double CalculateSunArea(ModularFI.ModularFlightIntegrator fi, FlightIntegrator.PartThermalData ptd)
{
FARAeroPartModule module = null;
if (ptd.part.Modules.Contains("FARAeroPartModule"))
{
module = (FARAeroPartModule)ptd.part.Modules["FARAeroPartModule"];
}
if ((object)module != null)
{
double sunArea = module.ProjectedAreaWorld(fi.sunVector) * ptd.sunAreaMultiplier;
if (sunArea > 0)
{
return(sunArea);
}
else
{
return(fi.BaseFIGetSunArea(ptd));
}
}
else
{
return(fi.BaseFIGetSunArea(ptd));
}
}
double CalculateAreaExposed(ModularFI.ModularFlightIntegrator fi, Part part, FARAeroPartModule aeroModule)
{
if ((object)aeroModule != null)
{
double exposedArea = aeroModule.ProjectedAreaLocal(-part.dragVectorDirLocal);
if (exposedArea > 0)
{
return(exposedArea);
}
else
{
return(fi.BaseFICalculateAreaExposed(part));
}
}
else
{
return(fi.BaseFICalculateAreaExposed(part));
}
/*else
* {
* if (stockRadArea > 0)
* return aeroModule.ProjectedAreas.totalArea * dragCubeExposed / stockRadArea;
* else
* return aeroModule.ProjectedAreas.totalArea;
* }*/
}
double CalculateBodyArea(ModularFI.ModularFlightIntegrator fi, FlightIntegrator.PartThermalData ptd)
{
FARAeroPartModule module = null;
if (ptd.part.Modules.Contains("FARAeroPartModule"))
{
module = (FARAeroPartModule)ptd.part.Modules["FARAeroPartModule"];
}
if ((object)module != null)
{
double bodyArea = module.ProjectedAreaWorld(-fi.Vessel.upAxis) * ptd.bodyAreaMultiplier;
if (bodyArea > 0)
{
return(bodyArea);
}
else
{
return(fi.BaseFIBodyArea(ptd));
}
}
else
{
return(fi.BaseFIBodyArea(ptd));
}
}
private static void UpdateThermodynamicsPre(ModularFlightIntegrator fi)
{
for (int i = 0; i < fi.PartThermalDataCount; i++)
{
PartThermalData ptd = fi.partThermalDataList[i];
Part part = ptd.part;
if (!part.Modules.Contains <FARAeroPartModule>())
{
continue;
}
FARAeroPartModule aeroModule = part.Modules.GetModule <FARAeroPartModule>();
// make sure drag cube areas are correct based on voxelization
if (!part.DragCubes.None && aeroModule)
{
for (int j = 0; j < 6; j++)
{
part.DragCubes.AreaOccluded[FARAeroPartModule.ProjectedArea.FaceMap[j]] =
(float)aeroModule.ProjectedAreas[j];
}
}
part.radiativeArea = CalculateAreaRadiative(fi, part, aeroModule);
part.exposedArea =
part.machNumber > 0 ? CalculateAreaExposed(fi, part, aeroModule) : part.radiativeArea;
if (FARSettings.ExposedAreaLimited && part.exposedArea > part.radiativeArea)
{
part.exposedArea = part.radiativeArea; //sanity check just in case
}
}
}
private void FixedUpdate()
{
if (_vehicleAero == null)
{
return;
}
if (_vehicleAero.CalculationCompleted)
{
_vehicleAero.GetNewAeroData(out _currentAeroModules, out _unusedAeroModules, out _currentAeroSections, out _legacyWingModels);
if ((object)_flightGUI == null)
{
_flightGUI = _vessel.GetComponent <FerramAerospaceResearch.FARGUI.FARFlightGUI.FlightGUI>();
}
_flightGUI.UpdateAeroModules(_currentAeroModules, _legacyWingModels);
//Debug.Log("Updating " + _vessel.vesselName + " aero properties\n\rCross-Sectional Area: " + _vehicleAero.MaxCrossSectionArea + " Crit Mach: " + _vehicleAero.CriticalMach + "\n\rUnusedAeroCount: " + _unusedAeroModules.Count + " UsedAeroCount: " + _currentAeroModules.Count + " sectCount: " + _currentAeroSections.Count);
for (int i = 0; i < _unusedAeroModules.Count; i++)
{
FARAeroPartModule a = _unusedAeroModules[i];
a.SetShielded(true);
a.ForceLegacyAeroUpdates();
//Debug.Log(a.part.partInfo.title + " shielded, area: " + a.ProjectedAreas.totalArea);
}
for (int i = 0; i < _currentAeroModules.Count; i++)
{
FARAeroPartModule a = _currentAeroModules[i];
a.SetShielded(false);
a.ForceLegacyAeroUpdates();
//Debug.Log(a.part.partInfo.title + " unshielded, area: " + a.ProjectedAreas.totalArea);
}
_vesselIntakeRamDrag.UpdateAeroData(_currentAeroModules, _unusedAeroModules);
}
if (FlightGlobals.ready && _currentAeroSections != null && _vessel)
{
CalculateAndApplyVesselAeroProperties();
}
if (_currentGeoModules.Count > geoModulesReady)
{
CheckGeoModulesReady();
}
if (_updateRateLimiter < FARSettingsScenarioModule.VoxelSettings.minPhysTicksPerUpdate)
{
_updateRateLimiter++;
}
else if (_updateQueued)
{
VesselUpdate(_recalcGeoModules);
}
}
double CalculateAreaRadiative(ModularFI.ModularFlightIntegrator fi, Part part, FARAeroPartModule aeroModule)
{
//double dragCubeExposed = fi.BaseFICalculateAreaExposed(part);
