forcesAndMoments

Class: Aero.FixedWing
Namespace: Aero

Calculate forces and moments of fixed-wing aircraft

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Syntax

[F,M] = forcesAndMoments(aircraft,state)
[F,M] = forcesAndMoments(aircraft,state,OutputReferenceFrame=outputReference)

Description

[F,M] = forcesAndMoments(aircraft,state) calculates the forces and moments of a fixed-wing aircraft, aircraft, based around a state state.

[F,M] = forcesAndMoments(aircraft,state,OutputReferenceFrame=outputReference) calculates the forces and moments using an output reference.

Input Arguments

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Aero.FixedWing object, specified as a scalar.

Aero.FixedWing.State object, specified as a scalar.

Output reference frame of the forces and moments calculation, specified as:

  • "Body"

  • "Wind"

  • "Stability"

Example: OutputReferenceFrame="Stability"

Output Arguments

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Forces output in OutputReferenceFrame, returned as a three-element vector.

Moments output in OutputReferenceFrame, returned as a three-element vector.

Examples

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Open Live Script

This example shows to calculate the forces and moments of a Cessna 182.

[C182,CruiseState] = astC182();
[F,M] = forcesAndMoments(C182, CruiseState)
F = 3×1

    0.0992
         0
    0.1024


M = 3×1

         0
 -125.7803
         0
Open Live Script

Create and set up dynamic behavior and the current state for an Aero.FixedWing object aircraft.

Create a fixed-wing object. 

aircraft = Aero.FixedWing()
aircraft = 
  FixedWing with properties:

        ReferenceArea: 0
        ReferenceSpan: 0
      ReferenceLength: 0
         Coefficients: [1×1 Aero.FixedWing.Coefficient]
     DegreesOfFreedom: "6DOF"
             Surfaces: [1×0 Aero.FixedWing.Surface]
              Thrusts: [1×0 Aero.FixedWing.Thrust]
          AspectRatio: NaN
           Properties: [1×1 Aero.Aircraft.Properties]
           UnitSystem: "Metric"
    TemperatureSystem: "Kelvin"
          AngleSystem: "Radians"

Define the reference area, span, and length. These quantities are used to compute forces and moments from nondimensional coefficients.

aircraft.ReferenceArea = 16;
aircraft.ReferenceSpan = 11;
aircraft.ReferenceLength = 1.5
aircraft = 
  FixedWing with properties:

        ReferenceArea: 16
        ReferenceSpan: 11
      ReferenceLength: 1.5000
         Coefficients: [1×1 Aero.FixedWing.Coefficient]
     DegreesOfFreedom: "6DOF"
             Surfaces: [1×0 Aero.FixedWing.Surface]
              Thrusts: [1×0 Aero.FixedWing.Thrust]
          AspectRatio: 7.5625
           Properties: [1×1 Aero.Aircraft.Properties]
           UnitSystem: "Metric"
    TemperatureSystem: "Kelvin"
          AngleSystem: "Radians"

To define the aircraft dynamic behavior, set lift and drag coefficients.

aircraft = setCoefficient(aircraft, ["CD", "CD", "CL", "CL"], ["Zero", "Alpha", "Zero", "Alpha"], [0.027, 0.121, 0.307, 4.41])
aircraft = 
  FixedWing with properties:

        ReferenceArea: 16
        ReferenceSpan: 11
      ReferenceLength: 1.5000
         Coefficients: [1×1 Aero.FixedWing.Coefficient]
     DegreesOfFreedom: "6DOF"
             Surfaces: [1×0 Aero.FixedWing.Surface]
              Thrusts: [1×0 Aero.FixedWing.Thrust]
          AspectRatio: 7.5625
           Properties: [1×1 Aero.Aircraft.Properties]
           UnitSystem: "Metric"
    TemperatureSystem: "Kelvin"
          AngleSystem: "Radians"

Define the current state of the aircraft.

state = Aero.FixedWing.State(...
  "Mass", 1400,...
  "Airspeed", 67,...
  "AltitudeMSL",2000)
state = 
  State with properties:

                     Mass: 1400
                  Inertia: [3×3 table]
          CenterOfGravity: [0 0 0]
         CenterOfPressure: [0 0 0]
              AltitudeMSL: 2000
             GroundHeight: 0
                       XN: 0
                       XE: 0
                       XD: -2000
                        U: 67
                        V: 0
                        W: 0
                 Airspeed: 67
                      Phi: 0
                    Theta: 0
                      Psi: 0
                        P: 0
                        Q: 0
                        R: 0
                    Alpha: 0
                     Beta: 0
                 AlphaDot: 0
                  BetaDot: 0
                   Weight: 13734
              AltitudeAGL: 2000
              GroundSpeed: 67
               MachNumber: 0.1969
             BodyVelocity: [67 0 0]
           GroundVelocity: [67 0 0]
                       Ug: 67
                       Vg: 0
                       Wg: 0
          FlightPathAngle: 0
              CourseAngle: 0
     InertialToBodyMatrix: [3×3 double]
     BodyToInertialMatrix: [3×3 double]
         BodyToWindMatrix: [3×3 double]
         WindToBodyMatrix: [3×3 double]
    BodyToStabilityMatrix: [3×3 double]
    StabilityToBodyMatrix: [3×3 double]
          DynamicPressure: 2.7495e+03
              Environment: [1×1 Aero.Aircraft.Environment]
            ControlStates: [1×0 Aero.Aircraft.ControlState]
         OutOfRangeAction: "Limit"
         DiagnosticAction: "Warning"
               Properties: [1×1 Aero.Aircraft.Properties]
               UnitSystem: "Metric"
        TemperatureSystem: "Kelvin"
              AngleSystem: "Radians"

Calculate the forces and moments on the aircraft.

[F, M] = forcesAndMoments(aircraft, state)
F = 3×1
103 ×

   -1.1878
         0
    0.2284


M = 3×1

     0
     0
     0

Version History

Introduced in R2021a

See Also

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