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

Type Parameters:

T - type of the field elements

All Implemented Interfaces:

PositionAngleBased, FieldTimeShiftable<FieldOrbit<T>,T>, FieldTimeStamped<T>, TimeShiftable<FieldOrbit<T>>, FieldPVCoordinatesProvider<T>
```
public class FieldKeplerianOrbit<T extends CalculusFieldElement<T>>
extends FieldOrbit<T>
implements PositionAngleBased
```
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	Description
`FieldKeplerianOrbit(Field<T> field, KeplerianOrbit op)`	Constructor from Field and KeplerianOrbit.
`FieldKeplerianOrbit(Field<T> field, Orbit op)`	Constructor from Field and Orbit.
`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, PositionAngleType 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, PositionAngleType type, PositionAngleType cachedPositionAngleType, 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, PositionAngleType 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, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, FieldAbsoluteDate<T> date, T mu)`	Creates a new instance.

Method Summary

All Methods Instance Methods Concrete Methods
Modifier and Type	Method	Description
`void`	`addKeplerContribution(PositionAngleType 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.
`T`	`getA()`	Get the semi-major axis.
`T`	`getADot()`	Get the semi-major axis derivative.
`T`	`getAnomaly(PositionAngleType type)`	Get the anomaly.
`T`	`getAnomalyDot(PositionAngleType type)`	Get the anomaly derivative.
`PositionAngleType`	`getCachedPositionAngleType()`	Get the cached `PositionAngleType`.
`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 derivative.
`T`	`getEquinoctialEy()`	Get the second component of the equinoctial eccentricity vector.
`T`	`getEquinoctialEyDot()`	Get the second component of the equinoctial eccentricity vector derivative.
`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.
`boolean`	`hasRates()`	Tells whether the instance holds rates (first-order time derivatives) for dependent variables.
`protected FieldVector3D<T>`	`initPosition()`	Compute the position coordinates from the canonical parameters.
`protected TimeStampedFieldPVCoordinates<T>`	`initPVCoordinates()`	Compute the position/velocity coordinates from the canonical parameters.
`FieldKeplerianOrbit<T>`	`removeRates()`	Create a new instance such that `PositionAngleBased.hasRates()` is false.
`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.

Methods inherited from class org.orekit.orbits.FieldOrbit
fillHalfRow, fillHalfRow, fillHalfRow, fillHalfRow, fillHalfRow, fillHalfRow, getDate, getField, getFrame, getJacobianWrtCartesian, getJacobianWrtParameters, getKeplerianMeanMotion, getKeplerianPeriod, getMeanAnomalyDotWrtA, getMu, getOne, getPosition, getPosition, getPosition, getPVCoordinates, getPVCoordinates, getPVCoordinates, getZero, hasNonKeplerianAcceleration, isElliptical

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

Methods inherited from interface org.orekit.time.FieldTimeStamped
durationFrom

- Constructor Detail
  - FieldKeplerianOrbit
```
public FieldKeplerianOrbit(T a,
                           T e,
                           T i,
                           T pa,
                           T raan,
                           T anomaly,
                           PositionAngleType type,
                           PositionAngleType cachedPositionAngleType,
                           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 (positive or equal to 0)
    
    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
    
    cachedPositionAngleType - type of cached 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:
    
    12.1
  - FieldKeplerianOrbit
```
public FieldKeplerianOrbit(T a,
                           T e,
                           T i,
                           T pa,
                           T raan,
                           T anomaly,
                           PositionAngleType 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 (positive or equal to 0)
    
    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
    
    Since:
    
    12.1
  - 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,
                           PositionAngleType type,
                           PositionAngleType cachedPositionAngleType,
                           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 (positive or equal to 0)
    
    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
    
    cachedPositionAngleType - type of cached 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:
    
    12.1
  - 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,
                           PositionAngleType 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 (positive or equal to 0)
    
    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(CalculusFieldElement) 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(CalculusFieldElement) 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
  - FieldKeplerianOrbit
```
public FieldKeplerianOrbit(Field<T> field,
                           KeplerianOrbit op)
```
    Constructor from Field and KeplerianOrbit.
    Build a FieldKeplerianOrbit from non-Field KeplerianOrbit.
    
    Parameters:
    
    field - CalculusField to base object on
    
    op - non-field orbit with only "constant" terms
    
    Since:
    
    12.0
  - FieldKeplerianOrbit
```
public FieldKeplerianOrbit(Field<T> field,
                           Orbit op)
```
    Constructor from Field and Orbit.
    Build a FieldKeplerianOrbit from any non-Field Orbit.
    
    Parameters:
    
    field - CalculusField to base object on
    
    op - non-field orbit with only "constant" terms
    
    Since:
    
    12.0
- Method Detail
  - getType
```
public OrbitType getType()
```
    Get the orbit type.
    
    Specified by:
    
    getType in class FieldOrbit<T extends CalculusFieldElement<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 CalculusFieldElement<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 CalculusFieldElement<T>>
    
    Returns:
    
    semi-major axis derivative (m/s)
  - getE
```
public T getE()
```
    Get the eccentricity.
    
    Specified by:
    
    getE in class FieldOrbit<T extends CalculusFieldElement<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 CalculusFieldElement<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 CalculusFieldElement<T>>
    
    Returns:
    
    inclination (rad)
  - getIDot
```
public T getIDot()
```
    Get the inclination derivative.
    
    Specified by:
    
    getIDot in class FieldOrbit<T extends CalculusFieldElement<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(PositionAngleType type)
```
    Get the anomaly.
    
    Parameters:
    
    type - type of the angle
    
    Returns:
    
    anomaly (rad)
  - getAnomalyDot
```
public T getAnomalyDot(PositionAngleType 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 CalculusFieldElement<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()
  - getEquinoctialEx
```
public T getEquinoctialEx()
```
    Get the first component of the equinoctial eccentricity vector.
    
