KeplerianOrbit (ORbit Extrapolation KIT 9.2 API)

java.lang.Object
- org.orekit.orbits.Orbit
- - org.orekit.orbits.KeplerianOrbit

All Implemented Interfaces:

Serializable, TimeInterpolable<Orbit>, TimeShiftable<Orbit>, TimeStamped, PVCoordinatesProvider
```
public class KeplerianOrbit
extends Orbit
```
This class handles traditional Keplerian orbital parameters.
The parameters used internally are the classical Keplerian elements:
```
     a
     e
     i
     ω
     Ω
     v
   
```
where ω stands for the Perigee Argument, Ω stands for the Right Ascension of the Ascending Node and v stands for the true anomaly.
This class supports hyperbolic orbits, using the convention that semi major axis is negative for such orbits (and of course eccentricity is greater than 1).

When orbit is either equatorial or circular, some Keplerian elements (more precisely ω and Ω) become ambiguous so this class should not be used for such orbits. For this reason, equinoctial orbits is the recommended way to represent orbits.

The instance KeplerianOrbit is guaranteed to be immutable.
Author:

Luc Maisonobe, Guylaine Prat, Fabien Maussion, Véronique Pommier-Maurussane

See Also:

Orbit, CircularOrbit, CartesianOrbit, EquinoctialOrbit, Serialized Form

Constructor Summary

Constructors
Constructor	Description
`KeplerianOrbit(double a, double e, double i, double pa, double raan, double anomaly, double aDot, double eDot, double iDot, double paDot, double raanDot, double anomalyDot, PositionAngle type, Frame frame, AbsoluteDate date, double mu)`	Creates a new instance.
`KeplerianOrbit(double a, double e, double i, double pa, double raan, double anomaly, PositionAngle type, Frame frame, AbsoluteDate date, double mu)`	Creates a new instance.
`KeplerianOrbit(Orbit op)`	Constructor from any kind of orbital parameters.
`KeplerianOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu)`	Constructor from Cartesian parameters.
`KeplerianOrbit(TimeStampedPVCoordinates pvCoordinates, Frame frame, double mu)`	Constructor from Cartesian parameters.

