Aero.FixedWing.State Class

Namespace: Aero

Define condition of Aero.FixedWing aircraft at time instant

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 body axes, specified as a three-element vector in body axes with positive X-axis forward, Y-axis right, and Z-axis down. The object considers only the distance between center of pressure and center of gravity, not the absolute positions. The vector is in one of 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 body frame axes, specified as a three-element vector in body axes with positive X-axis forward, Y-axis right, and Z-axis down. The vector is in one of 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

Airspeed — Current airspeed

50 (default) | scalar numeric

Current airspeed, 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

Alpha — Angle of attack

0 (default) | scalar numeric

Angle of attack, specified as a scalar numeric in the units defined in AngleSystem.

Attributes:

GetAccess	public
SetAccess	public

Data Types: string | char

Beta — Angle of sideslip

0 (default) | scalar numeric

Angle of sideslip, specified as a scalar numeric in the units specified in AngleSystem.

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

GroundSpeed — Current ground speed of fixed-wing aircraft

nonnegative scalar

Current ground speed of fixed-wing aircraft, specified as a nonnegative scalar 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 = sqrt(Ug2,Vg2,Wg2).

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 — Velocity of fixed-wing aircraft

three-element vector

Velocity of fixed-wing aircraft relative to freestream in body axes, specified as a three-element vector.

BodyVelocity depends on the values of U, V, and W public properties, with the equation

BodyVelocity = [U V W].

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 = BodyVelocity - (InertialToBodyMatrix * Environment.WindVelocity).

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: double

U — X component of body velocity

scalar numeric

X component of body velocity, specified as scalar numeric. U depends on Airspeed, Alpha, and Beta, defined with the equation

U = Airspeed * cos(Alpha) * cos(Beta).

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: double

V — Y component of body velocity

scalar numeric

Y component of body velocity, specified as scalar numeric. Y depends on Airspeed and Beta, defined with the equation

V = Airspeed * sin(Beta).

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: double

W — Z component of body velocity

scalar numeric

Z component of body velocity, specified as scalar numeric. Z depends on Airspeed, Alpha, and Beta, defined with the equation

Z = Airspeed * sin(Alpha) * cos(Beta).

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: double

Ug — X component of ground velocity

scalar numeric

X component of ground velocity, specified as scalar numeric. Ug depends on GroundVelocity.

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: double

Vg — Y component of ground velocity

scalar numeric

Y component of ground velocity, specified as scalar numeric. Ug depends on GroundVelocity.

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: double

Wg — Z component of ground velocity

scalar numeric

Z component of ground velocity, specified as scalar numeric. Wg depends on GroundVelocity.

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 depends on Wg and Ug. FlightPathAngle is defined with the equation:

FlightPathAngle = atan2(Wg,Ug).

.

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 Vg and Ug with the equation

CourseAngle = atan2(Vg,Ug).

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. For a definition of BodyToWindMatrix, see Algorithms.

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. For a definition of WindToBodyMatrix, see Algorithms.

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
setBodyVelocity	Calculate state from U, V, and W values

Examples

Create and Use Fixed-Wing Object

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

Set Fixed-Wing Coefficients and Compute Forces and Moments

Set aircraft coefficients for an Aero.FixedWing object and use these coefficients to compute aircraft forces and moments.

Create a fixed-wing object.

aircraft = Aero.FixedWing(...
  "ReferenceArea", 16,...
  "ReferenceSpan", 11,...
  "ReferenceLength", 1.5);

Set aircraft coefficients.

coeffs = {
  'CD', 'Zero', 0.027;
  'CL', 'Zero', 0.307;
  'Cm', 'Zero', 0.04;
  'CD', 'Alpha', 0.121;
  'CL', 'Alpha', 4.41;
  'Cm', 'Alpha', -0.613;
};
aircraft = setCoefficient(aircraft, coeffs(:,1), coeffs(:,2), coeffs(:,3))

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 aircraft state.

state = Aero.FixedWing.State(...
    "Mass", 1400,...
    "Airspeed", 67,...
    "AltitudeMSL",2000,...
    "Alpha",0)

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"

Compute the forces and moments on the aircraft.

