FieldEquinoctialOrbit (ORbit Extrapolation KIT 9.2 API)

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

All Implemented Interfaces:

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

9.0

Author:

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

See Also:

Orbit, KeplerianOrbit, CircularOrbit, CartesianOrbit

Constructor Summary

Constructors
Constructor	Description
`FieldEquinoctialOrbit(FieldOrbit<T> op)`	Constructor from any kind of orbital parameters.
`FieldEquinoctialOrbit(FieldPVCoordinates<T> pvCoordinates, Frame frame, FieldAbsoluteDate<T> date, double mu)`	Constructor from Cartesian parameters.
`FieldEquinoctialOrbit(TimeStampedFieldPVCoordinates<T> pvCoordinates, Frame frame, double mu)`	Constructor from Cartesian parameters.
`FieldEquinoctialOrbit(T a, T ex, T ey, T hx, T hy, T l, PositionAngle type, Frame frame, FieldAbsoluteDate<T> date, double mu)`	Creates a new instance.
`FieldEquinoctialOrbit(T a, T ex, T ey, T hx, T hy, T l, T aDot, T exDot, T eyDot, T hxDot, T hyDot, T lDot, PositionAngle type, Frame frame, FieldAbsoluteDate<T> date, double mu)`	Creates a new instance.

Method Summary

All Methods Static Methods Instance Methods Concrete Methods
Modifier and Type	Method	Description
`void`	`addKeplerContribution(PositionAngle type, double 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`	`eccentricToMean(T lE, T ex, T ey)`	Computes the mean longitude argument from the eccentric longitude argument.
`static <T extends RealFieldElement<T>> T`	`eccentricToTrue(T lE, T ex, T ey)`	Computes the true longitude argument from the eccentric longitude argument.
`static <T extends RealFieldElement<T>> FieldVector3D<T>`	`equinoctialToPosition(T a, T ex, T ey, T hx, T hy, T lv, double mu)`	Compute position from equinoctial parameters.
`T`	`getA()`	Get the semi-major axis.
`T`	`getADot()`	Get the semi-major axis derivative.
`T`	`getE()`	Get the eccentricity.
`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`	`getL(PositionAngle type)`	Get the longitude argument.
`T`	`getLDot(PositionAngle type)`	Get the longitude argument 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.
`OrbitType`	`getType()`	Get the orbit type.
`boolean`	`hasDerivatives()`	Check if orbit includes derivatives.
`protected TimeStampedFieldPVCoordinates<T>`	`initPVCoordinates()`	Compute the position/velocity coordinates from the canonical parameters.
`FieldEquinoctialOrbit<T>`	`interpolate(FieldAbsoluteDate<T> date, Stream<FieldOrbit<T>> sample)`	Get an interpolated instance.
`static <T extends RealFieldElement<T>> T`	`meanToEccentric(T lM, T ex, T ey)`	Computes the eccentric longitude argument from the mean longitude argument.
`static <T extends RealFieldElement<T>> T`	`normalizeAngle(T a, T center)`	Normalize an angle in a 2π wide interval around a center value.
`FieldEquinoctialOrbit<T>`	`shiftedBy(double dt)`	Get a time-shifted instance.
`FieldEquinoctialOrbit<T>`	`shiftedBy(T dt)`	Get a time-shifted orbit.
`EquinoctialOrbit`	`toOrbit()`	Transforms the FieldOrbit instance into an Orbit instance.
`String`	`toString()`	Returns a string representation of this equinoctial parameters object.
`static <T extends RealFieldElement<T>> T`	`trueToEccentric(T lv, T ex, T ey)`	Computes the eccentric longitude argument from the true longitude argument.

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 interface org.orekit.time.FieldTimeInterpolable
interpolate

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

- Constructor Detail
  - FieldEquinoctialOrbit
```
public FieldEquinoctialOrbit(T a,
                             T ex,
                             T ey,
                             T hx,
                             T hy,
                             T l,
                             PositionAngle type,
                             Frame frame,
                             FieldAbsoluteDate<T> 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
  - FieldEquinoctialOrbit
```
public FieldEquinoctialOrbit(T a,
                             T ex,
                             T ey,
                             T hx,
                             T hy,
                             T l,
                             T aDot,
                             T exDot,
                             T eyDot,
                             T hxDot,
                             T hyDot,
                             T lDot,
                             PositionAngle type,
                             Frame frame,
                             FieldAbsoluteDate<T> 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
  - FieldEquinoctialOrbit
```
public FieldEquinoctialOrbit(TimeStampedFieldPVCoordinates<T> pvCoordinates,
                             Frame frame,
                             double mu)
                      throws IllegalArgumentException
```
    Constructor from Cartesian parameters.
    The acceleration provided in pvCoordinates 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 position, velocity and acceleration
    
    frame - the frame in which are defined the FieldPVCoordinates (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
  - FieldEquinoctialOrbit
```
public FieldEquinoctialOrbit(FieldPVCoordinates<T> pvCoordinates,
                             Frame frame,
                             FieldAbsoluteDate<T> date,
                             double mu)
                      throws IllegalArgumentException
```
    Constructor from Cartesian parameters.
    The acceleration provided in pvCoordinates 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 position end velocity
    
