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Sync. with JSBSim CVS

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This commit is contained in:
ehofman 2009-01-26 20:36:17 +00:00 committed by Tim Moore
parent 0c5e9f46e7
commit 3cb45f4989
31 changed files with 352 additions and 317 deletions
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3
src/FDM/JSBSim/FGFDMExec.cpp
View file

@ -572,6 +572,9 @@ void FGFDMExec::BuildPropertyCatalog(struct PropertyCatalogStructure* pcs)
sprintf(int_buf, "[%d]", node_idx);
if (node_idx != 0) pcsNew->base_string += string(int_buf);
if (pcs->node->getChild(i)->nChildren() == 0) {
if (pcsNew->base_string.substr(0,11) == string("/fdm/jsbsim")) {
pcsNew->base_string = pcsNew->base_string.erase(0,12);
}
PropertyCatalog.push_back(pcsNew->base_string);
} else {
pcsNew->node = (FGPropertyManager*)pcs->node->getChild(i);

4
src/FDM/JSBSim/JSBSim.cxx
View file

@ -282,6 +282,10 @@ FGJSBsim::FGJSBsim( double dt )
fgGetDouble("/fdm/jsbsim/systems/hook/tailhook-offset-y-in", 0),
fgGetDouble("/fdm/jsbsim/systems/hook/tailhook-offset-z-in", -16));
// Untie the write-state-file property to avoid creating an initfile.xml
// file on each reset.
fgGetNode("/fdm/jsbsim/simulation/write-state-file")->untie();
crashed = false;
}

13
src/FDM/JSBSim/initialization/FGInitialCondition.cpp
View file

@ -156,7 +156,13 @@ void FGInitialCondition::InitializeIC(void)
void FGInitialCondition::WriteStateFile(int num)
{
string filename = fdmex->GetFullAircraftPath() + "/" + "initfile.xml";
string filename = fdmex->GetFullAircraftPath();
if (filename.empty())
filename = "initfile.xml";
else
filename.append("/initfile.xml");
ofstream outfile(filename.c_str());
FGPropagate* Propagate = fdmex->GetPropagate();
@ -173,11 +179,10 @@ void FGInitialCondition::WriteStateFile(int num)
outfile << " <latitude unit=\"DEG\"> " << Propagate->GetLatitudeDeg() << " </latitude>" << endl;
outfile << " <altitude unit=\"FT\"> " << Propagate->Geth() << " </altitude>" << endl;
outfile << "</initialize>" << endl;
outfile.close();
} else {
cerr << "Could not open and/or write the state to the initial conditions file." << endl;
cerr << "Could not open and/or write the state to the initial conditions file: " << filename << endl;
}
outfile.close();
}
//******************************************************************************

125
src/FDM/JSBSim/input_output/FGScript.cpp
View file

@ -46,7 +46,6 @@ INCLUDES
#include <initialization/FGTrim.h>
#include <iostream>
#include <iterator>
namespace JSBSim {
@ -204,12 +203,17 @@ bool FGScript::LoadScript( string script )
// Retrieve the event name if given
newEvent->Name = event_element->GetAttributeValue("name");
// Is this event persistent? That is, does it execute repeatedly as long as the
// condition is true, or does it execute as a one-shot event, only?
// Is this event persistent? That is, does it execute every time the
// condition triggers to true, or does it execute as a one-shot event, only?
if (event_element->GetAttributeValue("persistent") == string("true")) {
newEvent->Persistent = true;
}
// Does this event execute continuously when triggered to true?
if (event_element->GetAttributeValue("continuous") == string("true")) {
newEvent->Continuous = true;
}
// Process the conditions
condition_element = event_element->FindElement("condition");
if (condition_element != 0) {
@ -304,7 +308,6 @@ bool FGScript::LoadScript( string script )
bool FGScript::RunScript(void)
{
vector <struct event>::iterator iEvent = Events.begin();
unsigned i, j;
unsigned event_ctr = 0;
@ -314,90 +317,98 @@ bool FGScript::RunScript(void)
if (currentTime > EndTime) return false; //Script done!
// Iterate over all events.
while (iEvent < Events.end()) {
iEvent->PrevTriggered = iEvent->Triggered;
for (unsigned int ev_ctr=0; ev_ctr < Events.size(); ev_ctr++) {
// Determine whether the set of conditional tests for this condition equate
// to true and should cause the event to execute.
if (iEvent->Condition->Evaluate()) {
if (!iEvent->Triggered) {
// to true and should cause the event to execute. If the conditions evaluate
// to true, then the event is triggered. If the event is not persistent,
// then this trigger will remain set true. If the event is persistent,
// the trigger will reset to false when the condition evaluates to false.
if (Events[ev_ctr].Condition->Evaluate()) {
if (!Events[ev_ctr].Triggered) {
// The conditions are true, do the setting of the desired Event parameters
for (i=0; i<iEvent->SetValue.size(); i++) {
iEvent->OriginalValue[i] = iEvent->SetParam[i]->getDoubleValue();
if (iEvent->Functions[i] != 0) { // Parameter should be set to a function value
iEvent->SetValue[i] = iEvent->Functions[i]->GetValue();
for (i=0; i<Events[ev_ctr].SetValue.size(); i++) {
Events[ev_ctr].OriginalValue[i] = Events[ev_ctr].SetParam[i]->getDoubleValue();
if (Events[ev_ctr].Functions[i] != 0) { // Parameter should be set to a function value
Events[ev_ctr].SetValue[i] = Events[ev_ctr].Functions[i]->GetValue();
}
switch (iEvent->Type[i]) {
switch (Events[ev_ctr].Type[i]) {
case FG_VALUE:
case FG_BOOL:
iEvent->newValue[i] = iEvent->SetValue[i];
Events[ev_ctr].newValue[i] = Events[ev_ctr].SetValue[i];
break;
case FG_DELTA:
iEvent->newValue[i] = iEvent->OriginalValue[i] + iEvent->SetValue[i];
Events[ev_ctr].newValue[i] = Events[ev_ctr].OriginalValue[i] + Events[ev_ctr].SetValue[i];
break;
default:
cerr << "Invalid Type specified" << endl;
break;
}
iEvent->StartTime = currentTime + iEvent->Delay;
iEvent->ValueSpan[i] = iEvent->newValue[i] - iEvent->OriginalValue[i];
iEvent->Transiting[i] = true;
Events[ev_ctr].StartTime = currentTime + Events[ev_ctr].Delay;
Events[ev_ctr].ValueSpan[i] = Events[ev_ctr].newValue[i] - Events[ev_ctr].OriginalValue[i];
Events[ev_ctr].Transiting[i] = true;
}
}
iEvent->Triggered = true;
} else if (iEvent->Persistent) {
iEvent->Triggered = false; // Reset the trigger for persistent events
iEvent->Notified = false; // Also reset the notification flag
Events[ev_ctr].Triggered = true;
} else if (Events[ev_ctr].Persistent) { // If the event is persistent, reset the trigger.
Events[ev_ctr].Triggered = false; // Reset the trigger for persistent events
Events[ev_ctr].Notified = false; // Also reset the notification flag
}
if ((currentTime >= iEvent->StartTime) && iEvent->Triggered) {
if ((currentTime >= Events[ev_ctr].StartTime) && Events[ev_ctr].Triggered) {
for (i=0; i<iEvent->SetValue.size(); i++) {
if (iEvent->Transiting[i]) {
iEvent->TimeSpan = currentTime - iEvent->StartTime;
if (iEvent->Functions[i] == 0) {
switch (iEvent->Action[i]) {
case FG_RAMP:
if (iEvent->TimeSpan <= iEvent->TC[i]) {
newSetValue = iEvent->TimeSpan/iEvent->TC[i] * iEvent->ValueSpan[i] + iEvent->OriginalValue[i];
} else {
newSetValue = iEvent->newValue[i];
iEvent->Transiting[i] = false;
}
break;
case FG_STEP:
newSetValue = iEvent->newValue[i];
iEvent->Transiting[i] = false;
break;
case FG_EXP:
newSetValue = (1 - exp( -iEvent->TimeSpan/iEvent->TC[i] )) * iEvent->ValueSpan[i] + iEvent->OriginalValue[i];
break;
default:
cerr << "Invalid Action specified" << endl;
break;
for (i=0; i<Events[ev_ctr].SetValue.size(); i++) {
if (Events[ev_ctr].Transiting[i]) {
Events[ev_ctr].TimeSpan = currentTime - Events[ev_ctr].StartTime;
switch (Events[ev_ctr].Action[i]) {
case FG_RAMP:
if (Events[ev_ctr].TimeSpan <= Events[ev_ctr].TC[i]) {
newSetValue = Events[ev_ctr].TimeSpan/Events[ev_ctr].TC[i] * Events[ev_ctr].ValueSpan[i] + Events[ev_ctr].OriginalValue[i];
} else {
newSetValue = Events[ev_ctr].newValue[i];
if (Events[ev_ctr].Continuous != true) Events[ev_ctr].Transiting[i] = false;
}
} else { // Set the new value based on a function
newSetValue = iEvent->Functions[i]->GetValue();
break;
case FG_STEP:
newSetValue = Events[ev_ctr].newValue[i];
// If this is not a continuous event, reset the transiting flag.
// Otherwise, it is known that the event is a continuous event.
// Furthermore, if the event is to be determined by a function,
// then the function will be continuously calculated.
if (Events[ev_ctr].Continuous != true)
Events[ev_ctr].Transiting[i] = false;
else if (Events[ev_ctr].Functions[i] != 0)
newSetValue = Events[ev_ctr].Functions[i]->GetValue();
break;
case FG_EXP:
newSetValue = (1 - exp( -Events[ev_ctr].TimeSpan/Events[ev_ctr].TC[i] )) * Events[ev_ctr].ValueSpan[i] + Events[ev_ctr].OriginalValue[i];
break;
default:
cerr << "Invalid Action specified" << endl;
break;
}
iEvent->SetParam[i]->setDoubleValue(newSetValue);
Events[ev_ctr].SetParam[i]->setDoubleValue(newSetValue);
}
}
// Print notification values after setting them
if (iEvent->Notify && !iEvent->Notified) {
cout << endl << " Event " << event_ctr << " (" << iEvent->Name << ")"
if (Events[ev_ctr].Notify && !Events[ev_ctr].Notified) {
cout << endl << " Event " << event_ctr << " (" << Events[ev_ctr].Name << ")"
<< " executed at time: " << currentTime << endl;
for (j=0; j<iEvent->NotifyProperties.size();j++) {
cout << " " << iEvent->NotifyProperties[j]->GetName()
<< " = " << iEvent->NotifyProperties[j]->getDoubleValue() << endl;
for (j=0; j<Events[ev_ctr].NotifyProperties.size();j++) {
cout << " " << Events[ev_ctr].NotifyProperties[j]->GetName()
<< " = " << Events[ev_ctr].NotifyProperties[j]->getDoubleValue() << endl;
}
cout << endl;
iEvent->Notified = true;
Events[ev_ctr].Notified = true;
}
}
iEvent++;
event_ctr++;
}
return true;

