src/FDM/JSBSim/FGAuxiliary.cpp

   1 /*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
   2
   3  Module:       FGAuxiliary.cpp
   4  Author:       Tony Peden, Jon Berndt
   5  Date started: 01/26/99
   6  Purpose:      Calculates additional parameters needed by the visual system, etc.
   7  Called by:    FGSimExec
   8
   9  ------------- Copyright (C) 1999  Jon S. Berndt (jsb@hal-pc.org) -------------
  10
  11  This program is free software; you can redistribute it and/or modify it under
  12  the terms of the GNU General Public License as published by the Free Software
  13  Foundation; either version 2 of the License, or (at your option) any later
  14  version.
  15
  16  This program is distributed in the hope that it will be useful, but WITHOUT
  17  ANY WARRANTY; without even the implied warranty of MERCHANTABILITY or FITNESS
  18  FOR A PARTICULAR PURPOSE.  See the GNU General Public License for more
  19  details.
  20
  21  You should have received a copy of the GNU General Public License along with
  22  this program; if not, write to the Free Software Foundation, Inc., 59 Temple
  23  Place - Suite 330, Boston, MA  02111-1307, USA.
  24
  25  Further information about the GNU General Public License can also be found on
  26  the world wide web at http://www.gnu.org.
  27
  28 FUNCTIONAL DESCRIPTION
  29 --------------------------------------------------------------------------------
  30 This class calculates various auxiliary parameters.
  31
  32 REFERENCES
  33   Anderson, John D. "Introduction to Flight", 3rd Edition, McGraw-Hill, 1989
  34                     pgs. 112-126
  35 HISTORY
  36 --------------------------------------------------------------------------------
  37 01/26/99   JSB   Created
  38
  39 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
  40 INCLUDES
  41 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
  42
  43 #include "FGAuxiliary.h"
  44 #include "FGAerodynamics.h"
  45 #include "FGPropagate.h"
  46 #include "FGAtmosphere.h"
  47 #include "FGState.h"
  48 #include "FGFDMExec.h"
  49 #include "FGAircraft.h"
  50 #include "FGInertial.h"
  51 #include "FGPropertyManager.h"
  52
  53 namespace JSBSim {
  54
  55 static const char *IdSrc = "$Id$";
  56 static const char *IdHdr = ID_AUXILIARY;
  57
  58 /*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
  59 CLASS IMPLEMENTATION
  60 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
  61
  62
  63 FGAuxiliary::FGAuxiliary(FGFDMExec* fdmex) : FGModel(fdmex)
  64 {
  65   Name = "FGAuxiliary";
  66   vcas = veas = pt = tat = 0;
  67   psl = rhosl = 1;
  68   earthPosAngle = 0.0;
  69   qbar = 0;
  70   qbarUW = 0.0;
  71   qbarUV = 0.0;
  72   Mach = 0.0;
  73   alpha = beta = 0.0;
  74   adot = bdot = 0.0;
  75   gamma = Vt = Vground = 0.0;
