: abs(xHTrootLE - xCMdry - tan(lambdaHTle) * (bHT / 2 - dFusHT / 2) * (1 + 2 * TRht) / (3 + 3 * TRht) - 0.25 * cHTmean) Type: Length (m) Description: Horizontal tail arm length (from aircraft center of mass to horizontal tail 1/4 chord) |
| lHTwingAC |
Value: abs(xHTrootLE - (xWingRootLE - lambdaWingLE * (yWingAC - wFus / 2))) + tan(lambdaHTle) * (bHT / 2 - dFusHT / 2) * (1 + 2 * TRht) / (3 + 3 * TRht) + 0.25 * cHTmean - abs(xWingAC) Type: Length (m) Description: Horizontal tail arm length (from wing aerodynamic center to horizontal tail 1/4 chord) |
| vHT |
Value: SrefHT / SrefWing * (lHTcm / cWingMean) Type: Real Description: Horizontal tail volume coefficient |
| SwetHT |
Value: 2 * (SrefHT - cHTroot * dFusHT) * (1 + 0.25 * (tHTroot / cHTroot) * (1 + tHTtip / cHTtip / (tHTroot / cHTroot) * TRht) / (1 + TRht)) Type: Area (m²) Description: Horizontal tail wetted area |
| lambdaHTle |
Value: atan((cHTroot / 4 - cHTtip / 4 + tan(lambdaHT) * bHT / 2) / (bHT / 2)) Type: Angle (rad) Description: Horizontal tail leading edge sweep angle |
| CLmaxHT3D |
Value: 0.9 * ClMaxHT2D * cos(lambdaHT) Type: Real Description: Maximum lift coefficient of the horizontal tail (3D) |
| CDmaxHT3D |
Value: 1.98 - 0.81 * (1 - Modelica.Constants.e ^ (-20 / ARht)) Type: Real Description: Maximum drag coefficient of the horizontal tail (3D)*(SrefHT/SrefWing) |
| FFht |
Value: 1 + 0.1 * (1 - 0.893 * abs(zHTrootLE / hFus)) * (2 + 4 * tHTmean / cHTmean + 240 * (tHTmean / cHTmean) ^ 4) Type: Real Description: Horizontal tail form factor |
| sdHT |
Value: 0.9998 + 0.0421 * (dFusHT / bHT) - 2.6286 * (dFusHT / bHT) ^ 2 + 2 * (dFusHT / bHT) ^ 3 Type: Real Description: Fuselage drag factor for horizontal tail |
| kdHT |
Value: -3.333 * 10 ^ (-4) * lambdaHT ^ 2 + 6.667 * 10 ^ (-5) * lambdaHT + 0.38 Type: Real Description: Empirical constant for Oswald efficiency factor for horizontal tail |
| tauElv |
Value: 1.129 * (Selv / SrefHT) ^ 0.4044 - 0.1772 Type: Real Description: Elevator effectiveness parameter |
| SrefVT |
Value: (cVTroot + cVTtip) / 2 * bVT Type: Area (m²) Description: Vertical tail reference area |
| ARvt |
Value: bVT ^ 2 / SrefVT Type: Real Description: Aspect ratio of vertical tail |
| TRvt |
Value: cVTtip / cVTroot Type: Real Description: Taper ratio of vertical tail |
| cVTmean |
Value: 2 / 3 * cVTroot * (1 + TRvt + TRvt ^ 2) / (1 + TRvt) Type: Length (m) Description: Vertical tail mean chord |
| tVTmean |
Value: bVT * (1 + 2 * TRvt) / (3 + 3 * TRvt) * (tVTtip - tVTroot) / bVT + tVTroot Type: Length (m) Description: Vertical tail mean thickness |
| lVTcm |
Value: abs(xVTrootLE - xCMdry - tan(lambdaVTle) * bVT * (1 + 2 * TRvt) / (3 + 3 * TRvt) - 0.25 * cVTmean) Type: Length (m) Description: Vertical tail arm length (from aircraft center of mass to vertical tail 1/4 chord) |
| lVTwingAC |
Value: abs(xVTrootLE - (xWingRootLE - lambdaWingLE * (yWingAC - wFus / 2))) + tan(lambdaVTle) * bVT * (1 + 2 * TRvt) / (3 + 3 * TRvt) + 0.25 * cVTmean - abs(xWingAC) Type: Length (m) Description: Vertical tail arm length (from wing aerodynamic center to vertical tail aerodynamic center) |
| zVTac |
Value: zVTroot - bVT * (1 + 2 * TRvt) / (3 + 3 * TRvt) Type: Length (m) Description: Vertical tail center of pressure z-coordinate w.r.t. fuselage reference point |
| vVT |
Value: SrefVT / SrefWing * (lVTcm / bWing) Type: Real Description: Vertical tail volume coefficient |
| SwetVT |
Value: 2 * SrefVT * (1 + 0.25 * (tVTroot / cVTroot) * (1 + tVTtip / cVTtip / (tVTroot / cVTroot) * TRvt) / (1 + TRvt)) Type: Area (m²) Description: Vertical tail wetted area |
| lambdaVTle |
Value: atan((tan(lambdaVT) * bVT - cVTtip / 4 + cVTroot / 4) / bVT) Type: Angle (rad) Description: Vertical tail leading edge sweep angle |
| FFvt |
