
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 F16. 
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 "headsupdisplay". 
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 
BuildF16  Build the F16 Model. 
SVN Revision: 42425
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