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.control.indirect.adjoint	This package provides routines to model the adjoint dynamics as in the Pontryagin Maximum Principle, as used in indirect control.
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	This package provides initial orbit determination methods.
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.measurements.gnss	This package provides methods to handle GNSS measurements.
org.orekit.estimation.measurements.modifiers	This package provides measurement modifier.
org.orekit.estimation.sequential	The sequential package provides an implementation of a Kalman Filter engine to perform an orbit determination.
org.orekit.files.ccsds.definitions	This package contains definitions for CCSDS objects (frames, time systems...).
org.orekit.files.ccsds.ndm	This package contains the base hierarchy for CCSDS ADM, ODM and TDM.
org.orekit.files.ccsds.ndm.adm	This package contains class managing CCSDS Attitude Data Message.
org.orekit.files.ccsds.ndm.adm.acm	This package contains class managing CCSDS Attitude Comprehensive Message.
org.orekit.files.ccsds.ndm.adm.aem	This package contains class managing CCSDS Attitude Ephemeris Message.
org.orekit.files.ccsds.ndm.adm.apm	This package contains class managing CCSDS Attitude Parameter Message.
org.orekit.files.ccsds.ndm.cdm	This package contains class managing CCSDS Conjunction Data Message.
org.orekit.files.ccsds.ndm.odm	This package contains class managing CCSDS Orbit Data Message.
org.orekit.files.ccsds.ndm.odm.ocm	This package contains class managing CCSDS Orbit Comprehensive Message.
org.orekit.files.ccsds.ndm.odm.oem	This package contains class managing CCSDS Orbit Ephemeris Message.
org.orekit.files.ccsds.ndm.odm.omm	This package contains class managing CCSDS Orbit Mean-Elements Message.
org.orekit.files.ccsds.ndm.odm.opm	This package contains class managing CCSDS Orbit Parameter Message.
org.orekit.files.ccsds.ndm.tdm	This package contains class managing CCSDS Tracking Data Message.
org.orekit.files.ccsds.section	This package contains class managing the sections in CCSDS Messages.
org.orekit.files.ccsds.utils	This package contains utilities shared by many CCSDS messages parsers/writers.
org.orekit.files.ccsds.utils.generation	This package contains utilities for CCSDS messages generation.
org.orekit.files.ccsds.utils.lexical	This package contains utilities for CCSDS messages lexical analysis.
org.orekit.files.general	This package provides interfaces for orbit file representations and corresponding parsers.
org.orekit.files.ilrs	This package provides parsers for laser ranging data stored in CDR and CPF formats.
org.orekit.files.rinex.clock	This package provides classes related to navigation clock files.
org.orekit.files.rinex.navigation	This package provides classes related to RINEX navigation files.
org.orekit.files.rinex.observation	This package provides classes related to RINEX observation files.
org.orekit.files.rinex.section	This package contains class managing the sections in RINEX files.
org.orekit.files.sinex	This package provides classes related to station data.
org.orekit.files.sp3	This package provides a parser for orbit data stored in SP3 format.
org.orekit.files.stk	This package provides a parser for STK ephemeris files.
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.empirical	This package provides empirical forces.
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.maneuvers.jacobians	Generators for columns of Jacobian matrices related to maneuver parameters.
org.orekit.forces.maneuvers.propulsion	This package provides propulsion models intended to be used with class Maneuver.
org.orekit.forces.maneuvers.trigger	This package provides maneuver triggers' models intended to be used with class Maneuver.
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.frames.encounter	Package specific to encounter local orbital frame.
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.models.earth.atmosphere	This package provides the atmosphere model interface and several implementations.
org.orekit.models.earth.atmosphere.data	This package provides classes to get atmospheric data, including solar flux and planetary geomagnetic indices.
org.orekit.models.earth.displacement	This package provides models computing reference points displacements on Earth surface.
org.orekit.models.earth.ionosphere	This package provides models that simulate the impact of the ionosphere.
org.orekit.models.earth.troposphere	This package provides models that simulate the impact of the troposphere.
org.orekit.models.earth.weather	This package provides models that simulate global weather conditions on Earth.
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.gnss.data	This package provides classes related to navigation data containing in GNSS almanacs and navigation messages.
org.orekit.propagation.analytical.intelsat	This package provides classes to propagate Intelsat's 11 elements.
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.conversion.averaging	This package wraps methods from various (semi)analytical models in Orekit to convert back and forth between an averaged orbital state and an osculating one.
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.numerical.cr3bp	Top level package for CR3BP Models used with a numerical propagator.
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.ssa.collision.shorttermencounter.probability.twod	Package specific to calculus assuming a 2D short-term encounter model.
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.
AbsoluteDate	AggregateBoundedAttitudeProvider.getMaxDate()	Get the last date of the range.
AbsoluteDate	BoundedAttitudeProvider.getMaxDate()	Get the last date of the range.
AbsoluteDate	TabulatedLofOffset.getMaxDate()	Get the last date of the range.
AbsoluteDate	TabulatedProvider.getMaxDate()	Get the last date of the range.
AbsoluteDate	AggregateBoundedAttitudeProvider.getMinDate()
AbsoluteDate	BoundedAttitudeProvider.getMinDate()	Get the first date of the range.
AbsoluteDate	TabulatedLofOffset.getMinDate()	Get the first date of the range.
AbsoluteDate	TabulatedProvider.getMinDate()	Get the first date of the range.

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

Modifier and Type	Method	Description
Attitude	AggregateBoundedAttitudeProvider.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.
Attitude	AlignedAndConstrained.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.
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	FrameAlignedProvider.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	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	TorqueFree.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.
Rotation	AggregateBoundedAttitudeProvider.getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
Rotation	AlignedAndConstrained.getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
default Rotation	AttitudeProvider.getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
Rotation	AttitudesSequence.getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
Rotation	CelestialBodyPointed.getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
Rotation	FixedRate.getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
Rotation	FrameAlignedProvider.getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
Rotation	GroundPointing.getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
Rotation	LofOffset.getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
Rotation	LofOffsetPointing.getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
Rotation	SpinStabilized.getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
Attitude	GroundPointingAttitudeModifier.getBaseState(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the base system state at given date, without modifications.
protected Vector3D	BodyCenterPointing.getTargetPosition(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position in specified frame.
protected Vector3D	GroundPointing.getTargetPosition(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position in specified frame.
protected Vector3D	GroundPointingAttitudeModifier.getTargetPosition(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position in specified frame.
protected Vector3D	LofOffsetPointing.getTargetPosition(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position in specified frame.
protected Vector3D	NadirPointing.getTargetPosition(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position in specified frame.
protected Vector3D	TargetPointing.getTargetPosition(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position in specified frame.
TimeStampedPVCoordinates	BodyCenterPointing.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position/velocity in specified frame.
protected abstract TimeStampedPVCoordinates	GroundPointing.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position/velocity in specified frame.
TimeStampedPVCoordinates	GroundPointingAttitudeModifier.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	NadirPointing.getTargetPVViaInterpolation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute target position-velocity-acceleration vector via interpolation.
double	YawCompensation.getYawAngle(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the yaw compensation angle at date.
void	AttitudesSequence.Switch.init(SpacecraftState s0, AbsoluteDate t)	Initialize event handler at the start of a propagation.

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

Constructor	Description
Attitude(AbsoluteDate date, Frame referenceFrame, Rotation attitude, Vector3D spin, Vector3D acceleration)	Creates a new instance.
Attitude(AbsoluteDate date, Frame referenceFrame, AngularCoordinates orientation)	Creates a new instance.
SpinStabilized(AttitudeProvider nonRotatingLaw, AbsoluteDate start, Vector3D axis, double rate)	Creates a new instance.
TabulatedLofOffset(Frame inertialFrame, LOF lof, List<? extends TimeStampedAngularCoordinates> table, int n, AngularDerivativesFilter filter, AbsoluteDate minDate, AbsoluteDate maxDate)	Creates new instance.
TabulatedProvider(List<? extends TimeStampedAngularCoordinates> table, int n, AngularDerivativesFilter filter, AbsoluteDate minDate, AbsoluteDate maxDate, AttitudeBuilder builder)	Creates new instance.

Uses of AbsoluteDate in org.orekit.bodies

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

Modifier and Type	Method	Description
Vector3D	OneAxisEllipsoid.getCartesianIntersectionPoint(Line line, Vector3D close, Frame frame, AbsoluteDate date)	Get the intersection point of a line with the surface of the body.
GeodeticPoint	BodyShape.getIntersectionPoint(Line line, Vector3D close, Frame frame, AbsoluteDate date)	Get the intersection point of a line with the surface of the body.
GeodeticPoint	OneAxisEllipsoid.getIntersectionPoint(Line line, Vector3D close, Frame frame, AbsoluteDate date)	Get the intersection point of a line with the surface of the body.
default Vector3D	IAUPole.getNode(AbsoluteDate date)	Get the body Q Node direction in ICRF frame.
Vector3D	IAUPole.getPole(AbsoluteDate date)	Get the body North pole direction in ICRF frame.
Vector3D	AnalyticalSolarPositionProvider.getPosition(AbsoluteDate date, Frame frame)	Get the position of the body in the selected frame.
double	IAUPole.getPrimeMeridianAngle(AbsoluteDate date)	Get the prime meridian angle.
default Vector3D	JPLEphemeridesLoader.RawPVProvider.getRawPosition(AbsoluteDate date)	Get the position at date.
PVCoordinates	JPLEphemeridesLoader.RawPVProvider.getRawPV(AbsoluteDate date)	Get the position-velocity at date.
AbsolutePVCoordinates	CR3BPSystem.getRealAPV(AbsolutePVCoordinates apv0, AbsoluteDate initialDate, Frame outputFrame)	Get the AbsolutePVCoordinates from normalized units to standard units in an output frame.
static CR3BPSystem	CR3BPFactory.getSunEarthCR3BP(AbsoluteDate date, TimeScale timeScale)	Get the Sun-Earth CR3BP singleton bodies pair.
static CR3BPSystem	CR3BPFactory.getSunJupiterCR3BP(AbsoluteDate date, TimeScale timeScale)	Get the Sun-Jupiter CR3BP singleton bodies pair.
Vector3D	BodyShape.projectToGround(Vector3D point, AbsoluteDate date, Frame frame)	Project a point to the ground.
Vector3D	OneAxisEllipsoid.projectToGround(Vector3D point, AbsoluteDate date, Frame frame)	Project a point to the ground.
GeodeticPoint	BodyShape.transform(Vector3D point, Frame frame, AbsoluteDate date)	Transform a Cartesian point to a surface-relative point.
GeodeticPoint	OneAxisEllipsoid.transform(Vector3D point, Frame frame, AbsoluteDate date)	Transform a Cartesian point to a surface-relative point.
FieldGeodeticPoint<UnivariateDerivative2>	OneAxisEllipsoid.transform(PVCoordinates point, Frame frame, AbsoluteDate date)	Transform a Cartesian point to a surface-relative point.

Uses of AbsoluteDate in org.orekit.control.indirect.adjoint

Methods in org.orekit.control.indirect.adjoint with parameters of type AbsoluteDate

Modifier and Type	Method	Description
protected double[]	AbstractCartesianAdjointNonCentralBodyTerm.formRelativePosition(AbsoluteDate date, double[] stateVariables, Frame frame)	Form relative position vector w.r.t.
protected abstract Vector3D	AbstractCartesianAdjointEquationTerm.getAcceleration(AbsoluteDate date, double[] stateVariables, Frame frame)	Compute the acceleration vector.
protected Vector3D	CartesianAdjointInertialTerm.getAcceleration(AbsoluteDate date, double[] stateVariables, Frame frame)	Compute the acceleration vector.
Vector3D	CartesianAdjointJ2Term.getAcceleration(AbsoluteDate date, double[] stateVariables, Frame frame)	Compute the acceleration vector.
protected Vector3D	CartesianAdjointKeplerianTerm.getAcceleration(AbsoluteDate date, double[] stateVariables, Frame frame)	Compute the acceleration vector.
Vector3D	CartesianAdjointSingleBodyTerm.getAcceleration(AbsoluteDate date, double[] stateVariables, Frame frame)	Compute the acceleration vector.
Vector3D	CartesianAdjointThirdBodyTerm.getAcceleration(AbsoluteDate date, double[] stateVariables, Frame frame)	Compute the acceleration vector.
protected Vector3D	AbstractCartesianAdjointNonCentralBodyTerm.getBodyPosition(AbsoluteDate date, Frame frame)	Get body's position.
double	AbstractCartesianAdjointEquationTerm.getHamiltonianContribution(AbsoluteDate date, double[] stateVariables, double[] adjointVariables, Frame frame)	Computes the contribution to the Hamiltonian.
double	CartesianAdjointEquationTerm.getHamiltonianContribution(AbsoluteDate date, double[] stateVariables, double[] adjointVariables, Frame frame)	Computes the contribution to the Hamiltonian.
protected abstract double[]	AbstractCartesianAdjointGravitationalTerm.getPositionAdjointContribution(AbsoluteDate date, double[] stateVariables, double[] adjointVariables, Frame frame)	Computes the contribution to position adjoint derivatives.
double[]	AbstractCartesianAdjointNonCentralBodyTerm.getPositionAdjointContribution(AbsoluteDate date, double[] stateVariables, double[] adjointVariables, Frame frame)	Computes the contribution to position adjoint derivatives.
double[]	CartesianAdjointJ2Term.getPositionAdjointContribution(AbsoluteDate date, double[] stateVariables, double[] adjointVariables, Frame frame)	Computes the contribution to position adjoint derivatives.
double[]	CartesianAdjointKeplerianTerm.getPositionAdjointContribution(AbsoluteDate date, double[] stateVariables, double[] adjointVariables, Frame frame)	Computes the contribution to position adjoint derivatives.
double[]	AbstractCartesianAdjointEquationTerm.getRatesContribution(AbsoluteDate date, double[] stateVariables, double[] adjointVariables, Frame frame)	Computes the contribution to the rates of the adjoint variables.
double[]	AbstractCartesianAdjointGravitationalTerm.getRatesContribution(AbsoluteDate date, double[] stateVariables, double[] adjointVariables, Frame frame)	Computes the contribution to the rates of the adjoint variables.
double[]	CartesianAdjointEquationTerm.getRatesContribution(AbsoluteDate date, double[] stateVariables, double[] adjointVariables, Frame frame)	Computes the contribution to the rates of the adjoint variables.
double[]	CartesianAdjointInertialTerm.getRatesContribution(AbsoluteDate date, double[] stateVariables, double[] adjointVariables, Frame frame)	Computes the contribution to the rates of the adjoint variables.
void	CartesianAdjointDerivativesProvider.init(SpacecraftState initialState, AbsoluteDate target)	Initialize the generator at the start of propagation.

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
Orbit	IodGauss.estimate(Frame outputFrame, Vector3D obsP1, AbsoluteDate obsDate1, Vector3D los1, Vector3D obsP2, AbsoluteDate obsDate2, Vector3D los2, Vector3D obsP3, AbsoluteDate obsDate3, Vector3D los3)	Estimate and orbit based on Gauss Intial Orbit Determination method.
Orbit	IodGibbs.estimate(Frame frame, Vector3D r1, AbsoluteDate date1, Vector3D r2, AbsoluteDate date2, Vector3D r3, AbsoluteDate date3)	Give an initial orbit estimation, assuming Keplerian motion.
Orbit	IodGooding.estimate(Frame outputFrame, Vector3D O1, Vector3D O2, Vector3D O3, Vector3D lineOfSight1, AbsoluteDate dateObs1, Vector3D lineOfSight2, AbsoluteDate dateObs2, Vector3D lineOfSight3, AbsoluteDate dateObs3, double rho1init, double rho3init)	Estimate orbit from three line of sight.
Orbit	IodGooding.estimate(Frame outputFrame, Vector3D O1, Vector3D O2, Vector3D O3, Vector3D lineOfSight1, AbsoluteDate dateObs1, Vector3D lineOfSight2, AbsoluteDate dateObs2, Vector3D lineOfSight3, AbsoluteDate dateObs3, double rho1init, double rho3init, int nRev, boolean direction)	Estimate orbit from three line of sight.
Orbit	IodLambert.estimate(Frame frame, boolean posigrade, int nRev, Vector3D p1, AbsoluteDate t1, Vector3D p2, AbsoluteDate t2)	Estimate a Keplerian orbit given two position vectors and a duration.
Orbit	IodLaplace.estimate(Frame outputFrame, PVCoordinates obsPva, AbsoluteDate obsDate1, Vector3D los1, AbsoluteDate obsDate2, Vector3D los2, AbsoluteDate obsDate3, Vector3D los3)	Estimate orbit from three line of sight angles at the same location.

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	EstimatedMeasurementBase.getDate()	Get the date.
AbsoluteDate	QuadraticClockModel.getValidityEnd()	Get validity end.
AbsoluteDate	QuadraticClockModel.getValidityStart()	Get validity start.

