public static EngineSim New(PartSim theEngine,
ModuleEngines engineMod,
double atmosphere,
float machNumber,
bool vectoredThrust,
bool fullThrust,
LogMsg log)
{
float maxFuelFlow = engineMod.maxFuelFlow;
float minFuelFlow = engineMod.minFuelFlow;
float thrustPercentage = engineMod.thrustPercentage;
List <Transform> thrustTransforms = engineMod.thrustTransforms;
List <float> thrustTransformMultipliers = engineMod.thrustTransformMultipliers;
Vector3 vecThrust = CalculateThrustVector(vectoredThrust ? thrustTransforms : null,
vectoredThrust ? thrustTransformMultipliers : null,
log);
FloatCurve atmosphereCurve = engineMod.atmosphereCurve;
bool atmChangeFlow = engineMod.atmChangeFlow;
FloatCurve atmCurve = engineMod.useAtmCurve ? engineMod.atmCurve : null;
FloatCurve velCurve = engineMod.useVelCurve ? engineMod.velCurve : null;
float currentThrottle = engineMod.currentThrottle;
float IspG = engineMod.g;
bool throttleLocked = engineMod.throttleLocked || fullThrust;
List <Propellant> propellants = engineMod.propellants;
bool active = engineMod.isOperational;
float resultingThrust = engineMod.resultingThrust;
bool isFlamedOut = engineMod.flameout;
EngineSim engineSim = pool.Borrow();
engineSim.isp = 0.0;
engineSim.maxMach = 0.0f;
engineSim.actualThrust = 0.0;
engineSim.partSim = theEngine;
engineSim.isActive = active;
engineSim.thrustVec = vecThrust;
engineSim.isFlamedOut = isFlamedOut;
engineSim.resourceConsumptions.Reset();
engineSim.maxResourceConsumptions.Reset();
engineSim.resourceFlowModes.Reset();
engineSim.appliedForces.Clear();
double flowRate = 0.0;
double maxFlowRate = 0.0;
if (engineSim.partSim.hasVessel)
{
if (log != null)
{
log.AppendLine("hasVessel is true");
}
float flowModifier = GetFlowModifier(atmChangeFlow, atmCurve, engineSim.partSim.part.atmDensity, velCurve, machNumber, ref engineSim.maxMach);
engineSim.isp = atmosphereCurve.Evaluate((float)atmosphere);
engineSim.fullThrust = GetThrust(maxFuelFlow * flowModifier, engineSim.isp);
engineSim.thrust = GetThrust(Mathf.Lerp(minFuelFlow, maxFuelFlow, GetThrustPercent(thrustPercentage)) * flowModifier, engineSim.isp);
engineSim.actualThrust = engineSim.isActive ? resultingThrust : 0.0;
if (log != null)
{
log.buf.AppendFormat("flowMod = {0:g6}\n", flowModifier);
log.buf.AppendFormat("isp = {0:g6}\n", engineSim.isp);
log.buf.AppendFormat("thrust = {0:g6}\n", engineSim.thrust);
log.buf.AppendFormat("actual = {0:g6}\n", engineSim.actualThrust);
}
if (throttleLocked)
{
if (log != null)
{
log.AppendLine("throttleLocked is true, using thrust for flowRate");
}
flowRate = GetFlowRate(engineSim.thrust, engineSim.isp);
}
else
{
if (currentThrottle > 0.0f && engineSim.partSim.isLanded == false)
{
// TODO: This bit doesn't work for RF engines
if (log != null)
{
log.AppendLine("throttled up and not landed, using actualThrust for flowRate");
}
flowRate = GetFlowRate(engineSim.actualThrust, engineSim.isp);
}
else
{
if (log != null)
{
log.AppendLine("throttled down or landed, using thrust for flowRate");
}
flowRate = GetFlowRate(engineSim.thrust, engineSim.isp);
}
}
maxFlowRate = GetFlowRate(engineSim.fullThrust, engineSim.isp);
}
else
{
if (log != null)
{
log.buf.AppendLine("hasVessel is false");
}
float altitude = BasicDeltaV.Instance.AtmosphereDepth;
