Uses of Class
org.orekit.time.AbsoluteDate

Packages that use AbsoluteDate

Package	Description
org.orekit.attitudes	This package provides classes to represent simple attitudes.
org.orekit.bodies	This package provides interface to represent the position and geometry of space objects such as stars, planets or asteroids.
org.orekit.data	This package provide base classes for exploring the configured data directory tree and read external data that can be used by the library.
org.orekit.estimation.iod
org.orekit.estimation.measurements	The measurements package defines everything that is related to orbit determination measurements.
org.orekit.estimation.measurements.generation	This package provides Orbit Determination measurements generation.
org.orekit.estimation.sequential
org.orekit.files.ccsds	This package provides a parser for orbit data stored in CCSDS Orbit Data Message format.
org.orekit.files.general	This package provides interfaces for orbit file representations and corresponding parsers.
org.orekit.files.sp3	This package provides a parser for orbit data stored in SP3 format.
org.orekit.forces	This package provides the interface for force models that will be used by the NumericalPropagator, as well as some classical spacecraft models for surface forces (spherical, box and solar array ...).
org.orekit.forces.drag	This package provides all drag-related forces.
org.orekit.forces.drag.atmosphere	This package provides the atmosphere model interface and several implementations.
org.orekit.forces.drag.atmosphere.data	This package provides classes to get atmospheric data, including solar flux and planetary geomagnetic indices.
org.orekit.forces.gravity	This package provides all gravity-related forces.
org.orekit.forces.gravity.potential	This package provides classes to read gravity field files and supports several different formats.
org.orekit.forces.maneuvers	This package provides models of simple maneuvers.
org.orekit.forces.radiation	This package provides all radiation pressure related forces.
org.orekit.frames	This package provides classes to handle frames and transforms between them.
org.orekit.gnss	This package provides classes related to GNSS applications.
org.orekit.gnss.antenna	This package provides classes related to receiver and satellites antenna modeling.
org.orekit.gnss.attitude	This package provides classes related to navigation satellites attitude modeling.
org.orekit.models.earth	This package provides models that simulate certain physical phenomena of Earth and the near-Earth environment.
org.orekit.orbits	This package provides classes to represent orbits.
org.orekit.propagation	Propagation
org.orekit.propagation.analytical	Top level package for analytical propagators.
org.orekit.propagation.analytical.gnss	This package provides classes to propagate GNSS orbits.
org.orekit.propagation.analytical.tle	This package provides classes to read and extrapolate tle's.
org.orekit.propagation.conversion	This package provides tools to convert a given propagator or a set of SpacecraftState into another propagator.
org.orekit.propagation.events	This package provides interfaces and classes dealing with events occurring during propagation.
org.orekit.propagation.events.handlers	This package provides an interface and classes dealing with events occurrence only.
org.orekit.propagation.integration	Utilities for integration-based propagators (both numerical and semi-analytical).
org.orekit.propagation.numerical	Top level package for numerical propagators.
org.orekit.propagation.sampling	This package provides interfaces and classes dealing with step handling during propagation.
org.orekit.propagation.semianalytical.dsst	This package provides an implementation of the Draper Semi-analytical Satellite Theory (DSST).
org.orekit.propagation.semianalytical.dsst.forces	This package provides force models for Draper Semi-analytical Satellite Theory (DSST).
org.orekit.propagation.semianalytical.dsst.utilities	This package provides utilities for Draper Semi-analytical Satellite Theory (DSST).
org.orekit.time	This independent package provides classes to handle epochs, time scales, and to compare instants together.
org.orekit.utils	This package provides useful objects.

Uses of AbsoluteDate in org.orekit.attitudes

Methods in org.orekit.attitudes that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	Attitude.getDate()	Get the date of attitude parameters.

Methods in org.orekit.attitudes with parameters of type AbsoluteDate

Modifier and Type	Method	Description
Attitude	AttitudeProvider.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.
Attitude	AttitudesSequence.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.
Attitude	CelestialBodyPointed.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.
Attitude	FixedRate.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.
Attitude	GroundPointing.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.
Attitude	InertialProvider.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.
Attitude	LofOffset.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.
Attitude	LofOffsetPointing.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.
Attitude	SpinStabilized.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.
Attitude	TabulatedLofOffset.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.
Attitude	TabulatedProvider.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.
Attitude	YawCompensation.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.
Attitude	YawSteering.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.
Attitude	YawCompensation.getBaseState(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the base system state at given date, without compensation.
Attitude	YawSteering.getBaseState(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the base system state at given date, without compensation.
TimeStampedPVCoordinates	BodyCenterPointing.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position/velocity in specified frame.
abstract TimeStampedPVCoordinates	GroundPointing.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position/velocity in specified frame.
TimeStampedPVCoordinates	LofOffsetPointing.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position/velocity in specified frame.
TimeStampedPVCoordinates	NadirPointing.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position/velocity in specified frame.
TimeStampedPVCoordinates	TargetPointing.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position/velocity in specified frame.
TimeStampedPVCoordinates	YawCompensation.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position/velocity in specified frame.
TimeStampedPVCoordinates	YawSteering.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position/velocity in specified frame.
double	YawCompensation.getYawAngle(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the yaw compensation angle at date.
Attitude	Attitude.interpolate(AbsoluteDate interpolationDate, Stream<Attitude> sample)	Get an interpolated instance.

Constructors in org.orekit.attitudes with parameters of type AbsoluteDate

Constructor	Description
Attitude(AbsoluteDate date, Frame referenceFrame, org.hipparchus.geometry.euclidean.threed.Rotation attitude, org.hipparchus.geometry.euclidean.threed.Vector3D spin, org.hipparchus.geometry.euclidean.threed.Vector3D acceleration)	Creates a new instance.
Attitude(AbsoluteDate date, Frame referenceFrame, AngularCoordinates orientation)	Creates a new instance.
SpinStabilized(AttitudeProvider nonRotatingLaw, AbsoluteDate start, org.hipparchus.geometry.euclidean.threed.Vector3D axis, double rate)	Creates a new instance.

Uses of AbsoluteDate in org.orekit.bodies

Methods in org.orekit.bodies with parameters of type AbsoluteDate

Modifier and Type	Method	Description
org.hipparchus.geometry.euclidean.threed.Vector3D	OneAxisEllipsoid.getCartesianIntersectionPoint(org.hipparchus.geometry.euclidean.threed.Line line, org.hipparchus.geometry.euclidean.threed.Vector3D close, Frame frame, AbsoluteDate date)	Get the intersection point of a line with the surface of the body.
GeodeticPoint	BodyShape.getIntersectionPoint(org.hipparchus.geometry.euclidean.threed.Line line, org.hipparchus.geometry.euclidean.threed.Vector3D close, Frame frame, AbsoluteDate date)	Get the intersection point of a line with the surface of the body.
GeodeticPoint	OneAxisEllipsoid.getIntersectionPoint(org.hipparchus.geometry.euclidean.threed.Line line, org.hipparchus.geometry.euclidean.threed.Vector3D close, Frame frame, AbsoluteDate date)	Get the intersection point of a line with the surface of the body.
default org.hipparchus.geometry.euclidean.threed.Vector3D	IAUPole.getNode(AbsoluteDate date)	Get the body Q Node direction in ICRF frame.
org.hipparchus.geometry.euclidean.threed.Vector3D	IAUPole.getPole(AbsoluteDate date)	Get the body North pole direction in ICRF frame.
double	IAUPole.getPrimeMeridianAngle(AbsoluteDate date)	Get the prime meridian angle.
PVCoordinates	JPLEphemeridesLoader.RawPVProvider.getRawPV(AbsoluteDate date)	Get the position-velocity at date.
org.hipparchus.geometry.euclidean.threed.Vector3D	BodyShape.projectToGround(org.hipparchus.geometry.euclidean.threed.Vector3D point, AbsoluteDate date, Frame frame)	Project a point to the ground.
org.hipparchus.geometry.euclidean.threed.Vector3D	OneAxisEllipsoid.projectToGround(org.hipparchus.geometry.euclidean.threed.Vector3D point, AbsoluteDate date, Frame frame)	Project a point to the ground.
GeodeticPoint	BodyShape.transform(org.hipparchus.geometry.euclidean.threed.Vector3D point, Frame frame, AbsoluteDate date)	Transform a Cartesian point to a surface-relative point.
GeodeticPoint	OneAxisEllipsoid.transform(org.hipparchus.geometry.euclidean.threed.Vector3D point, Frame frame, AbsoluteDate date)	Transform a Cartesian point to a surface-relative point.
FieldGeodeticPoint<org.hipparchus.analysis.differentiation.DerivativeStructure>	OneAxisEllipsoid.transform(PVCoordinates point, Frame frame, AbsoluteDate date)	Transform a Cartesian point to a surface-relative point.

Uses of AbsoluteDate in org.orekit.data

Methods in org.orekit.data that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	DelaunayArguments.getDate()	Get the date.

Methods in org.orekit.data with parameters of type AbsoluteDate

Modifier and Type	Method	Description
BodiesElements	FundamentalNutationArguments.evaluateAll(AbsoluteDate date)	Evaluate all fundamental arguments for the current date (Delaunay plus planetary).

Constructors in org.orekit.data with parameters of type AbsoluteDate

Constructor	Description
BodiesElements(AbsoluteDate date, double tc, double gamma, double gammaDot, double l, double lDot, double lPrime, double lPrimeDot, double f, double fDot, double d, double dDot, double omega, double omegaDot, double lMe, double lMeDot, double lVe, double lVeDot, double lE, double lEDot, double lMa, double lMaDot, double lJu, double lJuDot, double lSa, double lSaDot, double lUr, double lUrDot, double lNe, double lNeDot, double pa, double paDot)	Simple constructor.
DelaunayArguments(AbsoluteDate date, double tc, double gamma, double gammaDot, double l, double lDot, double lPrime, double lPrimeDot, double f, double fDot, double d, double dDot, double omega, double omegaDot)	Simple constructor.

Uses of AbsoluteDate in org.orekit.estimation.iod

Methods in org.orekit.estimation.iod with parameters of type AbsoluteDate

Modifier and Type	Method	Description
KeplerianOrbit	IodGibbs.estimate(Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D r1, AbsoluteDate date1, org.hipparchus.geometry.euclidean.threed.Vector3D r2, AbsoluteDate date2, org.hipparchus.geometry.euclidean.threed.Vector3D r3, AbsoluteDate date3)	Give an initial orbit estimation, assuming Keplerian motion.
KeplerianOrbit	IodGooding.estimate(org.hipparchus.geometry.euclidean.threed.Vector3D O1, org.hipparchus.geometry.euclidean.threed.Vector3D O2, org.hipparchus.geometry.euclidean.threed.Vector3D O3, org.hipparchus.geometry.euclidean.threed.Vector3D lineOfSight1, AbsoluteDate dateObs1, org.hipparchus.geometry.euclidean.threed.Vector3D lineOfSight2, AbsoluteDate dateObs2, org.hipparchus.geometry.euclidean.threed.Vector3D lineOfSight3, AbsoluteDate dateObs3, double rho1init, double rho3init)	Orbit got from Observed Three Lines of Sight (angles only).
KeplerianOrbit	IodLambert.estimate(Frame frame, boolean posigrade, int nRev, org.hipparchus.geometry.euclidean.threed.Vector3D p1, AbsoluteDate t1, org.hipparchus.geometry.euclidean.threed.Vector3D p2, AbsoluteDate t2)	Estimate a Keplerian orbit given two position vectors and a duration.

Uses of AbsoluteDate in org.orekit.estimation.measurements

Methods in org.orekit.estimation.measurements that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	AbstractMeasurement.getDate()	Get the date.
AbsoluteDate	EstimatedMeasurement.getDate()	Get the date.

Methods in org.orekit.estimation.measurements with parameters of type AbsoluteDate

Modifier and Type	Method	Description
GeodeticPoint	GroundStation.getOffsetGeodeticPoint(AbsoluteDate date)	Get the geodetic point at the center of the offset frame.
Transform	GroundStation.getOffsetToInertial(Frame inertial, AbsoluteDate clockDate)	Get the transform between offset frame and inertial frame.
FieldTransform<org.hipparchus.analysis.differentiation.DerivativeStructure>	GroundStation.getOffsetToInertial(Frame inertial, AbsoluteDate clockDate, org.hipparchus.analysis.differentiation.DSFactory factory, Map<String,Integer> indices)	Get the transform between offset frame and inertial frame with derivatives.
Transform	EstimatedEarthFrameProvider.getTransform(AbsoluteDate date)	Get the Transform corresponding to specified date.
static double	AbstractMeasurement.signalTimeOfFlight(TimeStampedPVCoordinates adjustableEmitterPV, org.hipparchus.geometry.euclidean.threed.Vector3D receiverPosition, AbsoluteDate signalArrivalDate)	Compute propagation delay on a link leg (typically downlink or uplink).