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

Modifier and Type	Method	Description
static double	TDOA.forwardSignalTimeOfFlight(TimeStampedPVCoordinates adjustableEmitterPV, Vector3D receiverPosition, AbsoluteDate signalArrivalDate)	Compute propagation delay on a link leg (typically downlink or uplink).
ClockOffset	QuadraticClockModel.getOffset(AbsoluteDate date)	Get the clock offset at date.
GeodeticPoint	GroundStation.getOffsetGeodeticPoint(AbsoluteDate date)	Get the geodetic point at the center of the offset frame.
Transform	GroundStation.getOffsetToInertial(Frame inertial, AbsoluteDate date, boolean clockOffsetAlreadyApplied)	Get the transform between offset frame and inertial frame.
FieldTransform<Gradient>	GroundStation.getOffsetToInertial(Frame inertial, AbsoluteDate clockDate, int freeParameters, Map<String,Integer> indices)	Get the transform between offset frame and inertial frame with derivatives.
double[]	EstimatedMeasurement.getParameterDerivatives(ParameterDriver driver, AbsoluteDate date)	Get the partial derivatives of the simulated measurement with respect to a parameter.
PressureTemperatureHumidity	GroundStation.getPressureTemperatureHumidity(AbsoluteDate date)	Get the weather parameters.
StaticTransform	EstimatedEarthFrameProvider.getStaticTransform(AbsoluteDate date)	Get a transform for only rotations and translations on the specified date.
Transform	EstimatedEarthFrameProvider.getTransform(AbsoluteDate date)	Get the Transform corresponding to specified date.
void	EstimatedMeasurement.setParameterDerivatives(ParameterDriver driver, AbsoluteDate date, double... parameterDerivatives)	Set the partial derivatives of the simulated measurement with respect to parameter.
static double	AbstractMeasurement.signalTimeOfFlightAdjustableEmitter(PVCoordinatesProvider adjustableEmitter, AbsoluteDate approxEmissionDate, Vector3D receiverPosition, AbsoluteDate signalArrivalDate, Frame frame)	Compute propagation delay on a link leg (typically downlink or uplink).
static double	AbstractMeasurement.signalTimeOfFlightAdjustableEmitter(TimeStampedPVCoordinates adjustableEmitterPV, Vector3D receiverPosition, AbsoluteDate signalArrivalDate, Frame frame)	Compute propagation delay on a link leg (typically downlink or uplink).
static double	AbstractMeasurement.signalTimeOfFlightAdjustableReceiver(Vector3D emitterPosition, AbsoluteDate emissionDate, PVCoordinatesProvider adjustableReceiver, AbsoluteDate approxReceptionDate, Frame frame)	Compute propagation delay on a link leg (typically downlink or uplink).
static double	AbstractMeasurement.signalTimeOfFlightAdjustableReceiver(Vector3D emitterPosition, AbsoluteDate emissionDate, TimeStampedPVCoordinates adjustableReceiverPV, AbsoluteDate approxReceptionDate, Frame frame)	Compute propagation delay on a link leg (typically downlink or uplink).
QuadraticFieldClockModel<Gradient>	QuadraticClockModel.toGradientModel(int freeParameters, Map<String,Integer> indices, AbsoluteDate date)	Convert to gradient model.

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

Constructor	Description
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<ObservableSatellite> satellites)	Simple constructor for mono-dimensional measurements.
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, ObservableSatellite satellite)	Simple constructor.
BistaticRange(GroundStation emitter, GroundStation receiver, AbsoluteDate date, double range, double sigma, double baseWeight, ObservableSatellite satellite)	Simple constructor.
BistaticRangeRate(GroundStation emitter, GroundStation receiver, AbsoluteDate date, double rangeRate, double sigma, double baseWeight, ObservableSatellite satellite)	Simple constructor.
FDOA(GroundStation primeStation, GroundStation secondStation, double centreFrequency, AbsoluteDate date, double fdoa, double sigma, double baseWeight, ObservableSatellite satellite)	Simple constructor.
GroundReceiverMeasurement(GroundStation station, boolean twoWay, AbsoluteDate date, double[] observed, double[] sigma, double[] baseWeight, ObservableSatellite satellite)	Simple constructor.
GroundReceiverMeasurement(GroundStation station, boolean twoWay, AbsoluteDate date, double observed, double sigma, double baseWeight, ObservableSatellite satellite)	Simple constructor.
InterSatellitesRange(ObservableSatellite local, ObservableSatellite remote, boolean twoWay, AbsoluteDate date, double range, double sigma, double baseWeight)	Simple constructor.
Position(AbsoluteDate date, Vector3D position, double[][] covarianceMatrix, double baseWeight, ObservableSatellite satellite)	Constructor with full covariance matrix and all inputs.
Position(AbsoluteDate date, Vector3D position, double[] sigmaPosition, double baseWeight, ObservableSatellite satellite)	Constructor with one vector for the standard deviation.
Position(AbsoluteDate date, Vector3D position, double sigmaPosition, double baseWeight, ObservableSatellite satellite)	Constructor with one double for the standard deviation.
PV(AbsoluteDate date, Vector3D position, Vector3D velocity, double[][] positionCovarianceMatrix, double[][] velocityCovarianceMatrix, double baseWeight, ObservableSatellite satellite)	Constructor with 2 smaller covariance matrices.
PV(AbsoluteDate date, Vector3D position, Vector3D velocity, double[][] covarianceMatrix, double baseWeight, ObservableSatellite satellite)	Constructor with full covariance matrix and all inputs.
PV(AbsoluteDate date, Vector3D position, Vector3D velocity, double[] sigmaPosition, double[] sigmaVelocity, double baseWeight, ObservableSatellite satellite)	Constructor with two vectors for the standard deviations.
PV(AbsoluteDate date, Vector3D position, Vector3D velocity, double[] sigmaPV, double baseWeight, ObservableSatellite satellite)	Constructor with one vector for the standard deviations.
PV(AbsoluteDate date, Vector3D position, Vector3D velocity, double sigmaPosition, double sigmaVelocity, double baseWeight, ObservableSatellite satellite)	Constructor with two double for the standard deviations.
QuadraticClockModel(AbsoluteDate referenceDate, double a0, double a1, double a2)	Simple constructor.
Range(GroundStation station, boolean twoWay, AbsoluteDate date, double range, double sigma, double baseWeight, ObservableSatellite satellite)	Simple constructor.
RangeRate(GroundStation station, AbsoluteDate date, double rangeRate, double sigma, double baseWeight, boolean twoway, ObservableSatellite satellite)	Simple constructor.
TDOA(GroundStation primeStation, GroundStation secondStation, AbsoluteDate date, double tdoa, double sigma, double baseWeight, ObservableSatellite satellite)	Simple constructor.
TurnAroundRange(GroundStation primaryStation, GroundStation secondaryStation, 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
EstimatedMeasurementBase<T>	AbstractMeasurementBuilder.build(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)	Generate a single measurement.
EstimatedMeasurementBase<T>	MeasurementBuilder.build(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)	Generate a single measurement.
default EstimatedMeasurementBase<T>	MeasurementBuilder.build(AbsoluteDate date, SpacecraftState[] states)	Generate a single measurement.
EstimatedMeasurementBase<MultiplexedMeasurement>	MultiplexedMeasurementBuilder.build(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)	Generate a single measurement.
protected abstract T	AbstractMeasurementBuilder.buildObserved(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)	Build a dummy observed measurement.
protected AngularAzEl	AngularAzElBuilder.buildObserved(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)	Build a dummy observed measurement.
protected AngularRaDec	AngularRaDecBuilder.buildObserved(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)	Build a dummy observed measurement.
protected BistaticRange	BistaticRangeBuilder.buildObserved(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)	Build a dummy observed measurement.
protected BistaticRangeRate	BistaticRangeRateBuilder.buildObserved(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)	Build a dummy observed measurement.
protected FDOA	FDOABuilder.buildObserved(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)	Build a dummy observed measurement.
protected InterSatellitesOneWayRangeRate	InterSatellitesOneWayRangeRateBuilder.buildObserved(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)	Build a dummy observed measurement.
protected InterSatellitesPhase	InterSatellitesPhaseBuilder.buildObserved(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)	Build a dummy observed measurement.
protected InterSatellitesRange	InterSatellitesRangeBuilder.buildObserved(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)	Build a dummy observed measurement.
protected OneWayGNSSPhase	OneWayGNSSPhaseBuilder.buildObserved(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)	Build a dummy observed measurement.
protected OneWayGNSSRange	OneWayGNSSRangeBuilder.buildObserved(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)	Build a dummy observed measurement.
protected OneWayGNSSRangeRate	OneWayGNSSRangeRateBuilder.buildObserved(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)	Build a dummy observed measurement.
protected Position	PositionBuilder.buildObserved(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)	Build a dummy observed measurement.
protected PV	PVBuilder.buildObserved(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)	Build a dummy observed measurement.
protected Range	RangeBuilder.buildObserved(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)	Build a dummy observed measurement.
protected RangeRate	RangeRateBuilder.buildObserved(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)	Build a dummy observed measurement.
protected TDOA	TDOABuilder.buildObserved(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)	Build a dummy observed measurement.
protected TurnAroundRange	TurnAroundRangeBuilder.buildObserved(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)	Build a dummy observed measurement.
void	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	GatheringSubscriber.init(AbsoluteDate start, AbsoluteDate end)	Initialize subscriber at the start of a measurements generation.
void	GeneratedMeasurementSubscriber.init(AbsoluteDate start, AbsoluteDate end)	Initialize subscriber at the start of a measurements generation.
void	MeasurementBuilder.init(AbsoluteDate start, AbsoluteDate end)	Initialize builder at the start of a measurements generation.
void	MultiplexedMeasurementBuilder.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.
protected abstract boolean	AbstractScheduler.measurementIsFeasible(AbsoluteDate date)	Check if a measurement is feasible at some date.
boolean	ContinuousScheduler.measurementIsFeasible(AbsoluteDate date)	Check if a measurement is feasible at some date.
boolean	EventBasedScheduler.measurementIsFeasible(AbsoluteDate date)	Check if a measurement is feasible at some date.

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

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

Modifier and Type	Method	Description
AbsoluteDate	CycleSlipDetectorResults.getBeginDate(GnssSignal signal)	Return the date of validity beginning of the detector.
AbsoluteDate	CombinedObservationDataSet.getDate()	Get the date.
AbsoluteDate	CycleSlipDetectorResults.getEndDate(GnssSignal signal)	Return the end date at the given frequency.

Methods in org.orekit.estimation.measurements.gnss that return types with arguments of type AbsoluteDate

Modifier and Type	Method	Description
Map<GnssSignal,List<AbsoluteDate>>	CycleSlipDetectorResults.getCycleSlipMap()	Get the cycle slip Map with contains the results.

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

Modifier and Type	Method	Description
protected Phase	PhaseBuilder.buildObserved(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)	Build a dummy observed measurement.
protected void	AbstractCycleSlipDetector.cycleSlipDataSet(String nameSat, AbsoluteDate date, double value, GnssSignal signal)	Set the data: collect data at the current Date, at the current frequency, for a given satellite, add it within the attributes data and stuff.

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

Constructor	Description
AbstractInterSatellitesMeasurement(AbsoluteDate date, double observed, double sigma, double baseWeight, ObservableSatellite local, ObservableSatellite remote)	Constructor.
AbstractOnBoardMeasurement(AbsoluteDate date, double observed, double sigma, double baseWeight, List<ObservableSatellite> satellites)	Constructor.
AbstractOneWayGNSSMeasurement(PVCoordinatesProvider remotePV, QuadraticClockModel remoteClock, AbsoluteDate date, double range, double sigma, double baseWeight, ObservableSatellite local)	Simple constructor.
CombinedObservationDataSet(SatelliteSystem satelliteSystem, int prnNumber, AbsoluteDate tObs, double rcvrClkOffset, List<CombinedObservationData> observationData)	Simple constructor.
InterSatellitesOneWayRangeRate(ObservableSatellite local, ObservableSatellite remote, AbsoluteDate date, double rangeRate, double sigma, double baseWeight)	Constructor.
InterSatellitesPhase(ObservableSatellite local, ObservableSatellite remote, AbsoluteDate date, double phase, double wavelength, double sigma, double baseWeight, AmbiguityCache cache)	Constructor.
OneWayGNSSPhase(PVCoordinatesProvider remote, String remoteName, QuadraticClockModel remoteClock, AbsoluteDate date, double phase, double wavelength, double sigma, double baseWeight, ObservableSatellite local, AmbiguityCache cache)	Simple constructor.
OneWayGNSSRange(PVCoordinatesProvider remote, double dtRemote, AbsoluteDate date, double range, double sigma, double baseWeight, ObservableSatellite local)	Simple constructor.
OneWayGNSSRange(PVCoordinatesProvider remote, QuadraticClockModel remoteClock, AbsoluteDate date, double range, double sigma, double baseWeight, ObservableSatellite local)	Simple constructor.
OneWayGNSSRangeRate(PVCoordinatesProvider remote, double dtRemote, AbsoluteDate date, double rangeRate, double sigma, double baseWeight, ObservableSatellite local)	Simple constructor.
OneWayGNSSRangeRate(PVCoordinatesProvider remote, QuadraticClockModel remoteClock, AbsoluteDate date, double rangeRate, double sigma, double baseWeight, ObservableSatellite local)	Simple constructor.
Phase(GroundStation station, AbsoluteDate date, double phase, double wavelength, double sigma, double baseWeight, ObservableSatellite satellite, AmbiguityCache cache)	Simple constructor.

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

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

Modifier and Type	Method	Description
static double[]	AberrationModifier.naturalToProper(double[] naturalRaDec, GroundStation station, AbsoluteDate date, Frame frame)	Natural to proper correction for aberration of light.
static double[]	AberrationModifier.naturalToProper(double[] naturalRaDec, GroundStation station, AbsoluteDate date, Frame frame, DataContext context)	Natural to proper correction for aberration of light.
static double[]	AberrationModifier.properToNatural(double[] properRaDec, GroundStation station, AbsoluteDate date, Frame frame)	Proper to natural correction for aberration of light.
static double[]	AberrationModifier.properToNatural(double[] properRaDec, GroundStation station, AbsoluteDate date, Frame frame, DataContext context)	Proper to natural correction for aberration of light.

Uses of AbsoluteDate in org.orekit.estimation.sequential

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

Modifier and Type	Method	Description
AbsoluteDate	AbstractKalmanEstimator.getCurrentDate()	Get the current date.
AbsoluteDate	KalmanEstimation.getCurrentDate()	Get the current date.
AbsoluteDate	SemiAnalyticalKalmanModel.getCurrentDate()	Get the current date.
AbsoluteDate	SemiAnalyticalUnscentedKalmanModel.getCurrentDate()	Get the current date.

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

Modifier and Type	Method	Description
static MeasurementDecorator	KalmanEstimatorUtil.decorate(ObservedMeasurement<?> observedMeasurement, AbsoluteDate referenceDate)	Decorate an observed measurement.
static MeasurementDecorator	KalmanEstimatorUtil.decorateUnscented(ObservedMeasurement<?> observedMeasurement, AbsoluteDate referenceDate)	Decorate an observed measurement for an Unscented Kalman Filter.
void	SemiAnalyticalMeasurementHandler.init(SpacecraftState s0, AbsoluteDate t)	Initialize step handler at the start of a propagation.

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

Constructor	Description
MeasurementDecorator(ObservedMeasurement<?> observedMeasurement, RealMatrix covariance, AbsoluteDate reference)	Simple constructor.
SemiAnalyticalMeasurementHandler(SemiAnalyticalProcess model, KalmanFilter<MeasurementDecorator> filter, List<ObservedMeasurement<?>> observedMeasurements, AbsoluteDate referenceDate)	Simple constructor.
SemiAnalyticalMeasurementHandler(SemiAnalyticalProcess model, KalmanFilter<MeasurementDecorator> filter, List<ObservedMeasurement<?>> observedMeasurements, AbsoluteDate referenceDate, boolean isUnscented)	Simple constructor.

Uses of AbsoluteDate in org.orekit.files.ccsds.definitions

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

Modifier and Type	Method	Description
AbsoluteDate	TimeConverter.getReferenceDate()	Get the reference date for relative dates (may be null if no relative dates are used).
AbsoluteDate	TimeConverter.parse(String s)	Parse a relative or absolute date.

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

Modifier and Type	Method	Description
DateTimeComponents	TimeConverter.components(AbsoluteDate date)	Generate calendar components.
static Transform	FrameFacade.getTransform(FrameFacade frameIn, FrameFacade frameOut, Frame inertialPivotFrame, AbsoluteDate date, PVCoordinatesProvider pv)	Get the transform between CCSDS frames.
double	TimeConverter.offset(AbsoluteDate date)	Generate relative offset.

