FieldOrbit (ORbit Extrapolation KIT 10.2 API)

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

All Implemented Interfaces:

FieldTimeInterpolable<FieldOrbit<T>,T>, FieldTimeShiftable<FieldOrbit<T>,T>, FieldTimeStamped<T>, FieldPVCoordinatesProvider<T>

Direct Known Subclasses:

FieldCartesianOrbit, FieldCircularOrbit, FieldEquinoctialOrbit, FieldKeplerianOrbit
```
public abstract class FieldOrbit<T extends RealFieldElement<T>>
extends Object
implements FieldPVCoordinatesProvider<T>, FieldTimeStamped<T>, FieldTimeShiftable<FieldOrbit<T>,T>, FieldTimeInterpolable<FieldOrbit<T>,T>
```
This class handles orbital parameters.
For user convenience, both the Cartesian and the equinoctial elements are provided by this class, regardless of the canonical representation implemented in the derived class (which may be classical Keplerian elements for example).

The parameters are defined in a frame specified by the user. It is important to make sure this frame is consistent: it probably is inertial and centered on the central body. This information is used for example by some force models.

Instance of this class are guaranteed to be immutable.

Since:

9.0

Author:

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

Constructor Summary

Constructors
Modifier	Constructor and Description
`protected`	`FieldOrbit(Frame frame, FieldAbsoluteDate<T> date, T mu)` Default constructor.
`protected`	`FieldOrbit(TimeStampedFieldPVCoordinates<T> FieldPVCoordinates, Frame frame, T mu)` Set the orbit from Cartesian parameters.