if ((object)aeroModule == null)
return fi.BaseFICalculateAreaRadiative(part);
else
{
return aeroModule.ProjectedAreas.totalArea;
}
}
private void CalculateAndApplyVesselAeroProperties()
{
float atmDensity = (float)vessel.atmDensity;
if (atmDensity <= 0)
{
MachNumber = 0;
ReynoldsNumber = 0;
return;
}
MachNumber = vessel.mach;
ReynoldsNumber = FARAeroUtil.CalculateReynoldsNumber(vessel.atmDensity,
Length,
vessel.srfSpeed,
MachNumber,
FlightGlobals.getExternalTemperature((float)vessel
.altitude,
vessel.mainBody),
vessel.mainBody.atmosphereAdiabaticIndex);
float skinFrictionDragCoefficient = (float)FARAeroUtil.SkinFrictionDrag(ReynoldsNumber, MachNumber);
float pseudoKnudsenNumber = (float)(MachNumber / (ReynoldsNumber + MachNumber));
Vector3 frameVel = Krakensbane.GetFrameVelocityV3f();
//start from the top and come down to improve performance if it needs to remove anything
for (int i = _currentAeroModules.Count - 1; i >= 0; i--)
{
FARAeroPartModule m = _currentAeroModules[i];
if (m != null && m.part != null && m.part.partTransform != null)
{
m.UpdateVelocityAndAngVelocity(frameVel);
}
else
{
_currentAeroModules.RemoveAt(i);
}
}
foreach (FARAeroSection aeroSection in _currentAeroSections)
{
aeroSection.FlightCalculateAeroForces((float)MachNumber,
(float)(ReynoldsNumber / Length),
pseudoKnudsenNumber,
skinFrictionDragCoefficient);
}
_vesselIntakeRamDrag.ApplyIntakeRamDrag((float)MachNumber, vessel.srf_velocity.normalized);
foreach (FARAeroPartModule m in _currentAeroModules)
{
m.ApplyForces();
}
}
private void CalculateAndApplyVesselAeroProperties()
{
float atmDensity = (float)_vessel.atmDensity;
if (atmDensity <= 0)
{
machNumber = 0;
reynoldsNumber = 0;
return;
}
machNumber = _vessel.mach;
reynoldsNumber = FARAeroUtil.CalculateReynoldsNumber(_vessel.atmDensity, Length, _vessel.srfSpeed, machNumber, FlightGlobals.getExternalTemperature((float)_vessel.altitude, _vessel.mainBody), _vessel.mainBody.atmosphereAdiabaticIndex);
float skinFrictionDragCoefficient = (float)FARAeroUtil.SkinFrictionDrag(reynoldsNumber, machNumber);
Vector3 frameVel = Krakensbane.GetFrameVelocityV3f();
if (_updateQueued) //only happens if we have an voxelization scheduled, then we need to check for null
{
for (int i = _currentAeroModules.Count - 1; i >= 0; i--) //start from the top and come down to improve performance if it needs to remove anything
{
FARAeroPartModule m = _currentAeroModules[i];
if (m != null)
{
m.UpdateVelocityAndAngVelocity(frameVel);
}
else
{
_currentAeroModules.RemoveAt(i);
i++;
}
}
}
else //otherwise, we don't need to do Unity's expensive "is this part dead" null-check
{
for (int i = _currentAeroModules.Count - 1; i >= 0; i--) //start from the top and come down to improve performance if it needs to remove anything
{
FARAeroPartModule m = _currentAeroModules[i];
m.UpdateVelocityAndAngVelocity(frameVel);
}
}
for (int i = 0; i < _currentAeroSections.Count; i++)
{
_currentAeroSections[i].FlightCalculateAeroForces(atmDensity, (float)machNumber, (float)(reynoldsNumber / Length), skinFrictionDragCoefficient);
}
_vesselIntakeRamDrag.ApplyIntakeRamDrag((float)machNumber, _vessel.srf_velocity.normalized, (float)_vessel.dynamicPressurekPa);
for (int i = 0; i < _currentAeroModules.Count; i++)
{
FARAeroPartModule m = _currentAeroModules[i];
m.ApplyForces();
}
}
double CalculateAreaExposed(ModularFI.ModularFlightIntegrator fi, Part part)
{
FARAeroPartModule module = null;
if (part.Modules.Contains <FARAeroPartModule>())
{
module = part.Modules.GetModule <FARAeroPartModule>();
}
return(CalculateAreaExposed(fi, part, module));
}
private static double CalculateAreaRadiative(ModularFlightIntegrator fi, Part part)
{
FARAeroPartModule module = null;
if (part.Modules.Contains <FARAeroPartModule>())
{
module = part.Modules.GetModule <FARAeroPartModule>();
}
return(CalculateAreaRadiative(fi, part, module));
}
double CalculateAreaExposed(ModularFI.ModularFlightIntegrator fi, Part part)
{
FARAeroPartModule module = null;
if (part.Modules.Contains("FARAeroPartModule"))
{
module = (FARAeroPartModule)part.Modules["FARAeroPartModule"];
}
return(CalculateAreaExposed(fi, part, module));
}
private static double CalculateBodyArea(ModularFlightIntegrator fi, PartThermalData ptd)
{
FARAeroPartModule module = ptd.part.Modules.GetModule <FARAeroPartModule>();
