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   SetTurbType( ttCulp );
  85   TurbGain = 0.0;
  86   TurbRate = 1.7;
  87   Rhythmicity = 0.1;
  88   spike = target_time = strength = 0.0;
  89   wind_from_clockwise = 0.0;
  90
  91   T_dev_sl = T_dev = delta_T = 0.0;
  92   StandardTempOnly = false;
  93   first_pass = true;
  94   vGustNED(1) = vGustNED(2) = vGustNED(3) = 0.0; bgustSet = false;
  95   vTurbulence(1) = vTurbulence(2) = vTurbulence(3) = 0.0;
  96
  97   bind();
  98   Debug(0);
  99 }
 100
 101 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 102
 103 FGAtmosphere::~FGAtmosphere()
 104 {
 105   Debug(1);
 106 }
 107
 108 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 109
 110 bool FGAtmosphere::InitModel(void)
 111 {
 112   if (!FGModel::InitModel()) return false;
 113
 114   UseInternal();  // this is the default
 115
 116   Calculate(h);
 117   StdSLtemperature = SLtemperature = 518.67;
 118   StdSLpressure    = SLpressure = 2116.22;
 119   StdSLdensity     = SLdensity = 0.00237767;
 120   StdSLsoundspeed  = SLsoundspeed = sqrt(SHRatio*Reng*StdSLtemperature);
 121   rSLtemperature = 1.0/StdSLtemperature;
 122   rSLpressure    = 1.0/StdSLpressure;
 123   rSLdensity     = 1.0/StdSLdensity;
 124   rSLsoundspeed  = 1.0/StdSLsoundspeed;
 125
 126   return true;
 127 }
 128
 129 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 130
 131 bool FGAtmosphere::Run(void)
 132 {
 133   if (FGModel::Run()) return true;
 134   if (FDMExec->Holding()) return false;
 135
 136   T_dev = 0.0;
 137   h = Propagate->Geth();
 138
 139   if (!useExternal) {
 140     Calculate(h);
 141     CalculateDerived();
 142   } else {
 143     CalculateDerived();
 144   }
 145
 146   Debug(2);
 147   return false;
 148 }
 149
 150 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 151 //
 152 // See reference 1
 153
 154 void FGAtmosphere::Calculate(double altitude)
 155 {
 156   double slope, reftemp, refpress;
 157   int i = lastIndex;
 158
 159   if (altitude < htab[lastIndex]) {
 160     if (altitude <= 0) {
 161       i = 0;
 162       altitude=0;
 163     } else {
 164        i = lastIndex-1;
 165        while (htab[i] > altitude) i--;
 166     }
 167   } else if (altitude > htab[lastIndex+1]) {
 168     if (altitude >= htab[7]) {
 169       i = 7;
 170       altitude = htab[7];
 171     } else {
 172       i = lastIndex+1;
 173       while (htab[i+1] < altitude) i++;
 174     }
 175   }
 176
 177   switch(i) {
 178   case 1:     // 36089 ft.
 179     slope     = 0;
 180     reftemp   = 389.97;
 181     refpress  = 472.452;
 182     //refdens   = 0.000706032;
 183     break;
 184   case 2:     // 65616 ft.
 185     slope     = 0.00054864;
 186     reftemp   = 389.97;
 187     refpress  = 114.636;
 188     //refdens   = 0.000171306;
 189     break;
 190   case 3:     // 104986 ft.
 191     slope     = 0.00153619;
 192     reftemp   = 411.57;
 193     refpress  = 8.36364;
 194     //refdens   = 1.18422e-05;
 195     break;
 196   case 4:     // 154199 ft.
 197     slope     = 0;
 198     reftemp   = 487.17;
 199     refpress  = 0.334882;
 200     //refdens   = 4.00585e-7;
 201     break;
 202   case 5:     // 170603 ft.
 203     slope     = -0.00109728;
 204     reftemp   = 487.17;
 205     refpress  = 0.683084;
 206     //refdens   = 8.17102e-7;
 207     break;
 208   case 6:     // 200131 ft.
