| activePatch | Orbit | |
| altitude | Orbit | |
| an | Orbit | |
| ApA | Orbit | |
| ApR | Orbit | |
| argumentOfPeriapsis | Orbit | |
| ClAppr | Orbit | |
| ClEctr1 | Orbit | |
| ClEctr2 | Orbit | |
| closestEncounterBody | Orbit | |
| closestEncounterLevel | Orbit | |
| closestEncounterPatch | Orbit | |
| closestTgtApprUT | Orbit | |
| CrAppr | Orbit | |
| debug_returnFullEllipseTrajectory | Orbit | |
| debugAN | Orbit | |
| debugEccVec | Orbit | |
| debugH | Orbit | |
| debugPos | Orbit | |
| debugVel | Orbit | |
| DrawOrbit() | Orbit | |
| E | Orbit | |
| eccentricAnomaly | Orbit | |
| eccentricity | Orbit | |
| eccVec | Orbit | |
| EncounterSolutionLevel enum name | Orbit | |
| EndUT | Orbit | |
| epoch | Orbit | |
| FEVp | Orbit | |
| FEVs | Orbit | |
| FindClosestPoints(Orbit p, Orbit s, ref double CD, ref double CCD, ref double FFp, ref double FFs, ref double SFp, ref double SFs, double epsilon, int maxIterations, ref int iterationCount) | Orbit | static |
| fromE | Orbit | |
| fromV | Orbit | |
| GetANVector() | Orbit | |
| GetDTforTrueAnomaly(double tA, double wrapAfterSeconds) | Orbit | |
| GetEccentricAnomaly(double tA) | Orbit | |
| GetEccVector() | Orbit | |
| GetFrameVel() | Orbit | |
| GetFrameVelAtUT(double UT) | Orbit | |
| GetMeanAnomaly(double E, double tA) | Orbit | |
| getObTAtMeanAnomaly(double M) | Orbit | |
| getObtAtUT(double UT) | Orbit | |
| getOrbitalSpeedAt(double time) | Orbit | |
| getOrbitalSpeedAtDistance(double d) | Orbit | |
| getOrbitalSpeedAtPos(Vector3d pos) | Orbit | |
| getOrbitalSpeedAtRelativePos(Vector3d relPos) | Orbit | |
| getOrbitalVelocityAtObT(double ObT) | Orbit | |
| getOrbitalVelocityAtUT(double UT) | Orbit | |
| GetOrbitNormal() | Orbit | |
| GetPatchTrajectory(int sampleCount) | Orbit | |
| getPositionAtT(double T) | Orbit | |
| getPositionAtUT(double UT) | Orbit | |
| getPositionFromEccAnomaly(double E) | Orbit | |
| getPositionFromMeanAnomaly(double M) | Orbit | |
| getPositionFromTrueAnomaly(double tA) | Orbit | |
| getRelativePositionAtT(double T) | Orbit | |
| getRelativePositionAtUT(double UT) | Orbit | |
| getRelativePositionFromEccAnomaly(double E) | Orbit | |
| getRelativePositionFromMeanAnomaly(double M) | Orbit | |
| getRelativePositionFromTrueAnomaly(double tA) | Orbit | |
| GetRelativeVel() | Orbit | |
| GetRotFrameVel(CelestialBody refBody) | Orbit | |
| getTrueAnomaly(double E) | Orbit | |
| GetTrueAnomalyOfZupVector(Vector3d vector) | Orbit | |
| getTruePositionAtUT(double UT) | Orbit | |
| GetUTforTrueAnomaly(double tA, double wrapAfterSeconds) | Orbit | |
| GetVel() | Orbit | |
| GetWorldSpaceVel() | Orbit | |
| h | Orbit | |
| inclination | Orbit | |
| Init() | Orbit | |
| LAN | Orbit | |
| mag | Orbit | |
| meanAnomaly | Orbit | |
| meanAnomalyAtEpoch | Orbit | |
| nearestTT | Orbit | |
| nextPatch | Orbit | |
| nextTT | Orbit | |
| ObjectType enum name | Orbit | |
| objectType | Orbit | |
| ObT | Orbit | |
| ObTAtEpoch | Orbit | |
| Orbit() | Orbit | |
| Orbit(double inc, double e, double sma, double lan, double w, double mEp, double t, CelestialBody body) | Orbit | |
| orbitalEnergy | Orbit | |
| orbitalSpeed | Orbit | |
| orbitPercent | Orbit | |
| patchEndTransition | Orbit | |
| patchStartTransition | Orbit | |
| PatchTransitionType enum name | Orbit | |
| PeA | Orbit | |
| PeApIntersects(Orbit primary, Orbit secondary, double threshold) | Orbit | static |
| PeR | Orbit | |
| period | Orbit | |
| pos | Orbit | |
| previousPatch | Orbit | |
| radius | Orbit | |
| RadiusAtTrueAnomaly(double tA) | Orbit | |
| referenceBody | Orbit | |
| sampleInterval | Orbit | |
| secondaryPosAtTransition1 | Orbit | |
| secondaryPosAtTransition2 | Orbit | |
| semiLatusRectum | Orbit | |
| semiMajorAxis | Orbit | |
| semiMinorAxis | Orbit | |
| SEVp | Orbit | |
| SEVs | Orbit | |
| SolveClosestApproach(Orbit p, Orbit s, ref double UT, double dT, double threshold, double MinUT, double MaxUT, double epsilon, int maxIterations, ref int iterationCount) | Orbit | static |
| solveEccentricAnomaly(double M, double ecc, double maxError, int maxIterations) | Orbit | |
| SolveSOI_BSP(Orbit p, Orbit s, ref double UT, double dT, double Rsoi, double MinUT, double MaxUT, double epsilon, int maxIterations, ref int iterationCount) | Orbit | static |
| StartUT | Orbit | |
| timeToAp | Orbit | |
| timeToPe | Orbit | |
| timeToTransition1 | Orbit | |
| timeToTransition2 | Orbit | |
| toE | Orbit | |
| toV | Orbit | |
| trueAnomaly | Orbit | |
| TrueAnomalyAtRadius(double R) | Orbit | |
| TrueAnomalyAtT(double T) | Orbit | |
| TrueAnomalyAtUT(double UT) | Orbit | |
| UpdateFromOrbitAtUT(Orbit orbit, double UT, CelestialBody toBody) | Orbit | |
| UpdateFromStateVectors(Vector3d pos, Vector3d vel, CelestialBody refBody, double UT) | Orbit | |
| UpdateFromUT(double UT) | Orbit | |
| UTappr | Orbit | |
| UTsoi | Orbit | |
| V | Orbit | |
| vel | Orbit | |
1.8.7
