ACSensor:

Path: AC/Aircraft

% Generic aircraft sensor. Outputs are
     z acceleration
     roll rate       (rad/sec)
     angle of attack (deg)

   Since version 2 (ACT)
--------------------------------------------------------------------------
   Form:
   g = ACSensor( x, d, opt )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   x           (:)   acstate data structure
   d           (:)   Aircraft data structure
   opt               'rhs'  outputs state derivatives
                     'meas' outputs measurements

   -------
   Outputs
   -------
   g           (:)   Sensor output
                     .aN        (1,1) Normal acceleration
                     .q         (1,1) Pitch rate
                     .alpha     (1,1) Angle of attack
                     .p         (1,1) Roll rates
                     .r         (1,1) Yaw rates
                     .altitude  (1,1) Altitude
                     .machNo    (1,1) Mach number
                     .qBar      (1,1) Dynamic pressure

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

Children:

AC: ACCoord/AlphBeta
AerospaceUtils: AtmosphericCalculations/AirData
Common: Transform/Altitude
Math: Linear/Mag

Back to the AC Module page