void DriveCircularizationBurn(FlightCtrlState s)
{
if (!vessel.patchedConicsUnlocked() || skipCircularization)
{
this.users.Clear();
return;
}
DriveDeployableComponents(s);
if (placedCircularizeNode)
{
if (vessel.patchedConicSolver.maneuverNodes.Count == 0)
{
MechJebModuleFlightRecorder recorder = core.GetComputerModule <MechJebModuleFlightRecorder>();
if (recorder != null)
{
launchPhaseAngle = recorder.phaseAngleFromMark;
}
if (recorder != null)
{
launchLANDifference = vesselState.orbitLAN - recorder.markLAN;
}
//finished circularize
this.users.Clear();
return;
}
}
else
{
//place circularization node
vessel.RemoveAllManeuverNodes();
double UT = orbit.NextApoapsisTime(vesselState.time);
//During the circularization burn, try to correct any inclination errors because it's better to combine the two burns.
// For example, if you're about to do a 1500 m/s circularization burn, if you combine a 200 m/s inclination correction
// into it, you actually only spend 1513 m/s to execute combined manuver. Mechjeb should also do correction burns before
// this if possible, and this can't correct all errors... but it's better then nothing.
// (A better version of this should try to match inclination & LAN if target is specified)
// FIXME? this inclination correction is unlikely to be at tha AN/DN and will throw the LAN off with anything other than high
// TWR launches from equatorial launch sites -- should probably be made optional (or clip it if the correction is too large).
Vector3d inclinationCorrection = OrbitalManeuverCalculator.DeltaVToChangeInclination(orbit, UT, Math.Abs(desiredInclination));
Vector3d smaCorrection = OrbitalManeuverCalculator.DeltaVForSemiMajorAxis(orbit.PerturbedOrbit(UT, inclinationCorrection), UT,
desiredOrbitAltitude + mainBody.Radius);
Vector3d dV = inclinationCorrection + smaCorrection;
vessel.PlaceManeuverNode(orbit, dV, UT);
placedCircularizeNode = true;
core.node.ExecuteOneNode(this);
}
if (core.node.burnTriggered)
{
status = Localizer.Format("#MechJeb_Ascent_status7"); //"Circularizing"
}
else
{
status = Localizer.Format("#MechJeb_Ascent_status8"); //"Coasting to circularization burn"
}
}
void DriveCircularizationBurn(FlightCtrlState s)
{
if (!vessel.patchedConicsUnlocked() || skipCircularization)
{
this.users.Clear();
return;
}
if (placedCircularizeNode)
{
if (!vessel.patchedConicSolver.maneuverNodes.Any())
{
MechJebModuleFlightRecorder recorder = core.GetComputerModule <MechJebModuleFlightRecorder>();
if (recorder != null)
{
launchPhaseAngle = recorder.phaseAngleFromMark;
}
if (recorder != null)
{
launchLANDifference = vesselState.orbitLAN - recorder.markLAN;
}
//finished circularize
this.users.Clear();
return;
}
}
else
{
//place circularization node
vessel.RemoveAllManeuverNodes();
double UT = orbit.NextApoapsisTime(vesselState.time);
//During the circularization burn, try to correct any inclination errors because it's better to combine the two burns.
// For example, if you're about to do a 1500 m/s circularization burn, if you combine a 200 m/s inclination correction
// into it, you actually only spend 1513 m/s to execute combined manuver. Mechjeb should also do correction burns before
// this if possible, and this can't correct all errors... but it's better then nothing.
