Aero.FixedWing.State Class

Namespace: Aero

Define condition of Aero.FixedWing aircraft at time instant

Since R2021a

Description

Use the Aero.FixedWing.State class to define the condition of an Aero.FixedWing aircraft at a time instant. The Aero.FixedWing.State object contains the information about the current state of an aircraft at a single instance in time. A subclass can inherit the Aero.FixedWing.State.

• To get dependent properties defined by subclass, use the getState method.

• To set dependent properties, use the setState method.

• To use custom state properties within the Aero.FixedWing object methods, create a subclass.

Class Attributes

Sealed

false

For information on class attributes, see Class Attributes.

Creation

Description

Aero.FixedWing.State creates a single Aero.FixedWing.State object with default property values..

Aero.FixedWing.State(N) creates an N-by-N matrix of Aero.FixedWing.State.

Aero.FixedWing.State(M,N,P,...) or Aero.FixedWing.State([M N P ...]) creates an M-by-N-by-P-by-... array of Aero.FixedWing.State.

Aero.FixedWing.State(size(A)) creates an Aero.FixedWing.State object that is the same size as A and all Aero.FixedWing.State objects.

Aero.FixedWing.State(__,property,propertyValue) creates an array of Aero.FixedWing.State objects with property, propertyValue pairs applied to each of the Aero.FixedWing array objects. For a list of properties, see Properties.

Input Arguments

N — Number of fixed-wing objects

scalar

Number of fixed-wing objects, specified as a scalar.

M — Number of fixed-wing objects

scalar

Number of fixed-wing objects, specified as a scalar.

P — Number of fixed-wing objects

scalar

Number of fixed-wing objects, specified as a scalar.

A — Size of fixed-wing object

scalar

Size of fixed-wing object, specified as a scalar.

Properties

Public Properties

UnitSystem — Unit system

'Metric' (default) | 'English (kts)' | 'English (ft/s)' | scalar string | character vector

Unit system, specified as a scalar string or character vector.

Attributes:

GetAccess	public
SetAccess	public

Data Types: string | char

AngleSystem — Angle system

'Radians' (default) | 'Degrees'

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

Attributes:

GetAccess	public
SetAccess	public

Data Types: string | char

TemperatureSystem — Temperature system

'Kelvin' (default) | 'Celsius' | 'Rankine' | 'Fahrenheit'

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

Attributes:

GetAccess	public
SetAccess	public

Data Types: string | char

Mass — Fixed-wing aircraft mass

0 (default) | scalar numeric

Fixed-wing aircraft mass, specified as a scalar numeric, in the units:

Unit	Unit System
newtons (N)	'Metric'
slugs (slug)	'English (kts)' and 'English (ft/s)'

Attributes:

GetAccess	public
SetAccess	public

Data Types: string | char

Inertia — Inertial matrix of aircraft

3-by-3 table of numeric values (default) | scalar numeric

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

	X	Y	Z
X	Ixx	Ixy	Ixz
Y	Iyx	Iyy	Iyz
Z	Izx	Izy	Izz

The matrix has these units:

Unit	Unit System
kilogram meters squared (kg m^2)	'Metric'
slug feet squared (slug ft^2)	'English (kts)' and 'English (ft/s)'

Attributes:

GetAccess	public
SetAccess	public

Data Types: string | char

CenterOfGravity — Location of center of gravity

[0, 0, 0] (default) | three-element vector

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

Unit	Unit System
Meters (m)	'Metric'
Feet (ft)	'English (kts)' and 'English (ft/s)'

Attributes:

GetAccess	public
SetAccess	public

Data Types: string | char

CenterOfPressure — Location of center of pressure

[0, 0, 0] (default) | three-element vector

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

Unit	Unit System
Meters (m)	'Metric'
Feet (ft)	'English (kts)' and 'English (ft/s)'

Attributes:

GetAccess	public
SetAccess	public

Data Types: string | char

AltitudeMSL — Altitude above sea level

0 (default) | scalar numeric

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

Unit	Unit System
Meters (m)	'Metric'
Feet (ft)	'English (kts)' and 'English (ft/s)'

Attributes:

GetAccess	public
SetAccess	public

Data Types: string | char

GroundHeight — Ground height above sea level

0 (default) | scalar numeric

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

Unit	Unit System
Meters (m)	'Metric'
Feet (ft)	'English (kts)' and 'English (ft/s)'

Attributes:

GetAccess	public
SetAccess	public

Data Types: string | char

XN — North position of fixed-wing aircraft

0 (default) | scalar numeric

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

Unit	Unit System
Meters (m)	'Metric'
Feet (ft)	'English (kts)' and 'English (ft/s)'

Attributes:

GetAccess	public
SetAccess	public

Data Types: string | char

XE — East position of fixed-wing aircraft

0 (default) | scalar numeric

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

Unit	Unit System
Meters (m)	'Metric'
Feet (ft)	'English (kts)' and 'English (ft/s)'

Attributes:

GetAccess	public
SetAccess	public

Data Types: string | char

U — Forward component of ground velocity

50 (default) | scalar numeric

Forward component of ground velocity, 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)'