if (module is null)
{
return(fi.BaseFIBodyArea(ptd));
}
double bodyArea = module.ProjectedAreaWorld(-fi.Vessel.upAxis) * ptd.bodyAreaMultiplier;
return(bodyArea > 0 ? bodyArea : fi.BaseFIBodyArea(ptd));
}
private static double CalculateSunArea(ModularFlightIntegrator fi, PartThermalData ptd)
{
FARAeroPartModule module = ptd.part.Modules.GetModule <FARAeroPartModule>();
if (module is null)
{
return(fi.BaseFIGetSunArea(ptd));
}
double sunArea = module.ProjectedAreaWorld(fi.sunVector) * ptd.sunAreaMultiplier;
return(sunArea > 0 ? sunArea : fi.BaseFIGetSunArea(ptd));
}
double CalculateAreaExposed(ModularFI.ModularFlightIntegrator fi, Part part, FARAeroPartModule aeroModule)
{
double dragCubeExposed = fi.BaseFICalculateAreaExposed(part);
if (aeroModule == null)
return dragCubeExposed;
else
{
double cubeRadiative = fi.BaseFICalculateAreaRadiative(part);
if (cubeRadiative > 0)
return aeroModule.ProjectedAreas.totalArea * dragCubeExposed / cubeRadiative;
else
return aeroModule.ProjectedAreas.totalArea;
}
}
double CalculateAreaExposed(ModularFI.ModularFlightIntegrator fi, Part part, FARAeroPartModule aeroModule)
{
if ((object)aeroModule == null)
return fi.BaseFICalculateAreaExposed(part);
else
return aeroModule.ProjectedAreaLocal(-part.dragVectorDirLocal);
/*else
{
if (stockRadArea > 0)
return aeroModule.ProjectedAreas.totalArea * dragCubeExposed / stockRadArea;
else
return aeroModule.ProjectedAreas.totalArea;
}*/
}
private static double CalculateAreaRadiative(
ModularFlightIntegrator fi,
Part part,
FARAeroPartModule aeroModule
)
{
if (aeroModule is null)
{
return(fi.BaseFICalculateAreaRadiative(part));
}
double radArea = aeroModule.ProjectedAreas.totalArea;
return(radArea > 0 ? radArea : fi.BaseFICalculateAreaRadiative(part));
}
private void FixedUpdate()
{
if (_vehicleAero == null)
{
return;
}
if (_vehicleAero.CalculationCompleted)
{
_vehicleAero.GetNewAeroData(out _currentAeroModules, out _unusedAeroModules, out _currentAeroSections, out _legacyWingModels);
_vessel.SendMessage("UpdateAeroModules", _currentAeroModules);
for (int i = 0; i < _unusedAeroModules.Count; i++)
{
FARAeroPartModule a = _unusedAeroModules[i];
a.SetShielded(true);
//Debug.Log(a.part.partInfo.title + " shielded");
}
for (int i = 0; i < _currentAeroModules.Count; i++)
{
FARAeroPartModule a = _currentAeroModules[i];
a.SetShielded(false);
//Debug.Log(a.part.partInfo.title + " unshielded");
}
_vesselIntakeRamDrag.UpdateAeroData(_currentAeroModules, _unusedAeroModules);
}
if (FlightGlobals.ready && _currentAeroSections != null)
{
CalculateAndApplyVesselAeroProperties();
}
if (_currentGeoModules.Count > geoModulesReady)
{
CheckGeoModulesReady();
}
if (_updateRateLimiter < FARSettingsScenarioModule.VoxelSettings.minPhysTicksPerUpdate)
{
_updateRateLimiter++;
}
else if (_updateQueued)
{
VesselUpdate(_recalcGeoModules);
}
}
private void CalculateAndApplyVesselAeroProperties()
{
float atmDensity = (float)_vessel.atmDensity;
if (atmDensity <= 0)
{
machNumber = 0;
reynoldsNumber = 0;
return;
}
machNumber = _vessel.mach;
reynoldsNumber = FARAeroUtil.CalculateReynoldsNumber(_vessel.atmDensity, Length, _vessel.srfSpeed, machNumber, FlightGlobals.getExternalTemperature((float)_vessel.altitude, _vessel.mainBody), _vessel.mainBody.atmosphereAdiabaticIndex);
float skinFrictionDragCoefficient = (float)FARAeroUtil.SkinFrictionDrag(reynoldsNumber, machNumber);
Vector3 frameVel = Krakensbane.GetFrameVelocityV3f();
for (int i = 0; i < _currentAeroModules.Count; i++)
{
FARAeroPartModule m = _currentAeroModules[i];
if (m != null)
{
m.UpdateVelocityAndAngVelocity(frameVel);
}
else
{
_currentAeroModules.RemoveAt(i);
i--;
}
}
for (int i = 0; i < _currentAeroSections.Count; i++)
{
_currentAeroSections[i].FlightCalculateAeroForces(atmDensity, (float)machNumber, (float)(reynoldsNumber / Length), skinFrictionDragCoefficient);
}
_vesselIntakeRamDrag.ApplyIntakeRamDrag((float)machNumber, _vessel.srf_velocity.normalized, (float)_vessel.dynamicPressurekPa);
for (int i = 0; i < _currentAeroModules.Count; i++)
{
FARAeroPartModule m = _currentAeroModules[i];
if ((object)m != null)
{
m.ApplyForces();
}
}
}
private static void UpdateThermodynamicsPre(ModularFlightIntegrator fi)
{
bool voxelizationCompleted =
(fi.Vessel.vesselModules.Find(module => module is FARVesselAero) as FARVesselAero)?
