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   first_pass = true;
  93
  94   bind();
  95   Debug(0);
  96 }
  97
  98 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
  99
 100 FGAtmosphere::~FGAtmosphere()
 101 {
 102   unbind();
 103   Debug(1);
 104 }
 105
 106 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 107
 108 bool FGAtmosphere::InitModel(void)
 109 {
 110   FGModel::InitModel();
 111
 112   UseInternal();  // this is the default
 113
 114   Calculate(h);
 115   StdSLtemperature = SLtemperature = 518.67;
 116   StdSLpressure    = SLpressure = 2116.22;
 117   StdSLdensity     = SLdensity = 0.00237767;
 118   StdSLsoundspeed  = SLsoundspeed = sqrt(SHRatio*Reng*StdSLtemperature);
 119   rSLtemperature = 1.0/StdSLtemperature;
 120   rSLpressure    = 1.0/StdSLpressure;
 121   rSLdensity     = 1.0/StdSLdensity;
 122   rSLsoundspeed  = 1.0/StdSLsoundspeed;
 123
 124   return true;
 125 }
 126
 127 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 128
 129 bool FGAtmosphere::Run(void)
 130 {
 131   if (FGModel::Run()) return true;
 132   if (FDMExec->Holding()) return false;
 133
 134   T_dev = 0.0;
 135   h = Propagate->Geth();
 136
 137   if (!useExternal) {
 138     Calculate(h);
 139     CalculateDerived();
 140   } else {
 141     CalculateDerived();
 142   }
 143
 144   Debug(2);
 145   return false;
 146 }
 147
 148 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 149 //
 150 // See reference 1
 151
 152 void FGAtmosphere::Calculate(double altitude)
 153 {
 154   double slope, reftemp, refpress;
 155   int i = 0;
 156
 157   i = lastIndex;
 158   if (altitude < htab[lastIndex]) {
 159     if (altitude <= 0) {
 160       i = 0;
 161       altitude=0;
 162     } else {
 163        i = lastIndex-1;
 164        while (htab[i] > altitude) i--;
 165     }
 166   } else if (altitude > htab[lastIndex+1]) {
 167     if (altitude >= htab[7]) {
 168       i = 7;
 169       altitude = htab[7];
 170     } else {
 171       i = lastIndex+1;
 172       while (htab[i+1] < altitude) i++;
 173     }
 174   }
 175
 176   switch(i) {
 177   case 1:     // 36089 ft.
 178     slope     = 0;
 179     reftemp   = 389.97;
 180     refpress  = 472.452;
 181     //refdens   = 0.000706032;
 182     break;
 183   case 2:     // 65616 ft.
 184     slope     = 0.00054864;
 185     reftemp   = 389.97;
 186     refpress  = 114.636;
 187     //refdens   = 0.000171306;
 188     break;
 189   case 3:     // 104986 ft.
 190     slope     = 0.00153619;
 191     reftemp   = 411.57;
 192     refpress  = 8.36364;
 193     //refdens   = 1.18422e-05;
 194     break;
 195   case 4:     // 154199 ft.
 196     slope     = 0;
 197     reftemp   = 487.17;
 198     refpress  = 0.334882;
 199     //refdens   = 4.00585e-7;
 200     break;
 201   case 5:     // 170603 ft.
 202     slope     = -0.00109728;
 203     reftemp   = 487.17;
 204     refpress  = 0.683084;
 205     //refdens   = 8.17102e-7;
 206     break;
 207   case 6:     // 200131 ft.
 208     slope     = -0.00219456;
 209     reftemp   = 454.17;
 210     refpress  = 0.00684986;
 211     //refdens   = 8.77702e-9;
 212     break;
 213   case 7:     // 259186 ft.
 214     slope     = 0;
 215     reftemp   = 325.17;
 216     refpress  = 0.000122276;
 217     //refdens   = 2.19541e-10;
 218     break;
 219   case 0:
 220   default:     // sea level
 221     slope     = -0.00356616; // R/ft.