Method Summary

All Methods Static Methods Instance Methods Abstract Methods Concrete Methods
Modifier and Type	Method and Description
`abstract void`	`addKeplerContribution(PositionAngle type, T gm, T[] pDot)` Add the contribution of the Keplerian motion to parameters derivatives
`protected abstract T[][]`	`computeJacobianEccentricWrtCartesian()` Compute the Jacobian of the orbital parameters with eccentric angle with respect to the Cartesian parameters.
`protected abstract T[][]`	`computeJacobianMeanWrtCartesian()` Compute the Jacobian of the orbital parameters with mean angle with respect to the Cartesian parameters.
`protected abstract T[][]`	`computeJacobianTrueWrtCartesian()` Compute the Jacobian of the orbital parameters with true angle with respect to the Cartesian parameters.
`protected void`	`fillHalfRow(T a, FieldVector3D<T> v, T[] row, int j)` Fill a Jacobian half row with a single vector.
`protected void`	`fillHalfRow(T a1, FieldVector3D<T> v1, T a2, FieldVector3D<T> v2, T[] row, int j)` Fill a Jacobian half row with a linear combination of vectors.
`protected void`	`fillHalfRow(T a1, FieldVector3D<T> v1, T a2, FieldVector3D<T> v2, T a3, FieldVector3D<T> v3, T[] row, int j)` Fill a Jacobian half row with a linear combination of vectors.
`protected void`	`fillHalfRow(T a1, FieldVector3D<T> v1, T a2, FieldVector3D<T> v2, T a3, FieldVector3D<T> v3, T a4, FieldVector3D<T> v4, T[] row, int j)` Fill a Jacobian half row with a linear combination of vectors.
`protected void`	`fillHalfRow(T a1, FieldVector3D<T> v1, T a2, FieldVector3D<T> v2, T a3, FieldVector3D<T> v3, T a4, FieldVector3D<T> v4, T a5, FieldVector3D<T> v5, T[] row, int j)` Fill a Jacobian half row with a linear combination of vectors.
`protected void`	`fillHalfRow(T a1, FieldVector3D<T> v1, T a2, FieldVector3D<T> v2, T a3, FieldVector3D<T> v3, T a4, FieldVector3D<T> v4, T a5, FieldVector3D<T> v5, T a6, FieldVector3D<T> v6, T[] row, int j)` Fill a Jacobian half row with a linear combination of vectors.
`abstract T`	`getA()` Get the semi-major axis.
`abstract T`	`getADot()` Get the semi-major axis derivative.
`FieldAbsoluteDate<T>`	`getDate()` Get the date of orbital parameters.
`abstract T`	`getE()` Get the eccentricity.
`abstract T`	`getEDot()` Get the eccentricity derivative.
`abstract T`	`getEquinoctialEx()` Get the first component of the equinoctial eccentricity vector.
`abstract T`	`getEquinoctialExDot()` Get the first component of the equinoctial eccentricity vector.
`abstract T`	`getEquinoctialEy()` Get the second component of the equinoctial eccentricity vector.
`abstract T`	`getEquinoctialEyDot()` Get the second component of the equinoctial eccentricity vector.
`Frame`	`getFrame()` Get the frame in which the orbital parameters are defined.
`abstract T`	`getHx()` Get the first component of the inclination vector.
`abstract T`	`getHxDot()` Get the first component of the inclination vector derivative.
`abstract T`	`getHy()` Get the second component of the inclination vector.
`abstract T`	`getHyDot()` Get the second component of the inclination vector derivative.
`abstract T`	`getI()` Get the inclination.
`abstract T`	`getIDot()` Get the inclination derivative.
`void`	`getJacobianWrtCartesian(PositionAngle type, T[][] jacobian)` Compute the Jacobian of the orbital parameters with respect to the Cartesian parameters.
`void`	`getJacobianWrtParameters(PositionAngle type, T[][] jacobian)` Compute the Jacobian of the Cartesian parameters with respect to the orbital parameters.
`T`	`getKeplerianMeanMotion()` Get the Keplerian mean motion.
`T`	`getKeplerianPeriod()` Get the Keplerian period.
`abstract T`	`getLE()` Get the eccentric longitude argument.
`abstract T`	`getLEDot()` Get the eccentric longitude argument derivative.
`abstract T`	`getLM()` Get the mean longitude argument.
`abstract T`	`getLMDot()` Get the mean longitude argument derivative.
`abstract T`	`getLv()` Get the true longitude argument.
`abstract T`	`getLvDot()` Get the true longitude argument derivative.
`T`	`getMu()` Get the central attraction coefficient used for position and velocity conversions (m³/s²).
`TimeStampedFieldPVCoordinates<T>`	`getPVCoordinates()` Get the `TimeStampedPVCoordinates` in definition frame.
`TimeStampedFieldPVCoordinates<T>`	`getPVCoordinates(FieldAbsoluteDate<T> otherDate, Frame otherFrame)` Get the `FieldPVCoordinates` of the body in the selected frame.
`TimeStampedFieldPVCoordinates<T>`	`getPVCoordinates(Frame outputFrame)` Get the `TimeStampedPVCoordinates` in a specified frame.
`abstract OrbitType`	`getType()` Get the orbit type.
`abstract boolean`	`hasDerivatives()` Check if orbit includes derivatives.
`protected static <T extends RealFieldElement<T>> boolean`	`hasNonKeplerianAcceleration(FieldPVCoordinates<T> pva, T mu)` Check if Cartesian coordinates include non-Keplerian acceleration.
`protected abstract TimeStampedFieldPVCoordinates<T>`	`initPVCoordinates()` Compute the position/velocity coordinates from the canonical parameters.
`abstract FieldOrbit<T>`	`shiftedBy(T dt)` Get a time-shifted orbit.
`abstract Orbit`	`toOrbit()` Transforms the FieldOrbit instance into an Orbit instance.

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

Methods inherited from interface org.orekit.time.FieldTimeShiftable
shiftedBy

Methods inherited from interface org.orekit.time.FieldTimeInterpolable
interpolate, interpolate

- Constructor Detail
  - FieldOrbit
```
protected FieldOrbit(Frame frame,
                     FieldAbsoluteDate<T> date,
                     T mu)
              throws IllegalArgumentException
```
    Default constructor. Build a new instance with arbitrary default elements.
    
    Parameters:
    
    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 (m^3/s^2)
    
    Throws:
    
    IllegalArgumentException - if frame is not a pseudo-inertial frame
  - FieldOrbit
```
protected FieldOrbit(TimeStampedFieldPVCoordinates<T> FieldPVCoordinates,
                     Frame frame,
                     T mu)
              throws IllegalArgumentException
```
    Set the orbit from Cartesian parameters.
    The acceleration provided in FieldPVCoordinates is accessible using getPVCoordinates() and getPVCoordinates(Frame). All other methods use mu and the position to compute the acceleration, including shiftedBy(RealFieldElement) and getPVCoordinates(FieldAbsoluteDate, Frame).
    