Method Summary

All Methods Static Methods Instance Methods Concrete Methods
Modifier and Type	Method	Description
`void`	`addKeplerContribution(PositionAngle type, double gm, double[] pDot)`	Add the contribution of the Keplerian motion to parameters derivatives
`protected double[][]`	`computeJacobianEccentricWrtCartesian()`	Compute the Jacobian of the orbital parameters with eccentric angle with respect to the Cartesian parameters.
`protected double[][]`	`computeJacobianMeanWrtCartesian()`	Compute the Jacobian of the orbital parameters with mean angle with respect to the Cartesian parameters.
`protected double[][]`	`computeJacobianTrueWrtCartesian()`	Compute the Jacobian of the orbital parameters with true angle with respect to the Cartesian parameters.
`static double`	`ellipticEccentricToMean(double E, double e)`	Computes the mean anomaly from the elliptic eccentric anomaly.
`static double`	`ellipticEccentricToTrue(double E, double e)`	Computes the true anomaly from the elliptic eccentric anomaly.
`double`	`getA()`	Get the semi-major axis.
`double`	`getADot()`	Get the semi-major axis derivative.
`double`	`getAnomaly(PositionAngle type)`	Get the anomaly.
`double`	`getAnomalyDot(PositionAngle type)`	Get the anomaly derivative.
`double`	`getE()`	Get the eccentricity.
`double`	`getEccentricAnomaly()`	Get the eccentric anomaly.
`double`	`getEccentricAnomalyDot()`	Get the eccentric anomaly derivative.
`double`	`getEDot()`	Get the eccentricity derivative.
`double`	`getEquinoctialEx()`	Get the first component of the equinoctial eccentricity vector derivative.
`double`	`getEquinoctialExDot()`	Get the first component of the equinoctial eccentricity vector.
`double`	`getEquinoctialEy()`	Get the second component of the equinoctial eccentricity vector derivative.
`double`	`getEquinoctialEyDot()`	Get the second component of the equinoctial eccentricity vector.
`double`	`getHx()`	Get the first component of the inclination vector.
`double`	`getHxDot()`	Get the first component of the inclination vector derivative.
`double`	`getHy()`	Get the second component of the inclination vector.
`double`	`getHyDot()`	Get the second component of the inclination vector derivative.
`double`	`getI()`	Get the inclination.
`double`	`getIDot()`	Get the inclination derivative.
`double`	`getLE()`	Get the eccentric longitude argument.
`double`	`getLEDot()`	Get the eccentric longitude argument derivative.
`double`	`getLM()`	Get the mean longitude argument.
`double`	`getLMDot()`	Get the mean longitude argument derivative.
`double`	`getLv()`	Get the true longitude argument.
`double`	`getLvDot()`	Get the true longitude argument derivative.
`double`	`getMeanAnomaly()`	Get the mean anomaly.
`double`	`getMeanAnomalyDot()`	Get the mean anomaly derivative.
`double`	`getPerigeeArgument()`	Get the perigee argument.
`double`	`getPerigeeArgumentDot()`	Get the perigee argument derivative.
`double`	`getRightAscensionOfAscendingNode()`	Get the right ascension of the ascending node.
`double`	`getRightAscensionOfAscendingNodeDot()`	Get the right ascension of the ascending node derivative.
`double`	`getTrueAnomaly()`	Get the true anomaly.
`double`	`getTrueAnomalyDot()`	Get the true anomaly derivative.
`OrbitType`	`getType()`	Get the orbit type.
`static double`	`hyperbolicEccentricToMean(double H, double e)`	Computes the mean anomaly from the hyperbolic eccentric anomaly.
`static double`	`hyperbolicEccentricToTrue(double H, double e)`	Computes the true anomaly from the hyperbolic eccentric anomaly.
`protected TimeStampedPVCoordinates`	`initPVCoordinates()`	Compute the position/velocity coordinates from the canonical parameters.
`KeplerianOrbit`	`interpolate(AbsoluteDate date, Stream<Orbit> sample)`	Get an interpolated instance.
`static double`	`meanToEllipticEccentric(double M, double e)`	Computes the elliptic eccentric anomaly from the mean anomaly.
`static double`	`meanToHyperbolicEccentric(double M, double ecc)`	Computes the hyperbolic eccentric anomaly from the mean anomaly.
`KeplerianOrbit`	`shiftedBy(double dt)`	Get a time-shifted orbit.
`String`	`toString()`	Returns a string representation of this Keplerian parameters object.
`static double`	`trueToEllipticEccentric(double v, double e)`	Computes the elliptic eccentric anomaly from the true anomaly.
`static double`	`trueToHyperbolicEccentric(double v, double e)`	Computes the hyperbolic eccentric anomaly from the true anomaly.

Methods inherited from class java.lang.Object
clone, equals, finalize, getClass, hashCode, notify, notifyAll, wait, wait, wait

Methods inherited from class org.orekit.orbits.Orbit
fillHalfRow, fillHalfRow, fillHalfRow, fillHalfRow, fillHalfRow, fillHalfRow, getDate, getFrame, getJacobianWrtCartesian, getJacobianWrtParameters, getKeplerianMeanMotion, getKeplerianPeriod, getMu, getPVCoordinates, getPVCoordinates, getPVCoordinates, hasDerivatives, hasNonKeplerianAcceleration

Methods inherited from interface org.orekit.time.TimeInterpolable
interpolate

- Constructor Detail
  - KeplerianOrbit
```
public KeplerianOrbit(double a,
                      double e,
                      double i,
                      double pa,
                      double raan,
                      double anomaly,
                      PositionAngle type,
                      Frame frame,
                      AbsoluteDate date,
                      double mu)
               throws IllegalArgumentException
```
    Creates a new instance.
    
