Class CircularOrbit
- java.lang.Object
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- org.orekit.orbits.Orbit
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- org.orekit.orbits.CircularOrbit
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- All Implemented Interfaces:
Serializable
,PositionAngleBased
,TimeShiftable<Orbit>
,TimeStamped
,PVCoordinatesProvider
public class CircularOrbit extends Orbit implements PositionAngleBased
This class handles circular orbital parameters.The parameters used internally are the circular elements which can be related to Keplerian elements as follows:
- a
- ex = e cos(ω)
- ey = e sin(ω)
- i
- Ω
- αv = v + ω
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 circular (but not equatorial), the circular parameters are still unambiguously defined whereas some Keplerian elements (more precisely ω and Ω) become ambiguous. When orbit is equatorial, neither the Keplerian nor the circular parameters can be defined unambiguously.
equinoctial orbits
is the recommended way to represent orbits.The instance
CircularOrbit
is guaranteed to be immutable.- Author:
- Luc Maisonobe, Fabien Maussion, Véronique Pommier-Maurussane
- See Also:
Orbit
,KeplerianOrbit
,CartesianOrbit
,EquinoctialOrbit
, Serialized Form
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Constructor Summary
Constructors Constructor Description CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, double aDot, double exDot, double eyDot, double iDot, double raanDot, double alphaDot, PositionAngleType type, Frame frame, AbsoluteDate date, double mu)
Creates a new instance with derivatives and with cached position angle same as value inputted.CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, double aDot, double exDot, double eyDot, double iDot, double raanDot, double alphaDot, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, AbsoluteDate date, double mu)
Creates a new instance.CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, PositionAngleType type, Frame frame, AbsoluteDate date, double mu)
Creates a new instance without derivatives and with cached position angle same as value inputted.CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, AbsoluteDate date, double mu)
Creates a new instance.CircularOrbit(Orbit op)
Constructor from any kind of orbital parameters.CircularOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu)
Constructor from Cartesian parameters.CircularOrbit(TimeStampedPVCoordinates pvCoordinates, Frame frame, double mu)
Constructor from Cartesian parameters.
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Method Summary
All Methods Static Methods Instance Methods Concrete Methods Deprecated Methods Modifier and Type Method Description void
addKeplerContribution(PositionAngleType type, double gm, double[] pDot)
Add the contribution of the Keplerian motion to parameters derivativesprotected double[][]
computeJacobianEccentricWrtCartesian()
Compute the Jacobian of the orbital parameters with eccentric angle with respect to the Cartesian parameters.protected double[][]
computeJacobianMeanWrtCartesian()
Compute the Jacobian of the orbital parameters with mean angle with respect to the Cartesian parameters.protected double[][]
computeJacobianTrueWrtCartesian()
Compute the Jacobian of the orbital parameters with true angle with respect to the Cartesian parameters.static double
eccentricToMean(double alphaE, double ex, double ey)
Deprecated.static double
eccentricToTrue(double alphaE, double ex, double ey)
Deprecated.double
getA()
Get the semi-major axis.double
getADot()
Get the semi-major axis derivative.double
getAlpha(PositionAngleType type)
Get the latitude argument.double
getAlphaDot(PositionAngleType type)
Get the latitude argument derivative.double
getAlphaE()
Get the eccentric latitude argument.double
getAlphaEDot()
Get the eccentric latitude argument derivative.double
getAlphaM()
Get the mean latitude argument.double
getAlphaMDot()
Get the mean latitude argument derivative.double
getAlphaV()
Get the true latitude argument.double
getAlphaVDot()
Get the true latitude argument derivative.PositionAngleType
getCachedPositionAngleType()
Get the cachedPositionAngleType
.double
getCircularEx()
Get the first component of the circular eccentricity vector.double
getCircularExDot()
Get the first component of the circular eccentricity vector derivative.double
getCircularEy()
Get the second component of the circular eccentricity vector.double
getCircularEyDot()
Get the second component of the circular eccentricity vector derivative.double
getE()
Get the eccentricity.double
getEDot()
Get the eccentricity derivative.double
getEquinoctialEx()
Get the first component of the equinoctial eccentricity vector.double
getEquinoctialExDot()
Get the first component of the equinoctial eccentricity vector derivative.double
getEquinoctialEy()
Get the second component of the equinoctial eccentricity vector.double
getEquinoctialEyDot()
Get the second component of the equinoctial eccentricity vector derivative.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.double
getRightAscensionOfAscendingNode()
Get the right ascension of the ascending node.double
getRightAscensionOfAscendingNodeDot()
Get the right ascension of the ascending node derivative.OrbitType
getType()
Get the orbit type.boolean
hasRates()
Tells whether the instance holds rates (first-order time derivatives) for dependent variables.protected Vector3D
initPosition()
Compute the position coordinates from the canonical parameters.protected TimeStampedPVCoordinates
initPVCoordinates()
Compute the position/velocity coordinates from the canonical parameters.static double
meanToEccentric(double alphaM, double ex, double ey)
Deprecated.CircularOrbit
removeRates()
Create a new instance such thatPositionAngleBased.hasRates()
is false.CircularOrbit
shiftedBy(double dt)
Get a time-shifted orbit.String
toString()
