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fixedWingState

Define fixed-wing aircraft state

Since R2021b

    Description

    state = fixedWingState(aircraft) returns a fixed-wing state object created from a fixed-wing aircraft, aircraft, using a default environment.

    state = fixedWingState(aircraft,environment) returns a fixed-wing state object using a specified environment, environment.

    state = fixedWingState(___,Name=Value) returns a fixed-wing state object with an environment defined by Name=Value arguments.

    example

    Examples

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    Create a fixed-wing aircraft state object from a fixed-wing aircraft object

    aircraft = astC182();
    state = fixedWingState(aircraft)
    state = 
      State with properties:
    
                        Alpha: 0
                         Beta: 0
                     AlphaDot: 0
                      BetaDot: 0
                         Mass: 0
                      Inertia: [3x3 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
                          Phi: 0
                        Theta: 0
                          Psi: 0
                            P: 0
                            Q: 0
                            R: 0
                       Weight: 0
                  AltitudeAGL: 0
                     Airspeed: 50
                  GroundSpeed: 50
                   MachNumber: 0.0448
                 BodyVelocity: [50 0 0]
               GroundVelocity: [50 0 0]
                           Ur: 50
                           Vr: 0
                           Wr: 0
              FlightPathAngle: 0
                  CourseAngle: 0
         InertialToBodyMatrix: [3x3 double]
         BodyToInertialMatrix: [3x3 double]
             BodyToWindMatrix: [3x3 double]
             WindToBodyMatrix: [3x3 double]
        BodyToStabilityMatrix: [3x3 double]
        StabilityToBodyMatrix: [3x3 double]
              DynamicPressure: 2.9711
                  Environment: [1x1 Aero.Aircraft.Environment]
                ControlStates: [1x4 Aero.Aircraft.ControlState]
             OutOfRangeAction: "Limit"
             DiagnosticAction: "Warning"
                   Properties: [1x1 Aero.Aircraft.Properties]
                   UnitSystem: "English (ft/s)"
            TemperatureSystem: "Fahrenheit"
                  AngleSystem: "Radians"
    
    

    Create a fixed-wing aircraft state object from a fixed-wing aircraft object and specify the mass using positional arguments.

    aircraft = astC182();
    state = fixedWingState(aircraft,"Mass",500)
    state = 
      State with properties:
    
                        Alpha: 0
                         Beta: 0
                     AlphaDot: 0
                      BetaDot: 0
                         Mass: 500
                      Inertia: [3x3 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
                          Phi: 0
                        Theta: 0
                          Psi: 0
                            P: 0
                            Q: 0
                            R: 0
                       Weight: 1.6093e+04
                  AltitudeAGL: 0
                     Airspeed: 50
                  GroundSpeed: 50
                   MachNumber: 0.0448
                 BodyVelocity: [50 0 0]
               GroundVelocity: [50 0 0]
                           Ur: 50
                           Vr: 0
                           Wr: 0
              FlightPathAngle: 0
                  CourseAngle: 0
         InertialToBodyMatrix: [3x3 double]
         BodyToInertialMatrix: [3x3 double]
             BodyToWindMatrix: [3x3 double]
             WindToBodyMatrix: [3x3 double]
        BodyToStabilityMatrix: [3x3 double]
        StabilityToBodyMatrix: [3x3 double]
              DynamicPressure: 2.9711
                  Environment: [1x1 Aero.Aircraft.Environment]
                ControlStates: [1x4 Aero.Aircraft.ControlState]
             OutOfRangeAction: "Limit"
             DiagnosticAction: "Warning"
                   Properties: [1x1 Aero.Aircraft.Properties]
                   UnitSystem: "English (ft/s)"
            TemperatureSystem: "Fahrenheit"
                  AngleSystem: "Radians"
    
    

    Create a fixed-wing aircraft state object from a fixed-wing aircraft object using a custom environment and Name=Value arguments.

    aircraft = astC182();
    state = fixedWingState(aircraft,aircraftEnvironment(aircraft,"COESA",1000))
    state = 
      State with properties:
    
                        Alpha: 0
                         Beta: 0
                     AlphaDot: 0
                      BetaDot: 0
                         Mass: 0
                      Inertia: [3x3 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
                          Phi: 0
                        Theta: 0
                          Psi: 0
                            P: 0
                            Q: 0
                            R: 0
                       Weight: 0
                  AltitudeAGL: 0
                     Airspeed: 50
                  GroundSpeed: 50
                   MachNumber: 0.0449
                 BodyVelocity: [50 0 0]
               GroundVelocity: [50 0 0]
                           Ur: 50
                           Vr: 0
                           Wr: 0
              FlightPathAngle: 0
                  CourseAngle: 0
         InertialToBodyMatrix: [3x3 double]
         BodyToInertialMatrix: [3x3 double]
             BodyToWindMatrix: [3x3 double]
             WindToBodyMatrix: [3x3 double]
        BodyToStabilityMatrix: [3x3 double]
        StabilityToBodyMatrix: [3x3 double]
              DynamicPressure: 2.8851
                  Environment: [1x1 Aero.Aircraft.Environment]
                ControlStates: [1x4 Aero.Aircraft.ControlState]
             OutOfRangeAction: "Limit"
             DiagnosticAction: "Warning"
                   Properties: [1x1 Aero.Aircraft.Properties]
                   UnitSystem: "English (ft/s)"
            TemperatureSystem: "Fahrenheit"
                  AngleSystem: "Radians"
    
    

    Input Arguments

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    Fixed-wing aircraft object, specified as a scalar.

