1 /*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
3 Module: FGAtmosphere.cpp
5 Implementation of 1959 Standard Atmosphere added by Tony Peden
7 Purpose: Models the atmosphere
10 ------------- Copyright (C) 1999 Jon S. Berndt (jon@jsbsim.org) -------------
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
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
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.
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.
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.
35 --------------------------------------------------------------------------------
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
46 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
48 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
50 #include "FGAtmosphere.h"
52 #include "FGFDMExec.h"
53 #include "FGAircraft.h"
54 #include "FGPropagate.h"
55 #include "FGInertial.h"
56 #include "input_output/FGPropertyManager.h"
64 static const char *IdSrc = "$Id$";
65 static const char *IdHdr = ID_ATMOSPHERE;
67 /*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
69 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
71 FGAtmosphere::FGAtmosphere(FGFDMExec* fdmex) : FGModel(fdmex)
73 Name = "FGAtmosphere";
84 htab[7]=278385.0; //ft.
86 MagnitudedAccelDt = MagnitudeAccel = Magnitude = 0.0;
87 // SetTurbType( ttCulp );
88 SetTurbType( ttNone );
92 spike = target_time = strength = 0.0;
93 wind_from_clockwise = 0.0;
94 SutherlandConstant = 198.72; // deg Rankine
95 Beta = 2.269690E-08; // slug/(sec ft R^0.5)
97 T_dev_sl = T_dev = delta_T = 0.0;
98 StandardTempOnly = false;
100 vGustNED.InitMatrix();
101 vTurbulenceNED.InitMatrix();
107 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
109 FGAtmosphere::~FGAtmosphere()
114 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
116 bool FGAtmosphere::InitModel(void)
118 if (!FGModel::InitModel()) return false;
120 UseInternal(); // this is the default
123 StdSLtemperature = SLtemperature = 518.67;
124 StdSLpressure = SLpressure = 2116.22;
125 StdSLdensity = SLdensity = 0.00237767;
126 StdSLsoundspeed = SLsoundspeed = sqrt(SHRatio*Reng*StdSLtemperature);
127 rSLtemperature = 1.0/StdSLtemperature;
128 rSLpressure = 1.0/StdSLpressure;
129 rSLdensity = 1.0/StdSLdensity;
130 rSLsoundspeed = 1.0/StdSLsoundspeed;
135 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
137 bool FGAtmosphere::Run(void)
139 if (FGModel::Run()) return true;
140 if (FDMExec->Holding()) return false;
143 h = Propagate->GetAltitudeASL();
156 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
160 void FGAtmosphere::Calculate(double altitude)
162 double slope, reftemp, refpress;
165 if (altitude < htab[lastIndex]) {
171 while (htab[i] > altitude) i--;
173 } else if (altitude > htab[lastIndex+1]) {
174 if (altitude >= htab[7]) {
179 while (htab[i+1] < altitude) i++;
185 slope = -0.00356616; // R/ft.
186 reftemp = 518.67; // in degrees Rankine, 288.15 Kelvin
187 refpress = 2116.22; // psf
188 //refdens = 0.00237767; // slugs/cubic ft.
190 case 1: // 36089 ft. or 11 km
192 reftemp = 389.97; // in degrees Rankine, 216.65 Kelvin
194 //refdens = 0.000706032;
196 case 2: // 65616 ft. or 20 km
198 reftemp = 389.97; // in degrees Rankine, 216.65 Kelvin
200 //refdens = 0.000171306;
202 case 3: // 104986 ft. or 32 km
204 reftemp = 411.57; // in degrees Rankine, 228.65 Kelvin
206 //refdens = 1.18422e-05;
208 case 4: // 154199 ft. 47 km
210 reftemp = 487.17; // in degrees Rankine, 270.65 Kelvin
212 //refdens = 4.00585e-7;
214 case 5: // 167322 ft. or 51 km
215 slope = -0.001536192;
216 reftemp = 487.17; // in degrees Rankine, 270.65 Kelvin
218 //refdens = 8.17102e-7;
220 case 6: // 232940 ft. or 71 km
222 reftemp = 386.368; // in degrees Rankine, 214.649 Kelvin
224 //refdens = 8.77702e-9;
226 case 7: // 278385 ft. or 84.8520 km
228 reftemp = 336.5; // in degrees Rankine, 186.94 Kelvin
230 //refdens = 2.19541e-10;
232 default: // sea level
233 slope = -0.00356616; // R/ft.
