public DragCubeList.CubeData AddSurfaceDragDirection(Vector3 direction, float machNumber)
{
part.DragCubes.SetDrag(direction, machNumber);
//var liftCurves = GetPrivate<PhysicsGlobals.LiftingSurfaceCurve>("liftCurves", part.DragCubes);
var liftCurves = part.DragCubes.BodyLiftCurve;
float num = 0;
DragCubeList.CubeData result = default(DragCubeList.CubeData);
result.dragVector = direction;
for (int i = 0; i < 6; i++)
{
Vector3 faceDirection = DragCubeList.GetFaceDirection((DragCube.DragFace)i);
float num2 = Vector3.Dot(direction, faceDirection);
float dotNormalized = (num2 + 1) * 0.5f;
float num3 = PhysicsGlobals.DragCurveValue(PhysicsGlobals.SurfaceCurves, dotNormalized, machNumber);
float num4 = this.areaOccluded [i] * num3;
float num5 = this.weightedDrag [i];
float num6 = num5;
if (num6 < 1)
{
num6 = PhysicsGlobals.DragCurveCd.Evaluate(num6);
}
result.area += num4;
result.areaDrag += num4 * num6;
result.crossSectionalArea += this.areaOccluded [i] * Mathf.Clamp01(num2);
if (num5 < 0.01)
{
num5 = 1;
}
if (num5 < 1)
{
num5 = 1 / num5;
}
result.exposedArea += num4 / PhysicsGlobals.DragCurveMultiplier.Evaluate(machNumber) * num5;
if (num2 > 0)
{
num += num2;
double num7 = (double)liftCurves.liftCurve.Evaluate(num2);
if (!double.IsNaN(num7))
{
result.liftForce += -faceDirection * (num2 * this.areaOccluded [i] * this.weightedDrag [i] * (float)num7);
}
result.depth += num2 * this.weightedDepth [i];
result.dragCoeff += num2 * num6;
}
}
float num8 = 1 / num;
result.depth *= num8;
result.dragCoeff *= num8;
return(result);
}
private void Init(IShipconstruct v)
{
totalMass = 0;
dryMass = 0;
CoM = Vector3.zero;
CoM_dry = Vector3.zero;
relativeWingArea = 0;
stage = 0;
List <Part> oParts = v.Parts;
List <SimulatedPart> variableDragParts_ctrls = new List <SimulatedPart>();
count = oParts.Count;
if (HighLogic.LoadedSceneIsEditor)
{
for (int i = 0; i < v.Parts.Count; i++)
{
Part p = v.Parts[i];
if (p.dragModel == Part.DragModel.CUBE && !p.DragCubes.None)
{
DragCubeList cubes = p.DragCubes;
lock (cubes)
{
DragCubeList.CubeData p_drag_data = new DragCubeList.CubeData();
try
{
cubes.SetDragWeights();
cubes.SetPartOcclusion();
cubes.AddSurfaceDragDirection(-Vector3.forward, 0, ref p_drag_data);
}
catch (Exception)
{
cubes.SetDrag(Vector3.forward, 0);
cubes.ForceUpdate(true, true);
cubes.SetDragWeights();
cubes.SetPartOcclusion();
cubes.AddSurfaceDragDirection(-Vector3.forward, 0, ref p_drag_data);
//Debug.Log(String.Format("Trajectories: Caught NRE on Drag Initialization. Should be fixed now. {0}", e));
}
}
}
}
}
bool lgWarning = false;
for (int i = 0; i < count; i++)
{
if (!lgWarning)
{
ModuleWheels.ModuleWheelDeployment gear = oParts[i].FindModuleImplementing <ModuleWheels.ModuleWheelDeployment>();
bool forcedRetract = !oParts[i].ShieldedFromAirstream && gear != null && gear.Position > 0;
if (forcedRetract)
{
lgWarning = true;
}
}
}
// Recursively add all parts to collections
// What a crazy change to make just to accomodate rotating parts!
partCollection = PartCollection.Borrow(this, oParts[0]);
CoM /= totalMass;
CoM_dry /= dryMass;
partCollection.origin = CoM;
if (relativeWingArea == 0)
{
// I'm not sure what effect calling ScreenMessages from a background thread will be.
// Fortunately, anyone using this mod probably has at least one wing.
ScreenMessages.PostScreenMessage("No wings found, using a reference area of 1.", 5, ScreenMessageStyle.UPPER_CENTER);
relativeWingArea = 1;
}
//if (lgWarning)
//ScreenMessages.PostScreenMessage("Landing gear deployed, results may not be accurate.", 5, ScreenMessageStyle.UPPER_CENTER);
}
//*******************************************************
public static Vector3 SimAeroForce(Vessel _vessel, Vector3 v_wrld_vel, double altitude, double latitude = 0.0)
{
CelestialBody body = _vessel.mainBody;
double pressure = body.GetPressure(altitude);
// Lift and drag for force accumulation.
