protected void CalculateTTR()
{
//calculate TTR at design point first
// Don't overwrite th0 and th1
EngineThermodynamics ambientTherm = EngineThermodynamics.StandardConditions(false);
ambientTherm.T = T_d;
EngineThermodynamics inletTherm = ambientTherm.ChangeReferenceFrameMach(M_d);
// Note that this work is negative
// Different mass flows between compressor, turbine, and bypass automatically taken care of by MassRatio
double compressorWork;
th3 = inletTherm.AdiabaticProcessWithPressureRatio(CPR, out compressorWork, efficiency: eta_c);
double fanWork = 0d;
if (BPR > 0d)
{
th2 = inletTherm.AdiabaticProcessWithPressureRatio(FPR, out fanWork, efficiency: eta_c);
fanWork *= BPR;
fanWorkConstant = fanWork / compressorWork;
}
double turbineWork = compressorWork + fanWork;
th4 = th3.AddFuelToTemperature(Tt4, h_f);
th5 = th4.AdiabaticProcessWithWork(turbineWork, efficiency: eta_t);
TTR = th5.T / th4.T;
}
protected void GetThrustData(out double thrustVac, out double thrustASL)
{
rfSolver.SetPropellantStatus(true, true);
bool oldE = EngineIgnited;
bool oldIg = ignited;
float oldThrottle = currentThrottle;
double oldLastPropellantFraction = lastPropellantFraction;
currentThrottle = 1f;
lastPropellantFraction = 1d;
EngineIgnited = true;
ignited = true;
ambientTherm = EngineThermodynamics.StandardConditions(true);
inletTherm = ambientTherm;
rfSolver.UpdateThrustRatio(1d);
rfSolver.SetPropellantStatus(true, true);
UpdateSolver(EngineThermodynamics.StandardConditions(true), 0d, Vector3d.zero, 0d, true, true, false);
thrustASL = engineSolver.GetThrust() * 0.001d;
double spaceHeight = Planetarium.fetch?.Home?.atmosphereDepth + 1000d ?? 141000d;
UpdateSolver(EngineThermodynamics.VacuumConditions(true), spaceHeight, Vector3d.zero, 0d, true, true, false);
thrustVac = engineSolver.GetThrust() * 0.001d;
EngineIgnited = oldE;
ignited = oldIg;
currentThrottle = oldThrottle;
lastPropellantFraction = oldLastPropellantFraction;
}
private void SetStaticSimulation()
{
ambientTherm = EngineThermodynamics.StandardConditions(true);
inletTherm = ambientTherm;
inletTherm.P *= AJEInlet.OverallStaticTPR(defaultTPR);
areaRatio = 1d;
lastPropellantFraction = 1d;
}
public override void UpdateSolver(EngineThermodynamics ambientTherm, double altitude, Vector3d vel, double mach, bool ignited, bool oxygen, bool underwater)
{
Vector3 t = thrustTransforms[0].forward.normalized;
vx = (float)Vector3.Cross(vel, t).magnitude;
vz = -(float)Vector3.Dot(vel, t);
(engineSolver as SolverRotor).UpdateFlightParams(vx, vz);
base.UpdateSolver(ambientTherm, altitude, vel, mach, ignited, oxygen, underwater);
}
public override void UpdateSolver(EngineThermodynamics ambientTherm, double altitude, Vector3d vel, double mach, bool ignited, bool oxygen, bool underwater)
{
// change up the velocity vector, it's now vs the engine part.
v = Vector3d.Dot(vel, -thrustTransforms[0].forward);
vel = (Vector3d)thrustTransforms[0].forward * -v;
// set engine params prior to calculation
if (pistonEngine != null)
{
pistonEngine.SetWastegate(boost);
pistonEngine.SetMixture(mixture);
}
// set prop (+ engine) params
solverProp.SetRPMLever(rpmLever);
solverProp.SetTweaks(CtTweak, CpTweak, VolETweak, MachPowTweak);
base.UpdateSolver(ambientTherm, altitude, vel, mach, ignited, oxygen, underwater);
}
protected void InitializeEngine()
{
//calculate TTR at design point first
// Don't overwrite th0 and th1
EngineThermodynamics ambientTherm = EngineThermodynamics.StandardConditions(false);
ambientTherm.T = T_d;
EngineThermodynamics inletTherm = ambientTherm.ChangeReferenceFrameMach(M_d);
th7 = inletTherm.AddFuelToTemperature(9999d, h_f, throttle: throttle, maxFar: maxFar);
th7.P *= 0.95;
double massFlow = inletTherm.CalculateMassFlow(Aref, 0.5d);