    Parameters:
    
    FieldPVCoordinates - the position and velocity in the inertial frame
    
    frame - the frame in which the TimeStampedPVCoordinates are defined (must be a pseudo-inertial frame)
    
    mu - central attraction coefficient (m^3/s^2)
    
    Throws:
    
    IllegalArgumentException - if frame is not a pseudo-inertial frame
- Method Detail
  - hasNonKeplerianAcceleration
```
protected static <T extends RealFieldElement<T>> boolean hasNonKeplerianAcceleration(FieldPVCoordinates<T> pva,
                                                                                     T mu)
```
    Check if Cartesian coordinates include non-Keplerian acceleration.
    
    Type Parameters:
    
    T - type of the field elements
    
    Parameters:
    
    pva - Cartesian coordinates
    
    mu - central attraction coefficient
    
    Returns:
    
    true if Cartesian coordinates include non-Keplerian acceleration
  - getType
```
public abstract OrbitType getType()
```
    Get the orbit type.
    
    Returns:
    
    orbit type
  - getFrame
```
public Frame getFrame()
```
    Get the frame in which the orbital parameters are defined.
    
    Returns:
    
    frame in which the orbital parameters are defined
  - toOrbit
```
public abstract Orbit toOrbit()
```
    Transforms the FieldOrbit instance into an Orbit instance.
    
    Returns:
    
    Orbit instance with same properties
  - getA
```
public abstract T getA()
```
    Get the semi-major axis.
    Note that the semi-major axis is considered negative for hyperbolic orbits.
    
    Returns:
    
