FieldEquinoctialOrbit (OREKIT 12.0.1 API)

java.lang.Object
- org.orekit.orbits.FieldOrbit<T>
- - org.orekit.orbits.FieldEquinoctialOrbit<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 FieldEquinoctialOrbit<T extends org.hipparchus.CalculusFieldElement<T>>
extends FieldOrbit<T>
implements PositionAngleBased
```
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. Note however than the present implementation does not handle non-elliptical cases.

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 and Description
`FieldEquinoctialOrbit(org.hipparchus.Field<T> field, EquinoctialOrbit op)` Constructor from Field and EquinoctialOrbit.
`FieldEquinoctialOrbit(org.hipparchus.Field<T> field, Orbit op)` Constructor from Field and Orbit.
`FieldEquinoctialOrbit(FieldOrbit<T> op)` Constructor from any kind of orbital parameters.
`FieldEquinoctialOrbit(FieldPVCoordinates<T> pvCoordinates, Frame frame, FieldAbsoluteDate<T> date, T mu)` Constructor from Cartesian parameters.
`FieldEquinoctialOrbit(TimeStampedFieldPVCoordinates<T> pvCoordinates, Frame frame, T mu)` Constructor from Cartesian parameters.
`FieldEquinoctialOrbit(T a, T ex, T ey, T hx, T hy, T l, PositionAngleType type, Frame frame, FieldAbsoluteDate<T> date, T 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, PositionAngleType type, Frame frame, FieldAbsoluteDate<T> date, T mu)` Creates a new instance.

Method Summary

All Methods Static Methods Instance Methods Concrete Methods
Modifier and Type	Method and 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.
`static <T extends org.hipparchus.CalculusFieldElement<T>> T`	`eccentricToMean(T lE, T ex, T ey)` Computes the mean longitude argument from the eccentric longitude argument.
`static <T extends org.hipparchus.CalculusFieldElement<T>> T`	`eccentricToTrue(T lE, T ex, T ey)` Computes the true longitude argument from the eccentric longitude argument.
`T`	`getA()` Get the semi-major axis.
`T`	`getADot()` Get the semi-major axis derivative.
`PositionAngleType`	`getCachedPositionAngleType()` Get the cached `PositionAngleType`.
`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(PositionAngleType type)` Get the longitude argument.
`T`	`getLDot(PositionAngleType 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.
`boolean`	`hasRates()` Tells whether the instance holds rates (first-order time derivatives) for dependent variables.
`protected org.hipparchus.geometry.euclidean.threed.FieldVector3D<T>`	`initPosition()` Compute the position coordinates from the canonical parameters.
`protected TimeStampedFieldPVCoordinates<T>`	`initPVCoordinates()` Compute the position/velocity coordinates from the canonical parameters.
`static <T extends org.hipparchus.CalculusFieldElement<T>> T`	`meanToEccentric(T lM, T ex, T ey)` Computes the eccentric longitude argument from the mean longitude argument.
`FieldEquinoctialOrbit<T>`	`removeRates()` Create a new instance such that `PositionAngleBased.hasRates()` is false.
`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 org.hipparchus.CalculusFieldElement<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, getField, getFrame, getJacobianWrtCartesian, getJacobianWrtParameters, getKeplerianMeanMotion, getKeplerianPeriod, getMeanAnomalyDotWrtA, getMu, getOne, 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.utils.FieldPVCoordinatesProvider
getPosition

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

- Constructor Detail
  - FieldEquinoctialOrbit
```
public FieldEquinoctialOrbit(T a,
                             T ex,
                             T ey,
                             T hx,
                             T hy,
                             T l,
                             PositionAngleType type,
                             Frame frame,
                             FieldAbsoluteDate<T> date,
                             T 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,
                             PositionAngleType type,
                             Frame frame,
                             FieldAbsoluteDate<T> date,
                             T 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,
                             T 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(CalculusFieldElement) 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,
                             T 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(CalculusFieldElement) 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
  - FieldEquinoctialOrbit
```
public FieldEquinoctialOrbit(org.hipparchus.Field<T> field,
                             EquinoctialOrbit op)
```
    Constructor from Field and EquinoctialOrbit.
    Build a FieldEquinoctialOrbit from non-Field EquinoctialOrbit.
    
