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Sync'ed JSBSim

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- Now all the sea level properties from the standard atmosphere are updated along with the other atmosphere properties.
- The properties propulsion/start_cmd and propulsion/cutoff_cmd are now read/write (they were read only before).
This commit is contained in:
Bertrand Coconnier 2018-07-07 18:34:19 +02:00
parent 7178b3ef6a
commit 64f3c1d3b6
8 changed files with 104 additions and 39 deletions
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9
src/FDM/JSBSim/models/FGAtmosphere.cpp
View file

@ -94,12 +94,7 @@ bool FGAtmosphere::InitModel(void)
SLtemperature = Temperature = 518.67;
SLpressure = Pressure = 2116.228;
SLdensity = Density = Pressure/(Reng*Temperature);
SLsoundspeed = Soundspeed = sqrt(SHRatio*Reng*(Temperature));
rSLtemperature = 1/SLtemperature ;
rSLpressure = 1/SLpressure ;
rSLdensity = 1/SLdensity ;
rSLsoundspeed = 1/SLsoundspeed ;
SLsoundspeed = Soundspeed = sqrt(SHRatio*Reng*Temperature);
return true;
}
@ -137,7 +132,7 @@ void FGAtmosphere::Calculate(double altitude)
else
Density = node->GetDouble("atmosphere/override/density");
Soundspeed = sqrt(SHRatio*Reng*(Temperature));
Soundspeed = sqrt(SHRatio*Reng*Temperature);
PressureAltitude = CalculatePressureAltitude(Pressure, altitude);
DensityAltitude = CalculateDensityAltitude(Density, altitude);

13
src/FDM/JSBSim/models/FGAtmosphere.h
View file

@ -116,15 +116,15 @@ public:
/// Returns the actual, modeled sea level temperature in degrees Rankine.
/// @return The modeled temperature in degrees Rankine at sea level.
virtual double GetTemperatureSL() const { return GetTemperature(0.0); }
virtual double GetTemperatureSL() const { return SLtemperature; }
/// Returns the ratio of the at-current-altitude temperature as modeled
/// over the sea level value.
virtual double GetTemperatureRatio() const { return GetTemperature()*rSLtemperature; }
virtual double GetTemperatureRatio() const { return GetTemperature()/SLtemperature; }
/// Returns the ratio of the temperature as modeled at the supplied altitude
/// over the sea level value.
virtual double GetTemperatureRatio(double h) const { return GetTemperature(h)*rSLtemperature; }
virtual double GetTemperatureRatio(double h) const { return GetTemperature(h)/SLtemperature; }
/// Sets the Sea Level temperature.
/// @param t the temperature value in the unit provided.
@ -151,7 +151,7 @@ public:
virtual double GetPressureSL(ePressure to=ePSF) const { return ConvertFromPSF(SLpressure, to); }
/// Returns the ratio of at-altitude pressure over the sea level value.
virtual double GetPressureRatio(void) const { return Pressure*rSLpressure; }
virtual double GetPressureRatio(void) const { return Pressure/SLpressure; }
/** Sets the sea level pressure for modeling.
@param pressure The pressure in the units specified.
@ -174,7 +174,7 @@ public:
virtual double GetDensitySL(void) const { return SLdensity; }
/// Returns the ratio of at-altitude density over the sea level value.
virtual double GetDensityRatio(void) const { return Density*rSLdensity; }
virtual double GetDensityRatio(void) const { return Density/SLdensity; }
//@}
// *************************************************************************
@ -190,7 +190,7 @@ public:
virtual double GetSoundSpeedSL(void) const { return SLsoundspeed; }
/// Returns the ratio of at-altitude sound speed over the sea level value.
virtual double GetSoundSpeedRatio(void) const { return Soundspeed*rSLsoundspeed; }
virtual double GetSoundSpeedRatio(void) const { return Soundspeed/SLsoundspeed; }
//@}
// *************************************************************************
@ -214,7 +214,6 @@ public:
protected:
double SLtemperature, SLdensity, SLpressure, SLsoundspeed; // Sea level conditions
double Temperature, Density, Pressure, Soundspeed; // Current actual conditions at altitude
double rSLtemperature, rSLdensity, rSLpressure, rSLsoundspeed; // Reciprocal of sea level conditions
double PressureAltitude;
double DensityAltitude;

