Class PythonOrbit
- java.lang.Object
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- org.orekit.orbits.Orbit
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- org.orekit.orbits.PythonOrbit
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- All Implemented Interfaces:
Serializable
,TimeShiftable<Orbit>
,TimeStamped
,PVCoordinatesProvider
public class PythonOrbit extends Orbit
- See Also:
- Serialized Form
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Constructor Summary
Constructors Constructor Description PythonOrbit(Frame frame, AbsoluteDate date, double mu)
Default constructor.PythonOrbit(TimeStampedPVCoordinates pvCoordinates, Frame frame, double mu)
Set the orbit from Cartesian parameters.
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Method Summary
All Methods Instance Methods Concrete Methods Modifier and Type Method Description void
addKeplerContribution(PositionAngleType type, double gm, double[] pDot)
Add the contribution of the Keplerian motion to parameters derivativesdouble[][]
computeJacobianEccentricWrtCartesian()
Compute the Jacobian of the orbital parameters with eccentric angle with respect to the Cartesian parameters.double[][]
computeJacobianMeanWrtCartesian()
Compute the Jacobian of the orbital parameters with mean angle with respect to the Cartesian parameters.double[][]
computeJacobianTrueWrtCartesian()
Compute the Jacobian of the orbital parameters with true angle with respect to the Cartesian parameters.void
finalize()
Part of JCC Python interface to objectdouble
getA()
Get the semi-major axis.double
getADot()
Get the semi-major axis derivative.double
getE()
Get the eccentricity.double
getEDot()
Get the eccentricity derivative.double
getEquinoctialEx()
Get the first component of the equinoctial eccentricity vector derivative.double
getEquinoctialExDot()
Get the first component of the equinoctial eccentricity vector.double
getEquinoctialEy()
Get the second component of the equinoctial eccentricity vector derivative.double
getEquinoctialEyDot()
Get the second component of the equinoctial eccentricity vector.double
getHx()
Get the first component of the inclination vector.double
getHxDot()
Get the first component of the inclination vector derivative.double
getHy()
Get the second component of the inclination vector.double
getHyDot()
Get the second component of the inclination vector derivative.double
getI()
Get the inclination.double
getIDot()
Get the inclination derivative.double
getLE()
Get the eccentric longitude argument.double
getLEDot()
Get the eccentric longitude argument derivative.double
getLM()
Get the mean longitude argument.double
getLMDot()
Get the mean longitude argument derivative.double
getLv()
Get the true longitude argument.double
getLvDot()
Get the true longitude argument derivative.OrbitType
getType()
Get the orbit type.Vector3D
initPosition()
Compute the position coordinates from the canonical parameters.TimeStampedPVCoordinates
initPVCoordinates()
Compute the position/velocity coordinates from the canonical parameters.void
pythonDecRef()
Part of JCC Python interface to objectlong
pythonExtension()
Part of JCC Python interface to objectvoid
pythonExtension(long pythonObject)
Part of JCC Python interface to objectOrbit
shiftedBy(double dt)
Get a time-shifted orbit.-
Methods inherited from class org.orekit.orbits.Orbit
fillHalfRow, fillHalfRow, fillHalfRow, fillHalfRow, fillHalfRow, fillHalfRow, getDate, getFrame, getJacobianWrtCartesian, getJacobianWrtParameters, getKeplerianMeanMotion, getKeplerianPeriod, getMeanAnomalyDotWrtA, getMu, getPosition, getPosition, getPVCoordinates, getPVCoordinates, getPVCoordinates, hasDerivatives, hasNonKeplerianAcceleration, isElliptical
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Methods inherited from class java.lang.Object
clone, equals, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait
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Methods inherited from interface org.orekit.utils.PVCoordinatesProvider
getPosition
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Methods inherited from interface org.orekit.time.TimeStamped
durationFrom
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Constructor Detail
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PythonOrbit
public PythonOrbit(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 apseudo-inertial frame
)date
- date of the orbital parametersmu
- central attraction coefficient (m^3/s^2)- Throws:
IllegalArgumentException
- if frame is not apseudo-inertial frame
