Difference between revisions of "API:Orbit"
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|name=Orbit | |name=Orbit | ||
|args={{arg|double|inc}},{{arg|double|e}},{{arg|double|sma}},{{arg|double|lan}},{{arg|double|w}},{{arg|double|mEp}},{{arg|double|t}},{{arg|CelestialBody|body}} | |args={{arg|double|inc}},{{arg|double|e}},{{arg|double|sma}},{{arg|double|lan}},{{arg|double|w}},{{arg|double|mEp}},{{arg|double|t}},{{arg|CelestialBody|body}} | ||
| + | |desc="inc" is probably inclination, "e" is probably eccentricity, "sma" is probably semi-major axis, "lan" is probably longitude of the ascending node, "w" is probably the argument of periapsis (omega), and mEp is probably a mean anomaly at some time, like epoch, and t is probably current time, See https://en.wikipedia.org/wiki/Orbital_elements | ||
}} | }} | ||
Latest revision as of 17:32, 22 January 2020
Contents
Properties
The following are public properties available in Orbit.
| Signature | Description |
|---|---|
| double ApA { get; } | Apoapsis altitude, distance from the apoapsis to the surface of the reference body. |
| double ApR { get; } | Apoapsis radius, distance from the apoapsis to the center of the reference body. |
| double PeA { get; } | Periapsis altitude, distance from the periapsis to the surface of the reference body. |
| double PeR { get; } | Periapsis radius, distance from the periapsis to the center of the reference body. |
| double semiLatusRectum { get; } | Semi-latus rectum, half the length of the chord parallel to the directrix through one of the orbit's foci. |
| double semiMinorAxis { get; } | Semi-minor axis, half the length of the shorter axis through the center of the orbit. |
Fields
The following is a list of publically-accessible fields in Orbit. This includes protected items, which can be accessed by subclasses.
| Signature | Description |
|---|---|
| bool activePatch | ? |
| double altitude | Height above the surface of the reference body, including liquid bodies. |
| Vector3d an | ? |
| double argumentOfPeriapsis | Argument of periapsis (degrees) |
| double ClAppr | Presumably the distance to the target at closest approach agnostic of encounters, in meters). |
| double ClEctr1 | presumably as distance to target during the next closest encounter, in meters. |
| double ClEctr2 | Second closest encounter, as an unknown quantity (presumably distance to target, in meters). |
| CelestialBody closestEncounterBody | The next celestial body to be encountered. |
| EncounterSolutionLevel closestEncounterLevel | The type of the next closest encounter, constrained to the values enumerated in EncounterSolutionLevel. |
| Orbit closestEncounterPath | The Orbit around the next celestial body to be encountered. |
| double closestTgtApprUT | The time of the next closest approach, in Universal Time. |
| double crAppr | Unknown type of approach type, presumably distance in meters. |
| bool debug_returnFullEllipseTrajectory | ? |
| Vector3 debugAN | ? |
| Vector3 debugEccVec | ? |
| Vector3 debugH | ? |
| Vector3 debugPos | ? |
| Vector3 debugVel | ? |
| double E | ? |
| double eccentricAnomaly | The eccentric anomaly of the orbit, corresponding to the angle between the periapsis and the current projected position on a circle of radius equal to the semimajor axis. |
| double eccentricity | The eccentricity of the orbit, describing the deviation of the orbit from a perfect circle, from 0 to 1 exclusive for elliptical and 1 to infinity exclusive for hyperbolic (0 being circular and 1 being parabolic) |
| Vector3d eccVec | The eccentricity vector of the orbit, whose magnitude is the eccentricity. |
| double EndUT | ? |
| double epoch | The reference time of the orbit, presumably in Universal Time. |
| double FEVp | ? |
| double FEVs | ? |
| double fromE | ? |
| double fromV | ? |
| Vector3d h | The specific relative angular momentum vector of the orbit in meters squared per second, being specifically relative to the celestial body around which the orbit exists. |
| double inclination | The inclination of the orbit above the reference plane (degrees) |
| double LAN | Longitude of the ascending node (degrees) |
| double mag | ? |
| double meanAnomaly | Current mean anomaly (radians, not an angle) |
| double meanAnomalyAtEpoch | Mean anomaly at epoch (radians, not an angle) |
| double nearestTT | Obsolete, Use VesselType or CelestialBodyType instead. |
| double ObT | ? |
| double ObTAtEpoch | ? |
| double orbitalEnergy | ? |
| double orbitalSpeed | The current orbital speed(m/s). Use Orbit.vel.magnitude to get the actual orbital speed instead. |
| double orbitalPercent | ? |
| PatchTransitionType patchEndTransition | ? |
| PatchTransitionType patchStartTransition | ? |
| double period | ? |
| Vector3d pos | ? |
| Orbit previousPatch | ? |
| double radius | ? |
| CelestialBody referenceBody | CelestialBody around which you are orbiting. |
| double sampleInterval | ? |
| Vector3d secondaryPosAtTransition1 | ? |
| Vector3d secondaryPosAtTransition2 | ? |
| double semiMajorAxis | ? |
| double SEVp | ? |
| double SEVs | ? |
| double StartUT | ? |
| double timeToAp | Time in seconds before reach the apoapsis. |
| double timeToPe | Time in seconds before reach the periapsis. |
| double timeToTransition1 | ? |
| double timeToTransition2 | ? |
| double toE | ? |
| double toV | ? |
| double trueAnomaly | ? |
| double UTappr | ? |
| double UTsoi | ? |
| double V | ? |
| Vector3d vel | Actual orbital velocity (orbital speed). |
Methods
The following are methods included in Orbit.
