/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
Module: FGAtmosphere.cpp
- Author: Jon Berndt
- Implementation of 1959 Standard Atmosphere added by Tony Peden
- Date started: 11/24/98
- Purpose: Models the atmosphere
- Called by: FGSimExec
+ Author: Jon Berndt, Tony Peden
+ Date started: 6/2011
+ Purpose: Models an atmosphere interface class
+ Called by: FGFDMExec
- ------------- Copyright (C) 1999 Jon S. Berndt (jon@jsbsim.org) -------------
+ ------------- Copyright (C) 2011 Jon S. Berndt (jon@jsbsim.org) -------------
This program is free software; you can redistribute it and/or modify it under
the terms of the GNU Lesser General Public License as published by the Free Software
FUNCTIONAL DESCRIPTION
--------------------------------------------------------------------------------
-Models the atmosphere. The equation used below was determined by a third order
-curve fit using Excel. The data is from the ICAO atmosphere model.
+This models a base atmosphere class to serve as a common interface to any derived
+atmosphere models.
HISTORY
--------------------------------------------------------------------------------
-11/24/98 JSB Created
-07/23/99 TP Added implementation of 1959 Standard Atmosphere
- Moved calculation of Mach number to FGPropagate
- Later updated to '76 model
+6/18/2011 Started Jon S. Berndt
+
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
COMMENTS, REFERENCES, and NOTES
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-[1] Anderson, John D. "Introduction to Flight, Third Edition", McGraw-Hill,
- 1989, ISBN 0-07-001641-0
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
INCLUDES
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
-#include "FGAtmosphere.h"
-#include "FGAircraft.h"
-#include "FGPropagate.h"
-#include "FGInertial.h"
-#include "FGAuxiliary.h"
-#include "FGFDMExec.h"
-#include "input_output/FGPropertyManager.h"
#include <iostream>
+#include <iomanip>
#include <cstdlib>
-
-using namespace std;
+#include "FGFDMExec.h"
+#include "FGAtmosphere.h"
namespace JSBSim {
-static const char *IdSrc = "$Id: FGAtmosphere.cpp,v 1.35 2010/08/11 11:51:33 jberndt Exp $";
+static const char *IdSrc = "$Id: FGAtmosphere.cpp,v 1.51 2012/04/13 13:18:28 jberndt Exp $";
static const char *IdHdr = ID_ATMOSPHERE;
/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
CLASS IMPLEMENTATION
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
-FGAtmosphere::FGAtmosphere(FGFDMExec* fdmex) : FGModel(fdmex)
+FGAtmosphere::FGAtmosphere(FGFDMExec* fdmex) : FGModel(fdmex),
+ PressureAltitude(0.0), // ft
+ DensityAltitude(0.0), // ft
+ SutherlandConstant(198.72), // deg Rankine
+ Beta(2.269690E-08) // slug/(sec ft R^0.5)
{
Name = "FGAtmosphere";
- lastIndex = 0;
- h = 0.0;
- psiw = 0.0;
- htab[0]=0;
- htab[1]= 36089.0;
- htab[2]= 65617.0;
- htab[3]=104987.0;
- htab[4]=154199.0;
- htab[5]=167322.0;
- htab[6]=232940.0;
- htab[7]=278385.0; //ft.