  76   psigt = 0.0;
  77   day_of_year = 1;
  78   seconds_in_day = 0.0;
  79   hoverbmac = hoverbcg = 0.0;
  80
  81   vPilotAccel.InitMatrix();
  82   vPilotAccelN.InitMatrix();
  83   vToEyePt.InitMatrix();
  84   vAeroPQR.InitMatrix();
  85   vEulerRates.InitMatrix();
  86
  87   bind();
  88
  89   Debug(0);
  90 }
  91
  92 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
  93
  94 FGAuxiliary::~FGAuxiliary()
  95 {
  96   unbind();
  97   Debug(1);
  98 }
  99
 100 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 101
 102 bool FGAuxiliary::Run()
 103 {
 104   double A,B,D, hdot_Vt;
 105   const FGColumnVector3& vPQR = Propagate->GetPQR();
 106   const FGColumnVector3& vUVW = Propagate->GetUVW();
 107   const FGColumnVector3& vUVWdot = Propagate->GetUVWdot();
 108   const FGColumnVector3& vVel = Propagate->GetVel();
 109
 110   if (!FGModel::Run())
 111   {
 112     p = Atmosphere->GetPressure();
 113     rhosl = Atmosphere->GetDensitySL();
 114     psl = Atmosphere->GetPressureSL();
 115     sat = Atmosphere->GetTemperature();
 116
 117 // Rotation
 118
 119     double cTht = Propagate->GetCosEuler(eTht);
 120     double cPhi = Propagate->GetCosEuler(ePhi);
 121     double sPhi = Propagate->GetSinEuler(ePhi);
 122
 123     vEulerRates(eTht) = vPQR(eQ)*cPhi - vPQR(eR)*sPhi;
 124     if (cTht != 0.0) {
 125       vEulerRates(ePsi) = (vPQR(eQ)*sPhi + vPQR(eR)*cPhi)/cTht;
 126       vEulerRates(ePhi) = vPQR(eP) + vEulerRates(ePsi)*sPhi;
 127     }
 128
 129     vAeroPQR = vPQR + Atmosphere->GetTurbPQR();
 130
 131 // Translation
 132
 133     vAeroUVW = vUVW + Propagate->GetTl2b()*Atmosphere->GetWindNED();
 134
 135     Vt = vAeroUVW.Magnitude();
 136     if ( Vt > 0.05) {
 137       if (vAeroUVW(eW) != 0.0)
 138         alpha = vAeroUVW(eU)*vAeroUVW(eU) > 0.0 ? atan2(vAeroUVW(eW), vAeroUVW(eU)) : 0.0;
 139       if (vAeroUVW(eV) != 0.0)
 140         beta = vAeroUVW(eU)*vAeroUVW(eU)+vAeroUVW(eW)*vAeroUVW(eW) > 0.0 ? atan2(vAeroUVW(eV),
 141                sqrt(vAeroUVW(eU)*vAeroUVW(eU) + vAeroUVW(eW)*vAeroUVW(eW))) : 0.0;
 142
 143       double mUW = (vAeroUVW(eU)*vAeroUVW(eU) + vAeroUVW(eW)*vAeroUVW(eW));
 144       double signU=1;
 145       if (vAeroUVW(eU) != 0.0)
 146         signU = vAeroUVW(eU)/fabs(vAeroUVW(eU));
 147
 148       if ( (mUW == 0.0) || (Vt == 0.0) ) {
 149         adot = 0.0;
 150         bdot = 0.0;
 151       } else {
 152         adot = (vAeroUVW(eU)*vUVWdot(eW) - vAeroUVW(eW)*vUVWdot(eU))/mUW;
 153         bdot = (signU*mUW*vUVWdot(eV) - vAeroUVW(eV)*(vAeroUVW(eU)*vUVWdot(eU)
 154                 + vAeroUVW(eW)*vUVWdot(eW)))/(Vt*Vt*sqrt(mUW));
 155       }
 156     } else {
 157       alpha = beta = adot = bdot = 0;
 158     }
 159
 160     qbar = 0.5*Atmosphere->GetDensity()*Vt*Vt;
