EquinoctialOrbit (ORbit Extrapolation KIT 11.3.2 API)

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

All Implemented Interfaces:

Serializable, TimeInterpolable<Orbit>, TimeShiftable<Orbit>, TimeStamped, PVCoordinatesProvider
```
public class EquinoctialOrbit
extends Orbit
```
This class handles equinoctial orbital parameters, which can support both circular and equatorial orbits.
The parameters used internally are the equinoctial elements which can be related to Keplerian elements as follows:
```
     a
     ex = e cos(ω + Ω)
     ey = e sin(ω + Ω)
     hx = tan(i/2) cos(Ω)
     hy = tan(i/2) sin(Ω)
     lv = v + ω + Ω
   
```
where ω stands for the Perigee Argument and Ω stands for the Right Ascension of the Ascending Node.
The conversion equations from and to Keplerian elements given above hold only when both sides are unambiguously defined, i.e. when orbit is neither equatorial nor circular. When orbit is either equatorial or circular, the equinoctial parameters are still unambiguously defined whereas some Keplerian elements (more precisely ω and Ω) become ambiguous. For this reason, equinoctial parameters are the recommended way to represent orbits.

The instance EquinoctialOrbit is guaranteed to be immutable.
Author:

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

See Also:

Orbit, KeplerianOrbit, CircularOrbit, CartesianOrbit, Serialized Form

Constructor Summary

Constructors
Constructor and Description
`EquinoctialOrbit(double a, double ex, double ey, double hx, double hy, double l, double aDot, double exDot, double eyDot, double hxDot, double hyDot, double lDot, PositionAngle type, Frame frame, AbsoluteDate date, double mu)` Creates a new instance.
`EquinoctialOrbit(double a, double ex, double ey, double hx, double hy, double l, PositionAngle type, Frame frame, AbsoluteDate date, double mu)` Creates a new instance.
`EquinoctialOrbit(Orbit op)` Constructor from any kind of orbital parameters.
`EquinoctialOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu)` Constructor from Cartesian parameters.
`EquinoctialOrbit(TimeStampedPVCoordinates pvCoordinates, Frame frame, double mu)` Constructor from Cartesian parameters.

Method Summary

All Methods Static Methods Instance Methods Concrete Methods
Modifier and Type	Method and 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`	`eccentricToMean(double lE, double ex, double ey)` Computes the mean longitude argument from the eccentric longitude argument.
`static double`	`eccentricToTrue(double lE, double ex, double ey)` Computes the true longitude argument from the eccentric longitude argument.
`double`	`getA()` Get the semi-major axis.
`double`	`getADot()` Get the semi-major axis derivative.
`double`	`getE()` Get the eccentricity.
`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`	`getL(PositionAngle type)` Get the longitude argument.
`double`	`getLDot(PositionAngle type)` Get the longitude argument 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.
`OrbitType`	`getType()` Get the orbit type.
`protected TimeStampedPVCoordinates`	`initPVCoordinates()` Compute the position/velocity coordinates from the canonical parameters.
`EquinoctialOrbit`	`interpolate(AbsoluteDate date, Stream<Orbit> sample)` Get an interpolated instance.
`static double`	`meanToEccentric(double lM, double ex, double ey)` Computes the eccentric longitude argument from the mean longitude argument.
`EquinoctialOrbit`	`shiftedBy(double dt)` Get a time-shifted orbit.
`String`	`toString()` Returns a string representation of this equinoctial parameters object.
`static double`	`trueToEccentric(double lv, double ex, double ey)` Computes the eccentric longitude argument from the true longitude argument.

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

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

- Constructor Detail
  - EquinoctialOrbit
```
public EquinoctialOrbit(double a,
                        double ex,
                        double ey,
                        double hx,
                        double hy,
                        double l,
                        PositionAngle type,
                        Frame frame,
                        AbsoluteDate date,
                        double mu)
                 throws IllegalArgumentException
```
    Creates a new instance.
    
    Parameters:
    
    a - semi-major axis (m)
    
    ex - e cos(ω + Ω), first component of eccentricity vector
    
    ey - e sin(ω + Ω), second component of eccentricity vector
    
    hx - tan(i/2) cos(Ω), first component of inclination vector
    
    hy - tan(i/2) sin(Ω), second component of inclination vector
    
    l - (M or E or v) + ω + Ω, mean, eccentric or true longitude argument (rad)
    
    type - type of longitude argument
    
    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 eccentricity is equal to 1 or larger or if frame is not a pseudo-inertial frame
  - EquinoctialOrbit
```
public EquinoctialOrbit(double a,
                        double ex,
                        double ey,
                        double hx,
                        double hy,
                        double l,
                        double aDot,
                        double exDot,
                        double eyDot,
                        double hxDot,
                        double hyDot,
                        double lDot,
                        PositionAngle type,
                        Frame frame,
                        AbsoluteDate date,
                        double mu)
                 throws IllegalArgumentException
```
    Creates a new instance.
    