234 reftemp = 518.67; // in degrees Rankine, 288.15 Kelvin
235 refpress = 2116.22; // psf
236 //refdens = 0.00237767; // slugs/cubic ft.
241 // If delta_T is set, then that is our temperature deviation at any altitude.
242 // If not, then we'll estimate a deviation based on the sea level deviation (if set).
244 if(!StandardTempOnly) {
246 if (delta_T != 0.0) {
249 if ((altitude < 36089.239) && (T_dev_sl != 0.0)) {
250 T_dev = T_dev_sl * ( 1.0 - (altitude/36089.239));
257 intTemperature = reftemp;
258 intPressure = refpress*exp(-Inertial->SLgravity()/(reftemp*Reng)*(altitude-htab[i]));
259 intDensity = intPressure/(Reng*intTemperature);
261 intTemperature = reftemp+slope*(altitude-htab[i]);
262 intPressure = refpress*pow(intTemperature/reftemp,-Inertial->SLgravity()/(slope*Reng));
263 intDensity = intPressure/(Reng*intTemperature);
269 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
270 // Calculate parameters derived from T, P and rho
271 // Sum gust and turbulence values in NED frame into the wind vector.
273 void FGAtmosphere::CalculateDerived(void)
275 T_dev = (*temperature) - GetTemperature(h);
276 density_altitude = h + T_dev * 66.7;
278 if (turbType != ttNone) Turbulence();
280 vTotalWindNED = vWindNED + vGustNED + vTurbulenceNED;
282 // psiw (Wind heading) is the direction the wind is blowing towards
283 if (vWindNED(eX) != 0.0) psiw = atan2( vWindNED(eY), vWindNED(eX) );
284 if (psiw < 0) psiw += 2*M_PI;
286 soundspeed = sqrt(SHRatio*Reng*(*temperature));
288 intViscosity = Beta * pow(intTemperature, 1.5) / (SutherlandConstant + intTemperature);
289 intKinematicViscosity = intViscosity / intDensity;
293 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
294 // Get the standard atmospheric properties at a specified altitude
296 void FGAtmosphere::GetStdAtmosphere(double altitude) {
297 StandardTempOnly = true;
299 StandardTempOnly = false;
300 atmosphere.Temperature = intTemperature;
301 atmosphere.Pressure = intPressure;
302 atmosphere.Density = intDensity;
304 // Reset the internal atmospheric state
308 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
309 // Get the standard pressure at a specified altitude
311 double FGAtmosphere::GetPressure(double altitude) {
312 GetStdAtmosphere(altitude);
313 return atmosphere.Pressure;
316 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
317 // Get the standard temperature at a specified altitude
319 double FGAtmosphere::GetTemperature(double altitude) {
320 GetStdAtmosphere(altitude);
321 return atmosphere.Temperature;
324 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
325 // Get the standard density at a specified altitude
327 double FGAtmosphere::GetDensity(double altitude) {
328 GetStdAtmosphere(altitude);
329 return atmosphere.Density;
333 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
334 // square a value, but preserve the original sign
336 static inline double square_signed (double value)
339 return value * value * -1;
341 return value * value;
344 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
346 // psi is the angle that the wind is blowing *towards*
348 void FGAtmosphere::SetWindspeed(double speed)
350 if (vWindNED.Magnitude() == 0.0) {
352 vWindNED(eNorth) = speed;
354 vWindNED(eNorth) = speed * cos(psiw);
355 vWindNED(eEast) = speed * sin(psiw);
356 vWindNED(eDown) = 0.0;
360 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
362 double FGAtmosphere::GetWindspeed(void) const
364 return vWindNED.Magnitude();
367 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
369 // psi is the angle that the wind is blowing *towards*
371 void FGAtmosphere::SetWindPsi(double dir)
373 double mag = GetWindspeed();
378 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
380 void FGAtmosphere::Turbulence(void)
382 double DeltaT = rate*State->Getdt();
386 // TurbGain = TurbGain * TurbGain * 100.0; // what is this!?