 161     qbarUW = 0.5*Atmosphere->GetDensity()*(vAeroUVW(eU)*vAeroUVW(eU) + vAeroUVW(eW)*vAeroUVW(eW));
 162     qbarUV = 0.5*Atmosphere->GetDensity()*(vAeroUVW(eU)*vAeroUVW(eU) + vAeroUVW(eV)*vAeroUVW(eV));
 163     Mach = Vt / Atmosphere->GetSoundSpeed();
 164     MachU = vMachUVW(eU) = vAeroUVW(eU) / Atmosphere->GetSoundSpeed();
 165     vMachUVW(eV) = vAeroUVW(eV) / Atmosphere->GetSoundSpeed();
 166     vMachUVW(eW) = vAeroUVW(eW) / Atmosphere->GetSoundSpeed();
 167
 168 // Position
 169
 170     Vground = sqrt( vVel(eNorth)*vVel(eNorth) + vVel(eEast)*vVel(eEast) );
 171
 172     if (vVel(eNorth) == 0) psigt = 0;
 173     else psigt =  atan2(vVel(eEast), vVel(eNorth));
 174
 175     if (psigt < 0.0) psigt += 2*M_PI;
 176
 177     if (Vt != 0) {
 178       hdot_Vt = -vVel(eDown)/Vt;
 179       if (fabs(hdot_Vt) <= 1) gamma = asin(hdot_Vt);
 180     } else {
 181       gamma = 0.0;
 182     }
 183
 184     tat = sat*(1 + 0.2*Mach*Mach); // Total Temperature, isentropic flow
 185     tatc = RankineToCelsius(tat);
 186
 187     if (MachU < 1) {   // Calculate total pressure assuming isentropic flow
 188       pt = p*pow((1 + 0.2*MachU*MachU),3.5);
 189     } else {
 190       // Use Rayleigh pitot tube formula for normal shock in front of pitot tube
 191       B = 5.76*MachU*MachU/(5.6*MachU*MachU - 0.8);
 192       D = (2.8*MachU*MachU-0.4)*0.4167;
 193       pt = p*pow(B,3.5)*D;
 194     }
 195
 196     A = pow(((pt-p)/psl+1),0.28571);
 197     if (MachU > 0.0) {
 198       vcas = sqrt(7*psl/rhosl*(A-1));
 199       veas = sqrt(2*qbar/rhosl);
 200     } else {
 201       vcas = veas = 0.0;
 202     }
 203
 204     vPilotAccel.InitMatrix();
 205     if ( Vt > 1.0 ) {
 206        vPilotAccel =  Aerodynamics->GetForces()
 207                       +  Propulsion->GetForces()
 208                       +  GroundReactions->GetForces();
 209        vPilotAccel /= MassBalance->GetMass();
 210        vToEyePt = MassBalance->StructuralToBody(Aircraft->GetXYZep());
 211        vPilotAccel += Propagate->GetPQRdot() * vToEyePt;
 212        vPilotAccel += vPQR * (vPQR * vToEyePt);
 213     } else {
 214        vPilotAccel = Propagate->GetTl2b() * FGColumnVector3( 0.0, 0.0, Inertial->gravity() );
 215     }
 216
 217     vPilotAccelN = vPilotAccel/Inertial->gravity();
 218
 219     earthPosAngle += State->Getdt()*Inertial->omega();
 220
 221     // VRP computation
 222     const FGLocation& vLocation = Propagate->GetLocation();
 223     FGColumnVector3 vrpStructural = Aircraft->GetXYZvrp();
 224     FGColumnVector3 vrpBody = MassBalance->StructuralToBody( vrpStructural );
 225     FGColumnVector3 vrpLocal = Propagate->GetTb2l() * vrpBody;
 226     vLocationVRP = vLocation.LocalToLocation( vrpLocal );
 227
 228     // Recompute some derived values now that we know the dependent parameters values ...
