INCLUDES
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
-#include <vector>
+#include <iostream>
#include <sstream>
#include "FGTurbine.h"
+#include "FGThruster.h"
+
+using namespace std;
namespace JSBSim {
-static const char *IdSrc = "$Id$";
+static const char *IdSrc = "$Id: FGTurbine.cpp,v 1.36 2011/09/25 23:56:11 jentron Exp $";
static const char *IdHdr = ID_TURBINE;
/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
-FGTurbine::FGTurbine(FGFDMExec* exec, Element *el, int engine_number)
- : FGEngine(exec, el, engine_number)
+FGTurbine::FGTurbine(FGFDMExec* exec, Element *el, int engine_number, struct Inputs& input)
+ : FGEngine(exec, el, engine_number, input)
{
Type = etTurbine;
BypassRatio = BleedDemand = 0.0;
IdleThrustLookup = MilThrustLookup = MaxThrustLookup = InjectionLookup = 0;
N1_spinup = 1.0; N2_spinup = 3.0;
+ EPR = 1.0;
ResetToIC();
void FGTurbine::ResetToIC(void)
{
+
+ FGEngine::ResetToIC();
+
N1 = N2 = 0.0;
+ N2norm = 0.0;
correctedTSFC = TSFC;
- ThrottlePos = AugmentCmd = 0.0;
+ AugmentCmd = 0.0;
InletPosition = NozzlePosition = 1.0;
Stalled = Seized = Overtemp = Fire = Augmentation = Injection = Reversed = false;
Cutoff = true;
phase = tpOff;
- EGT_degC = 0.0;
- OilTemp_degK = (Auxiliary->GetTotalTemperature() - 491.69) * 0.5555556 + 273.0;
+ TAT = (in.TotalTempearture - 491.69) * 0.5555556;
+ EGT_degC = TAT;
+ OilTemp_degK = TAT + 273.0;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
// The main purpose of Calculate() is to determine what phase the engine should
// be in, then call the corresponding function.
-double FGTurbine::Calculate(void)
+void FGTurbine::Calculate(void)
{
double thrust;
- TAT = (Auxiliary->GetTotalTemperature() - 491.69) * 0.5555556;
- dt = State->Getdt() * Propulsion->GetRate();
- ThrottlePos = FCS->GetThrottlePos(EngineNumber);
+ RunPreFunctions();
+
+ ThrottlePos = in.ThrottlePos[EngineNumber];
+
+ TAT = (in.TotalTempearture - 491.69) * 0.5555556;
if (ThrottlePos > 1.0) {
AugmentCmd = ThrottlePos - 1.0;
ThrottlePos -= AugmentCmd;
}
// When trimming is finished check if user wants engine OFF or RUNNING
- if ((phase == tpTrim) && (dt > 0)) {
+ if ((phase == tpTrim) && (in.TotalDeltaT > 0)) {
if (Running && !Starved) {
phase = tpRun;
N2 = IdleN2 + ThrottlePos * N2_factor;
if (!Running && Cutoff && Starter) {
if (phase == tpOff) phase = tpSpinUp;
- }
- if (!Running && !Cutoff && (N2 > 15.0)) phase = tpStart;
+ }
+
+ // start
+ if ((Starter == true) || (in.qbar > 30.0)) {
+ if (!Running && !Cutoff && (N2 > 15.0)) phase = tpStart;
+ }
+
if (Cutoff && (phase != tpSpinUp)) phase = tpOff;
- if (dt == 0) phase = tpTrim;
+ if (in.TotalDeltaT == 0) phase = tpTrim;
if (Starved) phase = tpOff;
if (Stalled) phase = tpStall;
if (Seized) phase = tpSeize;
default: thrust = Off();
}
- thrust = Thruster->Calculate(thrust); // allow thruster to modify thrust (i.e. reversing)
+ Thruster->Calculate(thrust); // allow thruster to modify thrust (i.e. reversing)
- return thrust;
+ RunPostFunctions();
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
double FGTurbine::Off(void)
{
- double qbar = Auxiliary->Getqbar();
Running = false;
FuelFlow_pph = Seek(&FuelFlow_pph, 0, 1000.0, 10000.0);
- N1 = Seek(&N1, qbar/10.0, N1/2.0, N1/2.0);
- N2 = Seek(&N2, qbar/15.0, N2/2.0, N2/2.0);
+ N1 = Seek(&N1, in.qbar/10.0, N1/2.0, N1/2.0);
+ N2 = Seek(&N2, in.qbar/15.0, N2/2.0, N2/2.0);
EGT_degC = Seek(&EGT_degC, TAT, 11.7, 7.3);
OilTemp_degK = Seek(&OilTemp_degK, TAT + 273.0, 0.2, 0.2);
