FieldKeplerianOrbit (ORbit Extrapolation KIT 10.1 API)

java.lang.Object
- org.orekit.orbits.FieldOrbit<T>
- - org.orekit.orbits.FieldKeplerianOrbit<T>

All Implemented Interfaces:

FieldTimeInterpolable<FieldOrbit<T>,T>, FieldTimeShiftable<FieldOrbit<T>,T>, FieldTimeStamped<T>, FieldPVCoordinatesProvider<T>
```
public class FieldKeplerianOrbit<T extends RealFieldElement<T>>
extends FieldOrbit<T>
```
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.
Since:

9.0

Author:

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

See Also:

Orbit, CircularOrbit, CartesianOrbit, EquinoctialOrbit

Constructor Summary

Constructors
Constructor and Description
`FieldKeplerianOrbit(FieldOrbit<T> op)` Constructor from any kind of orbital parameters.
`FieldKeplerianOrbit(FieldPVCoordinates<T> FieldPVCoordinates, Frame frame, FieldAbsoluteDate<T> date, T mu)` Constructor from Cartesian parameters.
`FieldKeplerianOrbit(TimeStampedFieldPVCoordinates<T> pvCoordinates, Frame frame, T mu)` Constructor from Cartesian parameters.
`FieldKeplerianOrbit(T a, T e, T i, T pa, T raan, T anomaly, PositionAngle type, Frame frame, FieldAbsoluteDate<T> date, T mu)` Creates a new instance.
`FieldKeplerianOrbit(T a, T e, T i, T pa, T raan, T anomaly, T aDot, T eDot, T iDot, T paDot, T raanDot, T anomalyDot, PositionAngle type, Frame frame, FieldAbsoluteDate<T> date, T mu)` Creates a new instance.

Method Summary

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

Methods inherited from class org.orekit.orbits.FieldOrbit
fillHalfRow, fillHalfRow, fillHalfRow, fillHalfRow, fillHalfRow, fillHalfRow, getDate, getFrame, getJacobianWrtCartesian, getJacobianWrtParameters, getKeplerianMeanMotion, getKeplerianPeriod, getMu, getPVCoordinates, getPVCoordinates, getPVCoordinates, 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.FieldTimeInterpolable
interpolate

- Constructor Detail
  - FieldKeplerianOrbit
```
public FieldKeplerianOrbit(T a,
                           T e,
                           T i,
                           T pa,
                           T raan,
                           T anomaly,
                           PositionAngle type,
                           Frame frame,
                           FieldAbsoluteDate<T> date,
                           T 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
  - FieldKeplerianOrbit
```
public FieldKeplerianOrbit(T a,
                           T e,
                           T i,
                           T pa,
                           T raan,
                           T anomaly,
                           T aDot,
                           T eDot,
                           T iDot,
                           T paDot,
                           T raanDot,
                           T anomalyDot,
                           PositionAngle type,
                           Frame frame,
                           FieldAbsoluteDate<T> date,
                           T 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, null if unknown (m/s)
    
    eDot - eccentricity derivative, null if unknown
    
    iDot - inclination derivative, null if unknown (rad/s)
    
    paDot - perigee argument derivative, null if unknown (rad/s)
    
    raanDot - right ascension of ascending node derivative, null if unknown (rad/s)
    
    anomalyDot - mean, eccentric or true anomaly derivative, null if unknown (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
  - FieldKeplerianOrbit
```
public FieldKeplerianOrbit(TimeStampedFieldPVCoordinates<T> pvCoordinates,
                           Frame frame,
                           T mu)
                    throws IllegalArgumentException
```
    Constructor from Cartesian parameters.
    The acceleration provided in FieldPVCoordinates is accessible using FieldOrbit.getPVCoordinates() and FieldOrbit.getPVCoordinates(Frame). All other methods use mu and the position to compute the acceleration, including shiftedBy(RealFieldElement) and FieldOrbit.getPVCoordinates(FieldAbsoluteDate, Frame).
    