    Parameters:
    
    a - semi-major axis (m), negative for hyperbolic orbits
    
    e - eccentricity
    
    i - inclination (rad)
    
    pa - perigee argument (ω, rad)
    
    raan - right ascension of ascending node (Ω, rad)
    
    anomaly - mean, eccentric or true anomaly (rad)
    
    type - type of anomaly
    
    frame - the frame in which the parameters are defined (must be a pseudo-inertial frame)
    
    date - date of the orbital parameters
    
    mu - central attraction coefficient (m³/s²)
    
    Throws:
    
    IllegalArgumentException - if frame is not a pseudo-inertial frame or a and e don't match for hyperbolic orbits, or v is out of range for hyperbolic orbits
  - KeplerianOrbit
```
public KeplerianOrbit(double a,
                      double e,
                      double i,
                      double pa,
                      double raan,
                      double anomaly,
                      double aDot,
                      double eDot,
                      double iDot,
                      double paDot,
                      double raanDot,
                      double anomalyDot,
                      PositionAngle type,
                      Frame frame,
                      AbsoluteDate date,
                      double mu)
               throws IllegalArgumentException
```
    Creates a new instance.
    
    Parameters:
    
    a - semi-major axis (m), negative for hyperbolic orbits
    
    e - eccentricity
    
    i - inclination (rad)
    
    pa - perigee argument (ω, rad)
    
    raan - right ascension of ascending node (Ω, rad)
    
    anomaly - mean, eccentric or true anomaly (rad)
    
    aDot - semi-major axis derivative (m/s)
    
    eDot - eccentricity derivative
    
    iDot - inclination derivative (rad/s)
    
    paDot - perigee argument derivative (rad/s)
    
    raanDot - right ascension of ascending node derivative (rad/s)
    
    anomalyDot - mean, eccentric or true anomaly derivative (rad/s)
    
    type - type of anomaly
    
    frame - the frame in which the parameters are defined (must be a pseudo-inertial frame)
    
    date - date of the orbital parameters
    
    mu - central attraction coefficient (m³/s²)
    
    Throws:
    
    IllegalArgumentException - if frame is not a pseudo-inertial frame or a and e don't match for hyperbolic orbits, or v is out of range for hyperbolic orbits
    
    Since:
    
    9.0
  - KeplerianOrbit
```
public KeplerianOrbit(TimeStampedPVCoordinates pvCoordinates,
                      Frame frame,
                      double mu)
               throws IllegalArgumentException
```
    Constructor from Cartesian parameters.
    The acceleration provided in pvCoordinates is accessible using Orbit.getPVCoordinates() and Orbit.getPVCoordinates(Frame). All other methods use mu and the position to compute the acceleration, including shiftedBy(double) and Orbit.getPVCoordinates(AbsoluteDate, Frame).
    
    Parameters:
    
    pvCoordinates - the PVCoordinates of the satellite
    
    frame - the frame in which are defined the PVCoordinates (must be a pseudo-inertial frame)
    
    mu - central attraction coefficient (m³/s²)
    
    Throws:
    
    IllegalArgumentException - if frame is not a pseudo-inertial frame
  - KeplerianOrbit
```
public KeplerianOrbit(PVCoordinates pvCoordinates,
                      Frame frame,
                      AbsoluteDate date,
                      double mu)
               throws IllegalArgumentException
```
    Constructor from Cartesian parameters.
    The acceleration provided in pvCoordinates is accessible using Orbit.getPVCoordinates() and Orbit.getPVCoordinates(Frame). All other methods use mu and the position to compute the acceleration, including shiftedBy(double) and Orbit.getPVCoordinates(AbsoluteDate, Frame).
    