OilPressure_psi = N2 * 0.62;
NozzlePosition = Seek(&NozzlePosition, 1.0, 0.8, 0.8);
EPR = Seek(&EPR, 1.0, 0.2, 0.2);
Augmentation = false;
- ConsumeFuel();
return 0.0;
}
double FGTurbine::Run()
{
double idlethrust, milthrust, thrust;
- double N2norm; // 0.0 = idle N2, 1.0 = maximum N2
+ double spoolup; // acceleration in pct/sec
+ double sigma = in.DensityRatio;
+ double T = in.Temperature;
idlethrust = MilThrust * IdleThrustLookup->GetValue();
milthrust = (MilThrust - idlethrust) * MilThrustLookup->GetValue();
Running = true;
Starter = false;
- N2 = Seek(&N2, IdleN2 + ThrottlePos * N2_factor, delay, delay * 3.0);
- N1 = Seek(&N1, IdleN1 + ThrottlePos * N1_factor, delay, delay * 2.4);
+ // adjust acceleration for N2 and atmospheric density
+ double n = N2norm + 0.1;
+ if (n > 1) n = 1;
+ spoolup = delay / (1 + 3 * (1-n)*(1-n)*(1-n) + (1 - sigma));
+
+ N2 = Seek(&N2, IdleN2 + ThrottlePos * N2_factor, spoolup, spoolup * 3.0);
+ N1 = Seek(&N1, IdleN1 + ThrottlePos * N1_factor, spoolup, spoolup * 2.4);
N2norm = (N2 - IdleN2) / N2_factor;
thrust = idlethrust + (milthrust * N2norm * N2norm);
EGT_degC = TAT + 363.1 + ThrottlePos * 357.1;
OilTemp_degK = Seek(&OilTemp_degK, 366.0, 1.2, 0.1);
if (!Augmentation) {
- correctedTSFC = TSFC * (0.84 + (1-N2norm)*(1-N2norm));
- FuelFlow_pph = Seek(&FuelFlow_pph, thrust * correctedTSFC, 1000.0, 100000);
+ correctedTSFC = TSFC * sqrt(T/389.7) * (0.84 + (1-N2norm)*(1-N2norm));
+ FuelFlow_pph = Seek(&FuelFlow_pph, thrust * correctedTSFC, 1000.0, 10000.0);
if (FuelFlow_pph < IdleFF) FuelFlow_pph = IdleFF;
NozzlePosition = Seek(&NozzlePosition, 1.0 - N2norm, 0.8, 0.8);
thrust = thrust * (1.0 - BleedDemand);
}
if ((Injected == 1) && Injection) {
- InjectionTimer += dt;
+ InjectionTimer += in.TotalDeltaT;
if (InjectionTimer < InjectionTime) {
thrust = thrust * InjectionLookup->GetValue();
} else {
}
}
- ConsumeFuel();
if (Cutoff) phase = tpOff;
if (Starved) phase = tpOff;
OilTemp_degK = Seek(&OilTemp_degK, TAT + 273.0, 0.2, 0.2);
EPR = 1.0;
NozzlePosition = 1.0;
+ if (Starter == false) phase = tpOff;
return 0.0;
}
N2 = Seek(&N2, IdleN2, 2.0, N2/2.0);
N1 = Seek(&N1, IdleN1, 1.4, N1/2.0);
EGT_degC = Seek(&EGT_degC, TAT + 363.1, 21.3, 7.3);
- FuelFlow_pph = Seek(&FuelFlow_pph, IdleFF, 103.7, 103.7);
+ FuelFlow_pph = IdleFF * N2 / IdleN2;
OilPressure_psi = N2 * 0.62;
- ConsumeFuel();
+ if ((Starter == false) && (in.qbar < 30.0)) phase = tpOff; // aborted start
}
else {
phase = tpRun;
double FGTurbine::Stall(void)
{
- double qbar = Auxiliary->Getqbar();
EGT_degC = TAT + 903.14;
FuelFlow_pph = IdleFF;
- N1 = Seek(&N1, qbar/10.0, 0, N1/10.0);
- N2 = Seek(&N2, qbar/15.0, 0, N2/10.0);
- ConsumeFuel();
- if (ThrottlePos < 0.01) phase = tpRun; // clear the stall with throttle
-
+ N1 = Seek(&N1, in.qbar/10.0, 0, N1/10.0);
+ N2 = Seek(&N2, in.qbar/15.0, 0, N2/10.0);
+ if (ThrottlePos < 0.01) {
+ phase = tpRun; // clear the stall with throttle to idle
+ Stalled = false;
+ }
return 0.0;
}
double FGTurbine::Seize(void)
{
- double qbar = Auxiliary->Getqbar();
N2 = 0.0;
- N1 = Seek(&N1, qbar/20.0, 0, N1/15.0);
- FuelFlow_pph = IdleFF;
- ConsumeFuel();
+ N1 = Seek(&N1, in.qbar/20.0, 0, N1/15.0);
+ FuelFlow_pph = Cutoff ? 0.0 : IdleFF;
OilPressure_psi = 0.0;
OilTemp_degK = Seek(&OilTemp_degK, TAT + 273.0, 0, 0.2);
Running = false;
double FGTurbine::Trim()
{
- double idlethrust, milthrust, thrust, tdiff, N2norm;
+ double idlethrust, milthrust, thrust, tdiff, N2, N2norm;
idlethrust = MilThrust * IdleThrustLookup->GetValue();