Athroat = th7.CalculateFlowArea(massFlow * th7.MassRatio, 1d);
if (!adjustableNozzle)
{
p8 = ambientTherm.P;
CalculateANozzle();
}
}
public string GetStaticThrustInfo()
{
string output = "";
if (engineSolver == null || !(engineSolver is SolverRotor))
{
CreateEngine();
}
// get stats
ambientTherm = EngineThermodynamics.StandardConditions(true);
currentThrottle = 1f;
lastPropellantFraction = 1d;
UpdateSolver(ambientTherm, 0d, Vector3.zero, 0d, true, true, false);
double thrust = (engineSolver.GetThrust() * 0.001d);
double power = ((engineSolver as SolverRotor).GetPower() / 745.7d);
output += "<b>Static Power: </b>" + power.ToString("F0") + " HP\n";
output += "<b>Static Thrust: </b>" + thrust.ToString("F2") + " kN\n";
return(output);
}
protected string GetThrustInfo()
{
string output = "";
if (engineSolver == null || !(engineSolver is SolverRF))
{
CreateEngine();
}
rfSolver.SetPropellantStatus(true, true);
// get stats
double pressure = 101.325d, temperature = 288.15d, density = 1.225d;
if (Planetarium.fetch != null)
{
CelestialBody home = Planetarium.fetch.Home;
if (home != null)
{
pressure = home.GetPressure(0d);
temperature = home.GetTemperature(0d);
density = home.GetDensity(pressure, temperature);
}
}
ambientTherm = new EngineThermodynamics();
ambientTherm.FromAmbientConditions(pressure, temperature, density);
inletTherm = new EngineThermodynamics();
inletTherm.CopyFrom(ambientTherm);
currentThrottle = 1f;
lastPropellantFraction = 1d;
bool oldE = EngineIgnited;
EngineIgnited = true;
bool oldIg = ignited;
ignited = true;
rfSolver.UpdateThrustRatio(1d);
rfSolver.SetPropellantStatus(true, true);
UpdateSolver(ambientTherm, 0d, Vector3d.zero, 0d, true, true, false);
double thrustASL = (engineSolver.GetThrust() * 0.001d);
if (atmChangeFlow) // If it's a jet
{
output += "<b>Static Thrust: </b>" + (thrustASL).ToString("0.0##") + " kN" + ThrottleString();
if (useVelCurve) // if thrust changes with mach
{
float vMin, vMax, tMin, tMax;
velCurve.FindMinMaxValue(out vMin, out vMax, out tMin, out tMax); // get the max mult, and thus report maximum thrust possible.
output += "\n<b>Max. Thrust: </b>" + (thrustASL * vMax).ToString("0.0##") + " kN Mach " + tMax.ToString("0.#");
}
}
else
{
// get stats again
double spaceHeight = 131000d;
pressure = 0d;
density = 0d;
if (Planetarium.fetch != null)
{
CelestialBody home = Planetarium.fetch.Home;
if (home != null)
{
temperature = home.GetTemperature(home.atmosphereDepth + 1d);
spaceHeight = home.atmosphereDepth + 1000d;
}
}
else
{
temperature = PhysicsGlobals.SpaceTemperature;
}
ambientTherm.FromAmbientConditions(pressure, temperature, density);
UpdateSolver(ambientTherm, spaceHeight, Vector3d.zero, 0d, true, true, false);
double thrustVac = (engineSolver.GetThrust() * 0.001d);
if (thrustASL != thrustVac)
{
output += (throttleLocked ? "<b>" : "<b>Max. ") + "Thrust (Vac.): </b>" + (thrustVac).ToString("0.0##") + " kN" + ThrottleString()
+ "\n" + (throttleLocked ? "<b>" : "<b>Max. ") + "Thrust (ASL): </b>" + (thrustASL).ToString("0.0##") + " kN";
}
else
{
output += (throttleLocked ? "<b>" : "<b>Max. ") + "Thrust: </b>" + (thrustVac).ToString("0.0##") + " kN" + ThrottleString();
}
}
output += "\n";
EngineIgnited = oldE;
ignited = oldIg;
return(output);
}
public override void UpdateSolver(EngineThermodynamics ambientTherm, double altitude, Vector3d vel, double mach, bool ignited, bool oxygen, bool underwater)
{
choppercontrol = Vector3.zero;
float radar = 0;
if (HighLogic.LoadedSceneIsEditor)
{
hdg = vessel.ReferenceTransform.up;
choppercontrol.z = 0.85f;
}
else if (HighLogic.LoadedSceneIsFlight)
{
hdg = vessel.ReferenceTransform.up;
rgt = vessel.ReferenceTransform.right;
dwn = vessel.ReferenceTransform.forward;
