java.lang.Object
- org.orekit.orbits.Orbit

All Implemented Interfaces:

Serializable, TimeShiftable<Orbit>, TimeStamped, PVCoordinatesProvider

Direct Known Subclasses:

CartesianOrbit, CircularOrbit, EquinoctialOrbit, KeplerianOrbit
```
public abstract class Orbit
extends Object
implements TimeStamped, TimeShiftable<Orbit>, Serializable, PVCoordinatesProvider
```
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.

Author:

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

See Also:

Serialized Form

Field Summary

Fields
Modifier and Type Field Description

protected static double TOLERANCE_POSITION_ANGLE_RATE
Absolute tolerance when checking if the rate of the position angle is Keplerian or not.

Constructor Summary

Constructors
Modifier	Constructor	Description
`protected`	`Orbit(Frame frame, AbsoluteDate date, double mu)`	Default constructor.
`protected`	`Orbit(TimeStampedPVCoordinates pvCoordinates, Frame frame, double mu)`	Set the orbit from Cartesian parameters.

Method Summary

All Methods Static Methods Instance Methods Abstract Methods Concrete Methods
Modifier and Type	Method	Description
`abstract void`	`addKeplerContribution(PositionAngleType type, double gm, double[] pDot)`	Add the contribution of the Keplerian motion to parameters derivatives
`protected abstract double[][]`	`computeJacobianEccentricWrtCartesian()`	Compute the Jacobian of the orbital parameters with eccentric angle with respect to the Cartesian parameters.
`protected abstract double[][]`	`computeJacobianMeanWrtCartesian()`	Compute the Jacobian of the orbital parameters with mean angle with respect to the Cartesian parameters.
`protected abstract double[][]`	`computeJacobianTrueWrtCartesian()`	Compute the Jacobian of the orbital parameters with true angle with respect to the Cartesian parameters.
`protected static void`	`fillHalfRow(double a, Vector3D v, double[] row, int j)`	Fill a Jacobian half row with a single vector.
`protected static void`	`fillHalfRow(double a1, Vector3D v1, double a2, Vector3D v2, double[] row, int j)`	Fill a Jacobian half row with a linear combination of vectors.
`protected static void`	`fillHalfRow(double a1, Vector3D v1, double a2, Vector3D v2, double a3, Vector3D v3, double[] row, int j)`	Fill a Jacobian half row with a linear combination of vectors.
`protected static void`	`fillHalfRow(double a1, Vector3D v1, double a2, Vector3D v2, double a3, Vector3D v3, double a4, Vector3D v4, double[] row, int j)`	Fill a Jacobian half row with a linear combination of vectors.
`protected static void`	`fillHalfRow(double a1, Vector3D v1, double a2, Vector3D v2, double a3, Vector3D v3, double a4, Vector3D v4, double a5, Vector3D v5, double[] row, int j)`	Fill a Jacobian half row with a linear combination of vectors.
`protected static void`	`fillHalfRow(double a1, Vector3D v1, double a2, Vector3D v2, double a3, Vector3D v3, double a4, Vector3D v4, double a5, Vector3D v5, double a6, Vector3D v6, double[] row, int j)`	Fill a Jacobian half row with a linear combination of vectors.
`abstract double`	`getA()`	Get the semi-major axis.
`abstract double`	`getADot()`	Get the semi-major axis derivative.
`AbsoluteDate`	`getDate()`	Get the date of orbital parameters.
`abstract double`	`getE()`	Get the eccentricity.
`abstract double`	`getEDot()`	Get the eccentricity derivative.
`abstract double`	`getEquinoctialEx()`	Get the first component of the equinoctial eccentricity vector.
`abstract double`	`getEquinoctialExDot()`	Get the first component of the equinoctial eccentricity vector derivative.
`abstract double`	`getEquinoctialEy()`	Get the second component of the equinoctial eccentricity vector.
`abstract double`	`getEquinoctialEyDot()`	Get the second component of the equinoctial eccentricity vector derivative.
`Frame`	`getFrame()`	Get the frame in which the orbital parameters are defined.
`abstract double`	`getHx()`	Get the first component of the inclination vector.
`abstract double`	`getHxDot()`	Get the first component of the inclination vector derivative.
`abstract double`	`getHy()`	Get the second component of the inclination vector.
`abstract double`	`getHyDot()`	Get the second component of the inclination vector derivative.
`abstract double`	`getI()`	Get the inclination.
`abstract double`	`getIDot()`	Get the inclination derivative.
`void`	`getJacobianWrtCartesian(PositionAngleType type, double[][] jacobian)`	Compute the Jacobian of the orbital parameters with respect to the Cartesian parameters.
`void`	`getJacobianWrtParameters(PositionAngleType type, double[][] jacobian)`	Compute the Jacobian of the Cartesian parameters with respect to the orbital parameters.
`double`	`getKeplerianMeanMotion()`	Get the Keplerian mean motion.
`double`	`getKeplerianPeriod()`	Get the Keplerian period.
`abstract double`	`getLE()`	Get the eccentric longitude argument.
`abstract double`	`getLEDot()`	Get the eccentric longitude argument derivative.
`abstract double`	`getLM()`	Get the mean longitude argument.
`abstract double`	`getLMDot()`	Get the mean longitude argument derivative.
`abstract double`	`getLv()`	Get the true longitude argument.
`abstract double`	`getLvDot()`	Get the true longitude argument derivative.
`double`	`getMeanAnomalyDotWrtA()`	Get the derivative of the mean anomaly with respect to the semi major axis.
`double`	`getMu()`	Get the central acceleration constant.
`Vector3D`	`getPosition()`	Get the position in definition frame.
`Vector3D`	`getPosition(Frame outputFrame)`	Get the position in a specified frame.
`Vector3D`	`getPosition(AbsoluteDate otherDate, Frame otherFrame)`	Get the position of the body in the selected frame.
`TimeStampedPVCoordinates`	`getPVCoordinates()`	Get the `TimeStampedPVCoordinates` in definition frame.
`TimeStampedPVCoordinates`	`getPVCoordinates(Frame outputFrame)`	Get the `TimeStampedPVCoordinates` in a specified frame.
`TimeStampedPVCoordinates`	`getPVCoordinates(AbsoluteDate otherDate, Frame otherFrame)`	Get the `PVCoordinates` of the body in the selected frame.
`abstract OrbitType`	`getType()`	Get the orbit type.
`boolean`	`hasNonKeplerianAcceleration()`	Check if orbit includes non-Keplerian rates.
`protected static boolean`	`hasNonKeplerianAcceleration(PVCoordinates pva, double mu)`	Check if Cartesian coordinates include non-Keplerian acceleration.
`protected abstract Vector3D`	`initPosition()`	Compute the position coordinates from the canonical parameters.
`protected abstract TimeStampedPVCoordinates`	`initPVCoordinates()`	Compute the position/velocity coordinates from the canonical parameters.
`boolean`	`isElliptical()`	Returns true if and only if the orbit is elliptical i.e.
`abstract Orbit`	`shiftedBy(double dt)`	Get a time-shifted orbit.
`abstract Orbit`	`shiftedBy(TimeOffset dt)`	Get a time-shifted orbit.
`abstract Orbit`	`withFrame(Frame inertialFrame)`	Create a new object representing the same physical orbital state, but attached to a different reference frame.

