public override List <ManeuverParameters> MakeNodesImpl(Orbit o, double UT, MechJebModuleTargetController target)
{
if (!target.NormalTargetExists)
{
throw new OperationException(Localizer.Format("#MechJeb_approach_Exception1"));//must select a target for the course correction.
}
Orbit correctionPatch = o;
while (correctionPatch != null)
{
if (correctionPatch.referenceBody == target.TargetOrbit.referenceBody)
{
o = correctionPatch;
UT = correctionPatch.StartUT;
break;
}
correctionPatch = target.core.vessel.GetNextPatch(correctionPatch);
}
if (correctionPatch == null || correctionPatch.referenceBody != target.TargetOrbit.referenceBody)
{
throw new OperationException(Localizer.Format("#MechJeb_approach_Exception2"));//"target for course correction must be in the same sphere of influence"
}
if (o.NextClosestApproachTime(target.TargetOrbit, UT) < UT + 1 ||
o.NextClosestApproachDistance(target.TargetOrbit, UT) > target.TargetOrbit.semiMajorAxis * 0.2)
{
errorMessage = Localizer.Format("#MechJeb_Approach_errormsg");//Warning: orbit before course correction doesn't seem to approach target very closely. Planned course correction may be extreme. Recommend plotting an approximate intercept orbit and then plotting a course correction.
}
CelestialBody targetBody = target.Target as CelestialBody;
Vector3d dV = targetBody != null?
OrbitalManeuverCalculator.DeltaVAndTimeForCheapestCourseCorrection(o, UT, target.TargetOrbit, targetBody, targetBody.Radius + courseCorrectFinalPeA, out UT) :
OrbitalManeuverCalculator.DeltaVAndTimeForCheapestCourseCorrection(o, UT, target.TargetOrbit, interceptDistance, out UT);
List <ManeuverParameters> NodeList = new List <ManeuverParameters>();
NodeList.Add(new ManeuverParameters(dV, 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);
}