radar = (float)vessel.radarAltitude + Vector3.Dot(vessel.upAxis, thrustTransforms[0].position - vessel.transform.position);
if (cycAuth != 0)
{
choppercontrol.x = vessel.ctrlState.roll;
choppercontrol.y = vessel.ctrlState.pitch;
choppercontrol.y -= Vector3.Dot(vel, hdg) * cycTrim * 0.01f;
choppercontrol.z = vessel.ctrlState.mainThrottle;// - * vessel.ctrlState.pitch - colDiffRollCoeff * vessel.ctrlState.roll;
//thrustTransforms[0].forward = Quaternion.AngleAxis(-choppercontrol.x * maxSwashPlateAngle, hdg) * thrustTransformVectorDefault;
//thrustTransforms[0].forward = Quaternion.AngleAxis(choppercontrol.y * maxSwashPlateAngle, rgt) * thrustTransforms[0].forward;
Vector3 upAxis = (Vector3)vessel.upAxis;
float rollangle = Vector3.SignedAngle(rgt, upAxis, hdg) - 90f;
float pitchangle = 90f - Vector3.SignedAngle(upAxis, hdg, rgt);
rollPID.Update(-rollKp, -rollKi, -rollKd, choppercontrol.x * 90, rollangle, Time.deltaTime);
pitchPID.Update(-pitchKp, -pitchKi, -pitchKd, choppercontrol.y * 90, pitchangle, Time.deltaTime);
if (colDiffRoll)//Osprey
{
choppercontrol.z += rollPID.getDrive() * cycAuth / 100 * colDiffRollCoeff;
choppercontrol.x = 0;
choppercontrol.y = pitchPID.getDrive() / 100 + pitchDiffYawCoeff * vessel.ctrlState.yaw;
choppercontrol.y *= cycAuth;
}
else if (colDiffPitch)//Chinook
{
choppercontrol.z += pitchPID.getDrive() * cycAuth / 100 * colDiffPitchCoeff;
choppercontrol.y = Vector3.Dot(vel, hdg) * cycTrim * 0.01f;
choppercontrol.x = rollPID.getDrive() / 100 + rollDiffYawCoeff * vessel.ctrlState.yaw;
choppercontrol.x *= cycAuth;
}
else
{
choppercontrol.y = pitchPID.getDrive() / 100 + pitchDiffYawCoeff * vessel.ctrlState.yaw;
choppercontrol.y *= cycAuth;
choppercontrol.x = rollPID.getDrive() / 100 + rollDiffYawCoeff * vessel.ctrlState.yaw;
choppercontrol.x *= cycAuth;
}
}
else
{
choppercontrol.x = choppercontrol.y = 0;
choppercontrol.z = vessel.ctrlState.mainThrottle;
}
}
else
{
hdg.Set(0, 1, 0);
}
Vector3 t = thrustTransforms[0].forward.normalized;
vel += Vector3.Cross(vessel.angularVelocity, thrustTransforms[0].position - vessel.transform.position);
(engineSolver as SolverRotor).UpdateFlightParams(choppercontrol, vel, hdg, t, radar, (float)ambientTherm.SpeedOfSound(1), this.thrustPercentage);
base.UpdateSolver(ambientTherm, altitude, vel, mach, ignited, oxygen, underwater);
}
public override void CalculatePerformance(double airRatio, double commandedThrottle, double flowMult, double ispMult)
{
// set base bits
base.CalculatePerformance(airRatio, commandedThrottle, flowMult, ispMult);
// if we're not combusting, don't combust and start cooling off
combusting = running;
statusString = "Nominal";
if (running && (!oxygen || eair0 <= 0d))
{
combusting = false;
statusString = "No oxygen";
}
else if (ffFraction <= 0d)
{
combusting = false;
statusString = "No fuel";
}
else if (airRatio < 0.01d)
{
combusting = false;
statusString = "Insufficient intake area";
}
else if (underwater)
{
combusting = false;
statusString = "Nozzle in water";
}
if (combusting)
{
if (Tt7 > 0)
{
if (unifiedThrottle)
{
mainThrottle = commandedThrottle;
abThrottle = commandedThrottle;
}
else
{
mainThrottle = Math.Min(commandedThrottle * 1.5d, 1d);
abThrottle = Math.Max(commandedThrottle * 3d - 2d, 0d);
}
}
else
{
mainThrottle = commandedThrottle;
abThrottle = 0d;
}
double coreThrottle = SolverMathUtil.Lerp(minThrottle, 1d, mainThrottle);
prat3 = CPR;
double invfac = eta_c * th1.Gamma / (th1.Gamma - 1.0);
double turbineWork = 0d;
for (int i = 0; i < 20; i++) //use iteration to calculate CPR
{
th3 = th1.AdiabaticProcessWithPressureRatio(prat3, efficiency: eta_c);
// FIXME use ffFraction here? Instead of just multiplying thrust by fuel fraction in the module?
// is so, set multiplyThrustByFuelFrac = false in the ModuleEnginesAJEJet.
