RHS2DPointMass:

Path: ACPro/ACPointMass

% Simulate a point mass aircraft model in 2 dimensions.

   This model requires drag and thrust functions to be passed as part
   of the data structure. The thrust function is of the form

   [thrust, sFC] = ThrustFunction( m, d, p )

   where thrust is the scalar thrust. The drag function is of the form

   [lift, drag] = DragFunction( m, d ),

   where d is a data structure and drag is the scalar drag.

--------------------------------------------------------------------------
   Form:
   xDot = RHS2DPointMass( x, t, d )
   [thrust, drag] = RHS2DPointMass( x, t, d )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   t       (1,1)    Time vector for integration
   x       (5,1)    [v;gamma;h;mass;range]
   d       (1,1)    Data structure
                    .tFcn           (1,1) Pointer to thrust function
                    .g              (1,1) Gravitational acceleration
                    .engine         (1,1) Structure to engine data
                    .aero           (1,1) Structure to aero data
   -------
   Outputs
   -------
   if 1 output:
   xDot     (5,1)    d[v;gamma;h;mass;range]/dt

   if 2 outputs
   thrust   (1,1)    Thrust
   drag     (1,1)    Drag

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

Children:

Common: Atmosphere/StdAtm

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