388 vDirectiondAccelDt(eX) = 1 - 2.0*(double(rand())/double(RAND_MAX));
389 vDirectiondAccelDt(eY) = 1 - 2.0*(double(rand())/double(RAND_MAX));
390 vDirectiondAccelDt(eZ) = 1 - 2.0*(double(rand())/double(RAND_MAX));
392 MagnitudedAccelDt = 1 - 2.0*(double(rand())/double(RAND_MAX)) - Magnitude;
393 // Scale the magnitude so that it moves
394 // away from the peaks
395 MagnitudedAccelDt = ((MagnitudedAccelDt - Magnitude) /
396 (1 + fabs(Magnitude)));
397 MagnitudeAccel += MagnitudedAccelDt*TurbRate*DeltaT;
398 Magnitude += MagnitudeAccel*DeltaT;
399 Magnitude = fabs(Magnitude);
401 vDirectiondAccelDt.Normalize();
403 // deemphasise non-vertical forces
404 vDirectiondAccelDt(eX) = square_signed(vDirectiondAccelDt(eX));
405 vDirectiondAccelDt(eY) = square_signed(vDirectiondAccelDt(eY));
407 vDirectionAccel += vDirectiondAccelDt*TurbRate*DeltaT;
408 vDirectionAccel.Normalize();
409 vDirection += vDirectionAccel*DeltaT;
411 vDirection.Normalize();
413 // Diminish turbulence within three wingspans
415 vTurbulenceNED = TurbGain * Magnitude * vDirection;
416 double HOverBMAC = Auxiliary->GetHOverBMAC();
418 vTurbulenceNED *= (HOverBMAC / 3.0) * (HOverBMAC / 3.0);
420 // I don't believe these next two statements calculate the proper gradient over
421 // the aircraft body. One reason is because this has no relationship with the
422 // orientation or velocity of the aircraft, which it must have. What is vTurbulenceGrad
423 // supposed to represent? And the direction and magnitude of the turbulence can change,
424 // so both accelerations need to be accounted for, no?
426 // Need to determine the turbulence change in body axes between two time points.
428 vTurbulenceGrad = TurbGain*MagnitudeAccel * vDirection;
429 vBodyTurbGrad = Propagate->GetTl2b()*vTurbulenceGrad;
431 if (Aircraft->GetWingSpan() > 0) {
432 vTurbPQR(eP) = vBodyTurbGrad(eY)/Aircraft->GetWingSpan();
434 vTurbPQR(eP) = vBodyTurbGrad(eY)/30.0;
436 // if (Aircraft->GetHTailArm() != 0.0)
437 // vTurbPQR(eQ) = vBodyTurbGrad(eZ)/Aircraft->GetHTailArm();
439 // vTurbPQR(eQ) = vBodyTurbGrad(eZ)/10.0;
441 if (Aircraft->GetVTailArm() > 0)
442 vTurbPQR(eR) = vBodyTurbGrad(eX)/Aircraft->GetVTailArm();
444 vTurbPQR(eR) = vBodyTurbGrad(eX)/10.0;
446 // Clear the horizontal forces
447 // actually felt by the plane, now
448 // that we've used them to calculate
451 // vTurbulenceNED(eX) = 0.0;
452 // vTurbulenceNED(eY) = 0.0;
456 case ttBerndt: { // This is very experimental and incomplete at the moment.
