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>
60 static const char *IdSrc = "$Id$";
61 static const char *IdHdr = ID_ATMOSPHERE;
63 /*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
65 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
67 FGAtmosphere::FGAtmosphere(FGFDMExec* fdmex) : FGModel(fdmex)
69 Name = "FGAtmosphere";
80 htab[7]=278385.0; //ft.
82 MagnitudedAccelDt = MagnitudeAccel = Magnitude = 0.0;
83 // SetTurbType( ttCulp );
84 SetTurbType( ttNone );
88 spike = target_time = strength = 0.0;
89 wind_from_clockwise = 0.0;
90 SutherlandConstant = 198.72; // deg Rankine
91 Beta = 2.269690E-08; // slug/(sec ft R^0.5)
93 T_dev_sl = T_dev = delta_T = 0.0;
94 StandardTempOnly = false;
96 vGustNED.InitMatrix();
97 vTurbulenceNED.InitMatrix();
103 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
105 FGAtmosphere::~FGAtmosphere()
110 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
112 bool FGAtmosphere::InitModel(void)
114 if (!FGModel::InitModel()) return false;
116 UseInternal(); // this is the default
119 StdSLtemperature = SLtemperature = 518.67;
120 StdSLpressure = SLpressure = 2116.22;
121 StdSLdensity = SLdensity = 0.00237767;
122 StdSLsoundspeed = SLsoundspeed = sqrt(SHRatio*Reng*StdSLtemperature);
123 rSLtemperature = 1.0/StdSLtemperature;
124 rSLpressure = 1.0/StdSLpressure;
125 rSLdensity = 1.0/StdSLdensity;
126 rSLsoundspeed = 1.0/StdSLsoundspeed;
131 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
133 bool FGAtmosphere::Run(void)
135 if (FGModel::Run()) return true;
136 if (FDMExec->Holding()) return false;
139 h = Propagate->GetAltitudeASL();
152 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
156 void FGAtmosphere::Calculate(double altitude)
158 double slope, reftemp, refpress;
161 if (altitude < htab[lastIndex]) {
167 while (htab[i] > altitude) i--;
169 } else if (altitude > htab[lastIndex+1]) {
170 if (altitude >= htab[7]) {
175 while (htab[i+1] < altitude) i++;
181 slope = -0.00356616; // R/ft.
182 reftemp = 518.67; // in degrees Rankine, 288.15 Kelvin
183 refpress = 2116.22; // psf
184 //refdens = 0.00237767; // slugs/cubic ft.
186 case 1: // 36089 ft. or 11 km
188 reftemp = 389.97; // in degrees Rankine, 216.65 Kelvin
190 //refdens = 0.000706032;
192 case 2: // 65616 ft. or 20 km
194 reftemp = 389.97; // in degrees Rankine, 216.65 Kelvin
196 //refdens = 0.000171306;
198 case 3: // 104986 ft. or 32 km
200 reftemp = 411.57; // in degrees Rankine, 228.65 Kelvin
202 //refdens = 1.18422e-05;
204 case 4: // 154199 ft. 47 km
206 reftemp = 487.17; // in degrees Rankine, 270.65 Kelvin
208 //refdens = 4.00585e-7;
210 case 5: // 167322 ft. or 51 km
211 slope = -0.001536192;
212 reftemp = 487.17; // in degrees Rankine, 270.65 Kelvin
214 //refdens = 8.17102e-7;
216 case 6: // 232940 ft. or 71 km
218 reftemp = 386.368; // in degrees Rankine, 214.649 Kelvin
220 //refdens = 8.77702e-9;
222 case 7: // 278385 ft. or 84.8520 km
224 reftemp = 336.5; // in degrees Rankine, 186.94 Kelvin
226 //refdens = 2.19541e-10;
228 default: // sea level
229 slope = -0.00356616; // R/ft.
230 reftemp = 518.67; // in degrees Rankine, 288.15 Kelvin
231 refpress = 2116.22; // psf
232 //refdens = 0.00237767; // slugs/cubic ft.