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.TimeStamped
durationFrom

- Field Detail
  - TOLERANCE_POSITION_ANGLE_RATE
```
protected static final double TOLERANCE_POSITION_ANGLE_RATE
```
    Absolute tolerance when checking if the rate of the position angle is Keplerian or not.
    
    See Also:
    
    Constant Field Values
- Constructor Detail
  - Orbit
```
protected Orbit(Frame frame,
                AbsoluteDate date,
                double 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
  - Orbit
```
protected Orbit(TimeStampedPVCoordinates pvCoordinates,
                Frame frame,
                double mu)
         throws IllegalArgumentException
```
    Set the orbit from Cartesian parameters.
    The acceleration provided in pvCoordinates is accessible using getPVCoordinates() and getPVCoordinates(Frame). All other methods use mu and the position to compute the acceleration, including shiftedBy(double) and getPVCoordinates(AbsoluteDate, Frame).
    
    Parameters:
    
    pvCoordinates - 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 boolean hasNonKeplerianAcceleration(PVCoordinates pva,
                                                     double mu)
```
    Check if Cartesian coordinates include non-Keplerian acceleration.
    
    Parameters:
    
    pva - Cartesian coordinates
    
    mu - central attraction coefficient
    
    Returns:
    
    true if Cartesian coordinates include non-Keplerian acceleration
  - isElliptical
```
public boolean isElliptical()
```
    Returns true if and only if the orbit is elliptical i.e. has a non-negative semi-major axis.
    