    Parameters:
    
    field - CalculusField to base object on
    
    op - non-field orbit with only "constant" terms
    
    Since:
    
    12.0
  - FieldEquinoctialOrbit
```
public FieldEquinoctialOrbit(org.hipparchus.Field<T> field,
                             Orbit op)
```
    Constructor from Field and Orbit.
    Build a FieldEquinoctialOrbit 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 org.hipparchus.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 org.hipparchus.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 org.hipparchus.CalculusFieldElement<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 org.hipparchus.CalculusFieldElement<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 org.hipparchus.CalculusFieldElement<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 org.hipparchus.CalculusFieldElement<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 org.hipparchus.CalculusFieldElement<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 org.hipparchus.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 org.hipparchus.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 org.hipparchus.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 org.hipparchus.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 org.hipparchus.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 org.hipparchus.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 org.hipparchus.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 org.hipparchus.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 org.hipparchus.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 org.hipparchus.CalculusFieldElement<T>>
    
    Returns:
    
    d(M + ω + Ω)/dt mean longitude argument derivative (rad/s)
  - getL
```
public T getL(PositionAngleType type)
```
    Get the longitude argument.
    
    Parameters:
    
    type - type of the angle
    
    Returns:
    
    longitude argument (rad)
  - getLDot
```
public T getLDot(PositionAngleType 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 org.hipparchus.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()
  - eccentricToTrue
```
public static <T extends org.hipparchus.CalculusFieldElement<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 org.hipparchus.CalculusFieldElement<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 org.hipparchus.CalculusFieldElement<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 org.hipparchus.CalculusFieldElement<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
  - getE
```
public T getE()
```
    Get the eccentricity.
    
    Specified by:
    
    getE in class FieldOrbit<T extends org.hipparchus.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 org.hipparchus.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 org.hipparchus.CalculusFieldElement<T>>
    
    Returns:
    
    inclination (rad)
  - getIDot
```
public T getIDot()
```
    Get the inclination derivative.
    
    Specified by:
    
    getIDot in class FieldOrbit<T extends org.hipparchus.CalculusFieldElement<T>>
    
    Returns:
    
    inclination derivative (rad/s)
  - initPosition
```
protected org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> initPosition()
```
    Compute the position coordinates from the canonical parameters.
    
    Specified by:
    
    initPosition in class FieldOrbit<T extends org.hipparchus.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 org.hipparchus.CalculusFieldElement<T>>
    
    Returns:
    
    computed position/velocity coordinates
  - shiftedBy
```
public FieldEquinoctialOrbit<T> shiftedBy(double dt)
```
    Get a time-shifted instance.
    
    Specified by:
    
    shiftedBy in interface TimeShiftable<FieldOrbit<T extends org.hipparchus.CalculusFieldElement<T>>>
    
    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 org.hipparchus.CalculusFieldElement<T>>,T extends org.hipparchus.CalculusFieldElement<T>>
    
    Specified by:
    
    shiftedBy in class FieldOrbit<T extends org.hipparchus.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 org.hipparchus.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 org.hipparchus.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 org.hipparchus.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 org.hipparchus.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 equinoctial 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 FieldEquinoctialOrbit<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 EquinoctialOrbit toOrbit()
```
    Transforms the FieldOrbit instance into an Orbit instance.
    
    Specified by:
    
    toOrbit in class FieldOrbit<T extends org.hipparchus.CalculusFieldElement<T>>
    
    Returns:
    
    Orbit instance with same properties

Class FieldEquinoctialOrbit<T extends org.hipparchus.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.utils.FieldPVCoordinatesProvider

Methods inherited from interface org.orekit.time.FieldTimeStamped

Constructor Detail

FieldEquinoctialOrbit

FieldEquinoctialOrbit

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

getE

getEDot

getI

getIDot

initPosition

initPVCoordinates

shiftedBy

shiftedBy

computeJacobianMeanWrtCartesian

computeJacobianEccentricWrtCartesian

computeJacobianTrueWrtCartesian

addKeplerContribution

toString

getCachedPositionAngleType

hasRates

removeRates

toOrbit