57
src/FDM/JSBSim/models/FGPropulsion.cpp
View file

@ -636,6 +636,21 @@ void FGPropulsion::SetStarter(int setting)
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
int FGPropulsion::GetStarter(void) const
{
if (ActiveEngine < 0) {
bool starter = true;
for (unsigned i=0; i<Engines.size(); i++)
starter &= Engines[i]->GetStarter();
return starter ? 1 : 0;
} else
return Engines[ActiveEngine]->GetStarter() ? 1: 0;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGPropulsion::SetCutoff(int setting)
{
bool bsetting = setting == 0 ? false : true;
@ -669,6 +684,42 @@ void FGPropulsion::SetCutoff(int setting)
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
int FGPropulsion::GetCutoff(void) const
{
if (ActiveEngine < 0) {
bool cutoff = true;
for (unsigned i=0; i<Engines.size(); i++) {
switch (Engines[i]->GetType()) {
case FGEngine::etTurbine:
cutoff &= ((FGTurbine*)Engines[i])->GetCutoff();
break;
case FGEngine::etTurboprop:
cutoff &= ((FGTurboProp*)Engines[i])->GetCutoff();
break;
default:
return -1;
}
}
return cutoff ? 1 : 0;
} else {
switch (Engines[ActiveEngine]->GetType()) {
case FGEngine::etTurbine:
return ((FGTurbine*)Engines[ActiveEngine])->GetCutoff() ? 1 : 0;
case FGEngine::etTurboprop:
return ((FGTurboProp*)Engines[ActiveEngine])->GetCutoff() ? 1 : 0;
break;
default:
break;
}
}
return -1;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGPropulsion::SetActiveEngine(int engine)
{
if (engine >= (int)Engines.size() || engine < 0)
@ -760,12 +811,12 @@ void FGPropulsion::bind(void)
IsBound = true;
PropertyManager->Tie("propulsion/set-running", this, (iPMF)0, &FGPropulsion::InitRunning, false);
if (HaveTurbineEngine || HaveTurboPropEngine) {
PropertyManager->Tie("propulsion/starter_cmd", this, (iPMF)0, &FGPropulsion::SetStarter, false);
PropertyManager->Tie("propulsion/cutoff_cmd", this, (iPMF)0, &FGPropulsion::SetCutoff, false);
PropertyManager->Tie("propulsion/starter_cmd", this, &FGPropulsion::GetStarter, &FGPropulsion::SetStarter);
PropertyManager->Tie("propulsion/cutoff_cmd", this, &FGPropulsion::GetCutoff, &FGPropulsion::SetCutoff);
}
if (HavePistonEngine) {
PropertyManager->Tie("propulsion/starter_cmd", this, (iPMF)0, &FGPropulsion::SetStarter, false);
PropertyManager->Tie("propulsion/starter_cmd", this, &FGPropulsion::GetStarter, &FGPropulsion::SetStarter);
PropertyManager->Tie("propulsion/magneto_cmd", this, (iPMF)0, &FGPropulsion::SetMagnetos, false);
}

2
src/FDM/JSBSim/models/FGPropulsion.h
View file

@ -179,7 +179,9 @@ public:
void SetMagnetos(int setting);
void SetStarter(int setting);
int GetStarter(void) const;
void SetCutoff(int setting=0);
int GetCutoff(void) const;
void SetActiveEngine(int engine);
void SetFuelFreeze(bool f);
const FGMatrix33& CalculateTankInertias(void);

8
src/FDM/JSBSim/models/atmosphere/FGMSIS.cpp
View file

@ -143,10 +143,6 @@ bool MSIS::InitModel(void)
// SLpressure = intPressure = 2116.7;
// SLdensity = intDensity = 0.002378;
// SLsoundspeed = sqrt(2403.0832 * SLtemperature);
// rSLtemperature = 1.0/intTemperature;
// rSLpressure = 1.0/intPressure;
// rSLdensity = 1.0/intDensity;
// rSLsoundspeed = 1.0/SLsoundspeed;
return true;
}
@ -172,10 +168,6 @@ bool MSIS::Run(bool Holding)
SLdensity = output.d[5] * 1.940321;
SLpressure = 1716.488 * SLdensity * SLtemperature;
SLsoundspeed = sqrt(2403.0832 * SLtemperature);
rSLtemperature = 1.0/SLtemperature;
rSLpressure = 1.0/SLpressure;
rSLdensity = 1.0/SLdensity;
rSLsoundspeed = 1.0/SLsoundspeed;
// get at-altitude values
Calculate(FDMExec->GetAuxiliary()->GetDayOfYear(),