 229     hoverbcg = Propagate->GetDistanceAGL() / Aircraft->GetWingSpan();
 230
 231     FGColumnVector3 vMac = Propagate->GetTb2l()*MassBalance->StructuralToBody(Aircraft->GetXYZrp());
 232     hoverbmac = (Propagate->GetDistanceAGL() + vMac(3)) / Aircraft->GetWingSpan();
 233
 234     return false;
 235   } else {
 236     return true;
 237   }
 238 }
 239
 240 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 241
 242 double FGAuxiliary::GetHeadWind(void)
 243 {
 244   double psiw,vw;
 245
 246   psiw = Atmosphere->GetWindPsi();
 247   vw = Atmosphere->GetWindNED().Magnitude();
 248
 249   return vw*cos(psiw - Propagate->GetEuler(ePsi));
 250 }
 251
 252 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 253
 254 double FGAuxiliary::GetCrossWind(void)
 255 {
 256   double psiw,vw;
 257
 258   psiw = Atmosphere->GetWindPsi();
 259   vw = Atmosphere->GetWindNED().Magnitude();
 260
 261   return  vw*sin(psiw - Propagate->GetEuler(ePsi));
 262 }
 263
 264 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 265
 266 void FGAuxiliary::bind(void)
 267 {
 268   typedef double (FGAuxiliary::*PMF)(int) const;
 269   typedef double (FGAuxiliary::*PF)(void) const;
 270   PropertyManager->Tie("velocities/vc-fps", this, &FGAuxiliary::GetVcalibratedFPS);
 271   PropertyManager->Tie("velocities/vc-kts", this, &FGAuxiliary::GetVcalibratedKTS);
 272   PropertyManager->Tie("velocities/ve-fps", this, &FGAuxiliary::GetVequivalentFPS);
 273   PropertyManager->Tie("velocities/ve-kts", this, &FGAuxiliary::GetVequivalentKTS);
 274   PropertyManager->Tie("velocities/machU", this, &FGAuxiliary::GetMachU);
 275   PropertyManager->Tie("velocities/tat-r", this, &FGAuxiliary::GetTotalTemperature);
 276   PropertyManager->Tie("velocities/tat-c", this, &FGAuxiliary::GetTAT_C);
 277   PropertyManager->Tie("velocities/pt-lbs_sqft", this, &FGAuxiliary::GetTotalPressure);
 278   PropertyManager->Tie("velocities/p-aero-rad_sec", this, eX, (PMF)&FGAuxiliary::GetAeroPQR);
 279   PropertyManager->Tie("velocities/q-aero-rad_sec", this, eY, (PMF)&FGAuxiliary::GetAeroPQR);
 280   PropertyManager->Tie("velocities/r-aero-rad_sec", this, eZ, (PMF)&FGAuxiliary::GetAeroPQR);
 281   PropertyManager->Tie("velocities/phidot-rad_sec", this, ePhi, (PMF)&FGAuxiliary::GetEulerRates);
 282   PropertyManager->Tie("velocities/thetadot-rad_sec", this, eTht, (PMF)&FGAuxiliary::GetEulerRates);
 283   PropertyManager->Tie("velocities/psidot-rad_sec", this, ePsi, (PMF)&FGAuxiliary::GetEulerRates);
 284   PropertyManager->Tie("velocities/u-aero-fps", this, eU, (PMF)&FGAuxiliary::GetAeroUVW);
 285   PropertyManager->Tie("velocities/v-aero-fps", this, eV, (PMF)&FGAuxiliary::GetAeroUVW);
 286   PropertyManager->Tie("velocities/w-aero-fps", this, eW, (PMF)&FGAuxiliary::GetAeroUVW);
 287   PropertyManager->Tie("velocities/vt-fps", this, &FGAuxiliary::GetVt, &FGAuxiliary::SetVt, true);
 288   PropertyManager->Tie("velocities/mach-norm", this, &FGAuxiliary::GetMach, &FGAuxiliary::SetMach, true);
 289   PropertyManager->Tie("velocities/vg-fps", this, &FGAuxiliary::GetVground);
 290   PropertyManager->Tie("accelerations/a-pilot-x-ft_sec2", this, eX, (PMF)&FGAuxiliary::GetPilotAccel);
 291   PropertyManager->Tie("accelerations/a-pilot-y-ft_sec2", this, eY, (PMF)&FGAuxiliary::GetPilotAccel);
 292   PropertyManager->Tie("accelerations/a-pilot-z-ft_sec2", this, eZ, (PMF)&FGAuxiliary::GetPilotAccel);
 293   PropertyManager->Tie("accelerations/n-pilot-x-norm", this, eX, (PMF)&FGAuxiliary::GetNpilot);