th4 = th3.AddFuelToTemperature(Tt4, h_f, throttle: coreThrottle);
th5 = th4.AdiabaticProcessWithTempRatio(TTR, out turbineWork, eta_t);
th3 = th1.AdiabaticProcessWithWork(turbineWork / (1d + fanWorkConstant), efficiency: eta_c);
double x = prat3;
prat3 = th3.P / th1.P;
if (Math.Abs(x - prat3) < 0.01)
{
break;
}
}
if (BPR > 0d)
{
th2 = th1.AdiabaticProcessWithWork(turbineWork * fanWorkConstant / (1d + fanWorkConstant) / BPR, efficiency: eta_c);
th2.MassRatio = BPR;
prat2 = th2.P / th1.P;
}
if (exhaustMixer && BPR > 0)//exhaust mixer
{
th2.P *= 0.98;
th6 = EngineThermodynamics.MixStreams(th5, th2);
}
else
{
th6 = th5;
}
if (Tt7 > 0)
{
th7 = th6.AddFuelToTemperature(Tt7, h_f, throttle: abThrottle);
}
else
{
th7 = th6;
}
//Nozzle code is from NASA
double p8, V8;
//double A8;
double epr = th7.P / th1.P;
double etr = th7.T / th1.T;
// The factor of 0.75 implies that the mach number of air entering the compressor is about 0.5
// The factor can be calculated as
// 1 / (1 - ff_ab) * sqrt(gamma_c/gamma_ab * R_ab / R_c) * M * (1 + (gamma_c + 1)/2 * M^2)^(-(gamma_c + 1)/(2 * (gamma_c - 1)) / ((gamma_ab + 1) / 2)^(-(gamma_ab + 1)/(2 * (gamma_ab - 1))
//
//A8 = .75 * Aref * th7.MassRatio * Math.Sqrt(th1.Gamma / th7.Gamma * th7.R / th1.R) * Math.Sqrt(etr) / epr;//ratio of nozzle area to ref area
//double area8max = .75 * Math.Sqrt(etr) / epr;//ratio of nozzle area to ref area
//A8 = area8max * Aref;
//if (exhaustMixer && BPR > 0)
// A8 *= (1 + BPR);
//double eair = th7.P * Math.Sqrt(th7.Gamma / th7.R / th7.T) *
// Math.Pow((0.5d + 0.5d * th7.Gamma), 0.5d * (1d + th7.Gamma) / (1d - th7.Gamma));//corrected mass flow per area
//mdot = eair * A8;
// Assume turbine is choked all the time
coreAirflow = th4.CalculateMassFlow(Aref * turbineAreaRatio, 1d) / th4.MassRatio;
mdot = th7.MassRatio * coreAirflow;
if (!adjustableNozzle)
{
p8 = th7.ChokedPressure();
if (p8 < th0.P)
{
p8 = th0.P;
}
}
else
{
p8 = th0.P;
}
double exitEnergy = th7.Cp * th7.T * eta_n * (1.0 - Math.Pow(p8 / th7.P, th7.R / th7.Cp));
V8 = Math.Sqrt(Math.Abs(2d * exitEnergy)); //exit velocity - may be negative under certain conditions
V8 *= Math.Sign(exitEnergy);
double exitMach = th7.CalculateMach(Math.Abs(V8));
Anozzle = th7.CalculateFlowArea(mdot, exitMach);
thrust = V8 * mdot + (p8 - th0.P) * Anozzle;
thrust -= mdot * (1d - th7.FF) * (vel);//ram drag
if (BPR > 0d && FPR > 1d && exhaustMixer == false)
{
//fan thrust from NASA
double pfexit = th2.ChokedPressure();
if (pfexit < th0.P)
{
pfexit = th0.P;
}
double fExitEnergy = th2.Cp * th2.T * eta_n * (1d - Math.Pow(pfexit / th2.P, th2.R / th2.Cp));
double ues = Math.Sqrt(Math.Abs(2d * fExitEnergy));
ues *= Math.Sign(fExitEnergy);
double bypassAirFlow = coreAirflow * th2.MassRatio; // th2.MassRatio will be equal to BPR at this point
double ANozzleBypass = th2.CalculateFlowArea(bypassAirFlow, th2.CalculateMach(ues));
thrust += bypassAirFlow * ues + (pfexit - p0) * ANozzleBypass;
thrust -= bypassAirFlow * vel;
}
thrust *= flowMult * ispMult;
fuelFlow = mdot * th7.FF * flowMult;
Isp = thrust / (fuelFlow * 9.80665);
SFC = 3600d / Isp;
/*
* debugstring = "";
* debugstring += "TTR:\t" + TTR.ToString("F3") + "\r\n";
* debugstring += "CPR:\t" + prat3.ToString("F3") + "\r\n"; ;
* debugstring += "p0: " + th0.P.ToString("F2") + "\tt0: " + th0.T.ToString("F2") + "\r\n";
* debugstring += "P1: " + th1.P.ToString("F2") + "\tT1: " + th1.T.ToString("F2") + "\r\n";
* debugstring += "P2: " + th2.P.ToString("F2") + "\tT2: " + th2.T.ToString("F2") + "\r\n";
* debugstring += "P3: " + th3.P.ToString("F2") + "\tT3: " + th3.T.ToString("F2") + "\r\n";
* debugstring += "P4: " + th4.P.ToString("F2") + "\tT4: " + th4.T.ToString("F2") + "\r\n";
* debugstring += "P5: " + th5.P.ToString("F2") + "\tT5: " + th5.T.ToString("F2") + "\r\n";
* debugstring += "P6: " + th6.P.ToString("F2") + "\tT6: " + th6.T.ToString("F2") + "\r\n";
* debugstring += "P7: " + th7.P.ToString("F2") + "\tT7: " + th7.ToString("F2") + "\r\n";
* debugstring += "EPR: " + epr.ToString("F2") + "\tETR: " + etr.ToString("F2") + "\r\n";
*
* debugstring += "FF: " + th5.FF.ToString("P") + "\t";
* debugstring += "FF_AB: " + th7.FF.ToString("P") + "\r\n";
* debugstring += "V8: " + V8.ToString("F2") + "\tA8: " + A8.ToString("F2") + "\r\n";
* debugstring += "Thrust: " + (thrust / 1000).ToString("F1") + "\tmdot: " + mdot.ToString("F2") + "\r\n";
* debugstring += "Isp: " + Isp.ToString("F0") + "\tSFC: " + (3600 / Isp).ToString("F3") + "\r\n";
* Debug.Log(debugstring);*/
}
else
{
double shutdownScalar = Math.Pow(spoolFactor, TimeWarp.fixedDeltaTime);
th3.T = Math.Max(t0, th3.T * shutdownScalar - 4d);
mainThrottle = Math.Max(0d, mainThrottle * shutdownScalar - 0.05d);
if (Tt7 > 0)
{
abThrottle = Math.Max(0d, abThrottle * shutdownScalar - 0.05d);
