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void | DrawOrbit () |
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void | DrawOrbit (Color color) |
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double | EccentricAnomalyAtObT (double T) |
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double | EccentricAnomalyAtUT (double UT) |
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delegate int | 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) |
| Solves the closest point between two orbits starting from the given initial guess values. Both orbits need to share the same reference body. More...
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Vector3d | GetANVector () |
| Returns an updated ascending node vector (use instead of Orbit.eccVec for non-updating orbits when in a rotating ref frame) More...
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double | GetDTforTrueAnomaly (double tA, double wrapAfterSeconds) |
| Get the time remaining to reach the given true anomaly on this orbit More...
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double | GetDTforTrueAnomalyAtUT (double tA, double UT) |
| Determine time delta to get to the specified true anomaly at the given time. For closed trajectories, the delta is limited to +/- 1/2 period (ie, shorted time delta). If time to return to the specified point is desired, add a period. Open trajectories never return (infinity / 2 == infinity). More...
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double | GetEccentricAnomaly (double tA) |
| Get the Eccentric Anomaly for the given true anomaly More...
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Vector3d | GetEccVector () |
| Returns an updated eccentricity vector (use instead of Orbit.eccVec for non-updating orbits when in a rotating ref frame) More...
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Vector3d | GetFrameVel () |
| get the current total velocity of the orbiting body (relative to the solar system inertial frame) More...
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Vector3d | GetFrameVelAtUT (double UT) |
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double | GetMeanAnomaly (double E) |
| Get the Mean Anomaly for the given Eccentric Anomaly More...
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double | getMeanAnomalyAtUT (double UT) |
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double | GetMeanMotion (double sma) |
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double | GetNextApoapsisTime (double UT) |
| Get the next Apoapsis Time after UT More...
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double | GetNextPeriapsisTime (double UT) |
| Get the next Periapsis Time after UT More...
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double | GetNextTimeOfRadius (double UT, double radius) |
| Get Next Time that Orbit will be at Radius after UT. More...
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double | getObTAtMeanAnomaly (double M) |
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double | getObtAtTrueAnomaly (double tA) |
| Return orbit "time" for the given true anomaly without any time wrapping More...
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double | getObtAtUT (double UT) |
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double | GetOrbitalCurvatureAtTrueAnomaly (double ta) |
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double | getOrbitalSpeedAt (double time) |
| Get the orbital velocity of the object at the specified time (velocity relative to parent body) More...
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double | getOrbitalSpeedAtDistance (double d) |
| Get the orbital velocity of the orbiting object at the specified distance to the body it's orbiting (velocity relative to parent body) More...
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double | getOrbitalSpeedAtPos (Vector3d pos) |
| Get the orbital velocity of the object at the specified global position (velocity relative to parent body) More...
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double | getOrbitalSpeedAtRelativePos (Vector3d relPos) |
| Get the orbital velocity of the object at the specified relative position (velocity relative to parent body) More...
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double | GetOrbitalStateVectorsAtObT (double ObT, double UT, out Vector3d pos, out Vector3d vel) |
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double | GetOrbitalStateVectorsAtObT (double ObT, out State state) |
| Get "full" state vectors for specified orbit "time" (see GetOrbitalStateVectorsAtTrueAnomaly) More...
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double | GetOrbitalStateVectorsAtTrueAnomaly (double tA, double UT, out Vector3d pos, out Vector3d vel) |
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double | GetOrbitalStateVectorsAtTrueAnomaly (double tA, double UT, bool worldToLocal, out Vector3d pos, out Vector3d vel) |
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double | GetOrbitalStateVectorsAtTrueAnomaly (double tA, out State state) |
| Get "full" state vectors for specified true anomaly More...
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double | GetOrbitalStateVectorsAtUT (double UT, out Vector3d pos, out Vector3d vel) |
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double | GetOrbitalStateVectorsAtUT (double UT, out State state) |
| Get "full" state vectors for specified UT (see GetOrbitalStateVectorsAtTrueAnomaly) More...
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Vector3d | getOrbitalVelocityAtObT (double ObT) |
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Vector3d | getOrbitalVelocityAtTrueAnomaly (double tA) |
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Vector3d | getOrbitalVelocityAtTrueAnomaly (double tA, bool worldToLocal) |
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Vector3d | getOrbitalVelocityAtUT (double UT) |
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Vector3d | GetOrbitNormal () |
| Returns an updated orbit normal (use instead of Orbit.h for non-updating orbits when in a rotating ref frame) More...
