fixedWingState
Syntax
Description
returns a fixedwing state
= fixedWingState(aircraft
)state
object created from a fixedwing aircraft,
aircraft
, using a default environment.
returns a fixedwing state
= fixedWingState(aircraft
,environment
)state
object using a specified environment,
environment
.
returns a fixedwing state
= fixedWingState(___,Name=Value
)state
object with an environment defined by
Name=Value
arguments.
Examples
Create FixedWing Aircraft State Object and Default Environment
Create a fixedwing aircraft state object from a fixedwing 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 FixedWing Aircraft State Object from FixedWing Aircraft Object and Mass
Create a fixedwing aircraft state object from a fixedwing 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 FixedWing Aircraft State Object and Custom Environment
Create a fixedwing aircraft state object from a fixedwing 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
aircraft
— Fixedwing aircraft object
scalar
Fixedwing aircraft object, specified as a scalar.
environment
— Fixedwing aircraft environment name
aircraftEnvironment(aircraft, "ISA", 0)
(default)  scalar string
Fixedwing aircraft environment name, specified as a scalar string.
Tip
This argument also exists as the namevalue argument
Environment
. If you specify the
Environment
namevalue argument, its value supersedes the
environment
positional argument.
Data Types: string
NameValue Arguments
Specify optional pairs of arguments as
Name1=Value1,...,NameN=ValueN
, where Name
is
the argument name and Value
is the corresponding value.
Namevalue 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
UnitSystem
— Unit system
'Metric'
(default)  'English (kts)'
 'English (ft/s)'
Unit system, specified as 'Metric'
, 'English
(kts)'
, 'English (ft/s)'
.
AngleSystem
— Angle system
'Radians'
(default)  'Degrees'
Angle system, specified as 'Radians'
or
'Degrees'
.
TemperatureSystem
— Temperature system
'Kelvin'
(default)  'Celsius'
 'Rankine'
 'Fahrenheit'
Temperature system, specified as 'Kelvin'
,
'Celsius'
, 'Rankine'
, or
'Fahrenheit'
.
Mass
— Fixedwing aircraft mass
0
(default)  scalar numeric
Fixedwing aircraft mass, specified as a scalar numeric in these units.
Unit  Unit System 

newtons (N) 

slugs (slug) 

Data Types: double
Inertia
— Inertial matrix of aircraft
3by3
table of numeric values (default)  scalar numeric
Inertial matrix of aircraft, specified as a 3by3 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) 

slug feet squared (slug ft^2) 

Data Types: double
CenterOfGravity
— Location of center of gravity
[0, 0, 0] (default)  threeelement vector
Location of center of gravity on fixedwing aircraft in body frame, specified as a threeelement vector in these units.
Unit  Unit System 

Meters (m) 

Feet (ft) 

Data Types: double
CenterOfPressure
— Location of center of pressure
[0, 0, 0] (default)  threeelement vector
Location of center of pressure on fixedwing aircraft in body frame, specified as a threeelement vector in these units.
Unit  Unit System 

Meters (m) 

Feet (ft) 

Data Types: double
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) 

Feet (ft) 

Data Types: double
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) 

Feet (ft) 

Data Types: double
XN
— North position of fixedwing aircraft
0 (default)  scalar numeric
North position of fixedwing aircraft, specified as a scalar numeric in these units.
Unit  Unit System 

Meters (m) 

Feet (ft) 

Data Types: double
XE
— East position of fixedwing aircraft
0 (default)  scalar numeric
East position of fixedwing aircraft, specified as a scalar numeric in these units.
Unit  Unit System 

Meters (m) 

Feet (ft) 

Data Types: double
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) 

Feet per second (ft/s) 

Knots (kts) 

Data Types: double
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) 

Feet per second (ft/s) 

Knots (kts) 

Data Types: double
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) 

Feet per second (ft/s) 

Knots (kts) 

Data Types: double
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.
Data Types: double
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.
Data Types: double
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.
Data Types: double
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.
Data Types: double
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.
Data Types: double
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.
Data Types: double
AlphaDot
— Angle of attack rate on fixedwing aircraft
0 (default)  scalar numeric
Angle of attack rate on fixedwing aircraft, specified as a scalar numeric in
units of radians per second or degrees per second, depending on the
AngleSystem
property.
Data Types: double
BetaDot
— Angle of sideslip rate on fixedwing aircraft
0 (default)  scalar numeric
Angle of sideslip rate on the fixedwing aircraft, specified as a scalar numeric
in units of radians per second or degrees per second, depending on the
AngleSystem
property.
Data Types: double
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
.
Data Types: double
Environment
— Definition of current environment
scalar
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
namevalue argument,
its value supersedes the environment
positional
argument.
Output Arguments
state
— Aero.FixedWing.State
objects
matrix
Aero.FixedWing.State
objects, returned as a matrix the same size as
environment
.
Version History
Introduced in R2021b
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