src/FDM/JSBSim/models/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 Lesser 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 Lesser General Public License for more
  19  details.
  20
  21  You should have received a copy of the GNU Lesser 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 Lesser 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 <input_output/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()) return true; // return true if error returned from base class
 111
 112   if (FDMExec->Holding()) return false;
 113
 114   p = Atmosphere->GetPressure();
 115   rhosl = Atmosphere->GetDensitySL();
 116   psl = Atmosphere->GetPressureSL();
 117   sat = Atmosphere->GetTemperature();
 118
 119 // Rotation
 120
 121   double cTht = Propagate->GetCosEuler(eTht);
 122   double sTht = Propagate->GetSinEuler(eTht);
 123   double cPhi = Propagate->GetCosEuler(ePhi);
 124   double sPhi = Propagate->GetSinEuler(ePhi);
 125
 126   vEulerRates(eTht) = vPQR(eQ)*cPhi - vPQR(eR)*sPhi;
 127   if (cTht != 0.0) {
 128     vEulerRates(ePsi) = (vPQR(eQ)*sPhi + vPQR(eR)*cPhi)/cTht;
 129     vEulerRates(ePhi) = vPQR(eP) + vEulerRates(ePsi)*sTht;
 130   }
 131
 132 // 12/16/2005, JSB: For ground handling purposes, at this time, let's ramp
 133 // in the effects of wind from 10 fps to 30 fps when there is weight on the
 134 // landing gear wheels.
 135
 136   if (GroundReactions->GetWOW() && vUVW(eU) < 10) {
 137     vAeroPQR = vPQR;
 138     vAeroUVW = vUVW;
 139   } else if (GroundReactions->GetWOW() && vUVW(eU) < 30) {
 140     double factor = (vUVW(eU) - 10.0)/20.0;
 141     vAeroPQR = vPQR + factor*Atmosphere->GetTurbPQR();
 142     vAeroUVW = vUVW + factor*Propagate->GetTl2b()*Atmosphere->GetWindNED();
 143   } else {
 144     vAeroPQR = vPQR + Atmosphere->GetTurbPQR();
 145     vAeroUVW = vUVW + Propagate->GetTl2b()*Atmosphere->GetWindNED();
 146   }
 147
 148   Vt = vAeroUVW.Magnitude();
 149   if ( Vt > 0.05) {
 150     if (vAeroUVW(eW) != 0.0)
 151       alpha = vAeroUVW(eU)*vAeroUVW(eU) > 0.0 ? atan2(vAeroUVW(eW), vAeroUVW(eU)) : 0.0;
 152     if (vAeroUVW(eV) != 0.0)
 153       beta = vAeroUVW(eU)*vAeroUVW(eU)+vAeroUVW(eW)*vAeroUVW(eW) > 0.0 ? atan2(vAeroUVW(eV),
 154              sqrt(vAeroUVW(eU)*vAeroUVW(eU) + vAeroUVW(eW)*vAeroUVW(eW))) : 0.0;
 155
 156     double mUW = (vAeroUVW(eU)*vAeroUVW(eU) + vAeroUVW(eW)*vAeroUVW(eW));
 157     double signU=1;
 158     if (vAeroUVW(eU) != 0.0)
 159       signU = vAeroUVW(eU)/fabs(vAeroUVW(eU));
 160
 161     if ( (mUW == 0.0) || (Vt == 0.0) ) {
 162       adot = 0.0;
 163       bdot = 0.0;
 164     } else {
 165       adot = (vAeroUVW(eU)*vUVWdot(eW) - vAeroUVW(eW)*vUVWdot(eU))/mUW;
 166       bdot = (signU*mUW*vUVWdot(eV) - vAeroUVW(eV)*(vAeroUVW(eU)*vUVWdot(eU)
 167               + vAeroUVW(eW)*vUVWdot(eW)))/(Vt*Vt*sqrt(mUW));
 168     }
 169   } else {
 170     alpha = beta = adot = bdot = 0;
