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 FGAtmosphere::FGAtmosphere(FGFDMExec* fdmex) : FGModel(fdmex)
  68 {
  69   Name = "FGAtmosphere";
  70   lastIndex = 0;
  71   h = 0.0;
  72   psiw = 0.0;
  73   htab[0]=0;
  74   htab[1]=36089.239;
  75   htab[2]=65616.798;
  76   htab[3]=104986.878;
  77   htab[4]=154199.475;
  78   htab[5]=170603.675;
  79   htab[6]=200131.234;
  80   htab[7]=259186.352; //ft.
  81
  82   MagnitudedAccelDt = MagnitudeAccel = Magnitude = 0.0;
  83   SetTurbType( ttCulp );
  84   TurbGain = 0.0;
  85   TurbRate = 1.7;
  86   Rhythmicity = 0.1;
  87   spike = target_time = strength = 0.0;
  88   wind_from_clockwise = 0.0;
  89
  90   T_dev_sl = T_dev = delta_T = 0.0;
  91   StandardTempOnly = false;
  92   first_pass = true;
  93   vGustNED.InitMatrix();
  94   vTurbulenceNED.InitMatrix();
  95
  96   bind();
  97   Debug(0);
  98 }
  99
 100 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 101
 102 FGAtmosphere::~FGAtmosphere()
 103 {
 104   Debug(1);
 105 }
 106
 107 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 108
 109 bool FGAtmosphere::InitModel(void)
 110 {
 111   if (!FGModel::InitModel()) return false;
 112
 113   UseInternal();  // this is the default
 114
 115   Calculate(h);
 116   StdSLtemperature = SLtemperature = 518.67;
 117   StdSLpressure    = SLpressure = 2116.22;
 118   StdSLdensity     = SLdensity = 0.00237767;
 119   StdSLsoundspeed  = SLsoundspeed = sqrt(SHRatio*Reng*StdSLtemperature);
 120   rSLtemperature = 1.0/StdSLtemperature;
 121   rSLpressure    = 1.0/StdSLpressure;
 122   rSLdensity     = 1.0/StdSLdensity;
 123   rSLsoundspeed  = 1.0/StdSLsoundspeed;
 124
 125   return true;
 126 }
 127
 128 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 129
 130 bool FGAtmosphere::Run(void)
 131 {
 132   if (FGModel::Run()) return true;
 133   if (FDMExec->Holding()) return false;
 134
 135   T_dev = 0.0;
 136   h = Propagate->Geth();
 137
 138   if (!useExternal) {
 139     Calculate(h);
 140     CalculateDerived();
 141   } else {
 142     CalculateDerived();
 143   }
 144
 145   Debug(2);
 146   return false;
 147 }
 148
 149 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 150 //
 151 // See reference 1
 152
 153 void FGAtmosphere::Calculate(double altitude)
 154 {
 155   double slope, reftemp, refpress;
 156   int i = lastIndex;
 157
 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 // Sum gust and turbulence values in NED frame into the wind vector.