Vector3d total_lift = Vector3d.zero;
Vector3d total_drag = Vector3d.zero;
// dynamic pressure for standard drag equation
double rho = GetDensity(altitude, body);
double dyn_pressure = 0.0005 * rho * v_wrld_vel.sqrMagnitude;
if (rho <= 0)
{
return Vector3.zero;
}
double soundSpeed = body.GetSpeedOfSound(pressure, rho);
double mach = v_wrld_vel.magnitude / soundSpeed;
if (mach > 25.0) { mach = 25.0; }
// Loop through all parts, accumulating drag and lift.
for (int i = 0; i < _vessel.Parts.Count; ++i)
{
// need checks on shielded components
Part p = _vessel.Parts[i];
#if DEBUG
TrajectoriesDebug partDebug = VesselAerodynamicModel.DebugParts ? p.FindModuleImplementing<TrajectoriesDebug>() : null;
if (partDebug != null)
{
partDebug.Drag = 0;
partDebug.Lift = 0;
}
#endif
if (p.ShieldedFromAirstream || p.Rigidbody == null)
{
continue;
}
// Get Drag
Vector3 sim_dragVectorDir = v_wrld_vel.normalized;
Vector3 sim_dragVectorDirLocal = -(p.transform.InverseTransformDirection(sim_dragVectorDir));
Vector3 liftForce = new Vector3(0, 0, 0);
Vector3d dragForce;
switch(p.dragModel)
{
case Part.DragModel.DEFAULT:
case Part.DragModel.CUBE:
DragCubeList cubes = p.DragCubes;
DragCubeList.CubeData p_drag_data = new DragCubeList.CubeData();
float drag;
if (cubes.None) // since 1.0.5, some parts don't have drag cubes (for example fuel lines and struts)
{
drag = p.maximum_drag;
}
else
{
try
{
cubes.AddSurfaceDragDirection(-sim_dragVectorDirLocal, (float)mach, ref p_drag_data);
}
catch (Exception)
{
cubes.SetDrag(sim_dragVectorDirLocal, (float)mach);
cubes.ForceUpdate(true, true);
cubes.AddSurfaceDragDirection(-sim_dragVectorDirLocal, (float)mach, ref p_drag_data);
//Debug.Log(String.Format("Trajectories: Caught NRE on Drag Initialization. Should be fixed now. {0}", e));
}
drag = p_drag_data.areaDrag * PhysicsGlobals.DragCubeMultiplier;
liftForce = p_drag_data.liftForce;
}
double sim_dragScalar = dyn_pressure * (double)drag * PhysicsGlobals.DragMultiplier;
dragForce = -(Vector3d)sim_dragVectorDir * sim_dragScalar;
break;
case Part.DragModel.SPHERICAL:
dragForce = -(Vector3d)sim_dragVectorDir * (double)p.maximum_drag;
break;
case Part.DragModel.CYLINDRICAL:
dragForce = -(Vector3d)sim_dragVectorDir * (double)Mathf.Lerp(p.minimum_drag, p.maximum_drag, Mathf.Abs(Vector3.Dot(p.partTransform.TransformDirection(p.dragReferenceVector), sim_dragVectorDir)));
break;
case Part.DragModel.CONIC:
dragForce = -(Vector3d)sim_dragVectorDir * (double)Mathf.Lerp(p.minimum_drag, p.maximum_drag, Vector3.Angle(p.partTransform.TransformDirection(p.dragReferenceVector), sim_dragVectorDir) / 180f);
break;
default:
// no drag to apply
dragForce = new Vector3d();
break;
}
#if DEBUG
if (partDebug != null)
{
partDebug.Drag += (float)dragForce.magnitude;
}
#endif
total_drag += dragForce;
// If it isn't a wing or lifter, get body lift.
if (!p.hasLiftModule)
{
float simbodyLiftScalar = p.bodyLiftMultiplier * PhysicsGlobals.BodyLiftMultiplier * (float)dyn_pressure;
simbodyLiftScalar *= PhysicsGlobals.GetLiftingSurfaceCurve("BodyLift").liftMachCurve.Evaluate((float)mach);
Vector3 bodyLift = p.transform.rotation * (simbodyLiftScalar * liftForce);
bodyLift = Vector3.ProjectOnPlane(bodyLift, sim_dragVectorDir);
// Only accumulate forces for non-LiftModules
total_lift += bodyLift;
}
// Find ModuleLifingSurface for wings and liftforce.
// Should catch control surface as it is a subclass
for (int j = 0; j < p.Modules.Count; ++j)
{
var m = p.Modules[j];
float mcs_mod;
if (m is ModuleLiftingSurface)
{
mcs_mod = 1.0f;
double liftQ = dyn_pressure * 1000;
ModuleLiftingSurface wing = (ModuleLiftingSurface)m;
Vector3 nVel = Vector3.zero;
Vector3 liftVector = Vector3.zero;
float liftdot;
float absdot;
wing.SetupCoefficients(v_wrld_vel, out nVel, out liftVector, out liftdot, out absdot);
double prevMach = p.machNumber;
p.machNumber = mach;
Vector3 local_lift = mcs_mod * wing.GetLiftVector(liftVector, liftdot, absdot, liftQ, (float)mach);
Vector3 local_drag = mcs_mod * wing.GetDragVector(nVel, absdot, liftQ);
p.machNumber = prevMach;
total_lift += local_lift;
total_drag += local_drag;
#if DEBUG
if (partDebug != null)
{
partDebug.Lift += (float)local_lift.magnitude;
partDebug.Drag += (float)local_drag.magnitude;
}
#endif
}
}
}
// RETURN STUFF
Vector3 force = total_lift + total_drag;
return force;
}
//*******************************************************
public static Vector3 SimAeroForce(Vessel _vessel, Vector3 v_wrld_vel, double altitude, double latitude = 0)
{
CelestialBody body = _vessel.mainBody;
double pressure = body.GetPressure(altitude);
// Lift and drag for force accumulation.