-
- MagnitudedAccelDt = MagnitudeAccel = Magnitude = 0.0;
-// SetTurbType( ttCulp );
- SetTurbType( ttNone );
- TurbGain = 1.0;
- TurbRate = 10.0;
- Rhythmicity = 0.1;
- spike = target_time = strength = 0.0;
- wind_from_clockwise = 0.0;
- SutherlandConstant = 198.72; // deg Rankine
- Beta = 2.269690E-08; // slug/(sec ft R^0.5)
-
- T_dev_sl = T_dev = delta_T = 0.0;
- StandardTempOnly = false;
- first_pass = true;
- vGustNED.InitMatrix();
- vTurbulenceNED.InitMatrix();
bind();
Debug(0);
bool FGAtmosphere::InitModel(void)
{
- if (!FGModel::InitModel()) return false;
+ Calculate(0.0);
+ SLtemperature = Temperature = 518.67;
+ SLpressure = Pressure = 2116.22;
+ SLdensity = Density = Pressure/(Reng*Temperature);
+ SLsoundspeed = Soundspeed = sqrt(SHRatio*Reng*(Temperature));
- UseInternal(); // this is the default
-
- Calculate(h);
- StdSLtemperature = SLtemperature = 518.67;
- StdSLpressure = SLpressure = 2116.22;
- StdSLdensity = SLdensity = 0.00237767;
- StdSLsoundspeed = SLsoundspeed = sqrt(SHRatio*Reng*StdSLtemperature);
- rSLtemperature = 1.0/StdSLtemperature;
- rSLpressure = 1.0/StdSLpressure;
- rSLdensity = 1.0/StdSLdensity;
- rSLsoundspeed = 1.0/StdSLsoundspeed;
+ rSLtemperature = 1/SLtemperature ;
+ rSLpressure = 1/SLpressure ;
+ rSLdensity = 1/SLdensity ;
+ rSLsoundspeed = 1/SLsoundspeed ;
return true;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-bool FGAtmosphere::Run(void)
+bool FGAtmosphere::Run(bool Holding)
{
- if (FGModel::Run()) return true;
- if (FDMExec->Holding()) return false;
-
- RunPreFunctions();
-
- T_dev = 0.0;
- h = Propagate->GetAltitudeASL();
-
- if (!useExternal) {
- Calculate(h);
- CalculateDerived();
- } else {
- CalculateDerived();
- }
+ if (FGModel::Run(Holding)) return true;
+ if (Holding) return false;
- RunPostFunctions();
+ Calculate(in.altitudeASL);
Debug(2);
return false;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-//
-// See reference 1
void FGAtmosphere::Calculate(double altitude)
{
- double slope, reftemp, refpress;
- int i = lastIndex;
-
- if (altitude < htab[lastIndex]) {
- if (altitude <= 0) {
- i = 0;
- altitude=0;
- } else {
- i = lastIndex-1;
- while (htab[i] > altitude) i--;
- }
- } else if (altitude > htab[lastIndex+1]) {
- if (altitude >= htab[7]) {
- i = 7;
- altitude = htab[7];
- } else {
- i = lastIndex+1;
- while (htab[i+1] < altitude) i++;
- }
- }
-
- switch(i) {
- case 0: // Sea level
- slope = -0.00356616; // R/ft.
- reftemp = 518.67; // in degrees Rankine, 288.15 Kelvin
- refpress = 2116.22; // psf
- //refdens = 0.00237767; // slugs/cubic ft.
- break;
- case 1: // 36089 ft. or 11 km
- slope = 0;
- reftemp = 389.97; // in degrees Rankine, 216.65 Kelvin
- refpress = 472.763;
- //refdens = 0.000706032;
- break;
- case 2: // 65616 ft. or 20 km
- slope = 0.00054864;
- reftemp = 389.97; // in degrees Rankine, 216.65 Kelvin
- refpress = 114.636;
- //refdens = 0.000171306;
- break;
- case 3: // 104986 ft. or 32 km
- slope = 0.001536192;
- reftemp = 411.57; // in degrees Rankine, 228.65 Kelvin
- refpress = 18.128;
- //refdens = 1.18422e-05;
- break;
- case 4: // 154199 ft. 47 km
- slope = 0;
- reftemp = 487.17; // in degrees Rankine, 270.65 Kelvin
- refpress = 2.316;
- //refdens = 4.00585e-7;
- break;
- case 5: // 167322 ft. or 51 km
- slope = -0.001536192;
- reftemp = 487.17; // in degrees Rankine, 270.65 Kelvin
- refpress = 1.398;
- //refdens = 8.17102e-7;
- break;
- case 6: // 232940 ft. or 71 km
- slope = -0.00109728;
- reftemp = 386.368; // in degrees Rankine, 214.649 Kelvin
- refpress = 0.0826;
- //refdens = 8.77702e-9;
- break;
- case 7: // 278385 ft. or 84.8520 km
- slope = 0;
- reftemp = 336.5; // in degrees Rankine, 186.94 Kelvin
- refpress = 0.00831;
- //refdens = 2.19541e-10;
- break;
- default: // sea level
- slope = -0.00356616; // R/ft.