    Parameters:
    
    pvCoordinates - the PVCoordinates of the satellite
    
    frame - the frame in which are defined the FieldPVCoordinates (must be a pseudo-inertial frame)
    
    mu - central attraction coefficient (m³/s²)
    
    Throws:
    
    IllegalArgumentException - if frame is not a pseudo-inertial frame
  - FieldKeplerianOrbit
```
public FieldKeplerianOrbit(FieldPVCoordinates<T> FieldPVCoordinates,
                           Frame frame,
                           FieldAbsoluteDate<T> date,
                           T mu)
                    throws IllegalArgumentException
```
    Constructor from Cartesian parameters.
    The acceleration provided in FieldPVCoordinates is accessible using FieldOrbit.getPVCoordinates() and FieldOrbit.getPVCoordinates(Frame). All other methods use mu and the position to compute the acceleration, including shiftedBy(RealFieldElement) and FieldOrbit.getPVCoordinates(FieldAbsoluteDate, Frame).
    
    Parameters:
    
    FieldPVCoordinates - the PVCoordinates of the satellite
    
    frame - the frame in which are defined the FieldPVCoordinates (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
  - FieldKeplerianOrbit
```
public FieldKeplerianOrbit(FieldOrbit<T> 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 FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    orbit type
  - getA
```
public T getA()
```
    Get the semi-major axis.
    Note that the semi-major axis is considered negative for hyperbolic orbits.
    
    Specified by:
    
    getA in class FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    semi-major axis (m)
  - getADot
```
public T 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 null.
    
    Specified by:
    
    getADot in class FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    semi-major axis derivative (m/s)
  - getE
```
public T getE()
```
    Get the eccentricity.
    
    Specified by:
    
    getE in class FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    eccentricity
  - getEDot
```
public T getEDot()
```
    Get the eccentricity derivative.
    If the orbit was created without derivatives, the value returned is null.
    
    Specified by:
    
    getEDot in class FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    eccentricity derivative
  - getI
```
public T getI()
```
    Get the inclination.
    If the orbit was created without derivatives, the value returned is null.
    
    Specified by:
    
    getI in class FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    inclination (rad)
  - getIDot
```
public T getIDot()
```
    Get the inclination derivative.
    
    Specified by:
    
    getIDot in class FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    inclination derivative (rad/s)
  - getPerigeeArgument
```
public T getPerigeeArgument()
```
    Get the perigee argument.
    
    Returns:
    
    perigee argument (rad)
  - getPerigeeArgumentDot
```
public T getPerigeeArgumentDot()
```
    Get the perigee argument derivative.
    If the orbit was created without derivatives, the value returned is null.
    
    Returns:
    
    perigee argument derivative (rad/s)
  - getRightAscensionOfAscendingNode
```
public T getRightAscensionOfAscendingNode()
```
    Get the right ascension of the ascending node.
    
    Returns:
    
    right ascension of the ascending node (rad)
  - getRightAscensionOfAscendingNodeDot
```
public T getRightAscensionOfAscendingNodeDot()
```
    Get the right ascension of the ascending node derivative.
    If the orbit was created without derivatives, the value returned is null.
    
    Returns:
    
    right ascension of the ascending node derivative (rad/s)
  - getTrueAnomaly
```
public T getTrueAnomaly()
```
    Get the true anomaly.
    
    Returns:
    
    true anomaly (rad)
  - getTrueAnomalyDot
```
public T getTrueAnomalyDot()
```
    Get the true anomaly derivative.
    If the orbit was created without derivatives, the value returned is null.
    
    Returns:
    
    true anomaly derivative (rad/s)
  - getEccentricAnomaly
```
public T getEccentricAnomaly()
```
    Get the eccentric anomaly.
    
    Returns:
    
    eccentric anomaly (rad)
  - getEccentricAnomalyDot
```
public T getEccentricAnomalyDot()
```
    Get the eccentric anomaly derivative.
    If the orbit was created without derivatives, the value returned is null.
    
    Returns:
    
    eccentric anomaly derivative (rad/s)
  - getMeanAnomaly
```
public T getMeanAnomaly()
```
    Get the mean anomaly.
    
    Returns:
    
    mean anomaly (rad)
  - getMeanAnomalyDot
```
public T getMeanAnomalyDot()
```
    Get the mean anomaly derivative.
    If the orbit was created without derivatives, the value returned is null.
    
    Returns:
    
    mean anomaly derivative (rad/s)
  - getAnomaly
```
public T getAnomaly(PositionAngle type)
```
    Get the anomaly.
    
    Parameters:
    
    type - type of the angle
    
    Returns:
    
    anomaly (rad)
  - getAnomalyDot
```
public T getAnomalyDot(PositionAngle type)
```
    Get the anomaly derivative.
    If the orbit was created without derivatives, the value returned is null.
    
