Path: ACPro/ACPointMass
% Simulate the trajectory x(t) of a point mass aircraft model given u(t)
This is an open loop simulation. No feedback is applied, only the
specified control input u(t) is applied.
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:
[x,xDot] = AircraftPointMassSim( x0, u, t, data );
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Inputs
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x0 (7,1) Initial state vector
u (3,N) Control input vector
t (1,N) Time vector for integration
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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x (7,N) State vector
xDot (7,N) Time derivative of state vector
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ACPro: ACPointMass/AircraftPointMassRHS Math: Integration/RK4
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