}
}
// Set FX power
if (Tt7 == 0)
{
fxPower = (float)mainThrottle;
}
else
{
fxPower = (float)(mainThrottle * 0.25d + abThrottle * 0.75d);
}
}
protected new string GetThrustInfo()
{
string output = "";
if (engineSolver == null || !(engineSolver is SolverRF))
CreateEngine();
(engineSolver as SolverRF).SetEngineStatus(true, true, true);
// get stats
double pressure = 101.325d, temperature = 288.15d, density = 1.225d;
if (Planetarium.fetch != null)
{
CelestialBody home = Planetarium.fetch.Home;
if (home != null)
{
pressure = home.GetPressure(0d);
temperature = home.GetTemperature(0d);
density = home.GetDensity(pressure, temperature);
}
}
ambientTherm = new EngineThermodynamics();
ambientTherm.FromAmbientConditions(pressure, temperature, density);
inletTherm = new EngineThermodynamics();
inletTherm.CopyFrom(ambientTherm);
currentThrottle = 1f;
lastPropellantFraction = 1d;
bool oldE = EngineIgnited;
EngineIgnited = true;
(engineSolver as SolverRF).UpdateThrustRatio(1d);
UpdateFlightCondition(ambientTherm, 0d, Vector3d.zero, 0d, true);
double thrustASL = (engineSolver.GetThrust() * 0.001d);
if (atmChangeFlow) // If it's a jet
{
output += "<b>Static Thrust: </b>" + (thrustASL).ToString("0.0##") + " kN" + ThrottleString();
if (useVelCurve) // if thrust changes with mach
{
float vMin, vMax, tMin, tMax;
velCurve.FindMinMaxValue(out vMin, out vMax, out tMin, out tMax); // get the max mult, and thus report maximum thrust possible.
output += "\n<b>Max. Thrust: </b>" + (thrustASL* vMax).ToString("0.0##") + " kN Mach " + tMax.ToString("0.#");
}
}
else
{
// get stats again
double spaceHeight = 131000d;
pressure = 0d;
density = 0d;
if (Planetarium.fetch != null)
{
CelestialBody home = Planetarium.fetch.Home;
if (home != null)
{
temperature = home.GetTemperature(home.atmosphereDepth + 1d);
spaceHeight = home.atmosphereDepth + 1000d;
}
}
else
temperature = PhysicsGlobals.SpaceTemperature;
ambientTherm.FromAmbientConditions(pressure, temperature, density);
UpdateFlightCondition(ambientTherm, spaceHeight, Vector3d.zero, 0d, true);
double thrustVac = (engineSolver.GetThrust() * 0.001d);
if (thrustASL != thrustVac)
{
output += (throttleLocked ? "<b>" : "<b>Max. ") + "Thrust (Vac.): </b>" + (thrustVac).ToString("0.0##") + " kN" + ThrottleString()
+ "\n" + (throttleLocked ? "<b>" : "<b>Max. ") + "Thrust (ASL): </b>" + (thrustASL).ToString("0.0##") + " kN";
}
else
{
output += (throttleLocked ? "<b>" : "<b>Max. ") + "Thrust: </b>" + (thrustVac).ToString("0.0##") + " kN" + ThrottleString();
}
}
output += "\n";
EngineIgnited = oldE;
return output;
}
public override void CalculatePerformance(double airRatio, double commandedThrottle, double flowMult, double ispMult)
{
// set base bits
base.CalculatePerformance(airRatio, commandedThrottle, flowMult, ispMult);
// if we're not combusting, don't combust and start cooling off
combusting = running;
statusString = "Nominal";
if (running && (!oxygen || eair0 <= 0d))
{
combusting = false;
statusString = "No oxygen";
}
else if (ffFraction <= 0d)
{
combusting = false;
statusString = "No fuel";
}
else if (th1.P * 0.9 < th0.P)
{
combusting = false;
statusString = "Below ignition speed";
}
else if (airRatio < 0.01d)
{
combusting = false;
statusString = "Insufficient intake area";
}
else if (underwater)
{
combusting = false;
statusString = "Nozzle in water";
}
if (combusting)
{
th7 = th1.AddFuelToTemperature(9999d, h_f, throttle: throttle, maxFar: maxFar);
th7.P *= 0.95;
//Nozzle code is from NASA
//double A8;
double epr = th7.P / th1.P;
double etr = th7.T / th1.T;
coreAirflow = th7.CalculateMassFlow(Athroat, 1d) / th7.MassRatio;
mdot = th7.MassRatio * coreAirflow;
if (adjustableNozzle)
{
p8 = th0.P;
double exitEnergy = th7.Cp * th7.T * eta_n * (1.0 - Math.Pow(p8 / th7.P, th7.R / th7.Cp));
V8 = Math.Sqrt(Math.Abs(2d * exitEnergy)); //exit velocity - may be negative under certain conditions
V8 *= Math.Sign(exitEnergy);
double exitMach = th7.CalculateMach(Math.Abs(V8));
Anozzle = th7.CalculateFlowArea(mdot, exitMach);
}
thrust = V8 * mdot + (p8 - th0.P) * Anozzle;
thrust -= mdot * (1d - th7.FF) * (vel);//ram drag
thrust *= flowMult * ispMult;
fuelFlow = mdot * th7.FF * flowMult;
Isp = thrust / (fuelFlow * 9.80665);
SFC = 3600d / Isp;
}
// Set FX power
fxPower = (float)throttle;
}
public override void UpdateSolver(EngineThermodynamics ambientTherm, double altitude, Vector3d vel, double mach, bool sIgnited, bool oxygen, bool underwater)
{
UnityEngine.Profiling.Profiler.BeginSample("ModuleEnginesRF.UpdateSolver");
throttledUp = false;
// handle ignition
if (HighLogic.LoadedSceneIsFlight)
{
if (vessel.ctrlState.mainThrottle > 0f || throttleLocked)
{
throttledUp = true;
}
else
{
ignited = false; // FIXME handle engine spinning down, non-instant shutoff.
