Aero.FixedWing.Coefficient Class

Namespace: Aero

Create Aero.FixedWing aircraft coefficient set

Since R2021a

Description

Aero.FixedWing.Coefficient creates an Aero.FixedWing coefficient set that describes the behavior and body of an aircraft.

Class Attributes

Sealed

true

For information on class attributes, see Class Attributes.

Creation

Description

fixedWingCoefficient = Aero.FixedWing.Coefficient creates a single Aero.FixedWing.Coefficient object with default property values.

fixedWingCoefficient = Aero.FixedWing.Coefficient(N) creates an N-by-N matrix of Aero.FixedWing.Coefficient objects with default property values.

fixedWingCoefficient = Aero.FixedWing.Coefficient(M,N,P,...) or Aero.FixedWing.Coefficient([M N P ...]) creates an M-by-N-by-P-by-... array of Aero.FixedWing.Coefficient objects with default property values.

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

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

Input Arguments

N — Number of fixed-wing coefficient objects

scalar

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

M — Number of fixed-wing coefficient objects

scalar

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

P — Number of fixed-wing coefficient objects

scalar

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

A — Size of fixed-wing coefficient object

scalar

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

Properties

Public Properties

Table — Coefficient values

6-by-N table

Coefficient values, specified in a 6-by-N table. Each row in the table must be a member of and in the same order as the StateOutput property.

Setting the Table property also sets the contents of the Values property and StateVariables to the Table property variables. To have a Simulink.LookupTable object and a constant value in the same column, use the setCoefficient or set the desired content of the Values property. Setting the Table property does not set the ReferenceFrame.

Note

Tables must have a single data type per column. If there are both constant values and Simulink.LookupTable objects in a given column, the Table property automatically converts the constants to Simulink.LookupTable objects.

Attributes:

GetAccess	public
SetAccess	public

Data Types: double

Values — Coefficient values

6-by-N cell array

Coefficient values, specified as a 6-by-N cell array. Each entry in the cell array must be a single coefficient value corresponding to the StateOutput (row) and StateVariable (column) properties. Each coefficient value must be a scalar numeric value, Aero.Aircraft.CompositeCoefficient, or a Simulink.LookupTable object. If a value is a Simulink.LookupTable object, the FieldName of each breakpoint must be a valid property of the Aero.FixedWing.State object.

Unlike the Table property, Values do need to be a single data type per column.

Attributes:

GetAccess	public
SetAccess	public

Data Types: double

StateVariables — State variable names

'Zero' (default) | 1-by-N vector

State variable names, specified as a 1-by-N vector of strings. Each entry in this property corresponds to a column in the Values property. Each entry in StateVariables must be a valid property in the Aero.FixedWing.State object. Adding a state variable adds a column of zeros to the end of the Values cell array.

Attributes:

GetAccess	public
SetAccess	public

Data Types: char | string

ReferenceFrame — Reference frame for coefficients

Wind (default) | Body | Stability

Reference frame for coefficients, specified as Wind, Body, or Stability with these outputs:

Reference Frame	Coefficient Output
Wind	Forces: drag (CD) Y (CY) lift (CL)
	Moments: L (Cl) M (Cm) N (Cn)
Body	Forces: X (CX) Y (CY) Z (CZ)
	Moments: L (Cl) M (Cm) N (Cn)
Stability	Forces: drag (CD) Y (CY) lift (Cn)
	Moments: L (Cl) M (Cm) N (Cn)

Example of Wind table:

Coefficient	State
CD	state
CY	state
CL	state
Cl	state
Cm	state
Cn	state

Example of Body table:

Coefficient	State
CX	state
CY	state
CZ	state
Cl	state
Cm	state
Cn	state

Example of Stability table:

Coefficient	State
CD	state
CY	state
CL	state
Cl	state
Cm	state
Cn	state

Attributes:

GetAccess	public
SetAccess	public

Data Types: char | string

MultiplyStateVariables — Option to multiply coefficients by state variables

on (default) | off

Option to multiply coefficients by state variables when calculating forces and moments. To multiply coefficients by state variables, set this property to 'on'. Otherwise, set this property to 'off'.

Attributes:

GetAccess	public
SetAccess	public

Data Types: char | string

NonDimensional — Option to specify coefficients are nondimensional

on (default) | off

Option to specify that nondimensional coefficients. To specify nondimensional coefficients, set this property to 'on'. Otherwise, set this property to 'off'.

Attributes:

GetAccess	public
SetAccess	public

Data Types: char | string

Properties — Aero.Aircraft.Properties object

scalar

Aero.Aircraft.Properties object, specified as a scalar.

Attributes:

GetAccess	public
SetAccess	public

Protected Properties

StateOutput — Current state output

6-by-1 vector

Current state output, returned as one of these 6-by-1 vectors:

Wind	Body	Stability
CD	CX	CD
CY	CY	CY
CL	CZ	CL
Cl	Cl	Cl
Cm	Cm	Cm
Cn	Cn	Cn

This property depends on ReferenceFrame.

Attributes:

GetAccess	Restricts access
SetAccess	protected

Data Types: char | string

Methods

Public Methods

getCoefficient	Get coefficient values from fixed-wing coefficient object
setCoefficient	Set coefficient values for fixed-wing coefficient object
update	Update Aero.FixedWing.Coefficient 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

Limitations

• This class requires a Simulink^® license if the coefficient table contains Simulink.LookupTable objects.

• You cannot subclass Aero.FixedWing.Coefficient.

Version History

Introduced in R2021a