Vector3d total_lift = Vector3d.zero;
Vector3d total_drag = Vector3d.zero;
// dynamic pressure for standard drag equation
double rho = GetDensity(altitude, body);
double dyn_pressure = 0.0005 * rho * v_wrld_vel.sqrMagnitude;
if (rho <= 0)
{
return(Vector3.zero);
}
double soundSpeed = body.GetSpeedOfSound(pressure, rho);
double mach = v_wrld_vel.magnitude / soundSpeed;
if (mach > 25.0)
{
mach = 25.0;
}
// Loop through all parts, accumulating drag and lift.
for (int i = 0; i < _vessel.Parts.Count; ++i)
{
// need checks on shielded components
Part p = _vessel.Parts[i];
if (p.ShieldedFromAirstream || p.Rigidbody == null)
{
continue;
}
// Get Drag
Vector3 sim_dragVectorDir = v_wrld_vel.normalized;
Vector3 sim_dragVectorDirLocal = -(p.transform.InverseTransformDirection(sim_dragVectorDir));
Vector3 liftForce = new Vector3(0, 0, 0);
Vector3d dragForce;
switch (p.dragModel)
{
case Part.DragModel.DEFAULT:
case Part.DragModel.CUBE:
DragCubeList cubes = p.DragCubes;
DragCubeList.CubeData p_drag_data = new DragCubeList.CubeData();
float drag;
if (cubes.None) // since 1.0.5, some parts don't have drag cubes (for example fuel lines and struts)
{
drag = p.maximum_drag;
}
else
{
try
{
cubes.AddSurfaceDragDirection(-sim_dragVectorDirLocal, (float)mach, ref p_drag_data);
}
catch (Exception)
{
cubes.SetDrag(sim_dragVectorDirLocal, (float)mach);
cubes.ForceUpdate(true, true);
cubes.AddSurfaceDragDirection(-sim_dragVectorDirLocal, (float)mach, ref p_drag_data);
//Debug.Log(String.Format("Trajectories: Caught NRE on Drag Initialization. Should be fixed now. {0}", e));
}
float pseudoreynolds = (float)(rho * Mathf.Abs(v_wrld_vel.magnitude));
float pseudoredragmult = PhysicsGlobals.DragCurvePseudoReynolds.Evaluate(pseudoreynolds);
drag = p_drag_data.areaDrag * PhysicsGlobals.DragCubeMultiplier * pseudoredragmult;
liftForce = p_drag_data.liftForce;
}
double sim_dragScalar = dyn_pressure * (double)drag * PhysicsGlobals.DragMultiplier;
dragForce = -(Vector3d)sim_dragVectorDir * sim_dragScalar;
break;
case Part.DragModel.SPHERICAL:
dragForce = -(Vector3d)sim_dragVectorDir * (double)p.maximum_drag;
break;
case Part.DragModel.CYLINDRICAL:
dragForce = -(Vector3d)sim_dragVectorDir * (double)Mathf.Lerp(p.minimum_drag, p.maximum_drag, Mathf.Abs(Vector3.Dot(p.partTransform.TransformDirection(p.dragReferenceVector), sim_dragVectorDir)));
break;
case Part.DragModel.CONIC:
dragForce = -(Vector3d)sim_dragVectorDir * (double)Mathf.Lerp(p.minimum_drag, p.maximum_drag, Vector3.Angle(p.partTransform.TransformDirection(p.dragReferenceVector), sim_dragVectorDir) / 180f);
break;
default:
// no drag to apply
dragForce = new Vector3d();
break;
}
total_drag += dragForce;
// If it isn't a wing or lifter, get body lift.
if (!p.hasLiftModule)
{
float simbodyLiftScalar = p.bodyLiftMultiplier * PhysicsGlobals.BodyLiftMultiplier * (float)dyn_pressure;
simbodyLiftScalar *= PhysicsGlobals.GetLiftingSurfaceCurve("BodyLift").liftMachCurve.Evaluate((float)mach);
Vector3 bodyLift = p.transform.rotation * (simbodyLiftScalar * liftForce);
bodyLift = Vector3.ProjectOnPlane(bodyLift, sim_dragVectorDir);
// Only accumulate forces for non-LiftModules
//Debug.Log("[Trajectories] bodyLift=" + bodyLift);
total_lift += bodyLift;
}
// Find ModuleLifingSurface for wings and liftforce.