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

Constructor	Description
TimeConverter(TimeScale timeScale, AbsoluteDate referenceDate)	Build a time system.

Uses of AbsoluteDate in org.orekit.files.ccsds.ndm

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

Modifier and Type	Method	Description
AbsoluteDate	AbstractBuilder.getMissionReferenceDate()	Get the mission reference date or Mission Elapsed Time or Mission Relative Time time systems.
AbsoluteDate	CommonPhysicalProperties.getOebParentFrameEpoch()	Get the Optimally Enclosing Box parent reference frame epoch.

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

Modifier and Type	Method	Description
protected abstract T	AbstractBuilder.create(IERSConventions newConventions, double newEquatorialRadius, double newFlattening, DataContext newDataContext, AbsoluteDate newMissionReferenceDate, RangeUnitsConverter newRangeUnitsConverter)	Build an instance.
protected ParserBuilder	ParserBuilder.create(IERSConventions newConventions, double newEquatorialRadius, double newFlattening, DataContext newDataContext, AbsoluteDate newMissionReferenceDate, RangeUnitsConverter newRangeUnitsConverter)	Build an instance.
protected WriterBuilder	WriterBuilder.create(IERSConventions newConventions, double newEquatorialRadius, double newFlattening, DataContext newDataContext, AbsoluteDate newMissionReferenceDate, RangeUnitsConverter newRangeUnitsConverter)	Build an instance.
void	CommonPhysicalProperties.setOebParentFrameEpoch(AbsoluteDate oebParentFrameEpoch)	Set the Optimally Enclosing Box parent reference frame epoch.
T	AbstractBuilder.withMissionReferenceDate(AbsoluteDate newMissionReferenceDate)	Set up mission reference date or Mission Elapsed Time or Mission Relative Time time systems.

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

Constructor	Description
AbstractBuilder(IERSConventions conventions, double equatorialRadius, double flattening, DataContext dataContext, AbsoluteDate missionReferenceDate, RangeUnitsConverter rangeUnitsConverter)	Complete constructor.

Uses of AbsoluteDate in org.orekit.files.ccsds.ndm.adm

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

Modifier and Type	Method	Description
AbsoluteDate	AdmParser.getMissionReferenceDate()	Get reference date for Mission Elapsed Time and Mission Relative Time time systems.

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

Modifier and Type	Method	Description
abstract TimeStampedAngularCoordinates	AttitudeType.build(boolean isFirst, boolean isExternal2SpacecraftBody, RotationOrder eulerRotSequence, boolean isSpacecraftBodyRate, AbsoluteDate date, double... components)	Get the angular coordinates corresponding to the attitude data.

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

Constructor	Description
AdmParser(String root, String formatVersionKey, IERSConventions conventions, boolean simpleEOP, DataContext dataContext, AbsoluteDate missionReferenceDate, ParsedUnitsBehavior parsedUnitsBehavior, Function<ParseToken,List<ParseToken>>[] filters)	Complete constructor.

Uses of AbsoluteDate in org.orekit.files.ccsds.ndm.adm.acm

Methods in org.orekit.files.ccsds.ndm.adm.acm that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	AttitudeCovariance.getDate()	Get the date.
AbsoluteDate	AttitudeState.getDate()	Get the date.
AbsoluteDate	AcmMetadata.getEpochT0()	Get the epoch to which all relative times are referenced in data blocks.
AbsoluteDate	AcmMetadata.getNextLeapEpoch()	Get the epoch of next leap second.
AbsoluteDate	AcmSatelliteEphemeris.getStart()	Get the start date of the ephemeris.
AbsoluteDate	AttitudeStateHistory.getStart()	Get the start date of this ephemeris segment.
AbsoluteDate	AcmMetadata.getStartTime()	Get the time of the earliest data contained in the OCM.
AbsoluteDate	AcmSatelliteEphemeris.getStop()	Get the end date of the ephemeris.
AbsoluteDate	AttitudeStateHistory.getStop()	Get the end date of this ephemeris segment.
AbsoluteDate	AcmMetadata.getStopTime()	Get the time of the latest data contained in the OCM.

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

Modifier and Type	Method	Description
void	AcmMetadata.setEpochT0(AbsoluteDate epochT0)	Set the epoch to which all relative times are referenced in data blocks.
void	AcmMetadata.setNextLeapEpoch(AbsoluteDate nextLeapEpoch)	Set the epoch of next leap second.
void	AcmMetadata.setStartTime(AbsoluteDate startTime)	Set the time of the earliest data contained in the OCM.
void	AcmMetadata.setStopTime(AbsoluteDate stopTime)	Set the time of the latest data contained in the OCM.
abstract TimeStampedAngularCoordinates	RateElementsType.toAngular(AbsoluteDate date, RotationOrder order, Rotation rotation, int first, double[] elements)	Convert to angyla coordinates.

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

Constructor	Description
AttitudeCovariance(AttitudeCovarianceType type, AbsoluteDate date, String[] fields, int first)	Simple constructor.
AttitudePhysicalProperties(AbsoluteDate epochT0)	Simple constructor.
AttitudeState(AttitudeElementsType attitudeType, RateElementsType rateType, AbsoluteDate date, String[] fields, int first)	Simple constructor.

Uses of AbsoluteDate in org.orekit.files.ccsds.ndm.adm.aem

Methods in org.orekit.files.ccsds.ndm.adm.aem that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	AemMetadata.getStart()	Get the start date of this ephemeris segment.
AbsoluteDate	AemSatelliteEphemeris.getStart()	Get the start date of the ephemeris.
AbsoluteDate	AemSegment.getStart()	Get the start date of this ephemeris segment.
AbsoluteDate	AemMetadata.getStartTime()	Get start of total time span covered by attitude data.
AbsoluteDate	AemMetadata.getStop()	Get the end date of this ephemeris segment.
AbsoluteDate	AemSatelliteEphemeris.getStop()	Get the end date of the ephemeris.
AbsoluteDate	AemSegment.getStop()	Get the end date of this ephemeris segment.
AbsoluteDate	AemMetadata.getStopTime()	Get end of total time span covered by attitude data.
AbsoluteDate	AemMetadata.getUseableStartTime()	Get start of useable time span covered by attitude data.
AbsoluteDate	AemMetadata.getUseableStopTime()	Get end of useable time span covered by ephemerides data.

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

Modifier and Type	Method	Description
void	StreamingAemWriter.SegmentWriter.init(SpacecraftState s0, AbsoluteDate t, double step)	Initialize step handler at the start of a propagation.
void	AemMetadata.setStartTime(AbsoluteDate startTime)	Set start of total time span covered by attitude data.
void	AemMetadata.setStopTime(AbsoluteDate stopTime)	Set end of total time span covered by attitude data.
void	AemMetadata.setUseableStartTime(AbsoluteDate useableStartTime)	Set start of useable time span covered by attitude data.
void	AemMetadata.setUseableStopTime(AbsoluteDate useableStopTime)	Set end of useable time span covered by ephemerides data.

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

Constructor	Description
AemParser(IERSConventions conventions, boolean simpleEOP, DataContext dataContext, AbsoluteDate missionReferenceDate, int defaultInterpolationDegree, ParsedUnitsBehavior parsedUnitsBehavior, Function<ParseToken,List<ParseToken>>[] filters)	Complete constructor.
AemWriter(IERSConventions conventions, DataContext dataContext, AbsoluteDate missionReferenceDate)	Constructor used to create a new AEM writer configured with the necessary parameters to successfully fill in all required fields that aren't part of a standard object.

Uses of AbsoluteDate in org.orekit.files.ccsds.ndm.adm.apm

Methods in org.orekit.files.ccsds.ndm.adm.apm that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	ApmData.getEpoch()	Get the epoch of the data.
AbsoluteDate	Maneuver.getEpochStart()	Get epoch start.

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

Modifier and Type	Method	Description
void	Maneuver.setEpochStart(AbsoluteDate epochStart)	Set epoch start.

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

Constructor	Description
ApmData(CommentsContainer commentsBlock, AbsoluteDate epoch, ApmQuaternion quaternionBlock, Euler eulerBlock, AngularVelocity angularVelocityBlock, SpinStabilized spinStabilizedBlock, Inertia inertia)	Simple constructor.
ApmParser(IERSConventions conventions, boolean simpleEOP, DataContext dataContext, AbsoluteDate missionReferenceDate, ParsedUnitsBehavior parsedUnitsBehavior, Function<ParseToken,List<ParseToken>>[] filters)	Complete constructor.
ApmWriter(IERSConventions conventions, DataContext dataContext, AbsoluteDate missionReferenceDate)	Complete constructor.

Uses of AbsoluteDate in org.orekit.files.ccsds.ndm.cdm

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

Modifier and Type	Method	Description
AbsoluteDate	CdmRelativeMetadata.getNextMessageEpoch()	Get Scheduled UTC epoch of the next CDM associated with the event identified by CONJUNCTION_ID.
AbsoluteDate	ODParameters.getOdEpoch()	Get the epoch of the orbit determination used for this message.
AbsoluteDate	CdmRelativeMetadata.getPreviousMessageEpoch()	Get the UTC epoch of the previous CDM issued for the event identified by CONJUNCTION_ID.
AbsoluteDate	CdmRelativeMetadata.getScreenEntryTime()	Get the time in UTC when Object2 enters the screening volume.
AbsoluteDate	CdmRelativeMetadata.getScreenExitTime()	Get the time in UTC when Object2 exits the screening volume.
AbsoluteDate	CdmRelativeMetadata.getStartScreenPeriod()	Get the start time in UTC of the screening period for the conjunction assessment.
AbsoluteDate	CdmRelativeMetadata.getStopScreenPeriod()	Get the stop time in UTC of the screening period for the conjunction assessment.
AbsoluteDate	CdmRelativeMetadata.getTca()	Get the date and time in UTC of the closest approach.
AbsoluteDate	ODParameters.getTimeLastObsEnd()	Get the start of a time interval (UTC) that contains the time of the last accepted observation.
AbsoluteDate	ODParameters.getTimeLastObsStart()	Get the start of a time interval (UTC) that contains the time of the last accepted observation.

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

Modifier and Type	Method	Description
void	CdmRelativeMetadata.setNextMessageEpoch(AbsoluteDate nextMessageEpoch)	Set Scheduled UTC epoch of the next CDM associated with the event identified by CONJUNCTION_ID.
void	ODParameters.setOdEpoch(AbsoluteDate odEpoch)	Set the epoch of the orbit determination used for this message.
void	CdmRelativeMetadata.setPreviousMessageEpoch(AbsoluteDate previousMessageEpoch)	Set the UTC epoch of the previous CDM issued for the event identified by CONJUNCTION_ID.
void	CdmRelativeMetadata.setScreenEntryTime(AbsoluteDate screenEntryTime)	Set the time in UTC when Object2 enters the screening volume.
void	CdmRelativeMetadata.setScreenExitTime(AbsoluteDate screenExitTime)	Set the time in UTC when Object2 exits the screening volume.
void	CdmRelativeMetadata.setStartScreenPeriod(AbsoluteDate startScreenPeriod)	Set the start time in UTC of the screening period for the conjunction assessment.
void	CdmRelativeMetadata.setStopScreenPeriod(AbsoluteDate stopScreenPeriod)	Set the stop time in UTC of the screening period for the conjunction assessment.
void	CdmRelativeMetadata.setTca(AbsoluteDate tca)	Set the date and time in UTC of the closest approach.
void	ODParameters.setTimeLastObsEnd(AbsoluteDate timeLastObsEnd)	Set the start of a time interval (UTC) that contains the time of the last accepted observation.
void	ODParameters.setTimeLastObsStart(AbsoluteDate timeLastObsStart)	Set the start of a time interval (UTC) that contains the time of the last accepted observation.

Uses of AbsoluteDate in org.orekit.files.ccsds.ndm.odm

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

Modifier and Type	Method	Description
AbsoluteDate	CartesianCovariance.getEpoch()	Get matrix epoch.
AbsoluteDate	KeplerianElements.getEpoch()	Get epoch of state vector, Keplerian elements and covariance matrix data.
AbsoluteDate	StateVector.getEpoch()	Get epoch of state vector, Keplerian elements and covariance matrix data.
AbsoluteDate	OdmCommonMetadata.getFrameEpoch()	Get epoch of reference frame, if not intrinsic to the definition of the reference frame.
AbsoluteDate	OdmParser.getMissionReferenceDate()	Get reference date for Mission Elapsed Time and Mission Relative Time time systems.

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

Modifier and Type	Method	Description
void	CartesianCovariance.setEpoch(AbsoluteDate epoch)	Set matrix epoch.
void	KeplerianElements.setEpoch(AbsoluteDate epoch)	Set epoch of state vector, Keplerian elements and covariance matrix data.
void	StateVector.setEpoch(AbsoluteDate epoch)	Set epoch of state vector, Keplerian elements and covariance matrix data.
void	OdmCommonMetadata.setFrameEpoch(AbsoluteDate frameEpoch)	Set epoch of reference frame, if not intrinsic to the definition of the reference frame.

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

Constructor	Description
OdmParser(String root, String formatVersionKey, IERSConventions conventions, boolean simpleEOP, DataContext dataContext, AbsoluteDate missionReferenceDate, double mu, ParsedUnitsBehavior parsedUnitsBehavior, Function<ParseToken,List<ParseToken>>[] filters)	Complete constructor.

Uses of AbsoluteDate in org.orekit.files.ccsds.ndm.odm.ocm

Methods in org.orekit.files.ccsds.ndm.odm.ocm that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	OrbitCovarianceHistoryMetadata.getCovFrameEpoch()	Get epoch of the covariance reference frame.
AbsoluteDate	OrbitCovariance.getDate()	Get the date.
AbsoluteDate	OrbitManeuver.getDate()	Get the date.
AbsoluteDate	TrajectoryState.getDate()	Get the date.
AbsoluteDate	OrbitManeuverHistoryMetadata.getDcExecStart()	Get the start time of initial duty cycle-based maneuver execution.
AbsoluteDate	OrbitManeuverHistoryMetadata.getDcExecStop()	Get the end time of final duty cycle-based maneuver execution.
AbsoluteDate	OrbitManeuverHistoryMetadata.getDcRefTime()	Get duty cycle thrust reference time.
AbsoluteDate	OrbitManeuverHistoryMetadata.getDcWindowClose()	Get the end time of duty cycle-based maneuver window.
AbsoluteDate	OrbitManeuverHistoryMetadata.getDcWindowOpen()	Get the start time of duty cycle-based maneuver window.
AbsoluteDate	OrbitDetermination.getEpoch()	Get time tag for orbit determination solved-for state.
AbsoluteDate	OcmMetadata.getEpochT0()	Get the epoch to which all relative times are referenced in data blocks.
AbsoluteDate	OrbitManeuverHistoryMetadata.getManFrameEpoch()	Get epoch of the maneuver reference frame.
AbsoluteDate	OrbitManeuverHistoryMetadata.getManNextEpoch()	Get start time of next maneuver.
AbsoluteDate	OrbitManeuverHistoryMetadata.getManPrevEpoch()	Get completion time of previous maneuver.
AbsoluteDate	OcmMetadata.getNextLeapEpoch()	Get the epoch of next leap second.
AbsoluteDate	OcmMetadata.getNextMessageEpoch()	Get the creation date of next message from a given originator.
AbsoluteDate	OcmMetadata.getPreviousMessageEpoch()	Get the creation date of previous message from a given originator.
AbsoluteDate	Perturbations.getSpaceWeatherEpoch()	Get epoch of the Space Weather data.
AbsoluteDate	OcmSatelliteEphemeris.getStart()	Get the start date of the ephemeris.
AbsoluteDate	TrajectoryStateHistory.getStart()	Get the start date of this ephemeris segment.
AbsoluteDate	OcmMetadata.getStartTime()	Get the time of the earliest data contained in the OCM.
AbsoluteDate	OcmSatelliteEphemeris.getStop()	Get the end date of the ephemeris.
AbsoluteDate	TrajectoryStateHistory.getStop()	Get the end date of this ephemeris segment.
AbsoluteDate	OcmMetadata.getStopTime()	Get the time of the latest data contained in the OCM.
AbsoluteDate	TrajectoryStateHistoryMetadata.getTrajFrameEpoch()	Get epoch of the trajectory reference frame.
AbsoluteDate	TrajectoryStateHistoryMetadata.getUseableStartTime()	Get start of useable time span covered by ephemerides data, it may be necessary to allow for proper interpolation.
AbsoluteDate	TrajectoryStateHistoryMetadata.getUseableStopTime()	Get end of useable time span covered by ephemerides data, it may be necessary to allow for proper interpolation.