Returns a string representation of this Orbit object.static double
trueToEccentric(double alphaV, double ex, double ey)
Deprecated.-
Methods inherited from class org.orekit.orbits.Orbit
fillHalfRow, fillHalfRow, fillHalfRow, fillHalfRow, fillHalfRow, fillHalfRow, getDate, getFrame, getJacobianWrtCartesian, getJacobianWrtParameters, getKeplerianMeanMotion, getKeplerianPeriod, getMeanAnomalyDotWrtA, getMu, getPosition, getPosition, getPosition, getPVCoordinates, getPVCoordinates, getPVCoordinates, hasDerivatives, hasNonKeplerianAcceleration, isElliptical
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Methods inherited from class java.lang.Object
clone, equals, finalize, getClass, hashCode, notify, notifyAll, wait, wait, wait
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Methods inherited from interface org.orekit.time.TimeStamped
durationFrom
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Constructor Detail
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CircularOrbit
public CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, AbsoluteDate date, double mu) throws IllegalArgumentException
Creates a new instance.- Parameters:
a
- semi-major axis (m)ex
- e cos(ω), first component of circular eccentricity vectorey
- e sin(ω), second component of circular eccentricity vectori
- inclination (rad)raan
- right ascension of ascending node (Ω, rad)alpha
- an + ω, mean, eccentric or true latitude argument (rad)type
- type of latitude argumentcachedPositionAngleType
- type of cached latitude argumentframe
- the frame in which are defined the parameters (must be apseudo-inertial frame
)date
- date of the orbital parametersmu
- central attraction coefficient (m³/s²)- Throws:
IllegalArgumentException
- if eccentricity is equal to 1 or larger or if frame is not apseudo-inertial frame
- Since:
- 12.1
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CircularOrbit
public CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, PositionAngleType type, Frame frame, AbsoluteDate date, double mu) throws IllegalArgumentException
Creates a new instance without derivatives and with cached position angle same as value inputted.- Parameters:
a
- semi-major axis (m)ex
- e cos(ω), first component of circular eccentricity vectorey
- e sin(ω), second component of circular eccentricity vectori
- inclination (rad)raan
- right ascension of ascending node (Ω, rad)alpha
- an + ω, mean, eccentric or true latitude argument (rad)type
- type of latitude argumentframe
- the frame in which are defined the parameters (must be apseudo-inertial frame
)date
- date of the orbital parametersmu
- central attraction coefficient (m³/s²)- Throws:
IllegalArgumentException
- if eccentricity is equal to 1 or larger or if frame is not apseudo-inertial frame
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CircularOrbit
public CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, double aDot, double exDot, double eyDot, double iDot, double raanDot, double alphaDot, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, AbsoluteDate date, double mu) throws IllegalArgumentException
Creates a new instance.- Parameters:
a
- semi-major axis (m)ex
- e cos(ω), first component of circular eccentricity vectorey
- e sin(ω), second component of circular eccentricity vectori
- inclination (rad)raan
- right ascension of ascending node (Ω, rad)alpha
- an + ω, mean, eccentric or true latitude argument (rad)aDot
- semi-major axis derivative (m/s)exDot
- d(e cos(ω))/dt, first component of circular eccentricity vector derivativeeyDot
- d(e sin(ω))/dt, second component of circular eccentricity vector derivativeiDot
- inclination derivative(rad/s)raanDot
- right ascension of ascending node derivative (rad/s)alphaDot
- d(an + ω), mean, eccentric or true latitude argument derivative (rad/s)type
- type of latitude argumentcachedPositionAngleType
- type of cached latitude argumentframe
- the frame in which are defined the parameters (must be apseudo-inertial frame
)date
- date of the orbital parametersmu
- central attraction coefficient (m³/s²)- Throws:
IllegalArgumentException
- if eccentricity is equal to 1 or larger or if frame is not apseudo-inertial frame
- Since:
- 12.1
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CircularOrbit
public CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, double aDot, double exDot, double eyDot, double iDot, double raanDot, double alphaDot, PositionAngleType type, Frame frame, AbsoluteDate date, double mu) throws IllegalArgumentException
Creates a new instance with derivatives and with cached position angle same as value inputted.- Parameters:
a
- semi-major axis (m)ex
- e cos(ω), first component of circular eccentricity vectorey
- e sin(ω), second component of circular eccentricity vectori
- inclination (rad)raan
- right ascension of ascending node (Ω, rad)alpha
- an + ω, mean, eccentric or true latitude argument (rad)aDot
- semi-major axis derivative (m/s)exDot
- d(e cos(ω))/dt, first component of circular eccentricity vector derivativeeyDot
- d(e sin(ω))/dt, second component of circular eccentricity vector derivativeiDot
- inclination derivative(rad/s)raanDot
- right ascension of ascending node derivative (rad/s)alphaDot
- d(an + ω), mean, eccentric or true latitude argument derivative (rad/s)type
- type of latitude argumentframe
- the frame in which are defined the parameters (must be apseudo-inertial frame
)date
- date of the orbital parametersmu
- central attraction coefficient (m³/s²)- Throws:
IllegalArgumentException
- if eccentricity is equal to 1 or larger or if frame is not apseudo-inertial frame
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CircularOrbit
public CircularOrbit(TimeStampedPVCoordinates pvCoordinates, Frame frame, double mu) throws IllegalArgumentException
Constructor 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
- thePVCoordinates
in inertial frameframe