    Parameters:
    
    type - type of the angle
    
    Returns:
    
    anomaly derivative (rad/s)
  - hasDerivatives
```
public boolean hasDerivatives()
```
    Check if orbit includes derivatives.
    
    Specified by:
    
    hasDerivatives in class FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    true if orbit includes derivatives
    
    See Also:
    
    FieldOrbit.getADot(), FieldOrbit.getEquinoctialExDot(), FieldOrbit.getEquinoctialEyDot(), FieldOrbit.getHxDot(), FieldOrbit.getHyDot(), FieldOrbit.getLEDot(), FieldOrbit.getLvDot(), FieldOrbit.getLMDot(), FieldOrbit.getEDot(), FieldOrbit.getIDot()
  - ellipticEccentricToTrue
```
public static <T extends RealFieldElement<T>> T ellipticEccentricToTrue(T E,
                                                                        T e)
```
    Computes the true anomaly from the elliptic eccentric anomaly.
    
    Type Parameters:
    
    T - type of the field elements
    
    Parameters:
    
    E - eccentric anomaly (rad)
    
    e - eccentricity
    
    Returns:
    
    v the true anomaly
  - trueToEllipticEccentric
```
public static <T extends RealFieldElement<T>> T trueToEllipticEccentric(T v,
                                                                        T e)
```
    Computes the elliptic eccentric anomaly from the true anomaly.
    
    Type Parameters:
    
    T - type of the field elements
    
    Parameters:
    
    v - true anomaly (rad)
    
    e - eccentricity
    
    Returns:
    
    E the elliptic eccentric anomaly
  - hyperbolicEccentricToTrue
```
public static <T extends RealFieldElement<T>> T hyperbolicEccentricToTrue(T H,
                                                                          T e)
```
    Computes the true anomaly from the hyperbolic eccentric anomaly.
    
    Type Parameters:
    
    T - type of the field elements
    
    Parameters:
    
    H - hyperbolic eccentric anomaly (rad)
    
    e - eccentricity
    
    Returns:
    
    v the true anomaly
  - trueToHyperbolicEccentric
```
public static <T extends RealFieldElement<T>> T trueToHyperbolicEccentric(T v,
                                                                          T e)
```
    Computes the hyperbolic eccentric anomaly from the true anomaly.
    
    Type Parameters:
    
    T - type of the field elements
    
    Parameters:
    
    v - true anomaly (rad)
    
    e - eccentricity
    
    Returns:
    
    H the hyperbolic eccentric anomaly
  - hyperbolicEccentricToMean
```
public static <T extends RealFieldElement<T>> T hyperbolicEccentricToMean(T H,
                                                                          T e)
```
    Computes the mean anomaly from the hyperbolic eccentric anomaly.
    
    Type Parameters:
    
    T - type of the field elements
    
    Parameters:
    
    H - hyperbolic eccentric anomaly (rad)
    
    e - eccentricity
    
    Returns:
    