- reftemp = 518.67; // in degrees Rankine, 288.15 Kelvin
- refpress = 2116.22; // psf
- //refdens = 0.00237767; // slugs/cubic ft.
- break;
-
- }
-
- // If delta_T is set, then that is our temperature deviation at any altitude.
- // If not, then we'll estimate a deviation based on the sea level deviation (if set).
-
- if(!StandardTempOnly) {
- T_dev = 0.0;
- if (delta_T != 0.0) {
- T_dev = delta_T;
- } else {
- if ((altitude < 36089.239) && (T_dev_sl != 0.0)) {
- T_dev = T_dev_sl * ( 1.0 - (altitude/36089.239));
- }
- }
- reftemp+=T_dev;
- }
-
- if (slope == 0) {
- intTemperature = reftemp;
- intPressure = refpress*exp(-Inertial->SLgravity()/(reftemp*Reng)*(altitude-htab[i]));
- intDensity = intPressure/(Reng*intTemperature);
- } else {
- intTemperature = reftemp+slope*(altitude-htab[i]);
- intPressure = refpress*pow(intTemperature/reftemp,-Inertial->SLgravity()/(slope*Reng));
- intDensity = intPressure/(Reng*intTemperature);
- }
-
- lastIndex=i;
+ Temperature = GetTemperature(altitude);
+ Pressure = GetPressure(altitude);
+ Density = Pressure/(Reng*Temperature);
+ Soundspeed = sqrt(SHRatio*Reng*(Temperature));
+ PressureAltitude = altitude;
+ DensityAltitude = altitude;
+
+ Viscosity = Beta * pow(Temperature, 1.5) / (SutherlandConstant + Temperature);
+ KinematicViscosity = Viscosity / Density;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-// Calculate parameters derived from T, P and rho
-// Sum gust and turbulence values in NED frame into the wind vector.
-void FGAtmosphere::CalculateDerived(void)
+void FGAtmosphere::SetPressureSL(ePressure unit, double pressure)
{
- T_dev = (*temperature) - GetTemperature(h);
-
- if (T_dev == 0.0) density_altitude = h;
- else density_altitude = 518.4/0.00357 * (1.0 - pow(GetDensityRatio(),0.235));
+ double press = ConvertToPSF(pressure, unit);
- if (turbType != ttNone) Turbulence();
-
- vTotalWindNED = vWindNED + vGustNED + vTurbulenceNED;
-
- // psiw (Wind heading) is the direction the wind is blowing towards
- if (vWindNED(eX) != 0.0) psiw = atan2( vWindNED(eY), vWindNED(eX) );
- if (psiw < 0) psiw += 2*M_PI;
-
- soundspeed = sqrt(SHRatio*Reng*(*temperature));
-
- intViscosity = Beta * pow(intTemperature, 1.5) / (SutherlandConstant + intTemperature);
- intKinematicViscosity = intViscosity / intDensity;
-}
-
-
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-// Get the standard atmospheric properties at a specified altitude
-
-void FGAtmosphere::GetStdAtmosphere(double altitude) {
- StandardTempOnly = true;
- Calculate(altitude);
- StandardTempOnly = false;
- atmosphere.Temperature = intTemperature;
- atmosphere.Pressure = intPressure;
- atmosphere.Density = intDensity;
-
- // Reset the internal atmospheric state
- Calculate(h);
+ SLpressure = press;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-// Get the standard pressure at a specified altitude
-
-double FGAtmosphere::GetPressure(double altitude) {
- GetStdAtmosphere(altitude);
- return atmosphere.Pressure;
-}
+// Get the modeled density at a specified altitude
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-// Get the standard temperature at a specified altitude
-
-double FGAtmosphere::GetTemperature(double altitude) {
- GetStdAtmosphere(altitude);
- return atmosphere.Temperature;
-}
-
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-// Get the standard density at a specified altitude
-
-double FGAtmosphere::GetDensity(double altitude) {
- GetStdAtmosphere(altitude);
- return atmosphere.Density;
-}
-
-
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-// square a value, but preserve the original sign
-
-static inline double square_signed (double value)
+double FGAtmosphere::GetDensity(double altitude) const
{
- if (value < 0)
- return value * value * -1;
- else
- return value * value;
+ return GetPressure(altitude)/(Reng * GetTemperature(altitude));
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-//
-// psi is the angle that the wind is blowing *towards*
+// This function sets the sea level temperature.