458 vDirectiondAccelDt(eX) = GaussianRandomNumber();
459 vDirectiondAccelDt(eY) = GaussianRandomNumber();
460 vDirectiondAccelDt(eZ) = GaussianRandomNumber();
462 MagnitudedAccelDt = GaussianRandomNumber();
463 MagnitudeAccel += MagnitudedAccelDt * DeltaT;
464 Magnitude += MagnitudeAccel * DeltaT;
466 Magnitude += GaussianRandomNumber() * DeltaT;
468 vDirectiondAccelDt.Normalize();
469 vDirectionAccel += TurbRate * vDirectiondAccelDt * DeltaT;
470 vDirectionAccel.Normalize();
471 vDirection += vDirectionAccel*DeltaT;
473 // Diminish z-vector within two wingspans of the ground
474 double HOverBMAC = Auxiliary->GetHOverBMAC();
475 if (HOverBMAC < 2.0) vDirection(eZ) *= HOverBMAC / 2.0;
477 vDirection.Normalize();
479 vTurbulenceNED = TurbGain*Magnitude * vDirection;
480 vTurbulenceGrad = TurbGain*MagnitudeAccel * vDirection;
482 vBodyTurbGrad = Propagate->GetTl2b() * vTurbulenceGrad;
483 vTurbPQR(eP) = vBodyTurbGrad(eY) / Aircraft->GetWingSpan();
484 if (Aircraft->GetHTailArm() > 0)
485 vTurbPQR(eQ) = vBodyTurbGrad(eZ) / Aircraft->GetHTailArm();
487 vTurbPQR(eQ) = vBodyTurbGrad(eZ) / 10.0;
489 if (Aircraft->GetVTailArm() > 0)
490 vTurbPQR(eR) = vBodyTurbGrad(eX) / Aircraft->GetVTailArm();
492 vTurbPQR(eR) = vBodyTurbGrad(eX)/10.0;
498 vTurbPQR(eP) = wind_from_clockwise;
499 if (TurbGain == 0.0) return;
501 // keep the inputs within allowable limts for this model
502 if (TurbGain < 0.0) TurbGain = 0.0;
503 if (TurbGain > 1.0) TurbGain = 1.0;
504 if (TurbRate < 0.0) TurbRate = 0.0;
505 if (TurbRate > 30.0) TurbRate = 30.0;
506 if (Rhythmicity < 0.0) Rhythmicity = 0.0;
507 if (Rhythmicity > 1.0) Rhythmicity = 1.0;
509 // generate a sine wave corresponding to turbulence rate in hertz
510 double time = FDMExec->GetSimTime();
511 double sinewave = sin( time * TurbRate * 6.283185307 );
514 if (target_time == 0.0) {
515 strength = random = 1 - 2.0*(double(rand())/double(RAND_MAX));
516 target_time = time + 0.71 + (random * 0.5);
518 if (time > target_time) {
523 // max vertical wind speed in fps, corresponds to TurbGain = 1.0
526 vTurbulenceNED(1) = vTurbulenceNED(2) = vTurbulenceNED(3) = 0.0;
527 double delta = strength * max_vs * TurbGain * (1-Rhythmicity) * spike;
529 // Vertical component of turbulence.
530 vTurbulenceNED(3) = sinewave * max_vs * TurbGain * Rhythmicity;
531 vTurbulenceNED(3)+= delta;
532 double HOverBMAC = Auxiliary->GetHOverBMAC();
534 vTurbulenceNED(3) *= HOverBMAC * 0.3333;
536 // Yaw component of turbulence.
537 vTurbulenceNED(1) = sin( delta * 3.0 );
538 vTurbulenceNED(2) = cos( delta * 3.0 );
540 // Roll component of turbulence. Clockwise vortex causes left roll.