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Vector3d | getPositionAtT (double T) |
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Vector3d | getPositionAtUT (double UT) |
| Get the position of the orbiting object at the specified Universal Time (relative to the current position of the reference body); More...
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Vector3d | getPositionFromEccAnomaly (double E) |
| Get a global position vector from the given eccentric anomaly angle (in radians) More...
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Vector3d | getPositionFromEccAnomalyWithSemiMinorAxis (double E, double semiMinorAxis) |
| Get a global position vector from the given eccentric anomaly angle (in radians) Version that request semiMinorAxis for faster repeated call More...
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Vector3d | getPositionFromMeanAnomaly (double M) |
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Vector3d | getPositionFromTrueAnomaly (double tA) |
| Get a global position vector from the given true anomaly angle (in radians) More...
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Vector3d | getPositionFromTrueAnomaly (double tA, bool worldToLocal) |
| Get a ref-body-relative position vector from the given true anomaly angle (in radians) More...
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double | GetRadiusAtPhaseAngle (double phaseAngle) |
| Get Radius of the Orbit at a phase angle. More...
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double | GetRadiusAtUT (double time) |
| Get the Radius of the Orbit at a given UT time. More...
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double | GetRelativeInclination (Orbit otherOrbit) |
| Get the relative inclination between this orbit and another orbit. More...
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Vector3d | getRelativePositionAtT (double T) |
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Vector3d | getRelativePositionAtUT (double UT) |
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Vector3d | getRelativePositionFromEccAnomaly (double E) |
| Get a ref-body-relative position vector from the given eccentric anomaly angle (in radians) More...
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Vector3d | getRelativePositionFromEccAnomalyWithSemiMinorAxis (double E, double semiMinorAxis) |
| Get a ref-body-relative position vector from the given eccentric anomaly angle (in radians) Version that request semiMinorAxis for faster repeated call More...
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Vector3d | getRelativePositionFromMeanAnomaly (double M) |
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Vector3d | getRelativePositionFromTrueAnomaly (double tA) |
| Get a ref-body-relative position vector from the given true anomaly angle (in radians) More...
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Vector3d | GetRelativeVel () |
| get the current velocity of the orbiting body (relative to it's central body) More...
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Vector3d | GetRotFrameVel (CelestialBody refBody) |
| get the velocity of the rotating reference frame, when that frame is in use More...
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Vector3d | GetRotFrameVelAtPos (CelestialBody refBody, Vector3d refPos) |
| get the velocity of the rotating reference frame with respect to a given position (when that frame is in use) More...
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double | GetTimeToPeriapsis () |
| Time from StartUT to periapsis on this patch More...
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double | GetTrueAnomaly (double E) |
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double | GetTrueAnomalyOfZupVector (Vector3d vector) |
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Vector3d | getTruePositionAtUT (double UT) |
| Get the position of the orbiting object at the specified Universal Time (relative to the actual position of the reference body at the given UT); More...
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double | getUTAtMeanAnomaly (double M, double UT) |
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double | GetUTforTrueAnomaly (double tA, double wrapAfterSeconds) |
| Get the Universal Time at which this orbit will reach the given true anomaly More...
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Vector3d | GetVel () |
| get the current velocity of the orbiting body (in scene space) More...
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Vector3d | GetWorldSpaceVel () |
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Vector3d | Horizontal (double UT) |
| Return the Horizontal Vector for the orbit at UT. More...
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void | Init () |
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Vector3d | Normal (double UT) |
| Returns the Normal Positive Vector of the orbit at UT. More...
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| Orbit () |
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| Orbit (double inc, double e, double sma, double lan, double argPe, double mEp, double t, CelestialBody body) |
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| Orbit (Orbit orbit) |
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double | PhaseAngle (double time, double longitude) |
| Get the Phase Angle of the Orbit at a given UT time and Longitude. More...
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double | PhaseAngle (double time) |
| Get the Phase Angle of the Orbit at a given UT time. More...
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Vector3d | Prograde (double UT) |
| Return the Prograde Vector of the orbit at UT. More...
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Vector3d | Radial (double UT) |
| Returns the Radial Positive Vector of the orbit at UT. More...