 171   }
 172
 173   qbar = 0.5*Atmosphere->GetDensity()*Vt*Vt;
 174   qbarUW = 0.5*Atmosphere->GetDensity()*(vAeroUVW(eU)*vAeroUVW(eU) + vAeroUVW(eW)*vAeroUVW(eW));
 175   qbarUV = 0.5*Atmosphere->GetDensity()*(vAeroUVW(eU)*vAeroUVW(eU) + vAeroUVW(eV)*vAeroUVW(eV));
 176   Mach = Vt / Atmosphere->GetSoundSpeed();
 177   MachU = vMachUVW(eU) = vAeroUVW(eU) / Atmosphere->GetSoundSpeed();
 178   vMachUVW(eV) = vAeroUVW(eV) / Atmosphere->GetSoundSpeed();
 179   vMachUVW(eW) = vAeroUVW(eW) / Atmosphere->GetSoundSpeed();
 180
 181 // Position
 182
 183   Vground = sqrt( vVel(eNorth)*vVel(eNorth) + vVel(eEast)*vVel(eEast) );
 184
 185   if (vVel(eNorth) == 0) psigt = 0;
 186   else psigt =  atan2(vVel(eEast), vVel(eNorth));
 187
 188   if (psigt < 0.0) psigt += 2*M_PI;
 189
 190   if (Vground == 0.0) {
 191     if (vVel(eDown) == 0.0) gamma = 0.0;
 192     else if (vVel(eDown) < 0.0) gamma = 90.0*degtorad;
 193     else gamma = -90.0*degtorad;
 194   } else {
 195     gamma = atan2(-vVel(eDown), Vground);
 196   }
 197
 198   tat = sat*(1 + 0.2*Mach*Mach); // Total Temperature, isentropic flow
 199   tatc = RankineToCelsius(tat);
 200
 201   if (MachU < 1) {   // Calculate total pressure assuming isentropic flow
 202     pt = p*pow((1 + 0.2*MachU*MachU),3.5);
 203   } else {
 204     // Use Rayleigh pitot tube formula for normal shock in front of pitot tube
 205     B = 5.76*MachU*MachU/(5.6*MachU*MachU - 0.8);
 206     D = (2.8*MachU*MachU-0.4)*0.4167;
 207     pt = p*pow(B,3.5)*D;
 208   }
 209
 210   A = pow(((pt-p)/psl+1),0.28571);
 211   if (MachU > 0.0) {
 212     vcas = sqrt(7*psl/rhosl*(A-1));
 213     veas = sqrt(2*qbar/rhosl);
 214   } else {
 215     vcas = veas = 0.0;
 216   }
 217
 218   vPilotAccel.InitMatrix();
 219   if ( Vt > 1.0 ) {
 220      vPilotAccel =  Aerodynamics->GetForces()
 221                     +  Propulsion->GetForces()
 222                     +  GroundReactions->GetForces();
 223      vPilotAccel /= MassBalance->GetMass();
 224      vToEyePt = MassBalance->StructuralToBody(Aircraft->GetXYZep());
 225      vPilotAccel += Propagate->GetPQRdot() * vToEyePt;
 226      vPilotAccel += vPQR * (vPQR * vToEyePt);
 227   } else {
 228      vPilotAccel = Propagate->GetTl2b() * FGColumnVector3( 0.0, 0.0, Inertial->gravity() );
 229   }
 230
 231   vPilotAccelN = vPilotAccel/Inertial->gravity();
 232
 233   earthPosAngle += State->Getdt()*Inertial->omega();
 234
 235   // VRP computation
 236   const FGLocation& vLocation = Propagate->GetLocation();
 237   FGColumnVector3 vrpStructural = Aircraft->GetXYZvrp();
 238   FGColumnVector3 vrpBody = MassBalance->StructuralToBody( vrpStructural );
 239   FGColumnVector3 vrpLocal = Propagate->GetTb2l() * vrpBody;
 240   vLocationVRP = vLocation.LocalToLocation( vrpLocal );
 241
 242   // Recompute some derived values now that we know the dependent parameters values ...