237 // If delta_T is set, then that is our temperature deviation at any altitude.
238 // If not, then we'll estimate a deviation based on the sea level deviation (if set).
240 if(!StandardTempOnly) {
242 if (delta_T != 0.0) {
245 if ((altitude < 36089.239) && (T_dev_sl != 0.0)) {
246 T_dev = T_dev_sl * ( 1.0 - (altitude/36089.239));
253 intTemperature = reftemp;
254 intPressure = refpress*exp(-Inertial->SLgravity()/(reftemp*Reng)*(altitude-htab[i]));
255 intDensity = intPressure/(Reng*intTemperature);
257 intTemperature = reftemp+slope*(altitude-htab[i]);
258 intPressure = refpress*pow(intTemperature/reftemp,-Inertial->SLgravity()/(slope*Reng));
259 intDensity = intPressure/(Reng*intTemperature);
265 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
266 // Calculate parameters derived from T, P and rho
267 // Sum gust and turbulence values in NED frame into the wind vector.
269 void FGAtmosphere::CalculateDerived(void)
271 T_dev = (*temperature) - GetTemperature(h);
272 density_altitude = h + T_dev * 66.7;
274 if (turbType != ttNone) Turbulence();
276 vTotalWindNED = vWindNED + vGustNED + vTurbulenceNED;
278 // psiw (Wind heading) is the direction the wind is blowing towards
279 if (vWindNED(eX) != 0.0) psiw = atan2( vWindNED(eY), vWindNED(eX) );
280 if (psiw < 0) psiw += 2*M_PI;
282 soundspeed = sqrt(SHRatio*Reng*(*temperature));
284 intViscosity = Beta * pow(intTemperature, 1.5) / (SutherlandConstant + intTemperature);
285 intKinematicViscosity = intViscosity / intDensity;
289 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
290 // Get the standard atmospheric properties at a specified altitude
292 void FGAtmosphere::GetStdAtmosphere(double altitude) {
293 StandardTempOnly = true;
295 StandardTempOnly = false;
296 atmosphere.Temperature = intTemperature;
297 atmosphere.Pressure = intPressure;
298 atmosphere.Density = intDensity;
300 // Reset the internal atmospheric state
304 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
305 // Get the standard pressure at a specified altitude
307 double FGAtmosphere::GetPressure(double altitude) {
308 GetStdAtmosphere(altitude);
309 return atmosphere.Pressure;
312 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
313 // Get the standard temperature at a specified altitude
315 double FGAtmosphere::GetTemperature(double altitude) {
316 GetStdAtmosphere(altitude);
317 return atmosphere.Temperature;
320 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
321 // Get the standard density at a specified altitude
323 double FGAtmosphere::GetDensity(double altitude) {
324 GetStdAtmosphere(altitude);
325 return atmosphere.Density;
329 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
330 // square a value, but preserve the original sign
332 static inline double square_signed (double value)
335 return value * value * -1;
337 return value * value;
340 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
342 // psi is the angle that the wind is blowing *towards*
344 void FGAtmosphere::SetWindspeed(double speed)
346 if (vWindNED.Magnitude() == 0.0) {
348 vWindNED(eNorth) = speed;
350 vWindNED(eNorth) = speed * cos(psiw);
351 vWindNED(eEast) = speed * sin(psiw);
352 vWindNED(eDown) = 0.0;
356 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
358 double FGAtmosphere::GetWindspeed(void) const
360 return vWindNED.Magnitude();
363 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
365 // psi is the angle that the wind is blowing *towards*
367 void FGAtmosphere::SetWindPsi(double dir)
369 double mag = GetWindspeed();
374 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
376 void FGAtmosphere::Turbulence(void)
378 double DeltaT = rate*State->Getdt();
382 // TurbGain = TurbGain * TurbGain * 100.0; // what is this!?