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double | RadiusAtTrueAnomaly (double tA) |
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void | SetOrbit (double inc, double e, double sma, double lan, double argPe, double mEp, double t, CelestialBody body) |
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delegate double | SolveClosestApproachDelegate (Orbit p, Orbit s, ref double UT, double dT, double threshold, double MinUT, double MaxUT, double epsilon, int maxIterations, ref int iterationCount) |
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double | solveEccentricAnomaly (double M, double ecc, double maxError=1e-7, int maxIterations=8) |
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delegate bool | SolveSOI_BSPDelegate (Orbit p, Orbit s, ref double UT, double dT, double Rsoi, double MinUT, double MaxUT, double epsilon, int maxIterations, ref int iterationCount) |
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delegate bool | SolveSOI_Delegate (Orbit p, Orbit s, ref double UT, double dT, double Rsoi, double MinUT, double MaxUT, double epsilon, int maxIterations, ref int iterationCount) |
| Find the time of SoI crossing (entering) More...
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double | TimeOfTrueAnomaly (double tA, double UT) |
| Get the UT for the true anomaly. More...
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double | TrueAnomalyAtRadius (double R) |
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double | TrueAnomalyAtT (double T) |
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double | TrueAnomalyAtUT (double UT) |
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double | TrueAnomalyFromVector (Vector3d vec) |
| Returns the true anomaly from a direction vector. The vector is the angle between the direction vector and the vector pointing to periapsis. More...
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Vector3d | Up (double UT) |
| Return the Up vector of the orbit at UT. More...
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void | UpdateFromFixedVectors (Vector3d pos, Vector3d vel, CelestialBody refBody, double UT) |
| Calculate orbit parameters in the fixed frame rather (ie, pos and vel are in the absolute frame, same as the AN vector) More...
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void | UpdateFromOrbitAtUT (Orbit orbit, double UT, CelestialBody toBody) |
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void | UpdateFromStateVectors (Vector3d pos, Vector3d vel, CelestialBody refBody, double UT) |
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void | UpdateFromUT (double UT) |
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static int | _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) |
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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) |
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static bool | _SolveSOI (Orbit p, Orbit s, ref double UT, double dT, double Rsoi, double MinUT, double MaxUT, double epsilon, int maxIterations, ref int iterationCount) |
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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) |
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static double | AscendingNodeTrueAnomaly (Orbit p, Orbit s) |
| Return the true anomaly in orbit p where it's ascending node crosses orbit s. More...
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static Orbit | CreateRandomOrbitAround (CelestialBody body) |
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static Orbit | CreateRandomOrbitAround (CelestialBody body, double minAltitude, double maxAltitude) |
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static Orbit | CreateRandomOrbitFlyBy (CelestialBody tgtBody, double daysToClosestApproach) |
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static Orbit | CreateRandomOrbitFlyBy (Orbit targetOrbit, double timeToPeriapsis, double periapsis, double deltaVatPeriapsis) |
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static Orbit | CreateRandomOrbitNearby (Orbit baseOrbit) |
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static double | DescendingNodeTrueAnomaly (Orbit p, Orbit s) |
| Return the true anomaly in orbit p where it's descending node crosses orbit s. More...
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static void | 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) |
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static double | NextCloseApproachTime (Orbit p, Orbit s, double UT) |
| Find the UT of close approach between orbits. More...
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static Orbit | OrbitFromStateVectors (Vector3d pos, Vector3d vel, CelestialBody body, double UT) |
| Creates a new Orbit from the passed in state vectors. More...
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static bool | PeApIntersects (Orbit primary, Orbit secondary, double threshold) |
| Tests two orbits to see if they stand any chance of encounter based on their apoapsis and periapsis distances This is the first-stage test. If a pair fails this, it can be ruled out already as the orbits will never meet. Both orbits need to share the same reference body. More...
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static double | RelativeInclination (Orbit p, Orbit s) |
| Return the relative inclination between two orbits. More...
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static double | RelativeStateAtUT (Orbit p, Orbit s, double UT, out State pstate, out State sstate, out State rstate, bool dump=false) |
| Calculates the relative state vectors of the two bodies with the same parent and returns the relative radial velocity (-ve = approaching, +ve = receding) (sort of: r.v, so scaled by distance) More...
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static double | SafeAcos (double c) |
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static Vector3d | Swizzle (Vector3d vec) |
| Swizzles the vector to and from orbital <-> worldspace More...
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static double | SynodicPeriod (Orbit o1, Orbit o2) |
| Find the synodic period for two orbits. +ve if o1.period < o2.period, -ve if o1.period > o2.period. If one orbit is open, use the close orbit's period with appropriate sign (correct for lim p->inf) If both orbits are open, returns NaN. More...
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