bool FGPropulsion::Run(bool Holding)
{
unsigned int i;
if (FGModel::Run(Holding)) return true;
if (Holding) return false;
RunPreFunctions();
vForces.InitMatrix();
vMoments.InitMatrix();
for (i=0; i<numEngines; i++) {
Engines[i]->Calculate();
ConsumeFuel(Engines[i]);
vForces += Engines[i]->GetBodyForces(); // sum body frame forces
vMoments += Engines[i]->GetMoments(); // sum body frame moments
}
TotalFuelQuantity = 0.0;
for (i=0; i<numTanks; i++) {
Tanks[i]->Calculate( in.TotalDeltaT, in.TAT_c);
if (Tanks[i]->GetType() == FGTank::ttFUEL) {
TotalFuelQuantity += Tanks[i]->GetContents();
}
}
if (refuel) DoRefuel( in.TotalDeltaT );
if (dump) DumpFuel( in.TotalDeltaT );
RunPostFunctions();
return false;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGPiston::Calculate(void)
{
RunPreFunctions();
if (FuelFlow_gph > 0.0) ConsumeFuel();
Throttle = FCS->GetThrottlePos(EngineNumber);
Mixture = FCS->GetMixturePos(EngineNumber);
// Input values.
p_amb = Atmosphere->GetPressure() * psftopa;
double p = Auxiliary->GetTotalPressure() * psftopa;
p_ram = (p - p_amb) * Ram_Air_Factor + p_amb;
T_amb = RankineToKelvin(Atmosphere->GetTemperature());
RPM = Thruster->GetRPM() * Thruster->GetGearRatio();
MeanPistonSpeed_fps = ( RPM * Stroke) / (360); // AKA 2 * (RPM/60) * ( Stroke / 12) or 2NS
IAS = Auxiliary->GetVcalibratedKTS();
doEngineStartup();
if (Boosted) doBoostControl();
doMAP();
doAirFlow();
doFuelFlow();
//Now that the fuel flow is done check if the mixture is too lean to run the engine
//Assume lean limit at 22 AFR for now - thats a thi of 0.668
//This might be a bit generous, but since there's currently no audiable warning of impending
//cutout in the form of misfiring and/or rough running its probably reasonable for now.
// if (equivalence_ratio < 0.668)
// Running = false;
doEnginePower();
if (IndicatedHorsePower < 0.1250) Running = false;
doEGT();
doCHT();
doOilTemperature();
doOilPressure();
if (Thruster->GetType() == FGThruster::ttPropeller) {
((FGPropeller*)Thruster)->SetAdvance(FCS->GetPropAdvance(EngineNumber));
((FGPropeller*)Thruster)->SetFeather(FCS->GetPropFeather(EngineNumber));
}
PowerAvailable = (HP * hptoftlbssec) - Thruster->GetPowerRequired();
Thruster->Calculate(PowerAvailable);
RunPostFunctions();
}
double FGRocket::Calculate(void)
{
double dT = State->Getdt()*Propulsion->GetRate();
double thrust;
if (!Flameout && !Starved) ConsumeFuel();
PropellantFlowRate = (FuelExpended + OxidizerExpended)/dT;
Throttle = FCS->GetThrottlePos(EngineNumber);
// If there is a thrust table, it is a function of propellant remaining. The
// engine is started when the throttle is advanced to 1.0. After that, it
// burns without regard to throttle setting. The table returns a value between
// zero and one, representing the percentage of maximum vacuum thrust being
// applied.
if (ThrustTable != 0L) { // Thrust table given -> Solid fuel used
if ((Throttle == 1 || BurnTime > 0.0 ) && !Starved) {
BurnTime += State->Getdt();
double TotalEngineFuelAvailable=0.0;
for (int i=0; i<(int)SourceTanks.size(); i++)
TotalEngineFuelAvailable += Propulsion->GetTank(SourceTanks[i])->GetContents();
VacThrust = ThrustTable->GetValue(TotalEngineFuelAvailable);
} else {
VacThrust = 0.0;
}
} else { // liquid fueled rocket assumed
if (Throttle < MinThrottle || Starved) { // Combustion not supported
PctPower = 0.0; // desired thrust
Flameout = true;
VacThrust = 0.0;
} else { // Calculate thrust
PctPower = Throttle / MaxThrottle; // Min and MaxThrottle range from 0.0 to 1.0, normally.
Flameout = false;
VacThrust = Isp * PropellantFlowRate;
}
} // End thrust calculations
thrust = Thruster->Calculate(VacThrust);
It += thrust * dT;
return thrust;
}