AircraftPointMassCLPSim:

Path: ACPro/ACPointMass

% Simulate the controlled trajectory of a point mass aircraft model.
   This simulation includes feedback control. The control law is based on
   feedback linearization, so that the closed loop system approximates a
   linear system with desirable dynamic properties.

   State:     x = [V;gama;psi;x;y;h;Tbar]
   --------------------------------------
     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]
   -------------------------------
     Lbar    normalized excess lift
     phi     bank angle
     Tcbar   normalized excess thrust command

   Command:   cmd = [h;v;psi;x;y]
   -------------------------------
     h       altitude command (m)
     v       velocity command (true airspeed, m/s)
     psi     heading command (rad)
     x       eastward position (m)
     y       northward position (m)
     
--------------------------------------------------------------------------
   Form:
   [x,u,xDot,cmd] = AircraftPointMassCLPSim( x0, cmd, t, data );
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   x0      (7,1)    Initial state vector
   cmd     (3,N)    Command vector (only h,v,psi need to be provided)
   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

   -------
   Outputs
   -------
   x       (7,N)    State vector
   u       (3,N)    Control input vector
   xDot    (7,N)    Time derivative of state vector
   cmd     (5,N)    Command vector (all command variables are output)

--------------------------------------------------------------------------

Children:

ACPro: ACPointMass/AircraftPointMassControl
ACPro: ACPointMass/AircraftPointMassRHS
Math: Integration/RK4

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