    semi-major axis (m)
  - getADot
```
public abstract 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.
    
    Returns:
    
    semi-major axis derivative (m/s)
  - getEquinoctialEx
```
public abstract T getEquinoctialEx()
```
    Get the first component of the equinoctial eccentricity vector.
    
    Returns:
    
    first component of the equinoctial eccentricity vector
  - getEquinoctialExDot
```
public abstract T getEquinoctialExDot()
```
    Get the first component of the equinoctial eccentricity vector.
    If the orbit was created without derivatives, the value returned is null.
    
    Returns:
    
    first component of the equinoctial eccentricity vector
  - getEquinoctialEy
```
public abstract T getEquinoctialEy()
```
    Get the second component of the equinoctial eccentricity vector.
    
    Returns:
    
    second component of the equinoctial eccentricity vector
  - getEquinoctialEyDot
```
public abstract T getEquinoctialEyDot()
```
    Get the second component of the equinoctial eccentricity vector.
    If the orbit was created without derivatives, the value returned is null.
    
    Returns:
    
    second component of the equinoctial eccentricity vector
  - getHx
```
public abstract T getHx()
```
    Get the first component of the inclination vector.
    
    Returns:
    
    first component of the inclination vector
  - getHxDot
```
public abstract T getHxDot()
```
    Get the first component of the inclination vector derivative.
    If the orbit was created without derivatives, the value returned is null.
    
    Returns:
    
    first component of the inclination vector derivative
  - getHy
```
public abstract T getHy()
```
    Get the second component of the inclination vector.
    
    Returns:
    
    second component of the inclination vector
  - getHyDot
```
public abstract T getHyDot()
```
    Get the second component of the inclination vector derivative.
    
    Returns:
    
    second component of the inclination vector derivative
  - getLE
```
public abstract T getLE()
```
    Get the eccentric longitude argument.
    
    Returns:
    
    E + ω + Ω eccentric longitude argument (rad)
  - getLEDot
```
public abstract T getLEDot()
```
    Get the eccentric longitude argument derivative.
    If the orbit was created without derivatives, the value returned is null.
    
    Returns:
    
    d(E + ω + Ω)/dt eccentric longitude argument derivative (rad/s)
  - getLv
```
public abstract T getLv()
```
    Get the true longitude argument.
    
    Returns:
    
    v + ω + Ω true longitude argument (rad)
  - getLvDot
```
public abstract T getLvDot()
```
    Get the true longitude argument derivative.
    If the orbit was created without derivatives, the value returned is null.
    
    Returns:
    
    d(v + ω + Ω)/dt true longitude argument derivative (rad/s)
  - getLM
```
public abstract T getLM()
```
    Get the mean longitude argument.
    
    Returns:
    
    M + ω + Ω mean longitude argument (rad)
  - getLMDot
```
public abstract T getLMDot()
```
    Get the mean longitude argument derivative.
    If the orbit was created without derivatives, the value returned is null.
    
    Returns:
    
    d(M + ω + Ω)/dt mean longitude argument derivative (rad/s)
  - getE
```
public abstract T getE()
```
    Get the eccentricity.
    
    Returns:
    
    eccentricity
  - getEDot
```
public abstract T getEDot()
```
    Get the eccentricity derivative.
    If the orbit was created without derivatives, the value returned is null.
    
    Returns:
    
    eccentricity derivative
  - getI
```
public abstract T getI()
```
    Get the inclination.
    If the orbit was created without derivatives, the value returned is null.
    
    Returns:
    
    inclination (rad)
  - getIDot
```
public abstract T getIDot()
```
    Get the inclination derivative.
    
    Returns:
    
    inclination derivative (rad/s)
  - hasDerivatives
```
public abstract boolean hasDerivatives()
```
    Check if orbit includes derivatives.
    
    Returns:
    
    true if orbit includes derivatives
    
    Since:
    
    9.0
    
    See Also:
    
    getADot(), getEquinoctialExDot(), getEquinoctialEyDot(), getHxDot(), getHyDot(), getLEDot(), getLvDot(), getLMDot(), getEDot(), getIDot()
  - getMu
```
public T getMu()
```
    Get the central attraction coefficient used for position and velocity conversions (m³/s²).
    
    Returns:
    
    central attraction coefficient used for position and velocity conversions (m³/s²)
  - getKeplerianPeriod
```
public T getKeplerianPeriod()
```
    Get the Keplerian period.
    The Keplerian period is computed directly from semi major axis and central acceleration constant.
    
    Returns:
    
    Keplerian period in seconds, or positive infinity for hyperbolic orbits
  - getKeplerianMeanMotion
```
public T getKeplerianMeanMotion()
```
    Get the Keplerian mean motion.
    The Keplerian mean motion is computed directly from semi major axis and central acceleration constant.
    
    Returns:
    
    Keplerian mean motion in radians per second
  - getDate
```
public FieldAbsoluteDate<T> getDate()
```
    Get the date of orbital parameters.
    
    Specified by:
    
    getDate in interface FieldTimeStamped<T extends RealFieldElement<T>>
    
    Returns:
    
    date of the orbital parameters
  - getPVCoordinates
```
public TimeStampedFieldPVCoordinates<T> getPVCoordinates(Frame outputFrame)
```
    Get the TimeStampedPVCoordinates in a specified frame.
    
    Parameters:
    
    outputFrame - frame in which the position/velocity coordinates shall be computed
    
    Returns:
    
    FieldPVCoordinates in the specified output frame
    
    See Also:
    
    getPVCoordinates()
  - getPVCoordinates
```
public TimeStampedFieldPVCoordinates<T> getPVCoordinates(FieldAbsoluteDate<T> otherDate,
                                                         Frame otherFrame)
```
    Get the FieldPVCoordinates of the body in the selected frame.
    
    Specified by:
    
    getPVCoordinates in interface FieldPVCoordinatesProvider<T extends RealFieldElement<T>>
    
    Parameters:
    
    otherDate - current date
    
    otherFrame - the frame where to define the position
    
    Returns:
    
    time-stamped position/velocity of the body (m and m/s)
  - getPVCoordinates
```
public TimeStampedFieldPVCoordinates<T> getPVCoordinates()
```
    Get the TimeStampedPVCoordinates in definition frame.
    
    Returns:
    
    FieldPVCoordinates in the definition frame
    
    See Also:
    
    getPVCoordinates(Frame)
  - initPVCoordinates
```
protected abstract TimeStampedFieldPVCoordinates<T> initPVCoordinates()
```
    Compute the position/velocity coordinates from the canonical parameters.
    
    Returns:
    
    computed position/velocity coordinates
  - shiftedBy
```
public abstract FieldOrbit<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>>
    
    Parameters:
    
    dt - time shift in seconds
    
    Returns:
    
    a new orbit, shifted with respect to the instance (which is immutable)
  - getJacobianWrtCartesian
```
public void getJacobianWrtCartesian(PositionAngle type,
                                    T[][] jacobian)
```
    Compute the Jacobian of the orbital parameters 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 corresponds to one orbital parameter whereas columns 0 to 5 correspond to the Cartesian coordinates x, y, z, xDot, yDot and zDot.
    