// Should catch control surface as it is a subclass
for (int j = 0; j < p.Modules.Count; ++j)
{
var m = p.Modules[j];
float mcs_mod;
if (m is ModuleLiftingSurface)
{
mcs_mod = 1.0f;
double liftQ = dyn_pressure * 1000;
ModuleLiftingSurface wing = (ModuleLiftingSurface)m;
Vector3 nVel = Vector3.zero;
Vector3 liftVector = Vector3.zero;
float liftdot;
float absdot;
wing.SetupCoefficients(v_wrld_vel, out nVel, out liftVector, out liftdot, out absdot);
double prevMach = p.machNumber;
p.machNumber = mach;
Vector3 local_lift = mcs_mod * wing.GetLiftVector(liftVector, liftdot, absdot, liftQ, (float)mach);
Vector3 local_drag = mcs_mod * wing.GetDragVector(nVel, absdot, liftQ);
p.machNumber = prevMach;
total_lift += local_lift;
total_drag += local_drag;
}
}
}
// RETURN STUFF
//Debug.Log("[Trajectories] total_lift" + total_lift + " total_drag=" + total_drag);
Vector3 force = total_lift + total_drag;
return(force);
}
//*******************************************************
public static Vector3d SimAeroForce(Vessel vessel, Vector3d v_wrld_vel, double altitude, double latitude = 0.0)
{
Profiler.Start("SimAeroForce");
CelestialBody body = vessel.mainBody;
double pressure = body.GetPressure(altitude);
// Lift and drag for force accumulation.
Vector3d total_lift = Vector3d.zero;
Vector3d total_drag = Vector3d.zero;
// dynamic pressure for standard drag equation
double rho = GetDensity(altitude, body);
double dyn_pressure = 0.0005 * rho * v_wrld_vel.sqrMagnitude;
if (rho <= 0)
{
return(Vector3.zero);
}
double soundSpeed = body.GetSpeedOfSound(pressure, rho);
double mach = v_wrld_vel.magnitude / soundSpeed;
if (mach > 25.0)
{
mach = 25.0;
}
// Loop through all parts, accumulating drag and lift.
for (int i = 0; i < vessel.Parts.Count; ++i)
{
// need checks on shielded components
Part p = vessel.Parts[i];
#if DEBUG
TrajectoriesDebug partDebug = VesselAerodynamicModel.DebugParts ? p.FindModuleImplementing <TrajectoriesDebug>() : null;
if (partDebug != null)
{
partDebug.Drag = 0;
partDebug.Lift = 0;
}
#endif
if (p.ShieldedFromAirstream || p.Rigidbody == null)
{
continue;
}
// Get Drag
Vector3d sim_dragVectorDir = v_wrld_vel.normalized;
Vector3d sim_dragVectorDirLocal = -(p.transform.InverseTransformDirection(sim_dragVectorDir));
Vector3d liftForce = Vector3d.zero;
Vector3d dragForce;
Profiler.Start("SimAeroForce#drag");
switch (p.dragModel)
{
case Part.DragModel.DEFAULT:
case Part.DragModel.CUBE:
DragCubeList cubes = p.DragCubes;
DragCubeList.CubeData p_drag_data = new DragCubeList.CubeData();
double drag;
if (cubes.None) // since 1.0.5, some parts don't have drag cubes (for example fuel lines and struts)
{
drag = p.maximum_drag;
}
else
{
try
{
cubes.AddSurfaceDragDirection(-sim_dragVectorDirLocal, (float)mach, ref p_drag_data);
}
catch (Exception e)
{
cubes.SetDrag(sim_dragVectorDirLocal, (float)mach);
cubes.ForceUpdate(true, true);
cubes.AddSurfaceDragDirection(-sim_dragVectorDirLocal, (float)mach, ref p_drag_data);
Util.DebugLogError("Exception {0} on drag initialization", e);
}
double pseudoreynolds = rho * Math.Abs(v_wrld_vel.magnitude);
double pseudoredragmult = PhysicsGlobals.DragCurvePseudoReynolds.Evaluate((float)pseudoreynolds);
drag = p_drag_data.areaDrag * PhysicsGlobals.DragCubeMultiplier * pseudoredragmult;
liftForce = p_drag_data.liftForce;
}
double sim_dragScalar = dyn_pressure * drag * PhysicsGlobals.DragMultiplier;
dragForce = -sim_dragVectorDir * sim_dragScalar;
break;
case Part.DragModel.SPHERICAL:
dragForce = -sim_dragVectorDir * p.maximum_drag;
break;
case Part.DragModel.CYLINDRICAL:
dragForce = -sim_dragVectorDir *Mathf.Lerp(p.minimum_drag, p.maximum_drag, Mathf.Abs(Vector3.Dot(p.partTransform.TransformDirection(p.dragReferenceVector), sim_dragVectorDir)));
break;
case Part.DragModel.CONIC:
dragForce = -sim_dragVectorDir *Mathf.Lerp(p.minimum_drag, p.maximum_drag, Vector3.Angle(p.partTransform.TransformDirection(p.dragReferenceVector), sim_dragVectorDir) / 180f);
break;
default:
// no drag to apply
dragForce = Vector3d.zero;
break;
}
Profiler.Stop("SimAeroForce#drag");
#if DEBUG
if (partDebug != null)
{
partDebug.Drag += (float)dragForce.magnitude;
}
#endif
total_drag += dragForce;
// If it isn't a wing or lifter, get body lift.
if (!p.hasLiftModule)
{
Profiler.Start("SimAeroForce#BodyLift");
float simbodyLiftScalar = p.bodyLiftMultiplier * PhysicsGlobals.BodyLiftMultiplier * (float)dyn_pressure;
simbodyLiftScalar *= PhysicsGlobals.GetLiftingSurfaceCurve("BodyLift").liftMachCurve.Evaluate((float)mach);
Vector3 bodyLift = p.transform.rotation * (simbodyLiftScalar * liftForce);
bodyLift = Vector3.ProjectOnPlane(bodyLift, sim_dragVectorDir);
// Only accumulate forces for non-LiftModules
total_lift += bodyLift;
Profiler.Stop("SimAeroForce#BodyLift");
}
Profiler.Start("SimAeroForce#LiftingSurface");
// Find ModuleLifingSurface for wings and liftforce.