16
src/FDM/JSBSim/input_output/FGScript.h
View file

@ -70,13 +70,14 @@ CLASS DOCUMENTATION
format. A test condition (or conditions) can be set up in an event in a
script and when the condition evaluates to true, the specified
action[s] is/are taken. An event can be <em>persistent</em>,
meaning that at all times when the test condition evaluates to true
the specified <em>set</em> actions take place. When the set of
tests evaluates to true for a given
meaning that at every time the test condition first evaluates to true
(toggling from false to true) then the specified <em>set</em> actions take
place. An event can also be defined to execute or evaluate continuously
while the condition is true. When the set of tests evaluates to true for a given
condition, an item may be set to another value. This value may
be a value, or a delta value, and the change from the
current value to the new value can be either via a step function,
a ramp, or an exponential approach. The speed of a ramp or
current value to the new value can be either via a step action,
a ramp, or an exponential approach. The speed of a ramp or exponential
approach is specified via the time constant. Here is an example
illustrating the format of the script file:
@ -204,8 +205,8 @@ private:
struct event {
FGCondition *Condition;
bool Persistent;
bool Continuous;
bool Triggered;
bool PrevTriggered;
bool Notify;
bool Notified;
double Delay;
@ -226,8 +227,8 @@ private:
event() {
Triggered = false;
PrevTriggered = false;
Persistent = false;
Continuous = false;
Delay = 0.0;
Notify = Notified = false;
Name = "";
@ -237,7 +238,6 @@ private:
void reset(void) {
Triggered = false;
PrevTriggered = false;
Notified = false;
StartTime = 0.0;
}

4
src/FDM/JSBSim/math/FGColumnVector3.cpp
View file

@ -52,7 +52,7 @@ CLASS IMPLEMENTATION
FGColumnVector3::FGColumnVector3(void)
{
data[0] = data[1] = data[2] = 0.0;
Debug(0);
// Debug(0);
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
@ -60,7 +60,7 @@ FGColumnVector3::FGColumnVector3(void)
string FGColumnVector3::Dump(string delimeter) const
{
char buffer[256];
sprintf(buffer, "%10.3e%s%10.3e%s%10.3e", Entry(1), delimeter.c_str(), Entry(2), delimeter.c_str(), Entry(3));
sprintf(buffer, "%13.6e%s%13.6e%s%13.6e", Entry(1), delimeter.c_str(), Entry(2), delimeter.c_str(), Entry(3));
return string(buffer);
}

2
src/FDM/JSBSim/math/FGMatrix33.cpp
View file

@ -56,7 +56,7 @@ FGMatrix33::FGMatrix33(void)
data[0] = data[1] = data[2] = data[3] = data[4] = data[5] =
data[6] = data[7] = data[8] = 0.0;
Debug(0);
// Debug(0);
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

