Пример #1
0
        public override ManeuverParameters MakeNodeImpl(Orbit o, double universalTime, MechJebModuleTargetController target)
        {
            double UT = timeSelector.ComputeManeuverTime(o, universalTime, target);
            var    dV = OrbitalManeuverCalculator.DeltaVToResonantOrbit(o, UT, (double)resonanceNumerator.val / resonanceDenominator.val);

            return(new ManeuverParameters(dV, UT));
        }
Пример #2
0
        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);
        }