    M the mean anomaly
  - meanToEllipticEccentric
```
public static <T extends RealFieldElement<T>> T meanToEllipticEccentric(T M,
                                                                        T 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
    
    Type Parameters:
    
    T - type of the field elements
    
    Parameters:
    
    M - mean anomaly (rad)
    
    e - eccentricity
    
    Returns:
    
    E the eccentric anomaly
  - meanToHyperbolicEccentric
```
public static <T extends RealFieldElement<T>> T meanToHyperbolicEccentric(T M,
                                                                          T e)
```
    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.
    
    Type Parameters:
    
    T - Type of the field elements
    
    Parameters:
    
    M - mean anomaly (rad)
    
    e - eccentricity
    
    Returns:
    
    H the hyperbolic eccentric anomaly
  - ellipticEccentricToMean
```
public static <T extends RealFieldElement<T>> T ellipticEccentricToMean(T E,
                                                                        T e)
```
    Computes the mean anomaly from the elliptic eccentric anomaly.
    
    Type Parameters:
    
    T - type of the field elements
    
    Parameters:
    
    E - eccentric anomaly (rad)
    
    e - eccentricity
    
    Returns:
    
    M the mean anomaly
  - getEquinoctialEx
```
public T getEquinoctialEx()
```
    Get the first component of the equinoctial eccentricity vector.
    
    Specified by:
    
    getEquinoctialEx in class FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    first component of the equinoctial eccentricity vector
  - getEquinoctialExDot
```
public T getEquinoctialExDot()
```
    Get the first component of the equinoctial eccentricity vector.
    If the orbit was created without derivatives, the value returned is null.
    
    Specified by:
    
    getEquinoctialExDot in class FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    first component of the equinoctial eccentricity vector
  - getEquinoctialEy
```
public T getEquinoctialEy()
```
    Get the second component of the equinoctial eccentricity vector.
    
    Specified by:
    
    getEquinoctialEy in class FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    second component of the equinoctial eccentricity vector
  - getEquinoctialEyDot
```
public T getEquinoctialEyDot()
```
    Get the second component of the equinoctial eccentricity vector.
    If the orbit was created without derivatives, the value returned is null.
    
    Specified by:
    
    getEquinoctialEyDot in class FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    second component of the equinoctial eccentricity vector
  - getHx
```
public T getHx()
```
    Get the first component of the inclination vector.
    
    Specified by:
    
    getHx in class FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    first component of the inclination vector
  - getHxDot
```
public T getHxDot()
```
    Get the first component of the inclination vector derivative.
    If the orbit was created without derivatives, the value returned is null.
    
    Specified by:
    
    getHxDot in class FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    first component of the inclination vector derivative
  - getHy
```
public T getHy()
```
    Get the second component of the inclination vector.
    
    Specified by:
    
    getHy in class FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    second component of the inclination vector
  - getHyDot
```
public T getHyDot()
```
    Get the second component of the inclination vector derivative.
    
    Specified by:
    
    getHyDot in class FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    second component of the inclination vector derivative
  - getLv
```
public T getLv()
```
    Get the true longitude argument.
    
    Specified by:
    
    getLv in class FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    v + ω + Ω true longitude argument (rad)
  - getLvDot
```
public T getLvDot()
```
    Get the true longitude argument derivative.
    If the orbit was created without derivatives, the value returned is null.
    
    Specified by:
    
    getLvDot in class FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    d(v + ω + Ω)/dt true longitude argument derivative (rad/s)
  - getLE
```
public T getLE()
```
    Get the eccentric longitude argument.
    
    Specified by:
    
    getLE in class FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    E + ω + Ω eccentric longitude argument (rad)
  - getLEDot
```
public T getLEDot()
```
    Get the eccentric longitude argument derivative.
    If the orbit was created without derivatives, the value returned is null.
    
    Specified by:
    
    getLEDot in class FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    d(E + ω + Ω)/dt eccentric longitude argument derivative (rad/s)
  - getLM
```
public T getLM()
```
    Get the mean longitude argument.
    
    Specified by:
    
    getLM in class FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    M + ω + Ω mean longitude argument (rad)
  - getLMDot
```
public T getLMDot()
```
    Get the mean longitude argument derivative.
    If the orbit was created without derivatives, the value returned is null.
    
    Specified by:
    
    getLMDot in class FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    d(M + ω + Ω)/dt mean longitude argument derivative (rad/s)
  - initPVCoordinates
```
protected TimeStampedFieldPVCoordinates<T> initPVCoordinates()
```
    Compute the position/velocity coordinates from the canonical parameters.
    
    Specified by:
    
    initPVCoordinates in class FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    computed position/velocity coordinates
  - shiftedBy
```
public FieldKeplerianOrbit<T> shiftedBy(double dt)
```
    Get a time-shifted instance.
    
    Parameters:
    
    dt - time shift in seconds
    
    Returns:
    
    a new instance, shifted with respect to instance (which is not changed)
  - shiftedBy
```
public FieldKeplerianOrbit<T> shiftedBy(T dt)
```
    Get a time-shifted orbit.
    The orbit can be slightly shifted to close dates. This shift is based on a simple Keplerian model. It is not intended as a replacement for proper orbit and attitude propagation but should be sufficient for small time shifts or coarse accuracy.
    
    Specified by:
    
    shiftedBy in interface FieldTimeShiftable<FieldOrbit<T extends RealFieldElement<T>>,T extends RealFieldElement<T>>
    
    Specified by:
    
    shiftedBy in class FieldOrbit<T extends RealFieldElement<T>>
    
    Parameters:
    
    dt - time shift in seconds
    
    Returns:
    
    a new orbit, shifted with respect to the instance (which is immutable)
  - interpolate
```
public FieldKeplerianOrbit<T> interpolate(FieldAbsoluteDate<T> date,
                                          Stream<FieldOrbit<T>> 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 T[][] 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 FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    6x6 Jacobian matrix
    
