src/FDM/JSBSim/models/FGAtmosphere.cpp

   1 /*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
   2
   3  Module:       FGAtmosphere.cpp
   4  Author:       Jon Berndt
   5                Implementation of 1959 Standard Atmosphere added by Tony Peden
   6  Date started: 11/24/98
   7  Purpose:      Models the atmosphere
   8  Called by:    FGSimExec
   9
  10  ------------- Copyright (C) 1999  Jon S. Berndt (jsb@hal-pc.org) -------------
  11
  12  This program is free software; you can redistribute it and/or modify it under
  13  the terms of the GNU Lesser General Public License as published by the Free Software
  14  Foundation; either version 2 of the License, or (at your option) any later
  15  version.
  16
  17  This program is distributed in the hope that it will be useful, but WITHOUT
  18  ANY WARRANTY; without even the implied warranty of MERCHANTABILITY or FITNESS
  19  FOR A PARTICULAR PURPOSE.  See the GNU Lesser General Public License for more
  20  details.
  21
  22  You should have received a copy of the GNU Lesser General Public License along with
  23  this program; if not, write to the Free Software Foundation, Inc., 59 Temple
  24  Place - Suite 330, Boston, MA  02111-1307, USA.
  25
  26  Further information about the GNU Lesser General Public License can also be found on
  27  the world wide web at http://www.gnu.org.
  28
  29 FUNCTIONAL DESCRIPTION
  30 --------------------------------------------------------------------------------
  31 Models the atmosphere. The equation used below was determined by a third order
  32 curve fit using Excel. The data is from the ICAO atmosphere model.
  33
  34 HISTORY
  35 --------------------------------------------------------------------------------
  36 11/24/98   JSB   Created
  37 07/23/99   TP    Added implementation of 1959 Standard Atmosphere
  38                  Moved calculation of Mach number to FGPropagate
  39                  Later updated to '76 model
  40 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
  41 COMMENTS, REFERENCES,  and NOTES
  42 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
  43 [1]   Anderson, John D. "Introduction to Flight, Third Edition", McGraw-Hill,
  44       1989, ISBN 0-07-001641-0
  45
  46 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
  47 INCLUDES
  48 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
  49
  50 #include "FGAtmosphere.h"
  51 #include <FGState.h>
  52 #include <FGFDMExec.h>
  53 #include "FGAircraft.h"
  54 #include "FGPropagate.h"
  55 #include "FGInertial.h"
  56 #include <input_output/FGPropertyManager.h>
  57
  58 namespace JSBSim {
  59
  60 static const char *IdSrc = "$Id$";
  61 static const char *IdHdr = ID_ATMOSPHERE;
  62
  63 /*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
  64 CLASS IMPLEMENTATION
  65 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
  66
  67
  68 FGAtmosphere::FGAtmosphere(FGFDMExec* fdmex) : FGModel(fdmex)
  69 {
  70   Name = "FGAtmosphere";
  71   lastIndex = 0;
  72   h = 0.0;
  73   psiw = 0.0;
  74   htab[0]=0;
  75   htab[1]=36089.239;
  76   htab[2]=65616.798;
  77   htab[3]=104986.878;
  78   htab[4]=154199.475;
  79   htab[5]=170603.675;
  80   htab[6]=200131.234;
  81   htab[7]=259186.352; //ft.