 243   hoverbcg = Propagate->GetDistanceAGL() / Aircraft->GetWingSpan();
 244
 245   FGColumnVector3 vMac = Propagate->GetTb2l()*MassBalance->StructuralToBody(Aircraft->GetXYZrp());
 246   hoverbmac = (Propagate->GetDistanceAGL() + vMac(3)) / Aircraft->GetWingSpan();
 247
 248   return false;
 249 }
 250
 251 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 252
 253 double FGAuxiliary::GetHeadWind(void)
 254 {
 255   double psiw,vw;
 256
 257   psiw = Atmosphere->GetWindPsi();
 258   vw = Atmosphere->GetWindNED().Magnitude();
 259
 260   return vw*cos(psiw - Propagate->GetEuler(ePsi));
 261 }
 262
 263 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 264
 265 double FGAuxiliary::GetCrossWind(void)
 266 {
 267   double psiw,vw;
 268
 269   psiw = Atmosphere->GetWindPsi();
 270   vw = Atmosphere->GetWindNED().Magnitude();
 271
 272   return  vw*sin(psiw - Propagate->GetEuler(ePsi));
 273 }
 274
 275 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 276
 277 void FGAuxiliary::bind(void)
 278 {
 279   typedef double (FGAuxiliary::*PMF)(int) const;
 280   typedef double (FGAuxiliary::*PF)(void) const;
 281   PropertyManager->Tie("propulsion/tat-r", this, &FGAuxiliary::GetTotalTemperature);
 282   PropertyManager->Tie("propulsion/tat-c", this, &FGAuxiliary::GetTAT_C);
 283   PropertyManager->Tie("propulsion/pt-lbs_sqft", this, &FGAuxiliary::GetTotalPressure);
 284   PropertyManager->Tie("velocities/vc-fps", this, &FGAuxiliary::GetVcalibratedFPS);
 285   PropertyManager->Tie("velocities/vc-kts", this, &FGAuxiliary::GetVcalibratedKTS);
 286   PropertyManager->Tie("velocities/ve-fps", this, &FGAuxiliary::GetVequivalentFPS);
 287   PropertyManager->Tie("velocities/ve-kts", this, &FGAuxiliary::GetVequivalentKTS);
 288   PropertyManager->Tie("velocities/machU", this, &FGAuxiliary::GetMachU);
 289   PropertyManager->Tie("velocities/p-aero-rad_sec", this, eX, (PMF)&FGAuxiliary::GetAeroPQR);
 290   PropertyManager->Tie("velocities/q-aero-rad_sec", this, eY, (PMF)&FGAuxiliary::GetAeroPQR);
 291   PropertyManager->Tie("velocities/r-aero-rad_sec", this, eZ, (PMF)&FGAuxiliary::GetAeroPQR);
 292   PropertyManager->Tie("velocities/phidot-rad_sec", this, ePhi, (PMF)&FGAuxiliary::GetEulerRates);
 293   PropertyManager->Tie("velocities/thetadot-rad_sec", this, eTht, (PMF)&FGAuxiliary::GetEulerRates);
 294   PropertyManager->Tie("velocities/psidot-rad_sec", this, ePsi, (PMF)&FGAuxiliary::GetEulerRates);
 295   PropertyManager->Tie("velocities/u-aero-fps", this, eU, (PMF)&FGAuxiliary::GetAeroUVW);
 296   PropertyManager->Tie("velocities/v-aero-fps", this, eV, (PMF)&FGAuxiliary::GetAeroUVW);
 297   PropertyManager->Tie("velocities/w-aero-fps", this, eW, (PMF)&FGAuxiliary::GetAeroUVW);
 298   PropertyManager->Tie("velocities/vt-fps", this, &FGAuxiliary::GetVt, &FGAuxiliary::SetVt, true);
 299   PropertyManager->Tie("velocities/mach", this, &FGAuxiliary::GetMach, &FGAuxiliary::SetMach, true);
 300   PropertyManager->Tie("velocities/vg-fps", this, &FGAuxiliary::GetVground);
 301   PropertyManager->Tie("accelerations/a-pilot-x-ft_sec2", this, eX, (PMF)&FGAuxiliary::GetPilotAccel);
 302   PropertyManager->Tie("accelerations/a-pilot-y-ft_sec2", this, eY, (PMF)&FGAuxiliary::GetPilotAccel);
 303   PropertyManager->Tie("accelerations/a-pilot-z-ft_sec2", this, eZ, (PMF)&FGAuxiliary::GetPilotAccel);
 304   PropertyManager->Tie("accelerations/n-pilot-x-norm", this, eX, (PMF)&FGAuxiliary::GetNpilot);