17
src/FDM/JSBSim/models/FGAircraft.cpp
View file

@ -140,7 +140,7 @@ bool FGAircraft::Run(void)
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
double FGAircraft::GetNlf(void)
double FGAircraft::GetNlf(void) const
{
return -1*Aerodynamics->GetvFw(3)/MassBalance->GetWeight();
}
@ -216,13 +216,6 @@ void FGAircraft::bind(void)
PropertyManager->Tie("metrics/lv-norm", this, &FGAircraft::Getlbarv);
PropertyManager->Tie("metrics/vbarh-norm", this, &FGAircraft::Getvbarh);
PropertyManager->Tie("metrics/vbarv-norm", this, &FGAircraft::Getvbarv);
PropertyManager->Tie("forces/hold-down", this, &FGAircraft::GetHoldDown, &FGAircraft::SetHoldDown);
PropertyManager->Tie("moments/l-total-lbsft", this, eL, (PMF)&FGAircraft::GetMoments);
PropertyManager->Tie("moments/m-total-lbsft", this, eM, (PMF)&FGAircraft::GetMoments);
PropertyManager->Tie("moments/n-total-lbsft", this, eN, (PMF)&FGAircraft::GetMoments);
PropertyManager->Tie("forces/fbx-total-lbs", this, eX, (PMF)&FGAircraft::GetForces);
PropertyManager->Tie("forces/fby-total-lbs", this, eY, (PMF)&FGAircraft::GetForces);
PropertyManager->Tie("forces/fbz-total-lbs", this, eZ, (PMF)&FGAircraft::GetForces);
PropertyManager->Tie("metrics/aero-rp-x-in", this, eX, (PMF)&FGAircraft::GetXYZrp);
PropertyManager->Tie("metrics/aero-rp-y-in", this, eY, (PMF)&FGAircraft::GetXYZrp);
PropertyManager->Tie("metrics/aero-rp-z-in", this, eZ, (PMF)&FGAircraft::GetXYZrp);
@ -232,6 +225,14 @@ void FGAircraft::bind(void)
PropertyManager->Tie("metrics/visualrefpoint-x-in", this, eX, (PMF)&FGAircraft::GetXYZvrp);
PropertyManager->Tie("metrics/visualrefpoint-y-in", this, eY, (PMF)&FGAircraft::GetXYZvrp);
PropertyManager->Tie("metrics/visualrefpoint-z-in", this, eZ, (PMF)&FGAircraft::GetXYZvrp);
PropertyManager->Tie("forces/fbx-total-lbs", this, eX, (PMF)&FGAircraft::GetForces);
PropertyManager->Tie("forces/fby-total-lbs", this, eY, (PMF)&FGAircraft::GetForces);
PropertyManager->Tie("forces/fbz-total-lbs", this, eZ, (PMF)&FGAircraft::GetForces);
PropertyManager->Tie("forces/load-factor", this, &FGAircraft::GetNlf);
PropertyManager->Tie("forces/hold-down", this, &FGAircraft::GetHoldDown, &FGAircraft::SetHoldDown);
PropertyManager->Tie("moments/l-total-lbsft", this, eL, (PMF)&FGAircraft::GetMoments);
PropertyManager->Tie("moments/m-total-lbsft", this, eM, (PMF)&FGAircraft::GetMoments);
PropertyManager->Tie("moments/n-total-lbsft", this, eN, (PMF)&FGAircraft::GetMoments);
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

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

@ -171,7 +171,7 @@ public:
void SetWingArea(double S) {WingArea = S;}
double GetNlf(void);
double GetNlf(void) const;
inline FGColumnVector3& GetNwcg(void) { return vNwcg; }

78
src/FDM/JSBSim/models/FGAtmosphere.cpp
View file

@ -71,13 +71,13 @@ FGAtmosphere::FGAtmosphere(FGFDMExec* fdmex) : FGModel(fdmex)
h = 0.0;
psiw = 0.0;
htab[0]=0;
htab[1]=36089.239;
htab[2]=65616.798;
htab[3]=104986.878;
htab[4]=154199.475;
htab[5]=170603.675;
htab[6]=200131.234;
htab[7]=259186.352; //ft.
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 );
@ -86,6 +86,8 @@ FGAtmosphere::FGAtmosphere(FGFDMExec* fdmex) : FGModel(fdmex)
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;
@ -174,52 +176,57 @@ void FGAtmosphere::Calculate(double altitude)
}
switch(i) {
case 1: // 36089 ft.
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;
refpress = 472.452;
reftemp = 389.97; // in degrees Rankine, 216.65 Kelvin
refpress = 472.763;
//refdens = 0.000706032;
break;
case 2: // 65616 ft.
case 2: // 65616 ft. or 20 km
slope = 0.00054864;
reftemp = 389.97;
reftemp = 389.97; // in degrees Rankine, 216.65 Kelvin
refpress = 114.636;
//refdens = 0.000171306;
break;
case 3: // 104986 ft.
slope = 0.00153619;
reftemp = 411.57;
refpress = 8.36364;
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.
case 4: // 154199 ft. 47 km
slope = 0;
reftemp = 487.17;
refpress = 0.334882;
reftemp = 487.17; // in degrees Rankine, 270.65 Kelvin
refpress = 2.316;
//refdens = 4.00585e-7;
break;
case 5: // 170603 ft.
slope = -0.00109728;
reftemp = 487.17;
refpress = 0.683084;
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: // 200131 ft.
slope = -0.00219456;
reftemp = 454.17;
refpress = 0.00684986;
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: // 259186 ft.
case 7: // 278385 ft. or 84.8520 km
slope = 0;
reftemp = 325.17;
refpress = 0.000122276;
reftemp = 336.5; // in degrees Rankine, 186.94 Kelvin
refpress = 0.00831;
//refdens = 2.19541e-10;
break;
case 0:
default: // sea level
slope = -0.00356616; // R/ft.
reftemp = 518.67; // R
reftemp = 518.67; // in degrees Rankine, 288.15 Kelvin
refpress = 2116.22; // psf
//refdens = 0.00237767; // slugs/cubic ft.
break;
@ -250,7 +257,7 @@ void FGAtmosphere::Calculate(double altitude)
intPressure = refpress*pow(intTemperature/reftemp,-Inertial->SLgravity()/(slope*Reng));
intDensity = intPressure/(Reng*intTemperature);
}
lastIndex=i;
}
@ -263,7 +270,7 @@ void FGAtmosphere::CalculateDerived(void)
T_dev = (*temperature) - GetTemperature(h);
density_altitude = h + T_dev * 66.7;
if (turbType == ttStandard || ttCulp) Turbulence();
if (turbType != ttNone) Turbulence();
vTotalWindNED = vWindNED + vGustNED + vTurbulenceNED;
@ -271,6 +278,9 @@ void FGAtmosphere::CalculateDerived(void)
if (psiw < 0) psiw += 2*M_PI;
soundspeed = sqrt(SHRatio*Reng*(*temperature));
intViscosity = Beta * pow(intTemperature, 1.5) / (SutherlandConstant + intTemperature);
intKinematicViscosity = intViscosity / intDensity;
}

5
src/FDM/JSBSim/models/FGAtmosphere.h
View file

@ -100,6 +100,10 @@ public:
double GetDensity(double altitude);
/// Returns the speed of sound in ft/sec.
double GetSoundSpeed(void) const {return soundspeed;}
/// Returns the absolute viscosity.
double GetAbsoluteViscosity(void) const {return intViscosity;}
/// Returns the kinematic viscosity.
double GetKinematicViscosity(void) const {return intKinematicViscosity;}
/// Returns the sea level temperature in degrees Rankine.
double GetTemperatureSL(void) const { return SLtemperature; }
@ -237,6 +241,7 @@ protected:
bool useExternal;
double exTemperature,exDensity,exPressure;
double intTemperature, intDensity, intPressure;
double SutherlandConstant, Beta, intViscosity, intKinematicViscosity;
double T_dev_sl, T_dev, delta_T, density_altitude;
atmType atmosphere;
bool StandardTempOnly;

5
src/FDM/JSBSim/models/FGAuxiliary.cpp
View file

@ -71,6 +71,7 @@ FGAuxiliary::FGAuxiliary(FGFDMExec* fdmex) : FGModel(fdmex)
qbar = 0;
qbarUW = 0.0;
qbarUV = 0.0;
Re = 0.0;
Mach = 0.0;
alpha = beta = 0.0;
adot = bdot = 0.0;
@ -79,6 +80,7 @@ FGAuxiliary::FGAuxiliary(FGFDMExec* fdmex) : FGModel(fdmex)
day_of_year = 1;
seconds_in_day = 0.0;
hoverbmac = hoverbcg = 0.0;
tatc = RankineToCelsius(tat);
vPilotAccel.InitMatrix();
vPilotAccelN.InitMatrix();
@ -200,6 +202,8 @@ bool FGAuxiliary::Run()
alpha = beta = adot = bdot = 0;
}
Re = Vt * Aircraft->Getcbar() / Atmosphere->GetKinematicViscosity();
qbar = 0.5*Atmosphere->GetDensity()*Vt*Vt;
qbarUW = 0.5*Atmosphere->GetDensity()*(vAeroUVW(eU)*vAeroUVW(eU) + vAeroUVW(eW)*vAeroUVW(eW));
qbarUV = 0.5*Atmosphere->GetDensity()*(vAeroUVW(eU)*vAeroUVW(eU) + vAeroUVW(eV)*vAeroUVW(eV));
@ -349,6 +353,7 @@ void FGAuxiliary::bind(void)
PropertyManager->Tie("aero/alpha-deg", this, inDegrees, (PMF)&FGAuxiliary::Getalpha);
PropertyManager->Tie("aero/beta-deg", this, inDegrees, (PMF)&FGAuxiliary::Getbeta);
PropertyManager->Tie("aero/mag-beta-deg", this, inDegrees, (PMF)&FGAuxiliary::GetMagBeta);
PropertyManager->Tie("aero/Re", this, &FGAuxiliary::GetReynoldsNumber);
PropertyManager->Tie("aero/qbar-psf", this, &FGAuxiliary::Getqbar, &FGAuxiliary::Setqbar, true);
PropertyManager->Tie("aero/qbarUW-psf", this, &FGAuxiliary::GetqbarUW, &FGAuxiliary::SetqbarUW, true);
PropertyManager->Tie("aero/qbarUV-psf", this, &FGAuxiliary::GetqbarUV, &FGAuxiliary::SetqbarUV, true);