  82
  83   MagnitudedAccelDt = MagnitudeAccel = Magnitude = 0.0;
  84 //   turbType = ttNone;
  85   turbType = ttStandard;
  86 //   turbType = ttBerndt;
  87   TurbGain = 0.0;
  88   TurbRate = 1.0;
  89
  90   T_dev_sl = T_dev = delta_T = 0.0;
  91   StandardTempOnly = false;
  92
  93   bind();
  94   Debug(0);
  95 }
  96
  97 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
  98
  99 FGAtmosphere::~FGAtmosphere()
 100 {
 101   unbind();
 102   Debug(1);
 103 }
 104
 105 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 106
 107 bool FGAtmosphere::InitModel(void)
 108 {
 109   FGModel::InitModel();
 110
 111   UseInternal();  // this is the default
 112
 113   Calculate(h);
 114   StdSLtemperature = SLtemperature = 518.67;
 115   StdSLpressure    = SLpressure = 2116.22;
 116   StdSLdensity     = SLdensity = 0.00237767;
 117   StdSLsoundspeed  = SLsoundspeed = sqrt(SHRatio*Reng*StdSLtemperature);
 118   rSLtemperature = 1.0/StdSLtemperature;
 119   rSLpressure    = 1.0/StdSLpressure;
 120   rSLdensity     = 1.0/StdSLdensity;
 121   rSLsoundspeed  = 1.0/StdSLsoundspeed;
 122
 123   return true;
 124 }
 125
 126 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 127
 128 bool FGAtmosphere::Run(void)
 129 {
 130   if (FGModel::Run()) return true;
 131   if (FDMExec->Holding()) return false;
 132
 133   T_dev = 0.0;
 134   h = Propagate->Geth();
 135
 136   if (!useExternal) {
 137     Calculate(h);
 138     CalculateDerived();
 139   } else {
 140     CalculateDerived();
 141   }
 142
 143   Debug(2);
 144   return false;
 145 }
 146
 147 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 148 //
 149 // See reference 1
 150
 151 void FGAtmosphere::Calculate(double altitude)
 152 {
 153   double slope, reftemp, refpress;
 154   int i = 0;
 155
 156   i = lastIndex;
 157   if (altitude < htab[lastIndex]) {
 158     if (altitude <= 0) {
 159       i = 0;
 160       altitude=0;
 161     } else {
 162        i = lastIndex-1;
 163        while (htab[i] > altitude) i--;
 164     }
 165   } else if (altitude > htab[lastIndex+1]) {
 166     if (altitude >= htab[7]) {
 167       i = 7;
 168       altitude = htab[7];
 169     } else {
 170       i = lastIndex+1;
 171       while (htab[i+1] < altitude) i++;
 172     }
 173   }
 174
 175   switch(i) {
 176   case 1:     // 36089 ft.
 177     slope     = 0;
 178     reftemp   = 389.97;
 179     refpress  = 472.452;
 180     //refdens   = 0.000706032;
 181     break;
 182   case 2:     // 65616 ft.
 183     slope     = 0.00054864;
 184     reftemp   = 389.97;
 185     refpress  = 114.636;
 186     //refdens   = 0.000171306;
 187     break;
 188   case 3:     // 104986 ft.
 189     slope     = 0.00153619;
 190     reftemp   = 411.57;
 191     refpress  = 8.36364;
 192     //refdens   = 1.18422e-05;
 193     break;
 194   case 4:     // 154199 ft.
 195     slope     = 0;
 196     reftemp   = 487.17;
 197     refpress  = 0.334882;
 198     //refdens   = 4.00585e-7;
 199     break;
 200   case 5:     // 170603 ft.
 201     slope     = -0.00109728;
 202     reftemp   = 487.17;
 203     refpress  = 0.683084;
 204     //refdens   = 8.17102e-7;
 205     break;
 206   case 6:     // 200131 ft.
 207     slope     = -0.00219456;
 208     reftemp   = 454.17;
 209     refpress  = 0.00684986;
 210     //refdens   = 8.77702e-9;
 211     break;
 212   case 7:     // 259186 ft.
 213     slope     = 0;
 214     reftemp   = 325.17;
 215     refpress  = 0.000122276;
 216     //refdens   = 2.19541e-10;
 217     break;
 218   case 0:
 219   default:     // sea level
 220     slope     = -0.00356616; // R/ft.
 221     reftemp   = 518.67;    // R
 222     refpress  = 2116.22;    // psf
 223     //refdens   = 0.00237767;  // slugs/cubic ft.
 224     break;
 225
 226   }
 227
 228   // If delta_T is set, then that is our temperature deviation at any altitude.