float flowModifier = GetFlowModifier(atmChangeFlow, atmCurve, BasicDeltaV.Instance.CurrentCelestialBody.GetDensity(BasicDeltaV.Instance.CurrentCelestialBody.GetPressure(altitude), BasicDeltaV.Instance.CurrentCelestialBody.GetTemperature(altitude)), velCurve, machNumber, ref engineSim.maxMach);
engineSim.isp = atmosphereCurve.Evaluate((float)atmosphere);
engineSim.fullThrust = GetThrust(maxFuelFlow * flowModifier, engineSim.isp);
engineSim.thrust = GetThrust(Mathf.Lerp(minFuelFlow, maxFuelFlow, GetThrustPercent(thrustPercentage)) * flowModifier, engineSim.isp);
engineSim.actualThrust = 0d;
if (log != null)
{
log.buf.AppendFormat("flowMod = {0:g6}\n", flowModifier);
log.buf.AppendFormat("isp = {0:g6}\n", engineSim.isp);
log.buf.AppendFormat("thrust = {0:g6}\n", engineSim.thrust);
log.buf.AppendFormat("actual = {0:g6}\n", engineSim.actualThrust);
log.AppendLine("no vessel, using thrust for flowRate");
}
flowRate = GetFlowRate(engineSim.thrust, engineSim.isp);
maxFlowRate = GetFlowRate(engineSim.fullThrust, engineSim.isp);
}
if (log != null)
{
log.buf.AppendFormat("flowRate = {0:g6}\n", flowRate);
}
float flowMass = 0f;
for (int i = 0; i < propellants.Count; ++i)
{
Propellant propellant = propellants[i];
if (!propellant.ignoreForIsp)
{
flowMass += propellant.ratio * ResourceContainer.GetResourceDensity(propellant.id);
}
}
if (log != null)
{
log.buf.AppendFormat("flowMass = {0:g6}\n", flowMass);
}
for (int i = 0; i < propellants.Count; ++i)
{
Propellant propellant = propellants[i];
if (propellant.name == "ElectricCharge" || propellant.name == "IntakeAir")
{
continue;
}
double consumptionRate = propellant.ratio * flowRate / flowMass;
if (log != null)
{
log.buf.AppendFormat(
"Add consumption({0}, {1}:{2:d}) = {3:g6}\n",
ResourceContainer.GetResourceName(propellant.id),
theEngine.name,
theEngine.partId,
consumptionRate);
}
engineSim.resourceConsumptions.Add(propellant.id, consumptionRate);
engineSim.resourceFlowModes.Add(propellant.id, (double)propellant.GetFlowMode());
double maxConsumptionRate = propellant.ratio * maxFlowRate / flowMass;
engineSim.maxResourceConsumptions.Add(propellant.id, maxConsumptionRate);
}
for (int i = 0; i < thrustTransforms.Count; i++)
{
Transform thrustTransform = thrustTransforms[i];
Vector3d direction = thrustTransform.forward.normalized;
Vector3d position = thrustTransform.position;
AppliedForce appliedForce = AppliedForce.New(direction * engineSim.thrust * thrustTransformMultipliers[i], position);
engineSim.appliedForces.Add(appliedForce);
}
return(engineSim);
}
public static RCSSim New(PartSim theEngine,
ModuleRCS engineMod,
double atmosphere,
float machNumber,
bool vectoredThrust,
bool fullThrust,
LogMsg log)
{
double maxFuelFlow = engineMod.maxFuelFlow;
// double minFuelFlow = engineMod.minFuelFlow;
float thrustPercentage = engineMod.thrustPercentage;
List <Transform> thrustTransforms = engineMod.thrusterTransforms;
// List<float> thrustTransformMultipliers = engineMod.th
Vector3 vecThrust = CalculateThrustVector(vectoredThrust ? thrustTransforms : null, log);
FloatCurve atmosphereCurve = engineMod.atmosphereCurve;
// bool atmChangeFlow = engineMod.at
// FloatCurve atmCurve = engineMod.useAtmCurve ? engineMod.atmCurve : null;