18
src/FDM/JSBSim/models/FGAuxiliary.h
View file

@ -181,14 +181,15 @@ public:
double GetMagBeta (int unit) const { if (unit == inDegrees) return fabs(beta)*radtodeg;
else cerr << "Bad units" << endl; return 0.0;}
double Getqbar (void) const { return qbar; }
double GetqbarUW (void) const { return qbarUW; }
double GetqbarUV (void) const { return qbarUV; }
double GetVt (void) const { return Vt; }
double GetVground (void) const { return Vground; }
double GetMach (void) const { return Mach; }
double GetMachU (void) const { return MachU; }
double GetNz (void) const { return Nz; }
double Getqbar (void) const { return qbar; }
double GetqbarUW (void) const { return qbarUW; }
double GetqbarUV (void) const { return qbarUV; }
double GetReynoldsNumber(void) const { return Re; }
double GetVt (void) const { return Vt; }
double GetVground (void) const { return Vground; }
double GetMach (void) const { return Mach; }
double GetMachU (void) const { return MachU; }
double GetNz (void) const { return Nz; }
double GetHOverBCG(void) const { return hoverbcg; }
double GetHOverBMAC(void) const { return hoverbmac; }
@ -247,6 +248,7 @@ private:
double Vt, Vground, Mach, MachU;
double qbar, qbarUW, qbarUV;
double Re; // Reynolds Number = V*c/mu
double alpha, beta;
double adot,bdot;
double psigt, gamma;

9
src/FDM/JSBSim/models/FGFCS.cpp
View file

@ -46,7 +46,6 @@ INCLUDES
#include <models/flight_control/FGDeadBand.h>
#include <models/flight_control/FGGain.h>
#include <models/flight_control/FGPID.h>
#include <models/flight_control/FGGradient.h>
#include <models/flight_control/FGSwitch.h>
#include <models/flight_control/FGSummer.h>
#include <models/flight_control/FGKinemat.h>
@ -514,6 +513,10 @@ bool FGFCS::Load(Element* el, SystemType systype)
return false;
} else {
document = LoadXMLDocument(file);
if (!document) {
cerr << "Error loading file " << file << endl;
return false;
}
name = document->GetAttributeValue("name");
}
} else {
@ -551,7 +554,7 @@ bool FGFCS::Load(Element* el, SystemType systype)
}
// After reading interface properties in a file, read properties in the local
// flight_control, autopiot, or system element. This allows general-purpose
// flight_control, autopilot, or system element. This allows general-purpose
// systems to be defined in a file, with overrides or initial loaded constants
// supplied in the relevant element of the aircraft configuration file.
@ -967,7 +970,7 @@ void FGFCS::Debug(int from)
if (debug_lvl & 1) { // Standard console startup message output
if (from == 2) { // Loader
cout << endl << " Flight Control (" << Name << ")" << endl;
cout << endl << " " << Name << endl;
}
}
if (debug_lvl & 2 ) { // Instantiation/Destruction notification

19
src/FDM/JSBSim/models/FGGroundReactions.cpp
View file

@ -89,17 +89,14 @@ bool FGGroundReactions::Run(void)
vForces.InitMatrix();
vMoments.InitMatrix();
// Sum forces and moments for all gear, here.
// Some optimizations may be made here - or rather in the gear code itself.
// The gear ::Run() method is called several times - once for each gear.
// Perhaps there is some commonality for things which only need to be
// calculated once.
if ( Propagate->GetDistanceAGL() < 300.0 ) { // Only execute gear code below 300 feet
for (unsigned int i=0; i<lGear.size(); i++) {
vForces += lGear[i]->Force();
vMoments += lGear[i]->Moment();
}
// Sum forces and moments for all gear, here.
// Some optimizations may be made here - or rather in the gear code itself.
// The gear ::Run() method is called several times - once for each gear.
// Perhaps there is some commonality for things which only need to be
// calculated once.
for (unsigned int i=0; i<lGear.size(); i++) {
vForces += lGear[i]->Force();
vMoments += lGear[i]->Moment();
}
return false;

14
src/FDM/JSBSim/models/FGInertial.cpp
View file

@ -54,7 +54,7 @@ FGInertial::FGInertial(FGFDMExec* fgex) : FGModel(fgex)
{
Name = "FGInertial";
// Defaults
// Earth defaults
RotationRate = 0.00007292115;
GM = 14.07644180E15; // WGS84 value
RadiusReference = 20925650.00; // Equatorial radius (WGS84)
@ -64,6 +64,18 @@ FGInertial::FGInertial(FGFDMExec* fgex) : FGModel(fgex)
b = 20855486.5951; // WGS84 semiminor axis length in feet
earthPosAngle = 0.0;
// Lunar defaults
/*
RotationRate = 0.0000026617;
GM = 1.7314079E14; // Lunar GM
RadiusReference = 5702559.05; // Equatorial radius
C2_0 = 0; // value for the C2,0 coefficient
J2 = 2.033542482111609E-4; // value for J2
a = 5702559.05; // semimajor axis length in feet
b = 5695439.63; // semiminor axis length in feet
earthPosAngle = 0.0;
*/
gAccelReference = GM/(RadiusReference*RadiusReference);
gAccel = GM/(RadiusReference*RadiusReference);