 229   // If not, then we'll estimate a deviation based on the sea level deviation (if set).
 230
 231   if(!StandardTempOnly) {
 232     T_dev = 0.0;
 233     if (delta_T != 0.0) {
 234       T_dev = delta_T;
 235     } else {
 236       if ((altitude < 36089.239) && (T_dev_sl != 0.0)) {
 237         T_dev = T_dev_sl * ( 1.0 - (altitude/36089.239));
 238       }
 239     }
 240     reftemp+=T_dev;
 241   }
 242
 243   if (slope == 0) {
 244     intTemperature = reftemp;
 245     intPressure = refpress*exp(-Inertial->SLgravity()/(reftemp*Reng)*(altitude-htab[i]));
 246     intDensity = intPressure/(Reng*intTemperature);
 247   } else {
 248     intTemperature = reftemp+slope*(altitude-htab[i]);
 249     intPressure = refpress*pow(intTemperature/reftemp,-Inertial->SLgravity()/(slope*Reng));
 250     intDensity = intPressure/(Reng*intTemperature);
 251   }
 252
 253   lastIndex=i;
 254 }
 255
 256 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 257 // Calculate parameters derived from T, P and rho
 258
 259 void FGAtmosphere::CalculateDerived(void)
 260 {
 261   T_dev = (*temperature) - GetTemperature(h);
 262   density_altitude = h + T_dev * 66.7;
 263
 264   if (turbType == ttStandard) {
 265     Turbulence();
 266     vWindNED += vTurbulence;
 267   }
 268   if (vWindNED(1) != 0.0) psiw = atan2( vWindNED(2), vWindNED(1) );
 269   if (psiw < 0) psiw += 2*M_PI;
 270
 271   soundspeed = sqrt(SHRatio*Reng*(*temperature));
 272 }
 273
 274
 275 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 276 // Get the standard atmospheric properties at a specified altitude
 277
 278 void FGAtmosphere::GetStdAtmosphere(double altitude) {
 279   StandardTempOnly = true;
 280   Calculate(altitude);
 281   StandardTempOnly = false;
 282   atmosphere.Temperature = intTemperature;
 283   atmosphere.Pressure = intPressure;
 284   atmosphere.Density = intDensity;
 285
 286   // Reset the internal atmospheric state
 287   Calculate(h);
 288 }
 289
 290 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 291 // Get the standard pressure at a specified altitude
 292
 293 double FGAtmosphere::GetPressure(double altitude) {
 294   GetStdAtmosphere(altitude);
 295   return atmosphere.Pressure;
 296 }
 297
 298 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 299 // Get the standard temperature at a specified altitude
 300
 301 double FGAtmosphere::GetTemperature(double altitude) {
 302   GetStdAtmosphere(altitude);
 303   return atmosphere.Temperature;
 304 }
 305
 306 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 307 // Get the standard density at a specified altitude
 308
 309 double FGAtmosphere::GetDensity(double altitude) {
 310   GetStdAtmosphere(altitude);
 311   return atmosphere.Density;
 312 }
 313
 314
 315 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 316 // square a value, but preserve the original sign
 317
 318 static inline double square_signed (double value)
 319 {
 320     if (value < 0)
 321         return value * value * -1;
 322     else
 323         return value * value;
 324 }
 325
 326 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 327
 328 void FGAtmosphere::Turbulence(void)
 329 {
 330   switch (turbType) {
 331   case ttStandard: {
 332     vDirectiondAccelDt(eX) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 333     vDirectiondAccelDt(eY) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 334     vDirectiondAccelDt(eZ) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 335