    Parameters:
    
    type - type of the position angle to use
    
    jacobian - placeholder 6x6 (or larger) matrix to be filled with the Jacobian, if matrix is larger than 6x6, only the 6x6 upper left corner will be modified
  - getJacobianWrtParameters
```
public void getJacobianWrtParameters(PositionAngle type,
                                     T[][] jacobian)
```
    Compute the Jacobian of the Cartesian parameters with respect to the orbital parameters.
    Element jacobian[i][j] is the derivative of Cartesian coordinate i of the orbit with respect to orbital parameter j. This means each row corresponds to one Cartesian coordinate x, y, z, xdot, ydot, zdot whereas columns 0 to 5 correspond to the orbital parameters.
    
    Parameters:
    
    type - type of the position angle to use
    
    jacobian - placeholder 6x6 (or larger) matrix to be filled with the Jacobian, if matrix is larger than 6x6, only the 6x6 upper left corner will be modified
  - computeJacobianMeanWrtCartesian
```
protected abstract 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.
    
    Returns:
    
    6x6 Jacobian matrix
    
    See Also:
    
    computeJacobianEccentricWrtCartesian(), computeJacobianTrueWrtCartesian()
  - computeJacobianEccentricWrtCartesian
```
protected abstract 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.
    
    Returns:
    
    6x6 Jacobian matrix
    
    See Also:
    
