| public static GetResourceDensity ( int type ) : float | ||
| type | int | |
| Résultat | float | |
public void SetResourceConsumptions()
{
if (this.part.HasModule <MultiModeEngine>())
{
string mode = this.part.GetModule <MultiModeEngine>().mode;
foreach (ModuleEnginesFX engine in this.part.GetModules <ModuleEnginesFX>())
{
if (engine.engineID == mode)
{
double flowRate = 0d;
if (part.vessel != null)
{
if (engine.throttleLocked)
{
flowRate = engine.maxThrust * (engine.thrustPercentage / 100f) / (isp * 9.81d);
}
else
{
if (part.vessel.Landed)
{
flowRate = Math.Max(0.000001d, engine.maxThrust * (engine.thrustPercentage / 100f) * FlightInputHandler.state.mainThrottle) / (isp * 9.81d);
}
else
{
if (engine.requestedThrust > 0)
{
flowRate = engine.requestedThrust / (isp * 9.81d);
}
else
{
flowRate = engine.maxThrust * (engine.thrustPercentage / 100f) / (isp * 9.81d);
}
}
}
}
else
{
flowRate = engine.maxThrust * (engine.thrustPercentage / 100f) / (isp * 9.81d);
}
float flowMass = 0f;
foreach (Propellant propellant in engine.propellants)
{
flowMass += propellant.ratio * ResourceContainer.GetResourceDensity(propellant.id);
}
foreach (Propellant propellant in engine.propellants)
{
if (propellant.name == "ElectricCharge" || propellant.name == "IntakeAir")
{
continue;
}
double consumptionRate = propellant.ratio * flowRate / flowMass;
resourceConsumptions.Add(propellant.id, consumptionRate);
}
}
}
}
else if (this.part.HasModule <ModuleEnginesFX>())
{
foreach (ModuleEnginesFX engine in part.GetModules <ModuleEnginesFX>())
{
double flowRate = 0d;
if (part.vessel != null)
{
if (engine.throttleLocked)
{
flowRate = engine.maxThrust * (engine.thrustPercentage / 100f) / (isp * 9.81d);
}
else
{
if (part.vessel.Landed)
{
flowRate = Math.Max(0.000001d, engine.maxThrust * (engine.thrustPercentage / 100f) * FlightInputHandler.state.mainThrottle) / (isp * 9.81d);
}
else
{
if (engine.requestedThrust > 0)
{
flowRate = engine.requestedThrust / (isp * 9.81d);
}
else
{
flowRate = engine.maxThrust * (engine.thrustPercentage / 100f) / (isp * 9.81d);
}
}
}
}
else
{
flowRate = engine.maxThrust * (engine.thrustPercentage / 100f) / (isp * 9.81d);
}
float flowMass = 0f;
foreach (Propellant propellant in engine.propellants)
{
flowMass += propellant.ratio * ResourceContainer.GetResourceDensity(propellant.id);
}
foreach (Propellant propellant in engine.propellants)
{
if (propellant.name == "ElectricCharge" || propellant.name == "IntakeAir")
{
continue;
}
double consumptionRate = propellant.ratio * flowRate / flowMass;
resourceConsumptions.Add(propellant.id, consumptionRate);
}
}
}
else if (this.part.HasModule <ModuleEngines>())
{
foreach (ModuleEngines engine in part.GetModules <ModuleEngines>())
{
double flowRate = 0d;
if (part.vessel != null)
{
if (engine.throttleLocked)
{
flowRate = engine.maxThrust * (engine.thrustPercentage / 100f) / (isp * 9.81d);
}
else
{
if (part.vessel.Landed)
{
flowRate = Math.Max(0.000001d, engine.maxThrust * (engine.thrustPercentage / 100f) * FlightInputHandler.state.mainThrottle) / (isp * 9.81d);
}
else
{
if (engine.requestedThrust > 0)
{
flowRate = engine.requestedThrust / (isp * 9.81d);
}
else
{
flowRate = engine.maxThrust * (engine.thrustPercentage / 100f) / (isp * 9.81d);
}
}
}
}
else
{
flowRate = engine.maxThrust * (engine.thrustPercentage / 100f) / (isp * 9.81d);
}
float flowMass = 0f;
foreach (Propellant propellant in engine.propellants)
{
flowMass += propellant.ratio * ResourceContainer.GetResourceDensity(propellant.id);
}
foreach (Propellant propellant in engine.propellants)
{
if (propellant.name == "ElectricCharge" || propellant.name == "IntakeAir")