 209     slope     = -0.00219456;
 210     reftemp   = 454.17;
 211     refpress  = 0.00684986;
 212     //refdens   = 8.77702e-9;
 213     break;
 214   case 7:     // 259186 ft.
 215     slope     = 0;
 216     reftemp   = 325.17;
 217     refpress  = 0.000122276;
 218     //refdens   = 2.19541e-10;
 219     break;
 220   case 0:
 221   default:     // sea level
 222     slope     = -0.00356616; // R/ft.
 223     reftemp   = 518.67;    // R
 224     refpress  = 2116.22;    // psf
 225     //refdens   = 0.00237767;  // slugs/cubic ft.
 226     break;
 227
 228   }
 229
 230   // If delta_T is set, then that is our temperature deviation at any altitude.
 231   // If not, then we'll estimate a deviation based on the sea level deviation (if set).
 232
 233   if(!StandardTempOnly) {
 234     T_dev = 0.0;
 235     if (delta_T != 0.0) {
 236       T_dev = delta_T;
 237     } else {
 238       if ((altitude < 36089.239) && (T_dev_sl != 0.0)) {
 239         T_dev = T_dev_sl * ( 1.0 - (altitude/36089.239));
 240       }
 241     }
 242     reftemp+=T_dev;
 243   }
 244
 245   if (slope == 0) {
 246     intTemperature = reftemp;
 247     intPressure = refpress*exp(-Inertial->SLgravity()/(reftemp*Reng)*(altitude-htab[i]));
 248     intDensity = intPressure/(Reng*intTemperature);
 249   } else {
 250     intTemperature = reftemp+slope*(altitude-htab[i]);
 251     intPressure = refpress*pow(intTemperature/reftemp,-Inertial->SLgravity()/(slope*Reng));
 252     intDensity = intPressure/(Reng*intTemperature);
 253   }
 254
 255   lastIndex=i;
 256 }
 257
 258 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 259 // Calculate parameters derived from T, P and rho
 260
 261 void FGAtmosphere::CalculateDerived(void)
 262 {
 263   T_dev = (*temperature) - GetTemperature(h);
 264   density_altitude = h + T_dev * 66.7;
 265
 266   if (turbType == ttStandard || ttCulp) {
 267     Turbulence();
 268     vWindNED += vGustNED + vTurbulence;
 269   }
 270   if (vWindNED(1) != 0.0) psiw = atan2( vWindNED(2), vWindNED(1) );
 271   if (psiw < 0) psiw += 2*M_PI;
 272
 273   soundspeed = sqrt(SHRatio*Reng*(*temperature));
 274 }
 275
 276
 277 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 278 // Get the standard atmospheric properties at a specified altitude
 279
 280 void FGAtmosphere::GetStdAtmosphere(double altitude) {
 281   StandardTempOnly = true;
 282   Calculate(altitude);
 283   StandardTempOnly = false;
 284   atmosphere.Temperature = intTemperature;
 285   atmosphere.Pressure = intPressure;
 286   atmosphere.Density = intDensity;
 287
 288   // Reset the internal atmospheric state
 289   Calculate(h);
 290 }
 291
 292 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 293 // Get the standard pressure at a specified altitude
 294
 295 double FGAtmosphere::GetPressure(double altitude) {
 296   GetStdAtmosphere(altitude);
 297   return atmosphere.Pressure;
 298 }
 299
 300 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 301 // Get the standard temperature at a specified altitude
 302
 303 double FGAtmosphere::GetTemperature(double altitude) {
 304   GetStdAtmosphere(altitude);
 305   return atmosphere.Temperature;
 306 }
 307
 308 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 309 // Get the standard density at a specified altitude
 310
 311 double FGAtmosphere::GetDensity(double altitude) {
 312   GetStdAtmosphere(altitude);
 313   return atmosphere.Density;
 314 }
 315
 316
 317 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 318 // square a value, but preserve the original sign
 319
 320 static inline double square_signed (double value)
 321 {
 322     if (value < 0)