384 vDirectiondAccelDt(eX) = 1 - 2.0*(double(rand())/double(RAND_MAX));
385 vDirectiondAccelDt(eY) = 1 - 2.0*(double(rand())/double(RAND_MAX));
386 vDirectiondAccelDt(eZ) = 1 - 2.0*(double(rand())/double(RAND_MAX));
388 MagnitudedAccelDt = 1 - 2.0*(double(rand())/double(RAND_MAX)) - Magnitude;
389 // Scale the magnitude so that it moves
390 // away from the peaks
391 MagnitudedAccelDt = ((MagnitudedAccelDt - Magnitude) /
392 (1 + fabs(Magnitude)));
393 MagnitudeAccel += MagnitudedAccelDt*TurbRate*DeltaT;
394 Magnitude += MagnitudeAccel*DeltaT;
395 Magnitude = fabs(Magnitude);
397 vDirectiondAccelDt.Normalize();
399 // deemphasise non-vertical forces
400 vDirectiondAccelDt(eX) = square_signed(vDirectiondAccelDt(eX));
401 vDirectiondAccelDt(eY) = square_signed(vDirectiondAccelDt(eY));
403 vDirectionAccel += vDirectiondAccelDt*TurbRate*DeltaT;
404 vDirectionAccel.Normalize();
405 vDirection += vDirectionAccel*DeltaT;
407 vDirection.Normalize();
409 // Diminish turbulence within three wingspans
411 vTurbulenceNED = TurbGain * Magnitude * vDirection;
412 double HOverBMAC = Auxiliary->GetHOverBMAC();
414 vTurbulenceNED *= (HOverBMAC / 3.0) * (HOverBMAC / 3.0);
416 // I don't believe these next two statements calculate the proper gradient over
417 // the aircraft body. One reason is because this has no relationship with the
418 // orientation or velocity of the aircraft, which it must have. What is vTurbulenceGrad
419 // supposed to represent? And the direction and magnitude of the turbulence can change,
420 // so both accelerations need to be accounted for, no?
422 // Need to determine the turbulence change in body axes between two time points.
424 vTurbulenceGrad = TurbGain*MagnitudeAccel * vDirection;
425 vBodyTurbGrad = Propagate->GetTl2b()*vTurbulenceGrad;
427 if (Aircraft->GetWingSpan() > 0) {
428 vTurbPQR(eP) = vBodyTurbGrad(eY)/Aircraft->GetWingSpan();
430 vTurbPQR(eP) = vBodyTurbGrad(eY)/30.0;
432 // if (Aircraft->GetHTailArm() != 0.0)
433 // vTurbPQR(eQ) = vBodyTurbGrad(eZ)/Aircraft->GetHTailArm();
435 // vTurbPQR(eQ) = vBodyTurbGrad(eZ)/10.0;
437 if (Aircraft->GetVTailArm() > 0)
438 vTurbPQR(eR) = vBodyTurbGrad(eX)/Aircraft->GetVTailArm();
440 vTurbPQR(eR) = vBodyTurbGrad(eX)/10.0;
442 // Clear the horizontal forces
443 // actually felt by the plane, now
444 // that we've used them to calculate
447 // vTurbulenceNED(eX) = 0.0;
448 // vTurbulenceNED(eY) = 0.0;
452 case ttBerndt: { // This is very experimental and incomplete at the moment.