541 vTurbPQR(eP) += delta * 0.04;
551 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
553 void FGAtmosphere::UseExternal(void)
555 temperature=&exTemperature;
556 pressure=&exPressure;
561 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
563 void FGAtmosphere::UseInternal(void)
565 temperature=&intTemperature;
566 pressure=&intPressure;
571 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
573 void FGAtmosphere::bind(void)
575 typedef double (FGAtmosphere::*PMF)(int) const;
576 typedef double (FGAtmosphere::*PMFv)(void) const;
577 typedef int (FGAtmosphere::*PMFt)(void) const;
578 typedef void (FGAtmosphere::*PMFd)(int,double);
579 typedef void (FGAtmosphere::*PMFi)(int);
580 PropertyManager->Tie("atmosphere/T-R", this, (PMFv)&FGAtmosphere::GetTemperature);
581 PropertyManager->Tie("atmosphere/rho-slugs_ft3", this, (PMFv)&FGAtmosphere::GetDensity);
582 PropertyManager->Tie("atmosphere/P-psf", this, (PMFv)&FGAtmosphere::GetPressure);
583 PropertyManager->Tie("atmosphere/a-fps", this, &FGAtmosphere::GetSoundSpeed);
584 PropertyManager->Tie("atmosphere/T-sl-R", this, &FGAtmosphere::GetTemperatureSL);
585 PropertyManager->Tie("atmosphere/rho-sl-slugs_ft3", this, &FGAtmosphere::GetDensitySL);
586 PropertyManager->Tie("atmosphere/P-sl-psf", this, &FGAtmosphere::GetPressureSL);
587 PropertyManager->Tie("atmosphere/a-sl-fps", this, &FGAtmosphere::GetSoundSpeedSL);
588 PropertyManager->Tie("atmosphere/theta", this, &FGAtmosphere::GetTemperatureRatio);
589 PropertyManager->Tie("atmosphere/sigma", this, &FGAtmosphere::GetDensityRatio);
590 PropertyManager->Tie("atmosphere/delta", this, &FGAtmosphere::GetPressureRatio);
591 PropertyManager->Tie("atmosphere/a-ratio", this, &FGAtmosphere::GetSoundSpeedRatio);
592 PropertyManager->Tie("atmosphere/psiw-rad", this, &FGAtmosphere::GetWindPsi, &FGAtmosphere::SetWindPsi);
593 PropertyManager->Tie("atmosphere/delta-T", this, &FGAtmosphere::GetDeltaT, &FGAtmosphere::SetDeltaT);
594 PropertyManager->Tie("atmosphere/T-sl-dev-F", this, &FGAtmosphere::GetSLTempDev, &FGAtmosphere::SetSLTempDev);
595 PropertyManager->Tie("atmosphere/density-altitude", this, &FGAtmosphere::GetDensityAltitude);
597 PropertyManager->Tie("atmosphere/wind-north-fps", this, eNorth, (PMF)&FGAtmosphere::GetWindNED,
598 (PMFd)&FGAtmosphere::SetWindNED);
599 PropertyManager->Tie("atmosphere/wind-east-fps", this, eEast, (PMF)&FGAtmosphere::GetWindNED,
600 (PMFd)&FGAtmosphere::SetWindNED);
601 PropertyManager->Tie("atmosphere/wind-down-fps", this, eDown, (PMF)&FGAtmosphere::GetWindNED,
602 (PMFd)&FGAtmosphere::SetWindNED);
603 PropertyManager->Tie("atmosphere/wind-mag-fps", this, &FGAtmosphere::GetWindspeed,
604 &FGAtmosphere::SetWindspeed);
605 PropertyManager->Tie("atmosphere/total-wind-north-fps", this, eNorth, (PMF)&FGAtmosphere::GetTotalWindNED);
606 PropertyManager->Tie("atmosphere/total-wind-east-fps", this, eEast, (PMF)&FGAtmosphere::GetTotalWindNED);
607 PropertyManager->Tie("atmosphere/total-wind-down-fps", this, eDown, (PMF)&FGAtmosphere::GetTotalWindNED);
609 PropertyManager->Tie("atmosphere/gust-north-fps", this, eNorth, (PMF)&FGAtmosphere::GetGustNED,
610 (PMFd)&FGAtmosphere::SetGustNED);
611 PropertyManager->Tie("atmosphere/gust-east-fps", this, eEast, (PMF)&FGAtmosphere::GetGustNED,
612 (PMFd)&FGAtmosphere::SetGustNED);