Constructors in org.orekit.estimation.measurements with parameters of type AbsoluteDate

Constructor	Description
AbstractMeasurement(AbsoluteDate date, double[] observed, double[] sigma, double[] baseWeight, List<Integer> propagatorsIndices, ParameterDriver... supportedParameters)	Deprecated. since 9.3, replaced bew AbstractMeasurement(AbsoluteDate, double[], double[], double[], List) followed by AbstractMeasurement.addParameterDriver(ParameterDriver)
AbstractMeasurement(AbsoluteDate date, double[] observed, double[] sigma, double[] baseWeight, List<ObservableSatellite> satellites)	Simple constructor, for multi-dimensional measurements.
AbstractMeasurement(AbsoluteDate date, double observed, double sigma, double baseWeight, List<Integer> propagatorsIndices, ParameterDriver... supportedParameters)	Deprecated. since 9.3, replaced bew AbstractMeasurement(AbsoluteDate, double, double, double, List) followed by AbstractMeasurement.addParameterDriver(ParameterDriver)
AbstractMeasurement(AbsoluteDate date, double observed, double sigma, double baseWeight, List<ObservableSatellite> satellites)	Simple constructor for mono-dimensional measurements.
AngularAzEl(GroundStation station, AbsoluteDate date, double[] angular, double[] sigma, double[] baseWeight)	Deprecated. since 9.3, replaced by AngularAzEl(GroundStation, AbsoluteDate, double[], double[], double[], ObservableSatellite)
AngularAzEl(GroundStation station, AbsoluteDate date, double[] angular, double[] sigma, double[] baseWeight, int propagatorIndex)	Deprecated. since 9.3, replaced by AngularAzEl(GroundStation, AbsoluteDate, double[], double[], double[], ObservableSatellite)
AngularAzEl(GroundStation station, AbsoluteDate date, double[] angular, double[] sigma, double[] baseWeight, ObservableSatellite satellite)	Simple constructor.
AngularRaDec(GroundStation station, Frame referenceFrame, AbsoluteDate date, double[] angular, double[] sigma, double[] baseWeight)	Deprecated. since 9.3, replaced by AngularRaDec(GroundStation, Frame, AbsoluteDate, double[], double[], double[], ObservableSatellite)
AngularRaDec(GroundStation station, Frame referenceFrame, AbsoluteDate date, double[] angular, double[] sigma, double[] baseWeight, int propagatorIndex)	Deprecated. since 9.3, replaced by AngularRaDec(GroundStation, Frame, AbsoluteDate, double[], double[], double[], ObservableSatellite)
AngularRaDec(GroundStation station, Frame referenceFrame, AbsoluteDate date, double[] angular, double[] sigma, double[] baseWeight, ObservableSatellite satellite)	Simple constructor.
InterSatellitesRange(int localIndex, int remoteIndex, boolean twoWay, AbsoluteDate date, double range, double sigma, double baseWeight)	Deprecated. as of 9.3, replaced by InterSatellitesRange(ObservableSatellite, ObservableSatellite, boolean, AbsoluteDate, double, double, double)
InterSatellitesRange(ObservableSatellite local, ObservableSatellite remote, boolean twoWay, AbsoluteDate date, double range, double sigma, double baseWeight)	Simple constructor.
Phase(GroundStation station, AbsoluteDate date, double phase, double wavelength, double sigma, double baseWeight)	Deprecated. since 9.3 raplced by Phase(GroundStation, AbsoluteDate, double, double, double, double, ObservableSatellite)
Phase(GroundStation station, AbsoluteDate date, double phase, double wavelength, double sigma, double baseWeight, int propagatorIndex)	Deprecated. since 9.3 raplced by Phase(GroundStation, AbsoluteDate, double, double, double, double, ObservableSatellite)
Phase(GroundStation station, AbsoluteDate date, double phase, double wavelength, double sigma, double baseWeight, ObservableSatellite satellite)	Simple constructor.
Position(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, double[][] positionCovarianceMatrix, double baseWeight)	Deprecated. as of 9.3, replaced by Position(AbsoluteDate, Vector3D, double[][], double, ObservableSatellite)
Position(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, double[][] covarianceMatrix, double baseWeight, int propagatorIndex)	Deprecated. as of 9.3, replaced by Position(AbsoluteDate, Vector3D, double[][], double, ObservableSatellite)
Position(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, double[][] covarianceMatrix, double baseWeight, ObservableSatellite satellite)	Constructor with full covariance matrix and all inputs.
Position(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, double[] sigmaPosition, double baseWeight)	Deprecated. as of 9.3, replaced by Position(AbsoluteDate, Vector3D, double[], double, ObservableSatellite)
Position(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, double[] sigmaPosition, double baseWeight, int propagatorIndex)	Deprecated. as of 9.3, replaced by Position(AbsoluteDate, Vector3D, double[], double, ObservableSatellite)
Position(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, double[] sigmaPosition, double baseWeight, ObservableSatellite satellite)	Constructor with one vector for the standard deviation.
Position(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, double sigmaPosition, double baseWeight)	Deprecated. as of 9.3, replaced by Position(AbsoluteDate, Vector3D, double, double, ObservableSatellite)
Position(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, double sigmaPosition, double baseWeight, int propagatorIndex)	Deprecated. as of 9.3, replaced by Position(AbsoluteDate, Vector3D, double, double, ObservableSatellite)
Position(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, double sigmaPosition, double baseWeight, ObservableSatellite satellite)	Constructor with one double for the standard deviation.
PV(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Vector3D velocity, double[][] covarianceMatrix, double baseWeight)	Deprecated. as of 9.3, replaced by PV(AbsoluteDate, Vector3D, Vector3D, double[][], double, ObservableSatellite)
PV(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Vector3D velocity, double[][] positionCovarianceMatrix, double[][] velocityCovarianceMatrix, double baseWeight)	Deprecated. as of 9.3, replaced by PV(AbsoluteDate, Vector3D, Vector3D, double[][], double[][], double, ObservableSatellite)
PV(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Vector3D velocity, double[][] positionCovarianceMatrix, double[][] velocityCovarianceMatrix, double baseWeight, int propagatorIndex)	Deprecated. as of 9.3, replaced by PV(AbsoluteDate, Vector3D, Vector3D, double[][], double[][], double, ObservableSatellite)
PV(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Vector3D velocity, double[][] positionCovarianceMatrix, double[][] velocityCovarianceMatrix, double baseWeight, ObservableSatellite satellite)	Constructor with 2 smaller covariance matrices.
PV(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Vector3D velocity, double[][] covarianceMatrix, double baseWeight, int propagatorIndex)	Deprecated. as of 9.3, replaced by PV(AbsoluteDate, Vector3D, Vector3D, double[][], double, ObservableSatellite)
PV(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Vector3D velocity, double[][] covarianceMatrix, double baseWeight, ObservableSatellite satellite)	Constructor with full covariance matrix and all inputs.
PV(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Vector3D velocity, double[] sigmaPV, double baseWeight)	Deprecated. as of 9.3, replaced by PV(AbsoluteDate, Vector3D, Vector3D, double[], double, ObservableSatellite)
PV(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Vector3D velocity, double[] sigmaPosition, double[] sigmaVelocity, double baseWeight)	Deprecated. as of 9.3, replaced by PV(AbsoluteDate, Vector3D, Vector3D, double[], double[], double, ObservableSatellite)
PV(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Vector3D velocity, double[] sigmaPosition, double[] sigmaVelocity, double baseWeight, int propagatorIndex)	Deprecated. as of 9.3, replaced by PV(AbsoluteDate, Vector3D, Vector3D, double[], double[], double, ObservableSatellite)
PV(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Vector3D velocity, double[] sigmaPosition, double[] sigmaVelocity, double baseWeight, ObservableSatellite satellite)	Constructor with two vectors for the standard deviations.
PV(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Vector3D velocity, double[] sigmaPV, double baseWeight, int propagatorIndex)	Deprecated. as of 9.3, replaced by PV(AbsoluteDate, Vector3D, Vector3D, double[], double, ObservableSatellite)
PV(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Vector3D velocity, double[] sigmaPV, double baseWeight, ObservableSatellite satellite)	Constructor with one vector for the standard deviations.
PV(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Vector3D velocity, double sigmaPosition, double sigmaVelocity, double baseWeight)	Deprecated. as of 9.3, replaced by PV(AbsoluteDate, Vector3D, Vector3D, double, double, double, ObservableSatellite)
PV(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Vector3D velocity, double sigmaPosition, double sigmaVelocity, double baseWeight, int propagatorIndex)	Deprecated. as of 9.3, replaced by PV(AbsoluteDate, Vector3D, Vector3D, double, double, double, ObservableSatellite)
PV(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Vector3D velocity, double sigmaPosition, double sigmaVelocity, double baseWeight, ObservableSatellite satellite)	Constructor with two double for the standard deviations.
Range(GroundStation station, boolean twoWay, AbsoluteDate date, double range, double sigma, double baseWeight, int propagatorIndex)	Deprecated. as of 9.3, replaced by Range(GroundStation, boolean, AbsoluteDate, double, double, double, ObservableSatellite)
Range(GroundStation station, boolean twoWay, AbsoluteDate date, double range, double sigma, double baseWeight, ObservableSatellite satellite)	Simple constructor.
Range(GroundStation station, AbsoluteDate date, double range, double sigma, double baseWeight)	Deprecated. as of 9.3, replaced by Range(GroundStation, boolean, AbsoluteDate, double, double, double, ObservableSatellite)
Range(GroundStation station, AbsoluteDate date, double range, double sigma, double baseWeight, boolean twoWay)	Deprecated. as of 9.3, replaced by Range(GroundStation, boolean, AbsoluteDate, double, double, double, ObservableSatellite)
Range(GroundStation station, AbsoluteDate date, double range, double sigma, double baseWeight, int propagatorIndex)	Deprecated. as of 9.3, replaced by Range(GroundStation, boolean, AbsoluteDate, double, double, double, ObservableSatellite)
RangeRate(GroundStation station, AbsoluteDate date, double rangeRate, double sigma, double baseWeight, boolean twoway)	Deprecated. since 9.3 replaced by RangeRate(GroundStation, AbsoluteDate, double, double, double, boolean, ObservableSatellite)
RangeRate(GroundStation station, AbsoluteDate date, double rangeRate, double sigma, double baseWeight, boolean twoway, int propagatorIndex)	Deprecated. since 9.3 replaced by RangeRate(GroundStation, AbsoluteDate, double, double, double, boolean, ObservableSatellite)
RangeRate(GroundStation station, AbsoluteDate date, double rangeRate, double sigma, double baseWeight, boolean twoway, ObservableSatellite satellite)	Simple constructor.
TurnAroundRange(GroundStation masterStation, GroundStation slaveStation, AbsoluteDate date, double turnAroundRange, double sigma, double baseWeight)	Deprecated. as of 9.3, replaced by TurnAroundRange(GroundStation, GroundStation, AbsoluteDate, double, double, double, ObservableSatellite)
TurnAroundRange(GroundStation masterStation, GroundStation slaveStation, AbsoluteDate date, double turnAroundRange, double sigma, double baseWeight, int propagatorIndex)	Deprecated. as of 9.3, replaced by TurnAroundRange(GroundStation, GroundStation, AbsoluteDate, double, double, double, ObservableSatellite)
TurnAroundRange(GroundStation masterStation, GroundStation slaveStation, AbsoluteDate date, double turnAroundRange, double sigma, double baseWeight, ObservableSatellite satellite)	Simple constructor.

Uses of AbsoluteDate in org.orekit.estimation.measurements.generation

Methods in org.orekit.estimation.measurements.generation that return AbsoluteDate

Modifier and Type	Method	Description
protected AbsoluteDate	AbstractMeasurementBuilder.getEnd()	Get the end of the measurements time span.
protected AbsoluteDate	AbstractMeasurementBuilder.getStart()	Get the start of the measurements time span.

Methods in org.orekit.estimation.measurements.generation with parameters of type AbsoluteDate

Modifier and Type	Method	Description
SortedSet<ObservedMeasurement<?>>	Generator.generate(AbsoluteDate start, AbsoluteDate end)	Generate measurements.
void	AbstractMeasurementBuilder.init(AbsoluteDate start, AbsoluteDate end)	Initialize builder at the start of a measurements generation.
void	AbstractScheduler.init(AbsoluteDate start, AbsoluteDate end)	Initialize scheduler at the start of a measurements generation.
void	MeasurementBuilder.init(AbsoluteDate start, AbsoluteDate end)	Initialize builder at the start of a measurements generation.
void	Scheduler.init(AbsoluteDate start, AbsoluteDate end)	Initialize scheduler at the start of a measurements generation.

Uses of AbsoluteDate in org.orekit.estimation.sequential

Methods in org.orekit.estimation.sequential that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	KalmanEstimation.getCurrentDate()	Get the current date.
AbsoluteDate	KalmanEstimator.getCurrentDate()	Get the current date.
AbsoluteDate	Model.getCurrentDate()	Get the current date.

Constructors in org.orekit.estimation.sequential with parameters of type AbsoluteDate

Constructor	Description
MeasurementDecorator(ObservedMeasurement<?> observedMeasurement, org.hipparchus.linear.RealMatrix covariance, AbsoluteDate reference)	Simple constructor.

