WOLFRAM SYSTEM MODELER

AutopilotTurbofan

Autopilot for passenger aircraft with turbofan propulsion

Diagram

Wolfram Language

In[1]:=
SystemModel["Aircraft.ControlSystems.Autopilots.AutopilotTurbofan"]
Out[1]:=

Information

This autopilot model extends the AutopilotBase model and is adjusted to work with aircraft with turbofan engines.

Parameters (25)

nEng

Value: 1

Type: Integer

Description: Number of engines to control

elvControl

Value: true

Type: Boolean

Description: true, if elevator is controlled

throtControl

Value: true

Type: Boolean

Description: true, if throttle is controlled

ailControl

Value: true

Type: Boolean

Description: true, if ailerons are controlled

rdrControl

Value: true

Type: Boolean

Description: true, if rudder is controlled

maxPhi

Value: 0.349065850398866

Type: Angle (rad)

Description: Maximum roll angle

maxTheta

Value: 0.349065850398866

Type: Angle (rad)

Description: Maximum pitch angle

altPIDk

Value: 0.0075

Type: Real

Description: Altitude PID Gain

altPIDTi

Value: 50

Type: Time (s)

Description: Altitude PID Integrator Block

altPIDTd

Value: 5

Type: Time (s)

Description: Altitude PID Derivative Block

thetaPIDk

Value: 0.5

Type: Real

Description: Theta PID Gain

thetaPIDTi

Value: 15

Type: Time (s)

Description: Theta PID Integrator Block

thetaPIDTd

Value: 0.5

Type: Time (s)

Description: Theta PID Derivative Block

vtotPIDk

Value: 2

Type: Real

Description: Velocity PID Gain

vtotPIDTi

Value: 2

Type: Time (s)

Description: Velocity PID Integrator Block

vtotPIDTd

Value: 0.25

Type: Time (s)

Description: Velocity PID Derivative Block

trackPIDk

Value: 2

Type: Real

Description: Track PID Gain

trackPIDTi

Value: 100

Type: Time (s)

Description: Track PID Integrator Block

trackPIDTd

Value: 5

Type: Time (s)

Description: Track PID Derivative Block

phiPIDk

Value: 0.75

Type: Real

Description: Phi PID Gain

phiPIDTi

Value: 20

Type: Time (s)

Description: Phi PID Integrator Block

phiPIDTd

Value: 2

Type: Time (s)

Description: Phi PID Derivative Block

betaPIDk

Value: 1

Type: Real

Description: Beta PID Gain

betaPIDTi

Value: 2

Type: Time (s)

Description: Beta PID Integrator Block

betaPIDTd

Value: 0.75

Type: Time (s)

Description: Beta PID Derivative Block

Connectors (8)

deltaElvCmd

Type: RealOutput

Description: Elevator deflection command

deltaThrotCmd

Type: RealOutput[nEng]

Description: Throttle position command

altCmd

Type: RealInput

Description: Altitude command

vTotCmd

Type: RealInput

Description: Total velocity command

deltaRdrCmd

Type: RealOutput

Description: Rudder deflection command

deltaAilCmd

Type: RealOutput

Description: Aileron deflection command

trackCmd

Type: RealInput

Description: Track command

flightDataIn

Type: FlightDataIn

Description: Flight data input

Components (8)

altPID

Type: LimPID

Description: PID controller from altitude command to pitch angle (theta) command

vtotPID

Type: LimPID

Description: PID controller from total velocity command to throttle position command

trackPID

Type: LimPID

Description: PID controller from track angle command to roll angle (phi) command

betaPID

Type: LimPID

Description: PID controller from sideslip angle command to rudder deflection command

phiPID

Type: LimPID

Description: PID controller from roll angle (phi) command to aileron deflection command

thetaPID

Type: LimPID

Description: PID controller from pitch angle (theta) command to elevator deflection command

constBeta

Type: Constant

Description: Constant 0 signal to Beta PID setpoint input

deltaElvSignChange

Type: Gain

Description: Sign change for elevator deflection command

Used in Examples (3)

WeightEstimation

Aircraft.Examples

Comparison of the performance of Boeing 737-800 with known and estimated mass properties

LinearizedStateSpace

Aircraft.Examples

Example for demonstrating the linearized state space modeling environment

EngineFailure

Aircraft.Examples

Example of flying an aircraft with custom propulsion and engine failure