+// Internally, the Rankine scale is used for calculations, so any temperature
+// supplied must be converted to that unit.
-void FGAtmosphere::SetWindspeed(double speed)
+void FGAtmosphere::SetTemperatureSL(double t, eTemperature unit)
{
- if (vWindNED.Magnitude() == 0.0) {
- psiw = 0.0;
- vWindNED(eNorth) = speed;
- } else {
- vWindNED(eNorth) = speed * cos(psiw);
- vWindNED(eEast) = speed * sin(psiw);
- vWindNED(eDown) = 0.0;
- }
-}
-
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-
-double FGAtmosphere::GetWindspeed(void) const
-{
- return vWindNED.Magnitude();
+ SLtemperature = ConvertToRankine(t, unit);
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-//
-// psi is the angle that the wind is blowing *towards*
-void FGAtmosphere::SetWindPsi(double dir)
+double FGAtmosphere::ConvertToRankine(double t, eTemperature unit) const
{
- double mag = GetWindspeed();
- psiw = dir;
- SetWindspeed(mag);
-}
-
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-
-void FGAtmosphere::Turbulence(void)
-{
- double DeltaT = rate*FDMExec->GetDeltaT();
-
- switch (turbType) {
- case ttStandard: {
- // TurbGain = TurbGain * TurbGain * 100.0; // what is this!?
-
- vDirectiondAccelDt(eX) = 1 - 2.0*(double(rand())/double(RAND_MAX));
- vDirectiondAccelDt(eY) = 1 - 2.0*(double(rand())/double(RAND_MAX));
- vDirectiondAccelDt(eZ) = 1 - 2.0*(double(rand())/double(RAND_MAX));
-
- MagnitudedAccelDt = 1 - 2.0*(double(rand())/double(RAND_MAX)) - Magnitude;
- // Scale the magnitude so that it moves
- // away from the peaks
- MagnitudedAccelDt = ((MagnitudedAccelDt - Magnitude) /
- (1 + fabs(Magnitude)));
- MagnitudeAccel += MagnitudedAccelDt*TurbRate*DeltaT;
- Magnitude += MagnitudeAccel*DeltaT;
- Magnitude = fabs(Magnitude);
-
- vDirectiondAccelDt.Normalize();
-
- // deemphasise non-vertical forces
- vDirectiondAccelDt(eX) = square_signed(vDirectiondAccelDt(eX));
- vDirectiondAccelDt(eY) = square_signed(vDirectiondAccelDt(eY));
-
- vDirectionAccel += vDirectiondAccelDt*TurbRate*DeltaT;
- vDirectionAccel.Normalize();
- vDirection += vDirectionAccel*DeltaT;
-
- vDirection.Normalize();
-
- // Diminish turbulence within three wingspans
- // of the ground
- vTurbulenceNED = TurbGain * Magnitude * vDirection;
- double HOverBMAC = Auxiliary->GetHOverBMAC();
- if (HOverBMAC < 3.0)
- vTurbulenceNED *= (HOverBMAC / 3.0) * (HOverBMAC / 3.0);
-
- // I don't believe these next two statements calculate the proper gradient over
- // the aircraft body. One reason is because this has no relationship with the
- // orientation or velocity of the aircraft, which it must have. What is vTurbulenceGrad
- // supposed to represent? And the direction and magnitude of the turbulence can change,
- // so both accelerations need to be accounted for, no?