 323         return value * value * -1;
 324     else
 325         return value * value;
 326 }
 327
 328 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 329
 330 void FGAtmosphere::Turbulence(void)
 331 {
 332   switch (turbType) {
 333   case ttStandard: {
 334     TurbGain = TurbGain * TurbGain * 100.0;
 335
 336     vDirectiondAccelDt(eX) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 337     vDirectiondAccelDt(eY) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 338     vDirectiondAccelDt(eZ) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 339
 340     MagnitudedAccelDt = 1 - 2.0*(double(rand())/double(RAND_MAX)) - Magnitude;
 341                                 // Scale the magnitude so that it moves
 342                                 // away from the peaks
 343     MagnitudedAccelDt = ((MagnitudedAccelDt - Magnitude) /
 344                          (1 + fabs(Magnitude)));
 345     MagnitudeAccel    += MagnitudedAccelDt*rate*TurbRate*State->Getdt();
 346     Magnitude         += MagnitudeAccel*rate*State->Getdt();
 347     Magnitude          = fabs(Magnitude);
 348
 349     vDirectiondAccelDt.Normalize();
 350
 351                                 // deemphasise non-vertical forces
 352     vDirectiondAccelDt(eX) = square_signed(vDirectiondAccelDt(eX));
 353     vDirectiondAccelDt(eY) = square_signed(vDirectiondAccelDt(eY));
 354
 355     vDirectionAccel += vDirectiondAccelDt*rate*TurbRate*State->Getdt();
 356     vDirectionAccel.Normalize();
 357     vDirection      += vDirectionAccel*rate*State->Getdt();
 358
 359     vDirection.Normalize();
 360
 361                                 // Diminish turbulence within three wingspans
 362                                 // of the ground
 363     vTurbulence = TurbGain * Magnitude * vDirection;
 364     double HOverBMAC = Auxiliary->GetHOverBMAC();
 365     if (HOverBMAC < 3.0)
 366         vTurbulence *= (HOverBMAC / 3.0) * (HOverBMAC / 3.0);
 367
 368     // I don't believe these next two statements calculate the proper gradient over
 369     // the aircraft body. One reason is because this has no relationship with the
 370     // orientation or velocity of the aircraft, which it must have. What is vTurbulenceGrad
 371     // supposed to represent? And the direction and magnitude of the turbulence can change,
 372     // so both accelerations need to be accounted for, no?
 373
 374     // Need to determine the turbulence change in body axes between two time points.
 375
 376     vTurbulenceGrad = TurbGain*MagnitudeAccel * vDirection;
 377     vBodyTurbGrad = Propagate->GetTl2b()*vTurbulenceGrad;
 378
 379     if (Aircraft->GetWingSpan() > 0) {
 380       vTurbPQR(eP) = vBodyTurbGrad(eY)/Aircraft->GetWingSpan();
 381     } else {
 382       vTurbPQR(eP) = vBodyTurbGrad(eY)/30.0;
 383     }
 384 //     if (Aircraft->GetHTailArm() != 0.0)
 385 //       vTurbPQR(eQ) = vBodyTurbGrad(eZ)/Aircraft->GetHTailArm();
 386 //     else
 387 //       vTurbPQR(eQ) = vBodyTurbGrad(eZ)/10.0;
 388
 389     if (Aircraft->GetVTailArm() > 0)
 390       vTurbPQR(eR) = vBodyTurbGrad(eX)/Aircraft->GetVTailArm();
 391     else
 392       vTurbPQR(eR) = vBodyTurbGrad(eX)/10.0;
 393
 394                                 // Clear the horizontal forces
 395                                 // actually felt by the plane, now
 396                                 // that we've used them to calculate
 397                                 // moments.
 398                                 // Why? (JSB)
 399 //    vTurbulence(eX) = 0.0;
 400 //    vTurbulence(eY) = 0.0;
 401
 402     break;
 403   }
 404   case ttBerndt: { // This is very experimental and incomplete at the moment.