 222     reftemp   = 518.67;    // R
 223     refpress  = 2116.22;    // psf
 224     //refdens   = 0.00237767;  // slugs/cubic ft.
 225     break;
 226
 227   }
 228
 229   // If delta_T is set, then that is our temperature deviation at any altitude.
 230   // If not, then we'll estimate a deviation based on the sea level deviation (if set).
 231
 232   if(!StandardTempOnly) {
 233     T_dev = 0.0;
 234     if (delta_T != 0.0) {
 235       T_dev = delta_T;
 236     } else {
 237       if ((altitude < 36089.239) && (T_dev_sl != 0.0)) {
 238         T_dev = T_dev_sl * ( 1.0 - (altitude/36089.239));
 239       }
 240     }
 241     reftemp+=T_dev;
 242   }
 243
 244   if (slope == 0) {
 245     intTemperature = reftemp;
 246     intPressure = refpress*exp(-Inertial->SLgravity()/(reftemp*Reng)*(altitude-htab[i]));
 247     intDensity = intPressure/(Reng*intTemperature);
 248   } else {
 249     intTemperature = reftemp+slope*(altitude-htab[i]);
 250     intPressure = refpress*pow(intTemperature/reftemp,-Inertial->SLgravity()/(slope*Reng));
 251     intDensity = intPressure/(Reng*intTemperature);
 252   }
 253
 254   lastIndex=i;
 255 }
 256
 257 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 258 // Calculate parameters derived from T, P and rho
 259
 260 void FGAtmosphere::CalculateDerived(void)
 261 {
 262   T_dev = (*temperature) - GetTemperature(h);
 263   density_altitude = h + T_dev * 66.7;
 264
 265   if (turbType == ttStandard) {
 266     Turbulence();
 267     vWindNED += vTurbulence;
 268   }
 269   if (vWindNED(1) != 0.0) psiw = atan2( vWindNED(2), vWindNED(1) );
 270   if (psiw < 0) psiw += 2*M_PI;
 271
 272   soundspeed = sqrt(SHRatio*Reng*(*temperature));
 273 }
 274
 275
 276 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 277 // Get the standard atmospheric properties at a specified altitude
 278
 279 void FGAtmosphere::GetStdAtmosphere(double altitude) {
 280   StandardTempOnly = true;
 281   Calculate(altitude);
 282   StandardTempOnly = false;
 283   atmosphere.Temperature = intTemperature;
 284   atmosphere.Pressure = intPressure;
 285   atmosphere.Density = intDensity;
 286
 287   // Reset the internal atmospheric state
 288   Calculate(h);
 289 }
 290
 291 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 292 // Get the standard pressure at a specified altitude
 293
 294 double FGAtmosphere::GetPressure(double altitude) {
 295   GetStdAtmosphere(altitude);
 296   return atmosphere.Pressure;
 297 }
 298
 299 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 300 // Get the standard temperature at a specified altitude
 301
 302 double FGAtmosphere::GetTemperature(double altitude) {
 303   GetStdAtmosphere(altitude);
 304   return atmosphere.Temperature;
 305 }
 306
 307 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 308 // Get the standard density at a specified altitude
 309
 310 double FGAtmosphere::GetDensity(double altitude) {
 311   GetStdAtmosphere(altitude);
 312   return atmosphere.Density;
 313 }
 314
 315
 316 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 317 // square a value, but preserve the original sign
 318
 319 static inline double square_signed (double value)
 320 {
 321     if (value < 0)
 322         return value * value * -1;
 323     else
 324         return value * value;
 325 }
 326
 327 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 328
 329 void FGAtmosphere::Turbulence(void)
 330 {
 331   switch (turbType) {
 332   case ttStandard: {
