AC Module

Directory List

ACThrust	Thrust model for a gas turbine engine
F16Actuator	Model for the F16 actuators. Each has a lag.

AircraftControl	Implements an aircraft control system.
AircraftControlCAS	Implements a pitch rate control augmentation system.

AlphBeta	Compute angle of attack and sideslip.
BToS	Convert from the body axes to stability axes.
BToW	Convert from the body frame to wind axes.
ECIToNED	Convert from the ECI frame to the NED frame.
EulNED	Euler angles given ECI information.
EulRate	Euler rates.
JacobVB	Convert from the body axes to stability axes.
QECI	Compute ECI to body quaternion from ECI position and Euler angles.
RNEH	Convert from the ECI frame to the NEH frame.
SToW	Convert from stability axes to wind axes.
UFromAlphaBeta	Compute wind vector from angle of attack and sideslip.
VBDToVBT	Compute the total velocity derivative from the body velocity
VTToVB	Compute body velocity from alpha, beta and vT.

ACTConstants.mat - Aircraft constants database.

AtmData.mat - Atmospheric data.

F16TrimData.mat - Trim state and control settings for an F-16.

gCobra.mat - Cobra CAD database.

gF16.mat - F16 acstate.

DefaultACData	Provide a default aircraft data structure. The F16 model is used.
DefaultACState	Provide a default aircraft state.
F16Act	Models the F16 actuators as first order lags with time constants

AC	Dynamics model for an aircraft. Updates the data structure x.
ACBuild	Build the aircraft model.
ACInit	Initialize the aircraft model.
ACPlot	Plots the aircraft data. opt is 'info', 'init', 'store', 'plot'
ACTrim	Aircraft trimming algorithm. Uses the function FTrim.
FTrim	Cost function for the trimming algorithm
StateSpacePlot	Plots statespace data. opt is 'init', 'store', 'plot'

ThrustPropeller	Compute propeller thrust.
ThrustTurbofan	Compute turbofan thrust as a function of static thrust and velocity.

DrawAC	Draws an aircraft in the NED frame. The aircraft state vector can
DrawTerrain	Draw terrain.
HUD	Implements a "heads-up-display".
HUDCntrl	Perform actions specified by the HUD. Define a data structure
Trans3DMF	Transform a 3D data structure. r is optional.

ADC	Implements the "Air Data Computer" model.
AspectRatio	Compute aircraft aspect ratio.
MachFromPressureRatio	Computes the Mach number from pressure ratio.
PressureRatioFromMach	Computes impact to static pressure ratio from Mach number and gamma.
RayleighPitotTube	Stagnation pressure ratio in supersonic flow.

ACAero	Aerodynamic model.
ACEngEq	Find the equilibrium state of the engine.
ACEngine	Aircraft engine model.
ACModes	Compute the aircraft modes for straight and level flight.
ACSensor	Generic aircraft sensor. Outputs are
AeroD	Compute the state space system based on aerodynamic derivatives.
DC8	DC 8 stability derivatives model.
F16	The F16 aircraft properties database.
L1011	L1011 aircraft model.

abs	Computes the absolute value of acstate.
acstate	Create an object of class acstate
get	Get an element of the class acstate
length	Length of a state vector
minus	Subtract two objects of class acstate
mrdivide	Divides an object of acstate by a scalar.
mtimes	Multiplies an object of type acstate times a scalar
plus	Add two objects of class acstate
subsasgn	Assign a(i)
subsref	Finds a(i)
zeros	Create a zero vector the size of a.

CASDesign	Design a simple aircraft control system consisting of a pitch rate tracking system.
F16CAS	Test a pitch rate control augmentation system.

ACControl	Demonstrate aircraft control using the AircraftControl function.
CActuator	Try different control responses with a first order lag modeling the actuators.
CResponse	Try different control responses with ideal actuators.
CTSim	Simulate an F16 performing a coordinated turn. The F16 will go unstable due to an unstable longitudinal mode.
Fly	Fly an F16.
RigidBodyDemo	Simulate the linear and angular states of a rigid body using "AC.m"
Trim	Trim an F16

Build the F16 Model.

SVN Revision: 42425

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