    computeJacobianMeanWrtCartesian(), computeJacobianTrueWrtCartesian()
  - computeJacobianTrueWrtCartesian
```
protected abstract 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.
    
    Returns:
    
    6x6 Jacobian matrix
    
    See Also:
    
    computeJacobianMeanWrtCartesian(), computeJacobianEccentricWrtCartesian()
  - addKeplerContribution
```
public abstract void addKeplerContribution(PositionAngle type,
                                           T gm,
                                           T[] pDot)
```
    Add the contribution of the Keplerian motion to parameters derivatives
    This method is used by integration-based propagators to evaluate the part of Keplerian motion to evolution of the orbital state.
    
    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)
  - fillHalfRow
```
protected void fillHalfRow(T a,
                           FieldVector3D<T> v,
                           T[] row,
                           int j)
```
    Fill a Jacobian half row with a single vector.
    
    Parameters:
    
    a - coefficient of the vector
    
    v - vector
    
    row - Jacobian matrix row
    
    j - index of the first element to set (row[j], row[j+1] and row[j+2] will all be set)
  - fillHalfRow
```
protected void fillHalfRow(T a1,
                           FieldVector3D<T> v1,
                           T a2,
                           FieldVector3D<T> v2,
                           T[] row,
                           int j)
```
    Fill a Jacobian half row with a linear combination of vectors.
    
    Parameters:
    
    a1 - coefficient of the first vector
    
    v1 - first vector
    
    a2 - coefficient of the second vector
    
    v2 - second vector
    
    row - Jacobian matrix row
    
    j - index of the first element to set (row[j], row[j+1] and row[j+2] will all be set)
  - fillHalfRow
```
protected void fillHalfRow(T a1,
                           FieldVector3D<T> v1,
                           T a2,
                           FieldVector3D<T> v2,
                           T a3,
                           FieldVector3D<T> v3,
                           T[] row,
                           int j)
```
    Fill a Jacobian half row with a linear combination of vectors.
    
    Parameters:
    
    a1 - coefficient of the first vector
    
    v1 - first vector
    
    a2 - coefficient of the second vector
    
    v2 - second vector
    
    a3 - coefficient of the third vector
    
    v3 - third vector
    
    row - Jacobian matrix row
    
    j - index of the first element to set (row[j], row[j+1] and row[j+2] will all be set)
  - fillHalfRow
```
protected void fillHalfRow(T a1,
                           FieldVector3D<T> v1,
                           T a2,
                           FieldVector3D<T> v2,
                           T a3,
                           FieldVector3D<T> v3,
                           T a4,
                           FieldVector3D<T> v4,
                           T[] row,
                           int j)
```
    Fill a Jacobian half row with a linear combination of vectors.
    
    Parameters:
    
    a1 - coefficient of the first vector
    
    v1 - first vector
    
    a2 - coefficient of the second vector
    
    v2 - second vector
    
    a3 - coefficient of the third vector
    
    v3 - third vector
    
    a4 - coefficient of the fourth vector
    
    v4 - fourth vector
    
    row - Jacobian matrix row
    
    j - index of the first element to set (row[j], row[j+1] and row[j+2] will all be set)
  - fillHalfRow
```
protected void fillHalfRow(T a1,
                           FieldVector3D<T> v1,
                           T a2,
                           FieldVector3D<T> v2,
                           T a3,
                           FieldVector3D<T> v3,
                           T a4,
                           FieldVector3D<T> v4,
                           T a5,
                           FieldVector3D<T> v5,
                           T[] row,
                           int j)
```
    Fill a Jacobian half row with a linear combination of vectors.
    
    Parameters:
    
    a1 - coefficient of the first vector
    
    v1 - first vector
    
    a2 - coefficient of the second vector
    
    v2 - second vector
    
    a3 - coefficient of the third vector
    
    v3 - third vector
    
    a4 - coefficient of the fourth vector
    
    v4 - fourth vector
    
    a5 - coefficient of the fifth vector
    
    v5 - fifth vector
    
    row - Jacobian matrix row
    
    j - index of the first element to set (row[j], row[j+1] and row[j+2] will all be set)
  - fillHalfRow
```
protected void fillHalfRow(T a1,
                           FieldVector3D<T> v1,
                           T a2,
                           FieldVector3D<T> v2,
                           T a3,
                           FieldVector3D<T> v3,
                           T a4,
                           FieldVector3D<T> v4,
                           T a5,
                           FieldVector3D<T> v5,
                           T a6,
                           FieldVector3D<T> v6,
                           T[] row,
                           int j)
```
    Fill a Jacobian half row with a linear combination of vectors.
    
    Parameters:
    
    a1 - coefficient of the first vector
    
    v1 - first vector
    
    a2 - coefficient of the second vector
    
    v2 - second vector
    
    a3 - coefficient of the third vector
    
    v3 - third vector
    
    a4 - coefficient of the fourth vector
    
    v4 - fourth vector
    
    a5 - coefficient of the fifth vector
    
    v5 - fifth vector
    
    a6 - coefficient of the sixth vector
    
    v6 - sixth vector
    
    row - Jacobian matrix row
    
    j - index of the first element to set (row[j], row[j+1] and row[j+2] will all be set)

Class FieldOrbit<T extends RealFieldElement<T>>

Constructor Summary

Method Summary

Methods inherited from class java.lang.Object

Methods inherited from interface org.orekit.time.FieldTimeShiftable

Methods inherited from interface org.orekit.time.FieldTimeInterpolable

Constructor Detail

FieldOrbit

FieldOrbit

Method Detail

hasNonKeplerianAcceleration

getType

getFrame

toOrbit

getA

getADot

getEquinoctialEx

getEquinoctialExDot

getEquinoctialEy

getEquinoctialEyDot

getHx

getHxDot

getHy

getHyDot

getLE

getLEDot

getLv

getLvDot

getLM

getLMDot

getE

getEDot

getI

getIDot

hasDerivatives

getMu

getKeplerianPeriod

getKeplerianMeanMotion

getDate

getPVCoordinates

getPVCoordinates

getPVCoordinates

initPVCoordinates

shiftedBy

getJacobianWrtCartesian

getJacobianWrtParameters

computeJacobianMeanWrtCartesian

computeJacobianEccentricWrtCartesian

computeJacobianTrueWrtCartesian

addKeplerContribution

fillHalfRow

fillHalfRow

fillHalfRow

fillHalfRow

fillHalfRow

fillHalfRow