Uses of AbsoluteDate in org.orekit.files.ccsds

Methods in org.orekit.files.ccsds that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	ODMFile.getCreationDate()	Get the file creation date and time in UTC.
AbsoluteDate	TDMFile.getCreationDate()	Get the file creation date and time in UTC.
AbsoluteDate	OEMFile.CovarianceMatrix.getEpoch()	Get the epoch relative to the covariance matrix.
AbsoluteDate	OGMFile.getEpoch()	Get epoch of state vector, Keplerian elements and covariance matrix data.
AbsoluteDate	TDMFile.Observation.getEpoch()	Getter for the epoch.
AbsoluteDate	OPMFile.Maneuver.getEpochIgnition()	Get epoch ignition.
AbsoluteDate	ODMMetaData.getFrameEpoch()	Get epoch of reference frame, if not intrinsic to the definition of the reference frame.
AbsoluteDate	ODMFile.getMissionReferenceDate()	Get reference date for Mission Elapsed Time and Mission Relative Time time systems.
AbsoluteDate	ODMParser.getMissionReferenceDate()	Get initial date.
AbsoluteDate	TDMParser.getMissionReferenceDate()	Get initial date.
AbsoluteDate	OEMFile.EphemeridesBlock.getStart()
AbsoluteDate	OEMFile.OemSatelliteEphemeris.getStart()
AbsoluteDate	OEMFile.EphemeridesBlock.getStartTime()	Get start of total time span covered by ephemerides data and covariance data.
AbsoluteDate	TDMFile.TDMMetaData.getStartTime()	Getter for the startTime.
AbsoluteDate	OEMFile.EphemeridesBlock.getStop()
AbsoluteDate	OEMFile.OemSatelliteEphemeris.getStop()
AbsoluteDate	OEMFile.EphemeridesBlock.getStopTime()	Get end of total time span covered by ephemerides data and covariance data.
AbsoluteDate	TDMFile.TDMMetaData.getStopTime()	Getter for the stopTime.
AbsoluteDate	OEMFile.EphemeridesBlock.getUseableStartTime()	Get start of useable time span covered by ephemerides data, it may be necessary to allow for proper interpolation.
AbsoluteDate	OEMFile.EphemeridesBlock.getUseableStopTime()	Get end of useable time span covered by ephemerides data, it may be necessary to allow for proper interpolation.
AbsoluteDate	CcsdsTimeScale.parseDate(String date, IERSConventions conventions, AbsoluteDate missionReferenceDate)	Parse a date in this time scale.
protected AbsoluteDate	ODMParser.parseDate(String date, CcsdsTimeScale timeSystem)	Parse a date.

Methods in org.orekit.files.ccsds with parameters of type AbsoluteDate

Modifier and Type	Method	Description
void	TDMFile.ObservationsBlock.addObservation(String keyword, AbsoluteDate epoch, double measurement)	Adds an observation data line.
void	StreamingOemWriter.Segment.init(SpacecraftState s0, AbsoluteDate t, double step)	Initialize step handler at the start of a propagation.
AbsoluteDate	CcsdsTimeScale.parseDate(String date, IERSConventions conventions, AbsoluteDate missionReferenceDate)	Parse a date in this time scale.
void	TDMFile.setCreationDate(AbsoluteDate creationDate)	Set the file creation date and time in UTC.
void	TDMFile.Observation.setEpoch(AbsoluteDate epoch)	Setter for the epoch.
void	TDMFile.TDMMetaData.setStartTime(AbsoluteDate startTime)	Setter for the startTime.
void	TDMFile.TDMMetaData.setStopTime(AbsoluteDate stopTime)	Setter for the stopTime.
abstract ODMParser	ODMParser.withMissionReferenceDate(AbsoluteDate newMissionReferenceDate)	Set initial date.
OEMParser	OEMParser.withMissionReferenceDate(AbsoluteDate newMissionReferenceDate)	Set initial date.
OMMParser	OMMParser.withMissionReferenceDate(AbsoluteDate newMissionReferenceDate)	Set initial date.
OPMParser	OPMParser.withMissionReferenceDate(AbsoluteDate newMissionReferenceDate)	Set initial date.
TDMParser	TDMParser.withMissionReferenceDate(AbsoluteDate newMissionReferenceDate)	Set initial date.

Constructors in org.orekit.files.ccsds with parameters of type AbsoluteDate

Constructor	Description
ODMParser(AbsoluteDate missionReferenceDate, double mu, IERSConventions conventions, boolean simpleEOP, int launchYear, int launchNumber, String launchPiece)	Complete constructor.

Uses of AbsoluteDate in org.orekit.files.general

Methods in org.orekit.files.general that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	EphemerisFile.EphemerisSegment.getStart()	Get the start date of this ephemeris segment.
AbsoluteDate	EphemerisFile.SatelliteEphemeris.getStart()	Get the start date of the ephemeris.
AbsoluteDate	OrekitEphemerisFile.OrekitEphemerisSegment.getStart()
AbsoluteDate	OrekitEphemerisFile.OrekitSatelliteEphemeris.getStart()
AbsoluteDate	EphemerisFile.EphemerisSegment.getStop()	Get the end date of this ephemeris segment.
AbsoluteDate	EphemerisFile.SatelliteEphemeris.getStop()	Get the end date of the ephemeris.
AbsoluteDate	OrekitEphemerisFile.OrekitEphemerisSegment.getStop()
AbsoluteDate	OrekitEphemerisFile.OrekitSatelliteEphemeris.getStop()

Uses of AbsoluteDate in org.orekit.files.sp3

Methods in org.orekit.files.sp3 that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	SP3File.getEpoch()	Returns the start epoch of the orbit file.
AbsoluteDate	SP3File.SP3Ephemeris.getStart()
AbsoluteDate	SP3File.SP3Ephemeris.getStop()

Uses of AbsoluteDate in org.orekit.forces

Methods in org.orekit.forces with parameters of type AbsoluteDate

Modifier and Type	Method	Description
org.hipparchus.geometry.euclidean.threed.Vector3D	BoxAndSolarArraySpacecraft.dragAcceleration(AbsoluteDate date, Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Rotation rotation, double mass, double density, org.hipparchus.geometry.euclidean.threed.Vector3D relativeVelocity, double[] parameters)	Compute the acceleration due to drag.
org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure>	BoxAndSolarArraySpacecraft.dragAcceleration(AbsoluteDate date, Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Rotation rotation, double mass, double density, org.hipparchus.geometry.euclidean.threed.Vector3D relativeVelocity, double[] parameters, String paramName)	Compute acceleration due to drag, with parameters derivatives.
org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure>	BoxAndSolarArraySpacecraft.getNormal(AbsoluteDate date, Frame frame, org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure> position, org.hipparchus.geometry.euclidean.threed.FieldRotation<org.hipparchus.analysis.differentiation.DerivativeStructure> rotation)	Get solar array normal in spacecraft frame.
org.hipparchus.geometry.euclidean.threed.Vector3D	BoxAndSolarArraySpacecraft.getNormal(AbsoluteDate date, Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Rotation rotation)	Get solar array normal in spacecraft frame.
default void	ForceModel.init(SpacecraftState initialState, AbsoluteDate target)	Initialize the force model at the start of propagation.
void	HarmonicParametricAcceleration.init(SpacecraftState initialState, AbsoluteDate target)	Initialize the force model at the start of propagation.
void	PolynomialParametricAcceleration.init(SpacecraftState initialState, AbsoluteDate target)	Initialize the force model at the start of propagation.
org.hipparchus.geometry.euclidean.threed.Vector3D	BoxAndSolarArraySpacecraft.radiationPressureAcceleration(AbsoluteDate date, Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Rotation rotation, double mass, org.hipparchus.geometry.euclidean.threed.Vector3D flux, double[] parameters)	Compute the acceleration due to radiation pressure.
org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure>	BoxAndSolarArraySpacecraft.radiationPressureAcceleration(AbsoluteDate date, Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Rotation rotation, double mass, org.hipparchus.geometry.euclidean.threed.Vector3D flux, double[] parameters, String paramName)	Compute the acceleration due to radiation pressure, with parameters derivatives.

Constructors in org.orekit.forces with parameters of type AbsoluteDate

Constructor	Description
BoxAndSolarArraySpacecraft(double xLength, double yLength, double zLength, PVCoordinatesProvider sun, double solarArrayArea, org.hipparchus.geometry.euclidean.threed.Vector3D solarArrayAxis, AbsoluteDate referenceDate, org.hipparchus.geometry.euclidean.threed.Vector3D referenceNormal, double rotationRate, double dragCoeff, double absorptionCoeff, double reflectionCoeff)	Build a spacecraft model with linear rotation of solar array.
BoxAndSolarArraySpacecraft(double xLength, double yLength, double zLength, PVCoordinatesProvider sun, double solarArrayArea, org.hipparchus.geometry.euclidean.threed.Vector3D solarArrayAxis, AbsoluteDate referenceDate, org.hipparchus.geometry.euclidean.threed.Vector3D referenceNormal, double rotationRate, double dragCoeff, double liftRatio, double absorptionCoeff, double reflectionCoeff)	Build a spacecraft model with linear rotation of solar array.
BoxAndSolarArraySpacecraft(BoxAndSolarArraySpacecraft.Facet[] facets, PVCoordinatesProvider sun, double solarArrayArea, org.hipparchus.geometry.euclidean.threed.Vector3D solarArrayAxis, AbsoluteDate referenceDate, org.hipparchus.geometry.euclidean.threed.Vector3D referenceNormal, double rotationRate, double dragCoeff, double absorptionCoeff, double reflectionCoeff)	Build a spacecraft model with linear rotation of solar array.
BoxAndSolarArraySpacecraft(BoxAndSolarArraySpacecraft.Facet[] facets, PVCoordinatesProvider sun, double solarArrayArea, org.hipparchus.geometry.euclidean.threed.Vector3D solarArrayAxis, AbsoluteDate referenceDate, org.hipparchus.geometry.euclidean.threed.Vector3D referenceNormal, double rotationRate, double dragCoeff, double liftRatio, double absorptionCoeff, double reflectionCoeff)	Build a spacecraft model with linear rotation of solar array.
HarmonicParametricAcceleration(org.hipparchus.geometry.euclidean.threed.Vector3D direction, boolean isInertial, String prefix, AbsoluteDate referenceDate, double fundamentalPeriod, int harmonicMultiplier)	Simple constructor.
HarmonicParametricAcceleration(org.hipparchus.geometry.euclidean.threed.Vector3D direction, AttitudeProvider attitudeOverride, String prefix, AbsoluteDate referenceDate, double fundamentalPeriod, int harmonicMultiplier)	Simple constructor.
PolynomialParametricAcceleration(org.hipparchus.geometry.euclidean.threed.Vector3D direction, boolean isInertial, String prefix, AbsoluteDate referenceDate, int degree)	Simple constructor.
PolynomialParametricAcceleration(org.hipparchus.geometry.euclidean.threed.Vector3D direction, AttitudeProvider attitudeOverride, String prefix, AbsoluteDate referenceDate, int degree)	Simple constructor.

Uses of AbsoluteDate in org.orekit.forces.drag

Methods in org.orekit.forces.drag with parameters of type AbsoluteDate

Modifier and Type	Method	Description
org.hipparchus.geometry.euclidean.threed.Vector3D	DragSensitive.dragAcceleration(AbsoluteDate date, Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Rotation rotation, double mass, double density, org.hipparchus.geometry.euclidean.threed.Vector3D relativeVelocity, double[] parameters)	Compute the acceleration due to drag.
org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure>	DragSensitive.dragAcceleration(AbsoluteDate date, Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Rotation rotation, double mass, double density, org.hipparchus.geometry.euclidean.threed.Vector3D relativeVelocity, double[] parameters, String paramName)	Compute acceleration due to drag, with parameters derivatives.
org.hipparchus.geometry.euclidean.threed.Vector3D	IsotropicDrag.dragAcceleration(AbsoluteDate date, Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Rotation rotation, double mass, double density, org.hipparchus.geometry.euclidean.threed.Vector3D relativeVelocity, double[] parameters)	Compute the acceleration due to drag.
org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure>	IsotropicDrag.dragAcceleration(AbsoluteDate date, Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Rotation rotation, double mass, double density, org.hipparchus.geometry.euclidean.threed.Vector3D relativeVelocity, double[] parameters, String paramName)	Compute acceleration due to drag, with parameters derivatives.

Uses of AbsoluteDate in org.orekit.forces.drag.atmosphere

Methods in org.orekit.forces.drag.atmosphere that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	DTM2000InputParameters.getMaxDate()	Gets the available data range maximum date.
AbsoluteDate	JB2008InputParameters.getMaxDate()	Gets the available data range maximum date.
AbsoluteDate	NRLMSISE00InputParameters.getMaxDate()	Gets the available data range maximum date.
AbsoluteDate	DTM2000InputParameters.getMinDate()	Gets the available data range minimum date.
AbsoluteDate	JB2008InputParameters.getMinDate()	Gets the available data range minimum date.
AbsoluteDate	NRLMSISE00InputParameters.getMinDate()	Gets the available data range minimum date.

Methods in org.orekit.forces.drag.atmosphere with parameters of type AbsoluteDate

Modifier and Type	Method	Description
double	DTM2000InputParameters.get24HoursKp(AbsoluteDate date)	Get the last 24H mean geomagnetic index.
double[]	NRLMSISE00InputParameters.getAp(AbsoluteDate date)	Get the Ap geomagnetic indices.
double	NRLMSISE00InputParameters.getAverageFlux(AbsoluteDate date)	Get the value of the 81 day average of F10.7 solar flux centered on current day.
double	NRLMSISE00InputParameters.getDailyFlux(AbsoluteDate date)	Get the value of the daily F10.7 solar flux for previous day.
double	Atmosphere.getDensity(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, Frame frame)	Get the local density.
double	DTM2000.getDensity(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, Frame frame)	Get the local density.
double	HarrisPriester.getDensity(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, Frame frame)	Get the local density at some position.
double	JB2008.getDensity(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, Frame frame)	Get the local density.
double	NRLMSISE00.getDensity(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, Frame frame)	Get the local density.
double	SimpleExponentialAtmosphere.getDensity(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, Frame frame)	Get the local density.
double	JB2008InputParameters.getDSTDTC(AbsoluteDate date)	Get the temperature change computed from Dst index.
double	JB2008InputParameters.getF10(AbsoluteDate date)	Get the value of the instantaneous solar flux index (1e-22*Watt/(m²*Hertz)).
double	JB2008InputParameters.getF10B(AbsoluteDate date)	Get the value of the mean solar flux.
double	DTM2000InputParameters.getInstantFlux(AbsoluteDate date)	Get the value of the instantaneous solar flux.
double	DTM2000InputParameters.getMeanFlux(AbsoluteDate date)	Get the value of the mean solar flux.
double	JB2008InputParameters.getS10(AbsoluteDate date)	Get the EUV index (26-34 nm) scaled to F10.
double	JB2008InputParameters.getS10B(AbsoluteDate date)	Get the EUV 81-day averaged centered index.
double	DTM2000InputParameters.getThreeHourlyKP(AbsoluteDate date)	Get the value of the 3 hours geomagnetic index.
default org.hipparchus.geometry.euclidean.threed.Vector3D	Atmosphere.getVelocity(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, Frame frame)	Get the inertial velocity of atmosphere molecules.
double	JB2008InputParameters.getXM10(AbsoluteDate date)	Get the MG2 index scaled to F10.
double	JB2008InputParameters.getXM10B(AbsoluteDate date)	Get the MG2 81-day average centered index.
double	JB2008InputParameters.getY10(AbsoluteDate date)	Get the Solar X-Ray & Lya index scaled to F10.
double	JB2008InputParameters.getY10B(AbsoluteDate date)	Get the Solar X-Ray & Lya 81-day ave.