milthrust = (MilThrust - idlethrust) * MilThrustLookup->GetValue();
N2 = IdleN2 + ThrottlePos * N2_factor;
double FGTurbine::CalcFuelNeed(void)
{
- double dT = State->Getdt() * Propulsion->GetRate();
FuelFlowRate = FuelFlow_pph / 3600.0; // Calculates flow in lbs/sec from lbs/hr
- FuelExpended = FuelFlowRate * dT; // Calculates fuel expended in this time step
+ FuelExpended = FuelFlowRate * in.TotalDeltaT; // Calculates fuel expended in this time step
+ if (!Starved) FuelUsedLbs += FuelExpended;
return FuelExpended;
}
double FGTurbine::Seek(double *var, double target, double accel, double decel) {
double v = *var;
if (v > target) {
- v -= dt * decel;
+ v -= in.TotalDeltaT * decel;
if (v < target) v = target;
} else if (v < target) {
- v += dt * accel;
+ v += in.TotalDeltaT * accel;
if (v > target) v = target;
}
return v;
MaxThrustLookup = new FGFunction(PropertyManager, function_element, property_prefix);
} else if (name == "Injection") {
InjectionLookup = new FGFunction(PropertyManager, function_element, property_prefix);
- } else {
- cerr << "Unknown function type: " << name << " in turbine definition." <<
- endl;
}
}
// Pre-calculations and initializations
- delay = 60.0 / (BypassRatio + 3.0);
+ delay = 90.0 / (BypassRatio + 3.0);
N1_factor = MaxN1 - IdleN1;
N2_factor = MaxN2 - IdleN2;
- OilTemp_degK = (Auxiliary->GetTotalTemperature() - 491.69) * 0.5555556 + 273.0;
+ OilTemp_degK = (in.TotalTempearture - 491.69) * 0.5555556 + 273.0;
IdleFF = pow(MilThrust, 0.2) * 107.0; // just an estimate
bindmodel();
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-string FGTurbine::GetEngineLabels(string delimeter)
+string FGTurbine::GetEngineLabels(const string& delimiter)
{
std::ostringstream buf;
- buf << Name << "_N1[" << EngineNumber << "]" << delimeter
- << Name << "_N2[" << EngineNumber << "]" << delimeter
- << Thruster->GetThrusterLabels(EngineNumber, delimeter);
+ buf << Name << "_N1[" << EngineNumber << "]" << delimiter
+ << Name << "_N2[" << EngineNumber << "]" << delimiter
+ << Thruster->GetThrusterLabels(EngineNumber, delimiter);
return buf.str();
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-string FGTurbine::GetEngineValues(string delimeter)
+string FGTurbine::GetEngineValues(const string& delimiter)
{
std::ostringstream buf;
- buf << N1 << delimeter
- << N2 << delimeter
- << Thruster->GetThrusterValues(EngineNumber, delimeter);
+ buf << N1 << delimiter
+ << N2 << delimiter
+ << Thruster->GetThrusterValues(EngineNumber, delimiter);
return buf.str();
}
property_name = base_property_name + "/injection_cmd";
PropertyManager->Tie( property_name.c_str(), (FGTurbine*)this,
&FGTurbine::GetInjection, &FGTurbine::SetInjection);
+ property_name = base_property_name + "/seized";
+ PropertyManager->Tie( property_name.c_str(), &Seized);
+ property_name = base_property_name + "/stalled";
+ PropertyManager->Tie( property_name.c_str(), &Stalled);
+ property_name = base_property_name + "/bleed-factor";
+ PropertyManager->Tie( property_name.c_str(), (FGTurbine*)this, &FGTurbine::GetBleedDemand, &FGTurbine::SetBleedDemand);
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-int FGTurbine::InitRunning(void) {
- State->SuspendIntegration();
+int FGTurbine::InitRunning(void)
+{
+ FDMExec->SuspendIntegration();
Cutoff=false;
Running=true;
- N2=16.0;
+ N2=IdleN2;
Calculate();
- State->ResumeIntegration();
+ FDMExec->ResumeIntegration();
return phase==tpRun;
}
projects / flightgear.git / blobdiff