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

Modifier and Type	Method	Description
void	StreamingOcmWriter.BlockWriter.init(SpacecraftState s0, AbsoluteDate t, double step)	Initialize step handler at the start of a propagation.
void	OrbitCovarianceHistoryMetadata.setCovFrameEpoch(AbsoluteDate covFrameEpoch)	Set epoch of the covariance reference frame.
void	OrbitManeuver.setDate(AbsoluteDate date)	Set date.
void	OrbitManeuverHistoryMetadata.setDcExecStart(AbsoluteDate dcExecStart)	Set the start time of initial duty cycle-based maneuver execution.
void	OrbitManeuverHistoryMetadata.setDcExecStop(AbsoluteDate dcExecStop)	Set the end time of final duty cycle-based maneuver execution.
void	OrbitManeuverHistoryMetadata.setDcRefTime(AbsoluteDate dcRefTime)	Set duty cycle thrust reference time.
void	OrbitManeuverHistoryMetadata.setDcWindowClose(AbsoluteDate dcWindowClose)	Set the end time of duty cycle-based maneuver window.
void	OrbitManeuverHistoryMetadata.setDcWindowOpen(AbsoluteDate dcWindowOpen)	Set the start time of duty cycle-based maneuver window.
void	OrbitDetermination.setEpoch(AbsoluteDate epoch)	Set time tag for orbit determination solved-for state.
void	OcmMetadata.setEpochT0(AbsoluteDate epochT0)	Set the epoch to which all relative times are referenced in data blocks.
void	OrbitManeuverHistoryMetadata.setManFrameEpoch(AbsoluteDate manFrameEpoch)	Set epoch of the maneuver reference frame.
void	OrbitManeuverHistoryMetadata.setManNextEpoch(AbsoluteDate manNextEpoch)	Set start time of next maneuver.
void	OrbitManeuverHistoryMetadata.setManPrevEpoch(AbsoluteDate manPrevEpoch)	Set completion time of previous maneuver.
void	OcmMetadata.setNextLeapEpoch(AbsoluteDate nextLeapEpoch)	Set the epoch of next leap second.
void	OcmMetadata.setNextMessageEpoch(AbsoluteDate nextMessageEpoch)	Set the creation date of next message from a given originator.
void	OcmMetadata.setPreviousMessageEpoch(AbsoluteDate previousMessageEpoch)	Set the creation date of previous message from a given originator.
void	Perturbations.setSpaceWeatherEpoch(AbsoluteDate spaceWeatherEpoch)	Set epoch of the Space Weather data.
void	OcmMetadata.setStartTime(AbsoluteDate startTime)	Set the time of the earliest data contained in the OCM.
void	OcmMetadata.setStopTime(AbsoluteDate stopTime)	Set the time of the latest data contained in the OCM.
void	TrajectoryStateHistoryMetadata.setTrajFrameEpoch(AbsoluteDate trajFrameEpoch)	Set epoch of the trajectory reference frame.
void	TrajectoryStateHistoryMetadata.setUseableStartTime(AbsoluteDate useableStartTime)	Set start of useable time span covered by ephemerides data, it may be necessary to allow for proper interpolation.
void	TrajectoryStateHistoryMetadata.setUseableStopTime(AbsoluteDate useableStopTime)	Set end of useable time span covered by ephemerides data, it may be necessary to allow for proper interpolation.
TimeStampedPVCoordinates	OrbitElementsType.toCartesian(AbsoluteDate date, double[] elements, OneAxisEllipsoid body, double mu)	Convert to Cartesian coordinates.

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

Constructor	Description
OrbitCovariance(OrbitElementsType type, Ordering ordering, AbsoluteDate date, String[] fields, int first)	Simple constructor.
OrbitCovarianceHistoryMetadata(AbsoluteDate epochT0)	Simple constructor.
OrbitManeuverHistoryMetadata(AbsoluteDate epochT0)	Simple constructor.
OrbitPhysicalProperties(AbsoluteDate epochT0)	Simple constructor.
TrajectoryState(OrbitElementsType type, AbsoluteDate date, double[] elements)	Simple constructor.
TrajectoryState(OrbitElementsType type, AbsoluteDate date, String[] fields, int first, List<Unit> units)	Simple constructor.
TrajectoryStateHistoryMetadata(AbsoluteDate epochT0, DataContext dataContext)	Simple constructor.

Uses of AbsoluteDate in org.orekit.files.ccsds.ndm.odm.oem

Methods in org.orekit.files.ccsds.ndm.odm.oem that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	OemSatelliteEphemeris.getStart()	Get the start date of the ephemeris.
AbsoluteDate	OemSegment.getStart()	Get the start date of this ephemeris segment.
AbsoluteDate	OemMetadata.getStartTime()	Get start of total time span covered by ephemerides data and covariance data.
AbsoluteDate	OemSatelliteEphemeris.getStop()	Get the end date of the ephemeris.
AbsoluteDate	OemSegment.getStop()	Get the end date of this ephemeris segment.
AbsoluteDate	OemMetadata.getStopTime()	Get end of total time span covered by ephemerides data and covariance data.
AbsoluteDate	OemMetadata.getUseableStartTime()	Get start of useable time span covered by ephemerides data, it may be necessary to allow for proper interpolation.
AbsoluteDate	OemMetadata.getUseableStopTime()	Get end of useable time span covered by ephemerides data, it may be necessary to allow for proper interpolation.

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

Modifier and Type	Method	Description
void	StreamingOemWriter.SegmentWriter.init(SpacecraftState s0, AbsoluteDate t, double step)	Initialize step handler at the start of a propagation.
void	OemMetadata.setStartTime(AbsoluteDate startTime)	Set start of total time span covered by ephemerides data and covariance data.
void	OemMetadata.setStopTime(AbsoluteDate stopTime)	Set end of total time span covered by ephemerides data and covariance data.
void	OemMetadata.setUseableStartTime(AbsoluteDate useableStartTime)	Set start of useable time span covered by ephemerides data, it may be necessary to allow for proper interpolation.
void	OemMetadata.setUseableStopTime(AbsoluteDate useableStopTime)	Set end of useable time span covered by ephemerides data, it may be necessary to allow for proper interpolation.

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

Constructor	Description
OemParser(IERSConventions conventions, boolean simpleEOP, DataContext dataContext, AbsoluteDate missionReferenceDate, double mu, int defaultInterpolationDegree, ParsedUnitsBehavior parsedUnitsBehavior, Function<ParseToken,List<ParseToken>>[] filters)	Complete constructor.
OemWriter(IERSConventions conventions, DataContext dataContext, AbsoluteDate missionReferenceDate)	Constructor used to create a new OEM writer configured with the necessary parameters to successfully fill in all required fields that aren't part of a standard object.

Uses of AbsoluteDate in org.orekit.files.ccsds.ndm.odm.omm

Methods in org.orekit.files.ccsds.ndm.odm.omm that return AbsoluteDate

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

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

Constructor	Description
OmmParser(IERSConventions conventions, boolean simpleEOP, DataContext dataContext, AbsoluteDate missionReferenceDate, double mu, double defaultMass, ParsedUnitsBehavior parsedUnitsBehavior, Function<ParseToken,List<ParseToken>>[] filters)	Complete constructor.
OmmWriter(IERSConventions conventions, DataContext dataContext, AbsoluteDate missionReferenceDate)	Complete constructor.

Uses of AbsoluteDate in org.orekit.files.ccsds.ndm.odm.opm

Methods in org.orekit.files.ccsds.ndm.odm.opm that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	Opm.getDate()	Get the date.
AbsoluteDate	Maneuver.getEpochIgnition()	Get epoch ignition.

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

Modifier and Type	Method	Description
void	Maneuver.setEpochIgnition(AbsoluteDate epochIgnition)	Set epoch ignition.

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

Constructor	Description
OpmParser(IERSConventions conventions, boolean simpleEOP, DataContext dataContext, AbsoluteDate missionReferenceDate, double mu, double defaultMass, ParsedUnitsBehavior parsedUnitsBehavior, Function<ParseToken,List<ParseToken>>[] filters)	Complete constructor.
OpmWriter(IERSConventions conventions, DataContext dataContext, AbsoluteDate missionReferenceDate)	Complete constructor.

Uses of AbsoluteDate in org.orekit.files.ccsds.ndm.tdm

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

Modifier and Type	Method	Description
AbsoluteDate	Observation.getEpoch()	Getter for the epoch.
AbsoluteDate	TdmMetadata.getStartTime()	Getter for the startTime.
AbsoluteDate	TdmMetadata.getStopTime()	Getter for the stopTime.

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

Modifier and Type	Method	Description
void	ObservationsBlock.addObservation(ObservationType type, AbsoluteDate epoch, double measurement)	Adds an observation data line.
double	IdentityConverter.metersToRu(TdmMetadata metadata, AbsoluteDate date, double range)	Convert a range expressed in meters.
double	RangeUnitsConverter.metersToRu(TdmMetadata metadata, AbsoluteDate date, double range)	Convert a range expressed in meters.
double	ObservationType.rawToSI(RangeUnitsConverter ruConverter, TdmMetadata metadata, AbsoluteDate date, double rawValue)	Convert a measurement to SI units.
double	IdentityConverter.ruToMeters(TdmMetadata metadata, AbsoluteDate date, double range)	Convert a range expressed in Range Units.
double	RangeUnitsConverter.ruToMeters(TdmMetadata metadata, AbsoluteDate date, double range)	Convert a range expressed in Range Units.
void	TdmMetadata.setStartTime(AbsoluteDate startTime)	Setter for the startTime.
void	TdmMetadata.setStopTime(AbsoluteDate stopTime)	Setter for the stopTime.
double	ObservationType.siToRaw(RangeUnitsConverter ruConverter, TdmMetadata metadata, AbsoluteDate date, double siValue)	Convert a measurement from SI units.

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

Constructor	Description
Observation(ObservationType type, AbsoluteDate epoch, double measurement)	Simple constructor.

Uses of AbsoluteDate in org.orekit.files.ccsds.section

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

Modifier and Type	Method	Description
AbsoluteDate	Header.getCreationDate()	Get the message creation date and time in UTC.

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

Modifier and Type	Method	Description
void	Header.setCreationDate(AbsoluteDate creationDate)	Set the message creation date and time in UTC.

Uses of AbsoluteDate in org.orekit.files.ccsds.utils

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

Modifier and Type	Method	Description
AbsoluteDate	ContextBinding.getReferenceDate()	Get initial date.

Uses of AbsoluteDate in org.orekit.files.ccsds.utils.generation

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

Modifier and Type	Method	Description
String	AbstractGenerator.dateToCalendarString(TimeConverter converter, AbsoluteDate date)	Convert a date to calendar string value with high precision.
String	Generator.dateToCalendarString(TimeConverter converter, AbsoluteDate date)	Convert a date to calendar string value with high precision.
String	AbstractGenerator.dateToString(TimeConverter converter, AbsoluteDate date)	Convert a date to string value with high precision.
String	Generator.dateToString(TimeConverter converter, AbsoluteDate date)	Convert a date to string value with high precision.
void	AbstractGenerator.writeEntry(String key, TimeConverter converter, AbsoluteDate date, boolean forceCalendar, boolean mandatory)	Write a single key/value entry.
void	Generator.writeEntry(String key, TimeConverter converter, AbsoluteDate date, boolean forceCalendar, boolean mandatory)	Write a single key/value entry.

Uses of AbsoluteDate in org.orekit.files.ccsds.utils.lexical

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

Modifier and Type	Method	Description
void	ParseToken.DateConsumer.accept(AbsoluteDate value)	Consume a date.

Uses of AbsoluteDate in org.orekit.files.general

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

Modifier and Type	Method	Description
AbsoluteDate	EphemerisSegmentPropagator.getMaxDate()
AbsoluteDate	EphemerisSegmentPropagator.getMinDate()
AbsoluteDate	AttitudeEphemerisFile.AttitudeEphemerisSegment.getStart()	Get the start date of this ephemeris segment.
AbsoluteDate	AttitudeEphemerisFile.SatelliteAttitudeEphemeris.getStart()	Get the start date of the ephemeris.
AbsoluteDate	EphemerisFile.EphemerisSegment.getStart()	Get the start date of this ephemeris segment.
AbsoluteDate	EphemerisFile.SatelliteEphemeris.getStart()	Get the start date of the ephemeris.
AbsoluteDate	OrekitAttitudeEphemerisFile.OrekitAttitudeEphemerisSegment.getStart()	Get the start date of this ephemeris segment.
AbsoluteDate	OrekitAttitudeEphemerisFile.OrekitSatelliteAttitudeEphemeris.getStart()	Get the start date of the ephemeris.
AbsoluteDate	OrekitEphemerisFile.OrekitEphemerisSegment.getStart()	Get the start date of this ephemeris segment.
AbsoluteDate	OrekitEphemerisFile.OrekitSatelliteEphemeris.getStart()	Get the start date of the ephemeris.
AbsoluteDate	AttitudeEphemerisFile.AttitudeEphemerisSegment.getStop()	Get the end date of this ephemeris segment.
AbsoluteDate	AttitudeEphemerisFile.SatelliteAttitudeEphemeris.getStop()	Get the end date of the ephemeris.
AbsoluteDate	EphemerisFile.EphemerisSegment.getStop()	Get the end date of this ephemeris segment.
AbsoluteDate	EphemerisFile.SatelliteEphemeris.getStop()	Get the end date of the ephemeris.
AbsoluteDate	OrekitAttitudeEphemerisFile.OrekitAttitudeEphemerisSegment.getStop()	Get the end date of this ephemeris segment.
AbsoluteDate	OrekitAttitudeEphemerisFile.OrekitSatelliteAttitudeEphemeris.getStop()	Get the end date of the ephemeris.
AbsoluteDate	OrekitEphemerisFile.OrekitEphemerisSegment.getStop()	Get the end date of this ephemeris segment.
AbsoluteDate	OrekitEphemerisFile.OrekitSatelliteEphemeris.getStop()	Get the end date of the ephemeris.

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

Modifier and Type	Method	Description
protected double	EphemerisSegmentPropagator.getMass(AbsoluteDate date)
Vector3D	EphemerisSegmentPropagator.getPosition(AbsoluteDate date, Frame frame)
TimeStampedPVCoordinates	EphemerisSegmentPropagator.getPVCoordinates(AbsoluteDate date, Frame frame)
protected Orbit	EphemerisSegmentPropagator.propagateOrbit(AbsoluteDate date)

Uses of AbsoluteDate in org.orekit.files.ilrs

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

Modifier and Type	Method	Description
AbsoluteDate	CRD.AnglesMeasurement.getDate()	Get the date.
AbsoluteDate	CRD.Calibration.getDate()
AbsoluteDate	CRD.MeteorologicalMeasurement.getDate()	Get the date.
AbsoluteDate	CRD.RangeMeasurement.getDate()	Get the date.
AbsoluteDate	CRD.RangeSupplement.getDate()
AbsoluteDate	ILRSHeader.getEndEpoch()	Get the ending epoch (UTC).
AbsoluteDate	CPF.CPFEphemeris.getStart()	Get the start date of the ephemeris.
AbsoluteDate	ILRSHeader.getStartEpoch()	Get the starting epoch (UTC).
AbsoluteDate	CPF.CPFEphemeris.getStop()	Get the end date of the ephemeris.

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

Modifier and Type	Method	Description
CRD.MeteorologicalMeasurement	CRD.Meteo.getMeteo(AbsoluteDate date)	Get the meteorological parameters at a given date.
void	ILRSHeader.setEndEpoch(AbsoluteDate endEpoch)	Set the ending epoch (UTC).
void	ILRSHeader.setStartEpoch(AbsoluteDate startEpoch)	Set the staring epoch (UTC).