Uses of AbsoluteDate in org.orekit.forces.drag.atmosphere.data

Methods in org.orekit.forces.drag.atmosphere.data that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	MarshallSolarActivityFutureEstimation.getMaxDate()	Gets the available data range maximum date.
AbsoluteDate	MarshallSolarActivityFutureEstimation.getMinDate()	Gets the available data range minimum date.

Methods in org.orekit.forces.drag.atmosphere.data with parameters of type AbsoluteDate

Modifier and Type	Method	Description
double	MarshallSolarActivityFutureEstimation.get24HoursKp(AbsoluteDate date)	The Kp index is derived from the Ap index.
double[]	MarshallSolarActivityFutureEstimation.getAp(AbsoluteDate date)	Get the Ap geomagnetic indices.
double	MarshallSolarActivityFutureEstimation.getAverageFlux(AbsoluteDate date)	Get the value of the 81 day average of F10.7 solar flux centered on current day.
double	MarshallSolarActivityFutureEstimation.getDailyFlux(AbsoluteDate date)	Get the value of the daily F10.7 solar flux for previous day.
DateComponents	MarshallSolarActivityFutureEstimation.getFileDate(AbsoluteDate date)	Get the date of the file from which data at the specified date comes from.
double	MarshallSolarActivityFutureEstimation.getInstantFlux(AbsoluteDate date)	Get the value of the instantaneous solar flux.
double	MarshallSolarActivityFutureEstimation.getMeanFlux(AbsoluteDate date)	Get the value of the mean solar flux.
double	MarshallSolarActivityFutureEstimation.getThreeHourlyKP(AbsoluteDate date)	Get the value of the 3 hours geomagnetic index.

Uses of AbsoluteDate in org.orekit.forces.gravity

Methods in org.orekit.forces.gravity with parameters of type AbsoluteDate

Modifier and Type	Method	Description
double[]	HolmesFeatherstoneAttractionModel.gradient(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, double mu)	Compute the gradient of the non-central part of the gravity field.
double	HolmesFeatherstoneAttractionModel.nonCentralPart(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, double mu)	Compute the non-central part of the gravity field.
double	HolmesFeatherstoneAttractionModel.value(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, double mu)	Compute the value of the gravity field.

Uses of AbsoluteDate in org.orekit.forces.gravity.potential

Methods in org.orekit.forces.gravity.potential that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	CachedNormalizedSphericalHarmonicsProvider.getReferenceDate()	Get the reference date for the harmonics.
AbsoluteDate	SphericalHarmonicsProvider.getReferenceDate()	Get the reference date for the harmonics.

Methods in org.orekit.forces.gravity.potential with parameters of type AbsoluteDate

Modifier and Type	Method	Description
double	CachedNormalizedSphericalHarmonicsProvider.getOffset(AbsoluteDate date)	Get the offset from reference date for the harmonics.
double	SphericalHarmonicsProvider.getOffset(AbsoluteDate date)	Get the offset from reference date for the harmonics.
NormalizedSphericalHarmonicsProvider.NormalizedSphericalHarmonics	CachedNormalizedSphericalHarmonicsProvider.onDate(AbsoluteDate date)	Get the normalized spherical harmonic coefficients at a specific instance in time.
NormalizedSphericalHarmonicsProvider.NormalizedSphericalHarmonics	NormalizedSphericalHarmonicsProvider.onDate(AbsoluteDate date)	Get the normalized spherical harmonic coefficients at a specific instance in time.
RawSphericalHarmonicsProvider.RawSphericalHarmonics	RawSphericalHarmonicsProvider.onDate(AbsoluteDate date)	Get the raw spherical harmonic coefficients on a specific date.
UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics	UnnormalizedSphericalHarmonicsProvider.onDate(AbsoluteDate date)	Get the un-normalized spherical harmonic coefficients at a specific instance in time.

Uses of AbsoluteDate in org.orekit.forces.maneuvers

Methods in org.orekit.forces.maneuvers that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	SmallManeuverAnalyticalModel.getDate()	Get the date of the maneuver.
AbsoluteDate	ConstantThrustManeuver.getEndDate()	Get the end date.
AbsoluteDate	ConstantThrustManeuver.getStartDate()	Get the start date.

Methods in org.orekit.forces.maneuvers with parameters of type AbsoluteDate

Modifier and Type	Method	Description
void	ConstantThrustManeuver.init(SpacecraftState s0, AbsoluteDate t)	Initialize the force model at the start of propagation.
void	ImpulseManeuver.init(SpacecraftState s0, AbsoluteDate t)	Initialize event handler at the start of a propagation.

Constructors in org.orekit.forces.maneuvers with parameters of type AbsoluteDate

Constructor	Description
ConstantThrustManeuver(AbsoluteDate date, double duration, double thrust, double isp, org.hipparchus.geometry.euclidean.threed.Vector3D direction)	Simple constructor for a constant direction and constant thrust.
ConstantThrustManeuver(AbsoluteDate date, double duration, double thrust, double isp, org.hipparchus.geometry.euclidean.threed.Vector3D direction, String name)	Simple constructor for a constant direction and constant thrust.
ConstantThrustManeuver(AbsoluteDate date, double duration, double thrust, double isp, AttitudeProvider attitudeOverride, org.hipparchus.geometry.euclidean.threed.Vector3D direction)	Simple constructor for a constant direction and constant thrust.
ConstantThrustManeuver(AbsoluteDate date, double duration, double thrust, double isp, AttitudeProvider attitudeOverride, org.hipparchus.geometry.euclidean.threed.Vector3D direction, String name)	Simple constructor for a constant direction and constant thrust.

Uses of AbsoluteDate in org.orekit.forces.radiation

Methods in org.orekit.forces.radiation with parameters of type AbsoluteDate

Modifier and Type	Method	Description
double	SolarRadiationPressure.getLightingRatio(org.hipparchus.geometry.euclidean.threed.Vector3D position, Frame frame, AbsoluteDate date)	Get the lighting ratio ([0-1]).
org.hipparchus.geometry.euclidean.threed.Vector3D	IsotropicRadiationClassicalConvention.radiationPressureAcceleration(AbsoluteDate date, Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Rotation rotation, double mass, org.hipparchus.geometry.euclidean.threed.Vector3D flux, double[] parameters)	Compute the acceleration due to radiation pressure.
org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure>	IsotropicRadiationClassicalConvention.radiationPressureAcceleration(AbsoluteDate date, Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Rotation rotation, double mass, org.hipparchus.geometry.euclidean.threed.Vector3D flux, double[] parameters, String paramName)	Compute the acceleration due to radiation pressure, with parameters derivatives.
org.hipparchus.geometry.euclidean.threed.Vector3D	IsotropicRadiationCNES95Convention.radiationPressureAcceleration(AbsoluteDate date, Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Rotation rotation, double mass, org.hipparchus.geometry.euclidean.threed.Vector3D flux, double[] parameters)	Compute the acceleration due to radiation pressure.
org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure>	IsotropicRadiationCNES95Convention.radiationPressureAcceleration(AbsoluteDate date, Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Rotation rotation, double mass, org.hipparchus.geometry.euclidean.threed.Vector3D flux, double[] parameters, String paramName)	Compute the acceleration due to radiation pressure, with parameters derivatives.
org.hipparchus.geometry.euclidean.threed.Vector3D	IsotropicRadiationSingleCoefficient.radiationPressureAcceleration(AbsoluteDate date, Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Rotation rotation, double mass, org.hipparchus.geometry.euclidean.threed.Vector3D flux, double[] parameters)	Compute the acceleration due to radiation pressure.
org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure>	IsotropicRadiationSingleCoefficient.radiationPressureAcceleration(AbsoluteDate date, Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Rotation rotation, double mass, org.hipparchus.geometry.euclidean.threed.Vector3D flux, double[] parameters, String paramName)	Compute the acceleration due to radiation pressure, with parameters derivatives.
org.hipparchus.geometry.euclidean.threed.Vector3D	RadiationSensitive.radiationPressureAcceleration(AbsoluteDate date, Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Rotation rotation, double mass, org.hipparchus.geometry.euclidean.threed.Vector3D flux, double[] parameters)	Compute the acceleration due to radiation pressure.
org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure>	RadiationSensitive.radiationPressureAcceleration(AbsoluteDate date, Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Rotation rotation, double mass, org.hipparchus.geometry.euclidean.threed.Vector3D flux, double[] parameters, String paramName)	Compute the acceleration due to radiation pressure, with parameters derivatives.

Uses of AbsoluteDate in org.orekit.frames

Methods in org.orekit.frames that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	EOPEntry.getDate()	Get the date.
AbsoluteDate	FieldTransform.getDate()	Get the date.
AbsoluteDate	Transform.getDate()	Get the date.
AbsoluteDate	EOPHistory.getEndDate()	Get the date of the last available Earth Orientation Parameters.
AbsoluteDate	HelmertTransformation.getEpoch()	Get the reference epoch of the transform.
AbsoluteDate	EOPHistory.getStartDate()	Get the date of the first available Earth Orientation Parameters.

Methods in org.orekit.frames with parameters of type AbsoluteDate

Modifier and Type	Method	Description
List<FieldTransform<T>>	FieldTransformGenerator.generate(AbsoluteDate existingDate, AbsoluteDate date)	Generate a chronologically sorted list of entries to be cached.
List<Transform>	TransformGenerator.generate(AbsoluteDate existingDate, AbsoluteDate date)	Generate a chronologically sorted list of entries to be cached.
double	TopocentricFrame.getAzimuth(org.hipparchus.geometry.euclidean.threed.Vector3D extPoint, Frame frame, AbsoluteDate date)	Get the azimuth of a point with regards to the topocentric frame center point.
double	TopocentricFrame.getElevation(org.hipparchus.geometry.euclidean.threed.Vector3D extPoint, Frame frame, AbsoluteDate date)	Get the elevation of a point with regards to the local point.
double[]	EOPHistory.getEquinoxNutationCorrection(AbsoluteDate date)	Get the correction to the nutation parameters for equinox-based paradigm.
Frame	Frame.getFrozenFrame(Frame reference, AbsoluteDate freezingDate, String frozenName)	Get a new version of the instance, frozen with respect to a reference frame.
ITRFVersion	EOPHistory.getITRFVersion(AbsoluteDate date)	Get the ITRF version.
double	EOPHistory.getLOD(AbsoluteDate date)	Get the LoD (Length of Day) value.
protected Stream<EOPEntry>	EOPHistory.getNeighbors(AbsoluteDate central)	Get the entries surrounding a central date.
static Transform	FramesFactory.getNonInterpolatingTransform(Frame from, Frame to, AbsoluteDate date)	Get the transform between two frames, suppressing all interpolation.
double[]	EOPHistory.getNonRotatinOriginNutationCorrection(AbsoluteDate date)	Get the correction to the nutation parameters for Non-Rotating Origin paradigm.
PoleCorrection	EOPHistory.getPoleCorrection(AbsoluteDate date)	Get the pole IERS Reference Pole correction.
TimeStampedPVCoordinates	TopocentricFrame.getPVCoordinates(AbsoluteDate date, Frame frame)	Get the PVCoordinates of the topocentric frame origin in the selected frame.
double	TopocentricFrame.getRange(org.hipparchus.geometry.euclidean.threed.Vector3D extPoint, Frame frame, AbsoluteDate date)	Get the range of a point with regards to the topocentric frame center point.
double	TopocentricFrame.getRangeRate(PVCoordinates extPV, Frame frame, AbsoluteDate date)	Get the range rate of a point with regards to the topocentric frame center point.
Transform	EclipticProvider.getTransform(AbsoluteDate date)
Transform	FixedTransformProvider.getTransform(AbsoluteDate date)	Get the Transform corresponding to specified date.
Transform	GTODProvider.getTransform(AbsoluteDate date)	Get the Transform corresponding to specified date.
Transform	HelmertTransformation.getTransform(AbsoluteDate date)	Get the Transform corresponding to specified date.
Transform	InterpolatingTransformProvider.getTransform(AbsoluteDate date)	Get the Transform corresponding to specified date.
Transform	ITRFVersion.Converter.getTransform(AbsoluteDate date)	Get the Transform corresponding to specified date.
Transform	L1TransformProvider.getTransform(AbsoluteDate date)	Get the Transform corresponding to specified date.
Transform	ShiftingTransformProvider.getTransform(AbsoluteDate date)	Get the Transform corresponding to specified date.
Transform	TransformProvider.getTransform(AbsoluteDate date)	Get the Transform corresponding to specified date.
Transform	Frame.getTransformTo(Frame destination, AbsoluteDate date)	Get the transform from the instance to another frame.
double	EOPHistory.getUT1MinusUTC(AbsoluteDate date)	Get the UT1-UTC value.
protected boolean	EOPHistory.hasDataFor(AbsoluteDate date)	Check if the cache has data for the given date using EOPHistory.getStartDate() and EOPHistory.getEndDate().
Transform	Transform.interpolate(AbsoluteDate interpolationDate, Stream<Transform> sample)	Get an interpolated instance.
static Transform	Transform.interpolate(AbsoluteDate date, CartesianDerivativesFilter cFilter, AngularDerivativesFilter aFilter, Collection<Transform> sample)	Interpolate a transform from a sample set of existing transforms.
Transform	LOFType.transformFromInertial(AbsoluteDate date, PVCoordinates pv)	Get the transform from an inertial frame defining position-velocity and the local orbital frame.
void	UpdatableFrame.updateTransform(Frame f1, Frame f2, Transform f1Tof2, AbsoluteDate date)	Update the transform from parent frame implicitly according to two other frames.