-
- // Need to determine the turbulence change in body axes between two time points.
-
- vTurbulenceGrad = TurbGain*MagnitudeAccel * vDirection;
- vBodyTurbGrad = Propagate->GetTl2b()*vTurbulenceGrad;
-
- if (Aircraft->GetWingSpan() > 0) {
- vTurbPQR(eP) = vBodyTurbGrad(eY)/Aircraft->GetWingSpan();
- } else {
- vTurbPQR(eP) = vBodyTurbGrad(eY)/30.0;
- }
-// if (Aircraft->GetHTailArm() != 0.0)
-// vTurbPQR(eQ) = vBodyTurbGrad(eZ)/Aircraft->GetHTailArm();
-// else
-// vTurbPQR(eQ) = vBodyTurbGrad(eZ)/10.0;
-
- if (Aircraft->GetVTailArm() > 0)
- vTurbPQR(eR) = vBodyTurbGrad(eX)/Aircraft->GetVTailArm();
- else
- vTurbPQR(eR) = vBodyTurbGrad(eX)/10.0;
-
- // Clear the horizontal forces
- // actually felt by the plane, now
- // that we've used them to calculate
- // moments.
- // Why? (JSB)
-// vTurbulenceNED(eX) = 0.0;
-// vTurbulenceNED(eY) = 0.0;
+ double targetTemp=0; // in degrees Rankine
+ switch(unit) {
+ case eFahrenheit:
+ targetTemp = t + 459.67;
break;
- }
- case ttBerndt: { // This is very experimental and incomplete at the moment.
-
- vDirectiondAccelDt(eX) = GaussianRandomNumber();
- vDirectiondAccelDt(eY) = GaussianRandomNumber();
- vDirectiondAccelDt(eZ) = GaussianRandomNumber();
-/*
- MagnitudedAccelDt = GaussianRandomNumber();
- MagnitudeAccel += MagnitudedAccelDt * DeltaT;
- Magnitude += MagnitudeAccel * DeltaT;
-*/
- Magnitude += GaussianRandomNumber() * DeltaT;
-
- vDirectiondAccelDt.Normalize();
- vDirectionAccel += TurbRate * vDirectiondAccelDt * DeltaT;
- vDirectionAccel.Normalize();
- vDirection += vDirectionAccel*DeltaT;
-
- // Diminish z-vector within two wingspans of the ground
- double HOverBMAC = Auxiliary->GetHOverBMAC();
- if (HOverBMAC < 2.0) vDirection(eZ) *= HOverBMAC / 2.0;
-
- vDirection.Normalize();
-
- vTurbulenceNED = TurbGain*Magnitude * vDirection;
- vTurbulenceGrad = TurbGain*MagnitudeAccel * vDirection;
-
- vBodyTurbGrad = Propagate->GetTl2b() * vTurbulenceGrad;
- vTurbPQR(eP) = vBodyTurbGrad(eY) / Aircraft->GetWingSpan();
- if (Aircraft->GetHTailArm() > 0)
- vTurbPQR(eQ) = vBodyTurbGrad(eZ) / Aircraft->GetHTailArm();
- else
- vTurbPQR(eQ) = vBodyTurbGrad(eZ) / 10.0;
-
- if (Aircraft->GetVTailArm() > 0)
- vTurbPQR(eR) = vBodyTurbGrad(eX) / Aircraft->GetVTailArm();
- else
- vTurbPQR(eR) = vBodyTurbGrad(eX)/10.0;
-
+ case eCelsius:
+ targetTemp = t*9.0/5.0 + 32.0 + 459.67;
break;
- }
- case ttCulp: {
-
- vTurbPQR(eP) = wind_from_clockwise;
- if (TurbGain == 0.0) return;
-
- // keep the inputs within allowable limts for this model
- if (TurbGain < 0.0) TurbGain = 0.0;
- if (TurbGain > 1.0) TurbGain = 1.0;
- if (TurbRate < 0.0) TurbRate = 0.0;
- if (TurbRate > 30.0) TurbRate = 30.0;
- if (Rhythmicity < 0.0) Rhythmicity = 0.0;
