Path: ACPro/ACPointMass
% Compute the control inputs for a point mass aircraft model.
State: x = [V;gama;psi;x;y;h;Tbar]
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V true airspeed
gama air relative flight path angle
psi air relative flight heading angle
x East position
y North position
h altitude
Tbar normalized excess thrust
Control: u = [Lbar;phi;Tcbar]
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Lbar normalized excess lift
phi bank angle
Tcbar normalized excess thrust command
Command: cmd = [h;v;psi;x;y]
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h altitude command (m)
v velocity command (true airspeed, m/s)
psi heading command (rad)
x eastward position (m)
y northward position (m)
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Form:
u = AircraftPointMassControl( x, xDot, cmd, cmdDot, Tcbar, data );
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Inputs
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x (7,1) State vector
xDot (7,1) Time derivative of state vector
cmd (5,1) Command vector
cmdDot (5,1) Time derivative of command vector
Tcbar (1) Current value of normalzed excess thrust command
data Data structure with fields:
a Body-frame disturbance accel. (forward,x-track,normal)
W Wind speeds (East,North,up)
g Gravitatioanl acceleration
tau Engine thrust response time
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Outputs
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u (3,1) Control input vector
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