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PythonOrbit
public PythonOrbit(TimeStampedPVCoordinates pvCoordinates, Frame frame, double mu) throws IllegalArgumentException
Set the orbit from Cartesian parameters.The acceleration provided in
pvCoordinates
is accessible usingOrbit.getPVCoordinates()
andOrbit.getPVCoordinates(Frame)
. All other methods usemu
and the position to compute the acceleration, includingshiftedBy(double)
andOrbit.getPVCoordinates(AbsoluteDate, Frame)
.- Parameters:
pvCoordinates
- the position and velocity in the inertial frameframe
- the frame in which theTimeStampedPVCoordinates
are defined (must be apseudo-inertial frame
)mu
- central attraction coefficient (m^3/s^2)- Throws:
IllegalArgumentException
- if frame is not apseudo-inertial frame
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Method Detail
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pythonExtension
public void pythonExtension(long pythonObject)
Part of JCC Python interface to object
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pythonExtension
public long pythonExtension()
Part of JCC Python interface to object
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finalize
public void finalize() throws Throwable
Part of JCC Python interface to object
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pythonDecRef
public void pythonDecRef()
Part of JCC Python interface to object
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getType
public OrbitType getType()
Get the orbit type.
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getA
public double getA()
Get the semi-major axis.Note that the semi-major axis is considered negative for hyperbolic orbits.
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getADot
public 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
.- Specified by:
getADot
in classOrbit
- Returns:
- semi-major axis derivative (m/s)
- Since:
- 9.0
- See Also:
Orbit.hasDerivatives()
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getEquinoctialEx
public double getEquinoctialEx()
Get the first component of the equinoctial eccentricity vector derivative.- Specified by:
getEquinoctialEx
in classOrbit
- Returns:
- first component of the equinoctial eccentricity vector derivative
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getEquinoctialExDot
public double getEquinoctialExDot()
Get the first component of the equinoctial eccentricity vector.If the orbit was created without derivatives, the value returned is
Double.NaN
.- Specified by:
getEquinoctialExDot
in classOrbit
- Returns:
- first component of the equinoctial eccentricity vector
- Since:
- 9.0
- See Also:
Orbit.hasDerivatives()
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getEquinoctialEy
public double getEquinoctialEy()
Get the second component of the equinoctial eccentricity vector derivative.- Specified by:
getEquinoctialEy
in classOrbit
- Returns:
- second component of the equinoctial eccentricity vector derivative
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getEquinoctialEyDot
public double getEquinoctialEyDot()
Get the second component of the equinoctial eccentricity vector.If the orbit was created without derivatives, the value returned is
Double.NaN
.- Specified by:
getEquinoctialEyDot
in classOrbit
- Returns:
- second component of the equinoctial eccentricity vector
- Since:
- 9.0
- See Also:
Orbit.hasDerivatives()
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getHx
public double getHx()
Get the first component of the inclination vector.
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getHxDot
public double getHxDot()
Get the first component of the inclination vector derivative.If the orbit was created without derivatives, the value returned is
Double.NaN
.- Specified by:
getHxDot
in classOrbit
- Returns:
- first component of the inclination vector derivative
- Since:
- 9.0
- See Also:
Orbit.hasDerivatives()
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getHy
public double getHy()
Get the second component of the inclination vector.
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getHyDot
public double getHyDot()
Get the second component of the inclination vector derivative.If the orbit was created without derivatives, the value returned is
Double.NaN
.- Specified by:
getHyDot
in classOrbit
- Returns:
- second component of the inclination vector derivative
- Since:
- 9.0
- See Also:
Orbit.hasDerivatives()
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getLE
public double getLE()
Get the eccentric longitude argument.