37
src/FDM/JSBSim/models/atmosphere/FGStandardAtmosphere.cpp
View file

@ -146,11 +146,6 @@ bool FGStandardAtmosphere::InitModel(void)
StdSLsoundspeed = SLsoundspeed = Soundspeed;
rSLtemperature = 1/SLtemperature ;
rSLpressure = 1/SLpressure ;
rSLdensity = 1/SLdensity ;
rSLsoundspeed = 1/SLsoundspeed ;
// PrintStandardAtmosphereTable();
return true;
@ -211,11 +206,19 @@ void FGStandardAtmosphere::SetPressureSL(ePressure unit, double pressure)
{
double press = ConvertToPSF(pressure, unit);
PressureBreakpoints[0] = press;
SLpressure = PressureBreakpoints[0];
SLpressure = press;
CalculateSLDensity();
CalculatePressureBreakpoints();
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGStandardAtmosphere::CalculateSLSoundSpeedAndDensity(void)
{
SLsoundspeed = sqrt(SHRatio*Reng*SLtemperature);
CalculateSLDensity();
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
// Get the modeled temperature at a specified altitude, including any bias or gradient
// effects.
@ -349,6 +352,9 @@ void FGStandardAtmosphere::SetTemperature(double t, double h, eTemperature unit)
TemperatureBias -= TemperatureDeltaGradient * (GradientFadeoutAltitude - GeoPotAlt);
CalculatePressureBreakpoints();
SLtemperature = GetTemperature(0.0);
CalculateSLSoundSpeedAndDensity();
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
@ -360,6 +366,9 @@ void FGStandardAtmosphere::SetTemperatureBias(eTemperature unit, double t)
TemperatureBias = t;
CalculatePressureBreakpoints();
SLtemperature = GetTemperature(0.0);
CalculateSLSoundSpeedAndDensity();
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
@ -396,6 +405,9 @@ void FGStandardAtmosphere::SetTemperatureGradedDelta(double deltemp, double h, e
TemperatureDeltaGradient = deltemp/(GradientFadeoutAltitude - GeopotentialAltitude(h));
CalculateLapseRates();
CalculatePressureBreakpoints();
SLtemperature = GetTemperature(0.0);
CalculateSLSoundSpeedAndDensity();
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
@ -443,6 +455,8 @@ void FGStandardAtmosphere::CalculateLapseRates()
void FGStandardAtmosphere::CalculatePressureBreakpoints()
{
PressureBreakpoints[0] = SLpressure;
for (unsigned int b=0; b<PressureBreakpoints.size()-1; b++) {
double BaseTemp = StdAtmosTemperatureTable(b+1,1);
double BaseAlt = StdAtmosTemperatureTable(b+1,0);
@ -469,13 +483,17 @@ void FGStandardAtmosphere::ResetSLTemperature()
TemperatureBias = TemperatureDeltaGradient = 0.0;
CalculateLapseRates();
CalculatePressureBreakpoints();
SLtemperature = StdSLtemperature;
CalculateSLSoundSpeedAndDensity();
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGStandardAtmosphere::ResetSLPressure()
{
PressureBreakpoints[0] = StdSLpressure; // psf
SLpressure = StdSLpressure;
CalculateSLDensity();
CalculatePressureBreakpoints();
}
@ -484,9 +502,8 @@ void FGStandardAtmosphere::ResetSLPressure()
void FGStandardAtmosphere::CalculateStdDensityBreakpoints()
{
StdDensityBreakpoints.clear();
for (unsigned int i = 0; i < StdPressureBreakpoints.size(); i++) {
for (unsigned int i = 0; i < StdPressureBreakpoints.size(); i++)
StdDensityBreakpoints.push_back(StdPressureBreakpoints[i] / (Reng * StdAtmosTemperatureTable(i + 1, 1)));
}
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

10
src/FDM/JSBSim/models/atmosphere/FGStandardAtmosphere.h
View file

@ -125,11 +125,11 @@ public:
/// Returns the standard sea level temperature in degrees Rankine.
/// @return The STANDARD temperature at sea level in degrees Rankine.
virtual double GetStdTemperatureSL() const { return GetStdTemperature(0.0); }
virtual double GetStdTemperatureSL() const { return StdSLtemperature; }
/// Returns the ratio of the standard temperature at the supplied altitude
/// over the standard sea level temperature.
virtual double GetStdTemperatureRatio(double h) const { return GetStdTemperature(h)*rSLtemperature; }
virtual double GetStdTemperatureRatio(double h) const { return GetStdTemperature(h)/StdSLtemperature; }
/// Returns the temperature bias over the sea level value in degrees Rankine.
virtual double GetTemperatureBias(eTemperature to) const
@ -329,6 +329,12 @@ protected:
/// Calculate the pressure of water vapor with the Magnus formula.
double CalculateVaporPressure(double temperature);
/// Calculate the SL density
void CalculateSLDensity(void) { SLdensity = SLpressure / (Reng * SLtemperature); }
/// Calculate the SL density and sound speed
void CalculateSLSoundSpeedAndDensity(void);
virtual void bind(void);
void Debug(int from);

5
src/FDM/JSBSim/models/propulsion/FGPropeller.cpp
View file

@ -255,7 +255,10 @@ double FGPropeller::Calculate(double EnginePower)
double tangentialVel = localAeroVel.Magnitude(eV, eW);
if (tangentialVel > 0.0001) {
double angle = atan2(tangentialVel, localAeroVel(eU) + Vinduced);
// The angle made locally by the air flow with respect to the propeller
// axis is influenced by the induced velocity. This attenuates the
// influence of a string cross wind and gives a more realistic behavior.
double angle = atan2(tangentialVel, Vel+Vinduced);
double factor = Sense * P_Factor * angle / tangentialVel;
SetActingLocationY( GetLocationY() + factor * localAeroVel(eW));
SetActingLocationZ( GetLocationZ() + factor * localAeroVel(eV));