 294   PropertyManager->Tie("accelerations/n-pilot-y-norm", this, eY, (PMF)&FGAuxiliary::GetNpilot);
 295   PropertyManager->Tie("accelerations/n-pilot-z-norm", this, eZ, (PMF)&FGAuxiliary::GetNpilot);
 296   PropertyManager->Tie("position/epa-rad", this, &FGAuxiliary::GetEarthPositionAngle);
 297   /* PropertyManager->Tie("atmosphere/headwind-fps", this, &FGAuxiliary::GetHeadWind, true);
 298   PropertyManager->Tie("atmosphere/crosswind-fps", this, &FGAuxiliary::GetCrossWind, true); */
 299   PropertyManager->Tie("aero/alpha-rad", this, (PF)&FGAuxiliary::Getalpha, &FGAuxiliary::Setalpha, true);
 300   PropertyManager->Tie("aero/beta-rad", this, (PF)&FGAuxiliary::Getbeta, &FGAuxiliary::Setbeta, true);
 301   PropertyManager->Tie("aero/mag-beta-rad", this, (PF)&FGAuxiliary::GetMagBeta);
 302   PropertyManager->Tie("aero/alpha-deg", this, inDegrees, (PMF)&FGAuxiliary::Getalpha);
 303   PropertyManager->Tie("aero/beta-deg", this, inDegrees, (PMF)&FGAuxiliary::Getbeta);
 304   PropertyManager->Tie("aero/mag-beta-deg", this, inDegrees, (PMF)&FGAuxiliary::GetMagBeta);
 305   PropertyManager->Tie("aero/qbar-psf", this, &FGAuxiliary::Getqbar, &FGAuxiliary::Setqbar, true);
 306   PropertyManager->Tie("aero/qbarUW-psf", this, &FGAuxiliary::GetqbarUW, &FGAuxiliary::SetqbarUW, true);
 307   PropertyManager->Tie("aero/qbarUV-psf", this, &FGAuxiliary::GetqbarUV, &FGAuxiliary::SetqbarUV, true);
 308   PropertyManager->Tie("aero/alphadot-rad_sec", this, (PF)&FGAuxiliary::Getadot, &FGAuxiliary::Setadot, true);
 309   PropertyManager->Tie("aero/betadot-rad_sec", this, (PF)&FGAuxiliary::Getbdot, &FGAuxiliary::Setbdot, true);
 310   PropertyManager->Tie("aero/alphadot-deg_sec", this, inDegrees, (PMF)&FGAuxiliary::Getadot);
 311   PropertyManager->Tie("aero/betadot-deg_sec", this, inDegrees, (PMF)&FGAuxiliary::Getbdot);
 312   PropertyManager->Tie("aero/h_b-cg-ft", this, &FGAuxiliary::GetHOverBCG);
 313   PropertyManager->Tie("aero/h_b-mac-ft", this, &FGAuxiliary::GetHOverBMAC);
 314   PropertyManager->Tie("flight-path/gamma-rad", this, &FGAuxiliary::GetGamma, &FGAuxiliary::SetGamma);
 315   PropertyManager->Tie("flight-path/psi-gt-rad", this, &FGAuxiliary::GetGroundTrack);
 316 }
 317
 318 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 319
 320 void FGAuxiliary::unbind(void)
 321 {
 322   PropertyManager->Untie("velocities/vc-fps");
 323   PropertyManager->Untie("velocities/vc-kts");
 324   PropertyManager->Untie("velocities/ve-fps");
 325   PropertyManager->Untie("velocities/ve-kts");
 326   PropertyManager->Untie("velocities/machU");
 327   PropertyManager->Untie("velocities/tat-r");
 328   PropertyManager->Untie("velocities/tat-c");
 329   PropertyManager->Untie("velocities/p-aero-rad_sec");
 330   PropertyManager->Untie("velocities/q-aero-rad_sec");
 331   PropertyManager->Untie("velocities/r-aero-rad_sec");
 332   PropertyManager->Untie("velocities/pt-lbs_sqft");
 333   PropertyManager->Untie("velocities/phidot-rad_sec");
 334   PropertyManager->Untie("velocities/thetadot-rad_sec");
 335   PropertyManager->Untie("velocities/psidot-rad_sec");
 336   PropertyManager->Untie("velocities/u-aero-fps");
 337   PropertyManager->Untie("velocities/v-aero-fps");
 338   PropertyManager->Untie("velocities/w-aero-fps");
 339   PropertyManager->Untie("velocities/vt-fps");
 340   PropertyManager->Untie("velocities/mach-norm");
 341   PropertyManager->Untie("velocities/vg-fps");
 342   PropertyManager->Untie("accelerations/a-pilot-x-ft_sec2");