 336     MagnitudedAccelDt = 1 - 2.0*(double(rand())/double(RAND_MAX)) - Magnitude;
 337                                 // Scale the magnitude so that it moves
 338                                 // away from the peaks
 339     MagnitudedAccelDt = ((MagnitudedAccelDt - Magnitude) /
 340                          (1 + fabs(Magnitude)));
 341     MagnitudeAccel    += MagnitudedAccelDt*rate*TurbRate*State->Getdt();
 342     Magnitude         += MagnitudeAccel*rate*State->Getdt();
 343
 344     vDirectiondAccelDt.Normalize();
 345
 346                                 // deemphasise non-vertical forces
 347     vDirectiondAccelDt(eX) = square_signed(vDirectiondAccelDt(eX));
 348     vDirectiondAccelDt(eY) = square_signed(vDirectiondAccelDt(eY));
 349
 350     vDirectionAccel += vDirectiondAccelDt*rate*TurbRate*State->Getdt();
 351     vDirectionAccel.Normalize();
 352     vDirection      += vDirectionAccel*rate*State->Getdt();
 353
 354     vDirection.Normalize();
 355
 356                                 // Diminish turbulence within three wingspans
 357                                 // of the ground
 358     vTurbulence = TurbGain * Magnitude * vDirection;
 359     double HOverBMAC = Auxiliary->GetHOverBMAC();
 360     if (HOverBMAC < 3.0)
 361         vTurbulence *= (HOverBMAC / 3.0) * (HOverBMAC / 3.0);
 362
 363     vTurbulenceGrad = TurbGain*MagnitudeAccel * vDirection;
 364
 365     vBodyTurbGrad = Propagate->GetTl2b()*vTurbulenceGrad;
 366
 367     if (Aircraft->GetWingSpan() > 0) {
 368       vTurbPQR(eP) = vBodyTurbGrad(eY)/Aircraft->GetWingSpan();
 369     } else {
 370       vTurbPQR(eP) = vBodyTurbGrad(eY)/30.0;
 371     }
 372 //     if (Aircraft->GetHTailArm() != 0.0)
 373 //       vTurbPQR(eQ) = vBodyTurbGrad(eZ)/Aircraft->GetHTailArm();
 374 //     else
 375 //       vTurbPQR(eQ) = vBodyTurbGrad(eZ)/10.0;
 376
 377     if (Aircraft->GetVTailArm() > 0)
 378       vTurbPQR(eR) = vBodyTurbGrad(eX)/Aircraft->GetVTailArm();
 379     else
 380       vTurbPQR(eR) = vBodyTurbGrad(eX)/10.0;
 381
 382                                 // Clear the horizontal forces
 383                                 // actually felt by the plane, now
 384                                 // that we've used them to calculate
 385                                 // moments.
 386     vTurbulence(eX) = 0.0;
 387     vTurbulence(eY) = 0.0;
 388
 389     break;
 390   }
 391   case ttBerndt: {
 392     vDirectiondAccelDt(eX) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 393     vDirectiondAccelDt(eY) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 394     vDirectiondAccelDt(eZ) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 395
 396
 397     MagnitudedAccelDt = 1 - 2.0*(double(rand())/double(RAND_MAX)) - Magnitude;
 398     MagnitudeAccel    += MagnitudedAccelDt*rate*State->Getdt();
 399     Magnitude         += MagnitudeAccel*rate*State->Getdt();
 400
 401     vDirectiondAccelDt.Normalize();
 402     vDirectionAccel += vDirectiondAccelDt*rate*State->Getdt();
 403     vDirectionAccel.Normalize();
 404     vDirection      += vDirectionAccel*rate*State->Getdt();
 405
 406                                 // Diminish z-vector within two wingspans
 407                                 // of the ground
 408     double HOverBMAC = Auxiliary->GetHOverBMAC();
 409     if (HOverBMAC < 2.0)
 410         vDirection(eZ) *= HOverBMAC / 2.0;
 411