    Parameters:
    
    pvCoordinates - the PVCoordinates of the satellite
    
    frame - the frame in which are defined the PVCoordinates (must be a pseudo-inertial frame)
    
    date - date of the orbital parameters
    
    mu - central attraction coefficient (m³/s²)
    
    Throws:
    
    IllegalArgumentException - if frame is not a pseudo-inertial frame
  - KeplerianOrbit
```
public KeplerianOrbit(Orbit op)
```
    Constructor from any kind of orbital parameters.
    
    Parameters:
    
    op - orbital parameters to copy
- Method Detail
  - getType
```
public OrbitType getType()
```
    Get the orbit type.
    
    Specified by:
    
    getType in class Orbit
    
    Returns:
    
    orbit type
  - getA
```
public double getA()
```
    Get the semi-major axis.
    Note that the semi-major axis is considered negative for hyperbolic orbits.
    
    Specified by:
    
    getA in class Orbit
    
    Returns:
    
    semi-major axis (m)
  - getADot
```
public double getADot()
```
    Get the semi-major axis derivative.
    Note that the semi-major axis is considered negative for hyperbolic orbits.
    
    If the orbit was created without derivatives, the value returned is Double.NaN.
    
    Specified by:
    
    getADot in class Orbit
    
    Returns:
    
    semi-major axis derivative (m/s)
    
    See Also:
    
    Orbit.hasDerivatives()
  - getE
```
public double getE()
```
    Get the eccentricity.
    
    Specified by:
    
    getE in class Orbit
    
    Returns:
    
    eccentricity
  - getEDot
```
public double getEDot()
```
    Get the eccentricity derivative.
    If the orbit was created without derivatives, the value returned is Double.NaN.
    
    Specified by:
    
    getEDot in class Orbit
    
    Returns:
    
    eccentricity derivative
    
    See Also:
    
    Orbit.hasDerivatives()
  - getI
```
public double getI()
```
    Get the inclination.
    
    Specified by:
    
    getI in class Orbit
    
    Returns:
    
    inclination (rad)
  - getIDot
```
public double getIDot()
```
    Get the inclination derivative.
    If the orbit was created without derivatives, the value returned is Double.NaN.
    
    Specified by:
    
    getIDot in class Orbit
    
    Returns:
    
    inclination derivative (rad/s)
    
    See Also:
    
    Orbit.hasDerivatives()
  - getPerigeeArgument
```
public double getPerigeeArgument()
```
    Get the perigee argument.
    
    Returns:
    
    perigee argument (rad)
  - getPerigeeArgumentDot
```
public double getPerigeeArgumentDot()
```
    Get the perigee argument derivative.
    If the orbit was created without derivatives, the value returned is Double.NaN.
    
    Returns:
    
    perigee argument derivative (rad/s)
    
    Since:
    
    9.0
  - getRightAscensionOfAscendingNode
```
public double getRightAscensionOfAscendingNode()
```
    Get the right ascension of the ascending node.
    
    Returns:
    
    right ascension of the ascending node (rad)
  - getRightAscensionOfAscendingNodeDot
```
public double getRightAscensionOfAscendingNodeDot()
```
    Get the right ascension of the ascending node derivative.
    If the orbit was created without derivatives, the value returned is Double.NaN.
    
    Returns:
    
    right ascension of the ascending node derivative (rad/s)
    
    Since:
    
    9.0
  - getTrueAnomaly
```
public double getTrueAnomaly()
```
    Get the true anomaly.
    
    Returns:
    
    true anomaly (rad)
  - getTrueAnomalyDot
```
public double getTrueAnomalyDot()
```
    Get the true anomaly derivative.
    
    Returns:
    
    true anomaly derivative (rad/s)
  - getEccentricAnomaly
```
public double getEccentricAnomaly()
```
    Get the eccentric anomaly.
    
    Returns:
    
    eccentric anomaly (rad)
  - getEccentricAnomalyDot
```
public double getEccentricAnomalyDot()
```
    Get the eccentric anomaly derivative.
    