155
src/FDM/JSBSim/models/FGLGear.cpp
View file

@ -57,8 +57,9 @@ static const char *IdHdr = ID_LGEAR;
CLASS IMPLEMENTATION
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
FGLGear::FGLGear(Element* el, FGFDMExec* fdmex, int number) : Exec(fdmex),
GearNumber(number)
FGLGear::FGLGear(Element* el, FGFDMExec* fdmex, int number) :
GearNumber(number),
Exec(fdmex)
{
Element *force_table=0;
Element *dampCoeff=0;
@ -341,97 +342,96 @@ FGColumnVector3& FGLGear::Force(void)
if (isRetractable) ComputeRetractionState();
if (!GearDown) return vForce; // return the null vForce column vector
if (GearDown) {
vWhlBodyVec = MassBalance->StructuralToBody(vXYZ); // Get wheel in body frame
vLocalGear = Propagate->GetTb2l() * vWhlBodyVec; // Get local frame wheel location
vWhlBodyVec = MassBalance->StructuralToBody(vXYZ); // Get wheel in body frame
vLocalGear = Propagate->GetTb2l() * vWhlBodyVec; // Get local frame wheel location
gearLoc = Propagate->GetLocation().LocalToLocation(vLocalGear);
compressLength = -Exec->GetGroundCallback()->GetAGLevel(t, gearLoc, contact, normal, cvel);
gearLoc = Propagate->GetLocation().LocalToLocation(vLocalGear);
compressLength = -Exec->GetGroundCallback()->GetAGLevel(t, gearLoc, contact, normal, cvel);
// The compression length is measured in the Z-axis, only, at this time.
// The compression length is measured in the Z-axis, only, at this time.
if (compressLength > 0.00) {
if (compressLength > 0.00) {
WOW = true;
WOW = true;
// [The next equation should really use the vector to the contact patch of
// the tire including the strut compression and not the original vWhlBodyVec.]
// [The next equation should really use the vector to the contact patch of
// the tire including the strut compression and not the original vWhlBodyVec.]
vWhlVelVec = Propagate->GetTb2l() * (Propagate->GetPQR() * vWhlBodyVec);
vWhlVelVec += Propagate->GetVel() - cvel;
compressSpeed = vWhlVelVec(eZ);
vWhlVelVec = Propagate->GetTb2l() * (Propagate->GetPQR() * vWhlBodyVec);
vWhlVelVec += Propagate->GetVel() - cvel;
compressSpeed = vWhlVelVec(eZ);
InitializeReporting();
ComputeBrakeForceCoefficient();
ComputeSteeringAngle();
ComputeSlipAngle();
ComputeSideForceCoefficient();
ComputeVerticalStrutForce();
InitializeReporting();
ComputeBrakeForceCoefficient();
ComputeSteeringAngle();
ComputeSlipAngle();
ComputeSideForceCoefficient();
ComputeVerticalStrutForce();
// Compute the forces in the wheel ground plane.
// Compute the forces in the wheel ground plane.
double sign = RollingWhlVel>0?1.0:(RollingWhlVel<0?-1.0:0.0);
RollingForce = ((1.0 - TirePressureNorm) * 30 + vLocalForce(eZ) * BrakeFCoeff) * sign;
SideForce = vLocalForce(eZ) * FCoeff;
double sign = RollingWhlVel>0?1.0:(RollingWhlVel<0?-1.0:0.0);
RollingForce = ((1.0 - TirePressureNorm) * 30 + vLocalForce(eZ) * BrakeFCoeff) * sign;
SideForce = vLocalForce(eZ) * FCoeff;
// Transform these forces back to the local reference frame.
// Transform these forces back to the local reference frame.
vLocalForce(eX) = RollingForce*CosWheel - SideForce*SinWheel;
vLocalForce(eY) = SideForce*CosWheel + RollingForce*SinWheel;
vLocalForce(eX) = RollingForce*CosWheel - SideForce*SinWheel;
vLocalForce(eY) = SideForce*CosWheel + RollingForce*SinWheel;
// Transform the forces back to the body frame and compute the moment.
// Transform the forces back to the body frame and compute the moment.
vForce = Propagate->GetTl2b() * vLocalForce;
vForce = Propagate->GetTl2b() * vLocalForce;
// Start experimental section for gear jitter reduction
//
// Lag and attenuate the XY-plane forces dependent on velocity
// Lag and attenuate the XY-plane forces dependent on velocity
double ca, cb, denom;
FGColumnVector3 Output;
double ca, cb, denom;
FGColumnVector3 Output;
// This code implements a lag filter, C/(s + C) where
// "C" is the filter coefficient. When "C" is chosen at the
// frame rate (in Hz), the jittering is significantly reduced. This is because
// the jitter is present *at* the execution rate.
// If a coefficient is set to something equal to or less than zero, the filter
// is bypassed.
// This code implements a lag filter, C/(s + C) where
// "C" is the filter coefficient. When "C" is chosen at the
// frame rate (in Hz), the jittering is significantly reduced. This is because
// the jitter is present *at* the execution rate.
// If a coefficient is set to something equal to or less than zero, the filter
// is bypassed.
if (LongForceLagFilterCoeff > 0) {
denom = 2.00 + dT*LongForceLagFilterCoeff;
ca = dT*LongForceLagFilterCoeff / denom;
cb = (2.00 - dT*LongForceLagFilterCoeff) / denom;
Output(eX) = vForce(eX) * ca + prevIn(eX) * ca + prevOut(eX) * cb;
vForce(eX) = Output(eX);
if (LongForceLagFilterCoeff > 0) {
denom = 2.00 + dT*LongForceLagFilterCoeff;
ca = dT*LongForceLagFilterCoeff / denom;
cb = (2.00 - dT*LongForceLagFilterCoeff) / denom;
Output(eX) = vForce(eX) * ca + prevIn(eX) * ca + prevOut(eX) * cb;
vForce(eX) = Output(eX);
}
if (LatForceLagFilterCoeff > 0) {
denom = 2.00 + dT*LatForceLagFilterCoeff;
ca = dT*LatForceLagFilterCoeff / denom;
cb = (2.00 - dT*LatForceLagFilterCoeff) / denom;
Output(eY) = vForce(eY) * ca + prevIn(eY) * ca + prevOut(eY) * cb;
vForce(eY) = Output(eY);
}
prevIn = vForce;
prevOut = Output;
if ((fabs(RollingWhlVel) <= RFRV) && RFRV > 0) vForce(eX) *= fabs(RollingWhlVel)/RFRV;
if ((fabs(SideWhlVel) <= SFRV) && SFRV > 0) vForce(eY) *= fabs(SideWhlVel)/SFRV;
// End section for attentuating gear jitter
vMoment = vWhlBodyVec * vForce;
} else { // Gear is NOT compressed
WOW = false;
compressLength = 0.0;
// Return to neutral position between 1.0 and 0.8 gear pos.
SteerAngle *= max(GetGearUnitPos()-0.8, 0.0)/0.2;
ResetReporting();
}
if (LatForceLagFilterCoeff > 0) {
denom = 2.00 + dT*LatForceLagFilterCoeff;
ca = dT*LatForceLagFilterCoeff / denom;
cb = (2.00 - dT*LatForceLagFilterCoeff) / denom;
Output(eY) = vForce(eY) * ca + prevIn(eY) * ca + prevOut(eY) * cb;
vForce(eY) = Output(eY);
}
prevIn = vForce;
prevOut = Output;
if ((fabs(RollingWhlVel) <= RFRV) && RFRV > 0) vForce(eX) *= fabs(RollingWhlVel)/RFRV;
if ((fabs(SideWhlVel) <= SFRV) && SFRV > 0) vForce(eY) *= fabs(SideWhlVel)/SFRV;
// End section for attentuating gear jitter
vMoment = vWhlBodyVec * vForce;
} else { // Gear is NOT compressed
WOW = false;
compressLength = 0.0;
// Return to neutral position between 1.0 and 0.8 gear pos.
SteerAngle *= max(GetGearUnitPos()-0.8, 0.0)/0.2;
ResetReporting();
}
ReportTakeoffOrLanding();
@ -452,6 +452,7 @@ void FGLGear::ComputeRetractionState(void)
double gearPos = GetGearUnitPos();
if (gearPos < 0.01) {
GearUp = true;
WOW = false;
GearDown = false;
} else if (gearPos > 0.99) {
GearDown = true;
@ -575,7 +576,7 @@ void FGLGear::ReportTakeoffOrLanding(void)
LandingDistanceTraveled += Auxiliary->GetVground()*deltaT;
if (StartedGroundRun) {
TakeoffDistanceTraveled50ft += Auxiliary->GetVground()*deltaT;
TakeoffDistanceTraveled50ft += Auxiliary->GetVground()*deltaT;
if (WOW) TakeoffDistanceTraveled += Auxiliary->GetVground()*deltaT;
}
@ -739,6 +740,8 @@ void FGLGear::bind(void)
snprintf(property_name, 80, "gear/unit[%d]/z-position", GearNumber);
Exec->GetPropertyManager()->Tie( property_name, (FGLGear*)this,
&FGLGear::GetZPosition, &FGLGear::SetZPosition);
snprintf(property_name, 80, "gear/unit[%d]/compression-ft", GearNumber);
Exec->GetPropertyManager()->Tie( property_name, &compressLength );
}
if( isRetractable ) {
@ -752,6 +755,8 @@ void FGLGear::bind(void)
void FGLGear::Report(ReportType repType)
{
if (fabs(TakeoffDistanceTraveled) < 0.001) return; // Don't print superfluous reports
switch(repType) {
case erLand:
cout << endl << "Touchdown report for " << name << endl;

