protected string GetThrustInfo()
{
string output = "";
if (engineSolver == null || !(engineSolver is SolverRF))
CreateEngine();
rfSolver.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;
rfSolver.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;
}
protected string GetStaticThrustInfo(bool primaryField)//TODO WIP
{
string output = "";
if (engineSolver == null || !(engineSolver is SolverDEV))
CreateEngine();
SolverDEV devSolver = (engineSolver as SolverDEV);
devSolver.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);
}
}
currentThrottle = 1f;
lastPropellantFraction = 1d;
bool oldE = EngineIgnited;
EngineIgnited = true;
devSolver.UpdateThrustRatio(1d);
ambientTherm = new EngineThermodynamics();
ambientTherm.FromAmbientConditions(pressure, temperature, density);
inletTherm = new EngineThermodynamics();
inletTherm.CopyFrom(ambientTherm);
UpdateFlightCondition(ambientTherm, 0d, Vector3d.zero, 0d, true);
double thrust_atm = (devSolver.GetThrust() * 0.001d);
double Isp_atm = devSolver.GetIsp();
double Cstar_atm = devSolver.Cstar;
double Ct_atm = devSolver.Ct;
ambientTherm = new EngineThermodynamics();
ambientTherm.FromAmbientConditions(0d, 4d, 0d);
inletTherm = new EngineThermodynamics();
inletTherm.CopyFrom(ambientTherm);
UpdateFlightCondition(ambientTherm, 0d, Vector3d.zero, 0d, true);
double thrust_vac = (devSolver.GetThrust() * 0.001d);
double Isp_vac = devSolver.GetIsp();
double Cstar_vac = devSolver.Cstar;
double Ct_vac = devSolver.Ct;
double P_vac = devSolver.GetEnginePressure();
double T_vac = devSolver.GetEngineTemp();
ambientTherm = new EngineThermodynamics();
ambientTherm.FromAmbientConditions(pressure * 2, temperature, density * 2);
inletTherm = new EngineThermodynamics();
inletTherm.CopyFrom(ambientTherm);
UpdateFlightCondition(ambientTherm, 0d, Vector3d.zero, 0d, true);
double thrust_2atm = (devSolver.GetThrust() * 0.001d);
double Isp_2atm = devSolver.GetIsp();
double Cstar_2atm = devSolver.Cstar;
double Ct_2atm = devSolver.Ct;
FloatCurve tC = new FloatCurve();
tC.Add(0, (float)Isp_vac);
tC.Add(1, (float)Isp_atm);
tC.Add(2, (float)Isp_2atm);
atmosphereCurve = tC;
maxThrust = (float)Math.Max(thrust_vac, thrust_atm);
output += "<b>Max. Thrust(<color=#00FF99>ASL</color>/<color=#99CCFF>Vac.</color>):</b> <color=#00FF99>" + thrust_atm.ToString("N2") + "</color><b>/</b><color=#99CCFF>" + thrust_vac.ToString("N1") + "</color>kN ";
output += ThrottleString()+"\n";
output += "<b>Isp(<color=#00FF99>ASL</color>/<color=#99CCFF>Vac.</color>):</b> <color=#00FF99>" + Isp_atm.ToString("N2") + "</color><b>/</b><color=#99CCFF>" + Isp_vac.ToString("N2") + "</color>s\n";
output += "<b><color=#0099ff>Ignitions Available: </color></b>" + ignitions + "\n";
output += "<b><color=#0099ff>Max. Burn time: </color></b>" + maxBurnTime + " Sec.\n";
if (!primaryField) {
output += "<b>C*(<color=#00FF99>ASL</color>/<color=#99CCFF>Vac.</color>):</b> <color=#00FF99>" + Cstar_atm.ToString("N2") + "</color><b>/</b><color=#99CCFF>" + Cstar_vac.ToString("N2") + "</color>m/s\n";
output += "<b>Ct(<color=#00FF99>ASL</color>/<color=#99CCFF>Vac.</color>):</b> <color=#00FF99>" + Ct_atm.ToString("N2") + "</color><b>/</b><color=#99CCFF>" + Ct_vac.ToString("N2") + "</color>\n";
output += $"<b>Chamber Pressure:\n</b>{P_vac.ToString("N1")}<b>/</b>{nominalPcns.ToString("N1")}kPa\n<b>Chamber Temperature:\n</b>{T_vac.ToString("N1")}<b>/</b>{nominalTcns.ToString("N1")}K\n";
output += $"<b>Nozzle Exit Pressure: </b>{nominalPe} kPa\n<b>Nozzle Throat Area:</b>{At} m^2\n";
}
output += "\n";
EngineIgnited = oldE;
return output;
}