.HasEverValidVoxelization() ?? false;
for (int i = 0; i < fi.PartThermalDataCount; i++)
{
PartThermalData ptd = fi.partThermalDataList[i];
Part part = ptd.part;
FARAeroPartModule aeroModule = part.Modules.GetModule <FARAeroPartModule>();
if (aeroModule is null)
{
continue;
}
// make sure drag cube areas are correct based on voxelization
if (voxelizationCompleted)
{
if (!part.DragCubes.None && aeroModule)
{
for (int j = 0; j < 6; j++)
{
part.DragCubes.AreaOccluded[FARAeroPartModule.ProjectedArea.FaceMap[j]] =
(float)aeroModule.ProjectedAreas[j];
}
}
part.radiativeArea = CalculateAreaRadiative(fi, part, aeroModule);
part.exposedArea = part.machNumber > 0
? CalculateAreaExposed(fi, part, aeroModule)
: part.radiativeArea;
}
else
{
part.radiativeArea = fi.BaseFICalculateAreaRadiative(part);
part.exposedArea = fi.BaseFICalculateAreaExposed(part);
}
if (FARSettings.ExposedAreaLimited && part.exposedArea > part.radiativeArea)
{
part.exposedArea = part.radiativeArea; //sanity check just in case
}
}
}
void UpdateThermodynamicsPre(ModularFI.ModularFlightIntegrator fi)
{
for (int i = 0; i < fi.PartThermalDataCount; i++)
{
Part part = fi.partThermalDataList[i].part;
if (!part.Modules.Contains("FARAeroPartModule"))
{
continue;
}
PartModule module = part.Modules["FARAeroPartModule"];
FARAeroPartModule aeroModule = (FARAeroPartModule)module;
part.radiativeArea = CalculateAreaRadiative(fi, part, aeroModule);
part.exposedArea = part.machNumber > 0 ? CalculateAreaExposed(fi, part, aeroModule) : 0;
}
//Debug.Log("MFI: " + fi.CoM + " " + Planetarium.GetUniversalTime());
}
double CalculateAreaExposed(ModularFI.ModularFlightIntegrator fi, Part part, FARAeroPartModule aeroModule)
{
double dragCubeExposed = fi.BaseFICalculateAreaExposed(part);
if (aeroModule == null)
{
return(dragCubeExposed);
}
else
{
double cubeRadiative = fi.BaseFICalculateAreaRadiative(part);
if (cubeRadiative > 0)
{
return(aeroModule.ProjectedAreas.totalArea * dragCubeExposed / cubeRadiative);
}
else
{
return(aeroModule.ProjectedAreas.totalArea);
}
}
}
private void ApplyIntakeDrag(float currentRamDrag, Vector3 vesselVelNorm, float dynPres)
{
for (int i = _intakeTransforms.Count - 1; i >= 0; i--)
{
ModuleResourceIntake intake = _intakeModules[i];
if (!intake.intakeEnabled)
{
continue;
}
Transform transform = _intakeTransforms[i];
if (transform == null)
{
_intakeModules.RemoveAt(i);
_intakeTransforms.RemoveAt(i);
_aeroModulesWithIntakes.RemoveAt(i);
//++i;
continue;
}
float cosAoA = Vector3.Dot(_intakeTransforms[i].forward, vesselVelNorm);
if (cosAoA < 0)
{
cosAoA = 0;
}
if (cosAoA <= 0)
{
continue;
}
FARAeroPartModule aeroModule = _aeroModulesWithIntakes[i];
Vector3 force = -aeroModule.partLocalVelNorm * cosAoA * currentRamDrag * (float)intake.area * 100f;
//if(float.IsNaN(force.sqrMagnitude))
// force = Vector3.zero;
aeroModule.AddLocalForce(force, Vector3.zero);
}
}
private void ApplyIntakeDrag(float currentRamDrag, Vector3 vesselVelNorm, float dynPres)
{
for (int i = 0; i < _intakeTransforms.Count; i++)
{
ModuleResourceIntake intake = _intakeModules[i];
if (!intake.intakeEnabled)
{
continue;
}
Transform transform = _intakeTransforms[i];
if (transform == null)
{
_intakeModules.RemoveAt(i);
_intakeTransforms.RemoveAt(i);
_aeroModulesWithIntakes.RemoveAt(i);
--i;
continue;
}
float cosAoA = Vector3.Dot(_intakeTransforms[i].forward, vesselVelNorm);
if (cosAoA < 0)
{
cosAoA = 0;
}
if (cosAoA <= intake.aoaThreshold)
{
continue;
}
FARAeroPartModule aeroModule = _aeroModulesWithIntakes[i];
aeroModule.AddLocalForce(-aeroModule.partLocalVelNorm * dynPres * cosAoA * currentRamDrag * intake.area * 100, Vector3.zero);
}
}
private static double CalculateAreaExposed(ModularFlightIntegrator fi, Part part)
{
FARAeroPartModule module = part.Modules.GetModule <FARAeroPartModule>();
return(CalculateAreaExposed(fi, part, module));
}
double CalculateAreaRadiative(ModularFI.ModularFlightIntegrator fi, Part part, FARAeroPartModule aeroModule)
{
//double dragCubeExposed = fi.BaseFICalculateAreaExposed(part);
if ((object)aeroModule == null)
{
return(fi.BaseFICalculateAreaRadiative(part));
}
else
{
return(aeroModule.ProjectedAreas.totalArea);
}
}
public void PredictionCalculateAeroForces(float atmDensity, float machNumber, float reynoldsPerUnitLength, float pseudoKnudsenNumber, float skinFrictionDrag, Vector3 vel, ferram4.FARCenterQuery center)
{
if (partData.Count == 0)
{
return;
}
PartData data = partData[0];
FARAeroPartModule aeroModule = null;
for (int i = 0; i < partData.Count; i++)
{
data = partData[i];
aeroModule = data.aeroModule;
if (aeroModule.part == null || aeroModule.part.partTransform == null)
{
continue;
}
break;
}
if (aeroModule.part == null || aeroModule.part.transform == null)
{
return;
}
double skinFrictionForce = skinFrictionDrag * xForceSkinFriction.Evaluate(machNumber); //this will be the same for each part, so why recalc it multiple times?