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

Constructor	Description
AnglesMeasurement(AbsoluteDate date, double azimuth, double elevation, int directionFlag, int originIndicator, boolean refractionCorrected, double azimuthRate, double elevationRate)	Constructor.
Calibration(AbsoluteDate date, int typeOfData, String systemConfigurationId, int numberOfPointsRecorded, int numberOfPointsUsed, double oneWayDistance, double systemDelay, double delayShift, double rms, double skew, double kurtosis, double peakMinusMean, int typeIndicator, int shiftTypeIndicator, int detectorChannel, int span, double returnRate)	Constructor.
CalibrationDetail(AbsoluteDate date, int typeOfData, String systemConfigurationId, int numberOfPointsRecorded, int numberOfPointsUsed, double oneWayDistance, double systemDelay, double delayShift, double rms, double skew, double kurtosis, double peakMinusMean, int typeIndicator, int shiftTypeIndicator, int detectorChannel, int span, double returnRate)	Constructor.
CPFCoordinate(AbsoluteDate date, Vector3D position, int leap)	Constructor with null velocity vector.
CPFCoordinate(AbsoluteDate date, Vector3D position, Vector3D velocity, int leap)	Constructor.
FrRangeMeasurement(AbsoluteDate date, double timeOfFlight, int epochEvent, String systemConfigurationId, int filterFlag, int detectorChannel, int stopNumber, int receiveAmplitude, int transmitAmplitude)	Constructor.
MeteorologicalMeasurement(AbsoluteDate date, double pressure, double temperature, double humidity)	Constructor.
MeteorologicalMeasurement(AbsoluteDate date, double pressure, double temperature, double humidity, int originOfValues)	Constructor.
NptRangeMeasurement(AbsoluteDate date, double timeOfFlight, int epochEvent, double snr, String systemConfigurationId)	Constructor.
NptRangeMeasurement(AbsoluteDate date, double timeOfFlight, int epochEvent, double snr, String systemConfigurationId, double windowLength, int numberOfRawRanges, double binRms, double binSkew, double binKurtosis, double binPeakMinusMean, double returnRate, int detectorChannel)	Constructor.
RangeMeasurement(AbsoluteDate date, double timeOfFlight, int epochEvent)	Constructor.
RangeMeasurement(AbsoluteDate date, double timeOfFlight, int epochEvent, double snr)	Constructor.
RangeMeasurement(AbsoluteDate date, double timeOfFlight, int epochEvent, double snr, String systemConfigurationId)	Constructor.
RangeSupplement(AbsoluteDate date, String systemConfigurationId, double troposphericRefractionCorrection, double centerOfMassCorrection, double ndFilterValue, double timeBiasApplied, double rangeRate)	Constructor.

Uses of AbsoluteDate in org.orekit.files.rinex.clock

Methods in org.orekit.files.rinex.clock that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	RinexClock.getCreationDate()	Getter for the creation date.
AbsoluteDate	RinexClock.getEarliestEpoch()	Get earliest epoch from the clock data.
AbsoluteDate	RinexClock.ReferenceClock.getEndDate()	Getter for the validity period end date.
AbsoluteDate	RinexClock.ClockDataLine.getEpoch()	Get data line epoch.
AbsoluteDate	RinexClock.ClockDataLine.getEpoch(TimeScale epochTimeScale)	Get data line epoch.
AbsoluteDate	RinexClock.getLatestEpoch()	Get latest epoch from the clock data.
AbsoluteDate	RinexClock.ReferenceClock.getStartDate()	Getter for the validity period start date.

Methods in org.orekit.files.rinex.clock with parameters of type AbsoluteDate

Modifier and Type	Method	Description
void	RinexClock.addReferenceClockList(List<RinexClock.ReferenceClock> referenceClockList, AbsoluteDate startDate)	Add a list of reference clocks which will be used after a specified date.
void	RinexClock.setCreationDate(AbsoluteDate creationDate)	Setter for the creation date.

Constructors in org.orekit.files.rinex.clock with parameters of type AbsoluteDate

Constructor	Description
ReferenceClock(String referenceName, String clockID, double clockConstraint, AbsoluteDate startDate, AbsoluteDate endDate)	Constructor.

Uses of AbsoluteDate in org.orekit.files.rinex.navigation

Methods in org.orekit.files.rinex.navigation that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	TimeSystemCorrection.getReferenceDate()	Getter for the reference date of the time system correction polynomial.
AbsoluteDate	EarthOrientationParameterMessage.getReferenceEpoch()	Get the reference epoch.
AbsoluteDate	SystemTimeOffsetMessage.getReferenceEpoch()	Get the reference epoch.
AbsoluteDate	IonosphereBaseMessage.getTransmitTime()	Get the transmit time.

Methods in org.orekit.files.rinex.navigation with parameters of type AbsoluteDate

Modifier and Type	Method	Description
void	EarthOrientationParameterMessage.setReferenceEpoch(AbsoluteDate referenceEpoch)	Set the reference epoch.
void	SystemTimeOffsetMessage.setReferenceEpoch(AbsoluteDate referenceEpoch)	Set the reference epoch.
void	IonosphereBaseMessage.setTransmitTime(AbsoluteDate transmitTime)	Set the transmit time.

Constructors in org.orekit.files.rinex.navigation with parameters of type AbsoluteDate

Constructor	Description
TimeSystemCorrection(String timeSystemCorrectionType, AbsoluteDate referenceDate, double timeSystemCorrectionA0, double timeSystemCorrectionA1)	Constructor.

Uses of AbsoluteDate in org.orekit.files.rinex.observation

Methods in org.orekit.files.rinex.observation that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	ObservationDataSet.getDate()	Get the date.
AbsoluteDate	RinexObservationHeader.getTFirstObs()	Get the time of First observation record.
AbsoluteDate	RinexObservationHeader.getTLastObs()	Get the time of last observation record.

Methods in org.orekit.files.rinex.observation with parameters of type AbsoluteDate

Modifier and Type	Method	Description
void	RinexObservationHeader.setTFirstObs(AbsoluteDate firstObs)	Set the time of First observation record.
void	RinexObservationHeader.setTLastObs(AbsoluteDate lastObs)	Set the time of last observation record.

Constructors in org.orekit.files.rinex.observation with parameters of type AbsoluteDate

Constructor	Description
ObservationDataSet(SatInSystem satellite, AbsoluteDate tObs, int eventFlag, double rcvrClkOffset, List<ObservationData> observationData)	Simple constructor.

Uses of AbsoluteDate in org.orekit.files.rinex.section

Methods in org.orekit.files.rinex.section that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	RinexBaseHeader.getCreationDate()	Getter for the creation date.

Methods in org.orekit.files.rinex.section with parameters of type AbsoluteDate

Modifier and Type	Method	Description
void	RinexBaseHeader.setCreationDate(AbsoluteDate creationDate)	Setter for the creation date.

Uses of AbsoluteDate in org.orekit.files.sinex

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

Modifier and Type	Method	Description
AbsoluteDate	AbstractSinex.getCreationDate()	Get the creation date of the parsed SINEX file.
protected AbsoluteDate	ParseInfo.getCreationDate()	Get creation date.
AbsoluteDate	SinexEopEntry.getDate()	Get the date.
protected AbsoluteDate	ParseInfo.getEndDate()	Get end date.
AbsoluteDate	Station.getEpoch()	Get the coordinates reference epoch.
AbsoluteDate	AbstractSinex.getFileEpochEndTime()	Get the file epoch end time.
AbsoluteDate	AbstractSinex.getFileEpochStartTime()	Get the file epoch start time.
AbsoluteDate	ObservableSpecificSignalBias.getMaximumValidDateForObservation(ObservationType obs)	Get the maximum valid date for a given observation type.
AbsoluteDate	DifferentialSignalBias.getMaximumValidDateForObservationPair(ObservationType obs1, ObservationType obs2)	Get the maximum valid date for a given observation pair.
AbsoluteDate	ObservableSpecificSignalBias.getMinimumValidDateForObservation(ObservationType obs)	Get the minimum valid date for a given observation type.
AbsoluteDate	DifferentialSignalBias.getMinimumValidDateForObservationPair(ObservationType obs1, ObservationType obs2)	Get the minimum valid date for a given observation pair.
protected AbsoluteDate	ParseInfo.getStartDate()	Get start date.
AbsoluteDate	Station.getValidFrom()	Get start of validity.
AbsoluteDate	Station.getValidUntil()	Get end of validity.
protected AbsoluteDate	ParseInfo.stringEpochToAbsoluteDate(String stringDate, boolean isStart)	Transform a String epoch to an AbsoluteDate.

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

Modifier and Type	Method	Description
void	Station.addAntennaTypeValidAfter(String entry, AbsoluteDate earliestValidityDate)	Add a antenna type entry valid after a limit date. Using addAntennaTypeValidAfter(entry, t) will make entry valid in [t, +∞[ (note the closed bracket).
void	Station.addAntennaTypeValidBefore(String entry, AbsoluteDate latestValidityDate)	Add a antenna type entry valid before a limit date. Using addAntennaTypeValidBefore(entry, t) will make entry valid in ]-∞, t[ (note the open bracket).
void	DifferentialSignalBias.addBias(ObservationType obs1, ObservationType obs2, AbsoluteDate spanBegin, AbsoluteDate spanEnd, double biasValue)	Add a bias.
void	ObservableSpecificSignalBias.addBias(ObservationType obs, AbsoluteDate spanBegin, AbsoluteDate spanEnd, double biasValue)	Add a bias.
void	Station.addPsdCorrectionValidAfter(PsdCorrection entry, AbsoluteDate earliestValidityDate)	Add a Post-Seismic Deformation entry valid after a limit date. Using addPsdCorrectionValidAfter(entry, t) will make entry valid in [t, +∞[ (note the closed bracket).
void	Station.addStationEccentricitiesValidAfter(Vector3D entry, AbsoluteDate earliestValidityDate)	Add a station eccentricity vector entry valid after a limit date. Using addStationEccentricitiesValidAfter(entry, t) will make entry valid in [t, +∞[ (note the closed bracket).
void	Station.addStationEccentricitiesValidBefore(Vector3D entry, AbsoluteDate latestValidityDate)	Add a station eccentricity vector entry valid before a limit date. Using addStationEccentricitiesValidBefore(entry, t) will make entry valid in ]-∞, t[ (note the open bracket).
String	Station.getAntennaType(AbsoluteDate date)	Get the antenna type for the given epoch.
double	DifferentialSignalBias.getBias(ObservationType obs1, ObservationType obs2, AbsoluteDate date)	Get the value of the Differential Signal Bias for a given observation pair at a given date.
double	ObservableSpecificSignalBias.getBias(ObservationType obs, AbsoluteDate date)	Get the value of the Observable-specific Signal Bias for a given observation type at a given date.
Vector3D	Station.getEccentricities(AbsoluteDate date)	Get the station antenna eccentricities for the given epoch.
void	Station.setEpoch(AbsoluteDate epoch)	Set the coordinates reference epoch.
void	Station.setValidFrom(AbsoluteDate validFrom)	Set the start of validity.
void	Station.setValidUntil(AbsoluteDate validUntil)	Set the end of validity.

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

Constructor	Description
AbstractSinex(TimeScales timeScales, AbsoluteDate creationDate, AbsoluteDate startDate, AbsoluteDate endDate)	Simple constructor.
Sinex(TimeScales timeScales, AbsoluteDate creationDate, AbsoluteDate startDate, AbsoluteDate endDate, Map<String,Station> stations, Map<AbsoluteDate,SinexEopEntry> eop)	Simple constructor.
SinexBias(TimeScales timeScales, AbsoluteDate creationDate, AbsoluteDate startDate, AbsoluteDate endDate, BiasDescription description, Map<String,StationDifferentialSignalBias> stationsDsb, Map<SatInSystem,SatelliteDifferentialSignalBias> satellitesDsb, Map<String,StationObservableSpecificSignalBias> stationsOsb, Map<SatInSystem,SatelliteObservableSpecificSignalBias> satellitesOsb)	Simple constructor.
SinexEopEntry(AbsoluteDate epoch)	Constructor.

Uses of AbsoluteDate in org.orekit.files.sp3

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

Modifier and Type	Method	Description
AbsoluteDate	SP3Header.getEpoch()	Returns the start epoch of the orbit file.
AbsoluteDate	SP3Ephemeris.getStart()	Get the start date of the ephemeris.
AbsoluteDate	SP3Segment.getStart()	Get the start date of this ephemeris segment.
AbsoluteDate	SP3Ephemeris.getStop()	Get the end date of the ephemeris.
AbsoluteDate	SP3Segment.getStop()	Get the end date of this ephemeris segment.

Methods in org.orekit.files.sp3 with parameters of type AbsoluteDate

Modifier and Type	Method	Description
void	SP3Header.setEpoch(AbsoluteDate time)	Set the epoch of the SP3 file.

Constructors in org.orekit.files.sp3 with parameters of type AbsoluteDate

Constructor	Description
SP3Coordinate(AbsoluteDate date, Vector3D position, Vector3D positionAccuracy, Vector3D velocity, Vector3D velocityAccuracy, double clock, double clockAccuracy, double clockRate, double clockRateAccuracy, boolean clockEvent, boolean clockPrediction, boolean orbitManeuverEvent, boolean orbitPrediction)	Create a coordinate with position and velocity.

Uses of AbsoluteDate in org.orekit.files.stk

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

Modifier and Type	Method	Description
AbsoluteDate	STKEphemerisFile.STKEphemeris.getStart()
AbsoluteDate	STKEphemerisFile.STKEphemerisSegment.getStart()
AbsoluteDate	STKEphemerisFile.STKEphemeris.getStop()
AbsoluteDate	STKEphemerisFile.STKEphemerisSegment.getStop()

Uses of AbsoluteDate in org.orekit.forces

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

Modifier and Type	Method	Description
default void	ForceModel.init(SpacecraftState initialState, AbsoluteDate target)	Initialize the force model at the start of propagation.

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

Constructor	Description
SlewingPanel(Vector3D rotationAxis, double rotationRate, AbsoluteDate referenceDate, Vector3D referenceNormal, double area, double drag, double liftRatio, double absorption, double reflection)	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
void	TimeSpanDragForce.addDragSensitiveValidAfter(DragSensitive dragSensitive, AbsoluteDate earliestValidityDate)	Deprecated. Add a DragSensitive entry valid after a limit date. Using addDragSensitiveValidAfter(entry, t) will make entry valid in [t, +∞[ (note the closed bracket).
void	TimeSpanDragForce.addDragSensitiveValidBefore(DragSensitive dragSensitive, AbsoluteDate latestValidityDate)	Deprecated. Add a DragSensitive entry valid before a limit date. Using addDragSensitiveValidBefore(entry, t) will make entry valid in ]-∞, t[ (note the open bracket).
TimeSpanMap<DragSensitive>	TimeSpanDragForce.extractDragSensitiveRange(AbsoluteDate start, AbsoluteDate end)	Deprecated. Extract a range of the DragSensitive map.
double[]	TimeSpanDragForce.extractParameters(double[] parameters, AbsoluteDate date)	Deprecated. Extract the proper parameter drivers' values from the array in input of the acceleration method.
DragSensitive	TimeSpanDragForce.getDragSensitive(AbsoluteDate date)	Deprecated. Get the DragSensitive model valid at a date.
TimeSpanMap.Span<DragSensitive>	TimeSpanDragForce.getDragSensitiveSpan(AbsoluteDate date)	Deprecated. Get the DragSensitive TimeSpanMap.Span containing a specified date.
protected DerivativeStructure	AbstractDragForceModel.getDSDensityWrtState(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position)	Compute density and its derivatives.
protected DerivativeStructure	AbstractDragForceModel.getDSDensityWrtStateUsingFiniteDifferences(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position)	Compute density and its derivatives.
protected Gradient	AbstractDragForceModel.getGradientDensityWrtState(AbsoluteDate date, Frame frame, FieldVector3D<Gradient> position)	Compute density and its derivatives.
protected Gradient	AbstractDragForceModel.getGradientDensityWrtStateUsingFiniteDifferences(AbsoluteDate date, Frame frame, FieldVector3D<Gradient> position)	Compute density and its derivatives.

Uses of AbsoluteDate in org.orekit.forces.empirical

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

Modifier and Type	Method	Description
void	TimeSpanParametricAcceleration.addAccelerationModelValidAfter(AccelerationModel accelerationModel, AbsoluteDate earliestValidityDate)	Add a AccelerationModel entry valid after a limit date.
void	TimeSpanParametricAcceleration.addAccelerationModelValidBefore(AccelerationModel accelerationModel, AbsoluteDate latestValidityDate)	Add an AccelerationModel entry valid before a limit date.
TimeSpanMap<AccelerationModel>	TimeSpanParametricAcceleration.extractAccelerationModelRange(AbsoluteDate start, AbsoluteDate end)	Extract a range of the AccelerationModel map.
double[]	TimeSpanParametricAcceleration.extractParameters(double[] parameters, AbsoluteDate date)	Extract the proper parameter drivers' values from the array in input of the acceleration method.
AccelerationModel	TimeSpanParametricAcceleration.getAccelerationModel(AbsoluteDate date)	Get the AccelerationModel model valid at a date.
TimeSpanMap.Span<AccelerationModel>	TimeSpanParametricAcceleration.getAccelerationModelSpan(AbsoluteDate date)	Get the AccelerationModel TimeSpanMap.Span containing a specified date.
default void	AccelerationModel.init(SpacecraftState initialState, AbsoluteDate target)	Initialize the acceleration model at the start of the propagation.
void	HarmonicAccelerationModel.init(SpacecraftState initialState, AbsoluteDate target)	Initialize the acceleration model at the start of the propagation.
void	ParametricAcceleration.init(SpacecraftState initialState, AbsoluteDate target)	Initialize the force model at the start of propagation.
void	PolynomialAccelerationModel.init(SpacecraftState initialState, AbsoluteDate target)	Initialize the acceleration model at the start of the propagation.
void	TimeSpanParametricAcceleration.init(SpacecraftState initialState, AbsoluteDate target)	Initialize the force model at the start of propagation.