    Returns:
    
    true if getA() is strictly greater than 0
    
    Since:
    
    12.0
  - 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
  - getA
```
public abstract double 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 double 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 Double.NaN.
    
    Returns:
    
    semi-major axis derivative (m/s)
    
    Since:
    
    9.0
  - getEquinoctialEx
```
public abstract double getEquinoctialEx()
```
    Get the first component of the equinoctial eccentricity vector.
    
    Returns:
    
    first component of the equinoctial eccentricity vector
  - getEquinoctialExDot
```
public abstract double getEquinoctialExDot()
```
    Get the first component of the equinoctial eccentricity vector derivative.
    If the orbit was created without derivatives, the value returned is Double.NaN.
    
    Returns:
    
    first component of the equinoctial eccentricity vector derivative
    
    Since:
    
    9.0
  - getEquinoctialEy
```
public abstract double getEquinoctialEy()
```
    Get the second component of the equinoctial eccentricity vector.
    
    Returns:
    
    second component of the equinoctial eccentricity vector
  - getEquinoctialEyDot
```
public abstract double getEquinoctialEyDot()
```
    Get the second component of the equinoctial eccentricity vector derivative.
    If the orbit was created without derivatives, the value returned is Double.NaN.
    
    Returns:
    
    second component of the equinoctial eccentricity vector derivative
    
    Since:
    
    9.0
  - getHx
```
public abstract double getHx()
```
    Get the first component of the inclination vector.
    
    Returns:
    
    first component of the inclination vector
  - getHxDot
```
public abstract double getHxDot()
```
    Get the first component of the inclination vector derivative.
    If the orbit was created without derivatives, the value returned is Double.NaN.
    
    Returns:
    
    first component of the inclination vector derivative
    
    Since:
    
    9.0
  - getHy
```
public abstract double getHy()
```
    Get the second component of the inclination vector.
    
    Returns:
    
    second component of the inclination vector
  - getHyDot
```
public abstract double getHyDot()
```
    Get the second component of the inclination vector derivative.
    If the orbit was created without derivatives, the value returned is Double.NaN.
    
    Returns:
    
    second component of the inclination vector derivative
    
    Since:
    
    9.0
  - getLE
```
public abstract double getLE()
```
    Get the eccentric longitude argument.
    
    Returns:
    
    E + ω + Ω eccentric longitude argument (rad)
  - getLEDot
```
public abstract double getLEDot()
```
    Get the eccentric longitude argument derivative.
    If the orbit was created without derivatives, the value returned is Double.NaN.
    
    Returns:
    
    d(E + ω + Ω)/dt eccentric longitude argument derivative (rad/s)
    
    Since:
    
    9.0
  - getLv
```
public abstract double getLv()
```
    Get the true longitude argument.
    
    Returns:
    
    v + ω + Ω true longitude argument (rad)
  - getLvDot
```
public abstract double getLvDot()
```
    Get the true longitude argument derivative.
    If the orbit was created without derivatives, the value returned is Double.NaN.
    
    Returns:
    
    d(v + ω + Ω)/dt true longitude argument derivative (rad/s)
    
    Since:
    
    9.0
  - getLM
```
public abstract double getLM()
```
    Get the mean longitude argument.
    
    Returns:
    
    M + ω + Ω mean longitude argument (rad)
  - getLMDot
```
public abstract double getLMDot()
```
    Get the mean longitude argument derivative.
    If the orbit was created without derivatives, the value returned is Double.NaN.
    
    Returns:
    
    d(M + ω + Ω)/dt mean longitude argument derivative (rad/s)
    
    Since:
    
    9.0
  - getE
```
public abstract double getE()
```
    Get the eccentricity.
    
    Returns:
    
    eccentricity
  - getEDot
```
public abstract double getEDot()
```
    Get the eccentricity derivative.
    If the orbit was created without derivatives, the value returned is Double.NaN.
    
    Returns:
    
    eccentricity derivative
    
    Since:
    
    9.0
  - getI
```
public abstract double getI()
```
    Get the inclination.
    
    Returns:
    
    inclination (rad)
  - getIDot
```
public abstract double getIDot()
```
    Get the inclination derivative.
    If the orbit was created without derivatives, the value returned is Double.NaN.
    
    Returns:
    
    inclination derivative (rad/s)
    
    Since:
    
    9.0
  - hasNonKeplerianAcceleration
```
public boolean hasNonKeplerianAcceleration()
```
    Check if orbit includes non-Keplerian rates.
    
    Returns:
    
    true if orbit includes non-Keplerian derivatives
    
    Since:
    
    13.0
    
    See Also:
    
    getADot(), getEquinoctialExDot(), getEquinoctialEyDot(), getHxDot(), getHyDot(), getLEDot(), getLvDot(), getLMDot(), getEDot(), getIDot()
  - getMu
```
public double getMu()
```
    Get the central acceleration constant.
    
    Returns:
    
    central acceleration constant
  - getKeplerianPeriod
```
public double 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 double 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
  - getMeanAnomalyDotWrtA
```
public double getMeanAnomalyDotWrtA()
```
    Get the derivative of the mean anomaly with respect to the semi major axis.
    