Constructors in org.orekit.frames with parameters of type AbsoluteDate

Constructor	Description
HelmertTransformation(AbsoluteDate epoch, double t1, double t2, double t3, double r1, double r2, double r3, double t1Dot, double t2Dot, double t3Dot, double r1Dot, double r2Dot, double r3Dot)	Build a transform from its primitive operations.
InterpolatingTransformProvider(TransformProvider rawProvider, CartesianDerivativesFilter cFilter, AngularDerivativesFilter aFilter, AbsoluteDate earliest, AbsoluteDate latest, int gridPoints, double step, int maxSlots, double maxSpan, double newSlotInterval)	Deprecated. as of 9.1, replaced by InterpolatingTransformProvider(TransformProvider, CartesianDerivativesFilter, AngularDerivativesFilter, int, double, int, double, double)
ShiftingTransformProvider(TransformProvider rawProvider, CartesianDerivativesFilter cFilter, AngularDerivativesFilter aFilter, AbsoluteDate earliest, AbsoluteDate latest, int gridPoints, double step, int maxSlots, double maxSpan, double newSlotInterval)	Deprecated. as of 9.1, replaced by ShiftingTransformProvider(TransformProvider, CartesianDerivativesFilter, AngularDerivativesFilter, int, double, int, double, double)
Transform(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Rotation rotation)	Build a rotation transform.
Transform(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Rotation rotation, org.hipparchus.geometry.euclidean.threed.Vector3D rotationRate)	Build a rotation transform.
Transform(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Rotation rotation, org.hipparchus.geometry.euclidean.threed.Vector3D rotationRate, org.hipparchus.geometry.euclidean.threed.Vector3D rotationAcceleration)	Build a rotation transform.
Transform(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D translation)	Build a translation transform.
Transform(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D translation, org.hipparchus.geometry.euclidean.threed.Vector3D velocity)	Build a translation transform, with its first time derivative.
Transform(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D translation, org.hipparchus.geometry.euclidean.threed.Vector3D velocity, org.hipparchus.geometry.euclidean.threed.Vector3D acceleration)	Build a translation transform, with its first and second time derivatives.
Transform(AbsoluteDate date, Transform first, Transform second)	Build a transform by combining two existing ones.
Transform(AbsoluteDate date, AngularCoordinates angular)	Build a rotation transform.
Transform(AbsoluteDate date, PVCoordinates cartesian)	Build a translation transform, with its first time derivative.

Uses of AbsoluteDate in org.orekit.gnss

Methods in org.orekit.gnss that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	DOP.getDate()	Gets the calculation date of the DOP.
AbsoluteDate	GPSAlmanac.getDate()
AbsoluteDate	ObservationDataSet.getDate()	Get the date.
AbsoluteDate	RinexHeader.getTFirstObs()	Get the time of First observation record.
AbsoluteDate	RinexHeader.getTLastObs()	Get the time of last observation record.

Methods in org.orekit.gnss with parameters of type AbsoluteDate

Modifier and Type	Method	Description
DOP	DOPComputer.compute(AbsoluteDate date, List<Propagator> gnss)	Compute the DOP at a given date for a set of GNSS spacecrafts.

Constructors in org.orekit.gnss with parameters of type AbsoluteDate

Constructor	Description
DOP(GeodeticPoint location, AbsoluteDate date, int gnssNb, double gdop, double pdop, double hdop, double vdop, double tdop)	Constructor.
ObservationDataSet(RinexHeader header, SatelliteSystem satelliteSystem, int prnNumber, AbsoluteDate tObs, double rcvrClkOffset, List<ObservationData> observationData)	Simple constructor.
RinexHeader(double rinexVersion, SatelliteSystem satelliteSystem, String markerName, String markerNumber, String markerType, String observerName, String agencyName, String receiverNumber, String receiverType, String receiverVersion, String antennaNumber, String antennaType, org.hipparchus.geometry.euclidean.threed.Vector3D approxPos, double antHeight, org.hipparchus.geometry.euclidean.twod.Vector2D eccentricities, org.hipparchus.geometry.euclidean.threed.Vector3D antRefPoint, String obsCode, org.hipparchus.geometry.euclidean.threed.Vector3D antPhaseCenter, org.hipparchus.geometry.euclidean.threed.Vector3D antBSight, double antAzi, org.hipparchus.geometry.euclidean.threed.Vector3D antZeroDir, org.hipparchus.geometry.euclidean.threed.Vector3D centerMass, String sigStrengthUnit, double interval, AbsoluteDate tFirstObs, AbsoluteDate tLastObs, int clkOffset, List<RinexLoader.Parser.AppliedDCBS> listAppliedDCBS, List<RinexLoader.Parser.AppliedPCVS> listAppliedPCVS, List<RinexLoader.Parser.PhaseShiftCorrection> phaseShiftCorrections, int leapSeconds, int leapSecondsFuture, int leapSecondsWeekNum, int leapSecondsDayNum)	Simple constructor, for Rinex 3 Header.
RinexHeader(double rinexVersion, SatelliteSystem satelliteSystem, String markerName, String markerNumber, String markerType, String observerName, String agencyName, String receiverNumber, String receiverType, String receiverVersion, String antennaNumber, String antennaType, org.hipparchus.geometry.euclidean.threed.Vector3D approxPos, double antHeight, org.hipparchus.geometry.euclidean.twod.Vector2D eccentricities, org.hipparchus.geometry.euclidean.threed.Vector3D antRefPoint, org.hipparchus.geometry.euclidean.threed.Vector3D antBSight, org.hipparchus.geometry.euclidean.threed.Vector3D centerMass, double interval, AbsoluteDate tFirstObs, AbsoluteDate tLastObs, int clkOffset, int leapSeconds)	Simple constructor, for Rinex 2 Header.

Uses of AbsoluteDate in org.orekit.gnss.antenna

Methods in org.orekit.gnss.antenna that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	SatelliteAntenna.getValidFrom()	Get start of validity.
AbsoluteDate	SatelliteAntenna.getValidFUntil()	Get end of validity.

Methods in org.orekit.gnss.antenna with parameters of type AbsoluteDate

Modifier and Type	Method	Description
abstract GNSSAttitudeProvider	SatelliteType.buildAttitudeProvider(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame, int prnNumber)	Build an attitude provider suitable for this satellite type.

Constructors in org.orekit.gnss.antenna with parameters of type AbsoluteDate

Constructor	Description
SatelliteAntenna(String type, String sinexCode, Map<Frequency,FrequencyPattern> patterns, SatelliteSystem satelliteSystem, int prnNumber, int satelliteCode, String cosparID, AbsoluteDate validFrom, AbsoluteDate validUntil)	Deprecated. since 9.3 replaced by SatelliteAntenna(String, String, Map, SatelliteSystem, int, SatelliteType, int, String, AbsoluteDate, AbsoluteDate)
SatelliteAntenna(String type, String sinexCode, Map<Frequency,FrequencyPattern> patterns, SatelliteSystem satelliteSystem, int prnNumber, SatelliteType satelliteType, int satelliteCode, String cosparID, AbsoluteDate validFrom, AbsoluteDate validUntil)	Simple constructor.

Uses of AbsoluteDate in org.orekit.gnss.attitude

Methods in org.orekit.gnss.attitude that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	AbstractGNSSAttitudeProvider.validityEnd()	Get end of validity for this provider.
AbsoluteDate	GNSSAttitudeProvider.validityEnd()	Get end of validity for this provider.
AbsoluteDate	AbstractGNSSAttitudeProvider.validityStart()	Get start of validity for this provider.
AbsoluteDate	GNSSAttitudeProvider.validityStart()	Get start of validity for this provider.

Methods in org.orekit.gnss.attitude with parameters of type AbsoluteDate

Modifier and Type	Method	Description
Attitude	AbstractGNSSAttitudeProvider.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.

Constructors in org.orekit.gnss.attitude with parameters of type AbsoluteDate

Constructor	Description
AbstractGNSSAttitudeProvider(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)	Simple constructor.
BeidouGeo(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)	Simple constructor.
BeidouIGSO(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)	Simple constructor.
BeidouMeo(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)	Simple constructor.
Galileo(double yawRate, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)	Simple constructor.
GenericGNSS(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)	Simple constructor.
Glonass(double yawRate, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)	Simple constructor.
GPSBlockIIA(double yawRate, double yawBias, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)	Simple constructor.
GPSBlockIIA(double yawRate, double yawBias, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame, int prnNumber)	Deprecated. as of 9.3 replaced by GPSBlockIIA(double, double, AbsoluteDate, AbsoluteDate, ExtendedPVCoordinatesProvider, Frame)
GPSBlockIIF(double yawRate, double yawBias, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)	Simple constructor.
GPSBlockIIR(double yawRate, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)	Simple constructor.

Uses of AbsoluteDate in org.orekit.models.earth

Methods in org.orekit.models.earth with parameters of type AbsoluteDate

Modifier and Type	Method	Description
double[]	DiscreteTroposphericModel.computeZenithDelay(double height, double[] parameters, AbsoluteDate date)	This method allows the computation of the zenith hydrostatic and zenith wet delay.
double[]	EstimatedTroposphericModel.computeZenithDelay(double height, double[] parameters, AbsoluteDate date)	This method allows the computation of the zenith hydrostatic and zenith total delays.
double[]	MendesPavlisModel.computeZenithDelay(double height, double[] parameters, AbsoluteDate date)	This method allows the computation of the zenith hydrostatic and zenith wet delay.
default double[]	TroposphericModel.computeZenithDelay(double height, double[] parameters, AbsoluteDate date)	This method allows the computation of the zenith hydrostatic and zenith wet delay.
double[]	ViennaOneModel.computeZenithDelay(double height, double[] parameters, AbsoluteDate date)	This method allows the computation of the zenith hydrostatic and zenith wet delay.
double[]	ViennaThreeModel.computeZenithDelay(double height, double[] parameters, AbsoluteDate date)	This method allows the computation of the zenith hydrostatic and zenith wet delay.
GeodeticPoint	Geoid.getIntersectionPoint(org.hipparchus.geometry.euclidean.threed.Line lineInFrame, org.hipparchus.geometry.euclidean.threed.Vector3D closeInFrame, Frame frame, AbsoluteDate date)	Get the intersection point of a line with the surface of the body.
double	Geoid.getUndulation(double geodeticLatitude, double longitude, AbsoluteDate date)	Gets the Undulation of the Geoid, N at the given position.
double[]	EstimatedTroposphericModel.mappingFactors(double elevation, double height, double[] parameters, AbsoluteDate date)
double[]	GlobalMappingFunctionModel.mappingFactors(double elevation, double height, double[] parameters, AbsoluteDate date)	This method allows the computation of the hydrostatic and wet mapping functions.
double[]	MappingFunction.mappingFactors(double elevation, double height, double[] parameters, AbsoluteDate date)	This method allows the computation of the hydrostatic and wet mapping functions.
double[]	MendesPavlisModel.mappingFactors(double elevation, double height, double[] parameters, AbsoluteDate date)	With the Mendes Pavlis tropospheric model, the mapping function is not split into hydrostatic and wet component.
double[]	NiellMappingFunctionModel.mappingFactors(double elevation, double height, double[] parameters, AbsoluteDate date)
default double[]	TroposphericModel.mappingFactors(double elevation, double height, double[] parameters, AbsoluteDate date)	This method allows the computation of the hydrostatic and wet mapping functions.
double[]	ViennaOneModel.mappingFactors(double elevation, double height, double[] parameters, AbsoluteDate date)	This method allows the computation of the hydrostatic and wet mapping functions.
double[]	ViennaThreeModel.mappingFactors(double elevation, double height, double[] parameters, AbsoluteDate date)	This method allows the computation of the hydrostatic and wet mapping functions.
double	DiscreteTroposphericModel.pathDelay(double elevation, double height, double[] parameters, AbsoluteDate date)	Calculates the tropospheric path delay for the signal path from a ground station to a satellite.
double	EstimatedTroposphericModel.pathDelay(double elevation, double height, double[] parameters, AbsoluteDate date)
double	IonosphericModel.pathDelay(AbsoluteDate date, GeodeticPoint geo, double elevation, double azimuth)	Calculates the ionospheric path delay for the signal path from a ground station to a satellite.
double	KlobucharIonoModel.pathDelay(AbsoluteDate date, GeodeticPoint geo, double elevation, double azimuth)	Calculates the ionospheric path delay for the signal path from a ground station to a satellite.
double	MendesPavlisModel.pathDelay(double elevation, double height, double[] parameters, AbsoluteDate date)	Calculates the tropospheric path delay for the signal path from a ground station to a satellite.
default double	TroposphericModel.pathDelay(double elevation, double height, double[] parameters, AbsoluteDate date)	Calculates the tropospheric path delay for the signal path from a ground station to a satellite.
double	ViennaOneModel.pathDelay(double elevation, double height, double[] parameters, AbsoluteDate date)	Calculates the tropospheric path delay for the signal path from a ground station to a satellite.
double	ViennaThreeModel.pathDelay(double elevation, double height, double[] parameters, AbsoluteDate date)	Calculates the tropospheric path delay for the signal path from a ground station to a satellite.
org.hipparchus.geometry.euclidean.threed.Vector3D	Geoid.projectToGround(org.hipparchus.geometry.euclidean.threed.Vector3D point, AbsoluteDate date, Frame frame)
GeodeticPoint	Geoid.transform(org.hipparchus.geometry.euclidean.threed.Vector3D point, Frame frame, AbsoluteDate date)	Transform a Cartesian point to a surface-relative point.
void	GlobalPressureTemperature2Model.weatherParameters(double stationHeight, AbsoluteDate currentDate)
void	GlobalPressureTemperatureModel.weatherParameters(double height, AbsoluteDate date)
void	WeatherModel.weatherParameters(double stationHeight, AbsoluteDate currentDate)	Calculates the weather parameters of the model.