 405
 406     TurbGain = TurbGain * TurbGain * 100.0;
 407
 408     vDirectiondAccelDt(eX) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 409     vDirectiondAccelDt(eY) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 410     vDirectiondAccelDt(eZ) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 411
 412
 413     MagnitudedAccelDt = 1 - 2.0*(double(rand())/double(RAND_MAX)) - Magnitude;
 414     MagnitudeAccel    += MagnitudedAccelDt*rate*State->Getdt();
 415     Magnitude         += MagnitudeAccel*rate*State->Getdt();
 416
 417     vDirectiondAccelDt.Normalize();
 418     vDirectionAccel += vDirectiondAccelDt*rate*State->Getdt();
 419     vDirectionAccel.Normalize();
 420     vDirection      += vDirectionAccel*rate*State->Getdt();
 421
 422                                 // Diminish z-vector within two wingspans
 423                                 // of the ground
 424     double HOverBMAC = Auxiliary->GetHOverBMAC();
 425     if (HOverBMAC < 2.0)
 426         vDirection(eZ) *= HOverBMAC / 2.0;
 427
 428     vDirection.Normalize();
 429
 430     vTurbulence = TurbGain*Magnitude * vDirection;
 431     vTurbulenceGrad = TurbGain*MagnitudeAccel * vDirection;
 432
 433     vBodyTurbGrad = Propagate->GetTl2b()*vTurbulenceGrad;
 434     vTurbPQR(eP) = vBodyTurbGrad(eY)/Aircraft->GetWingSpan();
 435     if (Aircraft->GetHTailArm() > 0)
 436       vTurbPQR(eQ) = vBodyTurbGrad(eZ)/Aircraft->GetHTailArm();
 437     else
 438       vTurbPQR(eQ) = vBodyTurbGrad(eZ)/10.0;
 439
 440     if (Aircraft->GetVTailArm() > 0)
 441       vTurbPQR(eR) = vBodyTurbGrad(eX)/Aircraft->GetVTailArm();
 442     else
 443       vTurbPQR(eR) = vBodyTurbGrad(eX)/10.0;
 444
 445     break;
 446   }
 447   case ttCulp: {
 448
 449     vTurbPQR(eP) = wind_from_clockwise;
 450     if (TurbGain == 0.0) return;
 451
 452     // keep the inputs within allowable limts for this model
 453     if (TurbGain < 0.0) TurbGain = 0.0;
 454     if (TurbGain > 1.0) TurbGain = 1.0;
 455     if (TurbRate < 0.0) TurbRate = 0.0;
 456     if (TurbRate > 30.0) TurbRate = 30.0;
 457     if (Rhythmicity < 0.0) Rhythmicity = 0.0;
 458     if (Rhythmicity > 1.0) Rhythmicity = 1.0;
 459
 460     // generate a sine wave corresponding to turbulence rate in hertz
 461     double time = FDMExec->GetSimTime();
 462     double sinewave = sin( time * TurbRate * 6.283185307 );
 463
 464     double random = 0.0;
 465     if (target_time == 0.0) {
 466       strength = random = 1 - 2.0*(double(rand())/double(RAND_MAX));
 467       target_time = time + 0.71 + (random * 0.5);
 468     }
 469     if (time > target_time) {
 470       spike = 1.0;
 471       target_time = 0.0;
 472     }
 473
 474     // max vertical wind speed in fps, corresponds to TurbGain = 1.0
 475     double max_vs = 40;
 476
 477     vTurbulence(1) = vTurbulence(2) = vTurbulence(3) = 0.0;
 478     double delta = strength * max_vs * TurbGain * (1-Rhythmicity) * spike;
 479
 480     // Vertical component of turbulence.
 481     vTurbulence(3) = sinewave * max_vs * TurbGain * Rhythmicity;
 482     vTurbulence(3)+= delta;
 483     double HOverBMAC = Auxiliary->GetHOverBMAC();
 484     if (HOverBMAC < 3.0)
 485         vTurbulence(3) *= HOverBMAC * 0.3333;
 486
 487     // Yaw component of turbulence.