}
IgnitionUpdate();
// Ullage
if (ullage && RFSettings.Instance.simulateUllage)
{
if (EngineIgnited && ignited && throttledUp && rfSolver.GetRunning())
{
double state = ullageSet.GetUllageStability();
double testValue = Math.Pow(state, RFSettings.Instance.stabilityPower);
if (UnityEngine.Random.value > testValue)
{
ScreenMessages.PostScreenMessage(ullageFail);
FlightLogger.fetch.LogEvent($"[{FormatTime(vessel.missionTime)}] {ullageFail.message}");
reignitable = false;
ullageOK = false;
ignited = false;
Flameout("Vapor in feed line");
}
}
}
if (!ullageSet.PressureOK())
{
Flameout("Lack of pressure", false, ignited);
ignited = false;
reignitable = false;
}
rfSolver.SetPropellantStatus(ullageSet.PressureOK(), ullageOK || !RFSettings.Instance.simulateUllage);
// do thrust curve
if (ignited && useThrustCurve)
{
thrustCurveRatio = (float)(curveProp.totalResourceAvailable / curveProp.totalResourceCapacity);
thrustCurveDisplay = thrustCurve.Evaluate(thrustCurveUseTime ? curveTime : thrustCurveRatio);
if (thrustCurveUseTime && EngineIgnited)
{
curveTime += TimeWarp.fixedDeltaTime;
}
rfSolver.UpdateThrustRatio(thrustCurveDisplay);
}
}
// Set part temp
rfSolver.SetPartTemp(part.temperature);
// do heat
// heatProduction = (float)(scaleRecip * extHeatkW / PhysicsGlobals.InternalHeatProductionFactor * part.thermalMassReciprocal);
heatProduction = 0;
// run base method code
base.UpdateSolver(ambientTherm, altitude, vel, mach, ignited, oxygen, CheckTransformsUnderwater());
UnityEngine.Profiling.Profiler.EndSample();
}
public override void UpdateSolver(EngineThermodynamics ambientTherm, double altitude, Vector3d vel, double mach, bool sIgnited, bool oxygen, bool underwater)
{
throttledUp = false;
// handle ignition
if (HighLogic.LoadedSceneIsFlight)
{
if (vessel.ctrlState.mainThrottle > 0f || throttleLocked)
{
throttledUp = true;
}
else
{
ignited = false;
}
IgnitionUpdate();
// Ullage
bool pressureOK = ullageSet.PressureOK();
propellantStatus = "Nominal";
if (ullage && RFSettings.Instance.simulateUllage)
{
propellantStatus = ullageSet.GetUllageState(out ullageColor);
part.stackIcon.SetIconColor(ullageColor);
if (EngineIgnited && ignited && throttledUp && rfSolver.GetRunning())
{
double state = ullageSet.GetUllageStability();
double testValue = Math.Pow(state, RFSettings.Instance.stabilityPower);
if (UnityEngine.Random.value > testValue)
{
ScreenMessages.PostScreenMessage(ullageFail);
FlightLogger.fetch.LogEvent("[" + FormatTime(vessel.missionTime) + "] " + ullageFail.message);
reignitable = false;
ullageOK = false;
ignited = false;
Flameout("Vapor in feed line");
}
}
}
if (!pressureOK)
{
propellantStatus = "Feed pressure too low"; // override ullage status indicator
Flameout("Lack of pressure", false, ignited);
ignited = false;
reignitable = false;
}
needSetPropStatus = false;
rfSolver.SetPropellantStatus(pressureOK, (ullageOK || !RFSettings.Instance.simulateUllage));
// do thrust curve
if (ignited && useThrustCurve)
{
thrustCurveRatio = (float)((propellants[curveProp].totalResourceAvailable / propellants[curveProp].totalResourceCapacity));
if (thrustCurveUseTime)
{
thrustCurveDisplay = thrustCurve.Evaluate(curveTime);
if (EngineIgnited)
{
curveTime += TimeWarp.fixedDeltaTime;
}
}
else
{
thrustCurveDisplay = thrustCurve.Evaluate(thrustCurveRatio);
}
rfSolver.UpdateThrustRatio(thrustCurveDisplay);
}
}
// Set part temp
rfSolver.SetPartTemp(part.temperature);
// do heat
// heatProduction = (float)(scaleRecip * extHeatkW / PhysicsGlobals.InternalHeatProductionFactor * part.thermalMassReciprocal);
heatProduction = 0;
