AirshipStabConDerivatives:

--------------------------------------------------------------------------
   Compute the stability and control derivatives for an airship model.

     The subscripts are given after an underscore. For example,
      _V is a "V" subscript. Each subscript indicates the
      variable (state or control) that the partial derivative
      is taken with respect to. 
 
     The dimensional derivatives are named with the force or 
     moment abbreviation, followed by a subscript.
 
     The non-dimensional derivatives are named with "C"
     then the force or moment abbreviation, followed by a
     subscript.
 
     For eample:
       - M_alpha is the dimensional derivative for the pitch
         moment "M" with respect to angle of attack "alpha".
       - Cm_alpha is the corresponding non-dimensional
       derivative.

   Since version 4 (ACT)
--------------------------------------------------------------------------
   Form:
   [dim,nonDim] = AirshipStabConDerivatives( mdl, h, theta, alpha, V )
--------------------------------------------------------------------------

   ------
   Inputs
   ------

   -------
   Outputs
   -------
   dim     (.)   Data structure with fields for dimensional derivatives
                   - Partial derivatives of body frame forces with respect
                     to small changes in various states and controls, then
                     divided by mass.
                   - Partial derivatives of body frame moments with
                     respect to small changes in various states and
                     controls, then divided by the inertia of that axis.
                   
   nonDim  (.)   Data structure with fields for non-dimensional
                 derivatives. Each non-dimensional derivative is equal to
                 the corresponding dimensional derivative, multiplied by a
                 scaling factor. The following scaling factors are used:

                   - FORCE_VELOCITY :      V *    mass / (qBar * S)
                   - FORCE_ANGLE :                mass / (qBar * S)
                   - FORCE_ANGLE-RATE:   2*V *    mass / (qBar * S * c)

                   - MOMENT_VELOCITY :     V * inertia / (qBar * S * c)
                   - MOMENT_ANGLE :            inertia / (qBar * S * c)
                   - MOMENT_ANGLE-RATE : 2*V * inertia / (qBar * S * c * c)
                 
                 where V is the airspeed, qBar is the dynamic pressure, S
                 is the reference area, c is the reference length. The
                 inertia quantity used is for the corresponding axis of 
                 the moment, and is computed in the wind-frame.

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

Children:

AC: ACCoord/AlphBeta
AC: ACCoord/BToW
AC: ACCoord/ECIToNED
AeroUtils: AtmosphericCalculations/AirData
Airships: Control/AirshipState
Airships: Modeling/BuildAirshipModel
Airships: Simulation/AirshipInit
Common: Quaternion/Q2Eul
Common: Quaternion/QMult
Common: Quaternion/QPose
Common: Transform/Altitude
Math: Linear/Mag