    Returns:
    
    eccentric anomaly derivative (rad/s)
    
    Since:
    
    9.0
  - getMeanAnomaly
```
public double getMeanAnomaly()
```
    Get the mean anomaly.
    
    Returns:
    
    mean anomaly (rad)
  - getMeanAnomalyDot
```
public double getMeanAnomalyDot()
```
    Get the mean anomaly derivative.
    
    Returns:
    
    mean anomaly derivative (rad/s)
    
    Since:
    
    9.0
  - getAnomaly
```
public double getAnomaly(PositionAngle type)
```
    Get the anomaly.
    
    Parameters:
    
    type - type of the angle
    
    Returns:
    
    anomaly (rad)
  - getAnomalyDot
```
public double getAnomalyDot(PositionAngle type)
```
    Get the anomaly derivative.
    
    Parameters:
    
    type - type of the angle
    
    Returns:
    
    anomaly derivative (rad/s)
    
    Since:
    
    9.0
  - ellipticEccentricToTrue
```
public static double ellipticEccentricToTrue(double E,
                                             double e)
```
    Computes the true anomaly from the elliptic eccentric anomaly.
    
    Parameters:
    
    E - eccentric anomaly (rad)
    
    e - eccentricity
    
    Returns:
    
    v the true anomaly
    
    Since:
    
    9.0
  - trueToEllipticEccentric
```
public static double trueToEllipticEccentric(double v,
                                             double e)
```
    Computes the elliptic eccentric anomaly from the true anomaly.
    
    Parameters:
    
    v - true anomaly (rad)
    
    e - eccentricity
    
    Returns:
    
    E the elliptic eccentric anomaly
    
    Since:
    
    9.0
  - hyperbolicEccentricToTrue
```
public static double hyperbolicEccentricToTrue(double H,
                                               double e)
```
    Computes the true anomaly from the hyperbolic eccentric anomaly.
    
    Parameters:
    
    H - hyperbolic eccentric anomaly (rad)
    
    e - eccentricity
    
    Returns:
    
    v the true anomaly
  - trueToHyperbolicEccentric
```
public static double trueToHyperbolicEccentric(double v,
                                               double e)
```
    Computes the hyperbolic eccentric anomaly from the true anomaly.
    
    Parameters:
    
    v - true anomaly (rad)
    
    e - eccentricity
    
    Returns:
    
    H the hyperbolic eccentric anomaly
    
    Since:
    
    9.0
  - meanToEllipticEccentric
```
public static double meanToEllipticEccentric(double M,
                                             double e)
```
    Computes the elliptic eccentric anomaly from the mean anomaly.
    The algorithm used here for solving Kepler equation has been published in: "Procedures for solving Kepler's Equation", A. W. Odell and R. H. Gooding, Celestial Mechanics 38 (1986) 307-334
    
    Parameters:
    
    M - mean anomaly (rad)
    
    e - eccentricity
    
    Returns:
    
    E the eccentric anomaly
  - meanToHyperbolicEccentric
```
public static double meanToHyperbolicEccentric(double M,
                                               double ecc)
```
    Computes the hyperbolic eccentric anomaly from the mean anomaly.
    The algorithm used here for solving hyperbolic Kepler equation is Danby's iterative method (3rd order) with Vallado's initial guess.
    
    Parameters:
    
    M - mean anomaly (rad)
    
    ecc - eccentricity
    
    Returns:
    
    H the hyperbolic eccentric anomaly
  - ellipticEccentricToMean
```
public static double ellipticEccentricToMean(double E,
                                             double e)
```
    Computes the mean anomaly from the elliptic eccentric anomaly.
    