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

Constructor	Description
HarmonicAccelerationModel(String prefix, AbsoluteDate referenceDate, double fundamentalPeriod, int harmonicMultiplier)	Simple constructor.
PolynomialAccelerationModel(String prefix, AbsoluteDate referenceDate, int degree)	Simple constructor.

Uses of AbsoluteDate in org.orekit.forces.gravity

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

Modifier and Type	Method	Description
protected Vector3D	AbstractBodyAttraction.getBodyPosition(AbsoluteDate date, Frame frame)	Get the body's position vector.
protected TimeStampedPVCoordinates	AbstractBodyAttraction.getBodyPVCoordinates(AbsoluteDate date, Frame frame)	Get the body's position-velocity-acceleration vector.
double	J2OnlyPerturbation.getJ2(AbsoluteDate date)	Return J2 at requested date.
double	HolmesFeatherstoneAttractionModel.getMu(AbsoluteDate date)	Get the central attraction coefficient μ.
double	NewtonianAttraction.getMu(AbsoluteDate date)	Get the central attraction coefficient μ.
double[]	HolmesFeatherstoneAttractionModel.gradient(AbsoluteDate date, Vector3D position, double mu)	Compute the gradient of the non-central part of the gravity field.
double	HolmesFeatherstoneAttractionModel.nonCentralPart(AbsoluteDate date, Vector3D position, double mu)	Compute the non-central part of the gravity field.
double	HolmesFeatherstoneAttractionModel.value(AbsoluteDate date, 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.
protected AbsoluteDate	PotentialCoefficientsReader.toDate(DateComponents components)	Create a date from components.
protected AbsoluteDate	PotentialCoefficientsReader.toDate(DateComponents dc, TimeComponents tc)	Create a date from components.

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

Modifier and Type	Method	Description
static NormalizedSphericalHarmonicsProvider	GravityFieldFactory.getConstantNormalizedProvider(int degree, int order, AbsoluteDate freezingDate)	Get the constant gravity field coefficients provider from the first supported file.
NormalizedSphericalHarmonicsProvider	GravityFields.getConstantNormalizedProvider(int degree, int order, AbsoluteDate freezingDate)	Get a constant gravity field normalized coefficients provider frozen at a given epoch.
NormalizedSphericalHarmonicsProvider	LazyLoadedGravityFields.getConstantNormalizedProvider(int degree, int order, AbsoluteDate freezingDate)	Get a constant gravity field normalized coefficients provider frozen at a given epoch.
static UnnormalizedSphericalHarmonicsProvider	GravityFieldFactory.getConstantUnnormalizedProvider(int degree, int order, AbsoluteDate freezingDate)	Get the constant gravity field coefficients provider from the first supported file.
UnnormalizedSphericalHarmonicsProvider	GravityFields.getConstantUnnormalizedProvider(int degree, int order, AbsoluteDate freezingDate)	Get a constant gravity field unnormalized coefficients provider frozen at a given epoch.
UnnormalizedSphericalHarmonicsProvider	LazyLoadedGravityFields.getConstantUnnormalizedProvider(int degree, int order, AbsoluteDate freezingDate)	Get a constant gravity field unnormalized coefficients provider frozen at a given epoch.
default double	NormalizedSphericalHarmonicsProvider.getNormalizedC20(AbsoluteDate date)	Get the normalized coefficient of degree 2 and order 0 at a specific instance in time.
default double	UnnormalizedSphericalHarmonicsProvider.getUnnormalizedC20(AbsoluteDate date)	Get the un-normalized coefficient of degree 2 and order 0 at a specific instance in time.
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
Vector3D	ConstantThrustManeuver.getDirection(AbsoluteDate date)	Get the direction.
double	ConstantThrustManeuver.getFlowRate(AbsoluteDate date)	Get the flow rate at given date.
double	ConfigurableLowThrustManeuver.getIsp(AbsoluteDate date)	Get the specific impulse.
double	ConstantThrustManeuver.getIsp(AbsoluteDate date)	Get the specific impulse at given date.
double	ConfigurableLowThrustManeuver.getThrustMagnitude(AbsoluteDate date)	Get the thrust magnitude.
double	ConstantThrustManeuver.getThrustMagnitude(AbsoluteDate date)	Get the thrust magnitude.
Vector3D	ConstantThrustManeuver.getThrustVector(AbsoluteDate date)	Get the thrust vector (N) in S/C frame.
void	ImpulseManeuver.init(SpacecraftState s0, AbsoluteDate t)	Initialize event handler at the start of a propagation.
void	Maneuver.init(SpacecraftState initialState, AbsoluteDate target)	Initialize the force model at the start of propagation.
boolean	ConstantThrustManeuver.isFiring(AbsoluteDate date)	Check if maneuvering is on.

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

Constructor	Description
ConstantThrustManeuver(AbsoluteDate date, double duration, double thrust, double isp, Vector3D direction)	Simple constructor for a constant direction and constant thrust.
ConstantThrustManeuver(AbsoluteDate date, double duration, double thrust, double isp, Vector3D direction, String name)	Simple constructor for a constant direction and constant thrust.
ConstantThrustManeuver(AbsoluteDate date, double duration, double thrust, double isp, AttitudeProvider attitudeOverride, Vector3D direction)	Simple constructor for a constant direction and constant thrust.
ConstantThrustManeuver(AbsoluteDate date, double duration, double thrust, double isp, AttitudeProvider attitudeOverride, Vector3D direction, String name)	Simple constructor for a constant direction and constant thrust.
ConstantThrustManeuver(AbsoluteDate date, double duration, double thrust, double isp, AttitudeProvider attitudeOverride, Vector3D direction, Control3DVectorCostType control3DVectorCostType, String name)	Simple constructor for a constant direction and constant thrust.
ConstantThrustManeuver(AbsoluteDate date, double duration, AttitudeProvider attitudeOverride, AbstractConstantThrustPropulsionModel constantThrustPropulsionModel)	Simple constructor for a constant direction and constant thrust.

Uses of AbsoluteDate in org.orekit.forces.maneuvers.jacobians

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

Modifier and Type	Method	Description
void	MassDepletionDelay.init(SpacecraftState initialState, AbsoluteDate target)	Initialize the generator at the start of propagation.
void	TriggerDate.init(SpacecraftState initialState, AbsoluteDate target)	Initialize the additional state provider at the start of propagation.

Uses of AbsoluteDate in org.orekit.forces.maneuvers.propulsion

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

Modifier and Type	Method	Description
Vector3D	ConstantThrustDirectionProvider.computeThrustDirection(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Vector3D	ThrustDirectionProvider.computeThrustDirection(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the thrust direction corresponding to an orbital state.
Attitude	ThrustDirectionAndAttitudeProvider.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.
protected Attitude	ThrustDirectionAndAttitudeProvider.getAttitudeFromFrame(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude for DIRECTION_IN_FRAME or DIRECTION_IN_LOF types.
Vector3D	AbstractConstantThrustPropulsionModel.getDirection(AbsoluteDate date)	Get the thrust direction in S/C frame.
abstract double	AbstractConstantThrustPropulsionModel.getFlowRate(AbsoluteDate date)	Get the flow rate (kg/s).
double	BasicConstantThrustPropulsionModel.getFlowRate(AbsoluteDate date)	Get the flow rate (kg/s).
double	ScaledConstantThrustPropulsionModel.getFlowRate(AbsoluteDate date)	Get the flow rate (kg/s).
double	AbstractConstantThrustPropulsionModel.getIsp(AbsoluteDate date)	Get the specific impulse at given date.
double	AbstractConstantThrustPropulsionModel.getThrustMagnitude(AbsoluteDate date)	Get the thrust magnitude (N) at given date.
abstract Vector3D	AbstractConstantThrustPropulsionModel.getThrustVector(AbsoluteDate date)	Get the thrust vector in spacecraft frame (N).
Vector3D	BasicConstantThrustPropulsionModel.getThrustVector(AbsoluteDate date)	Get the thrust vector in spacecraft frame (N).
Vector3D	PolynomialThrustSegment.getThrustVector(AbsoluteDate date)	Get thrust vector at a specified date.
Vector3D	ScaledConstantThrustPropulsionModel.getThrustVector(AbsoluteDate date)	Get the thrust vector in spacecraft frame (N).
default void	PropulsionModel.init(SpacecraftState initialState, AbsoluteDate target)	Initialization method.

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

Constructor	Description
PolynomialThrustSegment(AbsoluteDate referenceDate, PolynomialFunction xThrust, PolynomialFunction yThrust, PolynomialFunction zThrust)	Simple constructor.

Uses of AbsoluteDate in org.orekit.forces.maneuvers.trigger

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

Modifier and Type	Method	Description
AbsoluteDate	DateBasedManeuverTriggers.getEndDate()	Get the end date.
AbsoluteDate	DateBasedManeuverTriggers.getStartDate()	Get the start date.

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

Modifier and Type	Method	Description
void	AbstractManeuverTriggers.init(SpacecraftState initialState, AbsoluteDate target)	Initialization method called at propagation start.
void	IntervalEventTrigger.init(SpacecraftState initialState, AbsoluteDate target)	Initialization method called at propagation start.
default void	ManeuverTriggers.init(SpacecraftState initialState, AbsoluteDate target)	Initialization method called at propagation start.
default void	ManeuverTriggersResetter.init(SpacecraftState initialState, AbsoluteDate target)	Initialization method called at propagation start.
void	StartStopEventsTrigger.init(SpacecraftState initialState, AbsoluteDate target)	Initialization method called at propagation start.
protected void	AbstractManeuverTriggers.initializeResetters(SpacecraftState initialState, AbsoluteDate target)	Initialize resetters.
boolean	AbstractManeuverTriggers.isFiring(AbsoluteDate date, double[] parameters)	Find out if the maneuver is firing or not.
boolean	ManeuverTriggers.isFiring(AbsoluteDate date, double[] parameters)	Find out if the maneuver is firing or not.

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

Constructor	Description
DateBasedManeuverTriggers(String name, AbsoluteDate date, double duration)	Simple constructor.
DateBasedManeuverTriggers(AbsoluteDate date, double duration)	Simple constructor.

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	KnockeRediffusedForceModel.computeAlbedo(AbsoluteDate date, double phi)	Compute Earth albedo.
double	KnockeRediffusedForceModel.computeEmissivity(AbsoluteDate date, double phi)	Compute Earth emisivity.
protected Vector3D	AbstractLightFluxModel.getOccultedBodyPosition(AbsoluteDate date, Frame frame)	Method computing the occulted body's position at a given date and frame.
void	ConicallyShadowedLightFluxModel.init(SpacecraftState initialState, AbsoluteDate targetDate)	Perform initialization steps before starting propagation.
default void	LightFluxModel.init(SpacecraftState initialState, AbsoluteDate targetDate)	Perform initialization steps before starting propagation.
void	RadiationPressureModel.init(SpacecraftState initialState, AbsoluteDate target)	Initialize the force model at the start of propagation.

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
static KinematicTransform	KinematicTransform.compose(AbsoluteDate date, KinematicTransform first, KinematicTransform second)	Build a transform by combining two existing ones.
static StaticTransform	StaticTransform.compose(AbsoluteDate date, StaticTransform first, StaticTransform second)	Build a transform by combining two existing ones.
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(Vector3D extPoint, Frame frame, AbsoluteDate date)	Get the azimuth of a point with regards to the topocentric frame center point.
double	TopocentricFrame.getElevation(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.
KinematicTransform	GTODProvider.getKinematicTransform(AbsoluteDate date)	Get a transform for position and velocity, not acceleration.
KinematicTransform	ITRFVersion.Converter.getKinematicTransform(AbsoluteDate date)	Get a transform for position and velocity, not acceleration.
default KinematicTransform	TransformProvider.getKinematicTransform(AbsoluteDate date)	Get a transform for position and velocity, not acceleration.
KinematicTransform	Frame.getKinematicTransformTo(Frame destination, AbsoluteDate date)	Get the kinematic portion of the transform from the instance to another frame.
double	EOPHistory.getLOD(AbsoluteDate date)	Get the LoD (Length of Day) value.
protected Stream<EOPEntry>	EOPHistory.getNeighbors(AbsoluteDate central, int n)	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.
Vector3D	TopocentricFrame.getPosition(AbsoluteDate date, Frame frame)	Get the position of the body in the selected frame.
TimeStampedPVCoordinates	TopocentricFrame.getPVCoordinates(AbsoluteDate date, Frame frame)	Get the PVCoordinates of the topocentric frame origin in the selected frame.
double	TopocentricFrame.getRange(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.
StaticTransform	GTODProvider.getStaticTransform(AbsoluteDate date)	Get a transform for only rotations and translations on the specified date.
StaticTransform	HelmertTransformation.getStaticTransform(AbsoluteDate date)	Get a transform for only rotations and translations on the specified date.
StaticTransform	ITRFVersion.Converter.getStaticTransform(AbsoluteDate date)	Get a transform for only rotations and translations on the specified date.
StaticTransform	L1TransformProvider.getStaticTransform(AbsoluteDate date)	Get a transform for only rotations and translations on the specified date.
StaticTransform	ShiftingTransformProvider.getStaticTransform(AbsoluteDate date)	Get a transform for only rotations and translations on the specified date.
default StaticTransform	TransformProvider.getStaticTransform(AbsoluteDate date)	Get a transform for only rotations and translations on the specified date.
StaticTransform	Frame.getStaticTransformTo(Frame destination, AbsoluteDate date)	Get the static portion of the transform from the instance to another frame.
TrackingCoordinates	TopocentricFrame.getTrackingCoordinates(Vector3D extPoint, Frame frame, AbsoluteDate date)	Get the tracking coordinates of a point with regards to the local 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)	Interpolate a transform from a sample set of existing transforms.
static Transform	Transform.interpolate(AbsoluteDate date, CartesianDerivativesFilter cFilter, AngularDerivativesFilter aFilter, Collection<Transform> sample)	Interpolate a transform from a sample set of existing transforms.
static KinematicTransform	KinematicTransform.of(AbsoluteDate date, Rotation rotation, Vector3D rotationRate)	Create a new kinematic transform from a rotation and zero, constant translation.
static KinematicTransform	KinematicTransform.of(AbsoluteDate date, PVCoordinates pvCoordinates)	Create a new kinematic transform from a translation and its rate.
static KinematicTransform	KinematicTransform.of(AbsoluteDate date, PVCoordinates pvCoordinates, Rotation rotation, Vector3D rotationRate)	Create a new kinematic transform from a translation and rotation.
static StaticTransform	StaticTransform.of(AbsoluteDate date, Rotation rotation)	Create a new static transform from a rotation and zero translation.
static StaticTransform	StaticTransform.of(AbsoluteDate date, Vector3D translation)	Create a new static transform from a translation and rotation.
static StaticTransform	StaticTransform.of(AbsoluteDate date, Vector3D translation, Rotation rotation)	Create a new static transform from a translation and rotation.
Rotation	LocalMagneticFieldFrame.rotationFromInertial(AbsoluteDate date, PVCoordinates pv)	Get the rotation from inertial frame to local orbital frame.
Rotation	LOF.rotationFromInertial(AbsoluteDate date, PVCoordinates pv)	Get the rotation from inertial frame to local orbital frame.
Rotation	LOFType.rotationFromInertial(AbsoluteDate date, PVCoordinates pv)	Get the rotation from inertial frame to local orbital frame.
default Rotation	LOF.rotationFromLOF(LOF fromLOF, AbsoluteDate date, PVCoordinates pv)	Get the rotation from input local orbital frame to the instance.
static Rotation	LOF.rotationFromLOFInToLOFOut(LOF in, LOF out, AbsoluteDate date, PVCoordinates pv)	Get the rotation from input to output local orbital frame.
default Transform	LOF.transformFromInertial(AbsoluteDate date, PVCoordinates pv)	Get the transform from an inertial frame defining position-velocity and the local orbital frame.
default Transform	LOF.transformFromLOF(LOF fromLOF, AbsoluteDate date, PVCoordinates pv)	Get the rotation from input local orbital frame to the instance.
static Transform	LOF.transformFromLOFInToLOFOut(LOF in, LOF out, AbsoluteDate date, PVCoordinates pv)	Get the transform from input to output 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
EOPEntry(int mjd, double dt, double lod, double x, double y, double xRate, double yRate, double ddPsi, double ddEps, double dx, double dy, ITRFVersion itrfType, AbsoluteDate date)	Simple constructor.
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.
Transform(AbsoluteDate date, Rotation rotation)	Build a rotation transform.
Transform(AbsoluteDate date, Rotation rotation, Vector3D rotationRate)	Build a rotation transform.
Transform(AbsoluteDate date, Rotation rotation, Vector3D rotationRate, Vector3D rotationAcceleration)	Build a rotation transform.
Transform(AbsoluteDate date, Vector3D translation)	Build a translation transform.
Transform(AbsoluteDate date, Vector3D translation, Rotation rotation)	Build a combined translation and rotation transform.
Transform(AbsoluteDate date, Vector3D translation, Vector3D velocity)	Build a translation transform, with its first time derivative.
Transform(AbsoluteDate date, Vector3D translation, Vector3D velocity, 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.
Transform(AbsoluteDate date, PVCoordinates cartesian, AngularCoordinates angular)	Build a transform from its primitive operations.