 412     vDirection.Normalize();
 413
 414     vTurbulence = TurbGain*Magnitude * vDirection;
 415     vTurbulenceGrad = TurbGain*MagnitudeAccel * vDirection;
 416
 417     vBodyTurbGrad = Propagate->GetTl2b()*vTurbulenceGrad;
 418     vTurbPQR(eP) = vBodyTurbGrad(eY)/Aircraft->GetWingSpan();
 419     if (Aircraft->GetHTailArm() > 0)
 420       vTurbPQR(eQ) = vBodyTurbGrad(eZ)/Aircraft->GetHTailArm();
 421     else
 422       vTurbPQR(eQ) = vBodyTurbGrad(eZ)/10.0;
 423
 424     if (Aircraft->GetVTailArm() > 0)
 425       vTurbPQR(eR) = vBodyTurbGrad(eX)/Aircraft->GetVTailArm();
 426     else
 427       vTurbPQR(eR) = vBodyTurbGrad(eX)/10.0;
 428
 429     break;
 430   }
 431   default:
 432     break;
 433   }
 434 }
 435
 436 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 437
 438 void FGAtmosphere::UseExternal(void)
 439 {
 440   temperature=&exTemperature;
 441   pressure=&exPressure;
 442   density=&exDensity;
 443   useExternal=true;
 444 }
 445
 446 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 447
 448 void FGAtmosphere::UseInternal(void)
 449 {
 450   temperature=&intTemperature;
 451   pressure=&intPressure;
 452   density=&intDensity;
 453   useExternal=false;
 454 }
 455
 456 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 457
 458 void FGAtmosphere::bind(void)
 459 {
 460   typedef double (FGAtmosphere::*PMF)(int) const;
 461   typedef double (FGAtmosphere::*PMFv)(void) const;
 462   PropertyManager->Tie("atmosphere/T-R", this, (PMFv)&FGAtmosphere::GetTemperature);
 463   PropertyManager->Tie("atmosphere/rho-slugs_ft3", this, (PMFv)&FGAtmosphere::GetDensity);
 464   PropertyManager->Tie("atmosphere/P-psf", this, (PMFv)&FGAtmosphere::GetPressure);
 465   PropertyManager->Tie("atmosphere/a-fps", this, &FGAtmosphere::GetSoundSpeed);
 466   PropertyManager->Tie("atmosphere/T-sl-R", this, &FGAtmosphere::GetTemperatureSL);
 467   PropertyManager->Tie("atmosphere/rho-sl-slugs_ft3", this, &FGAtmosphere::GetDensitySL);
 468   PropertyManager->Tie("atmosphere/P-sl-psf", this, &FGAtmosphere::GetPressureSL);
 469   PropertyManager->Tie("atmosphere/a-sl-fps", this, &FGAtmosphere::GetSoundSpeedSL);
 470   PropertyManager->Tie("atmosphere/theta", this, &FGAtmosphere::GetTemperatureRatio);
 471   PropertyManager->Tie("atmosphere/sigma", this, &FGAtmosphere::GetDensityRatio);
 472   PropertyManager->Tie("atmosphere/delta", this, &FGAtmosphere::GetPressureRatio);
 473   PropertyManager->Tie("atmosphere/a-ratio", this, &FGAtmosphere::GetSoundSpeedRatio);
 474   PropertyManager->Tie("atmosphere/psiw-rad", this, &FGAtmosphere::GetWindPsi);
 475   PropertyManager->Tie("atmosphere/delta-T", this, &FGAtmosphere::GetDeltaT, &FGAtmosphere::SetDeltaT);
 476   PropertyManager->Tie("atmosphere/T-sl-dev-F", this, &FGAtmosphere::GetSLTempDev, &FGAtmosphere::SetSLTempDev);
 477   PropertyManager->Tie("atmosphere/density-altitude", this, &FGAtmosphere::GetDensityAltitude);
 478   PropertyManager->Tie("atmosphere/p-turb-rad_sec", this,1, (PMF)&FGAtmosphere::GetTurbPQR);
 479   PropertyManager->Tie("atmosphere/q-turb-rad_sec", this,2, (PMF)&FGAtmosphere::GetTurbPQR);
 480   PropertyManager->Tie("atmosphere/r-turb-rad_sec", this,3, (PMF)&FGAtmosphere::GetTurbPQR);
 481 }
 482
 483 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 484
 485 void FGAtmosphere::unbind(void)
 486 {
 487   PropertyManager->Untie("atmosphere/T-R");
 488   PropertyManager->Untie("atmosphere/rho-slugs_ft3");