// (A better version of this should try to match inclination & LAN if target is specified)
Vector3d inclinationCorrection = OrbitalManeuverCalculator.DeltaVToChangeInclination(orbit, UT, desiredInclination);
Vector3d smaCorrection = OrbitalManeuverCalculator.DeltaVForSemiMajorAxis(orbit.PerturbedOrbit(UT, inclinationCorrection), UT,
desiredOrbitAltitude + mainBody.Radius);
Vector3d dV = inclinationCorrection + smaCorrection;
vessel.PlaceManeuverNode(orbit, dV, UT);
placedCircularizeNode = true;
core.node.ExecuteOneNode(this);
}
if (core.node.burnTriggered)
{
status = "Circularizing";
}
else
{
status = "Coasting to circularization burn";
}
}
public override List <ManeuverParameters> MakeNodesImpl(Orbit o, double universalTime, MechJebModuleTargetController target)
{
double UT = timeSelector.ComputeManeuverTime(o, universalTime, target);
List <ManeuverParameters> NodeList = new List <ManeuverParameters>();
NodeList.Add(new ManeuverParameters(OrbitalManeuverCalculator.DeltaVToChangeInclination(o, UT, newInc), UT));
return(NodeList);
}
void MakeNodeForOperation(Orbit o, double UT)
{
Vector3d dV = Vector3d.zero;
double bodyRadius = o.referenceBody.Radius;
switch (operation)
{
case Operation.CIRCULARIZE:
dV = OrbitalManeuverCalculator.DeltaVToCircularize(o, UT);
break;
case Operation.ELLIPTICIZE:
dV = OrbitalManeuverCalculator.DeltaVToEllipticize(o, UT, newPeA + bodyRadius, newApA + bodyRadius);
break;
case Operation.PERIAPSIS:
dV = OrbitalManeuverCalculator.DeltaVToChangePeriapsis(o, UT, newPeA + bodyRadius);
break;
case Operation.APOAPSIS:
dV = OrbitalManeuverCalculator.DeltaVToChangeApoapsis(o, UT, newApA + bodyRadius);
break;
case Operation.INCLINATION:
dV = OrbitalManeuverCalculator.DeltaVToChangeInclination(o, UT, newInc);
break;
case Operation.PLANE:
if (timeReference == TimeReference.REL_ASCENDING)
{
dV = OrbitalManeuverCalculator.DeltaVAndTimeToMatchPlanesAscending(o, core.target.Orbit, UT, out UT);
}
else
{
dV = OrbitalManeuverCalculator.DeltaVAndTimeToMatchPlanesDescending(o, core.target.Orbit, UT, out UT);
}
break;
case Operation.TRANSFER:
dV = OrbitalManeuverCalculator.DeltaVAndTimeForHohmannTransfer(o, core.target.Orbit, UT, out UT);
break;
case Operation.MOON_RETURN:
dV = OrbitalManeuverCalculator.DeltaVAndTimeForMoonReturnEjection(o, UT, o.referenceBody.referenceBody.Radius + moonReturnAltitude, out UT);
break;
case Operation.COURSE_CORRECTION:
CelestialBody targetBody = core.target.Target as CelestialBody;
if (targetBody != null)
{
dV = OrbitalManeuverCalculator.DeltaVAndTimeForCheapestCourseCorrection(o, UT, core.target.Orbit, targetBody, targetBody.Radius + courseCorrectFinalPeA, out UT);
}
else
{
dV = OrbitalManeuverCalculator.DeltaVAndTimeForCheapestCourseCorrection(o, UT, core.target.Orbit, out UT);
}
break;
case Operation.INTERPLANETARY_TRANSFER:
dV = OrbitalManeuverCalculator.DeltaVAndTimeForInterplanetaryTransferEjection(o, UT, core.target.Orbit, true, out UT);
break;
case Operation.LAMBERT:
dV = OrbitalManeuverCalculator.DeltaVToInterceptAtTime(o, UT, core.target.Orbit, UT + interceptInterval);
break;
case Operation.KILL_RELVEL:
dV = OrbitalManeuverCalculator.DeltaVToMatchVelocities(o, UT, core.target.Orbit);
