setBodyVelocity

Class: Aero.FixedWing.State
Namespace: Aero

Calculate state from U, V, and W values

Since R2026a

Syntax

state = setBodyVelocity(state,U,V,W)

Description

state = setBodyVelocity(state,U,V,W) calculates the airspeed, alpha, and beta values from U, V, and W values for the Aero.FixedWing.State object specified by state.

Input Arguments

state — Aero.FixedWing.State object

object

Aero.FixedWing.State object for which to calculate airspeed, alpha, and beta values.

U — Forward component of ground velocity

50 (default) | scalar numeric

Forward component of ground velocity along the aircraft body x-axis, specified as a scalar numeric in these units.

Unit	Unit System
Meters per second (m/s)	'Metric'
Feet per second (ft/s)	'English (kts)'
Knots (kts)	'English (ft/s)'

Data Types: double

V — Side component of ground velocity

0 (default) | scalar numeric

Side component of ground velocity along the aircraft body y-axis, specified as a scalar numeric in these units.

Unit	Unit System
Meters per second (m/s)	'Metric'
Feet per second (ft/s)	'English (kts)'
Knots (kts)	'English (ft/s)'

Data Types: double

W — Downward component of ground velocity

0 (default) | scalar numeric

Downward component of ground velocity along the aircraft body z-axis, specified as a scalar numeric in these units.

Unit	Unit System
Meters per second (m/s)	'Metric'
Feet per second (ft/s)	'English (kts)'
Knots (kts)	'English (ft/s)'

Data Types: double

Output Arguments

state — Modified Aero.FixedWing.State object

scalar

Modified Aero.FixedWing.State object, returned as a scalar.

Data Types: double

Examples

Calculate Fixed-Wing State from U, V, and W Values

Calculate the airspeed, alpha, and beta values from U, V, and W values for state.

Create a fixed-wing state object, state.

state = Aero.FixedWing.State();

Set the body-fixed velocities U, V, and W using the setBodyVelocity method. setBodyVelocity converts the values to their Airspeed, Alpha, and Beta counterparts and sets state with these values.

state = setBodyVelocity(state, 50, 0, 0.2)

state = 
  State with properties:

                     Mass: 0
                  Inertia: [3×3 table]
          CenterOfGravity: [0 0 0]
         CenterOfPressure: [0 0 0]
              AltitudeMSL: 0
             GroundHeight: 0
                       XN: 0
                       XE: 0
                       XD: 0
                        U: 50
                        V: 0
                        W: 0.2000
                 Airspeed: 50.0004
                      Phi: 0
                    Theta: 0
                      Psi: 0
                        P: 0
                        Q: 0
                        R: 0
                    Alpha: 0.0040
                     Beta: 0
                 AlphaDot: 0
                  BetaDot: 0
                   Weight: 0
              AltitudeAGL: 0
              GroundSpeed: 50.0004
               MachNumber: 0.1469
             BodyVelocity: [50 0 0.2000]
           GroundVelocity: [50 0 0.2000]
                       Ug: 50
                       Vg: 0
                       Wg: 0.2000
          FlightPathAngle: 0.0040
              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: 1.5313e+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"

Algorithms

The Aero.FixedWing.State.setBodyVelocity method uses these equations to calculate airspeed, alpha, and beta values from U, V, and W values.

airspeed = sqrt(U^2 + V^2 + W^2)
alpha = atan2(W,U)
beta = asin(V/airspeed)

Version History

Introduced in R2026a