Uses of AbsoluteDate in org.orekit.orbits

Methods in org.orekit.orbits that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	Orbit.getDate()	Get the date of orbital parameters.

Methods in org.orekit.orbits with parameters of type AbsoluteDate

Modifier and Type	Method	Description
TimeStampedPVCoordinates	Orbit.getPVCoordinates(AbsoluteDate otherDate, Frame otherFrame)	Get the PVCoordinates of the body in the selected frame.
CartesianOrbit	CartesianOrbit.interpolate(AbsoluteDate date, Stream<Orbit> sample)	Get an interpolated instance.
CircularOrbit	CircularOrbit.interpolate(AbsoluteDate date, Stream<Orbit> sample)	Get an interpolated instance.
EquinoctialOrbit	EquinoctialOrbit.interpolate(AbsoluteDate date, Stream<Orbit> sample)	Get an interpolated instance.
KeplerianOrbit	KeplerianOrbit.interpolate(AbsoluteDate date, Stream<Orbit> sample)	Get an interpolated instance.
abstract Orbit	OrbitType.mapArrayToOrbit(double[] array, double[] arrayDot, PositionAngle type, AbsoluteDate date, double mu, Frame frame)	Convert state array to orbital parameters.

Constructors in org.orekit.orbits with parameters of type AbsoluteDate

Constructor	Description
CartesianOrbit(PVCoordinates pvaCoordinates, Frame frame, AbsoluteDate date, double mu)	Constructor from Cartesian parameters.
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, PositionAngle type, Frame frame, AbsoluteDate date, double mu)	Creates a new instance.
CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, PositionAngle type, Frame frame, AbsoluteDate date, double mu)	Creates a new instance.
CircularOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu)	Constructor from Cartesian parameters.
EquinoctialOrbit(double a, double ex, double ey, double hx, double hy, double l, double aDot, double exDot, double eyDot, double hxDot, double hyDot, double lDot, PositionAngle type, Frame frame, AbsoluteDate date, double mu)	Creates a new instance.
EquinoctialOrbit(double a, double ex, double ey, double hx, double hy, double l, PositionAngle type, Frame frame, AbsoluteDate date, double mu)	Creates a new instance.
EquinoctialOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu)	Constructor from Cartesian parameters.
KeplerianOrbit(double a, double e, double i, double pa, double raan, double anomaly, double aDot, double eDot, double iDot, double paDot, double raanDot, double anomalyDot, PositionAngle type, Frame frame, AbsoluteDate date, double mu)	Creates a new instance.
KeplerianOrbit(double a, double e, double i, double pa, double raan, double anomaly, PositionAngle type, Frame frame, AbsoluteDate date, double mu)	Creates a new instance.
KeplerianOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu)	Constructor from Cartesian parameters.
Orbit(Frame frame, AbsoluteDate date, double mu)	Default constructor.

Uses of AbsoluteDate in org.orekit.propagation

Methods in org.orekit.propagation that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	SpacecraftState.getDate()	Get the date.
AbsoluteDate	BoundedPropagator.getMaxDate()	Get the last date of the range.
AbsoluteDate	BoundedPropagator.getMinDate()	Get the first date of the range.
protected AbsoluteDate	AbstractPropagator.getStartDate()	Get the start date.

Methods in org.orekit.propagation with parameters of type AbsoluteDate

Modifier and Type	Method	Description
TimeStampedPVCoordinates	AbstractPropagator.getPVCoordinates(AbsoluteDate date, Frame frame)	Get the PVCoordinates of the body in the selected frame.
SpacecraftState	SpacecraftState.interpolate(AbsoluteDate date, Stream<SpacecraftState> sample)	Get an interpolated instance.
SpacecraftState	AbstractPropagator.propagate(AbsoluteDate target)	Propagate towards a target date.
SpacecraftState	Propagator.propagate(AbsoluteDate target)	Propagate towards a target date.
SpacecraftState	Propagator.propagate(AbsoluteDate start, AbsoluteDate target)	Propagate from a start date towards a target date.
List<SpacecraftState>	PropagatorsParallelizer.propagate(AbsoluteDate start, AbsoluteDate target)	Propagate from a start date towards a target date.
protected void	AbstractPropagator.setStartDate(AbsoluteDate startDate)	Set a start date.

Uses of AbsoluteDate in org.orekit.propagation.analytical

Methods in org.orekit.propagation.analytical that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	AggregateBoundedPropagator.getMaxDate()
AbsoluteDate	Ephemeris.getMaxDate()	Get the last date of the range.
AbsoluteDate	AggregateBoundedPropagator.getMinDate()
AbsoluteDate	Ephemeris.getMinDate()	Get the first date of the range.

Methods in org.orekit.propagation.analytical with parameters of type AbsoluteDate

Modifier and Type	Method	Description
protected SpacecraftState	AbstractAnalyticalPropagator.acceptStep(OrekitStepInterpolator interpolator, AbsoluteDate target, double epsilon)	Accept a step, triggering events and step handlers.
protected SpacecraftState	AbstractAnalyticalPropagator.basicPropagate(AbsoluteDate date)	Propagate an orbit without any fancy features.
protected SpacecraftState	AdapterPropagator.basicPropagate(AbsoluteDate date)	Propagate an orbit without any fancy features.
SpacecraftState	Ephemeris.basicPropagate(AbsoluteDate date)
protected abstract double	AbstractAnalyticalPropagator.getMass(AbsoluteDate date)	Get the mass.
protected double	AdapterPropagator.getMass(AbsoluteDate date)	Get the mass.
protected double	AggregateBoundedPropagator.getMass(AbsoluteDate date)
protected double	EcksteinHechlerPropagator.getMass(AbsoluteDate date)	Get the mass.
protected double	Ephemeris.getMass(AbsoluteDate date)	Get the mass.
protected double	KeplerianPropagator.getMass(AbsoluteDate date)	Get the mass.
TimeStampedPVCoordinates	AggregateBoundedPropagator.getPVCoordinates(AbsoluteDate date, Frame frame)
TimeStampedPVCoordinates	Ephemeris.getPVCoordinates(AbsoluteDate date, Frame f)	Get the PVCoordinates of the body in the selected frame.
SpacecraftState	AbstractAnalyticalPropagator.propagate(AbsoluteDate start, AbsoluteDate target)	Propagate from a start date towards a target date.
protected abstract Orbit	AbstractAnalyticalPropagator.propagateOrbit(AbsoluteDate date)	Extrapolate an orbit up to a specific target date.
protected Orbit	AdapterPropagator.propagateOrbit(AbsoluteDate date)	Extrapolate an orbit up to a specific target date.
protected Orbit	AggregateBoundedPropagator.propagateOrbit(AbsoluteDate date)
CartesianOrbit	EcksteinHechlerPropagator.propagateOrbit(AbsoluteDate date)	Extrapolate an orbit up to a specific target date.
protected Orbit	Ephemeris.propagateOrbit(AbsoluteDate date)	Extrapolate an orbit up to a specific target date.
protected Orbit	KeplerianPropagator.propagateOrbit(AbsoluteDate date)	Extrapolate an orbit up to a specific target date.

Uses of AbsoluteDate in org.orekit.propagation.analytical.gnss

Methods in org.orekit.propagation.analytical.gnss with parameters of type AbsoluteDate

Modifier and Type	Method	Description
protected double	GPSPropagator.getMass(AbsoluteDate date)	Get the mass.
PVCoordinates	GPSPropagator.propagateInEcef(AbsoluteDate date)	Gets the PVCoordinates of the GPS SV in ECEF frame.
protected Orbit	GPSPropagator.propagateOrbit(AbsoluteDate date)	Extrapolate an orbit up to a specific target date.

Uses of AbsoluteDate in org.orekit.propagation.analytical.tle

Methods in org.orekit.propagation.analytical.tle that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	TLE.getDate()	Get the TLE current date.
AbsoluteDate	TLESeries.getFirstDate()	Deprecated. Get the start date of the series.
AbsoluteDate	TLESeries.getLastDate()	Deprecated. Get the last date of the series.

Methods in org.orekit.propagation.analytical.tle with parameters of type AbsoluteDate

Modifier and Type	Method	Description
TLE	TLESeries.getClosestTLE(AbsoluteDate date)	Deprecated. Get the closest TLE to the selected date.
protected double	TLEPropagator.getMass(AbsoluteDate date)	Get the mass.
PVCoordinates	TLEPropagator.getPVCoordinates(AbsoluteDate date)	Get the extrapolated position and velocity from an initial TLE.
PVCoordinates	TLESeries.getPVCoordinates(AbsoluteDate date)	Deprecated. Get the extrapolated position and velocity from an initial date.
protected Orbit	TLEPropagator.propagateOrbit(AbsoluteDate date)	Extrapolate an orbit up to a specific target date.

Constructors in org.orekit.propagation.analytical.tle with parameters of type AbsoluteDate

Constructor	Description
TLE(int satelliteNumber, char classification, int launchYear, int launchNumber, String launchPiece, int ephemerisType, int elementNumber, AbsoluteDate epoch, double meanMotion, double meanMotionFirstDerivative, double meanMotionSecondDerivative, double e, double i, double pa, double raan, double meanAnomaly, int revolutionNumberAtEpoch, double bStar)	Simple constructor from already parsed elements.

Uses of AbsoluteDate in org.orekit.propagation.conversion

Methods in org.orekit.propagation.conversion that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	AbstractPropagatorBuilder.getInitialOrbitDate()	Get the date of the initial orbit.
AbsoluteDate	PropagatorBuilder.getInitialOrbitDate()	Get the date of the initial orbit.

Uses of AbsoluteDate in org.orekit.propagation.events

Methods in org.orekit.propagation.events that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	DateDetector.getDate()	Get the current event date according to the propagator.
AbsoluteDate	EventState.getEventDate()	Get the occurrence time of the event triggered in the current step.
AbsoluteDate	EventState.EventOccurrence.getStopDate()	Get the new time for a stop action.

Methods in org.orekit.propagation.events with parameters of type AbsoluteDate

Modifier and Type	Method	Description
void	DateDetector.addEventDate(AbsoluteDate target)	Add an event date.
void	AbstractDetector.init(SpacecraftState s0, AbsoluteDate t)	Initialize event handler at the start of a propagation.
void	AdapterDetector.init(SpacecraftState s0, AbsoluteDate t)	Initialize event handler at the start of a propagation.
void	BooleanDetector.init(SpacecraftState s0, AbsoluteDate t)
default void	EventDetector.init(SpacecraftState s0, AbsoluteDate t)	Initialize event handler at the start of a propagation.
void	EventEnablingPredicateFilter.init(SpacecraftState s0, AbsoluteDate t)	Initialize event handler at the start of a propagation.
void	EventShifter.init(SpacecraftState s0, AbsoluteDate t)	Initialize event handler at the start of a propagation.
void	EventSlopeFilter.init(SpacecraftState s0, AbsoluteDate t)	Initialize event handler at the start of a propagation.
void	EventState.init(SpacecraftState s0, AbsoluteDate t)	Initialize event handler at the start of a propagation.
void	NegateDetector.init(SpacecraftState s0, AbsoluteDate t)
void	PositionAngleDetector.init(SpacecraftState s0, AbsoluteDate t)	Initialize event handler at the start of a propagation.

Constructors in org.orekit.propagation.events with parameters of type AbsoluteDate

Constructor	Description
DateDetector(AbsoluteDate target)	Build a new instance.

Uses of AbsoluteDate in org.orekit.propagation.events.handlers

Methods in org.orekit.propagation.events.handlers with parameters of type AbsoluteDate

Modifier and Type	Method	Description
default void	EventHandler.init(SpacecraftState initialState, AbsoluteDate target)	Initialize event handler at the start of a propagation.