 305   PropertyManager->Tie("accelerations/n-pilot-y-norm", this, eY, (PMF)&FGAuxiliary::GetNpilot);
 306   PropertyManager->Tie("accelerations/n-pilot-z-norm", this, eZ, (PMF)&FGAuxiliary::GetNpilot);
 307   PropertyManager->Tie("position/epa-rad", this, &FGAuxiliary::GetEarthPositionAngle);
 308   /* PropertyManager->Tie("atmosphere/headwind-fps", this, &FGAuxiliary::GetHeadWind, true);
 309   PropertyManager->Tie("atmosphere/crosswind-fps", this, &FGAuxiliary::GetCrossWind, true); */
 310   PropertyManager->Tie("aero/alpha-rad", this, (PF)&FGAuxiliary::Getalpha, &FGAuxiliary::Setalpha, true);
 311   PropertyManager->Tie("aero/beta-rad", this, (PF)&FGAuxiliary::Getbeta, &FGAuxiliary::Setbeta, true);
 312   PropertyManager->Tie("aero/mag-beta-rad", this, (PF)&FGAuxiliary::GetMagBeta);
 313   PropertyManager->Tie("aero/alpha-deg", this, inDegrees, (PMF)&FGAuxiliary::Getalpha);
 314   PropertyManager->Tie("aero/beta-deg", this, inDegrees, (PMF)&FGAuxiliary::Getbeta);
 315   PropertyManager->Tie("aero/mag-beta-deg", this, inDegrees, (PMF)&FGAuxiliary::GetMagBeta);
 316   PropertyManager->Tie("aero/qbar-psf", this, &FGAuxiliary::Getqbar, &FGAuxiliary::Setqbar, true);
 317   PropertyManager->Tie("aero/qbarUW-psf", this, &FGAuxiliary::GetqbarUW, &FGAuxiliary::SetqbarUW, true);
 318   PropertyManager->Tie("aero/qbarUV-psf", this, &FGAuxiliary::GetqbarUV, &FGAuxiliary::SetqbarUV, true);
 319   PropertyManager->Tie("aero/alphadot-rad_sec", this, (PF)&FGAuxiliary::Getadot, &FGAuxiliary::Setadot, true);
 320   PropertyManager->Tie("aero/betadot-rad_sec", this, (PF)&FGAuxiliary::Getbdot, &FGAuxiliary::Setbdot, true);
 321   PropertyManager->Tie("aero/alphadot-deg_sec", this, inDegrees, (PMF)&FGAuxiliary::Getadot);
 322   PropertyManager->Tie("aero/betadot-deg_sec", this, inDegrees, (PMF)&FGAuxiliary::Getbdot);
 323   PropertyManager->Tie("aero/h_b-cg-ft", this, &FGAuxiliary::GetHOverBCG);
 324   PropertyManager->Tie("aero/h_b-mac-ft", this, &FGAuxiliary::GetHOverBMAC);
 325   PropertyManager->Tie("flight-path/gamma-rad", this, &FGAuxiliary::GetGamma, &FGAuxiliary::SetGamma);
 326   PropertyManager->Tie("flight-path/psi-gt-rad", this, &FGAuxiliary::GetGroundTrack);
 327 }
 328
 329 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 330
 331 void FGAuxiliary::unbind(void)
 332 {
 333   PropertyManager->Untie("propulsion/tat-r");
 334   PropertyManager->Untie("propulsion/tat-c");
 335   PropertyManager->Untie("propulsion/pt-lbs_sqft");
 336
 337   PropertyManager->Untie("velocities/vc-fps");
 338   PropertyManager->Untie("velocities/vc-kts");
 339   PropertyManager->Untie("velocities/ve-fps");
 340   PropertyManager->Untie("velocities/ve-kts");
 341   PropertyManager->Untie("velocities/machU");
 342   PropertyManager->Untie("velocities/p-aero-rad_sec");
 343   PropertyManager->Untie("velocities/q-aero-rad_sec");
 344   PropertyManager->Untie("velocities/r-aero-rad_sec");
 345   PropertyManager->Untie("velocities/phidot-rad_sec");
 346   PropertyManager->Untie("velocities/thetadot-rad_sec");
 347   PropertyManager->Untie("velocities/psidot-rad_sec");
 348   PropertyManager->Untie("velocities/u-aero-fps");
 349   PropertyManager->Untie("velocities/v-aero-fps");
 350   PropertyManager->Untie("velocities/w-aero-fps");
 351   PropertyManager->Untie("velocities/vt-fps");
 352   PropertyManager->Untie("velocities/mach");
 353   PropertyManager->Untie("velocities/vg-fps");
 354   PropertyManager->Untie("accelerations/a-pilot-x-ft_sec2");
 355   PropertyManager->Untie("accelerations/a-pilot-y-ft_sec2");
