setState

Class: Aero.FixedWing.State
Namespace: Aero

Set state value to Aero.FixedWing.State object

Since R2021a

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Syntax

state = setState(state,statename,value)

Description

state = setState(state,statename,value) sets the state value to a specified state name value.

Input Arguments

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

State names, specified in a vector. You cannot set effective control variables created with asymmetric control surfaces. For more information on state names, see the Aero.FixedWing.State Properties.

Tip

Each vector of statename and value must be the same length.

Data Types: char | string

State values, specified as a vector.

  • If the states are all scalar constants, value is a numeric vector.

  • If one of more states are not scalar constants, value is a cell vector.

Tip

Each vector of statename and value must be the same length.

Output Arguments

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Modified input object with the modified states at the specified locations.

Examples

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Open Live Script

These examples show how to set the state value to specified state name.

Set Pitch Angle of Cruise State

Set the pitch angle of a cruise state.

[C182, CruiseState] = astC182();
CruiseState = setState(CruiseState, "Alpha", 5)
CruiseState = 
  State with properties:

                    Alpha: NaN
                     Beta: NaN
                 AlphaDot: 0
                  BetaDot: 0
                     Mass: 82.2981
                  Inertia: [3×3 table]
          CenterOfGravity: [1.2936 0 0]
         CenterOfPressure: [1.2250 0 0]
              AltitudeMSL: 5000
             GroundHeight: 0
                       XN: 0
                       XE: 0
                       XD: -5000
                        U: 220.1000
                        V: 0
                        W: 0
                      Phi: 0
                    Theta: -0.0073
                      Psi: 0
                        P: 0
                        Q: 0
                        R: 0
                   Weight: 2.6488e+03
              AltitudeAGL: 5000
                 Airspeed: NaN
              GroundSpeed: 220.1000
               MachNumber: NaN
             BodyVelocity: [NaN NaN NaN]
           GroundVelocity: [220.1000 0 0]
                       Ur: NaN
                       Vr: NaN
                       Wr: NaN
          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: NaN
              Environment: [1×1 Aero.Aircraft.Environment]
            ControlStates: [1×4 Aero.Aircraft.ControlState]
         OutOfRangeAction: "Limit"
         DiagnosticAction: "Warning"
               Properties: [1×1 Aero.Aircraft.Properties]
               UnitSystem: "English (ft/s)"
        TemperatureSystem: "Fahrenheit"
              AngleSystem: "Radians"

Set U, V, and W Velocity Components

Set the U, V, and W velocity components of a cruise state.

[C182, CruiseState] = astC182();
CruiseState = setState(CruiseState, ["U", "V", "W"], [50, 1, 10])
CruiseState = 
  State with properties:

                    Alpha: 0.1974
                     Beta: 0.0196
                 AlphaDot: 0
                  BetaDot: 0
                     Mass: 82.2981
                  Inertia: [3×3 table]
          CenterOfGravity: [1.2936 0 0]
         CenterOfPressure: [1.2250 0 0]
              AltitudeMSL: 5000
             GroundHeight: 0
                       XN: 0
                       XE: 0
                       XD: -5000
                        U: 50
                        V: 1
                        W: 10
                      Phi: 0
                    Theta: -0.0073
                      Psi: 0
                        P: 0
                        Q: 0
                        R: 0
                   Weight: 2.6488e+03
              AltitudeAGL: 5000
                 Airspeed: 51
              GroundSpeed: 51
               MachNumber: 0.0465
             BodyVelocity: [50 1 10]
           GroundVelocity: [50 1 10]
                       Ur: 50
                       Vr: 1
                       Wr: 10
          FlightPathAngle: 0.1974
              CourseAngle: 0.0200
     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: 2.6636
              Environment: [1×1 Aero.Aircraft.Environment]
            ControlStates: [1×4 Aero.Aircraft.ControlState]
         OutOfRangeAction: "Limit"
         DiagnosticAction: "Warning"
               Properties: [1×1 Aero.Aircraft.Properties]
               UnitSystem: "English (ft/s)"
        TemperatureSystem: "Fahrenheit"
              AngleSystem: "Radians"

Version History

Introduced in R2021a

See Also

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