Uses of AbsoluteDate in org.orekit.frames.encounter

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

Modifier and Type	Method	Description
default Rotation	EncounterLOF.rotationFromInertial(AbsoluteDate date, PVCoordinates pv)	Get the rotation from inertial frame to local orbital frame.

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.

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.

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.getValidUntil()	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, ExtendedPositionProvider 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<RadioWave,FrequencyPattern> patterns, SatInSystem satInSystem, 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	GNSSAttitudeProvider.validityEnd()	Get end of validity for this provider.
AbsoluteDate	GNSSAttitudeProvider.validityStart()	Get start of validity for this provider.

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

Constructor	Description
BeidouGeo(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPositionProvider sun, Frame inertialFrame)	Simple constructor.
BeidouIGSO(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPositionProvider sun, Frame inertialFrame)	Simple constructor.
BeidouMeo(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPositionProvider sun, Frame inertialFrame)	Simple constructor.
Galileo(double yawRate, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPositionProvider sun, Frame inertialFrame)	Simple constructor.
GenericGNSS(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPositionProvider sun, Frame inertialFrame)	Simple constructor.
Glonass(double yawRate, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPositionProvider sun, Frame inertialFrame)	Simple constructor.
GPSBlockIIA(double yawRate, double yawBias, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPositionProvider sun, Frame inertialFrame)	Simple constructor.
GPSBlockIIF(double yawRate, double yawBias, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPositionProvider sun, Frame inertialFrame)	Simple constructor.
GPSBlockIIR(double yawRate, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPositionProvider 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
GeodeticPoint	Geoid.getIntersectionPoint(Line lineInFrame, 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.
Vector3D	Geoid.projectToGround(Vector3D point, AbsoluteDate date, Frame frame)
GeodeticPoint	Geoid.transform(Vector3D point, Frame frame, AbsoluteDate date)	Transform a Cartesian point to a surface-relative point.

Uses of AbsoluteDate in org.orekit.models.earth.atmosphere

Methods in org.orekit.models.earth.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.models.earth.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, Vector3D position, Frame frame)	Get the local density.
double	DTM2000.getDensity(AbsoluteDate date, Vector3D position, Frame frame)	Get the local density.
double	HarrisPriester.getDensity(AbsoluteDate date, Vector3D position, Frame frame)	Get the local density at some position.
double	JB2008.getDensity(AbsoluteDate date, Vector3D position, Frame frame)	Get the local density.
double	NRLMSISE00.getDensity(AbsoluteDate date, Vector3D position, Frame frame)	Get the local density.
double	SimpleExponentialAtmosphere.getDensity(AbsoluteDate date, 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.
protected Vector3D	AbstractSunInfluencedAtmosphere.getSunPosition(AbsoluteDate date, Frame frame)	Method returning the Sun's position vector.
double	DTM2000InputParameters.getThreeHourlyKP(AbsoluteDate date)	Get the value of the 3 hours geomagnetic index.
default Vector3D	Atmosphere.getVelocity(AbsoluteDate date, 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.models.earth.atmosphere.data

Methods in org.orekit.models.earth.atmosphere.data that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	AbstractSolarActivityData.LocalSolarActivity.getDate()
AbsoluteDate	AbstractSolarActivityDataLoader.LineParameters.getDate()
AbsoluteDate	DtcDataLoader.LineParameters.getDate()
AbsoluteDate	SOLFSMYDataLoader.LineParameters.getDate()
AbsoluteDate	CssiSpaceWeatherDataLoader.getLastDailyPredictedDate()	Gets the day (at data start) of the last daily data entry.
AbsoluteDate	CssiSpaceWeatherDataLoader.getLastObservedDate()	Gets the day (at data start) of the last observed data entry.
AbsoluteDate	AbstractSolarActivityData.getMaxDate()	Gets the available data range maximum date.
AbsoluteDate	AbstractSolarActivityDataLoader.getMaxDate()	Gets the available data range maximum date.
AbsoluteDate	DtcDataLoader.getMaxDate()	Gets the available data range maximum date.
AbsoluteDate	JB2008SpaceEnvironmentData.getMaxDate()	Gets the available data range maximum date.
AbsoluteDate	SOLFSMYDataLoader.getMaxDate()	Gets the available data range maximum date.
AbsoluteDate	AbstractSolarActivityData.getMinDate()	Gets the available data range minimum date.
AbsoluteDate	AbstractSolarActivityDataLoader.getMinDate()	Gets the available data range minimum date.
AbsoluteDate	DtcDataLoader.getMinDate()	Gets the available data range minimum date.
AbsoluteDate	JB2008SpaceEnvironmentData.getMinDate()	Gets the available data range minimum date.
AbsoluteDate	SOLFSMYDataLoader.getMinDate()	Gets the available data range minimum date.

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

Modifier and Type	Method	Description
List<L>	AbstractSolarActivityData.SolarActivityGenerator.generate(AbsoluteDate existingDate, AbsoluteDate date)	Generate a chronologically sorted list of entries to be cached.
List<L>	AbstractSolarActivityData.SolarActivityGenerator.generateDataFromEarliestToLatestDates(AbsoluteDate earliest, AbsoluteDate latest)	Generate a list of parameters between earliest and latest dates.
double	CssiSpaceWeatherData.get24HoursKp(AbsoluteDate date)	Get the last 24H mean geomagnetic index.
double	MarshallSolarActivityFutureEstimation.get24HoursKp(AbsoluteDate date)	The Kp index is derived from the Ap index.
double[]	CssiSpaceWeatherData.getAp(AbsoluteDate date)	Get the Ap geomagnetic indices.
double[]	MarshallSolarActivityFutureEstimation.getAp(AbsoluteDate date)	Get the Ap geomagnetic indices.
double	CssiSpaceWeatherData.getAverageFlux(AbsoluteDate date)	Get the value of the 81 day average of F10.7 solar flux centered on current day.
double	MarshallSolarActivityFutureEstimation.getAverageFlux(AbsoluteDate date)
double	CssiSpaceWeatherData.getDailyFlux(AbsoluteDate date)	Get the value of the daily F10.7 solar flux for previous day.
double	MarshallSolarActivityFutureEstimation.getDailyFlux(AbsoluteDate date)	Get the value of the daily F10.7 solar flux for previous day.
double	JB2008SpaceEnvironmentData.getDSTDTC(AbsoluteDate date)	Get the temperature change computed from Dst index.
double	JB2008SpaceEnvironmentData.getF10(AbsoluteDate date)	Get the value of the instantaneous solar flux index (1e-22*Watt/(m²*Hertz)).
double	JB2008SpaceEnvironmentData.getF10B(AbsoluteDate date)	Get the value of the mean solar flux.
DateComponents	MarshallSolarActivityFutureEstimation.getFileDate(AbsoluteDate date)	Get the date of the file from which data at the specified date comes from.
double	CssiSpaceWeatherData.getInstantFlux(AbsoluteDate date)	Get the value of the instantaneous solar flux.
double	MarshallSolarActivityFutureEstimation.getInstantFlux(AbsoluteDate date)	Get the value of the instantaneous solar flux.
protected double	AbstractSolarActivityData.getLinearInterpolation(AbsoluteDate date, Function<L,Double> solarActivityToDoubleMapper)	Performs a linear interpolation between two values The weights are computed from the time delta between previous date, current date, next date.
double	CssiSpaceWeatherData.getMeanFlux(AbsoluteDate date)	Get the value of the mean solar flux.
double	MarshallSolarActivityFutureEstimation.getMeanFlux(AbsoluteDate date)	Get the value of the mean solar flux.
double	JB2008SpaceEnvironmentData.getS10(AbsoluteDate date)	Get the EUV index (26-34 nm) scaled to F10.
double	JB2008SpaceEnvironmentData.getS10B(AbsoluteDate date)	Get the EUV 81-day averaged centered index.
double	CssiSpaceWeatherData.getThreeHourlyKP(AbsoluteDate date)	Get the value of the 3 hours geomagnetic index.
double	MarshallSolarActivityFutureEstimation.getThreeHourlyKP(AbsoluteDate date)	Get the value of the 3 hours geomagnetic index.
double	JB2008SpaceEnvironmentData.getXM10(AbsoluteDate date)	Get the MG2 index scaled to F10.
double	JB2008SpaceEnvironmentData.getXM10B(AbsoluteDate date)	Get the MG2 81-day average centered index.
double	JB2008SpaceEnvironmentData.getY10(AbsoluteDate date)	Get the Solar X-Ray & Lya index scaled to F10.
double	JB2008SpaceEnvironmentData.getY10B(AbsoluteDate date)	Get the Solar X-Ray & Lya 81-day ave.
void	AbstractSolarActivityDataLoader.setMaxDate(AbsoluteDate date)	Set the available data range maximum date.
void	AbstractSolarActivityDataLoader.setMinDate(AbsoluteDate date)	Set the available data range minimum date.

Constructors in org.orekit.models.earth.atmosphere.data with parameters of type AbsoluteDate

Constructor	Description
LineParameters(AbsoluteDate date)	Constructor.
LineParameters(AbsoluteDate date, double[] threeHourlyKp, double kpSum, double[] threeHourlyAp, double apAvg, double f107Adj, int fluxQualifier, double ctr81Adj, double lst81Adj, double f107Obs, double ctr81Obs, double lst81Obs)	Constructor.
LineParameters(AbsoluteDate date, double dtc)	Constructor.
LineParameters(AbsoluteDate date, double f10, double f10b, double s10, double s10b, double xm10, double xm10b, double y10, double y10b)	Constructor.
LocalSolarActivity(AbsoluteDate date)	Constructor.

Uses of AbsoluteDate in org.orekit.models.earth.displacement

Methods in org.orekit.models.earth.displacement that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	PsdCorrection.getEarthquakeDate()	Get earthquake date.

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

Modifier and Type	Method	Description
Vector3D	PsdCorrection.displacement(AbsoluteDate date, GeodeticPoint base)	Compute displacement.

Constructors in org.orekit.models.earth.displacement with parameters of type AbsoluteDate

Constructor	Description
PsdCorrection(PsdCorrection.Axis axis, PsdCorrection.TimeEvolution evolution, AbsoluteDate earthquakeDate, double amplitude, double relaxationTime)	Simple constructor.
TectonicsDisplacement(AbsoluteDate epoch, Vector3D velocity)	Simple constructor.

Uses of AbsoluteDate in org.orekit.models.earth.ionosphere

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

Modifier and Type	Method	Description
double	KlobucharIonoModel.pathDelay(AbsoluteDate date, GeodeticPoint geo, double elevation, double azimuth, double frequency, double[] parameters)	Calculates the ionospheric path delay for the signal path from a ground station to a satellite.
double	NeQuickModel.stec(AbsoluteDate date, GeodeticPoint recP, GeodeticPoint satP)	This method allows the computation of the Stant Total Electron Content (STEC).

Uses of AbsoluteDate in org.orekit.models.earth.troposphere

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

Modifier and Type	Method	Description
void	TimeSpanEstimatedModel.addTroposphericModelValidAfter(EstimatedModel model, AbsoluteDate earliestValidityDate)	Add a EstimatedTroposphericModel entry valid after a limit date. Using addTroposphericModelValidAfter(entry, t) will make entry valid in [t, +∞[ (note the closed bracket).
void	TimeSpanEstimatedModel.addTroposphericModelValidBefore(EstimatedModel model, AbsoluteDate latestValidityDate)	Add an EstimatedTroposphericModel entry valid before a limit date. Using addTroposphericValidBefore(entry, t) will make entry valid in ]-∞, t[ (note the open bracket).
double[]	MendesPavlisModel.computeZenithDelay(GeodeticPoint point, AbsoluteDate date)	This method allows the computation of the zenith hydrostatic and zenith wet delay.
double[]	TimeSpanEstimatedModel.extractParameters(double[] parameters, AbsoluteDate date)	Extract the proper parameter drivers' values from the array in input of the pathDelay method.
ViennaACoefficients	ConstantViennaAProvider.getA(GeodeticPoint location, AbsoluteDate date)	Get coefficients array for VMF mapping function.
ViennaACoefficients	ViennaAProvider.getA(GeodeticPoint location, AbsoluteDate date)	Get coefficients array for VMF mapping function.
protected int	AbstractVienna.getDayOfYear(AbsoluteDate date)	Get day of year.
AzimuthalGradientCoefficients	AzimuthalGradientProvider.getGradientCoefficients(GeodeticPoint location, AbsoluteDate date)	Get azimuthal asymmetry gradients.
AzimuthalGradientCoefficients	ConstantAzimuthalGradientProvider.getGradientCoefficients(GeodeticPoint location, AbsoluteDate date)	Get azimuthal asymmetry gradients.
EstimatedModel	TimeSpanEstimatedModel.getTroposphericModel(AbsoluteDate date)	Get the EstimatedModel model valid at a date.
double[]	AbstractChaoMappingFunction.mappingFactors(TrackingCoordinates trackingCoordinates, GeodeticPoint point, PressureTemperatureHumidity weather, AbsoluteDate date)	This method allows the computation of the hydrostatic and wet mapping functions.
double[]	DummyMappingFunction.mappingFactors(TrackingCoordinates trackingCoordinates, GeodeticPoint point, PressureTemperatureHumidity weather, AbsoluteDate date)	This method allows the computation of the hydrostatic and wet mapping functions.
double[]	GlobalMappingFunctionModel.mappingFactors(TrackingCoordinates trackingCoordinates, GeodeticPoint point, PressureTemperatureHumidity weather, AbsoluteDate date)	This method allows the computation of the hydrostatic and wet mapping functions.
double[]	MendesPavlisModel.mappingFactors(TrackingCoordinates trackingCoordinates, GeodeticPoint point, PressureTemperatureHumidity weather, AbsoluteDate date)	With the Mendes Pavlis tropospheric model, the mapping function is not split into hydrostatic and wet component.
double[]	NiellMappingFunctionModel.mappingFactors(TrackingCoordinates trackingCoordinates, GeodeticPoint point, PressureTemperatureHumidity weather, AbsoluteDate date)	This method allows the computation of the hydrostatic and wet mapping functions.
double[]	TroposphereMappingFunction.mappingFactors(TrackingCoordinates trackingCoordinates, GeodeticPoint point, PressureTemperatureHumidity weather, AbsoluteDate date)	This method allows the computation of the hydrostatic and wet mapping functions.
double[]	ViennaOne.mappingFactors(TrackingCoordinates trackingCoordinates, GeodeticPoint point, PressureTemperatureHumidity weather, AbsoluteDate date)	This method allows the computation of the hydrostatic and wet mapping functions.
double[]	ViennaThree.mappingFactors(TrackingCoordinates trackingCoordinates, GeodeticPoint point, PressureTemperatureHumidity weather, AbsoluteDate date)	This method allows the computation of the hydrostatic and wet mapping functions.
TroposphericDelay	AbstractVienna.pathDelay(TrackingCoordinates trackingCoordinates, GeodeticPoint point, PressureTemperatureHumidity weather, double[] parameters, AbsoluteDate date)	Calculates the tropospheric path delay for the signal path from a ground station to a satellite.
TroposphericDelay	AskneNordiusModel.pathDelay(TrackingCoordinates trackingCoordinates, GeodeticPoint point, PressureTemperatureHumidity weather, double[] parameters, AbsoluteDate date)	Calculates the tropospheric path delay for the signal path from a ground station to a satellite.
TroposphericDelay	CanonicalSaastamoinenModel.pathDelay(TrackingCoordinates trackingCoordinates, GeodeticPoint point, PressureTemperatureHumidity weather, double[] parameters, AbsoluteDate date)	Calculates the tropospheric path delay for the signal path from a ground station to a satellite.
TroposphericDelay	ConstantTroposphericModel.pathDelay(TrackingCoordinates trackingCoordinates, GeodeticPoint point, PressureTemperatureHumidity weather, double[] parameters, AbsoluteDate date)	Calculates the tropospheric path delay for the signal path from a ground station to a satellite.
TroposphericDelay	EstimatedModel.pathDelay(TrackingCoordinates trackingCoordinates, GeodeticPoint point, PressureTemperatureHumidity weather, double[] parameters, AbsoluteDate date)	Calculates the tropospheric path delay for the signal path from a ground station to a satellite.
TroposphericDelay	FixedTroposphericDelay.pathDelay(TrackingCoordinates trackingCoordinates, GeodeticPoint point, PressureTemperatureHumidity weather, double[] parameters, AbsoluteDate date)	Calculates the tropospheric path delay for the signal path from a ground station to a satellite.
TroposphericDelay	MariniMurray.pathDelay(TrackingCoordinates trackingCoordinates, GeodeticPoint point, PressureTemperatureHumidity weather, double[] parameters, AbsoluteDate date)	Calculates the tropospheric path delay for the signal path from a ground station to a satellite.
TroposphericDelay	MendesPavlisModel.pathDelay(TrackingCoordinates trackingCoordinates, GeodeticPoint point, PressureTemperatureHumidity weather, double[] parameters, AbsoluteDate date)	Calculates the tropospheric path delay for the signal path from a ground station to a satellite.
TroposphericDelay	ModifiedHopfieldModel.pathDelay(TrackingCoordinates trackingCoordinates, GeodeticPoint point, PressureTemperatureHumidity weather, double[] parameters, AbsoluteDate date)	Calculates the tropospheric path delay for the signal path from a ground station to a satellite.
TroposphericDelay	ModifiedSaastamoinenModel.pathDelay(TrackingCoordinates trackingCoordinates, GeodeticPoint point, PressureTemperatureHumidity weather, double[] parameters, AbsoluteDate date)	Calculates the tropospheric path delay for the signal path from a ground station to a satellite.
TroposphericDelay	TimeSpanEstimatedModel.pathDelay(TrackingCoordinates trackingCoordinates, GeodeticPoint point, PressureTemperatureHumidity weather, double[] parameters, AbsoluteDate date)	Calculates the tropospheric path delay for the signal path from a ground station to a satellite.
TroposphericDelay	TroposphericModel.pathDelay(TrackingCoordinates trackingCoordinates, GeodeticPoint point, PressureTemperatureHumidity weather, double[] parameters, AbsoluteDate date)	Calculates the tropospheric path delay for the signal path from a ground station to a satellite.