 333     vDirectiondAccelDt(eX) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 334     vDirectiondAccelDt(eY) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 335     vDirectiondAccelDt(eZ) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 336
 337     MagnitudedAccelDt = 1 - 2.0*(double(rand())/double(RAND_MAX)) - Magnitude;
 338                                 // Scale the magnitude so that it moves
 339                                 // away from the peaks
 340     MagnitudedAccelDt = ((MagnitudedAccelDt - Magnitude) /
 341                          (1 + fabs(Magnitude)));
 342     MagnitudeAccel    += MagnitudedAccelDt*rate*TurbRate*State->Getdt();
 343     Magnitude         += MagnitudeAccel*rate*State->Getdt();
 344
 345     vDirectiondAccelDt.Normalize();
 346
 347                                 // deemphasise non-vertical forces
 348     vDirectiondAccelDt(eX) = square_signed(vDirectiondAccelDt(eX));
 349     vDirectiondAccelDt(eY) = square_signed(vDirectiondAccelDt(eY));
 350
 351     vDirectionAccel += vDirectiondAccelDt*rate*TurbRate*State->Getdt();
 352     vDirectionAccel.Normalize();
 353     vDirection      += vDirectionAccel*rate*State->Getdt();
 354
 355     vDirection.Normalize();
 356
 357                                 // Diminish turbulence within three wingspans
 358                                 // of the ground
 359     vTurbulence = TurbGain * Magnitude * vDirection;
 360     double HOverBMAC = Auxiliary->GetHOverBMAC();
 361     if (HOverBMAC < 3.0)
 362         vTurbulence *= (HOverBMAC / 3.0) * (HOverBMAC / 3.0);
 363
 364     vTurbulenceGrad = TurbGain*MagnitudeAccel * vDirection;
 365
 366     vBodyTurbGrad = Propagate->GetTl2b()*vTurbulenceGrad;
 367
 368     if (Aircraft->GetWingSpan() > 0) {
 369       vTurbPQR(eP) = vBodyTurbGrad(eY)/Aircraft->GetWingSpan();
 370     } else {
 371       vTurbPQR(eP) = vBodyTurbGrad(eY)/30.0;
 372     }
 373 //     if (Aircraft->GetHTailArm() != 0.0)
 374 //       vTurbPQR(eQ) = vBodyTurbGrad(eZ)/Aircraft->GetHTailArm();
 375 //     else
 376 //       vTurbPQR(eQ) = vBodyTurbGrad(eZ)/10.0;
 377
 378     if (Aircraft->GetVTailArm() > 0)
 379       vTurbPQR(eR) = vBodyTurbGrad(eX)/Aircraft->GetVTailArm();
 380     else
 381       vTurbPQR(eR) = vBodyTurbGrad(eX)/10.0;
 382
 383                                 // Clear the horizontal forces
 384                                 // actually felt by the plane, now
 385                                 // that we've used them to calculate
 386                                 // moments.
 387     vTurbulence(eX) = 0.0;
 388     vTurbulence(eY) = 0.0;
 389
 390     break;
 391   }
 392   case ttBerndt: {
 393     vDirectiondAccelDt(eX) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 394     vDirectiondAccelDt(eY) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 395     vDirectiondAccelDt(eZ) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 396
 397
 398     MagnitudedAccelDt = 1 - 2.0*(double(rand())/double(RAND_MAX)) - Magnitude;
 399     MagnitudeAccel    += MagnitudedAccelDt*rate*State->Getdt();
 400     Magnitude         += MagnitudeAccel*rate*State->Getdt();
 401
 402     vDirectiondAccelDt.Normalize();
 403     vDirectionAccel += vDirectiondAccelDt*rate*State->Getdt();
 404     vDirectionAccel.Normalize();
 405     vDirection      += vDirectionAccel*rate*State->Getdt();
 406
 407                                 // Diminish z-vector within two wingspans
 408                                 // of the ground
 409     double HOverBMAC = Auxiliary->GetHOverBMAC();