    Parameters:
    
    E - eccentric anomaly (rad)
    
    e - eccentricity
    
    Returns:
    
    M the mean anomaly
    
    Since:
    
    9.0
  - hyperbolicEccentricToMean
```
public static double hyperbolicEccentricToMean(double H,
                                               double e)
```
    Computes the mean anomaly from the hyperbolic eccentric anomaly.
    
    Parameters:
    
    H - hyperbolic eccentric anomaly (rad)
    
    e - eccentricity
    
    Returns:
    
    M the mean anomaly
    
    Since:
    
    9.0
  - getEquinoctialEx
```
public double getEquinoctialEx()
```
    Get the first component of the equinoctial eccentricity vector derivative.
    
    Specified by:
    
    getEquinoctialEx in class Orbit
    
    Returns:
    
    first component of the equinoctial eccentricity vector derivative
  - getEquinoctialExDot
```
public double getEquinoctialExDot()
```
    Get the first component of the equinoctial eccentricity vector.
    If the orbit was created without derivatives, the value returned is Double.NaN.
    
    Specified by:
    
    getEquinoctialExDot in class Orbit
    
    Returns:
    
    first component of the equinoctial eccentricity vector
    
    See Also:
    
    Orbit.hasDerivatives()
  - getEquinoctialEy
```
public double getEquinoctialEy()
```
    Get the second component of the equinoctial eccentricity vector derivative.
    
    Specified by:
    
    getEquinoctialEy in class Orbit
    
    Returns:
    
    second component of the equinoctial eccentricity vector derivative
  - getEquinoctialEyDot
```
public double getEquinoctialEyDot()
```
    Get the second component of the equinoctial eccentricity vector.
    If the orbit was created without derivatives, the value returned is Double.NaN.
    
    Specified by:
    
    getEquinoctialEyDot in class Orbit
    
    Returns:
    
    second component of the equinoctial eccentricity vector
    
    See Also:
    
    Orbit.hasDerivatives()
  - getHx
```
public double getHx()
```
    Get the first component of the inclination vector.
    
    Specified by:
    
    getHx in class Orbit
    
    Returns:
    
    first component of the inclination vector
  - getHxDot
```
public double getHxDot()
```
    Get the first component of the inclination vector derivative.
    If the orbit was created without derivatives, the value returned is Double.NaN.
    
    Specified by:
    
    getHxDot in class Orbit
    
    Returns:
    
    first component of the inclination vector derivative
    
    See Also:
    
    Orbit.hasDerivatives()
  - getHy
```
public double getHy()
```
    Get the second component of the inclination vector.
    
    Specified by:
    
    getHy in class Orbit
    
    Returns:
    
    second component of the inclination vector
  - getHyDot
```
public double getHyDot()
```
    Get the second component of the inclination vector derivative.
    If the orbit was created without derivatives, the value returned is Double.NaN.
    
    Specified by:
    
    getHyDot in class Orbit
    
    Returns:
    
    second component of the inclination vector derivative
    
    See Also:
    
    Orbit.hasDerivatives()
  - getLv
```
public double getLv()
```
    Get the true longitude argument.
    
    Specified by:
    
    getLv in class Orbit
    
    Returns:
    
    v + ω + Ω true longitude argument (rad)
  - getLvDot
```
public double getLvDot()
```
    Get the true longitude argument derivative.
    If the orbit was created without derivatives, the value returned is Double.NaN.
    
    Specified by:
    
    getLvDot in class Orbit
    
    Returns:
    
    d(v + ω + Ω)/dt true longitude argument derivative (rad/s)
    
    See Also:
    
    Orbit.hasDerivatives()
  - getLE
```
public double getLE()
```
    Get the eccentric longitude argument.
    
    Specified by:
    
    getLE in class Orbit
    
    Returns:
    
    E + ω + Ω eccentric longitude argument (rad)
  - getLEDot
```
public double getLEDot()
```
    Get the eccentric longitude argument derivative.
    If the orbit was created without derivatives, the value returned is Double.NaN.
    