3
src/FDM/JSBSim/models/FGLGear.h
View file

@ -257,6 +257,9 @@ public:
/// Sets the brake value in percent (0 - 100)
inline void SetBrake(double bp) {brakePct = bp;}
/// Sets the weight-on-wheels flag.
void SetWOW(bool wow) {WOW = wow;}
/** Set the console touchdown reporting feature
@param flag true turns on touchdown reporting, false turns it off */
inline void SetReport(bool flag) { ReportEnable = flag; }

28
src/FDM/JSBSim/models/FGOutput.cpp
View file

@ -247,6 +247,7 @@ void FGOutput::DelimitedOutput(string fname)
if (SubSystems & ssVelocities) {
outstream << delimeter;
outstream << "q bar (psf)" + delimeter;
outstream << "Reynolds Number" + delimeter;
outstream << "V_{Total} (ft/s)" + delimeter;
outstream << "V_{Inertial} (ft/s)" + delimeter;
outstream << "UBody" + delimeter + "VBody" + delimeter + "WBody" + delimeter;
@ -266,6 +267,9 @@ void FGOutput::DelimitedOutput(string fname)
if (SubSystems & ssAtmosphere) {
outstream << delimeter;
outstream << "Rho (slugs/ft^3)" + delimeter;
outstream << "Absolute Viscosity" + delimeter;
outstream << "Kinematic Viscosity" + delimeter;
outstream << "Temperature (R)" + delimeter;
outstream << "P_{SL} (psf)" + delimeter;
outstream << "P_{Ambient} (psf)" + delimeter;
outstream << "Turbulence Magnitude (ft/sec)" + delimeter;
@ -274,17 +278,17 @@ void FGOutput::DelimitedOutput(string fname)
}
if (SubSystems & ssMassProps) {
outstream << delimeter;
outstream << "I_xx" + delimeter;
outstream << "I_xy" + delimeter;
outstream << "I_xz" + delimeter;
outstream << "I_yx" + delimeter;
outstream << "I_yy" + delimeter;
outstream << "I_yz" + delimeter;
outstream << "I_zx" + delimeter;
outstream << "I_zy" + delimeter;
outstream << "I_zz" + delimeter;
outstream << "I_{xx}" + delimeter;
outstream << "I_{xy}" + delimeter;
outstream << "I_{xz}" + delimeter;
outstream << "I_{yx}" + delimeter;
outstream << "I_{yy}" + delimeter;
outstream << "I_{yz}" + delimeter;
outstream << "I_{zx}" + delimeter;
outstream << "I_{zy}" + delimeter;
outstream << "I_{zz}" + delimeter;
outstream << "Mass" + delimeter;
outstream << "X_cg" + delimeter + "Y_cg" + delimeter + "Z_cg";
outstream << "X_{cg}" + delimeter + "Y_{cg}" + delimeter + "Z_{cg}";
}
if (SubSystems & ssPropagate) {
outstream << delimeter;
@ -348,6 +352,7 @@ void FGOutput::DelimitedOutput(string fname)
if (SubSystems & ssVelocities) {
outstream << delimeter;
outstream << Auxiliary->Getqbar() << delimeter;
outstream << Auxiliary->GetReynoldsNumber() << delimeter;
outstream << setprecision(12) << Auxiliary->GetVt() << delimeter;
outstream << Propagate->GetInertialVelocityMagnitude() << delimeter;
outstream << setprecision(12) << Propagate->GetUVW().Dump(delimeter) << delimeter;
@ -367,6 +372,9 @@ void FGOutput::DelimitedOutput(string fname)
if (SubSystems & ssAtmosphere) {
outstream << delimeter;
outstream << Atmosphere->GetDensity() << delimeter;
outstream << Atmosphere->GetAbsoluteViscosity() << delimeter;
outstream << Atmosphere->GetKinematicViscosity() << delimeter;
outstream << Atmosphere->GetTemperature() << delimeter;
outstream << Atmosphere->GetPressureSL() << delimeter;
outstream << Atmosphere->GetPressure() << delimeter;
outstream << Atmosphere->GetTurbMagnitude() << delimeter;

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

@ -184,7 +184,7 @@ bool FGPropulsion::GetSteadyState(void)
while (!steady && j < 6000) {
Engines[i]->Calculate();
lastThrust = currentThrust;
currentThrust = Engines[i]->GetThrust();
currentThrust = Engines[i]->GetThruster()->GetThrust();
if (fabs(lastThrust-currentThrust) < 0.0001) {
steady_count++;
if (steady_count > 120) {

12
src/FDM/JSBSim/models/atmosphere/FGMSIS.cpp
View file

@ -136,7 +136,7 @@ bool MSIS::InitModel(void)
pressure = &intPressure;
density = &intDensity;
useExternal=false;
UseInternal();
return true;
}
@ -174,19 +174,11 @@ bool MSIS::Run(void)
intTemperature = output.t[1] * 1.8;
intDensity = output.d[5] * 1.940321;
intPressure = 1716.488 * intDensity * intTemperature;
soundspeed = sqrt(2403.0832 * intTemperature);
//cout << "T=" << intTemperature << " D=" << intDensity << " P=";
//cout << intPressure << " a=" << soundspeed << endl;
}
if (turbType != ttNone) {
Turbulence();
vWindNED += vTurbulenceNED;
}
if (vWindNED(1) != 0.0) psiw = atan2( vWindNED(2), vWindNED(1) );
if (psiw < 0) psiw += 2*M_PI;
CalculateDerived();
Debug(2);

3
src/FDM/JSBSim/models/propulsion/FGEngine.cpp
View file

@ -119,7 +119,7 @@ FGEngine::FGEngine(FGFDMExec* exec, Element* engine_element, int engine_number)
snprintf(property_name, 80, "propulsion/engine[%d]/set-running", EngineNumber);
PropertyManager->Tie( property_name, this, &FGEngine::GetRunning, &FGEngine::SetRunning );
snprintf(property_name, 80, "propulsion/engine[%u]/thrust-lbs", EngineNumber);
PropertyManager->Tie( property_name, this, &FGEngine::GetThrust);
PropertyManager->Tie( property_name, Thruster, &FGThruster::GetThrust);
snprintf(property_name, 80, "propulsion/engine[%u]/fuel-flow-rate-pps", EngineNumber);
PropertyManager->Tie( property_name, this, &FGEngine::GetFuelFlowRate);
@ -138,7 +138,6 @@ FGEngine::~FGEngine()
void FGEngine::ResetToIC(void)
{
Thrust = 0.0;
Throttle = 0.0;
Mixture = 1.0;
Starter = false;

2
src/FDM/JSBSim/models/propulsion/FGEngine.h
View file

@ -150,7 +150,6 @@ public:
virtual double getFuelFlow_gph () const {return FuelFlow_gph;}
virtual double getFuelFlow_pph () const {return FuelFlow_pph;}
virtual double GetFuelFlowRate(void) const {return FuelFlowRate;}
virtual double GetThrust(void) const { return Thrust; }
virtual bool GetStarved(void) { return Starved; }
virtual bool GetRunning(void) const { return Running; }
virtual bool GetCranking(void) { return Cranking; }
@ -216,7 +215,6 @@ protected:
double MaxThrottle;
double MinThrottle;
double Thrust;
double Throttle;
double Mixture;
double FuelExpended;