 488     vTurbulence(1) = sin( delta * 3.0 );
 489     vTurbulence(2) = cos( delta * 3.0 );
 490
 491     // Roll component of turbulence. Clockwise vortex causes left roll.
 492     vTurbPQR(eP) += delta * 0.04;
 493
 494     spike = spike * 0.9;
 495     break;
 496   }
 497   default:
 498     break;
 499   }
 500 }
 501
 502 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 503
 504 void FGAtmosphere::UseExternal(void)
 505 {
 506   temperature=&exTemperature;
 507   pressure=&exPressure;
 508   density=&exDensity;
 509   useExternal=true;
 510 }
 511
 512 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 513
 514 void FGAtmosphere::UseInternal(void)
 515 {
 516   temperature=&intTemperature;
 517   pressure=&intPressure;
 518   density=&intDensity;
 519   useExternal=false;
 520 }
 521
 522 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 523
 524 void FGAtmosphere::bind(void)
 525 {
 526   typedef double (FGAtmosphere::*PMF)(int) const;
 527   typedef double (FGAtmosphere::*PMFv)(void) const;
 528   typedef void   (FGAtmosphere::*PMFd)(int,double);
 529   PropertyManager->Tie("atmosphere/T-R", this, (PMFv)&FGAtmosphere::GetTemperature);
 530   PropertyManager->Tie("atmosphere/rho-slugs_ft3", this, (PMFv)&FGAtmosphere::GetDensity);
 531   PropertyManager->Tie("atmosphere/P-psf", this, (PMFv)&FGAtmosphere::GetPressure);
 532   PropertyManager->Tie("atmosphere/a-fps", this, &FGAtmosphere::GetSoundSpeed);
 533   PropertyManager->Tie("atmosphere/T-sl-R", this, &FGAtmosphere::GetTemperatureSL);
 534   PropertyManager->Tie("atmosphere/rho-sl-slugs_ft3", this, &FGAtmosphere::GetDensitySL);
 535   PropertyManager->Tie("atmosphere/P-sl-psf", this, &FGAtmosphere::GetPressureSL);
 536   PropertyManager->Tie("atmosphere/a-sl-fps", this, &FGAtmosphere::GetSoundSpeedSL);
 537   PropertyManager->Tie("atmosphere/theta", this, &FGAtmosphere::GetTemperatureRatio);
 538   PropertyManager->Tie("atmosphere/sigma", this, &FGAtmosphere::GetDensityRatio);
 539   PropertyManager->Tie("atmosphere/delta", this, &FGAtmosphere::GetPressureRatio);
 540   PropertyManager->Tie("atmosphere/a-ratio", this, &FGAtmosphere::GetSoundSpeedRatio);
 541   PropertyManager->Tie("atmosphere/psiw-rad", this, &FGAtmosphere::GetWindPsi);
 542   PropertyManager->Tie("atmosphere/delta-T", this, &FGAtmosphere::GetDeltaT, &FGAtmosphere::SetDeltaT);
 543   PropertyManager->Tie("atmosphere/T-sl-dev-F", this, &FGAtmosphere::GetSLTempDev, &FGAtmosphere::SetSLTempDev);
 544   PropertyManager->Tie("atmosphere/density-altitude", this, &FGAtmosphere::GetDensityAltitude);
 545   PropertyManager->Tie("atmosphere/p-turb-rad_sec", this,1, (PMF)&FGAtmosphere::GetTurbPQR);
 546   PropertyManager->Tie("atmosphere/q-turb-rad_sec", this,2, (PMF)&FGAtmosphere::GetTurbPQR);
 547   PropertyManager->Tie("atmosphere/r-turb-rad_sec", this,3, (PMF)&FGAtmosphere::GetTurbPQR);
 548   PropertyManager->Tie("atmosphere/turb-rate", this, &FGAtmosphere::GetTurbRate, &FGAtmosphere::SetTurbRate);
 549   PropertyManager->Tie("atmosphere/turb-gain", this, &FGAtmosphere::GetTurbGain, &FGAtmosphere::SetTurbGain);
 550   PropertyManager->Tie("atmosphere/turb-rhythmicity", this, &FGAtmosphere::GetRhythmicity,
 551                                                             &FGAtmosphere::SetRhythmicity);