    See Also:
    
    FieldOrbit.computeJacobianEccentricWrtCartesian(), FieldOrbit.computeJacobianTrueWrtCartesian()
  - computeJacobianEccentricWrtCartesian
```
protected T[][] 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 FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    6x6 Jacobian matrix
    
    See Also:
    
    FieldOrbit.computeJacobianMeanWrtCartesian(), FieldOrbit.computeJacobianTrueWrtCartesian()
  - computeJacobianTrueWrtCartesian
```
protected T[][] 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 FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    6x6 Jacobian matrix
    
    See Also:
    
    FieldOrbit.computeJacobianMeanWrtCartesian(), FieldOrbit.computeJacobianEccentricWrtCartesian()
  - addKeplerContribution
```
public void addKeplerContribution(PositionAngle type,
                                  T gm,
                                  T[] 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 FieldOrbit<T extends RealFieldElement<T>>
    
    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
  - normalizeAngle
```
@Deprecated
public static <T extends RealFieldElement<T>> T normalizeAngle(T a,
                                                                           T center)
```
    Deprecated. replaced by MathUtils.normalizeAngle(RealFieldElement, RealFieldElement)
    Normalize an angle in a 2π wide interval around a center value.
    This method has three main uses:
    - normalize an angle between 0 and 2π:
      a = MathUtils.normalizeAngle(a, FastMath.PI);
    - normalize an angle between -π and +π
      a = MathUtils.normalizeAngle(a, 0.0);
    - compute the angle between two defining angular positions:
      angle = MathUtils.normalizeAngle(end, start) - start;
    Note that due to numerical accuracy and since π cannot be represented exactly, the result interval is closed, it cannot be half-closed as would be more satisfactory in a purely mathematical view.
    Type Parameters:
    
    T - the type of the field elements
    
    Parameters:
    
    a - angle to normalize
    
    center - center of the desired 2π interval for the result
    
    Returns:
    
    a-2kπ with integer k and center-π <= a-2kπ <= center+π
  - toOrbit
```
public KeplerianOrbit toOrbit()
```
    Description copied from class: FieldOrbit
    
    Transforms the FieldOrbit instance into an Orbit instance.
    
    Specified by:
    
    toOrbit in class FieldOrbit<T extends RealFieldElement<T>>
    
    Returns:
    
    Orbit instance with same properties

Class FieldKeplerianOrbit<T extends RealFieldElement<T>>

Constructor Summary

Method Summary

Methods inherited from class org.orekit.orbits.FieldOrbit

Methods inherited from class java.lang.Object

Methods inherited from interface org.orekit.time.FieldTimeInterpolable

Constructor Detail

FieldKeplerianOrbit

FieldKeplerianOrbit

FieldKeplerianOrbit

FieldKeplerianOrbit

FieldKeplerianOrbit

Method Detail

getType

getA

getADot

getE

getEDot

getI

getIDot

getPerigeeArgument

getPerigeeArgumentDot

getRightAscensionOfAscendingNode

getRightAscensionOfAscendingNodeDot

getTrueAnomaly

getTrueAnomalyDot

getEccentricAnomaly

getEccentricAnomalyDot

getMeanAnomaly

getMeanAnomalyDot

getAnomaly

getAnomalyDot

hasDerivatives

ellipticEccentricToTrue

trueToEllipticEccentric

hyperbolicEccentricToTrue

trueToHyperbolicEccentric

hyperbolicEccentricToMean

meanToEllipticEccentric

meanToHyperbolicEccentric

ellipticEccentricToMean

getEquinoctialEx

getEquinoctialExDot

getEquinoctialEy

getEquinoctialEyDot

getHx

getHxDot

getHy

getHyDot

getLv

getLvDot

getLE

getLEDot

getLM

getLMDot

initPVCoordinates

shiftedBy

shiftedBy

interpolate

computeJacobianMeanWrtCartesian

computeJacobianEccentricWrtCartesian

computeJacobianTrueWrtCartesian

addKeplerContribution

toString

normalizeAngle

toOrbit