Value: 0.5 * (2 + 4 * tVTmean / cVTmean + 240 * (tVTmean / cVTmean) ^ 4) Type: Real Description: Vertical tail form factor |
| sdVT |
Value: 0.9998 Type: Real Description: Fuselage drag factor for vertical tail |
| kdVT |
Value: -3.333 * 10 ^ (-4) * lambdaVT ^ 2 + 6.667 * 10 ^ (-5) * lambdaVT + 0.38 Type: Real Description: Empirical constant for Oswald efficiency factor for vertical tail |
| tauRdr |
Value: 1.129 * (Srdr / SrefVT) ^ 0.4044 - 0.1772 Type: Real Description: Rudder effectiveness parameter |
| initialAltitude |
Value: 0 Type: Height (m) Description: Initial altitude |
| initialLatPosition |
Value: {0, 0} Type: Position[2] (m) Description: Initial lateral position of the aircraft (x and y coordinates in world frame) |
| initialVelocity |
Value: 0 Type: Velocity (m/s) Description: Initial velocity |
| initialTrack |
Value: 0 Type: Angle (rad) Description: Initial track angle |
| initialGamma |
Value: 0 Type: Angle (rad) Description: Initial flight path angle |
| initialPhi |
Value: 0 Type: Angle (rad) Description: Initial roll angle |
| initialTheta |
Value: 0 Type: Angle (rad) Description: Initial pitch angle |
| initialPsi |
Value: 0 Type: Angle (rad) Description: Initial yaw angle (heading) |
| initialAngularVelocity |
Value: {0, 0, 0} Type: AngularVelocity[3] (rad/s) Description: Initial {roll [p], pitch [q], yaw [r]} |
| CADshapes |
Value: Type: Boolean Description: true, if external CAD files are used for animation |
| CADpath |
Value: "modelica://Aircraft/Resources/CAD/PathName.obj" Type: String Description: Path for CAD file |
| T0 |
Value: atmos.T0 Type: Temperature (K) Description: Temperature at sea-level |
| rho0 |
Value: atmos.mAir * p0 / (atmos.R0 * T0) Type: Density (kg/m³) Description: Air density at sea-level |
| p0 |
Value: atmos.p0 Type: Pressure (Pa) Description: Static pressure at sea-level |
| a0 |
Value: sqrt(atmos.gammaAir * atmos.R0 / atmos.mAir * T0) Type: Velocity (m/s) Description: Speed of sound at sea-level |
| gammaAir |
Value: atmos.gammaAir Type: Real Description: Adiabatic index for air |
Outputs (1)
| xEtot |
Type: Real Description: State of aircraft total energy |
|---|
Connectors (11)
 |
deltaAilCmd |
Type: RealInput Description: Ailerons deflection command |
|---|---|---|
|
deltaElvCmd |
Type: RealInput Description: Elevator deflection command |
|
deltaRdrCmd |
Type: RealInput Description: Rudder deflection command |
|
deltaThrot1Cmd |
Type: RealInput Description: Engine 1 throttle command |
|
deltaThrot2Cmd |
Type: RealInput Description: Engine 2 throttle command |
|
deltaThrot3Cmd |
Type: RealInput Description: Engine 3 throttle command |
|
deltaThrot4Cmd |
Type: RealInput Description: Engine 4 throttle command |
|
deltaThrot5Cmd |
Type: RealInput Description: Engine 5 throttle command |
 |
aircraftRP |
Type: Frame_b Description: Connector to aircraft reference point |
 |
flightDataOut |
Type: FlightDataOut |
|
deltaThrotCmd |
Type: RealInput[nEng] Description: Engine throttle commands when custom propulsion is used |
Components (5)
 |
atmos |
Type: AtmosphericProperties |
|---|---|---|
 |
flightData |
Type: FlightData |
 |
body |
Type: Body |
 |
propulsion |
Type: ConventionalPropulsion Description: Propulsion model |
 |
surfaces |
Type: Conventional |
Extended by (7)
 |
Aircraft.Physical.FixedWing Narrow-body turbofan airliner: Hawker Siddeley HS-121 Trident 3B |
 |
Aircraft.Physical.FixedWing High-speed turboprop airliner: Saab 2000 |
 |
Aircraft.Physical.FixedWing Light-sport electric aircraft: Pipistrel Alpha Electro |
 |
Aircraft.Physical.FixedWing Model of a general aviation aircraft |
 |
Aircraft.Physical.FixedWing Mid-wing glider: Schweizer SGS 1-36 |
 |
Aircraft.Physical.FixedWing Narrow-body turbojet airliner: Douglas DC-8-20 |
 |
Aircraft.Physical.FixedWing Narrow-body turbofan airliner: Boeing 737-800 |