[F1, M1] = forcesAndMoments(aircraft, state)

F1 = 3×1
103 ×

   -1.1878
         0
    0.2284

M1 = 3×1
103 ×

         0
    2.6395
         0

Increase the angle of attack and recompute the forces and moments.

state.Alpha = deg2rad(2);
[F2, M2] = forcesAndMoments(aircraft, state)

F2 = 3×1
103 ×

   -0.6651
         0
   -6.5793

M2 = 3×1
103 ×

         0
    1.2275
         0

Set Fixed-Wing Control States and Compute Forces and Moments

Set up control states for an Aero.FixingWing object. The control states store data about positions of controllable surfaces and thrusts.

Create a fixed-wing object.

aircraft = astC182();

Create an Aero.FixedWing.State object.

state = Aero.FixedWing.State(1, ...
    "UnitSystem","English (ft/s)",...
    "AngleSystem","Radians", ...
    "TemperatureSystem","Fahrenheit", ...
    "Mass",82.2981, ...
    "Airspeed", 220.1, ...
    "Beta", -0.013, ...
    "AltitudeMSL",5000);
state.Environment = aircraftEnvironment(aircraft,"ISA",state.AltitudeMSL);
state.Inertia.Variables = [
    948, 0,    0   ;
    0  , 1346, 0   ;
    0  , 0   , 1967;
    ];
state.CenterOfGravity = [0.264, 0 , 0] .* 4.9;
state.CenterOfPressure = [0.35, 0, 0] .* 4.9;

Use the setupControlStates method to define control states in state and set control positions for the elevator and propeller.

state = setupControlStates(state, aircraft);
state = setState(state, ["Elevator", "Propeller"],[deg2rad(3.57), 0.809])

state = 
  State with properties:

                     Mass: 82.2981
                  Inertia: [3×3 table]
          CenterOfGravity: [1.2936 0 0]
         CenterOfPressure: [1.7150 0 0]
              AltitudeMSL: 5000
             GroundHeight: 0
                       XN: 0
                       XE: 0
                       XD: -5000
                        U: 220.0814
                        V: -2.8612
                        W: 0
                 Airspeed: 220.1000
                      Phi: 0
                    Theta: 0
                      Psi: 0
                        P: 0
                        Q: 0
                        R: 0
                    Alpha: 0
                     Beta: -0.0130
                 AlphaDot: 0
                  BetaDot: 0
                   Weight: 2.6488e+03
              AltitudeAGL: 5000
              GroundSpeed: 220.1000
               MachNumber: 0.2006
             BodyVelocity: [220.0814 -2.8612 0]
           GroundVelocity: [220.0814 -2.8612 0]
                       Ug: 220.0814
                       Vg: -2.8612
                       Wg: 0
          FlightPathAngle: 0
              CourseAngle: -0.0130
     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: 49.6090
              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"

Compute the aircraft forces and moments.

[F1, M1] = forcesAndMoments(aircraft, state)

F1 = 3×1

    9.6367
   44.1007
 -232.5206

M1 = 3×1

  372.8702
  -50.9126
 -218.5500

Deflect the elevator up to get a positive pitching moment, and then recompute forces and moments.

state = setState(state, "Elevator", deg2rad(4.5));
[F2, M2] = forcesAndMoments(aircraft, state)

F2 = 3×1

    9.6367
   44.1007
 -292.7681

M2 = 3×1

  372.8702
 -795.8233
 -218.5500

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'

The BodyToWindMatrix transformation is defined by this matrix:

[ cos(alpha)cos(beta)   sin(beta)   sin(alpha)cos(beta) ]
[-cos(alpha)sin(beta)   cos(beta)  -sin(alpha)sin(beta) ]
[-sin(alpha)                0       cos(alpha)          ]

The WindToBodyMatrix transformation is the transpose of BodyToWindMatrix transformation:

WindToBodyMatrix = BodyToWindMatrix'

Version History

Introduced in R2021a