86
src/FDM/JSBSim/models/propulsion/FGPiston.cpp
View file

@ -132,21 +132,6 @@ FGPiston::FGPiston(FGFDMExec* exec, Element* el, int engine_number)
*Lookup_Combustion_Efficiency << 1.60 << 0.525;
*Lookup_Combustion_Efficiency << 2.00 << 0.345;
Power_Mixture_Correlation = new FGTable(13);
*Power_Mixture_Correlation << (14.7/1.6) << 0.780;
*Power_Mixture_Correlation << 10 << 0.860;
*Power_Mixture_Correlation << 11 << 0.935;
*Power_Mixture_Correlation << 12 << 0.980;
*Power_Mixture_Correlation << 13 << 1.000;
*Power_Mixture_Correlation << 14 << 0.990;
*Power_Mixture_Correlation << 15 << 0.964;
*Power_Mixture_Correlation << 16 << 0.925;
*Power_Mixture_Correlation << 17 << 0.880;
*Power_Mixture_Correlation << 18 << 0.830;
*Power_Mixture_Correlation << 19 << 0.785;
*Power_Mixture_Correlation << 20 << 0.740;
*Power_Mixture_Correlation << (14.7/0.6) << 0.58;
Mixture_Efficiency_Correlation = new FGTable(15);
*Mixture_Efficiency_Correlation << 0.05000 << 0.00000;
*Mixture_Efficiency_Correlation << 0.05137 << 0.00862;
@ -165,21 +150,6 @@ FGPiston::FGPiston(FGFDMExec* exec, Element* el, int engine_number)
*Mixture_Efficiency_Correlation << 0.12500 << 0.00000;
/*
Manifold_Pressure_Lookup = new
0 0.2 0.4 0.6 0.8 1
0 1.0000 1.0000 1.0000 1.0000 1.0000 1.0000
1000 0.7778 0.8212 0.8647 0.9081 0.9516 0.9950
2000 0.5556 0.6424 0.7293 0.8162 0.9031 0.9900
3000 0.3333 0.4637 0.5940 0.7243 0.8547 0.9850
4000 0.2000 0.2849 0.4587 0.6324 0.8062 0.9800
5000 0.2000 0.2000 0.3233 0.5406 0.7578 0.9750
6000 0.2000 0.2000 0.2000 0.4487 0.7093 0.9700
7000 0.2000 0.2000 0.2000 0.2000 0.4570 0.7611
8000 0.2000 0.2000 0.2000 0.2000 0.2047 0.5522
*/
// Read inputs from engine data file where present.
if (el->FindElement("minmp")) // Should have ELSE statement telling default value used?
@ -238,10 +208,17 @@ Manifold_Pressure_Lookup = new
RatedAltitude[2] = el->FindElementValueAsNumberConvertTo("ratedaltitude3", "FT");
}
MaxManifoldPressure_Percent = MaxManifoldPressure_inHg / 29.92;
// Create a BSFC to match the engine if not provided
if (BSFC < 0) {
BSFC = ( Displacement * MaxRPM * volumetric_efficiency ) / (9411 * MaxHP);
BSFC *= (MaxManifoldPressure_Percent * MaxManifoldPressure_Percent * MaxManifoldPressure_Percent);
}
if ( MaxManifoldPressure_inHg > 29.9 ) { // Don't allow boosting with a bogus number
MaxManifoldPressure_inHg = 29.9;
MaxManifoldPressure_Percent = MaxManifoldPressure_inHg / 29.92;
}
char property_name[80];
snprintf(property_name, 80, "propulsion/engine[%d]/power-hp", EngineNumber);
PropertyManager->Tie(property_name, &HP);
@ -299,7 +276,9 @@ Manifold_Pressure_Lookup = new
BoostSpeed = 0;
}
bBoostOverride = (BoostOverride == 1 ? true : false);
if (MinThrottle < 0.001) MinThrottle = 0.001; //MinThrottle is a denominator in a power equation so it can't be zero
if (MinThrottle < 0.12) MinThrottle = 0.12; //MinThrottle is limited to 0.12 to prevent the
// throttle area equation from going negative
// 0.12 is 1% of maximum area
Debug(0); // Call Debug() routine from constructor if needed
}
@ -308,7 +287,6 @@ Manifold_Pressure_Lookup = new
FGPiston::~FGPiston()
{
delete Lookup_Combustion_Efficiency;
delete Power_Mixture_Correlation;
delete Mixture_Efficiency_Correlation;
Debug(1); // Call Debug() routine from constructor if needed
}
@ -338,7 +316,8 @@ double FGPiston::Calculate(void)
if (FuelFlow_gph > 0.0) ConsumeFuel();
Throttle = FCS->GetThrottlePos(EngineNumber);
ThrottlePos = MinThrottle+((MaxThrottle-MinThrottle)*Throttle );
// calculate the throttle plate angle. 1 unit is pi/2 radians.
ThrottleAngle = MinThrottle+((MaxThrottle-MinThrottle)*Throttle );
Mixture = FCS->GetMixturePos(EngineNumber);
//
@ -367,8 +346,7 @@ double FGPiston::Calculate(void)
// Running = false;
doEnginePower();
if(HP<0.1250)
Running = false;
if (HP < 0.1250) Running = false;
doEGT();
doCHT();
@ -390,8 +368,6 @@ if(HP<0.1250)
double FGPiston::CalcFuelNeed(void)
{
double dT = State->Getdt() * Propulsion->GetRate();
FuelFlow_pph = FuelFlow_gph * 6.0; // Assumes 6 lbs / gallon
FuelFlowRate = FuelFlow_pph / 3600.0;
FuelExpended = FuelFlowRate * dT;
return FuelExpended;
}
@ -510,20 +486,18 @@ void FGPiston::doBoostControl(void)
* from the throttle position, turbo/supercharger boost control
* system, engine speed and local ambient air density.
*
* TODO: changes in MP should not be instantaneous -- introduce
* a lag between throttle changes and MP changes, to allow pressure
* to build up or disperse.
*
* Inputs: minMAP, maxMAP, p_amb, Throttle
* Inputs: p_amb, Throttle, MaxManifoldPressure_Percent, ThrottleAngle
* RPM, MaxRPM
*
* Outputs: MAP, ManifoldPressure_inHg
*/
void FGPiston::doMAP(void)
{
suction_loss = RPM > 0.0 ? ThrottlePos * MaxRPM / RPM : 1.0;
if (suction_loss > 1.0) suction_loss = 1.0;
MAP = p_amb * suction_loss;
// estimate throttle plate area. This maps 0.2 -> 0.1 for historical performance reasons
double throttle_area = ThrottleAngle * 1.125 - 0.125;
map_coefficient = pow ((throttle_area * MaxManifoldPressure_Percent),RPM/MaxRPM);
MAP = p_amb * map_coefficient;
if(Boosted) {
// If takeoff boost is fitted, we currently assume the following throttle map:
@ -549,7 +523,7 @@ void FGPiston::doMAP(void)
}
}
// Boost the manifold pressure.
double boost_factor = BoostMul[BoostSpeed] * suction_loss * RPM/RatedRPM[BoostSpeed];
double boost_factor = BoostMul[BoostSpeed] * map_coefficient * RPM/RatedRPM[BoostSpeed];
if (boost_factor < 1.0) boost_factor = 1.0; // boost will never reduce the MAP
MAP *= boost_factor;
// Now clip the manifold pressure to BCV or Wastegate setting.
@ -575,7 +549,7 @@ void FGPiston::doMAP(void)
* (used in CHT calculation for air-cooled engines).
*
* Inputs: p_amb, R_air, T_amb, MAP, Displacement,
* RPM, volumetric_efficiency, ThrottlePos
* RPM, volumetric_efficiency, ThrottleAngle
*
* TODO: Model inlet manifold air temperature.
*
@ -587,7 +561,7 @@ void FGPiston::doAirFlow(void)
rho_air = p_amb / (R_air * T_amb);
double displacement_SI = Displacement * in3tom3;
double swept_volume = (displacement_SI * (RPM/60)) / 2;
double v_dot_air = swept_volume * volumetric_efficiency * suction_loss;
double v_dot_air = swept_volume * volumetric_efficiency * map_coefficient;
double rho_air_manifold = MAP / (R_air * T_amb);
m_dot_air = v_dot_air * rho_air_manifold;
@ -609,11 +583,9 @@ void FGPiston::doFuelFlow(void)
// double AFR = 10+(12*(1-Mixture));// mixture 10:1 to 22:1
// m_dot_fuel = m_dot_air / AFR;
m_dot_fuel = (m_dot_air * equivalence_ratio) / 14.7;
FuelFlow_gph = m_dot_fuel
* 3600 // seconds to hours
* 2.2046 // kg to lb
/ 6.0; // lb to gal_us of gasoline
// / 6.6; // lb to gal_us of kerosene
FuelFlowRate = m_dot_fuel * 2.2046; // kg to lb
FuelFlow_pph = FuelFlowRate * 3600; // seconds to hours
FuelFlow_gph = FuelFlow_pph / 6.0; // Assumes 6 lbs / gallon
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
@ -649,7 +621,7 @@ void FGPiston::doEnginePower(void)
if ( Magnetos != 3 ) power *= SparkFailDrop;
HP = (FuelFlow_gph * 6.0 / BSFC )* ME * suction_loss * power;
HP = (FuelFlow_gph * 6.0 / BSFC )* ME * map_coefficient * power;
} else {
@ -871,17 +843,13 @@ void FGPiston::Debug(int from)
cout << " IdleRPM: " << IdleRPM << endl;
cout << " MaxThrottle: " << MaxThrottle << endl;
cout << " MinThrottle: " << MinThrottle << endl;
cout << " BSFC: " << BSFC << endl;
cout << endl;
cout << " Combustion Efficiency table:" << endl;
Lookup_Combustion_Efficiency->Print();
cout << endl;
cout << endl;
cout << " Power Mixture Correlation table:" << endl;
Power_Mixture_Correlation->Print();
cout << endl;
cout << endl;
cout << " Mixture Efficiency Correlation table:" << endl;
Mixture_Efficiency_Correlation->Print();