double xForceAoA0 = xForcePressureAoA0.Evaluate(machNumber);
double xForceAoA180 = xForcePressureAoA180.Evaluate(machNumber);
Vector3 xRefVector = data.xRefVectorPartSpace;
Vector3 nRefVector = data.nRefVectorPartSpace;
Vector3 velLocal = aeroModule.part.partTransform.worldToLocalMatrix.MultiplyVector(vel);
//Vector3 angVelLocal = aeroModule.partLocalAngVel;
//velLocal += Vector3.Cross(angVelLocal, data.centroidPartSpace); //some transform issue here, needs investigation
Vector3 velLocalNorm = velLocal.normalized;
Vector3 localNormalForceVec = Vector3.ProjectOnPlane(-velLocalNorm, xRefVector).normalized;
double cosAoA = Vector3.Dot(xRefVector, velLocalNorm);
double cosSqrAoA = cosAoA * cosAoA;
double sinSqrAoA = Math.Max(1 - cosSqrAoA, 0);
double sinAoA = Math.Sqrt(sinSqrAoA);
double sin2AoA = 2 * sinAoA * Math.Abs(cosAoA);
double cosHalfAoA = Math.Sqrt(0.5 + 0.5 * Math.Abs(cosAoA));
double nForce = 0;
nForce = cosHalfAoA * sin2AoA * potentialFlowNormalForce * Math.Sign(cosAoA); //potential flow normal force
if (nForce < 0) //potential flow is not significant over the rear face of things
{
nForce = 0;
}
//if (machNumber > 3)
// nForce *= 2d - machNumber * 0.3333333333333333d;
float normalForceFactor = Math.Abs(Vector3.Dot(localNormalForceVec, nRefVector));
normalForceFactor *= normalForceFactor;
normalForceFactor = invFlatnessRatio * (1 - normalForceFactor) + flatnessRatio * normalForceFactor; //accounts for changes in relative flatness of shape
float crossFlowMach, crossFlowReynolds;
crossFlowMach = machNumber * (float)sinAoA;
crossFlowReynolds = reynoldsPerUnitLength * diameter * normalForceFactor * (float)sinAoA;
nForce += viscCrossflowDrag * sinSqrAoA * CalculateCrossFlowDrag(crossFlowMach, crossFlowReynolds); //viscous crossflow normal force
nForce *= normalForceFactor;
double xForce = -skinFrictionForce *Math.Sign(cosAoA) * cosSqrAoA;
double localVelForce = xForce * pseudoKnudsenNumber;
xForce -= localVelForce;
localVelForce = Math.Abs(localVelForce);
float moment = (float)(cosAoA * sinAoA);
if (cosAoA > 0)
{
xForce += cosSqrAoA * xForceAoA0;
float momentFactor;
if (machNumber > 6)
{
momentFactor = hypersonicMomentForward;
}
else if (machNumber < 0.6)
{
momentFactor = 0.6f * hypersonicMomentBackward;
}
else
{
float tmp = (-0.185185185f * machNumber + 1.11111111111f);
momentFactor = tmp * hypersonicMomentBackward * 0.6f + (1 - tmp) * hypersonicMomentForward;
}
//if (machNumber < 1.5)
// momentFactor += hypersonicMomentBackward * (0.5f - machNumber * 0.33333333333333333333333333333333f) * 0.2f;
moment *= momentFactor;
}
else
{
xForce += cosSqrAoA * xForceAoA180;
float momentFactor; //negative to deal with the ref vector facing the opposite direction, causing the moment vector to point in the opposite direction
if (machNumber > 6)
{
momentFactor = hypersonicMomentBackward;
}
else if (machNumber < 0.6)
{
momentFactor = 0.6f * hypersonicMomentForward;
}
else
{
float tmp = (-0.185185185f * machNumber + 1.11111111111f);
momentFactor = tmp * hypersonicMomentForward * 0.6f + (1 - tmp) * hypersonicMomentBackward;
}
//if (machNumber < 1.5)
// momentFactor += hypersonicMomentForward * (0.5f - machNumber * 0.33333333333333333333333333333333f) * 0.2f;
moment *= momentFactor;
}
moment /= normalForceFactor;
Vector3 forceVector = (float)xForce * xRefVector + (float)nForce * localNormalForceVec;
forceVector -= (float)localVelForce * velLocalNorm;
Vector3 torqueVector = Vector3.Cross(xRefVector, localNormalForceVec) * moment;
Matrix4x4 localToWorld = aeroModule.part.partTransform.localToWorldMatrix;
float dynPresAndScaling = 0.0005f * atmDensity * velLocal.sqrMagnitude; //dyn pres and N -> kN conversion
forceVector *= dynPresAndScaling;
torqueVector *= dynPresAndScaling;
forceVector = localToWorld.MultiplyVector(forceVector);
torqueVector = localToWorld.MultiplyVector(torqueVector);
Vector3 centroid = Vector3.zero;
for (int i = 0; i < partData.Count; i++)
{
PartData data2 = partData[i];
FARAeroPartModule module = data2.aeroModule;
if ((object)module == null)
{
continue;
}
if (module.part == null || module.part.partTransform == null)
{
continue;
}
centroid = module.part.partTransform.localToWorldMatrix.MultiplyPoint3x4(data2.centroidPartSpace);
center.AddForce(centroid, forceVector * data2.dragFactor);
}
center.AddTorque(torqueVector);
}
public void FlightCalculateAeroForces(float atmDensity, float machNumber, float reynoldsPerUnitLength, float pseudoKnudsenNumber, float skinFrictionDrag)
{
double skinFrictionForce = skinFrictionDrag * xForceSkinFriction.Evaluate(machNumber); //this will be the same for each part, so why recalc it multiple times?