// Should catch control surface as it is a subclass
for (int j = 0; j < p.Modules.Count; ++j)
{
var m = p.Modules[j];
if (m is ModuleLiftingSurface wing)
{
const float mcs_mod = 1.0f;
double liftQ = dyn_pressure * 1000;
wing.SetupCoefficients(v_wrld_vel, out var nVel, out var liftVector, out var liftdot, out var absdot);
double prevMach = p.machNumber;
p.machNumber = mach;
Vector3 local_lift = mcs_mod * wing.GetLiftVector(liftVector, liftdot, absdot, liftQ, (float)mach);
Vector3 local_drag = mcs_mod * wing.GetDragVector(nVel, absdot, liftQ);
p.machNumber = prevMach;
total_lift += local_lift;
total_drag += local_drag;
#if DEBUG
if (partDebug != null)
{
partDebug.Lift += local_lift.magnitude;
partDebug.Drag += local_drag.magnitude;
}
#endif
}
}
Profiler.Stop("SimAeroForce#LiftingSurface");
}
// RETURN STUFF
Vector3 force = total_lift + total_drag;
Profiler.Stop("SimAeroForce");
return(force);
}
//*******************************************************
public static Vector3 SimDragForce(CelestialBody body, IShipconstruct vessel, Vector3 v_wrld_vel, double altitude, double latitude = 0.0)
{
double pressure = body.GetPressure(altitude);
// Lift and drag for force accumulation.
Vector3d total_drag = Vector3d.zero;
// dynamic pressure for standard drag equation
double rho = GetDensity(altitude, body);
double dyn_pressure = 0.0005 * rho * v_wrld_vel.sqrMagnitude;
if (rho <= 0)
{
return(Vector3.zero);
}
double soundSpeed = body.GetSpeedOfSound(pressure, rho);
double mach = v_wrld_vel.magnitude / soundSpeed;
if (mach > 25.0)
{
mach = 25.0;
}
// Loop through all parts, accumulating drag and lift.
for (int i = vessel.Parts.Count - 1; i >= 0; i--)
{
// need checks on shielded components
Part part = vessel.Parts[i];
if (part.ShieldedFromAirstream || part.Rigidbody == null)
{
continue;
}
// Get Drag
Vector3 sim_dragVectorDir = v_wrld_vel.normalized;
Vector3 sim_dragVectorDirLocal = -(part.transform.InverseTransformDirection(sim_dragVectorDir));
Vector3d dragForce;
switch (part.dragModel)
{
case Part.DragModel.DEFAULT:
case Part.DragModel.CUBE:
DragCubeList cubes = part.DragCubes;
DragCubeList.CubeData p_drag_data = new DragCubeList.CubeData();
float drag;
if (cubes.None) // since 1.0.5, some parts don't have drag cubes (for example fuel lines and struts)
{
drag = part.maximum_drag;
}
else
{
try
{
cubes.SetDragWeights();
cubes.SetPartOcclusion();
cubes.AddSurfaceDragDirection(-sim_dragVectorDirLocal, (float)mach, ref p_drag_data);
}
catch (Exception)
{
cubes.SetDrag(sim_dragVectorDirLocal, (float)mach);
cubes.ForceUpdate(true, true);
cubes.AddSurfaceDragDirection(-sim_dragVectorDirLocal, (float)mach, ref p_drag_data);
//Debug.Log(String.Format("Trajectories: Caught NRE on Drag Initialization. Should be fixed now. {0}", e));
}
float pseudoreynolds = (float)(rho * Mathf.Abs(v_wrld_vel.magnitude));
float pseudoredragmult = PhysicsGlobals.DragCurvePseudoReynolds.Evaluate(pseudoreynolds);
drag = p_drag_data.areaDrag * PhysicsGlobals.DragCubeMultiplier * pseudoredragmult;
}
double sim_dragScalar = dyn_pressure * (double)drag * PhysicsGlobals.DragMultiplier;
dragForce = -(Vector3d)sim_dragVectorDir * sim_dragScalar;
break;
case Part.DragModel.SPHERICAL:
dragForce = -(Vector3d)sim_dragVectorDir * (double)part.maximum_drag;
break;
case Part.DragModel.CYLINDRICAL:
dragForce = -(Vector3d)sim_dragVectorDir * (double)Mathf.Lerp(part.minimum_drag, part.maximum_drag, Mathf.Abs(Vector3.Dot(part.partTransform.TransformDirection(part.dragReferenceVector), sim_dragVectorDir)));
break;
case Part.DragModel.CONIC:
dragForce = -(Vector3d)sim_dragVectorDir * (double)Mathf.Lerp(part.minimum_drag, part.maximum_drag, Vector3.Angle(part.partTransform.TransformDirection(part.dragReferenceVector), sim_dragVectorDir) / 180f);
break;
default:
// no drag to apply
dragForce = new Vector3d();
break;
}
total_drag += dragForce;
// Find ModuleLifingSurface for wings and liftforce.