// FloatCurve velCurve = engineMod.useVelCurve ? engineMod.velCurve : null;
// float currentThrottle = engineMod.currentThrottle;
double IspG = engineMod.G;
// bool throttleLocked = engineMod.throttleLocked || fullThrust;
List <Propellant> propellants = engineMod.propellants;
bool active = engineMod.moduleIsEnabled;
// float resultingThrust = engineMod.resultingThrust;
bool isFlamedOut = engineMod.flameout;
RCSSim engineSim = pool.Borrow();
engineSim.isp = 0.0;
engineSim.maxMach = 0.0f;
engineSim.actualThrust = 0.0;
engineSim.partSim = theEngine;
engineSim.isActive = active;
engineSim.thrustVec = vecThrust;
engineSim.isFlamedOut = isFlamedOut;
engineSim.resourceConsumptions.Reset();
engineSim.resourceFlowModes.Reset();
engineSim.appliedForces.Clear();
double flowRate = 0.0;
if (engineSim.partSim.hasVessel)
{
if (log != null)
{
log.AppendLine("hasVessel is true");
}
engineSim.isp = atmosphereCurve.Evaluate((float)atmosphere);
engineSim.thrust = GetThrust(maxFuelFlow, engineSim.isp);
engineSim.actualThrust = engineSim.isActive ? engineSim.thrust : 0.0;
if (log != null)
{
log.buf.AppendFormat("isp = {0:g6}\n", engineSim.isp);
log.buf.AppendFormat("thrust = {0:g6}\n", engineSim.thrust);
log.buf.AppendFormat("actual = {0:g6}\n", engineSim.actualThrust);
}
if (true)
{
if (log != null)
{
log.AppendLine("throttleLocked is true, using thrust for flowRate");
}
flowRate = GetFlowRate(engineSim.thrust, engineSim.isp);
}
else
{
// if (currentThrottle > 0.0f && engineSim.partSim.isLanded == false)
// {
//// TODO: This bit doesn't work for RF engines
//if (log != null) log.AppendLine("throttled up and not landed, using actualThrust for flowRate");
// flowRate = GetFlowRate(engineSim.actualThrust, engineSim.isp);
// }
// else
// {
// if (log != null) log.AppendLine("throttled down or landed, using thrust for flowRate");
// flowRate = GetFlowRate(engineSim.thrust, engineSim.isp);
// }
}
}
else
{
if (log != null)
{
log.buf.AppendLine("hasVessel is false");
}
engineSim.isp = atmosphereCurve.Evaluate((float)atmosphere);
engineSim.thrust = GetThrust(maxFuelFlow, engineSim.isp);
engineSim.actualThrust = 0d;
if (log != null)
{
log.buf.AppendFormat("isp = {0:g6}\n", engineSim.isp);
log.buf.AppendFormat("thrust = {0:g6}\n", engineSim.thrust);
log.buf.AppendFormat("actual = {0:g6}\n", engineSim.actualThrust);
log.AppendLine("no vessel, using thrust for flowRate");
}
flowRate = GetFlowRate(engineSim.thrust, engineSim.isp);
}
if (log != null)
{
log.buf.AppendFormat("flowRate = {0:g6}\n", flowRate);
}
float flowMass = 0f;
for (int i = 0; i < propellants.Count; ++i)
{
Propellant propellant = propellants[i];
if (!propellant.ignoreForIsp)
{
flowMass += propellant.ratio * ResourceContainer.GetResourceDensity(propellant.id);
}
}
if (log != null)
{
log.buf.AppendFormat("flowMass = {0:g6}\n", flowMass);
}
for (int i = 0; i < propellants.Count; ++i)
{
Propellant propellant = propellants[i];
if (propellant.name == "ElectricCharge" || propellant.name == "IntakeAir")
{
continue;
}
double consumptionRate = propellant.ratio * flowRate / flowMass;
if (log != null)
{
log.buf.AppendFormat(
"Add consumption({0}, {1}:{2:d}) = {3:g6}\n",
ResourceContainer.GetResourceName(propellant.id),
theEngine.name,
theEngine.partId,
consumptionRate);
}
engineSim.resourceConsumptions.Add(propellant.id, consumptionRate);