double xForceAoA0 = xForcePressureAoA0.Evaluate(machNumber);
double xForceAoA180 = xForcePressureAoA180.Evaluate(machNumber);
for (int i = 0; i < partData.Count; i++)
{
PartData data = partData[i];
FARAeroPartModule aeroModule = data.aeroModule;
if ((object)aeroModule == null)
{
continue;
}
Vector3 xRefVector = data.xRefVectorPartSpace;
Vector3 nRefVector = data.nRefVectorPartSpace;
Vector3 velLocal = aeroModule.partLocalVel;
Vector3 angVelLocal = aeroModule.partLocalAngVel;
velLocal += Vector3.Cross(data.centroidPartSpace, angVelLocal); //some transform issue here, needs investigation
Vector3 velLocalNorm = velLocal.normalized;
Vector3 localNormalForceVec = Vector3.ProjectOnPlane(-velLocalNorm, xRefVector).normalized;
double cosAoA = Vector3.Dot(xRefVector, velLocalNorm);
double cosSqrAoA = cosAoA * cosAoA;
double sinSqrAoA = Math.Max(1 - cosSqrAoA, 0);
double sinAoA = Math.Sqrt(sinSqrAoA);
double sin2AoA = 2 * sinAoA * Math.Abs(cosAoA);
double cosHalfAoA = Math.Sqrt(0.5 + 0.5 * Math.Abs(cosAoA));
double nForce = 0;
nForce = potentialFlowNormalForce * Math.Sign(cosAoA) * cosHalfAoA * sin2AoA; //potential flow normal force
if (nForce < 0) //potential flow is not significant over the rear face of things
{
nForce = 0;
}
//if (machNumber > 3)
// nForce *= 2d - machNumber * 0.3333333333333333d;
float normalForceFactor = Math.Abs(Vector3.Dot(localNormalForceVec, nRefVector));
normalForceFactor *= normalForceFactor;
normalForceFactor = invFlatnessRatio * (1 - normalForceFactor) + flatnessRatio * normalForceFactor; //accounts for changes in relative flatness of shape
float crossFlowMach, crossFlowReynolds;
crossFlowMach = machNumber * (float)sinAoA;
crossFlowReynolds = reynoldsPerUnitLength * diameter * (float)sinAoA / normalForceFactor;
nForce += viscCrossflowDrag * sinSqrAoA * CalculateCrossFlowDrag(crossFlowMach, crossFlowReynolds); //viscous crossflow normal force
nForce *= normalForceFactor;
double xForce = -skinFrictionForce *Math.Sign(cosAoA) * cosSqrAoA;
double localVelForce = xForce * pseudoKnudsenNumber;
xForce -= localVelForce;
localVelForce = Math.Abs(localVelForce);
float moment = (float)(cosAoA * sinAoA);
float dampingMoment = 4f * moment;
if (cosAoA > 0)
{
xForce += cosSqrAoA * xForceAoA0;
float momentFactor;
if (machNumber > 6)
{
momentFactor = hypersonicMomentForward;
}
else if (machNumber < 0.6)
{
momentFactor = 0.6f * hypersonicMomentBackward;
}
else
{
float tmp = (-0.185185185f * machNumber + 1.11111111111f);
momentFactor = tmp * hypersonicMomentBackward * 0.6f + (1 - tmp) * hypersonicMomentForward;
}
//if (machNumber < 1.5)
// momentFactor += hypersonicMomentBackward * (0.5f - machNumber * 0.33333333333333333333333333333333f) * 0.2f;
moment *= momentFactor;
dampingMoment *= momentFactor;
}
else
{
xForce += cosSqrAoA * xForceAoA180;
float momentFactor; //negative to deal with the ref vector facing the opposite direction, causing the moment vector to point in the opposite direction
if (machNumber > 6)
{
momentFactor = hypersonicMomentBackward;
}
else if (machNumber < 0.6)
{
momentFactor = 0.6f * hypersonicMomentForward;
}
else
{
float tmp = (-0.185185185f * machNumber + 1.11111111111f);
momentFactor = tmp * hypersonicMomentForward * 0.6f + (1 - tmp) * hypersonicMomentBackward;
}
//if (machNumber < 1.5)
// momentFactor += hypersonicMomentForward * (0.5f - machNumber * 0.33333333333333333333333333333333f) * 0.2f;
moment *= momentFactor;
dampingMoment *= momentFactor;
}
moment /= normalForceFactor;
dampingMoment = Math.Abs(dampingMoment) * 0.1f;
//dampingMoment += (float)Math.Abs(skinFrictionForce) * 0.1f;
float rollDampingMoment = (float)(skinFrictionForce * 0.5 * diameter); //skin friction force times avg moment arm for vehicle
rollDampingMoment *= (0.75f + flatnessRatio * 0.25f); //this is just an approximation for now
Vector3 forceVector = (float)xForce * xRefVector + (float)nForce * localNormalForceVec;
forceVector -= (float)localVelForce * velLocalNorm;
Vector3 torqueVector = Vector3.Cross(xRefVector, localNormalForceVec) * moment;
Vector3 axialAngLocalVel = Vector3.Dot(xRefVector, angVelLocal) * xRefVector;
Vector3 nonAxialAngLocalVel = angVelLocal - axialAngLocalVel;
if (velLocal.sqrMagnitude > 0.001f)
{
torqueVector -= (dampingMoment * nonAxialAngLocalVel) + (rollDampingMoment * axialAngLocalVel * axialAngLocalVel.magnitude) / velLocal.sqrMagnitude;
}
else
{
torqueVector -= (dampingMoment * nonAxialAngLocalVel) + (rollDampingMoment * axialAngLocalVel * axialAngLocalVel.magnitude) / 0.001f;
}
//float dynPresAndScaling = 0.0005f * atmDensity * velLocal.sqrMagnitude * data.dragFactor; //dyn pres and N -> kN conversion
//forceVector *= dynPresAndScaling;
//torqueVector *= dynPresAndScaling;