6
src/FDM/JSBSim/models/propulsion/FGPiston.h
View file

@ -205,8 +205,7 @@ public:
double getRPM(void) {return RPM;}
protected:
double ThrottlePos;
double ThrottleAngle;
private:
int crank_counter;
@ -252,6 +251,7 @@ private:
//
double MinManifoldPressure_inHg; // Inches Hg
double MaxManifoldPressure_inHg; // Inches Hg
double MaxManifoldPressure_Percent; // MaxManifoldPressure / 29.92
double Displacement; // cubic inches
double MaxHP; // horsepower
double SparkFailDrop; // drop of power due to spark failure
@ -304,7 +304,7 @@ private:
//
double rho_air;
double volumetric_efficiency;
double suction_loss;
double map_coefficient;
double m_dot_air;
double equivalence_ratio;
double m_dot_fuel;

9
src/FDM/JSBSim/models/propulsion/FGRocket.cpp
View file

@ -106,6 +106,7 @@ FGRocket::~FGRocket(void)
double FGRocket::Calculate(void)
{
double dT = State->Getdt()*Propulsion->GetRate();
double thrust;
if (!Flameout && !Starved) ConsumeFuel();
@ -135,7 +136,7 @@ double FGRocket::Calculate(void)
if (Throttle < MinThrottle || Starved) { // Combustion not supported
PctPower = Thrust = 0.0; // desired thrust
PctPower = 0.0; // desired thrust
Flameout = true;
VacThrust = 0.0;
@ -149,10 +150,10 @@ double FGRocket::Calculate(void)
} // End thrust calculations
Thrust = Thruster->Calculate(VacThrust);
It += Thrust * dT;
thrust = Thruster->Calculate(VacThrust);
It += thrust * dT;
return Thrust;
return thrust;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

2
src/FDM/JSBSim/models/propulsion/FGTank.cpp
View file

@ -148,6 +148,8 @@ FGTank::FGTank(FGFDMExec* exec, Element* el, int tank_number)
if (Temperature != -9999.0) InitialTemperature = Temperature = FahrenheitToCelsius(Temperature);
Area = 40.0 * pow(Capacity/1975, 0.666666667);
CalculateInertias();
Debug(0);
}

2
src/FDM/JSBSim/models/propulsion/FGThruster.cpp
View file

@ -86,7 +86,7 @@ FGThruster::FGThruster(FGFDMExec *FDMExec, Element *el, int num ): FGForce(FDMEx
PropertyManager->Tie( property_name, (FGForce *)this, &FGForce::GetYaw, &FGForce::SetYaw);
if (el->GetName() == "direct") // this is a direct thruster. At this time
// only a direct thruster can be reversed.
// only a direct thruster can be reversed.
{
snprintf(property_name, 80, "propulsion/engine[%d]/reverser-angle-rad", EngineNum);
PropertyManager->Tie( property_name, (FGThruster *)this, &FGThruster::GetReverserAngle,

2
src/FDM/JSBSim/models/propulsion/FGThruster.h
View file

@ -99,7 +99,7 @@ public:
virtual void SetRPM(double rpm) {};
virtual double GetPowerRequired(void) {return 0.0;}
virtual void SetdeltaT(double dt) {deltaT = dt;}
double GetThrust(void) {return Thrust;}
double GetThrust(void) const {return Thrust;}
eType GetType(void) {return Type;}
string GetName(void) {return Name;}
void SetReverserAngle(double angle) {ReverserAngle = angle;}

22
src/FDM/JSBSim/models/propulsion/FGTurbine.cpp
View file

@ -107,6 +107,8 @@ void FGTurbine::ResetToIC(void)
double FGTurbine::Calculate(void)
{
double thrust;
TAT = (Auxiliary->GetTotalTemperature() - 491.69) * 0.5555556;
dt = State->Getdt() * Propulsion->GetRate();
ThrottlePos = FCS->GetThrottlePos(EngineNumber);
@ -144,19 +146,19 @@ double FGTurbine::Calculate(void)
if (Seized) phase = tpSeize;
switch (phase) {
case tpOff: Thrust = Off(); break;
case tpRun: Thrust = Run(); break;
case tpSpinUp: Thrust = SpinUp(); break;
case tpStart: Thrust = Start(); break;
case tpStall: Thrust = Stall(); break;
case tpSeize: Thrust = Seize(); break;
case tpTrim: Thrust = Trim(); break;
default: Thrust = Off();
case tpOff: thrust = Off(); break;
case tpRun: thrust = Run(); break;
case tpSpinUp: thrust = SpinUp(); break;
case tpStart: thrust = Start(); break;
case tpStall: thrust = Stall(); break;
case tpSeize: thrust = Seize(); break;
case tpTrim: thrust = Trim(); break;
default: thrust = Off();
}
Thrust = Thruster->Calculate(Thrust); // allow thruster to modify thrust (i.e. reversing)
thrust = Thruster->Calculate(thrust); // allow thruster to modify thrust (i.e. reversing)
return Thrust;
return thrust;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

1
src/FDM/JSBSim/models/propulsion/FGTurbine.h
View file

@ -169,7 +169,6 @@ public:
double Calculate(void);
double CalcFuelNeed(void);
double GetPowerAvailable(void);
// double GetThrust(void) const {return Thrust;}
/** A lag filter.
Used to control the rate at which values are allowed to change.
@param var a pointer to a variable of type double