- the frame in which are defined thePVCoordinates
(must be apseudo-inertial frame
)mu
- central attraction coefficient (m³/s²)- Throws:
IllegalArgumentException
- if frame is not apseudo-inertial frame
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CircularOrbit
public CircularOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu) throws IllegalArgumentException
Constructor 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
- thePVCoordinates
in inertial frameframe
- the frame in which are defined thePVCoordinates
(must be apseudo-inertial frame
)date
- date of the orbital parametersmu
- central attraction coefficient (m³/s²)- Throws:
IllegalArgumentException
- if frame is not apseudo-inertial frame
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CircularOrbit
public CircularOrbit(Orbit op)
Constructor from any kind of orbital parameters.- Parameters:
op
- orbital parameters to copy
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Method Detail
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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)
- See Also:
Orbit.hasDerivatives()
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getEquinoctialEx
public double getEquinoctialEx()
Get the first component of the equinoctial eccentricity vector.- Specified by:
getEquinoctialEx
in classOrbit
- Returns:
- first component of the equinoctial eccentricity vector
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getEquinoctialExDot
public 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
.- Specified by:
getEquinoctialExDot
in classOrbit
- Returns:
- first component of the equinoctial eccentricity vector derivative
- See Also:
Orbit.hasDerivatives()
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getEquinoctialEy
public double getEquinoctialEy()
Get the second component of the equinoctial eccentricity vector.- Specified by:
getEquinoctialEy
in classOrbit
- Returns:
- second component of the equinoctial eccentricity vector
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getEquinoctialEyDot
public 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
.- Specified by:
getEquinoctialEyDot
in classOrbit
- Returns:
- second component of the equinoctial eccentricity vector derivative
- See Also:
Orbit.hasDerivatives()
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getCircularEx
public double getCircularEx()
Get the first component of the circular eccentricity vector.- Returns:
- ex = e cos(ω), first component of the circular eccentricity vector
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getCircularExDot
public double getCircularExDot()
Get the first component of the circular eccentricity vector derivative.- Returns:
- ex = e cos(ω), first component of the circular eccentricity vector derivative
- Since:
- 9.0
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getCircularEy
public double getCircularEy()
Get the second component of the circular eccentricity vector.- Returns:
- ey = e sin(ω), second component of the circular eccentricity vector
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getCircularEyDot
public double getCircularEyDot()
Get the second component of the circular eccentricity vector derivative.- Returns:
- ey = e sin(ω), second component of the circular eccentricity vector derivative
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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
- 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
- See Also:
Orbit.hasDerivatives()
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getAlphaV
public double getAlphaV()
Get the true latitude argument.- Returns:
- v + ω true latitude argument (rad)
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getAlphaVDot
public double getAlphaVDot()
Get the true latitude argument derivative.If the orbit was created without derivatives, the value returned is
Double.NaN
.- Returns:
- v + ω true latitude argument derivative (rad/s)
- Since:
- 9.0
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getAlphaE
public double getAlphaE()
Get the eccentric latitude argument.- Returns:
- E + ω eccentric latitude argument (rad)
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getAlphaEDot
public double getAlphaEDot()
Get the eccentric latitude argument derivative.If the orbit was created without derivatives, the value returned is
Double.NaN
.- Returns:
- d(E + ω)/dt eccentric latitude argument derivative (rad/s)
- Since:
- 9.0
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getAlphaM
public double getAlphaM()
Get the mean latitude argument.- Returns:
- M + ω mean latitude argument (rad)
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getAlphaMDot
public double getAlphaMDot()
Get the mean latitude argument derivative.If the orbit was created without derivatives, the value returned is
Double.NaN
.- Returns:
- d(M + ω)/dt mean latitude argument derivative (rad/s)
- Since:
- 9.0
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getAlpha
public double getAlpha(PositionAngleType type)
Get the latitude argument.- Parameters:
type
- type of the angle- Returns:
- latitude argument (rad)
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getAlphaDot
public double getAlphaDot(PositionAngleType type)
Get the latitude argument derivative.If the orbit was created without derivatives, the value returned is
Double.NaN
.- Parameters:
type
- type of the angle- Returns:
- latitude argument derivative (rad/s)
- Since:
- 9.0
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eccentricToTrue
@Deprecated public static double eccentricToTrue(double alphaE, double ex, double ey)
Deprecated.Computes the true latitude argument from the eccentric latitude argument.- Parameters:
alphaE
- = E + ω eccentric latitude argument (rad)ex
- e cos(ω), first component of circular eccentricity vectorey
- e sin(ω), second component of circular eccentricity vector- Returns:
- the true latitude argument.