- if (Rhythmicity > 1.0) Rhythmicity = 1.0;
-
- // generate a sine wave corresponding to turbulence rate in hertz
- double time = FDMExec->GetSimTime();
- double sinewave = sin( time * TurbRate * 6.283185307 );
-
- double random = 0.0;
- if (target_time == 0.0) {
- strength = random = 1 - 2.0*(double(rand())/double(RAND_MAX));
- target_time = time + 0.71 + (random * 0.5);
- }
- if (time > target_time) {
- spike = 1.0;
- target_time = 0.0;
- }
-
- // max vertical wind speed in fps, corresponds to TurbGain = 1.0
- double max_vs = 40;
-
- vTurbulenceNED(1) = vTurbulenceNED(2) = vTurbulenceNED(3) = 0.0;
- double delta = strength * max_vs * TurbGain * (1-Rhythmicity) * spike;
-
- // Vertical component of turbulence.
- vTurbulenceNED(3) = sinewave * max_vs * TurbGain * Rhythmicity;
- vTurbulenceNED(3)+= delta;
- double HOverBMAC = Auxiliary->GetHOverBMAC();
- if (HOverBMAC < 3.0)
- vTurbulenceNED(3) *= HOverBMAC * 0.3333;
-
- // Yaw component of turbulence.
- vTurbulenceNED(1) = sin( delta * 3.0 );
- vTurbulenceNED(2) = cos( delta * 3.0 );
-
- // Roll component of turbulence. Clockwise vortex causes left roll.
- vTurbPQR(eP) += delta * 0.04;
-
- spike = spike * 0.9;
+ case eRankine:
+ targetTemp = t;
+ break;
+ case eKelvin:
+ targetTemp = t*9.0/5.0;
break;
- }
default:
break;
}
+
+ return targetTemp;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGAtmosphere::UseExternal(void)
+double FGAtmosphere::ConvertToPSF(double p, ePressure unit) const
{
- temperature=&exTemperature;
- pressure=&exPressure;
- density=&exDensity;
- useExternal=true;
-}
+ double targetPressure=0; // Pressure in PSF
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+ switch(unit) {
+ case ePSF:
+ targetPressure = p;
+ break;
+ case eMillibars:
+ targetPressure = p*2.08854342;
+ break;
+ case ePascals:
+ targetPressure = p*0.0208854342;
+ break;
+ case eInchesHg:
+ targetPressure = p*70.7180803;
+ break;
+ default:
+ throw("Undefined pressure unit given");
+ }
-void FGAtmosphere::UseInternal(void)
-{
- temperature=&intTemperature;
- pressure=&intPressure;
- density=&intDensity;
- useExternal=false;
+ return targetPressure;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGAtmosphere::bind(void)
{
- typedef double (FGAtmosphere::*PMF)(int) const;
- typedef double (FGAtmosphere::*PMFv)(void) const;
- typedef int (FGAtmosphere::*PMFt)(void) const;
- typedef void (FGAtmosphere::*PMFd)(int,double);
- typedef void (FGAtmosphere::*PMFi)(int);
- PropertyManager->Tie("atmosphere/T-R", this, (PMFv)&FGAtmosphere::GetTemperature);
- PropertyManager->Tie("atmosphere/rho-slugs_ft3", this, (PMFv)&FGAtmosphere::GetDensity);
- PropertyManager->Tie("atmosphere/P-psf", this, (PMFv)&FGAtmosphere::GetPressure);