 552   PropertyManager->Tie("atmosphere/gust-north-fps", this,1, (PMF)&FGAtmosphere::GetGustNED,
 553                                                           (PMFd)&FGAtmosphere::SetGustNED);
 554   PropertyManager->Tie("atmosphere/gust-east-fps",  this,2, (PMF)&FGAtmosphere::GetGustNED,
 555                                                           (PMFd)&FGAtmosphere::SetGustNED);
 556   PropertyManager->Tie("atmosphere/gust-down-fps",  this,3, (PMF)&FGAtmosphere::GetGustNED,
 557                                                           (PMFd)&FGAtmosphere::SetGustNED);
 558   PropertyManager->Tie("atmosphere/wind-from-cw", this, &FGAtmosphere::GetWindFromClockwise,
 559                                                         &FGAtmosphere::SetWindFromClockwise);
 560 }
 561
 562 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 563 //    The bitmasked value choices are as follows:
 564 //    unset: In this case (the default) JSBSim would only print
 565 //       out the normally expected messages, essentially echoing
 566 //       the config files as they are read. If the environment
 567 //       variable is not set, debug_lvl is set to 1 internally
 568 //    0: This requests JSBSim not to output any messages
 569 //       whatsoever.
 570 //    1: This value explicity requests the normal JSBSim
 571 //       startup messages
 572 //    2: This value asks for a message to be printed out when
 573 //       a class is instantiated
 574 //    4: When this value is set, a message is displayed when a
 575 //       FGModel object executes its Run() method
 576 //    8: When this value is set, various runtime state variables
 577 //       are printed out periodically
 578 //    16: When set various parameters are sanity checked and
 579 //       a message is printed out when they go out of bounds
 580
 581 void FGAtmosphere::Debug(int from)
 582 {
 583   if (debug_lvl <= 0) return;
 584
 585   if (debug_lvl & 1) { // Standard console startup message output
 586     if (from == 0) { // Constructor
 587     }
 588   }
 589   if (debug_lvl & 2 ) { // Instantiation/Destruction notification
 590     if (from == 0) cout << "Instantiated: FGAtmosphere" << endl;
 591     if (from == 1) cout << "Destroyed:    FGAtmosphere" << endl;
 592   }
 593   if (debug_lvl & 4 ) { // Run() method entry print for FGModel-derived objects
 594   }
 595   if (debug_lvl & 8 ) { // Runtime state variables
 596   }
 597   if (debug_lvl & 16) { // Sanity checking
 598   }
 599   if (debug_lvl & 128) { // Turbulence
 600     if (first_pass && from == 2) {
 601       first_pass = false;
 602       cout << "vTurbulence(X), vTurbulence(Y), vTurbulence(Z), "
 603            << "vTurbulenceGrad(X), vTurbulenceGrad(Y), vTurbulenceGrad(Z), "
 604            << "vDirection(X), vDirection(Y), vDirection(Z), "
 605            << "Magnitude, "
 606            << "vTurbPQR(P), vTurbPQR(Q), vTurbPQR(R), " << endl;
 607     }
 608     if (from == 2) {
 609       cout << vTurbulence << ", " << vTurbulenceGrad << ", " << vDirection << ", " << Magnitude << ", " << vTurbPQR << endl;
 610     }
 611   }
 612   if (debug_lvl & 64) {
 613     if (from == 0) { // Constructor
 614       cout << IdSrc << endl;
 615       cout << IdHdr << endl;
 616     }
 617   }
 618 }
 619
 620 } // namespace JSBSim