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;
}
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 = 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);
}
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);
}
