public override ManeuverParameters MakeNodeImpl(Orbit o, double UT, MechJebModuleTargetController target) { // Check preconditions if (!target.NormalTargetExists) { throw new Exception("must select a target for the interplanetary transfer."); } if (o.referenceBody.referenceBody == null) { throw new Exception("doesn't make sense to plot an interplanetary transfer from an orbit around " + o.referenceBody.theName + "."); } if (o.referenceBody.referenceBody != target.TargetOrbit.referenceBody) { if (o.referenceBody == target.TargetOrbit.referenceBody) { throw new Exception("use regular Hohmann transfer function to intercept another body orbiting " + o.referenceBody.theName + "."); } throw new Exception("an interplanetary transfer from within " + o.referenceBody.theName + "'s sphere of influence must target a body that orbits " + o.referenceBody.theName + "'s parent, " + o.referenceBody.referenceBody.theName + "."); } // Simple warnings if (o.referenceBody.orbit.RelativeInclination(target.TargetOrbit) > 30) { errorMessage = "Warning: target's orbital plane is at a " + o.RelativeInclination(target.TargetOrbit).ToString("F0") + "º angle to " + o.referenceBody.theName + "'s orbital plane (recommend at most 30º). Planned interplanetary transfer may not intercept target properly."; } else { double relativeInclination = Vector3d.Angle(o.SwappedOrbitNormal(), o.referenceBody.orbit.SwappedOrbitNormal()); if (relativeInclination > 10) { errorMessage = "Warning: Recommend starting interplanetary transfers from " + o.referenceBody.theName + " from an orbit in the same plane as " + o.referenceBody.theName + "'s orbit around " + o.referenceBody.referenceBody.theName + ". Starting orbit around " + o.referenceBody.theName + " is inclined " + relativeInclination.ToString("F1") + "º with respect to " + o.referenceBody.theName + "'s orbit around " + o.referenceBody.referenceBody.theName + " (recommend < 10º). Planned transfer may not intercept target properly."; } else if (o.eccentricity > 0.2) { errorMessage = "Warning: Recommend starting interplanetary transfers from a near-circular orbit (eccentricity < 0.2). Planned transfer is starting from an orbit with eccentricity " + o.eccentricity.ToString("F2") + " and so may not intercept target properly."; } } var dV = OrbitalManeuverCalculator.DeltaVAndTimeForInterplanetaryTransferEjection(o, UT, target.TargetOrbit, waitForPhaseAngle, out UT); return(new ManeuverParameters(dV, UT)); }
public override List <ManeuverParameters> MakeNodesImpl(Orbit o, double UT, MechJebModuleTargetController target) { // Check preconditions if (!target.NormalTargetExists) { throw new OperationException(Localizer.Format("#MechJeb_transfer_Exception1"));//"must select a target for the interplanetary transfer." } if (o.referenceBody.referenceBody == null) { throw new OperationException(Localizer.Format("#MechJeb_transfer_Exception2", o.referenceBody.displayName));//doesn't make sense to plot an interplanetary transfer from an orbit around <<1>> } if (o.referenceBody.referenceBody != target.TargetOrbit.referenceBody) { if (o.referenceBody == target.TargetOrbit.referenceBody) { throw new OperationException(Localizer.Format("#MechJeb_transfer_Exception3", o.referenceBody.displayName)); //use regular Hohmann transfer function to intercept another body orbiting <<1>> } throw new OperationException(Localizer.Format("#MechJeb_transfer_Exception4", o.referenceBody.displayName, o.referenceBody.displayName, o.referenceBody.referenceBody.displayName)); //"an interplanetary transfer from within "<<1>>"'s sphere of influence must target a body that orbits "<<2>>"'s parent, "<<3>>. } // Simple warnings if (o.referenceBody.orbit.RelativeInclination(target.TargetOrbit) > 30) { errorMessage = Localizer.Format("#MechJeb_transfer_errormsg1", o.RelativeInclination(target.TargetOrbit).ToString("F0"), o.referenceBody.displayName);//"Warning: target's orbital plane is at a"<<1>>"º angle to "<<2>>"'s orbital plane (recommend at most 30º). Planned interplanetary transfer may not intercept target properly." } else { double relativeInclination = Vector3d.Angle(o.SwappedOrbitNormal(), o.referenceBody.orbit.SwappedOrbitNormal()); if (relativeInclination > 10) { errorMessage = Localizer.Format("#MechJeb_transfer_errormsg2", o.referenceBody.displayName, o.referenceBody.displayName, o.referenceBody.referenceBody.displayName, o.referenceBody.displayName, relativeInclination.ToString("F1"), o.referenceBody.displayName, o.referenceBody.referenceBody.displayName);//Warning: Recommend starting interplanetary transfers from <<1>> from an orbit in the same plane as "<<2>>"'s orbit around "<<3>>". Starting orbit around "<<4>>" is inclined "<<5>>"º with respect to "<<6>>"'s orbit around "<<7>> " (recommend < 10º). Planned transfer may not intercept target properly." } else if (o.eccentricity > 0.2) { errorMessage = Localizer.Format("#MechJeb_transfer_errormsg3", o.eccentricity.ToString("F2"));//Warning: Recommend starting interplanetary transfers from a near-circular orbit (eccentricity < 0.2). Planned transfer is starting from an orbit with eccentricity <<1>> and so may not intercept target properly. } } var dV = OrbitalManeuverCalculator.DeltaVAndTimeForInterplanetaryTransferEjection(o, UT, target.TargetOrbit, waitForPhaseAngle, 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); }