Aero.FixedWing.Thrust Class
Namespace: Aero
Description
Aero.FixedWing.Thrust
creates an Aero.FixedWing
thrust
vector that describes the thrust of an aircraft.
Creation
Description
fixedWingThrust = Aero.FixedWing.Thrust
creates a single
Aero.FixedWing.Thrust
object with default property values.
fixedWingThrust = Aero.FixedWing.Thrust(
creates an N-by-N matrix of
N
)Aero.FixedWing.Thrust
objects with default property values.
fixedWingThrust = Aero.FixedWing.Thrust(
or
M
,N
,P
,...)Aero.FixedWing.Thrust([
creates an M-by-N-by-P-by-...
array of M
N
P
...])Aero.FixedWing.Thrust
objects with default property values.
fixedWingThrust = Aero.FixedWing.Thrust(size(
creates an A
))Aero.FixedWing.Thrust
object that is the same size as
A
and all Aero.FixedWing.Thrust
objects.
fixedWing.Thrust = Aero.FixedWing.Thrust(__,property,propertyValue)
creates an array of Aero.FixedWing.Thrust
objects with
property
, propertyValue
pairs
applied to each of the Aero.FixedWing.Thrust
array objects. For a list of
properties, see Properties.
Input Arguments
N
— Number of fixed-wing thrust objects
scalar
Number of fixed-wing thrust objects, specified as a scalar.
M
— Number of fixed-wing thrust objects
scalar
Number of fixed-wing thrust objects, specified as a scalar.
P
— Number of fixed-wing thrust objects
scalar
Number of fixed-wing thrust objects, specified as a scalar.
A
— Size of fixed-wing thrust object
scalar
Size of fixed-wing thrust object, specified as a scalar.
Properties
Public Properties
Coefficients
— Aero.FixedWing.Coefficients
object
scalar
Aero.FixedWing.Coefficients
object, specified as a scalar, that
defines the thrust vector.
Attributes:
GetAccess | public |
SetAccess | public |
MaximumValue
— Maximum thrust value
1
(default) | scalar numeric
Maximum thrust value, specified as a scalar numeric.
Dependencies
If Symmetry
is set to Asymmetric
, then
this value applies to both control variables.
Attributes:
GetAccess | public |
SetAccess | public |
Data Types: double
MinimumValue
— Minimum thrust value
0
(default) | scalar numeric
Minimum thrust value, specified as a scalar numeric.
Dependencies
If Symmetry
is set to Asymmetric
, then
this value applies to both control variables.
Attributes:
GetAccess | public |
SetAccess | public |
Data Types: double
Controllable
— Controllable thrust value
on
(default) | off
Controllable thrust value, specified as on
or
off
. To control the thrust value, set this property to
on
. Otherwise, set this property to
off
.
Attributes:
GetAccess | public |
SetAccess | public |
Data Types: logical
Symmetry
— Symmetry of thrust control
Symmetric
(default) | Asymmetric
Symmetry of the thrust control, specified as Symmetric
or
Asymmetric
.
The Asymmetric
option creates two control variables, denoted by
the name on the properties and appended by _1
and
_2
. These control variables can be independently controlled, but
also produce an effective control variable specified by the name on the properties.
You cannot set this effective control variable. This equation defines the control
variable:
.name
=
(name
_1-name
_2)/2
You cannot set this effective control variable.
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 |
Data Types: double
Protected Properties
ControlVariables
— Control variable names
vector
Control variable names, specified as a vector. This property depends on
Properties.Name
, Controllable
, and
Symmetry
.
Attributes:
GetAccess | Restricts access |
SetAccess | protected |
Data Types: char
| string
Methods
Public Methods
getCoefficient | Get coefficient for fixed-wing thrust object |
getControlStates | Get control states for Aero.FixedWing.Thrust object |
setCoefficient | Set coefficient values for Aero.FixedWing.Thrust
object |
update | Update Aero.FixedWing.Thrust object |
Examples
Define Aircraft Thrust Actuators and Compute Forces and Moments for Aircraft
This example shows how to compute aircraft forces and moments using a FixedWing
thrust.