454 vDirectiondAccelDt(eX) = GaussianRandomNumber();
455 vDirectiondAccelDt(eY) = GaussianRandomNumber();
456 vDirectiondAccelDt(eZ) = GaussianRandomNumber();
458 MagnitudedAccelDt = GaussianRandomNumber();
459 MagnitudeAccel += MagnitudedAccelDt * DeltaT;
460 Magnitude += MagnitudeAccel * DeltaT;
462 vDirectiondAccelDt.Normalize();
463 vDirectionAccel += TurbRate * vDirectiondAccelDt * DeltaT;
464 vDirectionAccel.Normalize();
465 vDirection += vDirectionAccel*DeltaT;
467 // Diminish z-vector within two wingspans of the ground
468 double HOverBMAC = Auxiliary->GetHOverBMAC();
469 if (HOverBMAC < 2.0) vDirection(eZ) *= HOverBMAC / 2.0;
471 vDirection.Normalize();
473 vTurbulenceNED = TurbGain*Magnitude * vDirection;
474 vTurbulenceGrad = TurbGain*MagnitudeAccel * vDirection;
476 vBodyTurbGrad = Propagate->GetTl2b() * vTurbulenceGrad;
477 vTurbPQR(eP) = vBodyTurbGrad(eY) / Aircraft->GetWingSpan();
478 if (Aircraft->GetHTailArm() > 0)
479 vTurbPQR(eQ) = vBodyTurbGrad(eZ) / Aircraft->GetHTailArm();
481 vTurbPQR(eQ) = vBodyTurbGrad(eZ) / 10.0;
483 if (Aircraft->GetVTailArm() > 0)
484 vTurbPQR(eR) = vBodyTurbGrad(eX) / Aircraft->GetVTailArm();
486 vTurbPQR(eR) = vBodyTurbGrad(eX)/10.0;
492 vTurbPQR(eP) = wind_from_clockwise;
493 if (TurbGain == 0.0) return;
495 // keep the inputs within allowable limts for this model
496 if (TurbGain < 0.0) TurbGain = 0.0;
497 if (TurbGain > 1.0) TurbGain = 1.0;
498 if (TurbRate < 0.0) TurbRate = 0.0;
499 if (TurbRate > 30.0) TurbRate = 30.0;
500 if (Rhythmicity < 0.0) Rhythmicity = 0.0;
501 if (Rhythmicity > 1.0) Rhythmicity = 1.0;
503 // generate a sine wave corresponding to turbulence rate in hertz
504 double time = FDMExec->GetSimTime();
505 double sinewave = sin( time * TurbRate * 6.283185307 );
508 if (target_time == 0.0) {
509 strength = random = 1 - 2.0*(double(rand())/double(RAND_MAX));
510 target_time = time + 0.71 + (random * 0.5);
512 if (time > target_time) {
517 // max vertical wind speed in fps, corresponds to TurbGain = 1.0
520 vTurbulenceNED(1) = vTurbulenceNED(2) = vTurbulenceNED(3) = 0.0;
521 double delta = strength * max_vs * TurbGain * (1-Rhythmicity) * spike;
523 // Vertical component of turbulence.
524 vTurbulenceNED(3) = sinewave * max_vs * TurbGain * Rhythmicity;
525 vTurbulenceNED(3)+= delta;
526 double HOverBMAC = Auxiliary->GetHOverBMAC();
528 vTurbulenceNED(3) *= HOverBMAC * 0.3333;
530 // Yaw component of turbulence.
531 vTurbulenceNED(1) = sin( delta * 3.0 );
532 vTurbulenceNED(2) = cos( delta * 3.0 );
534 // Roll component of turbulence. Clockwise vortex causes left roll.