    Specified by:
    
    getLEDot in class Orbit
    
    Returns:
    
    d(E + ω + Ω)/dt eccentric longitude argument derivative (rad/s)
    
    See Also:
    
    Orbit.hasDerivatives()
  - getLM
```
public double getLM()
```
    Get the mean longitude argument.
    
    Specified by:
    
    getLM in class Orbit
    
    Returns:
    
    M + ω + Ω mean longitude argument (rad)
  - getLMDot
```
public double getLMDot()
```
    Get the mean longitude argument derivative.
    If the orbit was created without derivatives, the value returned is Double.NaN.
    
    Specified by:
    
    getLMDot in class Orbit
    
    Returns:
    
    d(M + ω + Ω)/dt mean longitude argument derivative (rad/s)
    
    See Also:
    
    Orbit.hasDerivatives()
  - initPVCoordinates
```
protected TimeStampedPVCoordinates initPVCoordinates()
```
    Compute the position/velocity coordinates from the canonical parameters.
    
    Specified by:
    
    initPVCoordinates in class Orbit
    
    Returns:
    
    computed position/velocity coordinates
  - shiftedBy
```
public KeplerianOrbit shiftedBy(double dt)
```
    Get a time-shifted orbit.
    The orbit can be slightly shifted to close dates. The shifting model is a Keplerian one if no derivatives are available in the orbit, or Keplerian plus quadratic effect of the non-Keplerian acceleration if derivatives are available. Shifting is not intended as a replacement for proper orbit propagation but should be sufficient for small time shifts or coarse accuracy.
    
    Specified by:
    
    shiftedBy in interface TimeShiftable<Orbit>
    
    Specified by:
    
    shiftedBy in class Orbit
    
    Parameters:
    
    dt - time shift in seconds
    
    Returns:
    
    a new orbit, shifted with respect to the instance (which is immutable)
  - interpolate
```
public KeplerianOrbit interpolate(AbsoluteDate date,
                                  Stream<Orbit> sample)
```
    Get an interpolated instance.
    Note that the state of the current instance may not be used in the interpolation process, only its type and non interpolable fields are used (for example central attraction coefficient or frame when interpolating orbits). The interpolable fields taken into account are taken only from the states of the sample points. So if the state of the instance must be used, the instance should be included in the sample points.
    
    Note that this method is designed for small samples only (say up to about 10-20 points) so it can be implemented using polynomial interpolation (typically Hermite interpolation). Using too much points may induce Runge's phenomenon and numerical problems (including NaN appearing).
    
    The interpolated instance is created by polynomial Hermite interpolation on Keplerian elements, without derivatives (which means the interpolation falls back to Lagrange interpolation only).
    
    As this implementation of interpolation is polynomial, it should be used only with small samples (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).
    
    If orbit interpolation on large samples is needed, using the Ephemeris class is a better way than using this low-level interpolation. The Ephemeris class automatically handles selection of a neighboring sub-sample with a predefined number of point from a large global sample in a thread-safe way.
    
    Parameters:
    
    date - interpolation date
    
    sample - sample points on which interpolation should be done
    
    Returns:
    
    a new instance, interpolated at specified date
  - computeJacobianMeanWrtCartesian
```
protected double[][] computeJacobianMeanWrtCartesian()
```
    Compute the Jacobian of the orbital parameters with mean angle with respect to the Cartesian parameters.
    Element jacobian[i][j] is the derivative of parameter i of the orbit with respect to Cartesian coordinate j. This means each row correspond to one orbital parameter whereas columns 0 to 5 correspond to the Cartesian coordinates x, y, z, xDot, yDot and zDot.
    
