Kerbal Space Program
1.12.4
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This is the complete list of members for Orbit, including all inherited members.
_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 | inlinestatic |
_SolveClosestApproach(Orbit p, Orbit s, ref double UT, double dT, double threshold, double MinUT, double MaxUT, double epsilon, int maxIterations, ref int iterationCount) | Orbit | inlinestatic |
_SolveSOI(Orbit p, Orbit s, ref double UT, double dT, double Rsoi, double MinUT, double MaxUT, double epsilon, int maxIterations, ref int iterationCount) | Orbit | inlinestatic |
_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 | inlinestatic |
activePatch | Orbit | |
altitude | Orbit | |
ApA | Orbit | |
ApR | Orbit | |
argumentOfPeriapsis | Orbit | |
AscendingNodeTrueAnomaly(Orbit p, Orbit s) | Orbit | inlinestatic |
closestEncounterBody | Orbit | |
closestEncounterLevel | Orbit | |
closestEncounterPatch | Orbit | |
closestTgtApprUT | Orbit | |
CreateRandomOrbitAround(CelestialBody body) | Orbit | inlinestatic |
CreateRandomOrbitAround(CelestialBody body, double minAltitude, double maxAltitude) | Orbit | inlinestatic |
CreateRandomOrbitFlyBy(CelestialBody tgtBody, double daysToClosestApproach) | Orbit | inlinestatic |
CreateRandomOrbitFlyBy(Orbit targetOrbit, double timeToPeriapsis, double periapsis, double deltaVatPeriapsis) | Orbit | inlinestatic |
CreateRandomOrbitNearby(Orbit baseOrbit) | Orbit | inlinestatic |
debug_returnFullEllipseTrajectory | Orbit | |
debugPos | Orbit | |
Deg2Rad | Orbit | |
DescendingNodeTrueAnomaly(Orbit p, Orbit s) | Orbit | inlinestatic |
DrawOrbit() | Orbit | inline |
DrawOrbit(Color color) | Orbit | inline |
eccentricAnomaly | Orbit | |
EccentricAnomalyAtObT(double T) | Orbit | inline |
EccentricAnomalyAtUT(double UT) | Orbit | inline |
eccentricity | Orbit | |
EncounterSolutionLevel enum name | Orbit | |
EndUT | Orbit | |
epoch | Orbit | |
FEVp | Orbit | |
FindClosestPoints | Orbit | static |
FindClosestPoints_old(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 | inlinestatic |
FindClosestPointsDelegate(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 | |
fromE | Orbit | |
GetANVector() | Orbit | inline |
GetDTforTrueAnomaly(double tA, double wrapAfterSeconds) | Orbit | inline |
GetDTforTrueAnomalyAtUT(double tA, double UT) | Orbit | inline |
GetEccentricAnomaly(double tA) | Orbit | inline |
GetEccVector() | Orbit | inline |
GetFrameVel() | Orbit | inline |
GetFrameVelAtUT(double UT) | Orbit | inline |
GetMeanAnomaly(double E) | Orbit | inline |
getMeanAnomalyAtUT(double UT) | Orbit | inline |
GetMeanMotion(double sma) | Orbit | inline |
GetNextApoapsisTime(double UT) | Orbit | inline |
GetNextPeriapsisTime(double UT) | Orbit | inline |
GetNextTimeOfRadius(double UT, double radius) | Orbit | inline |
getObTAtMeanAnomaly(double M) | Orbit | inline |
getObtAtTrueAnomaly(double tA) | Orbit | inline |
getObtAtUT(double UT) | Orbit | inline |
GetOrbitalCurvatureAtTrueAnomaly(double ta) | Orbit | inline |
getOrbitalSpeedAt(double time) | Orbit | inline |
getOrbitalSpeedAtDistance(double d) | Orbit | inline |