forceVector *= data.dragFactor;
torqueVector *= data.dragFactor;
aeroModule.AddLocalForceAndTorque(forceVector, torqueVector, data.centroidPartSpace);
}
}
public void UpdateAeroData(List <FARAeroPartModule> allUsedAeroModules, List <FARAeroPartModule> allUnusedAeroModules)
{
_aeroModulesWithIntakes.Clear();
_intakeModules.Clear();
_intakeTransforms.Clear();
_airBreathingEngines.Clear();
HashSet <string> intakeResourceNames = new HashSet <string>();
for (int i = 0; i < allUsedAeroModules.Count; i++) //get all exposed intakes
{
FARAeroPartModule aeroModule = allUsedAeroModules[i];
if (aeroModule == null)
{
continue;
}
Part p = aeroModule.part;
for (int j = 0; j < p.Modules.Count; j++)
{
PartModule m = p.Modules[j];
if (m is ModuleResourceIntake)
{
ModuleResourceIntake intake = (ModuleResourceIntake)m;
if (intake.node != null && intake.node.attachedPart != null)
{
continue;
}
_aeroModulesWithIntakes.Add(aeroModule);
_intakeModules.Add(intake);
_intakeTransforms.Add(p.FindModelTransform(intake.intakeTransformName));
if (!intakeResourceNames.Contains(intake.resourceName))
{
intakeResourceNames.Add(intake.resourceName);
}
}
}
}
for (int i = 0; i < allUsedAeroModules.Count; i++) //get all exposed engines
{
FARAeroPartModule aeroModule = allUsedAeroModules[i];
if (aeroModule == null)
{
continue;
}
Part p = aeroModule.part;
for (int j = 0; j < p.Modules.Count; j++)
{
PartModule m = p.Modules[j];
if (m is ModuleEngines)
{
ModuleEngines e = (ModuleEngines)m;
if (FARAeroUtil.AJELoaded)
{
if (m.ClassID == AJE_JET_CLASS_ID || m.ClassID == AJE_PROP_CLASS_ID)
{
_airBreathingEngines.Add(e);
continue;
}
}
for (int k = 0; k < e.propellants.Count; k++)
{
Propellant prop = e.propellants[k];
if (intakeResourceNames.Contains(prop.name))
{
_airBreathingEngines.Add(e);
break;
}
}
}
}
}
}
private static double CalculateAreaExposed(ModularFlightIntegrator fi, Part part, FARAeroPartModule aeroModule)
{
if (aeroModule is null)
{
return(fi.BaseFICalculateAreaExposed(part));
}
// Apparently stock exposed area is actually weighted by some function of mach number...
// otherwise heating is much lower
double exposedArea = FARSettings.ExposedAreaUsesKSPHack
? part.DragCubes.ExposedArea
: aeroModule.ProjectedAreaLocal(-part.dragVectorDirLocal);
return(exposedArea > 0 ? exposedArea : fi.BaseFICalculateAreaExposed(part));
}
private void CalculateAeroForces(
float machNumber,
float reynoldsPerUnitLength,
float pseudoKnudsenNumber,
float skinFrictionDrag,
IForceContext forceContext
)
{
//this will be the same for each part, so why recalc it multiple times?
double skinFrictionForce = skinFrictionDrag * xForceSkinFriction.Evaluate(machNumber);
double xForceAoA0 = xForcePressureAoA0.Evaluate(machNumber);
double xForceAoA180 = xForcePressureAoA180.Evaluate(machNumber);
foreach (PartData data in partData)
{
FARAeroPartModule aeroModule = data.aeroModule;
if (aeroModule is null)
{
continue;
}
Vector3 xRefVector = data.xRefVectorPartSpace;
Vector3 nRefVector = data.nRefVectorPartSpace;
Vector3 velLocal = forceContext.LocalVelocity(data);
// Rejects both negligible speed and invalid simulation cases
if (velLocal.sqrMagnitude.NearlyEqual(0.0f))
{
continue;
}
Vector3 angVelLocal = aeroModule.partLocalAngVel;
//some transform issue here, needs investigation
velLocal += Vector3.Cross(data.centroidPartSpace, angVelLocal);
Vector3 velLocalNorm = velLocal.normalized;
Vector3 localNormalForceVec = Vector3.ProjectOnPlane(-velLocalNorm, xRefVector).normalized;
double cosAoA = Vector3.Dot(xRefVector, velLocalNorm);
double cosSqrAoA = cosAoA * cosAoA;
double sinSqrAoA = Math.Max(1 - cosSqrAoA, 0);
double sinAoA = Math.Sqrt(sinSqrAoA);
double sin2AoA = 2 * sinAoA * Math.Abs(cosAoA);
double cosHalfAoA = Math.Sqrt(0.5 + 0.5 * Math.Abs(cosAoA));
//potential flow normal force
double nForce = potentialFlowNormalForce * Math.Sign(cosAoA) * cosHalfAoA * sin2AoA;
//potential flow is not significant over the rear face of things
if (nForce < 0)
{
nForce = 0;
}
float normalForceFactor = Math.Abs(Vector3.Dot(localNormalForceVec, nRefVector));
normalForceFactor *= normalForceFactor;
//accounts for changes in relative flatness of shape
normalForceFactor = invFlatnessRatio * (1 - normalForceFactor) + flatnessRatio * normalForceFactor;
float crossFlowMach = machNumber * (float)sinAoA;
float crossFlowReynolds = reynoldsPerUnitLength * diameter * (float)sinAoA / normalForceFactor;
//viscous crossflow normal force
nForce += viscCrossflowDrag * sinSqrAoA * CalculateCrossFlowDrag(crossFlowMach, crossFlowReynolds);
nForce *= normalForceFactor;
double xForce = -skinFrictionForce *Math.Sign(cosAoA) * cosSqrAoA;
double localVelForce = xForce * pseudoKnudsenNumber;