+ typedef double (FGAtmosphere::*PMFi)(int) const;
+ typedef void (FGAtmosphere::*PMF)(int, double);
+ PropertyManager->Tie("atmosphere/T-R", this, &FGAtmosphere::GetTemperature);
+ PropertyManager->Tie("atmosphere/rho-slugs_ft3", this, &FGAtmosphere::GetDensity);
+ PropertyManager->Tie("atmosphere/P-psf", this, &FGAtmosphere::GetPressure);
PropertyManager->Tie("atmosphere/a-fps", this, &FGAtmosphere::GetSoundSpeed);
PropertyManager->Tie("atmosphere/T-sl-R", this, &FGAtmosphere::GetTemperatureSL);
PropertyManager->Tie("atmosphere/rho-sl-slugs_ft3", this, &FGAtmosphere::GetDensitySL);
- PropertyManager->Tie("atmosphere/P-sl-psf", this, &FGAtmosphere::GetPressureSL);
+// PropertyManager->Tie("atmosphere/P-sl-psf", this, ePSF,
+// (PMFi)&FGAtmosphere::GetPressureSL,
+// (PMF)&FGAtmosphere::SetPressureSL);
PropertyManager->Tie("atmosphere/a-sl-fps", this, &FGAtmosphere::GetSoundSpeedSL);
PropertyManager->Tie("atmosphere/theta", this, &FGAtmosphere::GetTemperatureRatio);
PropertyManager->Tie("atmosphere/sigma", this, &FGAtmosphere::GetDensityRatio);
PropertyManager->Tie("atmosphere/delta", this, &FGAtmosphere::GetPressureRatio);
PropertyManager->Tie("atmosphere/a-ratio", this, &FGAtmosphere::GetSoundSpeedRatio);
- PropertyManager->Tie("atmosphere/psiw-rad", this, &FGAtmosphere::GetWindPsi, &FGAtmosphere::SetWindPsi);
- PropertyManager->Tie("atmosphere/delta-T", this, &FGAtmosphere::GetDeltaT, &FGAtmosphere::SetDeltaT);
- PropertyManager->Tie("atmosphere/T-sl-dev-F", this, &FGAtmosphere::GetSLTempDev, &FGAtmosphere::SetSLTempDev);
PropertyManager->Tie("atmosphere/density-altitude", this, &FGAtmosphere::GetDensityAltitude);
-
- PropertyManager->Tie("atmosphere/wind-north-fps", this, eNorth, (PMF)&FGAtmosphere::GetWindNED,
- (PMFd)&FGAtmosphere::SetWindNED);
- PropertyManager->Tie("atmosphere/wind-east-fps", this, eEast, (PMF)&FGAtmosphere::GetWindNED,
- (PMFd)&FGAtmosphere::SetWindNED);
- PropertyManager->Tie("atmosphere/wind-down-fps", this, eDown, (PMF)&FGAtmosphere::GetWindNED,
- (PMFd)&FGAtmosphere::SetWindNED);
- PropertyManager->Tie("atmosphere/wind-mag-fps", this, &FGAtmosphere::GetWindspeed,
- &FGAtmosphere::SetWindspeed);
- PropertyManager->Tie("atmosphere/total-wind-north-fps", this, eNorth, (PMF)&FGAtmosphere::GetTotalWindNED);
- PropertyManager->Tie("atmosphere/total-wind-east-fps", this, eEast, (PMF)&FGAtmosphere::GetTotalWindNED);
- PropertyManager->Tie("atmosphere/total-wind-down-fps", this, eDown, (PMF)&FGAtmosphere::GetTotalWindNED);
-
- PropertyManager->Tie("atmosphere/gust-north-fps", this, eNorth, (PMF)&FGAtmosphere::GetGustNED,
- (PMFd)&FGAtmosphere::SetGustNED);
- PropertyManager->Tie("atmosphere/gust-east-fps", this, eEast, (PMF)&FGAtmosphere::GetGustNED,