 489   PropertyManager->Untie("atmosphere/P-psf");
 490   PropertyManager->Untie("atmosphere/a-fps");
 491   PropertyManager->Untie("atmosphere/T-sl-R");
 492   PropertyManager->Untie("atmosphere/rho-sl-slugs_ft3");
 493   PropertyManager->Untie("atmosphere/P-sl-psf");
 494   PropertyManager->Untie("atmosphere/a-sl-fps");
 495   PropertyManager->Untie("atmosphere/delta-T");
 496   PropertyManager->Untie("atmosphere/T-sl-dev-F");
 497   PropertyManager->Untie("atmosphere/density-altitude");
 498   PropertyManager->Untie("atmosphere/theta");
 499   PropertyManager->Untie("atmosphere/sigma");
 500   PropertyManager->Untie("atmosphere/delta");
 501   PropertyManager->Untie("atmosphere/a-ratio");
 502   PropertyManager->Untie("atmosphere/psiw-rad");
 503   PropertyManager->Untie("atmosphere/p-turb-rad_sec");
 504   PropertyManager->Untie("atmosphere/q-turb-rad_sec");
 505   PropertyManager->Untie("atmosphere/r-turb-rad_sec");
 506 }
 507
 508 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 509 //    The bitmasked value choices are as follows:
 510 //    unset: In this case (the default) JSBSim would only print
 511 //       out the normally expected messages, essentially echoing
 512 //       the config files as they are read. If the environment
 513 //       variable is not set, debug_lvl is set to 1 internally
 514 //    0: This requests JSBSim not to output any messages
 515 //       whatsoever.
 516 //    1: This value explicity requests the normal JSBSim
 517 //       startup messages
 518 //    2: This value asks for a message to be printed out when
 519 //       a class is instantiated
 520 //    4: When this value is set, a message is displayed when a
 521 //       FGModel object executes its Run() method
 522 //    8: When this value is set, various runtime state variables
 523 //       are printed out periodically
 524 //    16: When set various parameters are sanity checked and
 525 //       a message is printed out when they go out of bounds
 526
 527 void FGAtmosphere::Debug(int from)
 528 {
 529   if (debug_lvl <= 0) return;
 530
 531   if (debug_lvl & 1) { // Standard console startup message output
 532     if (from == 0) { // Constructor
 533     }
 534   }
 535   if (debug_lvl & 2 ) { // Instantiation/Destruction notification
 536     if (from == 0) cout << "Instantiated: FGAtmosphere" << endl;
 537     if (from == 1) cout << "Destroyed:    FGAtmosphere" << endl;
 538   }
 539   if (debug_lvl & 4 ) { // Run() method entry print for FGModel-derived objects
 540   }
 541   if (debug_lvl & 8 ) { // Runtime state variables
 542   }
 543   if (debug_lvl & 16) { // Sanity checking
 544   }
 545   if (debug_lvl & 128) { // Turbulence
 546     if (frame == 0 && from == 2) {
 547       cout << "vTurbulence(X), vTurbulence(Y), vTurbulence(Z), "
 548            << "vTurbulenceGrad(X), vTurbulenceGrad(Y), vTurbulenceGrad(Z), "
 549            << "vDirection(X), vDirection(Y), vDirection(Z), "
 550            << "Magnitude, "
 551            << "vTurbPQR(P), vTurbPQR(Q), vTurbPQR(R), " << endl;
 552     } else if (from == 2) {
 553       cout << vTurbulence << ", " << vTurbulenceGrad << ", " << vDirection << ", " << Magnitude << ", " << vTurbPQR << endl;
 554     }
 555   }
 556   if (debug_lvl & 64) {
 557     if (from == 0) { // Constructor
 558       cout << IdSrc << endl;
 559       cout << IdHdr << endl;
 560     }
 561   }
 562 }
 563
 564 } // namespace JSBSim