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getLEDot
public double getLEDot()
Get the eccentric longitude argument derivative.If the orbit was created without derivatives, the value returned is
Double.NaN
.- Specified by:
getLEDot
in classOrbit
- Returns:
- d(E + ω + Ω)/dt eccentric longitude argument derivative (rad/s)
- Since:
- 9.0
- See Also:
Orbit.hasDerivatives()
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getLv
public double getLv()
Get the true longitude argument.
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getLvDot
public double getLvDot()
Get the true longitude argument derivative.If the orbit was created without derivatives, the value returned is
Double.NaN
.- Specified by:
getLvDot
in classOrbit
- Returns:
- d(v + ω + Ω)/dt true longitude argument derivative (rad/s)
- Since:
- 9.0
- See Also:
Orbit.hasDerivatives()
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getLM
public double getLM()
Get the mean longitude argument.
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getLMDot
public double getLMDot()
Get the mean longitude argument derivative.If the orbit was created without derivatives, the value returned is
Double.NaN
.- Specified by:
getLMDot
in classOrbit
- Returns:
- d(M + ω + Ω)/dt mean longitude argument derivative (rad/s)
- Since:
- 9.0
- See Also:
Orbit.hasDerivatives()
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getE
public double getE()
Get the eccentricity.
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getEDot
public double getEDot()
Get the eccentricity derivative.If the orbit was created without derivatives, the value returned is
Double.NaN
.- Specified by:
getEDot
in classOrbit
- Returns:
- eccentricity derivative
- Since:
- 9.0
- See Also:
Orbit.hasDerivatives()
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getI
public double getI()
Get the inclination.
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getIDot
public double getIDot()
Get the inclination derivative.If the orbit was created without derivatives, the value returned is
Double.NaN
.- Specified by:
getIDot
in classOrbit
- Returns:
- inclination derivative (rad/s)
- Since:
- 9.0
- See Also:
Orbit.hasDerivatives()
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initPosition
public Vector3D initPosition()
Description copied from class:Orbit
Compute the position coordinates from the canonical parameters.- Specified by:
initPosition
in classOrbit
- Returns:
- computed position coordinates
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initPVCoordinates
public TimeStampedPVCoordinates initPVCoordinates()
Compute the position/velocity coordinates from the canonical parameters.- Specified by:
initPVCoordinates
in classOrbit
- Returns:
- computed position/velocity coordinates
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shiftedBy
public 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 interfaceTimeShiftable<Orbit>
- Specified by:
shiftedBy
in classOrbit
- Parameters:
dt
- time shift in seconds- Returns:
- a new orbit, shifted with respect to the instance (which is immutable)
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computeJacobianMeanWrtCartesian
public 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.- Specified by:
computeJacobianMeanWrtCartesian
in classOrbit
- Returns:
- 6x6 Jacobian matrix
- See Also:
computeJacobianEccentricWrtCartesian()
,computeJacobianTrueWrtCartesian()
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computeJacobianEccentricWrtCartesian
public 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.- Specified by:
computeJacobianEccentricWrtCartesian
in classOrbit
- Returns:
- 6x6 Jacobian matrix
- See Also:
computeJacobianMeanWrtCartesian()
,computeJacobianTrueWrtCartesian()
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computeJacobianTrueWrtCartesian
public 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.- Specified by:
computeJacobianTrueWrtCartesian
in classOrbit
- Returns:
- 6x6 Jacobian matrix
- See Also:
computeJacobianMeanWrtCartesian()
,computeJacobianEccentricWrtCartesian()
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addKeplerContribution
public void addKeplerContribution(PositionAngleType type, double gm, double[] pDot)
Description copied from class:Orbit
Add the contribution of the Keplerian motion to parameters derivativesThis method is used by integration-based propagators to evaluate the part of Keplerian motion to evolution of the orbital state.
- Specified by:
addKeplerContribution
in classOrbit
- Parameters:
type
- type of the position angle in the stategm
- attraction coefficient to usepDot
- 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)
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