// Should catch control surface as it is a subclass
for (int j = part.Modules.Count - 1; j >= 0; j--)
{
if (part.Modules[j] is ModuleLiftingSurface)
{
float mcs_mod = 1.0f;
double liftQ = dyn_pressure * 1000;
ModuleLiftingSurface wing = (ModuleLiftingSurface)part.Modules[j];
Vector3 nVel = Vector3.zero;
Vector3 liftVector = Vector3.zero;
float liftdot;
float absdot;
wing.SetupCoefficients(v_wrld_vel, out nVel, out liftVector, out liftdot, out absdot);
double prevMach = part.machNumber;
part.machNumber = mach;
Vector3 local_drag = mcs_mod * wing.GetDragVector(nVel, absdot, liftQ);
part.machNumber = prevMach;
total_drag += local_drag;
}
}
}
// RETURN STUFF
return(total_drag);
}
//*******************************************************
public static Vector3 SimLiftForce(CelestialBody body, IShipconstruct vessel, Vector3 v_wrld_vel, double altitude, double latitude = 0.0)
{
//Profiler.Start("SimLiftForce");
double pressure = body.GetPressure(altitude);
// Lift and drag for force accumulation.
Vector3d total_lift = Vector3d.zero;
// dynamic pressure for standard drag equation
double rho = GetDensity(altitude, body);
double dyn_pressure = 0.0005 * rho * v_wrld_vel.sqrMagnitude;
if (rho <= 0)
{
return(Vector3.zero);
}
double soundSpeed = body.GetSpeedOfSound(pressure, rho);
double mach = v_wrld_vel.magnitude / soundSpeed;
if (mach > 25.0)
{
mach = 25.0;
}
// Loop through all parts, accumulating drag and lift.
for (int i = vessel.Parts.Count - 1; i >= 0; i--)
{
// need checks on shielded components
Part part = vessel.Parts[i];
if (part.ShieldedFromAirstream || part.Rigidbody == null)
{
continue;
}
// Get Drag
Vector3 sim_dragVectorDir = v_wrld_vel.normalized;
Vector3 sim_dragVectorDirLocal = -(part.transform.InverseTransformDirection(sim_dragVectorDir));
Vector3 liftForce = new Vector3(0, 0, 0);
//Profiler.Start("SimLiftForce#Body");
switch (part.dragModel)
{
case Part.DragModel.DEFAULT:
case Part.DragModel.CUBE:
DragCubeList cubes = part.DragCubes;
DragCubeList.CubeData p_drag_data = new DragCubeList.CubeData();
if (!cubes.None) // since 1.0.5, some parts don't have drag cubes (for example fuel lines and struts)
{
try
{
cubes.SetDragWeights();
cubes.SetPartOcclusion();
cubes.AddSurfaceDragDirection(-sim_dragVectorDirLocal, (float)mach, ref p_drag_data);
}
catch (Exception)
{
cubes.SetDrag(sim_dragVectorDirLocal, (float)mach);
cubes.ForceUpdate(true, true);
cubes.AddSurfaceDragDirection(-sim_dragVectorDirLocal, (float)mach, ref p_drag_data);
//Debug.Log(String.Format("Trajectories: Caught NRE on Drag Initialization. Should be fixed now. {0}", e));
}
float pseudoreynolds = (float)(rho * Mathf.Abs(v_wrld_vel.magnitude));
float pseudoredragmult = PhysicsGlobals.DragCurvePseudoReynolds.Evaluate(pseudoreynolds);
liftForce = p_drag_data.liftForce;
}
break;
}
// If it isn't a wing or lifter, get body lift.
if (!part.hasLiftModule)
{
float simbodyLiftScalar = part.bodyLiftMultiplier * PhysicsGlobals.BodyLiftMultiplier * (float)dyn_pressure;
simbodyLiftScalar *= PhysicsGlobals.GetLiftingSurfaceCurve("BodyLift").liftMachCurve.Evaluate((float)mach);
Vector3 bodyLift = part.transform.rotation * (simbodyLiftScalar * liftForce);
bodyLift = Vector3.ProjectOnPlane(bodyLift, sim_dragVectorDir);
// Only accumulate forces for non-LiftModules
total_lift += bodyLift;
}
//Profiler.Stop("SimLiftForce#Body");
// Find ModuleLifingSurface for wings and liftforce.