 410     if (HOverBMAC < 2.0)
 411         vDirection(eZ) *= HOverBMAC / 2.0;
 412
 413     vDirection.Normalize();
 414
 415     vTurbulence = TurbGain*Magnitude * vDirection;
 416     vTurbulenceGrad = TurbGain*MagnitudeAccel * vDirection;
 417
 418     vBodyTurbGrad = Propagate->GetTl2b()*vTurbulenceGrad;
 419     vTurbPQR(eP) = vBodyTurbGrad(eY)/Aircraft->GetWingSpan();
 420     if (Aircraft->GetHTailArm() > 0)
 421       vTurbPQR(eQ) = vBodyTurbGrad(eZ)/Aircraft->GetHTailArm();
 422     else
 423       vTurbPQR(eQ) = vBodyTurbGrad(eZ)/10.0;
 424
 425     if (Aircraft->GetVTailArm() > 0)
 426       vTurbPQR(eR) = vBodyTurbGrad(eX)/Aircraft->GetVTailArm();
 427     else
 428       vTurbPQR(eR) = vBodyTurbGrad(eX)/10.0;
 429
 430     break;
 431   }
 432   default:
 433     break;
 434   }
 435 }
 436
 437 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 438
 439 void FGAtmosphere::UseExternal(void)
 440 {
 441   temperature=&exTemperature;
 442   pressure=&exPressure;
 443   density=&exDensity;
 444   useExternal=true;
 445 }
 446
 447 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 448
 449 void FGAtmosphere::UseInternal(void)
 450 {
 451   temperature=&intTemperature;
 452   pressure=&intPressure;
 453   density=&intDensity;
 454   useExternal=false;
 455 }
 456
 457 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 458
 459 void FGAtmosphere::bind(void)
 460 {
 461   typedef double (FGAtmosphere::*PMF)(int) const;
 462   typedef double (FGAtmosphere::*PMFv)(void) const;
 463   PropertyManager->Tie("atmosphere/T-R", this, (PMFv)&FGAtmosphere::GetTemperature);
 464   PropertyManager->Tie("atmosphere/rho-slugs_ft3", this, (PMFv)&FGAtmosphere::GetDensity);
 465   PropertyManager->Tie("atmosphere/P-psf", this, (PMFv)&FGAtmosphere::GetPressure);
 466   PropertyManager->Tie("atmosphere/a-fps", this, &FGAtmosphere::GetSoundSpeed);
 467   PropertyManager->Tie("atmosphere/T-sl-R", this, &FGAtmosphere::GetTemperatureSL);
 468   PropertyManager->Tie("atmosphere/rho-sl-slugs_ft3", this, &FGAtmosphere::GetDensitySL);
 469   PropertyManager->Tie("atmosphere/P-sl-psf", this, &FGAtmosphere::GetPressureSL);
 470   PropertyManager->Tie("atmosphere/a-sl-fps", this, &FGAtmosphere::GetSoundSpeedSL);
 471   PropertyManager->Tie("atmosphere/theta", this, &FGAtmosphere::GetTemperatureRatio);
 472   PropertyManager->Tie("atmosphere/sigma", this, &FGAtmosphere::GetDensityRatio);
 473   PropertyManager->Tie("atmosphere/delta", this, &FGAtmosphere::GetPressureRatio);
 474   PropertyManager->Tie("atmosphere/a-ratio", this, &FGAtmosphere::GetSoundSpeedRatio);
 475   PropertyManager->Tie("atmosphere/psiw-rad", this, &FGAtmosphere::GetWindPsi);
 476   PropertyManager->Tie("atmosphere/delta-T", this, &FGAtmosphere::GetDeltaT, &FGAtmosphere::SetDeltaT);
 477   PropertyManager->Tie("atmosphere/T-sl-dev-F", this, &FGAtmosphere::GetSLTempDev, &FGAtmosphere::SetSLTempDev);
 478   PropertyManager->Tie("atmosphere/density-altitude", this, &FGAtmosphere::GetDensityAltitude);
 479   PropertyManager->Tie("atmosphere/p-turb-rad_sec", this,1, (PMF)&FGAtmosphere::GetTurbPQR);
 480   PropertyManager->Tie("atmosphere/q-turb-rad_sec", this,2, (PMF)&FGAtmosphere::GetTurbPQR);
 481   PropertyManager->Tie("atmosphere/r-turb-rad_sec", this,3, (PMF)&FGAtmosphere::GetTurbPQR);
 482 }
 483
 484 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 485
 486 void FGAtmosphere::unbind(void)
 487 {
 488   PropertyManager->Untie("atmosphere/T-R");