engineSim.resourceFlowModes.Add(propellant.id, (double)propellant.GetFlowMode());
}
for (int i = 0; i < thrustTransforms.Count; i++)
{
Transform thrustTransform = thrustTransforms[i];
Vector3d direction = thrustTransform.forward.normalized;
Vector3d position = thrustTransform.position;
AppliedForce appliedForce = AppliedForce.New(direction * engineSim.thrust, position);
engineSim.appliedForces.Add(appliedForce);
}
return(engineSim);
}
public static EngineSim New(PartSim theEngine,
double atmosphere,
float machNumber,
float maxFuelFlow,
float minFuelFlow,
float thrustPercentage,
Vector3 vecThrust,
FloatCurve atmosphereCurve,
bool atmChangeFlow,
FloatCurve atmCurve,
FloatCurve velCurve,
float currentThrottle,
float IspG,
bool throttleLocked,
List <Propellant> propellants,
bool active,
float resultingThrust,
List <Transform> thrustTransforms,
LogMsg log)
{
EngineSim engineSim = pool.Borrow();
engineSim.isp = 0.0;
engineSim.maxMach = 0.0f;
engineSim.actualThrust = 0.0;
engineSim.partSim = theEngine;
engineSim.isActive = active;
engineSim.thrustVec = vecThrust;
engineSim.resourceConsumptions.Reset();
engineSim.resourceFlowModes.Reset();
engineSim.appliedForces.Clear();
double flowRate = 0.0;
if (engineSim.partSim.hasVessel)
{
if (log != null)
{
log.buf.AppendLine("hasVessel is true");
}
float flowModifier = GetFlowModifier(atmChangeFlow, atmCurve, engineSim.partSim.part.atmDensity, velCurve, machNumber, ref engineSim.maxMach);
engineSim.isp = atmosphereCurve.Evaluate((float)atmosphere);
engineSim.thrust = GetThrust(Mathf.Lerp(minFuelFlow, maxFuelFlow, GetThrustPercent(thrustPercentage)) * flowModifier, engineSim.isp);
engineSim.actualThrust = engineSim.isActive ? resultingThrust : 0.0;
if (log != null)
{
log.buf.AppendFormat("flowMod = {0:g6}\n", flowModifier);
log.buf.AppendFormat("isp = {0:g6}\n", engineSim.isp);
log.buf.AppendFormat("thrust = {0:g6}\n", engineSim.thrust);
log.buf.AppendFormat("actual = {0:g6}\n", engineSim.actualThrust);
}
if (throttleLocked)
{
if (log != null)
{
log.buf.AppendLine("throttleLocked is true, using thrust for flowRate");
}
flowRate = GetFlowRate(engineSim.thrust, engineSim.isp);
}
else
{
if (currentThrottle > 0.0f && engineSim.partSim.isLanded == false)
{
if (log != null)
{
log.buf.AppendLine("throttled up and not landed, using actualThrust for flowRate");
}
flowRate = GetFlowRate(engineSim.actualThrust, engineSim.isp);
}
else
{
if (log != null)
{
log.buf.AppendLine("throttled down or landed, using thrust for flowRate");
}
flowRate = GetFlowRate(engineSim.thrust, engineSim.isp);
}
}
}
else
{
if (log != null)
{
log.buf.AppendLine("hasVessel is false");
}
float flowModifier = GetFlowModifier(atmChangeFlow, atmCurve, SimManager.Body.GetDensity(FlightGlobals.getStaticPressure(0, SimManager.Body), FlightGlobals.getExternalTemperature(0, SimManager.Body)), velCurve, machNumber, ref engineSim.maxMach);
engineSim.isp = atmosphereCurve.Evaluate((float)atmosphere);
engineSim.thrust = GetThrust(Mathf.Lerp(minFuelFlow, maxFuelFlow, GetThrustPercent(thrustPercentage)) * flowModifier, engineSim.isp);
engineSim.actualThrust = 0d;
if (log != null)
{
log.buf.AppendFormat("flowMod = {0:g6}\n", flowModifier);
log.buf.AppendFormat("isp = {0:g6}\n", engineSim.isp);