    Parameters:
    
    a - semi-major axis (m)
    
    ex - e cos(ω + Ω), first component of eccentricity vector
    
    ey - e sin(ω + Ω), second component of eccentricity vector
    
    hx - tan(i/2) cos(Ω), first component of inclination vector
    
    hy - tan(i/2) sin(Ω), second component of inclination vector
    
    l - (M or E or v) + ω + Ω, mean, eccentric or true longitude argument (rad)
    
    aDot - semi-major axis derivative (m/s)
    
    exDot - d(e cos(ω + Ω))/dt, first component of eccentricity vector derivative
    
    eyDot - d(e sin(ω + Ω))/dt, second component of eccentricity vector derivative
    
    hxDot - d(tan(i/2) cos(Ω))/dt, first component of inclination vector derivative
    
    hyDot - d(tan(i/2) sin(Ω))/dt, second component of inclination vector derivative
    
    lDot - d(M or E or v) + ω + Ω)/dr, mean, eccentric or true longitude argument derivative (rad/s)
    
    type - type of longitude argument
    
    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 eccentricity is equal to 1 or larger or if frame is not a pseudo-inertial frame
  - EquinoctialOrbit
```
public EquinoctialOrbit(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 position, velocity and acceleration
    
    frame - the frame in which are defined the PVCoordinates (must be a pseudo-inertial frame)
    
    mu - central attraction coefficient (m³/s²)
    
    Throws:
    
    IllegalArgumentException - if eccentricity is equal to 1 or larger or if frame is not a pseudo-inertial frame
  - EquinoctialOrbit
```
public EquinoctialOrbit(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 position end velocity
    
    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 eccentricity is equal to 1 or larger or if frame is not a pseudo-inertial frame
  - EquinoctialOrbit
```
public EquinoctialOrbit(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()
  - 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()
  - getL
```
public double getL(PositionAngle type)
```
    Get the longitude argument.
    
    Parameters:
    
    type - type of the angle
    
    Returns:
    
    longitude argument (rad)
  - getLDot
```
public double getLDot(PositionAngle type)
```
    Get the longitude argument derivative.
    
    Parameters:
    
    type - type of the angle
    
    Returns:
    
    longitude argument derivative (rad/s)
  - eccentricToTrue
```
public static double eccentricToTrue(double lE,
                                     double ex,
                                     double ey)
```
    Computes the true longitude argument from the eccentric longitude argument.
    
    Parameters:
    
    lE - = E + ω + Ω eccentric longitude argument (rad)
    
    ex - first component of the eccentricity vector
    
    ey - second component of the eccentricity vector
    
    Returns:
    
    the true longitude argument
  - trueToEccentric
```
public static double trueToEccentric(double lv,
                                     double ex,
                                     double ey)
```
    Computes the eccentric longitude argument from the true longitude argument.
    
    Parameters:
    
    lv - = v + ω + Ω true longitude argument (rad)
    
    ex - first component of the eccentricity vector
    
    ey - second component of the eccentricity vector
    
    Returns:
    
    the eccentric longitude argument
  - meanToEccentric
```
public static double meanToEccentric(double lM,
                                     double ex,
                                     double ey)
```
    Computes the eccentric longitude argument from the mean longitude argument.
    
    Parameters:
    
    lM - = M + ω + Ω mean longitude argument (rad)
    
    ex - first component of the eccentricity vector
    
    ey - second component of the eccentricity vector
    
    Returns:
    
    the eccentric longitude argument
  - eccentricToMean
```
public static double eccentricToMean(double lE,
                                     double ex,
                                     double ey)
```
    Computes the mean longitude argument from the eccentric longitude argument.
    
    Parameters:
    
    lE - = E + ω + Ω mean longitude argument (rad)
    
    ex - first component of the eccentricity vector
    
    ey - second component of the eccentricity vector
    
    Returns:
    
    the mean longitude argument
  - 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()
  - 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 EquinoctialOrbit 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 EquinoctialOrbit 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 equinoctial 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 equinoctial parameters object.
    
    Overrides:
    
    toString in class Object
    
    Returns:
    
    a string representation of this object

Class EquinoctialOrbit

Constructor Summary

Method Summary

Methods inherited from class org.orekit.orbits.Orbit

Methods inherited from class java.lang.Object

Methods inherited from interface org.orekit.time.TimeInterpolable

Constructor Detail

EquinoctialOrbit

EquinoctialOrbit

EquinoctialOrbit

EquinoctialOrbit

EquinoctialOrbit

Method Detail

getType

getA

getADot

getEquinoctialEx

getEquinoctialExDot

getEquinoctialEy

getEquinoctialEyDot

getHx

getHxDot

getHy

getHyDot

getLv

getLvDot

getLE

getLEDot

getLM

getLMDot

getL

getLDot

eccentricToTrue

trueToEccentric

meanToEccentric

eccentricToMean

getE

getEDot

getI

getIDot

initPVCoordinates

shiftedBy

interpolate

computeJacobianMeanWrtCartesian

computeJacobianEccentricWrtCartesian

computeJacobianTrueWrtCartesian

addKeplerContribution

toString