 489   PropertyManager->Untie("atmosphere/rho-slugs_ft3");
 490   PropertyManager->Untie("atmosphere/P-psf");
 491   PropertyManager->Untie("atmosphere/a-fps");
 492   PropertyManager->Untie("atmosphere/T-sl-R");
 493   PropertyManager->Untie("atmosphere/rho-sl-slugs_ft3");
 494   PropertyManager->Untie("atmosphere/P-sl-psf");
 495   PropertyManager->Untie("atmosphere/a-sl-fps");
 496   PropertyManager->Untie("atmosphere/delta-T");
 497   PropertyManager->Untie("atmosphere/T-sl-dev-F");
 498   PropertyManager->Untie("atmosphere/density-altitude");
 499   PropertyManager->Untie("atmosphere/theta");
 500   PropertyManager->Untie("atmosphere/sigma");
 501   PropertyManager->Untie("atmosphere/delta");
 502   PropertyManager->Untie("atmosphere/a-ratio");
 503   PropertyManager->Untie("atmosphere/psiw-rad");
 504   PropertyManager->Untie("atmosphere/p-turb-rad_sec");
 505   PropertyManager->Untie("atmosphere/q-turb-rad_sec");
 506   PropertyManager->Untie("atmosphere/r-turb-rad_sec");
 507 }
 508
 509 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 510 //    The bitmasked value choices are as follows:
 511 //    unset: In this case (the default) JSBSim would only print
 512 //       out the normally expected messages, essentially echoing
 513 //       the config files as they are read. If the environment
 514 //       variable is not set, debug_lvl is set to 1 internally
 515 //    0: This requests JSBSim not to output any messages
 516 //       whatsoever.
 517 //    1: This value explicity requests the normal JSBSim
 518 //       startup messages
 519 //    2: This value asks for a message to be printed out when
 520 //       a class is instantiated
 521 //    4: When this value is set, a message is displayed when a
 522 //       FGModel object executes its Run() method
 523 //    8: When this value is set, various runtime state variables
 524 //       are printed out periodically
 525 //    16: When set various parameters are sanity checked and
 526 //       a message is printed out when they go out of bounds
 527
 528 void FGAtmosphere::Debug(int from)
 529 {
 530   if (debug_lvl <= 0) return;
 531
 532   if (debug_lvl & 1) { // Standard console startup message output
 533     if (from == 0) { // Constructor
 534     }
 535   }
 536   if (debug_lvl & 2 ) { // Instantiation/Destruction notification
 537     if (from == 0) cout << "Instantiated: FGAtmosphere" << endl;
 538     if (from == 1) cout << "Destroyed:    FGAtmosphere" << endl;
 539   }
 540   if (debug_lvl & 4 ) { // Run() method entry print for FGModel-derived objects
 541   }
 542   if (debug_lvl & 8 ) { // Runtime state variables
 543   }
 544   if (debug_lvl & 16) { // Sanity checking
 545   }
 546   if (debug_lvl & 128) { // Turbulence
 547     if (first_pass && from == 2) {
 548       first_pass = false;
 549       cout << "vTurbulence(X), vTurbulence(Y), vTurbulence(Z), "
 550            << "vTurbulenceGrad(X), vTurbulenceGrad(Y), vTurbulenceGrad(Z), "
 551            << "vDirection(X), vDirection(Y), vDirection(Z), "
 552            << "Magnitude, "
 553            << "vTurbPQR(P), vTurbPQR(Q), vTurbPQR(R), " << endl;
 554     }
 555     if (from == 2) {
 556       cout << vTurbulence << ", " << vTurbulenceGrad << ", " << vDirection << ", " << Magnitude << ", " << vTurbPQR << endl;
 557     }
 558   }
 559   if (debug_lvl & 64) {
 560     if (from == 0) { // Constructor
 561       cout << IdSrc << endl;
 562       cout << IdHdr << endl;
 563     }
 564   }
 565 }
 566
 567 } // namespace JSBSim