log.buf.AppendFormat("thrust = {0:g6}\n", engineSim.thrust);
log.buf.AppendFormat("actual = {0:g6}\n", engineSim.actualThrust);
}
if (log != null)
{
log.buf.AppendLine("no vessel, using thrust for flowRate");
}
flowRate = GetFlowRate(engineSim.thrust, engineSim.isp);
}
if (log != null)
{
log.buf.AppendFormat("flowRate = {0:g6}\n", flowRate);
}
float flowMass = 0f;
for (int i = 0; i < propellants.Count; ++i)
{
Propellant propellant = propellants[i];
if (!propellant.ignoreForIsp)
{
flowMass += propellant.ratio * ResourceContainer.GetResourceDensity(propellant.id);
}
}
if (log != null)
{
log.buf.AppendFormat("flowMass = {0:g6}\n", flowMass);
}
for (int i = 0; i < propellants.Count; ++i)
{
Propellant propellant = propellants[i];
if (propellant.name == "ElectricCharge" || propellant.name == "IntakeAir")
{
continue;
}
double consumptionRate = propellant.ratio * flowRate / flowMass;
if (log != null)
{
log.buf.AppendFormat(
"Add consumption({0}, {1}:{2:d}) = {3:g6}\n",
ResourceContainer.GetResourceName(propellant.id),
theEngine.name,
theEngine.partId,
consumptionRate);
}
engineSim.resourceConsumptions.Add(propellant.id, consumptionRate);
engineSim.resourceFlowModes.Add(propellant.id, (double)propellant.GetFlowMode());
}
double thrustPerThrustTransform = engineSim.thrust / thrustTransforms.Count;
for (int i = 0; i < thrustTransforms.Count; i++)
{
Transform thrustTransform = thrustTransforms[i];
Vector3d direction = thrustTransform.forward.normalized;
Vector3d position = thrustTransform.position;
AppliedForce appliedForce = AppliedForce.New(direction * thrustPerThrustTransform, position);
engineSim.appliedForces.Add(appliedForce);
}
return(engineSim);
}
public static EngineSim New(PartSim theEngine,
ModuleEngines engineMod,
double atmosphere,
float machNumber,
bool vectoredThrust,
bool fullThrust,
LogMsg log)
{
float maxFuelFlow = engineMod.maxFuelFlow;
float minFuelFlow = engineMod.minFuelFlow;
float thrustPercentage = engineMod.thrustPercentage;
List <Transform> thrustTransforms = engineMod.thrustTransforms;
List <float> thrustTransformMultipliers = engineMod.thrustTransformMultipliers;
Vector3 vecThrust = CalculateThrustVector(vectoredThrust ? thrustTransforms : null,
vectoredThrust ? thrustTransformMultipliers : null,
log);
FloatCurve atmosphereCurve = engineMod.atmosphereCurve;
bool atmChangeFlow = engineMod.atmChangeFlow;
FloatCurve atmCurve = engineMod.useAtmCurve ? engineMod.atmCurve : null;
FloatCurve velCurve = engineMod.useVelCurve ? engineMod.velCurve : null;
FloatCurve thrustCurve = engineMod.useThrustCurve ? engineMod.thrustCurve : null;
float currentThrottle = engineMod.currentThrottle;
float IspG = engineMod.g;
bool throttleLocked = engineMod.throttleLocked || fullThrust;
List <Propellant> propellants = engineMod.propellants;
float thrustCurveRatio = engineMod.thrustCurveRatio;
foreach (Propellant p in propellants)
{
if (p.ignoreForThrustCurve)
{
continue;
}
double ratio = p.totalResourceAvailable / p.totalResourceCapacity;
if (ratio < thrustCurveRatio)
{
thrustCurveRatio = (float)ratio;
}
}
bool active = engineMod.isOperational;
//I do not know if this matters. RF and stock always have finalThrust. But stock uses resultingThrust in the mass flow calculations, so keep it.