Create a FixedWing
thrust object, propeller
.
propeller = Aero.FixedWing.Thrust(... Controllable="on", ... Properties=Aero.Aircraft.Properties("Name","Propeller"), ... Coefficients=Aero.FixedWing.Coefficient(... "StateVariables",["Propeller", "U"], ... "ReferenceFrame","Body" ... ) ... )
propeller = Thrust with properties: Coefficients: [1x1 Aero.FixedWing.Coefficient] MaximumValue: 1 MinimumValue: 0 Controllable: on Symmetry: "Symmetric" ControlVariables: "Propeller" Properties: [1x1 Aero.Aircraft.Properties]
Assign the propeller
thrust to the FixedWing aircraft object, aircraft
.Set the coefficient reference frame, Stability
.
aircraft = Aero.FixedWing(... ReferenceArea=30, ... ReferenceSpan=12, ... Thrusts=propeller, ... Properties=Aero.Aircraft.Properties("Name","Aircraft"))
aircraft = FixedWing with properties: ReferenceArea: 30 ReferenceSpan: 12 ReferenceLength: 0 Coefficients: [1x1 Aero.FixedWing.Coefficient] DegreesOfFreedom: "6DOF" Surfaces: [1x0 Aero.FixedWing.Surface] Thrusts: [1x1 Aero.FixedWing.Thrust] AspectRatio: 4.8000 Properties: [1x1 Aero.Aircraft.Properties] UnitSystem: "Metric" TemperatureSystem: "Kelvin" AngleSystem: "Radians"
aircraft.Coefficients.ReferenceFrame = "Stability";
Set the coefficients for aircraft
.
BodyCoefficients = { 'CD', 'Zero', 0.02; 'CD', 'Alpha', 0.1; 'CL', 'Alpha', 4.5; }; PropellerCoefficients = { 'CX', 'Propeller', 8 'CX', 'U', -0.1; }; aircraft = setCoefficient(... aircraft, ... BodyCoefficients(:, 1), ... BodyCoefficients(:, 2), ... BodyCoefficients(:, 3)); aircraft = setCoefficient(... aircraft, ... PropellerCoefficients(:, 1), ... PropellerCoefficients(:, 2), ... PropellerCoefficients(:, 3), ... "Component", "Propeller");
Get the cruise state for aircraft
.
state = Aero.FixedWing.State(... Mass=200, ... U=50, ... Alpha=0.01); state = setupControlStates(state, aircraft); state = setState(state, "Propeller", 0.63)
state = State with properties: Alpha: 0.0100 Beta: 0 AlphaDot: 0 BetaDot: 0 Mass: 200 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: 1962 AltitudeAGL: 0 Airspeed: 50.0025 GroundSpeed: 50 MachNumber: 0.1469 BodyVelocity: [50 0 0.5000] GroundVelocity: [50 0 0] Ur: 50 Vr: 0 Wr: 0.5000 FlightPathAngle: 0 CourseAngle: 0 InertialToBodyMatrix: [3x3 double] BodyToInertialMatrix: [3x3 double] BodyToWindMatrix: [3x3 double] WindToBodyMatrix: [3x3 double] BodyToStabilityMatrix: [3x3 double] StabilityToBodyMatrix: [3x3 double] DynamicPressure: 1.5314e+03 Environment: [1x1 Aero.Aircraft.Environment] ControlStates: [1x1 Aero.Aircraft.ControlState] OutOfRangeAction: "Limit" DiagnosticAction: "Warning" Properties: [1x1 Aero.Aircraft.Properties] UnitSystem: "Metric" TemperatureSystem: "Kelvin" AngleSystem: "Radians"
Compute the resulting forces and moments for aircraft
.
[F, M] = forcesAndMoments(aircraft, state)
F = 3×1
893.6216
0
-114.9385
M = 3×1
0
0
0
Limitations
You cannot subclass Aero.FixedWing.Thrust
.
Version History
Introduced in R2021a
See Also
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