    Specified by:
    
    computeJacobianMeanWrtCartesian in class Orbit
    
    Returns:
    
    6x6 Jacobian matrix
    
    See Also:
    
    Orbit.computeJacobianEccentricWrtCartesian(), Orbit.computeJacobianTrueWrtCartesian()
  - computeJacobianEccentricWrtCartesian
```
protected double[][] computeJacobianEccentricWrtCartesian()
```
    Compute the Jacobian of the orbital parameters with eccentric angle with respect to the Cartesian parameters.
    Element jacobian[i][j] is the derivative of parameter i of the orbit with respect to Cartesian coordinate j. This means each row correspond to one orbital parameter whereas columns 0 to 5 correspond to the Cartesian coordinates x, y, z, xDot, yDot and zDot.
    
    Specified by:
    
    computeJacobianEccentricWrtCartesian in class Orbit
    
    Returns:
    
    6x6 Jacobian matrix
    
    See Also:
    
    Orbit.computeJacobianMeanWrtCartesian(), Orbit.computeJacobianTrueWrtCartesian()
  - computeJacobianTrueWrtCartesian
```
protected double[][] computeJacobianTrueWrtCartesian()
```
    Compute the Jacobian of the orbital parameters with true angle with respect to the Cartesian parameters.
    Element jacobian[i][j] is the derivative of parameter i of the orbit with respect to Cartesian coordinate j. This means each row correspond to one orbital parameter whereas columns 0 to 5 correspond to the Cartesian coordinates x, y, z, xDot, yDot and zDot.
    
    Specified by:
    
    computeJacobianTrueWrtCartesian in class Orbit
    
    Returns:
    
    6x6 Jacobian matrix
    
    See Also:
    
    Orbit.computeJacobianMeanWrtCartesian(), Orbit.computeJacobianEccentricWrtCartesian()
  - addKeplerContribution
```
public void addKeplerContribution(PositionAngle type,
                                  double gm,
                                  double[] pDot)
```
    Add the contribution of the Keplerian motion to parameters derivatives
    This method is used by integration-based propagators to evaluate the part of Keplerian motion to evolution of the orbital state.
    
    Specified by:
    
    addKeplerContribution in class Orbit
    
    Parameters:
    
    type - type of the position angle in the state
    
    gm - attraction coefficient to use
    
    pDot - array containing orbital state derivatives to update (the Keplerian part must be added to the array components, as the array may already contain some non-zero elements corresponding to non-Keplerian parts)
  - toString
```
public String toString()
```
    Returns a string representation of this Keplerian parameters object.
    
    Overrides:
    
    toString in class Object
    
    Returns:
    
    a string representation of this object

Class KeplerianOrbit

Constructor Summary

Method Summary

Methods inherited from class java.lang.Object

Methods inherited from class org.orekit.orbits.Orbit

Methods inherited from interface org.orekit.time.TimeInterpolable

Constructor Detail

KeplerianOrbit

KeplerianOrbit

KeplerianOrbit

KeplerianOrbit

KeplerianOrbit

Method Detail

getType

getA

getADot

getE

getEDot

getI

getIDot

getPerigeeArgument

getPerigeeArgumentDot

getRightAscensionOfAscendingNode

getRightAscensionOfAscendingNodeDot

getTrueAnomaly

getTrueAnomalyDot

getEccentricAnomaly

getEccentricAnomalyDot

getMeanAnomaly

getMeanAnomalyDot

getAnomaly

getAnomalyDot

ellipticEccentricToTrue

trueToEllipticEccentric

hyperbolicEccentricToTrue

trueToHyperbolicEccentric

meanToEllipticEccentric

meanToHyperbolicEccentric

ellipticEccentricToMean

hyperbolicEccentricToMean

getEquinoctialEx

getEquinoctialExDot

getEquinoctialEy

getEquinoctialEyDot

getHx

getHxDot

getHy

getHyDot

getLv

getLvDot

getLE

getLEDot

getLM

getLMDot

initPVCoordinates

shiftedBy

interpolate

computeJacobianMeanWrtCartesian

computeJacobianEccentricWrtCartesian

computeJacobianTrueWrtCartesian

addKeplerContribution

toString