float resultingThrust = SimManager.hasInstalledRealFuels ? engineMod.finalThrust : engineMod.resultingThrust;
bool isFlamedOut = engineMod.flameout;
EngineSim engineSim = pool.Borrow();
engineSim.isp = 0.0;
engineSim.maxMach = 0.0f;
engineSim.actualThrust = 0.0;
engineSim.partSim = theEngine;
engineSim.isActive = active;
engineSim.thrustVec = vecThrust;
engineSim.isFlamedOut = isFlamedOut;
engineSim.resourceConsumptionsForMass.Reset();
engineSim.resourceConsumptionsForIsp.Reset();
engineSim.resourceFlowModes.Reset();
engineSim.appliedForces.Clear();
double flowRate = 0.0;
if (engineSim.partSim.hasVessel)
{
if (log != null)
{
log.AppendLine("hasVessel is true");
}
float flowModifier = GetFlowModifier(atmChangeFlow, atmCurve, engineSim.partSim.part.atmDensity, velCurve, machNumber, thrustCurve, thrustCurveRatio, ref engineSim.maxMach, engineMod.flowMultCap, engineMod.flowMultCapSharpness);
engineSim.isp = atmosphereCurve.Evaluate((float)atmosphere);
engineSim.thrust = GetThrust(Mathf.Lerp(minFuelFlow, maxFuelFlow, GetThrustPercent(thrustPercentage)) * flowModifier, engineSim.isp);
engineSim.actualThrust = engineSim.isActive ? resultingThrust : 0.0;
if (log != null)
{
log.buf.AppendFormat("flowMod = {0:g6}\n", flowModifier);
log.buf.AppendFormat("isp = {0:g6}\n", engineSim.isp);
log.buf.AppendFormat("thrust = {0:g6}\n", engineSim.thrust);
log.buf.AppendFormat("actual = {0:g6}\n", engineSim.actualThrust);
log.buf.AppendFormat("final = {0:g6}\n", engineMod.finalThrust);
log.buf.AppendFormat("resulting = {0:g6}\n", engineMod.resultingThrust);
}
if (throttleLocked)
{
if (log != null)
{
log.AppendLine("throttleLocked is true, using thrust for flowRate");
}
flowRate = GetFlowRate(engineSim.thrust, engineSim.isp);
}
else
{
if (currentThrottle > 0.0f && engineSim.partSim.isLanded == false)
{
if (log != null)
{
log.AppendLine("throttled up and not landed, using actualThrust for flowRate");
}
flowRate = GetFlowRate(engineSim.actualThrust, engineSim.isp);
}
else
{
if (log != null)
{
log.AppendLine("throttled down or landed, using thrust for flowRate");
}
flowRate = GetFlowRate(engineSim.thrust, engineSim.isp);
}
}
}
else
{
if (log != null)
{
log.buf.AppendLine("hasVessel is false");
}
float flowModifier = GetFlowModifier(atmChangeFlow, atmCurve, CelestialBodies.SelectedBody.GetDensity(BuildAdvanced.Altitude), velCurve, machNumber, thrustCurve, thrustCurveRatio, ref engineSim.maxMach, engineMod.flowMultCap, engineMod.flowMultCapSharpness);
engineSim.isp = atmosphereCurve.Evaluate((float)atmosphere);
engineSim.thrust = GetThrust(Mathf.Lerp(minFuelFlow, maxFuelFlow, GetThrustPercent(thrustPercentage)) * flowModifier, engineSim.isp);
engineSim.actualThrust = 0d;
if (log != null)
{
log.buf.AppendFormat("flowMod = {0:g6}\n", flowModifier);
log.buf.AppendFormat("isp = {0:g6}\n", engineSim.isp);
log.buf.AppendFormat("thrust = {0:g6}\n", engineSim.thrust);
log.buf.AppendFormat("actual = {0:g6}\n", engineSim.actualThrust);
log.AppendLine("no vessel, using thrust for flowRate");
}
flowRate = GetFlowRate(engineSim.thrust, engineSim.isp);
}
if (log != null)
{
log.buf.AppendFormat("flowRate = {0:g6}\n", flowRate);
}
float flowMass = 0f;
for (int i = 0; i < propellants.Count; ++i)
{
Propellant propellant = propellants[i];
if (propellant.name == "ElectricCharge" || propellant.name == "IntakeAir")
{
continue;
}
flowMass += propellant.ratio * ResourceContainer.GetResourceDensity(propellant.id);
}