    Specified by:
    
    getEquinoctialEx in class FieldOrbit<T extends CalculusFieldElement<T>>
    
    Returns:
    
    first component of the equinoctial eccentricity vector
  - getEquinoctialExDot
```
public T getEquinoctialExDot()
```
    Get the first component of the equinoctial eccentricity vector derivative.
    If the orbit was created without derivatives, the value returned is null.
    
    Specified by:
    
    getEquinoctialExDot in class FieldOrbit<T extends CalculusFieldElement<T>>
    
    Returns:
    
    first component of the equinoctial eccentricity vector derivative
  - getEquinoctialEy
```
public T getEquinoctialEy()
```
    Get the second component of the equinoctial eccentricity vector.
    
    Specified by:
    
    getEquinoctialEy in class FieldOrbit<T extends CalculusFieldElement<T>>
    
    Returns:
    
    second component of the equinoctial eccentricity vector
  - getEquinoctialEyDot
```
public T getEquinoctialEyDot()
```
    Get the second component of the equinoctial eccentricity vector derivative.
    If the orbit was created without derivatives, the value returned is null.
    
    Specified by:
    
    getEquinoctialEyDot in class FieldOrbit<T extends CalculusFieldElement<T>>
    
    Returns:
    
    second component of the equinoctial eccentricity vector derivative
  - getHx
```
public T getHx()
```
    Get the first component of the inclination vector.
    
    Specified by:
    
    getHx in class FieldOrbit<T extends CalculusFieldElement<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 CalculusFieldElement<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 CalculusFieldElement<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 CalculusFieldElement<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 CalculusFieldElement<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 CalculusFieldElement<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 CalculusFieldElement<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 CalculusFieldElement<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 CalculusFieldElement<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 CalculusFieldElement<T>>
    
    Returns:
    
    d(M + ω + Ω)/dt mean longitude argument derivative (rad/s)
  - initPosition
```
protected FieldVector3D<T> initPosition()
```
    Compute the position coordinates from the canonical parameters.
    
    Specified by:
    
    initPosition in class FieldOrbit<T extends CalculusFieldElement<T>>
    
    Returns:
    
    computed position coordinates
  - initPVCoordinates
```
protected TimeStampedFieldPVCoordinates<T> initPVCoordinates()
```
    Compute the position/velocity coordinates from the canonical parameters.
    
    Specified by:
    
    initPVCoordinates in class FieldOrbit<T extends CalculusFieldElement<T>>
    
    Returns:
    
    computed position/velocity coordinates
  - shiftedBy
```
public FieldKeplerianOrbit<T> shiftedBy(double dt)
```
    Get a time-shifted instance.
    
    Specified by:
    
    shiftedBy in interface TimeShiftable<T extends CalculusFieldElement<T>>
    
    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 CalculusFieldElement<T>>,T extends CalculusFieldElement<T>>
    
    Specified by:
    
    shiftedBy in class FieldOrbit<T extends CalculusFieldElement<T>>
    
    Parameters:
    
    dt - time shift in seconds
    
    Returns:
    
    a new orbit, shifted with respect to the instance (which is immutable)
  - 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 CalculusFieldElement<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 CalculusFieldElement<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 CalculusFieldElement<T>>
    
    Returns:
    
    6x6 Jacobian matrix
    
    See Also:
    
    FieldOrbit.computeJacobianMeanWrtCartesian(), FieldOrbit.computeJacobianEccentricWrtCartesian()
  - addKeplerContribution
```
public void addKeplerContribution(PositionAngleType 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 CalculusFieldElement<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
  - getCachedPositionAngleType
```
public PositionAngleType getCachedPositionAngleType()
```
    Get the cached PositionAngleType.
    
    Specified by:
    
    getCachedPositionAngleType in interface PositionAngleBased
    
    Returns:
    
    cached type of position angle
  - hasRates
```
public boolean hasRates()
```
    Tells whether the instance holds rates (first-order time derivatives) for dependent variables.
    
    Specified by:
    
    hasRates in interface PositionAngleBased
    
    Returns:
    
    true if and only if holding rates
  - removeRates
```
public FieldKeplerianOrbit<T> removeRates()
```
    Create a new instance such that PositionAngleBased.hasRates() is false.
    
    Specified by:
    
    removeRates in interface PositionAngleBased
    
    Returns:
    
    new object without rates
  - toOrbit
```
public KeplerianOrbit toOrbit()
```
    Transforms the FieldOrbit instance into an Orbit instance.
    
    Specified by:
    
    toOrbit in class FieldOrbit<T extends CalculusFieldElement<T>>
    
    Returns:
    
    Orbit instance with same properties

Class FieldKeplerianOrbit<T extends CalculusFieldElement<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.FieldTimeStamped

Constructor Detail

FieldKeplerianOrbit

FieldKeplerianOrbit

FieldKeplerianOrbit

FieldKeplerianOrbit

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

getEquinoctialEx

getEquinoctialExDot

getEquinoctialEy

getEquinoctialEyDot

getHx

getHxDot

getHy

getHyDot

getLv

getLvDot

getLE

getLEDot

getLM

getLMDot

initPosition

initPVCoordinates

shiftedBy

shiftedBy

computeJacobianMeanWrtCartesian

computeJacobianEccentricWrtCartesian

computeJacobianTrueWrtCartesian

addKeplerContribution

toString

getCachedPositionAngleType

hasRates

removeRates

toOrbit