 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) Turbulence();
 267
 268   vTotalWindNED = vWindNED + vGustNED + vTurbulenceNED;
 269
 270   if (vWindNED(eX) != 0.0) psiw = atan2( vWindNED(eY), vWindNED(eX) );
 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::SetWindspeed(double speed)
 331 {
 332   if (vWindNED.Magnitude() == 0.0) {
 333     psiw = 0.0;
 334     vWindNED(eNorth) = speed;
 335   } else {
 336     vWindNED(eNorth) = speed * cos(psiw);
 337     vWindNED(eEast) = speed * sin(psiw);
 338     vWindNED(eDown) = 0.0;
 339   }
 340 }
 341
 342 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 343
 344 double FGAtmosphere::GetWindspeed(void) const
 345 {
 346   return vWindNED.Magnitude();
 347 }
 348
 349 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 350
 351 void FGAtmosphere::SetWindPsi(double dir)
 352 {
 353   double mag = GetWindspeed();
 354   psiw = dir;
 355   SetWindspeed(mag);
 356 }
 357
 358 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 359
 360 void FGAtmosphere::Turbulence(void)
 361 {
 362   switch (turbType) {
 363   case ttStandard: {
 364     TurbGain = TurbGain * TurbGain * 100.0;
 365
 366     vDirectiondAccelDt(eX) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 367     vDirectiondAccelDt(eY) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 368     vDirectiondAccelDt(eZ) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 369
 370     MagnitudedAccelDt = 1 - 2.0*(double(rand())/double(RAND_MAX)) - Magnitude;
 371                                 // Scale the magnitude so that it moves
 372                                 // away from the peaks
 373     MagnitudedAccelDt = ((MagnitudedAccelDt - Magnitude) /
 374                          (1 + fabs(Magnitude)));
 375     MagnitudeAccel    += MagnitudedAccelDt*rate*TurbRate*State->Getdt();
 376     Magnitude         += MagnitudeAccel*rate*State->Getdt();
 377     Magnitude          = fabs(Magnitude);
 378
 379     vDirectiondAccelDt.Normalize();
 380
 381                                 // deemphasise non-vertical forces
 382     vDirectiondAccelDt(eX) = square_signed(vDirectiondAccelDt(eX));
 383     vDirectiondAccelDt(eY) = square_signed(vDirectiondAccelDt(eY));
 384
 385     vDirectionAccel += vDirectiondAccelDt*rate*TurbRate*State->Getdt();
 386     vDirectionAccel.Normalize();
 387     vDirection      += vDirectionAccel*rate*State->Getdt();
 388
 389     vDirection.Normalize();
 390
 391                                 // Diminish turbulence within three wingspans
 392                                 // of the ground
 393     vTurbulenceNED = TurbGain * Magnitude * vDirection;
 394     double HOverBMAC = Auxiliary->GetHOverBMAC();
 395     if (HOverBMAC < 3.0)
 396         vTurbulenceNED *= (HOverBMAC / 3.0) * (HOverBMAC / 3.0);
 397
 398     // I don't believe these next two statements calculate the proper gradient over
 399     // the aircraft body. One reason is because this has no relationship with the
 400     // orientation or velocity of the aircraft, which it must have. What is vTurbulenceGrad
 401     // supposed to represent? And the direction and magnitude of the turbulence can change,
 402     // so both accelerations need to be accounted for, no?
 403
 404     // Need to determine the turbulence change in body axes between two time points.
 405
 406     vTurbulenceGrad = TurbGain*MagnitudeAccel * vDirection;
 407     vBodyTurbGrad = Propagate->GetTl2b()*vTurbulenceGrad;
 408
 409     if (Aircraft->GetWingSpan() > 0) {
 410       vTurbPQR(eP) = vBodyTurbGrad(eY)/Aircraft->GetWingSpan();
 411     } else {
 412       vTurbPQR(eP) = vBodyTurbGrad(eY)/30.0;
 413     }
 414 //     if (Aircraft->GetHTailArm() != 0.0)
 415 //       vTurbPQR(eQ) = vBodyTurbGrad(eZ)/Aircraft->GetHTailArm();
 416 //     else
 417 //       vTurbPQR(eQ) = vBodyTurbGrad(eZ)/10.0;
 418
 419     if (Aircraft->GetVTailArm() > 0)
 420       vTurbPQR(eR) = vBodyTurbGrad(eX)/Aircraft->GetVTailArm();
 421     else
 422       vTurbPQR(eR) = vBodyTurbGrad(eX)/10.0;
 423
 424                                 // Clear the horizontal forces
 425                                 // actually felt by the plane, now
 426                                 // that we've used them to calculate
 427                                 // moments.
 428                                 // Why? (JSB)
 429 //    vTurbulenceNED(eX) = 0.0;
 430 //    vTurbulenceNED(eY) = 0.0;
 431
 432     break;
 433   }
 434   case ttBerndt: { // This is very experimental and incomplete at the moment.
