AircraftPointMassRHSWithSideslip:

Path: ACPro/ACPointMass

% Point mass dynamic model with sideslip as an input.
   The function uses AtmDens2 for atmospheric density.
   The built-in aero model is

   cC = 2*pi*bE*d.cCScale;
   f  = GroundEffect( h, d.l );
   cL = 2*pi*f*(aE - d.aE0);
   cD = d.cD0 + d.aL*cL^2 + d.aC*cC^2;
 
   cCScale scales the effective lift in the y direction to the wing
   area. If you use your own aero function you, don't need these fields in
   d.

   If the point mass is within hTakeoff of the ground downward forces
   are balanced by the ground.

   Your supplied aerodynamics force function is of the form

   [cD,cC,cL] = feval( d.aerofun, alphaEff, betaEff, h, d )
   
   h is altitude. This allows you to model ground effect.
   Since version 4 (ACT).
--------------------------------------------------------------------------
   Form:
   stateDot = AircraftPointMassRHSWithSideslip( state, t, u, d )
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   ------
   Inputs
   ------
   state          (7,1)  [v;gamma;psi;h;thrust;x;y]
   t              (1,1)  Time
   u              (4,1)  Control [angle of attack;side slip;bank angle;
                                  thrust]
   d               (.)   Data structure
                         .mass    (1,1) Mass
                         .aeroFun (1,:) Name of aerodynamics function
                         .g       (1,1) Gravitational acceleration
                         .S       (1,1) Reference area
                         .hTakeoff(1,1) Altitude for ground force
                                        constraint
                         .l       (1,1) Wing span (for ground effect)
                         .cCScale (1,1) Sideforce scale
                         .aE0     (1,1) Zero lift angle
                         .cD0     (1,1) Zero lift drage
                         .aL      (1,1) Induced drag due to the lift
                                        coefficient
                         .aC      (1,1) Induced drag due to the sideforce
                                        coefficient

   -------
   Outputs
   -------
   stateDot      (7,1)  Derivative

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   Reference: T. Kinoshita1 and F. Imado, "The Application of an UAV
              Flight Simulator -The Development of a New Point Mass Model
              for an Aircraft-", SICE-ICASE International Joint Conference
              Oct. 18-21, 2006,Bexco, Busan, Korea.
--------------------------------------------------------------------------

Children:

ACPro: ACProAerodynamics/AeroCoefficientPointMass
AerospaceUtils: AtmosphericCalculations/AtmDens2
Math: Linear/Mag

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