Attributes:

GetAccess	public
SetAccess	public

Data Types: string | char

V — Side component of ground velocity

0 (default) | scalar numeric

Side component of ground velocity, 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)'

Attributes:

GetAccess	public
SetAccess	public

Data Types: string | char

W — Downward component of ground velocity

0 (default) | scalar numeric

Downward component of ground velocity, 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)'

Attributes:

GetAccess	public
SetAccess	public

Data Types: string | char

Phi — Euler roll angle

0 (default) | scalar numeric

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

Attributes:

GetAccess	public
SetAccess	public

Data Types: string | char

Theta — Euler pitch angle

0 (default) | scalar numeric

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

Attributes:

GetAccess	public
SetAccess	public

Data Types: string | char

Psi — Euler yaw angle

0 (default) | scalar numeric

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

Attributes:

GetAccess	public
SetAccess	public

Data Types: string | char

P — Body roll rate

0 (default) | scalar numeric

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

Attributes:

GetAccess	public
SetAccess	public

Data Types: string | char

Q — Body pitch rate

0 (default) | scalar numeric

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

Attributes:

GetAccess	public
SetAccess	public

Data Types: string | char

R — Body yaw rate

0 (default) | scalar numeric

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

Attributes:

GetAccess	public
SetAccess	public

Data Types: string | char

AlphaDot — Angle of attack rate on fixed-wing aircraft

0 (default) | scalar numeric

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.

Attributes:

GetAccess	public
SetAccess	public

Data Types: string | char

BetaDot — Angle of sideslip rate on fixed-wing aircraft

0 (default) | scalar numeric

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.

Attributes:

GetAccess	public
SetAccess	public

Data Types: string | char

ControlStates — Current control state values

vector

Current control state values, specified as a vector.

• To set up control states, use setupControlStates.

• To set the control state positions, use setState.

• To get the control state positions, use getState.

You cannot set effective control variables created with asymmetric control surfaces.

Attributes:

GetAccess	public
SetAccess	public

Data Types: string | char

Environment — Definition of current environment

scalar

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

Attributes:

GetAccess	public
SetAccess	public

Data Types: string | char

Protected Properties

Weight — Fixed-wing aircraft weight

scalar numeric

Fixed-wing aircraft weight, specified as a scalar numeric, in these units:

Unit	Unit System
newtons (N)	'Metric'
pound-force (lbf)	'English (kts)' and 'English (ft/s)'

Weight depends on the values of the Mass and Gravity properties of the Aero.Aircraft.Environment object, with the equation

Weight = Mass * Environment.Gravity.

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: double

AltitudeAGL — Altitude above ground level

scalar numeric

Altitude above ground level, specified as a scalar numeric value in these units:

Unit	Unit System
meters (m)	'Metric'
feet (ft)	'English (kts)' and 'English (ft/s)'

AltitudeAGL depends on the values of the AltitudeMSL and GroundHeight public properties, with the equation:

AltitudeAGL = AltitudeMSL - GroundHeight.

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: double

XD — Down position of fixed-wing aircraft

0 (default) | scalar numeric

Down position of fixed-wing aircraft, specified as a scalar numeric in these units:

Unit	Unit System
Meters (m)	'Metric'
Feet (ft)	'English (kts)' and 'English (ft/s)'

XD depends on the value of the AltitudeMSL public property, with the equation

XD = -1 * AltitudeMSL.

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: double

Airspeed — Current airspeed of fixed-wing aircraft

0 (default) | scalar numeric

Current airspeed of fixed-wing aircraft, specified as a scalar numeric in these units:

Unit	Unit System
Meters/sec (m/s)	'Metric'
Feet/sec (ft/s)	'English (ft/s)'
knots (kts)	'English (kts)'

Airspeed depends on the values of the Ur, Vr, and Wr public properties, with the equation

Airspeed = sqrt(Ur² + Vr²+Wr²).

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: double

GroundSpeed — Current ground speed of fixed-wing aircraft

three-element vector

Current ground speed of fixed-wing aircraft, specified as a three-element vector in these units:

Unit	Unit System
Meters/sec (m/s)	'Metric'
Feet/sec (ft/s)	'English (ft/s)'
knots (kts)	'English (kts)'

Groundspeed depends on the values of the U, V, and R public properties, with the equation

Groundspeed = [U, V, W].

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: double

MachNumber — Mach number

numeric scalar

Mach number of fixed-wing aircraft, specified as a numeric scalar.

MachNumber depends on the values of the AirSpeed and SpeedOfSound public properties, with the equation

MachNumber = AirSpeed/Environment.SpeedOfSound.

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: double

BodyVelocity — Body velocity of fixed-wing aircraft

three-element vector

Body velocity of fixed-wing aircraft, specified as a three-element vector.

BodyVelocity depends on the values of the GroundSpeed, Phi, Theta, and Psi public properties, with the equation

BodyVelocity = GroundVelocity - InertialToBodyMatrix * Environment.WindVelocity.

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: double

GroundVelocity — Ground velocity of fixed-wing aircraft

three-element vector

Ground velocity of the fixed-wing aircraft, specified as a three-element vector, defined with the equation

GroundVelocity = [U, V, W].