 435
 436     TurbGain = TurbGain * TurbGain * 100.0;
 437
 438     vDirectiondAccelDt(eX) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 439     vDirectiondAccelDt(eY) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 440     vDirectiondAccelDt(eZ) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 441
 442
 443     MagnitudedAccelDt = 1 - 2.0*(double(rand())/double(RAND_MAX)) - Magnitude;
 444     MagnitudeAccel    += MagnitudedAccelDt*rate*State->Getdt();
 445     Magnitude         += MagnitudeAccel*rate*State->Getdt();
 446
 447     vDirectiondAccelDt.Normalize();
 448     vDirectionAccel += vDirectiondAccelDt*rate*State->Getdt();
 449     vDirectionAccel.Normalize();
 450     vDirection      += vDirectionAccel*rate*State->Getdt();
 451
 452                                 // Diminish z-vector within two wingspans
 453                                 // of the ground
 454     double HOverBMAC = Auxiliary->GetHOverBMAC();
 455     if (HOverBMAC < 2.0)
 456         vDirection(eZ) *= HOverBMAC / 2.0;
 457
 458     vDirection.Normalize();
 459
 460     vTurbulenceNED = TurbGain*Magnitude * vDirection;
 461     vTurbulenceGrad = TurbGain*MagnitudeAccel * vDirection;
 462
 463     vBodyTurbGrad = Propagate->GetTl2b()*vTurbulenceGrad;
 464     vTurbPQR(eP) = vBodyTurbGrad(eY)/Aircraft->GetWingSpan();
 465     if (Aircraft->GetHTailArm() > 0)
 466       vTurbPQR(eQ) = vBodyTurbGrad(eZ)/Aircraft->GetHTailArm();
 467     else
 468       vTurbPQR(eQ) = vBodyTurbGrad(eZ)/10.0;
 469
 470     if (Aircraft->GetVTailArm() > 0)
 471       vTurbPQR(eR) = vBodyTurbGrad(eX)/Aircraft->GetVTailArm();
 472     else
 473       vTurbPQR(eR) = vBodyTurbGrad(eX)/10.0;
 474
 475     break;
 476   }
 477   case ttCulp: {
 478
 479     vTurbPQR(eP) = wind_from_clockwise;
 480     if (TurbGain == 0.0) return;
 481
 482     // keep the inputs within allowable limts for this model
 483     if (TurbGain < 0.0) TurbGain = 0.0;
 484     if (TurbGain > 1.0) TurbGain = 1.0;
 485     if (TurbRate < 0.0) TurbRate = 0.0;
 486     if (TurbRate > 30.0) TurbRate = 30.0;
 487     if (Rhythmicity < 0.0) Rhythmicity = 0.0;
 488     if (Rhythmicity > 1.0) Rhythmicity = 1.0;
 489
 490     // generate a sine wave corresponding to turbulence rate in hertz
 491     double time = FDMExec->GetSimTime();
 492     double sinewave = sin( time * TurbRate * 6.283185307 );
 493
 494     double random = 0.0;
 495     if (target_time == 0.0) {
 496       strength = random = 1 - 2.0*(double(rand())/double(RAND_MAX));
 497       target_time = time + 0.71 + (random * 0.5);
 498     }
 499     if (time > target_time) {
 500       spike = 1.0;
 501       target_time = 0.0;
 502     }
 503
 504     // max vertical wind speed in fps, corresponds to TurbGain = 1.0
 505     double max_vs = 40;
 506
 507     vTurbulenceNED(1) = vTurbulenceNED(2) = vTurbulenceNED(3) = 0.0;
 508     double delta = strength * max_vs * TurbGain * (1-Rhythmicity) * spike;
 509
 510     // Vertical component of turbulence.
 511     vTurbulenceNED(3) = sinewave * max_vs * TurbGain * Rhythmicity;
 512     vTurbulenceNED(3)+= delta;
 513     double HOverBMAC = Auxiliary->GetHOverBMAC();
 514     if (HOverBMAC < 3.0)
 515         vTurbulenceNED(3) *= HOverBMAC * 0.3333;
 516
 517     // Yaw component of turbulence.
 518     vTurbulenceNED(1) = sin( delta * 3.0 );
 519     vTurbulenceNED(2) = cos( delta * 3.0 );
 520
 521     // Roll component of turbulence. Clockwise vortex causes left roll.