535 vTurbPQR(eP) += delta * 0.04;
545 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
547 void FGAtmosphere::UseExternal(void)
549 temperature=&exTemperature;
550 pressure=&exPressure;
555 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
557 void FGAtmosphere::UseInternal(void)
559 temperature=&intTemperature;
560 pressure=&intPressure;
565 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
567 void FGAtmosphere::bind(void)
569 typedef double (FGAtmosphere::*PMF)(int) const;
570 typedef double (FGAtmosphere::*PMFv)(void) const;
571 typedef int (FGAtmosphere::*PMFt)(void) const;
572 typedef void (FGAtmosphere::*PMFd)(int,double);
573 typedef void (FGAtmosphere::*PMFi)(int);
574 PropertyManager->Tie("atmosphere/T-R", this, (PMFv)&FGAtmosphere::GetTemperature);
575 PropertyManager->Tie("atmosphere/rho-slugs_ft3", this, (PMFv)&FGAtmosphere::GetDensity);
576 PropertyManager->Tie("atmosphere/P-psf", this, (PMFv)&FGAtmosphere::GetPressure);
577 PropertyManager->Tie("atmosphere/a-fps", this, &FGAtmosphere::GetSoundSpeed);
578 PropertyManager->Tie("atmosphere/T-sl-R", this, &FGAtmosphere::GetTemperatureSL);
579 PropertyManager->Tie("atmosphere/rho-sl-slugs_ft3", this, &FGAtmosphere::GetDensitySL);
580 PropertyManager->Tie("atmosphere/P-sl-psf", this, &FGAtmosphere::GetPressureSL);
581 PropertyManager->Tie("atmosphere/a-sl-fps", this, &FGAtmosphere::GetSoundSpeedSL);
582 PropertyManager->Tie("atmosphere/theta", this, &FGAtmosphere::GetTemperatureRatio);
583 PropertyManager->Tie("atmosphere/sigma", this, &FGAtmosphere::GetDensityRatio);
584 PropertyManager->Tie("atmosphere/delta", this, &FGAtmosphere::GetPressureRatio);
585 PropertyManager->Tie("atmosphere/a-ratio", this, &FGAtmosphere::GetSoundSpeedRatio);
586 PropertyManager->Tie("atmosphere/psiw-rad", this, &FGAtmosphere::GetWindPsi, &FGAtmosphere::SetWindPsi);
587 PropertyManager->Tie("atmosphere/delta-T", this, &FGAtmosphere::GetDeltaT, &FGAtmosphere::SetDeltaT);
588 PropertyManager->Tie("atmosphere/T-sl-dev-F", this, &FGAtmosphere::GetSLTempDev, &FGAtmosphere::SetSLTempDev);
589 PropertyManager->Tie("atmosphere/density-altitude", this, &FGAtmosphere::GetDensityAltitude);
591 PropertyManager->Tie("atmosphere/wind-north-fps", this, eNorth, (PMF)&FGAtmosphere::GetWindNED,
592 (PMFd)&FGAtmosphere::SetWindNED);
593 PropertyManager->Tie("atmosphere/wind-east-fps", this, eEast, (PMF)&FGAtmosphere::GetWindNED,
594 (PMFd)&FGAtmosphere::SetWindNED);
595 PropertyManager->Tie("atmosphere/wind-down-fps", this, eDown, (PMF)&FGAtmosphere::GetWindNED,
596 (PMFd)&FGAtmosphere::SetWindNED);
597 PropertyManager->Tie("atmosphere/wind-mag-fps", this, &FGAtmosphere::GetWindspeed,
598 &FGAtmosphere::SetWindspeed);
599 PropertyManager->Tie("atmosphere/total-wind-north-fps", this, eNorth, (PMF)&FGAtmosphere::GetTotalWindNED);
600 PropertyManager->Tie("atmosphere/total-wind-east-fps", this, eEast, (PMF)&FGAtmosphere::GetTotalWindNED);
601 PropertyManager->Tie("atmosphere/total-wind-down-fps", this, eDown, (PMF)&FGAtmosphere::GetTotalWindNED);
603 PropertyManager->Tie("atmosphere/gust-north-fps", this, eNorth, (PMF)&FGAtmosphere::GetGustNED,
604 (PMFd)&FGAtmosphere::SetGustNED);
605 PropertyManager->Tie("atmosphere/gust-east-fps", this, eEast, (PMF)&FGAtmosphere::GetGustNED,
606 (PMFd)&FGAtmosphere::SetGustNED);