 343   PropertyManager->Untie("accelerations/a-pilot-y-ft_sec2");
 344   PropertyManager->Untie("accelerations/a-pilot-z-ft_sec2");
 345   PropertyManager->Untie("accelerations/n-pilot-x-norm");
 346   PropertyManager->Untie("accelerations/n-pilot-y-norm");
 347   PropertyManager->Untie("accelerations/n-pilot-z-norm");
 348   PropertyManager->Untie("position/epa-rad");
 349   /* PropertyManager->Untie("atmosphere/headwind-fps");
 350   PropertyManager->Untie("atmosphere/crosswind-fps"); */
 351   PropertyManager->Untie("aero/qbar-psf");
 352   PropertyManager->Untie("aero/qbarUW-psf");
 353   PropertyManager->Untie("aero/qbarUV-psf");
 354   PropertyManager->Untie("aero/alpha-rad");
 355   PropertyManager->Untie("aero/beta-rad");
 356   PropertyManager->Untie("aero/alpha-deg");
 357   PropertyManager->Untie("aero/beta-deg");
 358   PropertyManager->Untie("aero/alphadot-rad_sec");
 359   PropertyManager->Untie("aero/betadot-rad_sec");
 360   PropertyManager->Untie("aero/mag-beta-rad");
 361   PropertyManager->Untie("aero/alphadot-deg_sec");
 362   PropertyManager->Untie("aero/betadot-deg_sec");
 363   PropertyManager->Untie("aero/mag-beta-deg");
 364   PropertyManager->Untie("aero/h_b-cg-ft");
 365   PropertyManager->Untie("aero/h_b-mac-ft");
 366   PropertyManager->Untie("flight-path/gamma-rad");
 367   PropertyManager->Untie("flight-path/psi-gt-rad");
 368 }
 369
 370 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 371 //    The bitmasked value choices are as follows:
 372 //    unset: In this case (the default) JSBSim would only print
 373 //       out the normally expected messages, essentially echoing
 374 //       the config files as they are read. If the environment
 375 //       variable is not set, debug_lvl is set to 1 internally
 376 //    0: This requests JSBSim not to output any messages
 377 //       whatsoever.
 378 //    1: This value explicity requests the normal JSBSim
 379 //       startup messages
 380 //    2: This value asks for a message to be printed out when
 381 //       a class is instantiated
 382 //    4: When this value is set, a message is displayed when a
 383 //       FGModel object executes its Run() method
 384 //    8: When this value is set, various runtime state variables
 385 //       are printed out periodically
 386 //    16: When set various parameters are sanity checked and
 387 //       a message is printed out when they go out of bounds
 388
 389 void FGAuxiliary::Debug(int from)
 390 {
 391   if (debug_lvl <= 0) return;
 392
 393   if (debug_lvl & 1) { // Standard console startup message output
 394     if (from == 0) { // Constructor
 395
 396     }
 397   }
 398   if (debug_lvl & 2 ) { // Instantiation/Destruction notification
 399     if (from == 0) cout << "Instantiated: FGAuxiliary" << endl;
 400     if (from == 1) cout << "Destroyed:    FGAuxiliary" << endl;
 401   }
 402   if (debug_lvl & 4 ) { // Run() method entry print for FGModel-derived objects
 403   }
 404   if (debug_lvl & 8 ) { // Runtime state variables
 405   }
 406   if (debug_lvl & 16) { // Sanity checking
 407     if (Mach > 100 || Mach < 0.00)
 408       cout << "FGPropagate::Mach is out of bounds: " << Mach << endl;
 409     if (qbar > 1e6 || qbar < 0.00)
 410       cout << "FGPropagate::qbar is out of bounds: " << qbar << endl;
 411   }
 412   if (debug_lvl & 64) {
 413     if (from == 0) { // Constructor
 414       cout << IdSrc << endl;
 415       cout << IdHdr << endl;
 416     }
 417   }
 418 }
 419
 420 } // namespace JSBSim