Uses of AbsoluteDate in org.orekit.propagation.integration

Methods in org.orekit.propagation.integration that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	IntegratedEphemeris.getMaxDate()	Get the last date of the range.
AbsoluteDate	IntegratedEphemeris.getMinDate()	Get the first date of the range.
AbsoluteDate	StateMapper.getReferenceDate()	Get reference date.
AbsoluteDate	StateMapper.mapDoubleToDate(double t)	Map the raw double time offset to a date.
AbsoluteDate	StateMapper.mapDoubleToDate(double t, AbsoluteDate date)	Map the raw double time offset to a date.

Methods in org.orekit.propagation.integration with parameters of type AbsoluteDate

Modifier and Type	Method	Description
protected SpacecraftState	IntegratedEphemeris.basicPropagate(AbsoluteDate date)	Propagate an orbit without any fancy features.
protected void	AbstractIntegratedPropagator.beforeIntegration(SpacecraftState initialState, AbsoluteDate tEnd)	Method called just before integration.
protected abstract StateMapper	AbstractIntegratedPropagator.createMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame)	Create a mapper between raw double components and spacecraft state.
protected double	IntegratedEphemeris.getMass(AbsoluteDate date)	Get the mass.
TimeStampedPVCoordinates	IntegratedEphemeris.getPVCoordinates(AbsoluteDate date, Frame frame)	Get the PVCoordinates of the body in the selected frame.
default void	AbstractIntegratedPropagator.MainStateEquations.init(SpacecraftState initialState, AbsoluteDate target)	Initialize the equations at the start of propagation.
default void	AdditionalEquations.init(SpacecraftState initialState, AbsoluteDate target)	Initialize the equations at the start of propagation.
void	ModeHandler.initialize(boolean activateHandlers, AbsoluteDate targetDate)	Initialize the mode handler.
abstract SpacecraftState	StateMapper.mapArrayToState(AbsoluteDate date, double[] y, double[] yDot, boolean meanOnly)	Map the raw double components to a spacecraft state.
double	StateMapper.mapDateToDouble(AbsoluteDate date)	Map a date to a raw double time offset.
AbsoluteDate	StateMapper.mapDoubleToDate(double t, AbsoluteDate date)	Map the raw double time offset to a date.
SpacecraftState	AbstractIntegratedPropagator.propagate(AbsoluteDate target)	Propagate towards a target date.
protected SpacecraftState	AbstractIntegratedPropagator.propagate(AbsoluteDate tEnd, boolean activateHandlers)	Propagation with or without event detection.
SpacecraftState	AbstractIntegratedPropagator.propagate(AbsoluteDate tStart, AbsoluteDate tEnd)	Propagate from a start date towards a target date.
protected Orbit	IntegratedEphemeris.propagateOrbit(AbsoluteDate date)	Extrapolate an orbit up to a specific target date.

Constructors in org.orekit.propagation.integration with parameters of type AbsoluteDate

Constructor	Description
IntegratedEphemeris(AbsoluteDate startDate, AbsoluteDate minDate, AbsoluteDate maxDate, StateMapper mapper, boolean meanOrbit, org.hipparchus.ode.DenseOutputModel model, Map<String,double[]> unmanaged, List<AdditionalStateProvider> providers, String[] equations)	Creates a new instance of IntegratedEphemeris.
StateMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame)	Simple constructor.

Uses of AbsoluteDate in org.orekit.propagation.numerical

Methods in org.orekit.propagation.numerical with parameters of type AbsoluteDate

Modifier and Type	Method	Description
protected StateMapper	NumericalPropagator.createMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame)	Create a mapper between raw double components and spacecraft state.
TimeStampedPVCoordinates	NumericalPropagator.getPVCoordinates(AbsoluteDate date, Frame frame)	Get the PVCoordinates of the body in the selected frame.

Uses of AbsoluteDate in org.orekit.propagation.sampling

Methods in org.orekit.propagation.sampling with parameters of type AbsoluteDate

Modifier and Type	Method	Description
SpacecraftState	OrekitStepInterpolator.getInterpolatedState(AbsoluteDate date)	Get the state at interpolated date.
default void	MultiSatStepHandler.init(List<SpacecraftState> states0, AbsoluteDate t)	Initialize step handler at the start of a propagation.
default void	OrekitFixedStepHandler.init(SpacecraftState s0, AbsoluteDate t)	Deprecated. as of 9.0, replaced by OrekitFixedStepHandler.init(SpacecraftState, AbsoluteDate, double)
default void	OrekitFixedStepHandler.init(SpacecraftState s0, AbsoluteDate t, double step)	Initialize step handler at the start of a propagation.
default void	OrekitStepHandler.init(SpacecraftState s0, AbsoluteDate t)	Initialize step handler at the start of a propagation.
void	OrekitStepHandlerMultiplexer.init(SpacecraftState s0, AbsoluteDate t)	Initialize step handler at the start of a propagation.
void	OrekitStepNormalizer.init(SpacecraftState s0, AbsoluteDate t)	Initialize step handler at the start of a propagation.

Uses of AbsoluteDate in org.orekit.propagation.semianalytical.dsst

Methods in org.orekit.propagation.semianalytical.dsst with parameters of type AbsoluteDate

Modifier and Type	Method	Description
protected void	DSSTPropagator.beforeIntegration(SpacecraftState initialState, AbsoluteDate tEnd)	Method called just before integration.
protected StateMapper	DSSTPropagator.createMapper(AbsoluteDate referenceDate, double mu, OrbitType ignoredOrbitType, PositionAngle ignoredPositionAngleType, AttitudeProvider attitudeProvider, Frame frame)	Create a mapper between raw double components and spacecraft state.

Uses of AbsoluteDate in org.orekit.propagation.semianalytical.dsst.forces

Methods in org.orekit.propagation.semianalytical.dsst.forces with parameters of type AbsoluteDate

Modifier and Type	Method	Description
Map<String,double[]>	ShortPeriodTerms.getCoefficients(AbsoluteDate date, Set<String> selected)	Computes the coefficients involved in the contributions.

Uses of AbsoluteDate in org.orekit.propagation.semianalytical.dsst.utilities

Methods in org.orekit.propagation.semianalytical.dsst.utilities that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	AuxiliaryElements.getDate()	Get the date of the orbit.

Methods in org.orekit.propagation.semianalytical.dsst.utilities with parameters of type AbsoluteDate

Modifier and Type	Method	Description
void	ShortPeriodicsInterpolatedCoefficient.addGridPoint(AbsoluteDate date, double[] value)	Add a point to the interpolation grid.
double[]	ShortPeriodicsInterpolatedCoefficient.value(AbsoluteDate date)	Compute the value of the coefficient.

Uses of AbsoluteDate in org.orekit.time

Fields in org.orekit.time declared as AbsoluteDate

Modifier and Type	Field	Description
static AbsoluteDate	AbsoluteDate.CCSDS_EPOCH	Reference epoch for CCSDS Time Code Format (CCSDS 301.0-B-4): 1958-01-01T00:00:00 International Atomic Time (not UTC).
static AbsoluteDate	AbsoluteDate.FIFTIES_EPOCH	Reference epoch for 1950 dates: 1950-01-01T00:00:00 Terrestrial Time.
static AbsoluteDate	AbsoluteDate.FUTURE_INFINITY	Dummy date at infinity in the future direction.
static AbsoluteDate	AbsoluteDate.GALILEO_EPOCH	Reference epoch for Galileo System Time: 1999-08-22T00:00:00 UTC.
static AbsoluteDate	AbsoluteDate.GPS_EPOCH	Reference epoch for GPS weeks: 1980-01-06T00:00:00 GPS time.
static AbsoluteDate	AbsoluteDate.J2000_EPOCH	J2000.0 Reference epoch: 2000-01-01T12:00:00 Terrestrial Time (not UTC).
static AbsoluteDate	AbsoluteDate.JAVA_EPOCH	Java Reference epoch: 1970-01-01T00:00:00 Universal Time Coordinate.
static AbsoluteDate	AbsoluteDate.JULIAN_EPOCH	Reference epoch for julian dates: -4712-01-01T12:00:00 Terrestrial Time.
static AbsoluteDate	AbsoluteDate.MODIFIED_JULIAN_EPOCH	Reference epoch for modified julian dates: 1858-11-17T00:00:00 Terrestrial Time.
static AbsoluteDate	AbsoluteDate.PAST_INFINITY	Dummy date at infinity in the past direction.

Methods in org.orekit.time that return AbsoluteDate

Modifier and Type	Method	Description
static AbsoluteDate	AbsoluteDate.createBesselianEpoch(double besselianEpoch)	Build an instance corresponding to a Besselian Epoch (BE).
static AbsoluteDate	AbsoluteDate.createGPSDate(int weekNumber, double milliInWeek)	Deprecated. as of 9.3, replaced by GPSDate(int, double).GPSDate.getDate()
static AbsoluteDate	AbsoluteDate.createJDDate(int jd, double secondsSinceNoon, TimeScale timeScale)	Build an instance corresponding to a Julian Day date.
static AbsoluteDate	AbsoluteDate.createJulianEpoch(double julianEpoch)	Build an instance corresponding to a Julian Epoch (JE).
static AbsoluteDate	AbsoluteDate.createMJDDate(int mjd, double secondsInDay, TimeScale timeScale)	Build an instance corresponding to a Modified Julian Day date.
AbsoluteDate	AbsoluteDate.getDate()	Get the date.
AbsoluteDate	GPSDate.getDate()	Get the date.
AbsoluteDate	TimeStamped.getDate()	Get the date.
AbsoluteDate	UTCScale.getFirstKnownLeapSecond()	Get the date of the first known leap second.
AbsoluteDate	UTCScale.getLastKnownLeapSecond()	Get the date of the last known leap second.
static AbsoluteDate	AbsoluteDate.parseCCSDSCalendarSegmentedTimeCode(byte preambleField, byte[] timeField)	Build an instance from a CCSDS Calendar Segmented Time Code (CCS).
static AbsoluteDate	AbsoluteDate.parseCCSDSDaySegmentedTimeCode(byte preambleField, byte[] timeField, DateComponents agencyDefinedEpoch)	Build an instance from a CCSDS Day Segmented Time Code (CDS).
static AbsoluteDate	AbsoluteDate.parseCCSDSUnsegmentedTimeCode(byte preambleField1, byte preambleField2, byte[] timeField, AbsoluteDate agencyDefinedEpoch)	Build an instance from a CCSDS Unsegmented Time Code (CUC).
AbsoluteDate	AbsoluteDate.shiftedBy(double dt)	Get a time-shifted date.
AbsoluteDate	FieldAbsoluteDate.toAbsoluteDate()	Transform the FieldAbsoluteDate in an AbsoluteDate.

Methods in org.orekit.time that return types with arguments of type AbsoluteDate

Modifier and Type	Method	Description
List<AbsoluteDate>	BurstSelector.selectDates(AbsoluteDate start, AbsoluteDate end)	Select dates within an interval.
List<AbsoluteDate>	DatesSelector.selectDates(AbsoluteDate start, AbsoluteDate end)	Select dates within an interval.
List<AbsoluteDate>	FixedStepSelector.selectDates(AbsoluteDate start, AbsoluteDate end)	Select dates within an interval.

Methods in org.orekit.time with parameters of type AbsoluteDate

Modifier and Type	Method	Description
int	AbsoluteDate.compareTo(AbsoluteDate date)	Compare the instance with another date.
double	AbsoluteDate.durationFrom(AbsoluteDate instant)	Compute the physically elapsed duration between two instants.
T	FieldAbsoluteDate.durationFrom(AbsoluteDate instant)	Compute the physically elapsed duration between two instants.
double	GLONASSScale.getLeap(AbsoluteDate date)	Get the value of the previous leap.
default double	TimeScale.getLeap(AbsoluteDate date)	Get the value of the previous leap.
double	UTCScale.getLeap(AbsoluteDate date)	Get the value of the previous leap.
boolean	GLONASSScale.insideLeap(AbsoluteDate date)	Check if date is within a leap second introduction in this time scale.
default boolean	TimeScale.insideLeap(AbsoluteDate date)	Check if date is within a leap second introduction in this time scale.
boolean	UTCScale.insideLeap(AbsoluteDate date)	Check if date is within a leap second introduction in this time scale.
default T	TimeInterpolable.interpolate(AbsoluteDate date, Collection<T> sample)	Get an interpolated instance.
T	TimeInterpolable.interpolate(AbsoluteDate date, Stream<T> sample)	Get an interpolated instance.
int	GLONASSScale.minuteDuration(AbsoluteDate date)	Check length of the current minute in this time scale.
default int	TimeScale.minuteDuration(AbsoluteDate date)	Check length of the current minute in this time scale.
int	UTCScale.minuteDuration(AbsoluteDate date)	Check length of the current minute in this time scale.
double	AbsoluteDate.offsetFrom(AbsoluteDate instant, TimeScale timeScale)	Compute the apparent clock offset between two instant in the perspective of a specific time scale.
double	BDTScale.offsetFromTAI(AbsoluteDate date)	Get the offset to convert locations from TAIScale to instance.
double	GalileoScale.offsetFromTAI(AbsoluteDate date)	Get the offset to convert locations from TAIScale to instance.
double	GLONASSScale.offsetFromTAI(AbsoluteDate date)	Get the offset to convert locations from TAIScale to instance.
double	GMSTScale.offsetFromTAI(AbsoluteDate date)	Get the offset to convert locations from TAIScale to instance.
double	GPSScale.offsetFromTAI(AbsoluteDate date)	Get the offset to convert locations from TAIScale to instance.
double	IRNSSScale.offsetFromTAI(AbsoluteDate date)	Get the offset to convert locations from TAIScale to instance.
double	QZSSScale.offsetFromTAI(AbsoluteDate date)	Get the offset to convert locations from TAIScale to instance.
double	TAIScale.offsetFromTAI(AbsoluteDate taiTime)	Get the offset to convert locations from TAIScale to instance.
double	TCBScale.offsetFromTAI(AbsoluteDate date)	Get the offset to convert locations from TAIScale to instance.
double	TCGScale.offsetFromTAI(AbsoluteDate date)	Get the offset to convert locations from TAIScale to instance.
double	TDBScale.offsetFromTAI(AbsoluteDate date)	Get the offset to convert locations from TAIScale to instance.
double	TimeScale.offsetFromTAI(AbsoluteDate date)	Get the offset to convert locations from TAIScale to instance.
double	TTScale.offsetFromTAI(AbsoluteDate date)	Get the offset to convert locations from TAIScale to instance.
double	UT1Scale.offsetFromTAI(AbsoluteDate date)	Get the offset to convert locations from TAIScale to instance.
double	UTCScale.offsetFromTAI(AbsoluteDate date)	Get the offset to convert locations from TAIScale to instance.
static AbsoluteDate	AbsoluteDate.parseCCSDSUnsegmentedTimeCode(byte preambleField1, byte preambleField2, byte[] timeField, AbsoluteDate agencyDefinedEpoch)	Build an instance from a CCSDS Unsegmented Time Code (CUC).
List<AbsoluteDate>	BurstSelector.selectDates(AbsoluteDate start, AbsoluteDate end)	Select dates within an interval.
List<AbsoluteDate>	DatesSelector.selectDates(AbsoluteDate start, AbsoluteDate end)	Select dates within an interval.
List<AbsoluteDate>	FixedStepSelector.selectDates(AbsoluteDate start, AbsoluteDate end)	Select dates within an interval.
double	TimeScalarFunction.value(AbsoluteDate date)	Compute a function of time.
double[]	TimeVectorFunction.value(AbsoluteDate date)	Compute a function of time.

