Class CartesianOrbit
- java.lang.Object
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- org.orekit.orbits.Orbit
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- org.orekit.orbits.CartesianOrbit
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- All Implemented Interfaces:
Serializable
,TimeShiftable<Orbit>
,TimeStamped
,PVCoordinatesProvider
public class CartesianOrbit extends Orbit
This class holds Cartesian orbital parameters.The parameters used internally are the Cartesian coordinates:
- x
- y
- z
- xDot
- yDot
- zDot
PVCoordinates
.Note that the implementation of this class delegates all non-Cartesian related computations (
getA()
,getEquinoctialEx()
, ...) to an underlying instance of theEquinoctialOrbit
class. This implies that using this class only for analytical computations which are always based on non-Cartesian parameters is perfectly possible but somewhat sub-optimal.The instance
CartesianOrbit
is guaranteed to be immutable.- Author:
- Luc Maisonobe, Guylaine Prat, Fabien Maussion, Véronique Pommier-Maurussane, Andrew Goetz
- See Also:
Orbit
,KeplerianOrbit
,CircularOrbit
,EquinoctialOrbit
, Serialized Form
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Constructor Summary
Constructors Constructor Description CartesianOrbit(Orbit op)
Constructor from any kind of orbital parameters.CartesianOrbit(PVCoordinates pvaCoordinates, Frame frame, AbsoluteDate date, double mu)
Constructor from Cartesian parameters.CartesianOrbit(TimeStampedPVCoordinates pvaCoordinates, Frame frame, double mu)
Constructor 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 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.double
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.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.OrbitType
getType()
Get the orbit type.boolean
hasDerivatives()
Check if orbit includes derivatives.protected Vector3D
initPosition()
Compute the position coordinates from the canonical parameters.protected TimeStampedPVCoordinates
initPVCoordinates()
Compute the position/velocity coordinates from the canonical parameters.CartesianOrbit
shiftedBy(double dt)
Get a time-shifted orbit.String
toString()
Returns a string representation of this Orbit object.-
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, 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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CartesianOrbit
public CartesianOrbit(TimeStampedPVCoordinates pvaCoordinates, 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:
pvaCoordinates
- the position, velocity and acceleration of the satellite.frame
- the frame in which thePVCoordinates
are defined (must be apseudo-inertial frame
)mu
- central attraction coefficient (m³/s²)- Throws:
IllegalArgumentException
- if frame is not apseudo-inertial frame
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CartesianOrbit
public CartesianOrbit(PVCoordinates pvaCoordinates, 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:
pvaCoordinates
- the position and velocity of the satellite.frame
- the frame in which thePVCoordinates
are defined (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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CartesianOrbit
public CartesianOrbit(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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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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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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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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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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hasDerivatives
public boolean hasDerivatives()
Check if orbit includes derivatives.- Overrides:
hasDerivatives
in classOrbit
- Returns:
- true if orbit includes derivatives
- See Also:
Orbit.getADot()
,Orbit.getEquinoctialExDot()
,Orbit.getEquinoctialEyDot()
,Orbit.getHxDot()
,Orbit.getHyDot()
,Orbit.getLEDot()
,Orbit.getLvDot()
,Orbit.getLMDot()
,Orbit.getEDot()
,Orbit.getIDot()
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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 CartesianOrbit 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()
Description copied from class:Orbit
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()
Description copied from class:Orbit
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()
Description copied from class:Orbit
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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