 356   PropertyManager->Untie("accelerations/a-pilot-z-ft_sec2");
 357   PropertyManager->Untie("accelerations/n-pilot-x-norm");
 358   PropertyManager->Untie("accelerations/n-pilot-y-norm");
 359   PropertyManager->Untie("accelerations/n-pilot-z-norm");
 360   PropertyManager->Untie("position/epa-rad");
 361   /* PropertyManager->Untie("atmosphere/headwind-fps");
 362   PropertyManager->Untie("atmosphere/crosswind-fps"); */
 363   PropertyManager->Untie("aero/qbar-psf");
 364   PropertyManager->Untie("aero/qbarUW-psf");
 365   PropertyManager->Untie("aero/qbarUV-psf");
 366   PropertyManager->Untie("aero/alpha-rad");
 367   PropertyManager->Untie("aero/beta-rad");
 368   PropertyManager->Untie("aero/alpha-deg");
 369   PropertyManager->Untie("aero/beta-deg");
 370   PropertyManager->Untie("aero/alphadot-rad_sec");
 371   PropertyManager->Untie("aero/betadot-rad_sec");
 372   PropertyManager->Untie("aero/mag-beta-rad");
 373   PropertyManager->Untie("aero/alphadot-deg_sec");
 374   PropertyManager->Untie("aero/betadot-deg_sec");
 375   PropertyManager->Untie("aero/mag-beta-deg");
 376   PropertyManager->Untie("aero/h_b-cg-ft");
 377   PropertyManager->Untie("aero/h_b-mac-ft");
 378   PropertyManager->Untie("flight-path/gamma-rad");
 379   PropertyManager->Untie("flight-path/psi-gt-rad");
 380 }
 381
 382 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 383 //    The bitmasked value choices are as follows:
 384 //    unset: In this case (the default) JSBSim would only print
 385 //       out the normally expected messages, essentially echoing
 386 //       the config files as they are read. If the environment
 387 //       variable is not set, debug_lvl is set to 1 internally
 388 //    0: This requests JSBSim not to output any messages
 389 //       whatsoever.
 390 //    1: This value explicity requests the normal JSBSim
 391 //       startup messages
 392 //    2: This value asks for a message to be printed out when
 393 //       a class is instantiated
 394 //    4: When this value is set, a message is displayed when a
 395 //       FGModel object executes its Run() method
 396 //    8: When this value is set, various runtime state variables
 397 //       are printed out periodically
 398 //    16: When set various parameters are sanity checked and
 399 //       a message is printed out when they go out of bounds
 400
 401 void FGAuxiliary::Debug(int from)
 402 {
 403   if (debug_lvl <= 0) return;
 404
 405   if (debug_lvl & 1) { // Standard console startup message output
 406     if (from == 0) { // Constructor
 407
 408     }
 409   }
 410   if (debug_lvl & 2 ) { // Instantiation/Destruction notification
 411     if (from == 0) cout << "Instantiated: FGAuxiliary" << endl;
 412     if (from == 1) cout << "Destroyed:    FGAuxiliary" << endl;
 413   }
 414   if (debug_lvl & 4 ) { // Run() method entry print for FGModel-derived objects
 415   }
 416   if (debug_lvl & 8 ) { // Runtime state variables
 417   }
 418   if (debug_lvl & 16) { // Sanity checking
 419     if (Mach > 100 || Mach < 0.00)
 420       cout << "FGPropagate::Mach is out of bounds: " << Mach << endl;
 421     if (qbar > 1e6 || qbar < 0.00)
 422       cout << "FGPropagate::qbar is out of bounds: " << qbar << endl;
 423   }
 424   if (debug_lvl & 64) {
 425     if (from == 0) { // Constructor
 426       cout << IdSrc << endl;
 427       cout << IdHdr << endl;
 428     }
 429   }
 430 }
 431
 432 } // namespace JSBSim