// run base method code
base.UpdateSolver(ambientTherm, altitude, vel, mach, ignited, oxygen, CheckTransformsUnderwater());
}
protected string GetThrustInfo()
{
string output = string.Empty;
if (engineSolver == null || !(engineSolver is SolverRF))
{
CreateEngine();
}
rfSolver.SetPropellantStatus(true, true);
ambientTherm = EngineThermodynamics.StandardConditions(true);
inletTherm = ambientTherm;
currentThrottle = 1f;
lastPropellantFraction = 1d;
bool oldE = EngineIgnited;
EngineIgnited = true;
bool oldIg = ignited;
ignited = true;
rfSolver.UpdateThrustRatio(1d);
rfSolver.SetPropellantStatus(true, true);
UpdateSolver(ambientTherm, 0d, Vector3d.zero, 0d, true, true, false);
double thrustASL = (engineSolver.GetThrust() * 0.001d);
if (atmChangeFlow) // If it's a jet
{
output += "<b>Static Thrust: </b>" + (thrustASL).ToString("0.0##") + " kN" + ThrottleString();
if (useVelCurve) // if thrust changes with mach
{
float vMin, vMax, tMin, tMax;
velCurve.FindMinMaxValue(out vMin, out vMax, out tMin, out tMax); // get the max mult, and thus report maximum thrust possible.
output += "\n<b>Max. Thrust: </b>" + (thrustASL * vMax).ToString("0.0##") + " kN Mach " + tMax.ToString("0.#");
}
}
else
{
// get stats again
ambientTherm = EngineThermodynamics.VacuumConditions(true);
double spaceHeight = Planetarium.fetch?.Home?.atmosphereDepth + 1000d ?? 141000d;
UpdateSolver(ambientTherm, spaceHeight, Vector3d.zero, 0d, true, true, false);
double thrustVac = (engineSolver.GetThrust() * 0.001d);
if (thrustASL != thrustVac)
{
output += (throttleLocked ? "<b>" : "<b>Max. ") + "Thrust (Vac.): </b>" + (thrustVac).ToString("0.0##") + " kN" + ThrottleString()
+ "\n" + (throttleLocked ? "<b>" : "<b>Max. ") + "Thrust (ASL): </b>" + (thrustASL).ToString("0.0##") + " kN";
}
else
{
output += (throttleLocked ? "<b>" : "<b>Max. ") + "Thrust: </b>" + (thrustVac).ToString("0.0##") + " kN" + ThrottleString();
}
}
output += "\n";
EngineIgnited = oldE;
ignited = oldIg;
return(output);
}
protected string GetThrustInfo()
{
string output = string.Empty;
if (engineSolver == null || !(engineSolver is SolverRF))
{
CreateEngine();
}
rfSolver.SetPropellantStatus(true, true);
ambientTherm = EngineThermodynamics.StandardConditions(true);
inletTherm = ambientTherm;
currentThrottle = 1f;
lastPropellantFraction = 1d;
bool oldE = EngineIgnited;
EngineIgnited = true;
bool oldIg = ignited;
ignited = true;
rfSolver.UpdateThrustRatio(1d);
rfSolver.SetPropellantStatus(true, true);
UpdateSolver(ambientTherm, 0d, Vector3d.zero, 0d, true, true, false);
double thrustASL = (engineSolver.GetThrust() * 0.001d);
var weight = part.mass * (Planetarium.fetch?.Home?.GeeASL * 9.80665 ?? 9.80665);
if (atmChangeFlow) // If it's a jet
{
if (throttleLocked || minThrottle == 1f)
{
output += String.Format("<b> Static Thrust: </b>{0} (TWR {1}), {2}\n", Utilities.FormatThrust(thrustASL), (thrustASL / weight).ToString("0.0##"), (throttleLocked ? "throttle locked" : "unthrottleable"));
}
else
{
output += String.Format("{0}% min throttle\n", (minThrottle * 100f).ToString("N0"));
output += String.Format("<b>Max. Static Thrust: </b>{0} (TWR {1})\n", Utilities.FormatThrust(thrustASL), (thrustASL / weight).ToString("0.0##"));
output += String.Format("<b>Min. Static Thrust: </b>{0} (TWR {1})\n", Utilities.FormatThrust(thrustASL * minThrottle), (thrustASL * minThrottle / weight).ToString("0.0##"));
}
if (useVelCurve) // if thrust changes with mach
{
float vMin, vMax, tMin, tMax;
velCurve.FindMinMaxValue(out vMin, out vMax, out tMin, out tMax); // get the max mult, and thus report maximum thrust possible.