Constructors in org.orekit.time with parameters of type AbsoluteDate

Constructor	Description
AbsoluteDate(AbsoluteDate since, double elapsedDuration)	Build an instance from an elapsed duration since to another instant.
AbsoluteDate(AbsoluteDate reference, double apparentOffset, TimeScale timeScale)	Build an instance from an apparent clock offset with respect to another instant in the perspective of a specific time scale.
FieldAbsoluteDate(org.hipparchus.Field<T> field, AbsoluteDate date)	Build an instance from an AbsoluteDate.
FieldAbsoluteDate(AbsoluteDate since, T elapsedDuration)	Build an instance from an elapsed duration since to another instant.
GPSDate(AbsoluteDate date)	Build an instance from an absolute date.

Uses of AbsoluteDate in org.orekit.utils

Methods in org.orekit.utils that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	FieldTimeSpanMap.Transition.getDate()	Get the transition absolute date.
AbsoluteDate	TimeSpanMap.Transition.getDate()	Get the transition date.
AbsoluteDate	TimeStampedAngularCoordinates.getDate()	Get the date.
AbsoluteDate	TimeStampedPVCoordinates.getDate()	Get the date.
AbsoluteDate	TimeSpanMap.Span.getEnd()	Get the end of this time span.
AbsoluteDate	IERSConventions.getNutationReferenceEpoch()	Get the reference epoch for fundamental nutation arguments.
AbsoluteDate	ParameterDriver.getReferenceDate()	Get current reference date.
AbsoluteDate	SecularAndHarmonic.getReferenceDate()	Get the reference date.
AbsoluteDate	TimeSpanMap.Span.getStart()	Get the start of this time span.

Methods in org.orekit.utils with parameters of type AbsoluteDate

Modifier and Type	Method	Description
void	SecularAndHarmonic.addPoint(AbsoluteDate date, double osculatingValue)	Add a fitting point.
void	TimeSpanMap.addValidAfter(T entry, AbsoluteDate earliestValidityDate)	Add an entry valid after a limit date.
void	TimeSpanMap.addValidBefore(T entry, AbsoluteDate latestValidityDate)	Add an entry valid before a limit date.
double[]	SecularAndHarmonic.approximateAsPolynomialOnly(int combinedDegree, AbsoluteDate combinedReference, int meanDegree, int meanHarmonics, AbsoluteDate start, AbsoluteDate end, double step)	Approximate an already fitted model to polynomial only terms.
double	IERSConventions.evaluateTC(AbsoluteDate date)	Evaluate the date offset between the current date and the reference date.
TimeSpanMap<T>	TimeSpanMap.extractRange(AbsoluteDate start, AbsoluteDate end)	Extract a range of the map.
List<T>	TimeStampedGenerator.generate(AbsoluteDate existingDate, AbsoluteDate date)	Generate a chronologically sorted list of entries to be cached.
T	TimeSpanMap.get(AbsoluteDate date)	Get the entry valid at a specified date.
Stream<T>	GenericTimeStampedCache.getNeighbors(AbsoluteDate central)	Get the entries surrounding a central date.
Stream<T>	ImmutableTimeStampedCache.getNeighbors(AbsoluteDate central)	Get the entries surrounding a central date.
Stream<T>	TimeStampedCache.getNeighbors(AbsoluteDate central)	Get the entries surrounding a central date.
TimeStampedPVCoordinates	PVCoordinatesProvider.getPVCoordinates(AbsoluteDate date, Frame frame)	Get the PVCoordinates of the body in the selected frame.
TimeSpanMap.Span<T>	TimeSpanMap.getSpan(AbsoluteDate date)	Get the time span containing a specified date.
static TimeStampedAngularCoordinates	TimeStampedAngularCoordinates.interpolate(AbsoluteDate date, AngularDerivativesFilter filter, Collection<TimeStampedAngularCoordinates> sample)	Interpolate angular coordinates.
static <T extends org.hipparchus.RealFieldElement<T>> TimeStampedFieldAngularCoordinates<T>	TimeStampedFieldAngularCoordinates.interpolate(AbsoluteDate date, AngularDerivativesFilter filter, Collection<TimeStampedFieldAngularCoordinates<T>> sample)	Interpolate angular coordinates.
static TimeStampedPVCoordinates	TimeStampedPVCoordinates.interpolate(AbsoluteDate date, CartesianDerivativesFilter filter, Collection<TimeStampedPVCoordinates> sample)	Interpolate position-velocity.
static TimeStampedPVCoordinates	TimeStampedPVCoordinates.interpolate(AbsoluteDate date, CartesianDerivativesFilter filter, Stream<TimeStampedPVCoordinates> sample)	Interpolate position-velocity.
double	SecularAndHarmonic.meanDerivative(AbsoluteDate date, int degree, int harmonics)	Get mean derivative, truncated to first components.
double	SecularAndHarmonic.meanSecondDerivative(AbsoluteDate date, int degree, int harmonics)	Get mean second derivative, truncated to first components.
double	SecularAndHarmonic.meanValue(AbsoluteDate date, int degree, int harmonics)	Get mean value, truncated to first components.
double	SecularAndHarmonic.osculatingDerivative(AbsoluteDate date)	Get fitted osculating derivative.
double	SecularAndHarmonic.osculatingSecondDerivative(AbsoluteDate date)	Get fitted osculating second derivative.
double	SecularAndHarmonic.osculatingValue(AbsoluteDate date)	Get fitted osculating value.
default void	ParameterObserver.referenceDateChanged(AbsoluteDate previousReferenceDate, ParameterDriver driver)	Notify that a parameter reference date has been changed.
void	SecularAndHarmonic.resetFitting(AbsoluteDate date, double... initialGuess)	Reset fitting.
void	ParameterDriver.setReferenceDate(AbsoluteDate newReferenceDate)	Set reference date.
double[]	IERSConventions.NutationCorrectionConverter.toEquinox(AbsoluteDate date, double dX, double dY)	Convert nutation corrections.
double[]	IERSConventions.NutationCorrectionConverter.toNonRotating(AbsoluteDate date, double ddPsi, double ddEpsilon)	Convert nutation corrections.

Constructors in org.orekit.utils with parameters of type AbsoluteDate

Constructor	Description
TimeStampedAngularCoordinates(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.FieldRotation<org.hipparchus.analysis.differentiation.DerivativeStructure> r)	Builds a TimeStampedAngularCoordinates from a FieldRotation<DerivativeStructure>.
TimeStampedAngularCoordinates(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Rotation rotation, org.hipparchus.geometry.euclidean.threed.Vector3D rotationRate, org.hipparchus.geometry.euclidean.threed.Vector3D rotationAcceleration)	Builds a rotation/rotation rate pair.
TimeStampedAngularCoordinates(AbsoluteDate date, PVCoordinates u, PVCoordinates v)	Build one of the rotations that transform one pv coordinates into another one.
TimeStampedAngularCoordinates(AbsoluteDate date, PVCoordinates u1, PVCoordinates u2, PVCoordinates v1, PVCoordinates v2, double tolerance)	Build the rotation that transforms a pair of pv coordinates into another pair.
TimeStampedFieldAngularCoordinates(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.FieldRotation<T> rotation, org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> rotationRate, org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> rotationAcceleration)	Builds a rotation/rotation rate pair.
TimeStampedFieldAngularCoordinates(AbsoluteDate date, FieldPVCoordinates<T> u1, FieldPVCoordinates<T> u2, FieldPVCoordinates<T> v1, FieldPVCoordinates<T> v2, double tolerance)	Build the rotation that transforms a pair of pv coordinates into another pair.
TimeStampedFieldPVCoordinates(AbsoluteDate date, double a, FieldPVCoordinates<T> pv)	Multiplicative constructor
TimeStampedFieldPVCoordinates(AbsoluteDate date, double a1, FieldPVCoordinates<T> pv1, double a2, FieldPVCoordinates<T> pv2)	Linear constructor
TimeStampedFieldPVCoordinates(AbsoluteDate date, double a1, FieldPVCoordinates<T> pv1, double a2, FieldPVCoordinates<T> pv2, double a3, FieldPVCoordinates<T> pv3)	Linear constructor
TimeStampedFieldPVCoordinates(AbsoluteDate date, double a1, FieldPVCoordinates<T> pv1, double a2, FieldPVCoordinates<T> pv2, double a3, FieldPVCoordinates<T> pv3, double a4, FieldPVCoordinates<T> pv4)	Linear constructor
TimeStampedFieldPVCoordinates(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position, org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> velocity, org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> acceleration)	Builds a PVCoordinates pair.
TimeStampedFieldPVCoordinates(AbsoluteDate date, FieldPVCoordinates<T> pv)	Basic constructor.
TimeStampedFieldPVCoordinates(AbsoluteDate date, FieldPVCoordinates<T> start, FieldPVCoordinates<T> end)	Subtractive constructor
TimeStampedFieldPVCoordinates(AbsoluteDate date, T a, FieldPVCoordinates<T> pv)	Multiplicative constructor
TimeStampedFieldPVCoordinates(AbsoluteDate date, T a1, FieldPVCoordinates<T> pv1, T a2, FieldPVCoordinates<T> pv2)	Linear constructor
TimeStampedFieldPVCoordinates(AbsoluteDate date, T a1, FieldPVCoordinates<T> pv1, T a2, FieldPVCoordinates<T> pv2, T a3, FieldPVCoordinates<T> pv3)	Linear constructor
TimeStampedFieldPVCoordinates(AbsoluteDate date, T a1, FieldPVCoordinates<T> pv1, T a2, FieldPVCoordinates<T> pv2, T a3, FieldPVCoordinates<T> pv3, T a4, FieldPVCoordinates<T> pv4)	Linear constructor
TimeStampedFieldPVCoordinates(AbsoluteDate date, T a, PVCoordinates pv)	Multiplicative constructor
TimeStampedFieldPVCoordinates(AbsoluteDate date, T a1, PVCoordinates pv1, T a2, PVCoordinates pv2)	Linear constructor
TimeStampedFieldPVCoordinates(AbsoluteDate date, T a1, PVCoordinates pv1, T a2, PVCoordinates pv2, T a3, PVCoordinates pv3)	Linear constructor
TimeStampedFieldPVCoordinates(AbsoluteDate date, T a1, PVCoordinates pv1, T a2, PVCoordinates pv2, T a3, PVCoordinates pv3, T a4, PVCoordinates pv4)	Linear constructor
TimeStampedPVCoordinates(AbsoluteDate date, double a, PVCoordinates pv)	Multiplicative constructor
TimeStampedPVCoordinates(AbsoluteDate date, double a1, PVCoordinates pv1, double a2, PVCoordinates pv2)	Linear constructor
TimeStampedPVCoordinates(AbsoluteDate date, double a1, PVCoordinates pv1, double a2, PVCoordinates pv2, double a3, PVCoordinates pv3)	Linear constructor
TimeStampedPVCoordinates(AbsoluteDate date, double a1, PVCoordinates pv1, double a2, PVCoordinates pv2, double a3, PVCoordinates pv3, double a4, PVCoordinates pv4)	Linear constructor
TimeStampedPVCoordinates(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure> p)	Builds a TimeStampedPVCoordinates triplet from a FieldVector3D<DerivativeStructure>.
TimeStampedPVCoordinates(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Vector3D velocity)	Build from position and velocity.
TimeStampedPVCoordinates(AbsoluteDate date, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Vector3D velocity, org.hipparchus.geometry.euclidean.threed.Vector3D acceleration)	Builds a TimeStampedPVCoordinates pair.
TimeStampedPVCoordinates(AbsoluteDate date, PVCoordinates pv)	Build from position velocity acceleration coordinates.
TimeStampedPVCoordinates(AbsoluteDate date, PVCoordinates start, PVCoordinates end)	Subtractive constructor