    Returns:
    
    derivative of the mean anomaly with respect to the semi major axis
  - getDate
```
public AbsoluteDate getDate()
```
    Get the date of orbital parameters.
    
    Specified by:
    
    getDate in interface TimeStamped
    
    Returns:
    
    date of the orbital parameters
  - getPVCoordinates
```
public TimeStampedPVCoordinates getPVCoordinates(Frame outputFrame)
```
    Get the TimeStampedPVCoordinates in a specified frame.
    
    Parameters:
    
    outputFrame - frame in which the position/velocity coordinates shall be computed
    
    Returns:
    
    pvCoordinates in the specified output frame
    
    See Also:
    
    getPVCoordinates()
  - getPVCoordinates
```
public TimeStampedPVCoordinates getPVCoordinates(AbsoluteDate otherDate,
                                                 Frame otherFrame)
```
    Get the PVCoordinates of the body in the selected frame.
    
    Specified by:
    
    getPVCoordinates in interface PVCoordinatesProvider
    
    Parameters:
    
    otherDate - current date
    
    otherFrame - the frame where to define the position
    
    Returns:
    
    time-stamped position/velocity of the body (m and m/s)
  - getPosition
```
public Vector3D getPosition(AbsoluteDate otherDate,
                            Frame otherFrame)
```
    Get the position of the body in the selected frame.
    
    Specified by:
    
    getPosition in interface PVCoordinatesProvider
    
    Parameters:
    
    otherDate - current date
    
    otherFrame - the frame where to define the position
    
    Returns:
    
    position of the body (m and)
  - getPosition
```
public Vector3D getPosition(Frame outputFrame)
```
    Get the position in a specified frame.
    
    Parameters:
    
    outputFrame - frame in which the position coordinates shall be computed
    
    Returns:
    
    position in the specified output frame
    
    Since:
    
    12.0
    
    See Also:
    
    getPosition()
  - getPosition
```
public Vector3D getPosition()
```
    Get the position in definition frame.
    
    Returns:
    
    position in the definition frame
    
    Since:
    
    12.0
    
    See Also:
    
    getPVCoordinates()
  - getPVCoordinates
```
public TimeStampedPVCoordinates getPVCoordinates()
```
    Get the TimeStampedPVCoordinates in definition frame.
    
    Returns:
    
    pvCoordinates in the definition frame
    
    See Also:
    
    getPVCoordinates(Frame)
  - initPosition
```
protected abstract Vector3D initPosition()
```
    Compute the position coordinates from the canonical parameters.
    
    Returns:
    
    computed position coordinates
    
    Since:
    
    12.0
  - initPVCoordinates
```
protected abstract TimeStampedPVCoordinates initPVCoordinates()
```
    Compute the position/velocity coordinates from the canonical parameters.
    
    Returns:
    
    computed position/velocity coordinates
  - withFrame
```
public abstract Orbit withFrame(Frame inertialFrame)
```
    Create a new object representing the same physical orbital state, but attached to a different reference frame. If the new frame is not inertial, an exception will be thrown.
    
    Parameters:
    
    inertialFrame - reference frame of output orbit
    
    Returns:
    
    orbit with different frame
    
    Since:
    
    13.0
  - shiftedBy
```
public abstract Orbit shiftedBy(double dt)
```
    Get a time-shifted orbit.
    The orbit can be slightly shifted to close dates. The shifting model is a Keplerian one if no derivatives are available in the orbit, or Keplerian plus quadratic effect of the non-Keplerian acceleration if derivatives are available. Shifting is not intended as a replacement for proper orbit propagation but should be sufficient for small time shifts or coarse accuracy.
    