{
continue;
}
double consumptionRate = propellant.ratio * flowRate / flowMass;
resourceConsumptions.Add(propellant.id, consumptionRate);
}
}
}
}
public EngineSim(PartSim theEngine,
double atmosphere,
double velocity,
float maxThrust,
float minThrust,
float thrustPercentage,
float requestedThrust,
Vector3 vecThrust,
float realIsp,
FloatCurve atmosphereCurve,
FloatCurve velocityCurve,
bool throttleLocked,
List <Propellant> propellants,
bool active,
bool correctThrust)
{
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);
partSim = theEngine;
isActive = active;
thrust = (maxThrust - minThrust) * (thrustPercentage / 100f) + minThrust;
//MonoBehaviour.print("thrust = " + thrust);
thrustVec = vecThrust;
double flowRate = 0d;
if (partSim.hasVessel)
{
//MonoBehaviour.print("hasVessel is true");
actualThrust = requestedThrust;
if (velocityCurve != null)
{
actualThrust *= velocityCurve.Evaluate((float)velocity);
//MonoBehaviour.print("actualThrust at velocity = " + actualThrust);
}
isp = atmosphereCurve.Evaluate((float)partSim.part.staticPressureAtm);
if (isp == 0d)
{
MonoBehaviour.print("Isp at " + partSim.part.staticPressureAtm + " is zero. Flow rate will be NaN");
}
if (correctThrust && realIsp == 0)
{
float ispsl = atmosphereCurve.Evaluate(0);
if (ispsl != 0)
{
thrust = thrust * isp / ispsl;
}
else
{
MonoBehaviour.print("Isp at sea level is zero. Unable to correct thrust.");
}
//MonoBehaviour.print("corrected thrust = " + thrust);
}
if (velocityCurve != null)
{
thrust *= velocityCurve.Evaluate((float)velocity);
//MonoBehaviour.print("thrust at velocity = " + thrust);
}
if (throttleLocked)
{
//MonoBehaviour.print("throttleLocked is true");
flowRate = thrust / (isp * 9.81d);
}
else
{
if (partSim.isLanded)
{
//MonoBehaviour.print("partSim.isLanded is true, mainThrottle = " + FlightInputHandler.state.mainThrottle);
flowRate = Math.Max(0.000001d, thrust * FlightInputHandler.state.mainThrottle) / (isp * 9.81d);
}
else
{
if (requestedThrust > 0)
{
if (velocityCurve != null)
{
requestedThrust *= velocityCurve.Evaluate((float)velocity);
//MonoBehaviour.print("requestedThrust at velocity = " + requestedThrust);
}
//MonoBehaviour.print("requestedThrust > 0");
flowRate = requestedThrust / (isp * 9.81d);
}
else
{
//MonoBehaviour.print("requestedThrust <= 0");
flowRate = thrust / (isp * 9.81d);
}
}
}
}
else
{
//MonoBehaviour.print("hasVessel is false");
isp = atmosphereCurve.Evaluate((float)atmosphere);
if (isp == 0d)
{
MonoBehaviour.print("Isp at " + atmosphere + " is zero. Flow rate will be NaN");
}
if (correctThrust)
{
float ispsl = atmosphereCurve.Evaluate(0);
if (ispsl != 0)
{
thrust = thrust * isp / ispsl;
}
else
{
MonoBehaviour.print("Isp at sea level is zero. Unable to correct thrust.");
}
//MonoBehaviour.print("corrected thrust = " + thrust);
}
if (velocityCurve != null)
{
thrust *= velocityCurve.Evaluate((float)velocity);
//MonoBehaviour.print("thrust at velocity = " + thrust);
}
flowRate = thrust / (isp * 9.81d);
}
if (SimManager.logOutput)
{
buffer = new StringBuilder(1024);
buffer.AppendFormat("flowRate = {0:g6}\n", flowRate);
}
float flowMass = 0f;
foreach (Propellant propellant in propellants)
{
flowMass += propellant.ratio * ResourceContainer.GetResourceDensity(propellant.id);
}
if (SimManager.logOutput)
{
buffer.AppendFormat("flowMass = {0:g6}\n", flowMass);
}
foreach (Propellant propellant in propellants)
{
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);
}
resourceConsumptions.Add(propellant.id, consumptionRate);
}
if (SimManager.logOutput)
{
MonoBehaviour.print(buffer);
}
}