    Fixed-wing aircraft environment name, specified as a scalar string.

    Tip

    This argument also exists as the name-value argument Environment. If you specify the Environment name-value argument, its value supersedes the environment positional argument.

    Data Types: string

    Name-Value Arguments

    Specify optional pairs of arguments as Name1=Value1,...,NameN=ValueN, where Name is the argument name and Value is the corresponding value. Name-value arguments must appear after other arguments, but the order of the pairs does not matter.

    Before R2021a, use commas to separate each name and value, and enclose Name in quotes.

    Example: "Mass",500

    Unit system, specified as 'Metric', 'English (kts)', 'English (ft/s)'.

    Angle system, specified as 'Radians' or 'Degrees'.

    Temperature system, specified as 'Kelvin', 'Celsius', 'Rankine', or 'Fahrenheit'.

    Fixed-wing aircraft mass, specified as a scalar numeric in these units.

    UnitUnit System

    newtons (N)

    'Metric'

    slugs (slug)

    'English (kts)' and 'English (ft/s)'

    Data Types: double

    Inertial matrix of aircraft, specified as a 3-by-3 table of numeric values specifying the body in this matrix form.

     XYZ
    XIxxIxyIxz
    YIyxIyyIyz
    ZIzxIzyIzz

    The matrix has these units.

    UnitUnit System

    kilogram meters squared (kg m^2)

    'Metric'

    slug feet squared (slug ft^2)

    'English (kts)' and 'English (ft/s)'

    Data Types: double

    Location of center of gravity on fixed-wing aircraft in body frame, specified as a three-element vector in these units.

    UnitUnit System

    Meters (m)

    'Metric'

    Feet (ft)

    'English (kts)' and 'English (ft/s)'

    Data Types: double

    Location of center of pressure on fixed-wing aircraft in body frame, specified as a three-element vector in these units.

    UnitUnit System

    Meters (m)

    'Metric'

    Feet (ft)

    'English (kts)' and 'English (ft/s)'

    Data Types: double

    Altitude above sea level, specified as a scalar numeric in these units.

    UnitUnit System

    Meters (m)

    'Metric'

    Feet (ft)

    'English (kts)' and 'English (ft/s)'

    Data Types: double

    Ground height above sea level, specified as a scalar numeric in these units.

    UnitUnit System

    Meters (m)

    'Metric'

    Feet (ft)

    'English (kts)' and 'English (ft/s)'

    Data Types: double

    North position of fixed-wing aircraft, specified as a scalar numeric in these units.

    UnitUnit System

    Meters (m)

    'Metric'

    Feet (ft)

    'English (kts)' and 'English (ft/s)'

    Data Types: double

    East position of fixed-wing aircraft, specified as a scalar numeric in these units.

    UnitUnit System

    Meters (m)

    'Metric'

    Feet (ft)

    'English (kts)' and 'English (ft/s)'

    Data Types: double

    Forward component of ground velocity, specified as a scalar numeric in these units.

    UnitUnit System

    Meters per second (m/s)

    'Metric'

    Feet per second (ft/s)

    'English (kts)'

    Knots (kts)

    'English (ft/s)'

    Data Types: double

    Side component of ground velocity, specified as a scalar numeric in these units.

    UnitUnit System

    Meters per second (m/s)

    'Metric'

    Feet per second (ft/s)

    'English (kts)'

    Knots (kts)

    'English (ft/s)'

    Data Types: double

    Downward component of ground velocity, specified as a scalar numeric in these units.

    UnitUnit System

    Meters per second (m/s)

    'Metric'

    Feet per second (ft/s)

    'English (kts)'

    Knots (kts)

    'English (ft/s)'

    Data Types: double

    Euler roll angle, specified as a scalar numeric in units of radians or degrees, depending on the AngleSystem property.

    Data Types: double

    Euler pitch angle, specified as a scalar numeric in units of radians or degrees, depending on the AngleSystem property.

    Data Types: double

    Euler yaw angle, specified as a scalar numeric in units of radians or degrees, depending on the AngleSystem property.

    Data Types: double

    Body roll rate, specified as a scalar numeric in units of radians per second or degrees per second, depending on the AngleSystem property.

    Data Types: double

    Body pitch rate, specified as a scalar numeric in units of radians per second or degrees per second, depending on the AngleSystem property.

    Data Types: double

    Body yaw rate, specified as a scalar numeric in units of radians per second or degrees per second, depending on the AngleSystem property.

    Data Types: double

    Angle of attack rate on fixed-wing aircraft, specified as a scalar numeric in units of radians per second or degrees per second, depending on the AngleSystem property.

    Data Types: double

    Angle of sideslip rate on the fixed-wing aircraft, specified as a scalar numeric in units of radians per second or degrees per second, depending on the AngleSystem property.

    Data Types: double

    Current control state values, specified as a vector.

    Data Types: double

    Definition of current environment, contained in an Aero.Aircraft.Environment object, specified as a scalar.

    Tip

    This argument also exists as the environment positional argument. If you specify the Environment name-value argument, its value supersedes the environment positional argument.

    Output Arguments

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    Aero.FixedWing.State objects, returned as a matrix the same size as environment.

    Version History

    Introduced in R2021b