// Should catch control surface as it is a subclass
//Profiler.Start("SimLiftForce#LiftModule");
for (int j = part.Modules.Count - 1; j >= 0; j--)
{
if (part.Modules[j] is ModuleLiftingSurface)
{
float mcs_mod = 1.0f;
double liftQ = dyn_pressure * 1000;
ModuleLiftingSurface wing = (ModuleLiftingSurface)part.Modules[j];
Vector3 nVel = Vector3.zero;
Vector3 liftVector = Vector3.zero;
float liftdot;
float absdot;
wing.SetupCoefficients(v_wrld_vel, out nVel, out liftVector, out liftdot, out absdot);
double prevMach = part.machNumber;
part.machNumber = mach;
Vector3 local_lift = mcs_mod * wing.GetLiftVector(liftVector, liftdot, absdot, liftQ, (float)mach);
part.machNumber = prevMach;
total_lift += local_lift;
}
}
//Profiler.Stop("SimLiftForce#LiftModule");
}
// RETURN STUFF
//Profiler.Stop("SimLiftForce");
return(total_lift);
}
private void Init(IShipconstruct v, SimCurves _simCurves)
{
totalMass = 0;
dryMass = 0;
CoM = Vector3.zero;
CoM_dry = Vector3.zero;
List<Part> oParts = v.Parts;
List<SimulatedPart> variableDragParts_ctrls = new List<SimulatedPart>();
count = oParts.Count;
if (HighLogic.LoadedSceneIsEditor)
{
for (int i = 0; i < v.Parts.Count; i++)
{
Part p = v.Parts[i];
if (p.dragModel == Part.DragModel.CUBE && !p.DragCubes.None)
{
DragCubeList cubes = p.DragCubes;
DragCubeList.CubeData p_drag_data = new DragCubeList.CubeData();
try
{
cubes.SetDragWeights();
cubes.SetPartOcclusion();
cubes.AddSurfaceDragDirection(-Vector3.forward, 0, ref p_drag_data);
}
catch (Exception)
{
cubes.SetDrag(Vector3.forward, 0);
cubes.ForceUpdate(true, true);
cubes.SetDragWeights();
cubes.SetPartOcclusion();
cubes.AddSurfaceDragDirection(-Vector3.forward, 0, ref p_drag_data);
//Debug.Log(String.Format("Trajectories: Caught NRE on Drag Initialization. Should be fixed now. {0}", e));
}
}
}
}
simCurves = _simCurves;
if (parts.Capacity < count)
parts.Capacity = count;
bool lgWarning = false;
int stage = 0;
for (int i = 0; i < count; i++)
{
if (!lgWarning)
{
ModuleWheels.ModuleWheelDeployment gear = oParts[i].FindModuleImplementing<ModuleWheels.ModuleWheelDeployment>();
bool forcedRetract = !oParts[i].ShieldedFromAirstream && gear != null && gear.Position > 0;
if (forcedRetract)
lgWarning = true;
}
SimulatedPart simulatedPart = SimulatedPart.Borrow(oParts[i], this);
parts.Add(simulatedPart);
totalMass += simulatedPart.totalMass;
dryMass += simulatedPart.dryMass;
CoM += simulatedPart.totalMass * simulatedPart.CoM;
CoM_dry += simulatedPart.dryMass * simulatedPart.CoM;
ModuleLiftingSurface liftingSurface = oParts[i].FindModuleImplementing<ModuleLiftingSurface>();
if (liftingSurface != null)
{
parts[i].hasLiftModule = true;
if (liftingSurface is ModuleControlSurface ctrlSurface)
{
ctrls.Add(SimulatedControlSurface.Borrow(ctrlSurface, simulatedPart));
variableDragParts_ctrls.Add(simulatedPart);
if (ctrlSurface.ctrlSurfaceArea < 1)
surfaces.Add(SimulatedLiftingSurface.Borrow(ctrlSurface, simulatedPart));
}
else
surfaces.Add(SimulatedLiftingSurface.Borrow(liftingSurface, simulatedPart));
}
List<ITorqueProvider> torqueProviders = oParts[i].FindModulesImplementing<ITorqueProvider>();
// TODO: Add them to a list.
if(oParts[i].inverseStage > stage)
{
SimulatedEngine.Release(engines);
engines.Clear();
stage = oParts[i].inverseStage;
}
if (oParts[i].inverseStage >= stage)
{
MultiModeEngine multiMode = oParts[i].FindModuleImplementing<MultiModeEngine>();
if (multiMode != null)
{
engines.Add(SimulatedEngine.Borrow(oParts[i].FindModulesImplementing<ModuleEngines>().Find(engine => engine.engineID == multiMode.mode), simulatedPart));
}
else
{
ModuleEngines engine = oParts[i].FindModulesImplementing<ModuleEngines>().FirstOrDefault();
if (engine != null)
engines.Add(SimulatedEngine.Borrow(engine, simulatedPart));
}
}
}
CoM /= totalMass;
CoM_dry /= dryMass;
if (lgWarning)
ScreenMessages.PostScreenMessage("Landing gear deployed, results may not be accurate.", 5, ScreenMessageStyle.UPPER_CENTER);
/*for (int i = 0; i < count; i++)
{
parts[i].CoM -= this.CoM;
parts[i].CoL -= this.CoM;
parts[i].CoP -= this.CoM;
}*/
parts.RemoveAll(part => variableDragParts_ctrls.Contains(part));
}
public void update(double curSpeed, double curDensity)
{
maxSpeed = 0;
breakDistance = 0;
curDensity = Math.Max(curDensity, 0.2 * vesselState.mainBody.atmDensityASL);
double curSpeedOfSound = Math.Max(vesselState.speedOfSound, vesselState.mainBody.GetSpeedOfSound(0.2 * vesselState.mainBody.atmPressureASL, 0.2 * vesselState.mainBody.atmDensityASL));
//create List by descending order of maxSpeed with drag and max chute reaction time