getOrbitalSpeedAtPos(Vector3d pos) | Orbit | inline |
getOrbitalSpeedAtRelativePos(Vector3d relPos) | Orbit | inline |
GetOrbitalStateVectorsAtObT(double ObT, double UT, out Vector3d pos, out Vector3d vel) | Orbit | inline |
GetOrbitalStateVectorsAtObT(double ObT, out State state) | Orbit | inline |
GetOrbitalStateVectorsAtTrueAnomaly(double tA, double UT, out Vector3d pos, out Vector3d vel) | Orbit | inline |
GetOrbitalStateVectorsAtTrueAnomaly(double tA, double UT, bool worldToLocal, out Vector3d pos, out Vector3d vel) | Orbit | inline |
GetOrbitalStateVectorsAtTrueAnomaly(double tA, out State state) | Orbit | inline |
GetOrbitalStateVectorsAtUT(double UT, out Vector3d pos, out Vector3d vel) | Orbit | inline |
GetOrbitalStateVectorsAtUT(double UT, out State state) | Orbit | inline |
getOrbitalVelocityAtObT(double ObT) | Orbit | inline |
getOrbitalVelocityAtTrueAnomaly(double tA) | Orbit | inline |
getOrbitalVelocityAtTrueAnomaly(double tA, bool worldToLocal) | Orbit | inline |
getOrbitalVelocityAtUT(double UT) | Orbit | inline |
GetOrbitNormal() | Orbit | inline |
getPositionAtT(double T) | Orbit | inline |
getPositionAtUT(double UT) | Orbit | inline |
getPositionFromEccAnomaly(double E) | Orbit | inline |
getPositionFromEccAnomalyWithSemiMinorAxis(double E, double semiMinorAxis) | Orbit | inline |
getPositionFromMeanAnomaly(double M) | Orbit | inline |
getPositionFromTrueAnomaly(double tA) | Orbit | inline |
getPositionFromTrueAnomaly(double tA, bool worldToLocal) | Orbit | inline |
GetRadiusAtPhaseAngle(double phaseAngle) | Orbit | inline |
GetRadiusAtUT(double time) | Orbit | inline |
GetRelativeInclination(Orbit otherOrbit) | Orbit | inline |
getRelativePositionAtT(double T) | Orbit | inline |
getRelativePositionAtUT(double UT) | Orbit | inline |
getRelativePositionFromEccAnomaly(double E) | Orbit | inline |
getRelativePositionFromEccAnomalyWithSemiMinorAxis(double E, double semiMinorAxis) | Orbit | inline |
getRelativePositionFromMeanAnomaly(double M) | Orbit | inline |
getRelativePositionFromTrueAnomaly(double tA) | Orbit | inline |
GetRelativeVel() | Orbit | inline |
GetRotFrameVel(CelestialBody refBody) | Orbit | inline |
GetRotFrameVelAtPos(CelestialBody refBody, Vector3d refPos) | Orbit | inline |
GetTimeToPeriapsis() | Orbit | inline |
GetTrueAnomaly(double E) | Orbit | inline |
GetTrueAnomalyOfZupVector(Vector3d vector) | Orbit | inline |
getTruePositionAtUT(double UT) | Orbit | inline |
getUTAtMeanAnomaly(double M, double UT) | Orbit | inline |
GetUTforTrueAnomaly(double tA, double wrapAfterSeconds) | Orbit | inline |
GetVel() | Orbit | inline |
GetWorldSpaceVel() | Orbit | inline |
h | Orbit | |
Horizontal(double UT) | Orbit | inline |
inclination | Orbit | |
Init() | Orbit | inline |
LAN | Orbit | |
mag | Orbit | |
meanAnomaly | Orbit | |
meanAnomalyAtEpoch | Orbit | |
meanMotion | Orbit | |
NextCloseApproachTime(Orbit p, Orbit s, double UT) | Orbit | inlinestatic |
nextPatch | Orbit | |
Normal(double UT) | Orbit | inline |
numClosePoints | Orbit | |
ObjectType enum name | Orbit | |
objectType | Orbit | |