break;
}
vessel.PlaceManeuverNode(o, dV, UT);
}
void MakeNodeForOperation(Orbit o, double UT, Operation op, double newPeA, double newApA, double newInc, double courseCorrectFinalPeA, double moonReturnAltitude, double interceptInterval)
{
Vector3d dV = Vector3d.zero;
double bodyRadius = o.referenceBody.Radius;
// print(newPeA + " - " + this.newPeA + "\n" +
// newApA + " - " + this.newApA + "\n" +
// newInc + " - " + this.newInc + "\n" +
// courseCorrectFinalPeA + " - " + this.courseCorrectFinalPeA + "\n" +
// moonReturnAltitude + " - " + this.moonReturnAltitude + "\n" +
// interceptInterval + " - " + this.interceptInterval);
switch (op)
{
case Operation.CIRCULARIZE:
dV = OrbitalManeuverCalculator.DeltaVToCircularize(o, UT);
break;
case Operation.ELLIPTICIZE:
dV = OrbitalManeuverCalculator.DeltaVToEllipticize(o, UT, newPeA + bodyRadius, newApA + bodyRadius);
break;
case Operation.PERIAPSIS:
dV = OrbitalManeuverCalculator.DeltaVToChangePeriapsis(o, UT, newPeA + bodyRadius);
break;
case Operation.APOAPSIS:
dV = OrbitalManeuverCalculator.DeltaVToChangeApoapsis(o, UT, newApA + bodyRadius);
break;
case Operation.INCLINATION:
dV = OrbitalManeuverCalculator.DeltaVToChangeInclination(o, UT, newInc);
break;
case Operation.PLANE:
if (timeReference == TimeReference.REL_ASCENDING)
{
dV = OrbitalManeuverCalculator.DeltaVAndTimeToMatchPlanesAscending(o, core.target.TargetOrbit, UT, out UT);
}
else
{
dV = OrbitalManeuverCalculator.DeltaVAndTimeToMatchPlanesDescending(o, core.target.TargetOrbit, UT, out UT);
}
break;
case Operation.TRANSFER:
dV = OrbitalManeuverCalculator.DeltaVAndTimeForHohmannTransfer(o, core.target.TargetOrbit, UT, out UT);
break;
case Operation.MOON_RETURN:
dV = OrbitalManeuverCalculator.DeltaVAndTimeForMoonReturnEjection(o, UT, o.referenceBody.referenceBody.Radius + moonReturnAltitude, out UT);
break;
case Operation.COURSE_CORRECTION:
CelestialBody targetBody = core.target.Target as CelestialBody;
if (targetBody != null)
{
dV = OrbitalManeuverCalculator.DeltaVAndTimeForCheapestCourseCorrection(o, UT, core.target.TargetOrbit, targetBody, targetBody.Radius + courseCorrectFinalPeA, out UT);
}
else
{
dV = OrbitalManeuverCalculator.DeltaVAndTimeForCheapestCourseCorrection(o, UT, core.target.TargetOrbit, interceptDistance, out UT);
}
break;
case Operation.INTERPLANETARY_TRANSFER:
dV = OrbitalManeuverCalculator.DeltaVAndTimeForInterplanetaryTransferEjection(o, UT, core.target.TargetOrbit, true, out UT);
break;
case Operation.LAMBERT:
dV = OrbitalManeuverCalculator.DeltaVToInterceptAtTime(o, UT, core.target.TargetOrbit, UT + interceptInterval);
break;
case Operation.KILL_RELVEL:
dV = OrbitalManeuverCalculator.DeltaVToMatchVelocities(o, UT, core.target.TargetOrbit);
break;
case Operation.RESONANT_ORBIT:
dV = OrbitalManeuverCalculator.DeltaVToResonantOrbit(o, UT, (double)resonanceNumerator.val / resonanceDenominator.val);
break;
case Operation.SEMI_MAJOR:
dV = OrbitalManeuverCalculator.DeltaVForSemiMajorAxis(o, UT, newSMA);
break;
case Operation.LAN:
dV = OrbitalManeuverCalculator.DeltaVToShiftLAN(o, UT, core.target.targetLongitude);
break;
}
vessel.PlaceManeuverNode(o, dV, UT);
}