| Signature | Description |
|---|---|
| static Orbit() | ? |
| public Orbit(double inc,double e,double sma,double lan,double w,double mEp,double t,CelestialBody body) | "inc" is probably inclination, "e" is probably eccentricity, "sma" is probably semi-major axis, "lan" is probably longitude of the ascending node, "w" is probably the argument of periapsis (omega), and mEp is probably a mean anomaly at some time, like epoch, and t is probably current time, See https://en.wikipedia.org/wiki/Orbital_elements |
| void DrawOrbit() | ? |
| static void 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) | ? |
| Vector3d GetANVector() | ? |
| double GetDTforTrueAnomaly(double tA,double wrapAfterSeconds) | ? |
| double GetEccentricAnomaly(double tA) | ? |
| Vector3d GetEccVector() | ? |
| Vector3d GetFrameVel() | ? |
| Vector3d GetFrameVelAtUT(double UT) | ? |
| double GetMeanAnomaly(double E,double tA) | ? |
| double getObTAtMeanAnomaly(double M) | ? |
| double getObtAtUT(double UT) | ? |
| double getOrbitalSpeedAt(double time) | ? |
| double getOrbitalSpeedAtDistance(double d) | ? |
| double getOrbitalSpeedAtPos(Vector3d pos) | ? |
| double getOrbitalSpeedAtRelativePos(Vector3d relPos) | ? |
| Vector3d getOrbitalVelocityAtObT(double ObT) | ? |
| Vector3d getOrbitalVelocityAtUT(double UT) | ? |
| Vector3d GetOrbitNormal()() | ? |
| Trajectory GetPatchTrajectory(int sampleCount) | ? |
| Vector3d getPositionAtT(double T) | ? |
| Vector3d getPositionAtUT(double UT) | ? |
| Vector3d getPositionFromEccAnomaly(double E) | ? |
| Vector3d getPositionFromMeanAnomaly(double M) | ? |
| Vector3d getPositionFromTrueAnomaly(double tA) | ? |
| Vector3d getRelativePositionAtT(double T) | ?
|
| Vector3d getRelativePositionAtUT(double UT) | ?
|
| Vector3d getRelativePositionFromEccAnomaly(double E) | ?
|
| Vector3d getRelativePositionFromMeanAnomaly(double m) | ?
|
| Vector3d getRelativePositionFromTrueAnomaly(double tA) | ?
|
| Vector3d GetRelativeVel() | ?
|
| Vector3d GetRotFrameVel(CelestialBody refBody) | ?
|
| double getTrueAnomaly(double E) | ?
|
| double GetTrueAnomalyOfZupVector(Vector3d vector) | ? |
| Vector3d getTruePositionAtUT(double UT) | ? |
| double GetUTforTrueAnomaly(double tA,double wrapAfterSeconds) | ? |
| Vector3d GetVel() | ? |
| Vector3d GetWorldSpaceVel() | ? |
| static bool PeApIntersects(Orbit primary,Orbit secondary,double threshold) | ? |
| double RadiusAtTrueAnomaly(double tA) | ? |
| static double SolveClosestApproach(Orbit p,Orbit s,ref double UT,double dT,double threshold,double MinUT,double MaxUT,double epsilon,int maxIterations,ref int iterationCount) | ? |
| static double SolveClosestBSP(ref double Fp,ref double Fs,double Ir,double dF,Orbit p,orbit s,double epsilon,int maxIterations,ref int iterationCount) | ? |
| double solveEccentricAnomaly(double M,double ecc,double maxError,int maxIterations) | ? |
| static bool SolveSOI_BSP(Orbit p,Orbit s,ref double UT,double dT,double Rsoi,double MinUT,double MaxUT,double epsilon,int maxIterations,ref int iterationCount) | ? |
| double TrueAnomalyAtRadius(double R) | ? |
| double TrueAnomalyAtT(double T) | ? |
| double TrueAnomalyAtUT(double UT) | ? |
| void UpdateFromOrbitAtUT(Orbit orbit,double UT,CelestialBody toBody) | ? |
| void UpdateFromStateVectors(Vector3d pos,Vector3d vel,CelestialBody refBody,double UT) | ? |
| void UpdateFromUT(double UT) | ? |
Enumerations
public enum EncounterSolutionLevel {
- NONE,
- ESCAPE,
- ORBIT_INTERSECT,
- SOI_INTERSECT_2,
- SOI_INTERSECT_1
}
public enum ObjectType {
- VESSEL,
- SPACE_DEBRIS,
- CELESTIAL_BODIES,
- UNKOWN_MISC,
- KERBAL
}
public enum PatchTransitionType{
- INITIAL,
- FINAL,
- ENCOUNTER,
- ESCAPE,
- MANEUVER
}
Tips
-Use FlightGlobals.ActiveVessel.orbit.ApA to get the actual Apoapsis of the vessel controlled by the player.
-Use FlightGlobals.ActiveVessel.orbit.vel.magnitude to get the actual orbital speed in m/s of the vessel controlled by the player.