613 PropertyManager->Tie("atmosphere/gust-down-fps", this, eDown, (PMF)&FGAtmosphere::GetGustNED,
614 (PMFd)&FGAtmosphere::SetGustNED);
616 PropertyManager->Tie("atmosphere/turb-north-fps", this, eNorth, (PMF)&FGAtmosphere::GetTurbNED,
617 (PMFd)&FGAtmosphere::SetTurbNED);
618 PropertyManager->Tie("atmosphere/turb-east-fps", this, eEast, (PMF)&FGAtmosphere::GetTurbNED,
619 (PMFd)&FGAtmosphere::SetTurbNED);
620 PropertyManager->Tie("atmosphere/turb-down-fps", this, eDown, (PMF)&FGAtmosphere::GetTurbNED,
621 (PMFd)&FGAtmosphere::SetTurbNED);
623 PropertyManager->Tie("atmosphere/p-turb-rad_sec", this,1, (PMF)&FGAtmosphere::GetTurbPQR);
624 PropertyManager->Tie("atmosphere/q-turb-rad_sec", this,2, (PMF)&FGAtmosphere::GetTurbPQR);
625 PropertyManager->Tie("atmosphere/r-turb-rad_sec", this,3, (PMF)&FGAtmosphere::GetTurbPQR);
626 PropertyManager->Tie("atmosphere/turb-type", this, (PMFt)&FGAtmosphere::GetTurbType, (PMFi)&FGAtmosphere::SetTurbType);
627 PropertyManager->Tie("atmosphere/turb-rate", this, &FGAtmosphere::GetTurbRate, &FGAtmosphere::SetTurbRate);
628 PropertyManager->Tie("atmosphere/turb-gain", this, &FGAtmosphere::GetTurbGain, &FGAtmosphere::SetTurbGain);
629 PropertyManager->Tie("atmosphere/turb-rhythmicity", this, &FGAtmosphere::GetRhythmicity,
630 &FGAtmosphere::SetRhythmicity);
633 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
634 // The bitmasked value choices are as follows:
635 // unset: In this case (the default) JSBSim would only print
636 // out the normally expected messages, essentially echoing
637 // the config files as they are read. If the environment
638 // variable is not set, debug_lvl is set to 1 internally
639 // 0: This requests JSBSim not to output any messages
641 // 1: This value explicity requests the normal JSBSim
643 // 2: This value asks for a message to be printed out when
644 // a class is instantiated
645 // 4: When this value is set, a message is displayed when a
646 // FGModel object executes its Run() method
647 // 8: When this value is set, various runtime state variables
648 // are printed out periodically
649 // 16: When set various parameters are sanity checked and
650 // a message is printed out when they go out of bounds
652 void FGAtmosphere::Debug(int from)
654 if (debug_lvl <= 0) return;
656 if (debug_lvl & 1) { // Standard console startup message output
657 if (from == 0) { // Constructor
660 if (debug_lvl & 2 ) { // Instantiation/Destruction notification
661 if (from == 0) cout << "Instantiated: FGAtmosphere" << endl;
662 if (from == 1) cout << "Destroyed: FGAtmosphere" << endl;
664 if (debug_lvl & 4 ) { // Run() method entry print for FGModel-derived objects
666 if (debug_lvl & 8 ) { // Runtime state variables
668 if (debug_lvl & 16) { // Sanity checking
670 if (debug_lvl & 128) { // Turbulence
671 if (first_pass && from == 2) {
673 cout << "vTurbulenceNED(X), vTurbulenceNED(Y), vTurbulenceNED(Z), "
674 << "vTurbulenceGrad(X), vTurbulenceGrad(Y), vTurbulenceGrad(Z), "
675 << "vDirection(X), vDirection(Y), vDirection(Z), "
677 << "vTurbPQR(P), vTurbPQR(Q), vTurbPQR(R), " << endl;
680 cout << vTurbulenceNED << ", " << vTurbulenceGrad << ", " << vDirection << ", " << Magnitude << ", " << vTurbPQR << endl;
683 if (debug_lvl & 64) {
684 if (from == 0) { // Constructor
685 cout << IdSrc << endl;
686 cout << IdHdr << endl;
691 } // namespace JSBSim