SortedList <double, (float, float)> parachuteTypes = new SortedList <double, (float, float)>(Comparer <double> .Create((a, b) => Math.Sign(b - a)));
foreach (var p in vesselState.parachutes)
{
if (p.deploymentState == ModuleParachute.deploymentStates.STOWED)
{
p.refDensity = curDensity;
p.CalcBaseStats();
DragCubeList simParachute = new DragCubeList();
simParachute.LoadCube(p.part.DragCubes, "DEPLOYED");
simParachute.SetPart(p.part);
simParachute.SetOcclusionMultiplier(0f);
simParachute.ResetCubeWeights();
simParachute.SetDragWeights();
simParachute.SetPartOcclusion();
//Debug.Log(String.Format("ParachuteInfo.update Parchute {0} has up Cube area={1:F1} drag={2:F1} weight={3:F1} AreaOccluded={4:F1}",
// p.part.name, simParachute.Cubes[0].Area[(int) DragCube.DragFace.YP], simParachute.Cubes[0].Drag[(int) DragCube.DragFace.YP],
// simParachute.Cubes[0].Weight, simParachute.AreaOccluded[(int)DragCube.DragFace.YP]));
DragCubeList.CubeData simDrag = new DragCubeList.CubeData();
simParachute.AddSurfaceDragDirection(Vector3.up, (float)(p.maxSafeSpeedAtRef / curSpeedOfSound), ref simDrag);
//Debug.Log(String.Format("ParachuteInfo.update Parchute {0} has areaDrag={1:F1}, crossSectionalArea={2:F1}, exposedArea={3:F1}",
// p.part.name, simDrag.areaDrag, simDrag.crossSectionalArea, simDrag.exposedArea));
if (parachuteTypes.ContainsKey(p.maxSafeSpeedAtRef))
{
parachuteTypes[p.maxSafeSpeedAtRef] = (parachuteTypes[p.maxSafeSpeedAtRef].Item1 + simDrag.areaDrag,
Mathf.Max(parachuteTypes[p.maxSafeSpeedAtRef].Item2, p.Anim[p.semiDeployedAnimation].length / p.semiDeploymentSpeed + p.Anim[p.fullyDeployedAnimation].length / p.deploymentSpeed));
}
else
{
parachuteTypes.Add(p.maxSafeSpeedAtRef, (simDrag.areaDrag, p.Anim[p.semiDeployedAnimation].length / p.semiDeploymentSpeed + p.Anim[p.fullyDeployedAnimation].length / p.deploymentSpeed));
}
}
}
float totalFriction = 0;
double lastSpeed = 0;
foreach (var pt in parachuteTypes)
{
double effSpeed = Math.Min(curSpeed, pt.Key);
// base equation deceleration term + chute reaction term with deceleration taken from moving equations with netwon friction
// during reaction time we hardly break, so assume
float friction_const = pt.Value.Item1 * 0.0005f * (float)curDensity * PhysicsGlobals.DragMultiplier
* PhysicsGlobals.DragCubeMultiplier * PhysicsGlobals.DragCurvePseudoReynolds.Evaluate((float)(effSpeed * curDensity));
if (breakDistance == 0) // first term for highest speed
{
breakDistance = (float)vesselState.mass / friction_const * Math.Log(effSpeed) + effSpeed * pt.Value.Item2;
undeployedDistance = effSpeed * pt.Value.Item2;// - vesselState.mass / friction_const ;
maxSpeed = lastSpeed = effSpeed;
totalFriction = friction_const;
//Debug.Log(String.Format("ParachuteInfo.update has first chute type with friction={0:F4} and effSpeed={1:F0}, delay={3:F1} results break dist={2:F0}", friction_const, effSpeed, breakDistance, pt.Value.Item2));
}
else
{
// calculate slowdown during parachute opening using old friction
effSpeed *= (float)vesselState.mass / (totalFriction * pt.Value.Item2 * effSpeed + vesselState.mass);
breakDistance -= (float)vesselState.mass / (totalFriction + friction_const) * friction_const / totalFriction * Math.Log(effSpeed);
undeployedDistance += pt.Value.Item2 * effSpeed;// + vesselState.mass * lastSpeed / (totalFriction * effSpeed) - vesselState.mass / (totalFriction + friction_const);
lastSpeed = effSpeed;
totalFriction += friction_const;
//Debug.Log(String.Format("ParachuteInfo.update has next chute type with friction={0:F4} and effSpeed={1:F0}, delay={3:F1} results break dist={2:F0}", friction_const, effSpeed, breakDistance, pt.Value.Item2));
}
}
if (totalFriction > 0)
{
double terminalSpeed = Math.Sqrt((float)vesselState.mass / totalFriction * vesselState.mainBody.GeeASL * PhysicsGlobals.GravitationalAcceleration);
//we are not getting slower than terminal velocity, so substract this as best guess for integration constant v
breakDistance -= (float)vesselState.mass / totalFriction * Math.Log(terminalSpeed);
//undeployedDistance += vesselState.mass * lastSpeed / (totalFriction * terminalSpeed);
//Debug.Log(String.Format("ParachuteInfo.update has terminal velocity term with friction={0:F4} and terminalSpeed={1:F0} results break dist={2:F0}", totalFriction, terminalSpeed, breakDistance));
}
Debug.Log(String.Format("ParachuteInfo.update for speed={0:F0} gives maxSpeed={1:F0} break dist={2:F0} undeployedDistance={3:F0}", curSpeed, maxSpeed, breakDistance, undeployedDistance));
}