xForce -= localVelForce;
localVelForce = Math.Abs(localVelForce);
float moment = (float)(cosAoA * sinAoA);
float dampingMoment = 4f * moment;
if (cosAoA > 0)
{
xForce += cosSqrAoA * xForceAoA0;
float momentFactor;
if (machNumber > 6)
{
momentFactor = hypersonicMomentForward;
}
else if (machNumber < 0.6)
{
momentFactor = 0.6f * hypersonicMomentBackward;
}
else
{
float tmp = -0.185185185f * machNumber + 1.11111111111f;
momentFactor = tmp * hypersonicMomentBackward * 0.6f + (1 - tmp) * hypersonicMomentForward;
}
moment *= momentFactor;
dampingMoment *= momentFactor;
}
else
{
xForce += cosSqrAoA * xForceAoA180;
//negative to deal with the ref vector facing the opposite direction, causing the moment vector to point in the opposite direction
float momentFactor;
if (machNumber > 6)
{
momentFactor = hypersonicMomentBackward;
}
else if (machNumber < 0.6)
{
momentFactor = 0.6f * hypersonicMomentForward;
}
else
{
float tmp = -0.185185185f * machNumber + 1.11111111111f;
momentFactor = tmp * hypersonicMomentForward * 0.6f + (1 - tmp) * hypersonicMomentBackward;
}
moment *= momentFactor;
dampingMoment *= momentFactor;
}
moment /= normalForceFactor;
dampingMoment = Math.Abs(dampingMoment) * 0.1f;
//skin friction force times avg moment arm for vehicle
float rollDampingMoment = (float)(skinFrictionForce * 0.5 * diameter);
//this is just an approximation for now
rollDampingMoment *= 0.75f + flatnessRatio * 0.25f;
Vector3 forceVector = (float)xForce * xRefVector + (float)nForce * localNormalForceVec;
forceVector -= (float)localVelForce * velLocalNorm;
Vector3 torqueVector = Vector3.Cross(xRefVector, localNormalForceVec) * moment;
Vector3 axialAngLocalVel = Vector3.Dot(xRefVector, angVelLocal) * xRefVector;
Vector3 nonAxialAngLocalVel = angVelLocal - axialAngLocalVel;
if (velLocal.sqrMagnitude > 0.001f)
{
torqueVector -= dampingMoment * nonAxialAngLocalVel +
rollDampingMoment *
axialAngLocalVel *
axialAngLocalVel.magnitude /
velLocal.sqrMagnitude;
}
else
{
torqueVector -= dampingMoment * nonAxialAngLocalVel +
rollDampingMoment * axialAngLocalVel * axialAngLocalVel.magnitude / 0.001f;
}
forceVector *= data.dragFactor;
torqueVector *= data.dragFactor;
forceContext.ApplyForce(data, velLocal, forceVector, torqueVector);
}
}
private static double CalculateAreaExposed(ModularFlightIntegrator fi, Part part, FARAeroPartModule aeroModule)
{
if (aeroModule is null)
{
return(fi.BaseFICalculateAreaExposed(part));
}
double exposedArea = aeroModule.ProjectedAreaLocal(-part.dragVectorDirLocal);
return(exposedArea > 0 ? exposedArea : fi.BaseFICalculateAreaExposed(part));
}
public void UpdateAeroData(List <FARAeroPartModule> allUsedAeroModules, List <FARAeroPartModule> allUnusedAeroModules)
{
_aeroModulesWithIntakes.Clear();
_intakeModules.Clear();
_intakeTransforms.Clear();
_airBreathingEngines.Clear();
for (int i = 0; i < allUsedAeroModules.Count; i++) //get all exposed intakes and engines
{
FARAeroPartModule aeroModule = allUsedAeroModules[i];
if (aeroModule == null)
{
continue;
}
Part p = aeroModule.part;
if (p.Modules.Contains("ModuleResourceIntake"))
{
ModuleResourceIntake intake = (ModuleResourceIntake)p.Modules["ModuleResourceIntake"];
_aeroModulesWithIntakes.Add(aeroModule);
_intakeModules.Add(intake);
_intakeTransforms.Add(p.FindModelTransform(intake.intakeTransformName));
}
if (p.Modules.Contains("ModuleEngines"))
{
ModuleEngines engines = (ModuleEngines)p.Modules["ModuleEngines"];
for (int j = 0; j < engines.propellants.Count; j++)
{
Propellant prop = engines.propellants[j];
if (prop.name == "IntakeAir")
{
_airBreathingEngines.Add(engines);
break;
}
}
}
if (p.Modules.Contains("ModuleEnginesFX"))
{
ModuleEnginesFX engines = (ModuleEnginesFX)p.Modules["ModuleEnginesFX"];
for (int j = 0; j < engines.propellants.Count; j++)
{
Propellant prop = engines.propellants[j];
if (prop.name == "IntakeAir")
{
_airBreathingEngines.Add(engines);
break;
}
}
}
}
for (int i = 0; i < allUnusedAeroModules.Count; i++) //get all covered airbreathing Engines
{
FARAeroPartModule aeroModule = allUnusedAeroModules[i];
if (aeroModule == null)
{
continue;
}
Part p = aeroModule.part;
if (p.Modules.Contains("ModuleEngines"))
{
ModuleEngines engines = (ModuleEngines)p.Modules["ModuleEngines"];
for (int j = 0; j < engines.propellants.Count; j++)
{
Propellant prop = engines.propellants[j];
if (prop.name == "IntakeAir")
{
_airBreathingEngines.Add(engines);
break;
}
}
}
if (p.Modules.Contains("ModuleEnginesFX"))
{
ModuleEnginesFX engines = (ModuleEnginesFX)p.Modules["ModuleEnginesFX"];
for (int j = 0; j < engines.propellants.Count; j++)
{
Propellant prop = engines.propellants[j];
if (prop.name == "IntakeAir")
{
_airBreathingEngines.Add(engines);
break;
}
}
}
}
}