ObT | Orbit | |
ObTAtEpoch | Orbit | |
Orbit() | Orbit | inline |
Orbit(double inc, double e, double sma, double lan, double argPe, double mEp, double t, CelestialBody body) | Orbit | inline |
Orbit(Orbit orbit) | Orbit | inline |
orbitalEnergy | Orbit | |
orbitalSpeed | Orbit | |
OrbitFrame | Orbit | |
OrbitFrameX | Orbit | |
OrbitFromStateVectors(Vector3d pos, Vector3d vel, CelestialBody body, double UT) | Orbit | inlinestatic |
orbitPercent | Orbit | |
patchEndTransition | Orbit | |
patchStartTransition | Orbit | |
PatchTransitionType enum name | Orbit | |
PeA | Orbit | |
PeApIntersects(Orbit primary, Orbit secondary, double threshold) | Orbit | inlinestatic |
PeR | Orbit | |
period | Orbit | |
PhaseAngle(double time, double longitude) | Orbit | inline |
PhaseAngle(double time) | Orbit | inline |
pos | Orbit | |
Prograde(double UT) | Orbit | inline |
Rad2Deg | Orbit | |
Radial(double UT) | Orbit | inline |
radius | Orbit | |
RadiusAtTrueAnomaly(double tA) | Orbit | inline |
referenceBody | Orbit | |
RelativeInclination(Orbit p, Orbit s) | Orbit | inlinestatic |
RelativeStateAtUT(Orbit p, Orbit s, double UT, out State pstate, out State sstate, out State rstate, bool dump=false) | Orbit | inlinestatic |
SafeAcos(double c) | Orbit | inlinestatic |
secondaryPosAtTransition1 | Orbit | |
semiLatusRectum | Orbit | |
semiMajorAxis | Orbit | |
semiMinorAxis | Orbit | |
SetOrbit(double inc, double e, double sma, double lan, double argPe, double mEp, double t, CelestialBody body) | Orbit | inline |
SolveClosestApproach | Orbit | static |
SolveClosestApproachDelegate(Orbit p, Orbit s, ref double UT, double dT, double threshold, double MinUT, double MaxUT, double epsilon, int maxIterations, ref int iterationCount) | Orbit | |
solveEccentricAnomaly(double M, double ecc, double maxError=1e-7, int maxIterations=8) | Orbit | inline |
SolveSOI | Orbit | static |
SolveSOI_BSP | Orbit | static |
SolveSOI_BSPDelegate(Orbit p, Orbit s, ref double UT, double dT, double Rsoi, double MinUT, double MaxUT, double epsilon, int maxIterations, ref int iterationCount) | Orbit | |
SolveSOI_Delegate(Orbit p, Orbit s, ref double UT, double dT, double Rsoi, double MinUT, double MaxUT, double epsilon, int maxIterations, ref int iterationCount) | Orbit | |
StartUT | Orbit | |
Swizzle(Vector3d vec) | Orbit | inlinestatic |
SynodicPeriod(Orbit o1, Orbit o2) | Orbit | inlinestatic |
TimeOfTrueAnomaly(double tA, double UT) | Orbit | inline |
timeToAp | Orbit | |
timeToPe | Orbit | |
timeToTransition1 | Orbit | |
trueAnomaly | Orbit | |
TrueAnomalyAtRadius(double R) | Orbit | inline |
TrueAnomalyAtT(double T) | Orbit | inline |
TrueAnomalyAtUT(double UT) | Orbit | inline |
TrueAnomalyFromVector(Vector3d vec) | Orbit | inline |
Up(double UT) | Orbit | inline |
UpdateFromFixedVectors(Vector3d pos, Vector3d vel, CelestialBody refBody, double UT) | Orbit | inline |
UpdateFromOrbitAtUT(Orbit orbit, double UT, CelestialBody toBody) | Orbit | inline |
UpdateFromStateVectors(Vector3d pos, Vector3d vel, CelestialBody refBody, double UT) | Orbit | inline |
UpdateFromUT(double UT) | Orbit | inline |