if (log != null)
{
log.buf.AppendFormat("flowMass = {0:g6}\n", flowMass);
}
for (int i = 0; i < propellants.Count; ++i)
{
Propellant propellant = propellants[i];
if (propellant.name == "ElectricCharge" || propellant.name == "IntakeAir")
{
continue;
}
double consumptionRate = propellant.ratio * flowRate / flowMass;
if (log != null)
{
log.buf.AppendFormat(
"Add consumption({0}, {1}:{2:d}) = {3:g6}\n",
ResourceContainer.GetResourceName(propellant.id),
theEngine.name,
theEngine.partId,
consumptionRate);
}
// Add all for mass
engineSim.resourceConsumptionsForMass.Add(propellant.id, consumptionRate);
if (!propellant.ignoreForIsp)
{
engineSim.resourceConsumptionsForIsp.Add(propellant.id, consumptionRate);
}
engineSim.resourceFlowModes.Add(propellant.id, (double)propellant.GetFlowMode());
}
for (int i = 0; i < thrustTransforms.Count; i++)
{
Transform thrustTransform = thrustTransforms[i];
Vector3d direction = thrustTransform.forward.normalized;
Vector3d position = thrustTransform.position;
AppliedForce appliedForce = AppliedForce.New(direction * engineSim.thrust * thrustTransformMultipliers[i], position);
engineSim.appliedForces.Add(appliedForce);
}
return(engineSim);
}
public static EngineSim New(PartSim theEngine,
double atmosphere,
double machNumber,
float maxFuelFlow,
float minFuelFlow,
float thrustPercentage,
Vector3 vecThrust,
FloatCurve atmosphereCurve,
bool atmChangeFlow,
FloatCurve atmCurve,
FloatCurve velCurve,
float currentThrottle,
float IspG,
bool throttleLocked,
List <Propellant> propellants,
bool active,
bool correctThrust,
List <Transform> thrustTransforms)
{
EngineSim engineSim = pool.Borrow();
StringBuilder buffer = null;
//MonoBehaviour.print("Create EngineSim for " + theEngine.name);
//MonoBehaviour.print("maxThrust = " + maxThrust);
//MonoBehaviour.print("minThrust = " + minThrust);
//MonoBehaviour.print("thrustPercentage = " + thrustPercentage);
//MonoBehaviour.print("requestedThrust = " + requestedThrust);
//MonoBehaviour.print("velocity = " + velocity);
engineSim.partSim = theEngine;
engineSim.isActive = active;
//engineSim.thrust = (maxThrust - minThrust) * (thrustPercentage / 100f) + minThrust;
//MonoBehaviour.print("thrust = " + thrust);
engineSim.thrustVec = vecThrust;
double flowRate = 0d;
if (engineSim.partSim.hasVessel)
{
//MonoBehaviour.print("hasVessel is true");
//engineSim.actualThrust = engineSim.isActive ? resultingThrust : 0.0;
engineSim.isp = atmosphereCurve.Evaluate((float)atmosphere);
//if (engineSim.isp == 0d)
//{
// MonoBehaviour.print("Isp at " + engineSim.partSim.part.staticPressureAtm + " is zero. Flow rate will be NaN");
//}
//if (correctThrust && realIsp == 0)
//{
// float ispsl = atmosphereCurve.Evaluate(0);
// if (ispsl != 0)
// {
// engineSim.thrust = engineSim.thrust * engineSim.isp / ispsl;
// }
// else
// {
// MonoBehaviour.print("Isp at sea level is zero. Unable to correct thrust.");
// }
// //MonoBehaviour.print("corrected thrust = " + thrust);
//}
//if (velocityCurve != null)
//{
// engineSim.thrust *= velocityCurve.Evaluate((float)velocity);
// //MonoBehaviour.print("thrust at velocity = " + thrust);
//}
float multiplier = 1;
if (atmChangeFlow)
{
multiplier = (float)(engineSim.partSim.part.atmDensity / 1.225);
if (atmCurve != null)
{
multiplier = atmCurve.Evaluate(multiplier);
}
}
if (velCurve != null)
{
multiplier *= velCurve.Evaluate((float)machNumber);
}
if (throttleLocked)
{
//MonoBehaviour.print("throttleLocked is true");