    Specified by:
    
    shiftedBy in interface TimeShiftable<Orbit>
    
    Parameters:
    
    dt - time shift in seconds
    
    Returns:
    
    a new orbit, shifted with respect to the instance (which is immutable)
  - shiftedBy
```
public abstract Orbit shiftedBy(TimeOffset dt)
```
    Get a time-shifted orbit.
    The orbit can be slightly shifted to close dates. The shifting model is a Keplerian one if no derivatives are available in the orbit, or Keplerian plus quadratic effect of the non-Keplerian acceleration if derivatives are available. Shifting is not intended as a replacement for proper orbit propagation but should be sufficient for small time shifts or coarse accuracy.
    
    Specified by:
    
    shiftedBy in interface TimeShiftable<Orbit>
    
    Parameters:
    
    dt - time shift
    
    Returns:
    
    a new orbit, shifted with respect to the instance (which is immutable)
  - getJacobianWrtCartesian
```
public void getJacobianWrtCartesian(PositionAngleType type,
                                    double[][] 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(PositionAngleType type,
                                     double[][] 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 double[][] 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.
    
    The array returned by this method will not be modified.
    
    Returns:
    
    6x6 Jacobian matrix
    
    See Also:
    
    computeJacobianEccentricWrtCartesian(), computeJacobianTrueWrtCartesian()
  - computeJacobianEccentricWrtCartesian
```
protected abstract double[][] 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.
    
    The array returned by this method will not be modified.
    
    Returns:
    
    6x6 Jacobian matrix
    
    See Also:
    
    computeJacobianMeanWrtCartesian(), computeJacobianTrueWrtCartesian()
  - computeJacobianTrueWrtCartesian
```
protected abstract double[][] 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.
    
    The array returned by this method will not be modified.
    
    Returns:
    
    6x6 Jacobian matrix
    
    See Also:
    
    computeJacobianMeanWrtCartesian(), computeJacobianEccentricWrtCartesian()
  - addKeplerContribution
```
public abstract void addKeplerContribution(PositionAngleType type,
                                           double gm,
                                           double[] 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 static void fillHalfRow(double a,
                                  Vector3D v,
                                  double[] 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 static void fillHalfRow(double a1,
                                  Vector3D v1,
                                  double a2,
                                  Vector3D v2,
                                  double[] 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 static void fillHalfRow(double a1,
                                  Vector3D v1,
                                  double a2,
                                  Vector3D v2,
                                  double a3,
                                  Vector3D v3,
                                  double[] 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 static void fillHalfRow(double a1,
                                  Vector3D v1,
                                  double a2,
                                  Vector3D v2,
                                  double a3,
                                  Vector3D v3,
                                  double a4,
                                  Vector3D v4,
                                  double[] 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 static void fillHalfRow(double a1,
                                  Vector3D v1,
                                  double a2,
                                  Vector3D v2,
                                  double a3,
                                  Vector3D v3,
                                  double a4,
                                  Vector3D v4,
                                  double a5,
                                  Vector3D v5,
                                  double[] 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 static void fillHalfRow(double a1,
                                  Vector3D v1,
                                  double a2,
                                  Vector3D v2,
                                  double a3,
                                  Vector3D v3,
                                  double a4,
                                  Vector3D v4,
                                  double a5,
                                  Vector3D v5,
                                  double a6,
                                  Vector3D v6,
                                  double[] 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 Orbit

Field Summary

Constructor Summary

Method Summary

Methods inherited from class java.lang.Object

Methods inherited from interface org.orekit.time.TimeStamped

Field Detail

TOLERANCE_POSITION_ANGLE_RATE

Constructor Detail

Orbit

Orbit

Method Detail

hasNonKeplerianAcceleration

isElliptical

getType

getFrame

getA

getADot

getEquinoctialEx

getEquinoctialExDot

getEquinoctialEy

getEquinoctialEyDot

getHx

getHxDot

getHy

getHyDot

getLE

getLEDot

getLv

getLvDot

getLM

getLMDot

getE

getEDot

getI

getIDot

hasNonKeplerianAcceleration

getMu

getKeplerianPeriod

getKeplerianMeanMotion

getMeanAnomalyDotWrtA

getDate

getPVCoordinates

getPVCoordinates

getPosition

getPosition

getPosition

getPVCoordinates

initPosition

initPVCoordinates

withFrame

shiftedBy

shiftedBy

getJacobianWrtCartesian

getJacobianWrtParameters

computeJacobianMeanWrtCartesian

computeJacobianEccentricWrtCartesian

computeJacobianTrueWrtCartesian

addKeplerContribution

fillHalfRow

fillHalfRow

fillHalfRow

fillHalfRow

fillHalfRow

fillHalfRow