Path: ACPro/ACPointMass
% Compute a linear model for a point mass aircraft at a flight condition.
At each time step k, a linearized model of the open-loop aircraft
dynamics is generated using APMLinMod. This continuous model is then
discretized at a sampling time equal to the current time step, t(k+1)-t(k).
The process is repeated to generate a matrix-form expression that
describes the
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
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Form:
[A,B] = APMLinMod( x, u, tau, g );
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Inputs
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x (7,1) State trajectory
u (3,1) Control input trajectory
tau (1) Time constant for engine response
g (1) Acceleration due to gravity (default 9.81)
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Outputs
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A (7,7) State transition matrix (continuous time)
B (7,3) Control effect matrix (continuous time)
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