src/FDM/UIUCModel/uiuc_get_flapper.cpp

   1 #include "uiuc_get_flapper.h"
   2
   3 void uiuc_get_flapper(double dt)
   4 {
   5   double flapper_alpha;
   6   double flapper_V;
   7   //double cycle_incr;
   8   flapStruct flapper_struct;
   9   //FlapStruct flapper_struct;
  10
  11   flapper_alpha = Std_Alpha*180/LS_PI;
  12   flapper_V = V_rel_wind;
  13
  14   flapper_freq = 0.8 + 0.45*Throttle_pct;
  15
  16   //if (Simtime == 0)
  17   //  flapper_cycle_pct = flapper_cycle_pct_init;
  18   //else
  19   //  {
  20   //    cycle_incr = flapper_freq*dt - static_cast<int>(flapper_freq*dt);
  21   //    if (cycle_incr < 1)
  22   //      flapper_cycle_pct += cycle_incr;
  23   //    else  //need because problem when flapper_freq*dt is same as int
  24   //        flapper_cycle_pct += cycle_incr - 1;
  25   //  }
  26   //if (flapper_cycle_pct >= 1)
  27   //  flapper_cycle_pct -= 1;
  28
  29   //if (flapper_cycle_pct >= 0 && flapper_cycle_pct < 0.25)
  30   //  flapper_phi = LS_PI/2 * (sin(2*LS_PI*flapper_cycle_pct+3*LS_PI/2)+1);
  31   //if (flapper_cycle_pct >= 0.25 && flapper_cycle_pct < 0.5)
  32   //  flapper_phi = LS_PI/2 * sin(2*LS_PI*(flapper_cycle_pct-0.25))+LS_PI/2;
  33   //if (flapper_cycle_pct >= 0.5 && flapper_cycle_pct < 0.75)
  34   //  flapper_phi = LS_PI/2 * (sin(2*LS_PI*(flapper_cycle_pct-0.5)+3*LS_PI/2)+1)+LS_PI;
  35   //if (flapper_cycle_pct >= 0.75 && flapper_cycle_pct < 1)
  36   //  flapper_phi = LS_PI/2 * sin(2*LS_PI*(flapper_cycle_pct-0.75))+3*LS_PI/2;
  37
  38   if (Simtime == 0)
  39     flapper_phi = flapper_phi_init;
  40   else
  41     flapper_phi += 2* LS_PI * flapper_freq * dt;
  42
  43   if (flapper_phi >= 2*LS_PI)
  44     flapper_phi -= 2*LS_PI;
  45
  46   flapper_struct=flapper_data->flapper(flapper_alpha,flapper_V,flapper_freq,flapper_phi);
  47   flapper_Lift=flapper_struct.getLift();
  48   flapper_Thrust=flapper_struct.getThrust();
  49   flapper_Inertia=flapper_struct.getInertia();
  50   flapper_Moment=flapper_struct.getMoment();
  51
  52   F_Z_aero_flapper = -1*flapper_Lift*cos(Std_Alpha) - flapper_Thrust*sin(Std_Alpha);
  53   F_Z_aero_flapper -= flapper_Inertia;
  54   F_X_aero_flapper = -1*flapper_Lift*sin(Std_Alpha) + flapper_Thrust*cos(Std_Alpha);
  55
  56 }