//flowRate = engineSim.thrust / (engineSim.isp * 9.82);
flowRate = Mathf.Lerp(minFuelFlow, maxFuelFlow, (thrustPercentage / 100f)) * multiplier;
}
else
{
if (engineSim.partSim.isLanded)
{
//MonoBehaviour.print("partSim.isLanded is true, mainThrottle = " + FlightInputHandler.state.mainThrottle);
flowRate = Mathf.Lerp(minFuelFlow, maxFuelFlow, FlightInputHandler.state.mainThrottle * (thrustPercentage / 100f)) * multiplier;
}
else
{
if (currentThrottle > 0)
{
//MonoBehaviour.print("requestedThrust > 0");
//flowRate = requestedThrust / (engineSim.isp * 9.82) * multiplier;
flowRate = Mathf.Lerp(minFuelFlow, maxFuelFlow, currentThrottle * (thrustPercentage / 100f)) * multiplier;
}
else
{
//MonoBehaviour.print("requestedThrust <= 0");
flowRate = Mathf.Lerp(minFuelFlow, maxFuelFlow, (thrustPercentage / 100f)) * multiplier;
}
}
}
}
else
{
//MonoBehaviour.print("hasVessel is false");
engineSim.isp = atmosphereCurve.Evaluate((float)atmosphere);
if (engineSim.isp == 0d)
{
MonoBehaviour.print("Isp at " + atmosphere + " is zero. Flow rate will be NaN");
}
//if (correctThrust)
//{
// float ispsl = atmosphereCurve.Evaluate(0);
// if (ispsl != 0)
// {
// engineSim.thrust = engineSim.thrust * engineSim.isp / ispsl;
// }
// else
// {
// MonoBehaviour.print("Isp at sea level is zero. Unable to correct thrust.");
// }
// //MonoBehaviour.print("corrected thrust = " + thrust);
//}
float multiplier = 1;
if (atmChangeFlow)
{
//multiplier = (float)(engineSim.partSim.part.atmDensity / 1.225);
multiplier = (float)atmosphere; // technically wrong but about the same for my Editor need
if (atmCurve != null)
{
multiplier = atmCurve.Evaluate(multiplier);
}
}
if (velCurve != null)
{
multiplier *= velCurve.Evaluate((float)machNumber);
}
flowRate = Mathf.Lerp(minFuelFlow, maxFuelFlow, (thrustPercentage / 100f)) * multiplier;
}
if (SimManager.logOutput)
{
buffer = new StringBuilder(1024);
buffer.AppendFormat("flowRate = {0:g6}\n", flowRate);
}
engineSim.thrust = flowRate * (engineSim.isp * IspG);
// TODO : look into the diff between the 2 in the old code (jet real thrust vs ideal thrust ?)
engineSim.actualThrust = engineSim.thrust;
float flowMass = 0f;
for (int i = 0; i < propellants.Count; i++)
{
Propellant propellant = propellants[i];
flowMass += propellant.ratio * ResourceContainer.GetResourceDensity(propellant.id);
}
if (SimManager.logOutput)
{
buffer.AppendFormat("flowMass = {0:g6}\n", flowMass);
}
for (int i = 0; i < propellants.Count; i++)
{
Propellant propellant = propellants[i];
if (propellant.name == "ElectricCharge" || propellant.name == "IntakeAir")
{
continue;
}
double consumptionRate = propellant.ratio * flowRate / flowMass;
if (SimManager.logOutput)
{
buffer.AppendFormat(
"Add consumption({0}, {1}:{2:d}) = {3:g6}\n",
ResourceContainer.GetResourceName(propellant.id),
theEngine.name,
theEngine.partId,
consumptionRate);
}
engineSim.resourceConsumptions.Add(propellant.id, consumptionRate);
}
if (SimManager.logOutput)
{
MonoBehaviour.print(buffer);
}
double thrustPerThrustTransform = engineSim.thrust / thrustTransforms.Count;
for (int i = 0; i < thrustTransforms.Count; i++)
{
Transform thrustTransform = thrustTransforms[i];
Vector3d direction = thrustTransform.forward.normalized;
Vector3d position = thrustTransform.position;
AppliedForce appliedForce = AppliedForce.New(direction * thrustPerThrustTransform, position);
engineSim.appliedForces.Add(appliedForce);
}
return(engineSim);
}