- (PMFd)&FGAtmosphere::SetGustNED);
- PropertyManager->Tie("atmosphere/gust-down-fps", this, eDown, (PMF)&FGAtmosphere::GetGustNED,
- (PMFd)&FGAtmosphere::SetGustNED);
-
- PropertyManager->Tie("atmosphere/turb-north-fps", this, eNorth, (PMF)&FGAtmosphere::GetTurbNED,
- (PMFd)&FGAtmosphere::SetTurbNED);
- PropertyManager->Tie("atmosphere/turb-east-fps", this, eEast, (PMF)&FGAtmosphere::GetTurbNED,
- (PMFd)&FGAtmosphere::SetTurbNED);
- PropertyManager->Tie("atmosphere/turb-down-fps", this, eDown, (PMF)&FGAtmosphere::GetTurbNED,
- (PMFd)&FGAtmosphere::SetTurbNED);
-
- PropertyManager->Tie("atmosphere/p-turb-rad_sec", this,1, (PMF)&FGAtmosphere::GetTurbPQR);
- PropertyManager->Tie("atmosphere/q-turb-rad_sec", this,2, (PMF)&FGAtmosphere::GetTurbPQR);
- PropertyManager->Tie("atmosphere/r-turb-rad_sec", this,3, (PMF)&FGAtmosphere::GetTurbPQR);
- PropertyManager->Tie("atmosphere/turb-type", this, (PMFt)&FGAtmosphere::GetTurbType, (PMFi)&FGAtmosphere::SetTurbType);
- PropertyManager->Tie("atmosphere/turb-rate", this, &FGAtmosphere::GetTurbRate, &FGAtmosphere::SetTurbRate);
- PropertyManager->Tie("atmosphere/turb-gain", this, &FGAtmosphere::GetTurbGain, &FGAtmosphere::SetTurbGain);
- PropertyManager->Tie("atmosphere/turb-rhythmicity", this, &FGAtmosphere::GetRhythmicity,
- &FGAtmosphere::SetRhythmicity);
+ PropertyManager->Tie("atmosphere/pressure-altitude", this, &FGAtmosphere::GetPressureAltitude);
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
}
}
if (debug_lvl & 2 ) { // Instantiation/Destruction notification
- if (from == 0) cout << "Instantiated: FGAtmosphere" << endl;
- if (from == 1) cout << "Destroyed: FGAtmosphere" << endl;
+ if (from == 0) std::cout << "Instantiated: FGAtmosphere" << std::endl;
+ if (from == 1) std::cout << "Destroyed: FGAtmosphere" << std::endl;
}
if (debug_lvl & 4 ) { // Run() method entry print for FGModel-derived objects
}
}
if (debug_lvl & 16) { // Sanity checking
}
- if (debug_lvl & 128) { // Turbulence
- if (first_pass && from == 2) {
- first_pass = false;
- cout << "vTurbulenceNED(X), vTurbulenceNED(Y), vTurbulenceNED(Z), "
- << "vTurbulenceGrad(X), vTurbulenceGrad(Y), vTurbulenceGrad(Z), "
- << "vDirection(X), vDirection(Y), vDirection(Z), "
- << "Magnitude, "
- << "vTurbPQR(P), vTurbPQR(Q), vTurbPQR(R), " << endl;
- }
- if (from == 2) {
- cout << vTurbulenceNED << ", " << vTurbulenceGrad << ", " << vDirection << ", " << Magnitude << ", " << vTurbPQR << endl;
- }
+ if (debug_lvl & 128) { //
}
if (debug_lvl & 64) {
if (from == 0) { // Constructor
- cout << IdSrc << endl;
- cout << IdHdr << endl;
+ std::cout << IdSrc << std::endl;
+ std::cout << IdHdr << std::endl;
}
}
}
projects / flightgear.git / blobdiff