 522     vTurbPQR(eP) += delta * 0.04;
 523
 524     spike = spike * 0.9;
 525     break;
 526   }
 527   default:
 528     break;
 529   }
 530 }
 531
 532 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 533
 534 void FGAtmosphere::UseExternal(void)
 535 {
 536   temperature=&exTemperature;
 537   pressure=&exPressure;
 538   density=&exDensity;
 539   useExternal=true;
 540 }
 541
 542 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 543
 544 void FGAtmosphere::UseInternal(void)
 545 {
 546   temperature=&intTemperature;
 547   pressure=&intPressure;
 548   density=&intDensity;
 549   useExternal=false;
 550 }
 551
 552 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 553
 554 void FGAtmosphere::bind(void)
 555 {
 556   typedef double (FGAtmosphere::*PMF)(int) const;
 557   typedef double (FGAtmosphere::*PMFv)(void) const;
 558   typedef void   (FGAtmosphere::*PMFd)(int,double);
 559   PropertyManager->Tie("atmosphere/T-R", this, (PMFv)&FGAtmosphere::GetTemperature);
 560   PropertyManager->Tie("atmosphere/rho-slugs_ft3", this, (PMFv)&FGAtmosphere::GetDensity);
 561   PropertyManager->Tie("atmosphere/P-psf", this, (PMFv)&FGAtmosphere::GetPressure);
 562   PropertyManager->Tie("atmosphere/a-fps", this, &FGAtmosphere::GetSoundSpeed);
 563   PropertyManager->Tie("atmosphere/T-sl-R", this, &FGAtmosphere::GetTemperatureSL);
 564   PropertyManager->Tie("atmosphere/rho-sl-slugs_ft3", this, &FGAtmosphere::GetDensitySL);
 565   PropertyManager->Tie("atmosphere/P-sl-psf", this, &FGAtmosphere::GetPressureSL);
 566   PropertyManager->Tie("atmosphere/a-sl-fps", this, &FGAtmosphere::GetSoundSpeedSL);
 567   PropertyManager->Tie("atmosphere/theta", this, &FGAtmosphere::GetTemperatureRatio);
 568   PropertyManager->Tie("atmosphere/sigma", this, &FGAtmosphere::GetDensityRatio);
 569   PropertyManager->Tie("atmosphere/delta", this, &FGAtmosphere::GetPressureRatio);
 570   PropertyManager->Tie("atmosphere/a-ratio", this, &FGAtmosphere::GetSoundSpeedRatio);
 571   PropertyManager->Tie("atmosphere/psiw-rad", this, &FGAtmosphere::GetWindPsi);
 572   PropertyManager->Tie("atmosphere/delta-T", this, &FGAtmosphere::GetDeltaT, &FGAtmosphere::SetDeltaT);
 573   PropertyManager->Tie("atmosphere/T-sl-dev-F", this, &FGAtmosphere::GetSLTempDev, &FGAtmosphere::SetSLTempDev);
 574   PropertyManager->Tie("atmosphere/density-altitude", this, &FGAtmosphere::GetDensityAltitude);
 575
 576   PropertyManager->Tie("atmosphere/wind-north-fps", this, eNorth, (PMF)&FGAtmosphere::GetWindNED,
 577                                                           (PMFd)&FGAtmosphere::SetWindNED);
 578   PropertyManager->Tie("atmosphere/wind-east-fps",  this, eEast, (PMF)&FGAtmosphere::GetWindNED,
 579                                                           (PMFd)&FGAtmosphere::SetWindNED);
 580   PropertyManager->Tie("atmosphere/wind-down-fps",  this, eDown, (PMF)&FGAtmosphere::GetWindNED,
 581                                                           (PMFd)&FGAtmosphere::SetWindNED);
 582   PropertyManager->Tie("atmosphere/wind-from-cw", this, &FGAtmosphere::GetWindFromClockwise,
 583                                                         &FGAtmosphere::SetWindFromClockwise);
 584   PropertyManager->Tie("atmosphere/wind-mag-fps", this, &FGAtmosphere::GetWindspeed,
 585                                                         &FGAtmosphere::SetWindspeed);
 586   PropertyManager->Tie("atmosphere/total-wind-north-fps", this, eNorth, (PMF)&FGAtmosphere::GetTotalWindNED);
 587   PropertyManager->Tie("atmosphere/total-wind-east-fps",  this, eEast,  (PMF)&FGAtmosphere::GetTotalWindNED);
 588   PropertyManager->Tie("atmosphere/total-wind-down-fps",  this, eDown,  (PMF)&FGAtmosphere::GetTotalWindNED);
 589
 590   PropertyManager->Tie("atmosphere/gust-north-fps", this, eNorth, (PMF)&FGAtmosphere::GetGustNED,