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: double

Ur — X component of body velocity

scalar numeric

X component of body velocity, specified as scalar numeric. Ur depends on BodyVelocity.

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: double

Vr — Y component of body velocity

scalar numeric

Y component of body velocity, specified as scalar numeric. Ur depends on BodyVelocity.

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: double

Wr — Z component of body velocity

scalar numeric

Z component of body velocity, specified as scalar numeric. Ur depends on BodyVelocity.

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: double

FlightPathAngle — Flight path angle

scalar numeric

Flight path angle, specified as a scalar numeric in units of radians or degrees depending on the AngleSystem property. FlightPathAngle is defined with the equation:

FlightPathAngle = atan2(W,U).

.

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: double

CourseAngle — Course angle

scalar numeric

Course angle, specified as a scalar numeric in units of radians or degrees depending on the AngleSystem property. CourseAngle depends on V and U with the equation

CourseAngle = atan2(V,U).

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: double

Alpha — Angle of attack

scalar numeric

Angle of attack, specified as a scalar numeric in units of radians or degrees depending on the AngleSystem property. Alpha depends on Wr and Ur with the equation:

Alpha = atan2(Wr,Ur).

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: double

Beta — Angle of side slip

scalar numeric

Angle of side slip, specified as a scalar numeric in units of radians or degrees depends on the AngleSystem property. Beta depends on Vr and Airspeed with the equation:

Beta = asin(Vr/Airspeed).

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: double

InertialToBodyMatrix — Inertial to body axes transformation matrix

3-by-3 matrix

Inertial to body axes transformation matrix, specified as a 3-by-3 matrix to convert stability axes to body axes. This property depends on the Phi, Theta, and Psi properties.

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: double

BodyToInertialMatrix — Body axes to stability axes transformation matrix

3-by-3 matrix

Body axes to stability axes transformation matrix, specified as a 3-by-3 matrix to convert stability axes to body axes. This property depends on the Phi, Theta, and Psi properties.

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: double

BodyToWindMatrix — Body to wind axes transformation matrix

3-by-3 matrix

Body to wind axes transformation matrix, specified as a 3-by-3 matrix to convert body axes to wind axes. This property depends on the Alpha and Beta properties.

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: double

WindToBodyMatrix — Wind to body axes transformation matrix

3-by-3 matrix

Wind to body axes transformation matrix, specified as a 3-by-3 matrix to convert wind axes to the body axes. This property depends on the Alpha and Beta properties.

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: double

BodyToStabilityMatrix — Body axes to stability axes transformation matrix

3-by-3 matrix

Body axes to stability axes transformation matrix, specified as a 3-by-3 matrix. For a definition of BodyToStabilityMatrix, see Algorithms.

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: string | char

StabilityToBodyMatrix — Stability axes to body matrix axes transformation matrix

3-by-3 matrix

Stability axes to body matrix axes transformation matrix, specified as a 3-by-3 matrix. For a definition of StabilityToBodyMatrix, see Algorithms.

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: string | char

DynamicPressure — Dynamic pressure at current state

scalar numeric

Dynamic pressure at current state, specified as a scalar numeric in these units:

Unit	Unit System
Pascals (Pa)	'Metric'
pounds per foot squared (lbf/ft2)	'English (ft/s)' and 'English (kts)'

This property is defined with the equation

DynamicPressure = 0.5 * Environment.Density * Airspeed².

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: double

Methods

Public Methods

getState	Get state value
setState	Set state value to Aero.FixedWing.State object
setupControlStates	Set up control states for Aero.FixedWing.State object

Examples

Create and Use Fixed-Wing Object

Create and set up dynamic behavior and the current state for the fixed-wing 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"

To define the aircraft dynamic behavior, set a coefficient for it.

aircraft = setCoefficient(aircraft, "CD", "Zero", 0.27)

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 aircraft's current state.

state = Aero.FixedWing.State("Mass", 500)

state = 
  State with properties:

                    Alpha: 0
                     Beta: 0
                 AlphaDot: 0
                  BetaDot: 0
                     Mass: 500
                  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
                      Phi: 0
                    Theta: 0
                      Psi: 0
                        P: 0
                        Q: 0
                        R: 0
                   Weight: 4905
              AltitudeAGL: 0
                 Airspeed: 50
              GroundSpeed: 50
               MachNumber: 0.1469
             BodyVelocity: [50 0 0]
           GroundVelocity: [50 0 0]
                       Ur: 50
                       Vr: 0
                       Wr: 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: 1.5312e+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

           0
           0
        4905

M = 3×1

     0
     0
     0

Algorithms

The BodyToStabilityMatrix transformation is defined by this matrix:

BodyToStabilityMatrix = 
[cos(Alpha),  0, sin(Alpha)]
[     0,      1,      0    ]
[-sin(Alpha), 0, cos(Alpha)]

The StabilityToBodyMatrix transformation is the transpose of BodyToStabilityMatrix transformation:

StabilityToBodyMatrix = BodyToStabilityMatrix'

Version History

Introduced in R2021a