    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 eccentricity is equal to 1 or larger or if frame is not a pseudo-inertial frame
  - FieldEquinoctialOrbit
```
public FieldEquinoctialOrbit(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)
  - 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)
  - getL
```
public T getL(PositionAngle type)
```
    Get the longitude argument.
    
    Parameters:
    
    type - type of the angle
    
    Returns:
    
    longitude argument (rad)
  - getLDot
```
public T getLDot(PositionAngle type)
```
    Get the longitude argument derivative.
    
    Parameters:
    
    type - type of the angle
    
    Returns:
    
    longitude argument 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()
  - eccentricToTrue
```
public static <T extends RealFieldElement<T>> T eccentricToTrue(T lE,
                                                                T ex,
                                                                T ey)
```
    Computes the true longitude argument from the eccentric longitude argument.
    
    Type Parameters:
    
    T - Type of the field elements
    
    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 <T extends RealFieldElement<T>> T trueToEccentric(T lv,
                                                                T ex,
                                                                T ey)
```
    Computes the eccentric longitude argument from the true longitude argument.
    
    Type Parameters:
    
    T - Type of the field elements
    
    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 <T extends RealFieldElement<T>> T meanToEccentric(T lM,
                                                                T ex,
                                                                T ey)
```
    Computes the eccentric longitude argument from the mean longitude argument.
    
    Type Parameters:
    
    T - Type of the field elements
    
    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 <T extends RealFieldElement<T>> T eccentricToMean(T lE,
                                                                T ex,
                                                                T ey)
```
    Computes the mean longitude argument from the eccentric longitude argument.
    
    Type Parameters:
    
    T - Type of the field elements
    
    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
  - equinoctialToPosition
```
public static <T extends RealFieldElement<T>> FieldVector3D<T> equinoctialToPosition(T a,
                                                                                     T ex,
                                                                                     T ey,
                                                                                     T hx,
                                                                                     T hy,
                                                                                     T lv,
                                                                                     double mu)
```
    Compute position from equinoctial parameters.
    
    Type Parameters:
    
    T - type of the fiels elements
    
    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
    
    lv - v + ω + Ω true longitude argument (rad)
    
    mu - central attraction coefficient (m³/s²)
    
    Returns:
    
    position vector
  - 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)
  - 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 FieldEquinoctialOrbit<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 FieldEquinoctialOrbit<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 FieldEquinoctialOrbit<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 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 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,
                                  double 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 equinoctial parameters object.
    
    Overrides:
    
    toString in class Object
    
    Returns:
    
    a string representation of this object
  - normalizeAngle
```
public static <T extends RealFieldElement<T>> T normalizeAngle(T a,
                                                               T center)
```
    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 EquinoctialOrbit 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 FieldEquinoctialOrbit<T extends RealFieldElement<T>>

Constructor Summary

Method Summary

Methods inherited from class org.orekit.orbits.FieldOrbit

Methods inherited from interface org.orekit.time.FieldTimeInterpolable

Methods inherited from class java.lang.Object

Constructor Detail

FieldEquinoctialOrbit

FieldEquinoctialOrbit

FieldEquinoctialOrbit

FieldEquinoctialOrbit

FieldEquinoctialOrbit

Method Detail

getType

getA

getADot

getEquinoctialEx

getEquinoctialExDot

getEquinoctialEy

getEquinoctialEyDot

getHx

getHxDot

getHy

getHyDot

getLv

getLvDot

getLE

getLEDot

getLM

getLMDot

getL

getLDot

hasDerivatives

eccentricToTrue

trueToEccentric

meanToEccentric

eccentricToMean

equinoctialToPosition

getE

getEDot

getI

getIDot

initPVCoordinates

shiftedBy

shiftedBy

interpolate

computeJacobianMeanWrtCartesian

computeJacobianEccentricWrtCartesian

computeJacobianTrueWrtCartesian

addKeplerContribution

toString

normalizeAngle

toOrbit