 591                                                           (PMFd)&FGAtmosphere::SetGustNED);
 592   PropertyManager->Tie("atmosphere/gust-east-fps",  this, eEast, (PMF)&FGAtmosphere::GetGustNED,
 593                                                           (PMFd)&FGAtmosphere::SetGustNED);
 594   PropertyManager->Tie("atmosphere/gust-down-fps",  this, eDown, (PMF)&FGAtmosphere::GetGustNED,
 595                                                           (PMFd)&FGAtmosphere::SetGustNED);
 596
 597   PropertyManager->Tie("atmosphere/p-turb-rad_sec", this,1, (PMF)&FGAtmosphere::GetTurbPQR);
 598   PropertyManager->Tie("atmosphere/q-turb-rad_sec", this,2, (PMF)&FGAtmosphere::GetTurbPQR);
 599   PropertyManager->Tie("atmosphere/r-turb-rad_sec", this,3, (PMF)&FGAtmosphere::GetTurbPQR);
 600   PropertyManager->Tie("atmosphere/turb-rate", this, &FGAtmosphere::GetTurbRate, &FGAtmosphere::SetTurbRate);
 601   PropertyManager->Tie("atmosphere/turb-gain", this, &FGAtmosphere::GetTurbGain, &FGAtmosphere::SetTurbGain);
 602   PropertyManager->Tie("atmosphere/turb-rhythmicity", this, &FGAtmosphere::GetRhythmicity,
 603                                                             &FGAtmosphere::SetRhythmicity);
 604 }
 605
 606 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 607 //    The bitmasked value choices are as follows:
 608 //    unset: In this case (the default) JSBSim would only print
 609 //       out the normally expected messages, essentially echoing
 610 //       the config files as they are read. If the environment
 611 //       variable is not set, debug_lvl is set to 1 internally
 612 //    0: This requests JSBSim not to output any messages
 613 //       whatsoever.
 614 //    1: This value explicity requests the normal JSBSim
 615 //       startup messages
 616 //    2: This value asks for a message to be printed out when
 617 //       a class is instantiated
 618 //    4: When this value is set, a message is displayed when a
 619 //       FGModel object executes its Run() method
 620 //    8: When this value is set, various runtime state variables
 621 //       are printed out periodically
 622 //    16: When set various parameters are sanity checked and
 623 //       a message is printed out when they go out of bounds
 624
 625 void FGAtmosphere::Debug(int from)
 626 {
 627   if (debug_lvl <= 0) return;
 628
 629   if (debug_lvl & 1) { // Standard console startup message output
 630     if (from == 0) { // Constructor
 631     }
 632   }
 633   if (debug_lvl & 2 ) { // Instantiation/Destruction notification
 634     if (from == 0) cout << "Instantiated: FGAtmosphere" << endl;
 635     if (from == 1) cout << "Destroyed:    FGAtmosphere" << endl;
 636   }
 637   if (debug_lvl & 4 ) { // Run() method entry print for FGModel-derived objects
 638   }
 639   if (debug_lvl & 8 ) { // Runtime state variables
 640   }
 641   if (debug_lvl & 16) { // Sanity checking
 642   }
 643   if (debug_lvl & 128) { // Turbulence
 644     if (first_pass && from == 2) {
 645       first_pass = false;
 646       cout << "vTurbulenceNED(X), vTurbulenceNED(Y), vTurbulenceNED(Z), "
 647            << "vTurbulenceGrad(X), vTurbulenceGrad(Y), vTurbulenceGrad(Z), "
 648            << "vDirection(X), vDirection(Y), vDirection(Z), "
 649            << "Magnitude, "
 650            << "vTurbPQR(P), vTurbPQR(Q), vTurbPQR(R), " << endl;
 651     }
 652     if (from == 2) {
 653       cout << vTurbulenceNED << ", " << vTurbulenceGrad << ", " << vDirection << ", " << Magnitude << ", " << vTurbPQR << endl;
 654     }
 655   }
 656   if (debug_lvl & 64) {
 657     if (from == 0) { // Constructor
 658       cout << IdSrc << endl;
 659       cout << IdHdr << endl;
 660     }
 661   }
 662 }
 663
 664 } // namespace JSBSim