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trueToEccentric
@Deprecated public static double trueToEccentric(double alphaV, double ex, double ey)
Deprecated.Computes the eccentric latitude argument from the true latitude argument.- Parameters:
alphaV
- = V + ω true latitude argument (rad)ex
- e cos(ω), first component of circular eccentricity vectorey
- e sin(ω), second component of circular eccentricity vector- Returns:
- the eccentric latitude argument.
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meanToEccentric
@Deprecated public static double meanToEccentric(double alphaM, double ex, double ey)
Deprecated.Computes the eccentric latitude argument from the mean latitude argument.- Parameters:
alphaM
- = M + ω mean latitude argument (rad)ex
- e cos(ω), first component of circular eccentricity vectorey
- e sin(ω), second component of circular eccentricity vector- Returns:
- the eccentric latitude argument.
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eccentricToMean
@Deprecated public static double eccentricToMean(double alphaE, double ex, double ey)
Deprecated.Computes the mean latitude argument from the eccentric latitude argument.- Parameters:
alphaE
- = E + ω mean latitude argument (rad)ex
- e cos(ω), first component of circular eccentricity vectorey
- e sin(ω), second component of circular eccentricity vector- Returns:
- the mean latitude argument.
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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
- 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)
- See Also:
Orbit.hasDerivatives()
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getRightAscensionOfAscendingNode
public double getRightAscensionOfAscendingNode()
Get the right ascension of the ascending node.- Returns:
- right ascension of the ascending node (rad)
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getRightAscensionOfAscendingNodeDot
public double getRightAscensionOfAscendingNodeDot()
Get the right ascension of the ascending node derivative.If the orbit was created without derivatives, the value returned is
Double.NaN
.- Returns:
- right ascension of the ascending node derivative (rad/s)
- Since:
- 9.0
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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)
- 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)
- 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)
- See Also:
Orbit.hasDerivatives()
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initPosition
protected Vector3D initPosition()
Compute the position coordinates from the canonical parameters.- Specified by:
initPosition
in classOrbit
- Returns:
- computed position coordinates
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initPVCoordinates
protected 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 CircularOrbit 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
protected 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.
- Specified by:
computeJacobianMeanWrtCartesian
in classOrbit
- Returns:
- 6x6 Jacobian matrix
- See Also:
Orbit.computeJacobianEccentricWrtCartesian()
,Orbit.computeJacobianTrueWrtCartesian()
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computeJacobianEccentricWrtCartesian
protected 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.
- Specified by:
computeJacobianEccentricWrtCartesian
in classOrbit
- Returns:
- 6x6 Jacobian matrix
- See Also:
Orbit.computeJacobianMeanWrtCartesian()
,Orbit.computeJacobianTrueWrtCartesian()
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computeJacobianTrueWrtCartesian
protected 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.
- Specified by:
computeJacobianTrueWrtCartesian
in classOrbit
- Returns:
- 6x6 Jacobian matrix
- See Also:
Orbit.computeJacobianMeanWrtCartesian()
,Orbit.computeJacobianEccentricWrtCartesian()
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addKeplerContribution
public void addKeplerContribution(PositionAngleType type, double gm, double[] pDot)
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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toString
public String toString()
Returns a string representation of this Orbit object.
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getCachedPositionAngleType
public PositionAngleType getCachedPositionAngleType()
Get the cachedPositionAngleType
.- Specified by:
getCachedPositionAngleType
in interfacePositionAngleBased
- Returns:
- cached type of position angle
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hasRates
public boolean hasRates()
Tells whether the instance holds rates (first-order time derivatives) for dependent variables.- Specified by:
hasRates
in interfacePositionAngleBased
- Returns:
- true if and only if holding rates
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removeRates
public CircularOrbit removeRates()
Create a new instance such thatPositionAngleBased.hasRates()
is false.- Specified by:
removeRates
in interfacePositionAngleBased
- Returns:
- new object without rates
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