output += String.Format("<b>Max. Thrust: </b>{0} at Mach {1} (TWR {2})\n", Utilities.FormatThrust(thrustASL * vMax), tMax.ToString("0.#"), (thrustASL * vMax / weight).ToString("0.0##"));
}
}
else
{
// get stats again
ambientTherm = EngineThermodynamics.VacuumConditions(true);
double spaceHeight = Planetarium.fetch?.Home?.atmosphereDepth + 1000d ?? 141000d;
UpdateSolver(ambientTherm, spaceHeight, Vector3d.zero, 0d, true, true, false);
double thrustVac = (engineSolver.GetThrust() * 0.001d);
if (throttleLocked || minThrottle == 1f)
{
var suffix = throttleLocked ? "throttle locked" : "unthrottleable";
if (thrustASL != thrustVac)
{
output += String.Format("<b>Thrust (Vac): </b>{0} (TWR {1}), {2}\n", Utilities.FormatThrust(thrustVac), (thrustVac / weight).ToString("0.0##"), suffix);
output += String.Format("<b>Thrust (ASL): </b>{0} (TWR {1}), {2}\n", Utilities.FormatThrust(thrustASL), (thrustASL / weight).ToString("0.0##"), suffix);
}
else
{
output += String.Format("<b>Thrust: </b>{0} (TWR {1}), {2}\n", Utilities.FormatThrust(thrustVac), (thrustVac / weight).ToString("0.0##"), suffix);
}
}
else
{
output += String.Format("{0}% min throttle\n", (minThrottle * 100f).ToString("N0"));
if (thrustASL != thrustVac)
{
output += String.Format("<b>Max. Thrust (Vac): </b>{0} (TWR {1})\n", Utilities.FormatThrust(thrustVac), (thrustVac / weight).ToString("0.0##"));
output += String.Format("<b>Max. Thrust (ASL): </b>{0} (TWR {1})\n", Utilities.FormatThrust(thrustASL), (thrustASL / weight).ToString("0.0##"));
output += String.Format("<b>Min. Thrust (Vac): </b>{0} (TWR {1})\n", Utilities.FormatThrust(thrustVac * minThrottle), (thrustVac * minThrottle / weight).ToString("0.0##"));
output += String.Format("<b>Min. Thrust (ASL): </b>{0} (TWR {1})\n", Utilities.FormatThrust(thrustASL * minThrottle), (thrustASL * minThrottle / weight).ToString("0.0##"));
}
else
{
output += String.Format("<b>Max. Thrust: </b>{0} (TWR {1})\n", Utilities.FormatThrust(thrustVac), (thrustVac / weight).ToString("0.0##"));
output += String.Format("<b>Min. Thrust: </b>{0} (TWR {1})\n", Utilities.FormatThrust(thrustVac * minThrottle), (thrustVac * minThrottle / weight).ToString("0.0##"));
}
}
}
EngineIgnited = oldE;
ignited = oldIg;
return(output);
}
public override void UpdateFlightCondition(EngineThermodynamics ambientTherm, double altitude, Vector3d vel, double mach, bool oxygen)
{
throttledUp = false;
if (!(engineSolver is ModularEngineSolver)) {
base.UpdateFlightCondition(ambientTherm, altitude, vel, mach, oxygen);
return;
}
SolverRF realSolver = (engineSolver as SolverRF);
// handle ignition
if (HighLogic.LoadedSceneIsFlight && vessel != null)
{
if (vessel.ctrlState.mainThrottle > 0f || throttleLocked)
throttledUp = true;
else
ignited = false;
IgnitionUpdate();
// Ullage
bool pressureOK = ullageSet.PressureOK();
propellantStatus = "Nominal";
if (ullage && RFSettings.Instance.simulateUllage)
{
propellantStatus = ullageSet.GetUllageState();
if (EngineIgnited && ignited && throttledUp && realSolver.GetRunning())
{
double state = ullageSet.GetUllageStability();
double testValue = Math.Pow(state, RFSettings.Instance.stabilityPower);
if (UnityEngine.Random.value > testValue)
{
ScreenMessages.PostScreenMessage(ullageFail);
FlightLogger.eventLog.Add("[" + FormatTime(vessel.missionTime) + "] " + ullageFail.message);
reignitable = false;
ullageOK = false;
ignited = false;
Flameout("Vapor in feed line");
}
}
}
if (!pressureOK)
{
propellantStatus = "Feed pressure too low"; // override ullage status indicator
vFlameout("Lack of pressure", false, ignited);
ignited = false;
reignitable = false;
}
realSolver.SetEngineStatus(pressureOK, (ullageOK || !RFSettings.Instance.simulateUllage), ignited);
// do thrust curve
if (ignited && useThrustCurve)
{
thrustCurveRatio = (float)((propellants[curveProp].totalResourceAvailable / propellants[curveProp].totalResourceCapacity));
if (thrustCurveUseTime)
{
thrustCurveDisplay = thrustCurve.Evaluate(curveTime);
if (EngineIgnited)
{
curveTime += TimeWarp.fixedDeltaTime;
}
}
else
{
thrustCurveDisplay = thrustCurve.Evaluate(thrustCurveRatio);
}
realSolver.UpdateThrustRatio(thrustCurveDisplay);
thrustCurveDisplay *= 100f;
}
}
// Set part temp
realSolver.SetPartTemp(part.temperature);
// do heat
heatProduction = (float)(scaleRecip * extHeatkW / PhysicsGlobals.InternalHeatProductionFactor * part.thermalMassReciprocal);
// run base method code
base.UpdateFlightCondition(ambientTherm, altitude, vel, mach, oxygen);
}