607 PropertyManager->Tie("atmosphere/gust-down-fps", this, eDown, (PMF)&FGAtmosphere::GetGustNED,
608 (PMFd)&FGAtmosphere::SetGustNED);
610 PropertyManager->Tie("atmosphere/turb-north-fps", this, eNorth, (PMF)&FGAtmosphere::GetTurbNED,
611 (PMFd)&FGAtmosphere::SetTurbNED);
612 PropertyManager->Tie("atmosphere/turb-east-fps", this, eEast, (PMF)&FGAtmosphere::GetTurbNED,
613 (PMFd)&FGAtmosphere::SetTurbNED);
614 PropertyManager->Tie("atmosphere/turb-down-fps", this, eDown, (PMF)&FGAtmosphere::GetTurbNED,
615 (PMFd)&FGAtmosphere::SetTurbNED);
617 PropertyManager->Tie("atmosphere/p-turb-rad_sec", this,1, (PMF)&FGAtmosphere::GetTurbPQR);
618 PropertyManager->Tie("atmosphere/q-turb-rad_sec", this,2, (PMF)&FGAtmosphere::GetTurbPQR);
619 PropertyManager->Tie("atmosphere/r-turb-rad_sec", this,3, (PMF)&FGAtmosphere::GetTurbPQR);
620 PropertyManager->Tie("atmosphere/turb-type", this, (PMFt)&FGAtmosphere::GetTurbType, (PMFi)&FGAtmosphere::SetTurbType);
621 PropertyManager->Tie("atmosphere/turb-rate", this, &FGAtmosphere::GetTurbRate, &FGAtmosphere::SetTurbRate);
622 PropertyManager->Tie("atmosphere/turb-gain", this, &FGAtmosphere::GetTurbGain, &FGAtmosphere::SetTurbGain);
623 PropertyManager->Tie("atmosphere/turb-rhythmicity", this, &FGAtmosphere::GetRhythmicity,
624 &FGAtmosphere::SetRhythmicity);
627 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
628 // The bitmasked value choices are as follows:
629 // unset: In this case (the default) JSBSim would only print
630 // out the normally expected messages, essentially echoing
631 // the config files as they are read. If the environment
632 // variable is not set, debug_lvl is set to 1 internally
633 // 0: This requests JSBSim not to output any messages
635 // 1: This value explicity requests the normal JSBSim
637 // 2: This value asks for a message to be printed out when
638 // a class is instantiated
639 // 4: When this value is set, a message is displayed when a
640 // FGModel object executes its Run() method
641 // 8: When this value is set, various runtime state variables
642 // are printed out periodically
643 // 16: When set various parameters are sanity checked and
644 // a message is printed out when they go out of bounds
646 void FGAtmosphere::Debug(int from)
648 if (debug_lvl <= 0) return;
650 if (debug_lvl & 1) { // Standard console startup message output
651 if (from == 0) { // Constructor
654 if (debug_lvl & 2 ) { // Instantiation/Destruction notification
655 if (from == 0) cout << "Instantiated: FGAtmosphere" << endl;
656 if (from == 1) cout << "Destroyed: FGAtmosphere" << endl;
658 if (debug_lvl & 4 ) { // Run() method entry print for FGModel-derived objects
660 if (debug_lvl & 8 ) { // Runtime state variables
662 if (debug_lvl & 16) { // Sanity checking
664 if (debug_lvl & 128) { // Turbulence
665 if (first_pass && from == 2) {
667 cout << "vTurbulenceNED(X), vTurbulenceNED(Y), vTurbulenceNED(Z), "
668 << "vTurbulenceGrad(X), vTurbulenceGrad(Y), vTurbulenceGrad(Z), "
669 << "vDirection(X), vDirection(Y), vDirection(Z), "
671 << "vTurbPQR(P), vTurbPQR(Q), vTurbPQR(R), " << endl;
674 cout << vTurbulenceNED << ", " << vTurbulenceGrad << ", " << vDirection << ", " << Magnitude << ", " << vTurbPQR << endl;
677 if (debug_lvl & 64) {
678 if (from == 0) { // Constructor
679 cout << IdSrc << endl;
680 cout << IdHdr << endl;
685 } // namespace JSBSim