Uses of AbsoluteDate in org.orekit.models.earth.weather

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

Modifier and Type	Method	Description
protected abstract double	AbstractGlobalPressureTemperature.deltaRef(AbsoluteDate date)	Get duration since reference date.
protected double	GlobalPressureTemperature2.deltaRef(AbsoluteDate date)	Get duration since reference date.
protected double	GlobalPressureTemperature2w.deltaRef(AbsoluteDate date)	Get duration since reference date.
protected double	GlobalPressureTemperature3.deltaRef(AbsoluteDate date)	Get duration since reference date.
ViennaACoefficients	AbstractGlobalPressureTemperature.getA(GeodeticPoint location, AbsoluteDate date)	Get coefficients array for VMF mapping function.
AzimuthalGradientCoefficients	AbstractGlobalPressureTemperature.getGradientCoefficients(GeodeticPoint location, AbsoluteDate date)	Get azimuthal asymmetry gradients.
PressureTemperatureHumidity	AbstractGlobalPressureTemperature.getWeatherParameters(GeodeticPoint location, AbsoluteDate date)	Provide weather parameters.
PressureTemperatureHumidity	ConstantPressureTemperatureHumidityProvider.getWeatherParameters(GeodeticPoint location, AbsoluteDate date)	Provide weather parameters.
PressureTemperature	GlobalPressureTemperature.getWeatherParameters(GeodeticPoint location, AbsoluteDate date)	Provide weather parameters.
PressureTemperatureHumidity	PressureTemperatureHumidityProvider.getWeatherParameters(GeodeticPoint location, AbsoluteDate date)	Provide weather parameters.

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
Vector3D	Orbit.getPosition(AbsoluteDate otherDate, Frame otherFrame)	Get the position of the body in the selected frame.
TimeStampedPVCoordinates	Orbit.getPVCoordinates(AbsoluteDate otherDate, Frame otherFrame)	Get the PVCoordinates of the body in the selected frame.
Orbit	AbstractOrbitInterpolator.interpolate(AbsoluteDate interpolationDate, Collection<Orbit> sample)	Get an interpolated instance.
abstract Orbit	OrbitType.mapArrayToOrbit(double[] array, double[] arrayDot, PositionAngleType 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, PositionAngleType type, Frame frame, AbsoluteDate date, double mu)	Creates a new instance with derivatives and with cached position angle same as value inputted.
CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, double aDot, double exDot, double eyDot, double iDot, double raanDot, double alphaDot, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, AbsoluteDate date, double mu)	Creates a new instance.
CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, PositionAngleType type, Frame frame, AbsoluteDate date, double mu)	Creates a new instance without derivatives and with cached position angle same as value inputted.
CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, AbsoluteDate date, double mu)	Creates a new instance.
CircularOrbit(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, PositionAngleType type, Frame frame, AbsoluteDate date, double mu)	Creates a new instance with derivatives and with cached position angle same as value inputted.
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, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, AbsoluteDate date, double mu)	Creates a new instance.
EquinoctialOrbit(double a, double ex, double ey, double hx, double hy, double l, PositionAngleType type, Frame frame, AbsoluteDate date, double mu)	Creates a new instance without derivatives and with cached position angle same as value inputted.
EquinoctialOrbit(double a, double ex, double ey, double hx, double hy, double l, PositionAngleType type, PositionAngleType cachedPositionAngleType, 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, PositionAngleType type, Frame frame, AbsoluteDate date, double mu)	Creates a new instance with cached position angle same as value inputted.
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, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, AbsoluteDate date, double mu)	Creates a new instance.
KeplerianOrbit(double a, double e, double i, double pa, double raan, double anomaly, PositionAngleType type, Frame frame, AbsoluteDate date, double mu)	Creates a new instance without derivatives and with cached position angle same as value inputted.
KeplerianOrbit(double a, double e, double i, double pa, double raan, double anomaly, PositionAngleType type, PositionAngleType cachedPositionAngleType, 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	StateCovariance.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
default Vector3D	Propagator.getPosition(AbsoluteDate date, Frame frame)	Get the position of the body in the selected frame.
default TimeStampedPVCoordinates	Propagator.getPVCoordinates(AbsoluteDate date, Frame frame)	Get the PVCoordinates of the body in the selected frame.
default void	AdditionalStateProvider.init(SpacecraftState initialState, AbsoluteDate target)	Initialize the additional state provider at the start of propagation.
void	StateCovarianceMatrixProvider.init(SpacecraftState initialState, AbsoluteDate target)	Initialize the additional state provider at the start of propagation.
protected void	AbstractPropagator.initializeAdditionalStates(AbsoluteDate target)	Initialize the additional state providers at the start of propagation.
SpacecraftState	SpacecraftStateInterpolator.interpolate(AbsoluteDate interpolationDate, Collection<SpacecraftState> sample)	Get an interpolated instance.
protected Orbit	AbstractStateCovarianceInterpolator.interpolateOrbit(AbsoluteDate interpolationDate, List<TimeStampedPair<Orbit,StateCovariance>> neighborList)	Interpolate orbit at given interpolation date.
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.

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

Constructor	Description
StateCovariance(RealMatrix orbitalCovariance, AbsoluteDate epoch, Frame covarianceFrame, OrbitType orbitType, PositionAngleType angleType)	Constructor.
StateCovariance(RealMatrix orbitalCovariance, AbsoluteDate epoch, LOF lof)	Constructor.

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)	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.
protected SpacecraftState	AggregateBoundedPropagator.basicPropagate(AbsoluteDate date)
SpacecraftState	Ephemeris.basicPropagate(AbsoluteDate date)	Propagate an orbit without any fancy features.
Optional<StateCovariance>	Ephemeris.getCovariance(AbsoluteDate date)	Get the covariance at given date.
double	FieldBrouwerLyddanePropagator.getM2(AbsoluteDate date)	Get the value of the M2 drag parameter.
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	BrouwerLyddanePropagator.getMass(AbsoluteDate date)	Get the mass.
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.
Vector3D	AggregateBoundedPropagator.getPosition(AbsoluteDate date, Frame frame)
TimeStampedPVCoordinates	AggregateBoundedPropagator.getPVCoordinates(AbsoluteDate date, Frame 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)
KeplerianOrbit	BrouwerLyddanePropagator.propagateOrbit(AbsoluteDate date)	Extrapolate an orbit up to a specific target 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.

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

Constructor	Description
AggregateBoundedPropagator(NavigableMap<AbsoluteDate,? extends BoundedPropagator> propagators, AbsoluteDate min, AbsoluteDate max)	Create a propagator from several constituent propagators.

Constructor parameters in org.orekit.propagation.analytical with type arguments of type AbsoluteDate

Constructor	Description
AggregateBoundedPropagator(NavigableMap<AbsoluteDate,? extends BoundedPropagator> propagators, AbsoluteDate min, AbsoluteDate max)	Create a propagator from several constituent propagators.

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	GLONASSAnalyticalPropagator.getMass(AbsoluteDate date)	Get the mass.
protected double	GNSSPropagator.getMass(AbsoluteDate date)	Get the mass.
protected double	SBASPropagator.getMass(AbsoluteDate date)	Get the mass.
PVCoordinates	GLONASSAnalyticalPropagator.propagateInEcef(AbsoluteDate date)	Gets the PVCoordinates of the GLONASS SV in ECEF frame.
PVCoordinates	GNSSPropagator.propagateInEcef(AbsoluteDate date)	Gets the PVCoordinates of the GNSS SV in ECEF frame.
PVCoordinates	SBASPropagator.propagateInEcef(AbsoluteDate date)	Gets the PVCoordinates of the GNSS SV in ECEF frame.
protected Orbit	GLONASSAnalyticalPropagator.propagateOrbit(AbsoluteDate date)	Extrapolate an orbit up to a specific target date.
protected Orbit	GNSSPropagator.propagateOrbit(AbsoluteDate date)	Extrapolate an orbit up to a specific target date.
protected Orbit	SBASPropagator.propagateOrbit(AbsoluteDate date)	Extrapolate an orbit up to a specific target date.

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

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

Modifier and Type	Method	Description
AbsoluteDate	AbstractEphemerisMessage.getDate()	Getter for the reference date of the ephemeris.
AbsoluteDate	CommonGnssData.getDate()	Getter for the ephemeris reference date.
AbsoluteDate	GLONASSAlmanac.getDate()
AbsoluteDate	GLONASSEphemeris.getDate()
AbsoluteDate	AbstractEphemerisMessage.getEpochToc()	Getter for the time of clock epoch.
AbsoluteDate	AbstractNavigationMessage.getEpochToc()	Getter for the time of clock epoch.

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

Modifier and Type	Method	Description
void	AbstractEphemerisMessage.setDate(AbsoluteDate date)	Setter for the reference date of the ephemeris.
void	CommonGnssData.setDate(AbsoluteDate date)	Setter for the reference epoch.
void	AbstractEphemerisMessage.setEpochToc(AbsoluteDate epochToc)	Setter for the time of clock epoch.
void	AbstractNavigationMessage.setEpochToc(AbsoluteDate epochToc)	Setter for the time of clock epoch.

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

Constructor	Description
GLONASSEphemeris(int n4, int nt, double tb, double x, double xDot, double xDotDot, double y, double yDot, double yDotDot, double z, double zDot, double zDotDot, AbsoluteDate date)	Build a new instance.

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

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

Modifier and Type	Method	Description
AbsoluteDate	IntelsatElevenElements.getEpoch()	Get the elements epoch.

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

Modifier and Type	Method	Description
protected double	IntelsatElevenElementsPropagator.getMass(AbsoluteDate date)	Get the mass.
PVCoordinates	IntelsatElevenElementsPropagator.propagateInEcef(AbsoluteDate date)	Converts the Intelsat's 11 elements into Position/Velocity coordinates in ECEF.
protected Orbit	IntelsatElevenElementsPropagator.propagateOrbit(AbsoluteDate date)	Extrapolate an orbit up to a specific target date.

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

Constructor	Description
IntelsatElevenElements(AbsoluteDate epoch, double lm0, double lm1, double lm2, double lonC, double lonC1, double lonS, double lonS1, double latC, double latC1, double latS, double latS1)	Constructor.

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.

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

Modifier and Type	Method	Description
double	TLE.getBStar(AbsoluteDate date)	Get the ballistic coefficient at a specific 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.
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.
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, TimeScale utc)	Simple constructor from already parsed elements using the given time scale as UTC.

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.conversion.averaging

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

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

Constructors in org.orekit.propagation.conversion.averaging with parameters of type AbsoluteDate

Constructor	Description
AbstractAveragedOrbitalState(AbsoluteDate date, Frame frame)	Protected constructor.
BrouwerLyddaneOrbitalState(AbsoluteDate date, AveragedKeplerianWithMeanAngle elements, Frame frame, UnnormalizedSphericalHarmonicsProvider harmonicsProvider)	Constructor.
DSST6X0OrbitalState(AbsoluteDate date, AveragedEquinoctialWithMeanAngle elements, Frame frame, UnnormalizedSphericalHarmonicsProvider harmonicsProvider)	Constructor.
EcksteinHechlerOrbitalState(AbsoluteDate date, AveragedCircularWithMeanAngle elements, Frame frame, UnnormalizedSphericalHarmonicsProvider harmonicsProvider)	Constructor.
SGP4OrbitalState(AbsoluteDate date, AveragedKeplerianWithMeanAngle elements)	Constructor with default data context.
SGP4OrbitalState(AbsoluteDate date, AveragedKeplerianWithMeanAngle elements, DataContext dataContext)	Constructor.

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	EventsLogger.LoggedEvent.getDate()	Get the date.
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	LongitudeCrossingDetector.init(SpacecraftState s0, AbsoluteDate t)	Initialize event handler at the start of a propagation.
void	MagneticFieldDetector.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
FieldParameterDrivenDateIntervalDetector(Field<T> field, String prefix, AbsoluteDate refMedian, double refDuration)	Build a new instance.
FieldParameterDrivenDateIntervalDetector(Field<T> field, String prefix, AbsoluteDate refStart, AbsoluteDate refStop)	Build a new instance.
ParameterDrivenDateIntervalDetector(String prefix, AbsoluteDate refMedian, double refDuration)	Build a new instance.
ParameterDrivenDateIntervalDetector(String prefix, AbsoluteDate refStart, AbsoluteDate refStop)	Build a new instance.

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

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

Modifier and Type	Method	Description
AbsoluteDate	RecallLastOccurrence.getLastOccurrence()	Getter for last occurrence.

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, EventDetector detector)	Initialize event handler at the start of a propagation.
void	EventMultipleHandler.init(SpacecraftState initialState, AbsoluteDate target, EventDetector detector)	Initialize event handler at the start of a propagation.
void	RecallLastOccurrence.init(SpacecraftState initialState, AbsoluteDate target, EventDetector detector)	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, PositionAngleType positionAngleType, AttitudeProvider attitudeProvider, Frame frame)	Create a mapper between raw double components and spacecraft state.
protected double	IntegratedEphemeris.getMass(AbsoluteDate date)	Get the mass.
default void	AbstractIntegratedPropagator.MainStateEquations.init(SpacecraftState initialState, AbsoluteDate target)	Initialize the equations at the start of propagation.
default void	AdditionalDerivativesProvider.init(SpacecraftState initialState, AbsoluteDate target)	Initialize the generator at the start of propagation.
abstract SpacecraftState	StateMapper.mapArrayToState(AbsoluteDate date, double[] y, double[] yDot, PropagationType type)	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.
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, PropagationType type, DenseOutputModel model, DoubleArrayDictionary unmanaged, List<AdditionalStateProvider> providers, String[] equations, int[] dimensions)	Creates a new instance of IntegratedEphemeris.
StateMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngleType 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 void	NumericalPropagator.beforeIntegration(SpacecraftState initialState, AbsoluteDate tEnd)	Method called just before integration.
protected StateMapper	GLONASSNumericalPropagator.createMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngleType positionAngleType, AttitudeProvider attitudeProvider, Frame frame)
protected StateMapper	NumericalPropagator.createMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngleType positionAngleType, AttitudeProvider attitudeProvider, Frame frame)	Create a mapper between raw double components and spacecraft state.
SpacecraftState	GLONASSNumericalPropagator.propagate(AbsoluteDate date)	Propagate towards a target date.

Uses of AbsoluteDate in org.orekit.propagation.numerical.cr3bp

Methods in org.orekit.propagation.numerical.cr3bp with parameters of type AbsoluteDate

Modifier and Type	Method	Description
static double	CR3BPConstants.getEarthMoonBarycenterSemiMajorAxis(AbsoluteDate date, TimeScale timeScale)	Get the Earth-Moon barycenter semi-major axis.
static double	CR3BPConstants.getJupiterSemiMajorAxis(AbsoluteDate date, TimeScale timeScale)	Get the Jupiter semi-major axis.

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 TimeStampedPVCoordinates	OrekitStepInterpolator.getPVCoordinates(AbsoluteDate date, Frame frame)	Get the PVCoordinates of the body in the selected frame.
default void	MultiSatFixedStepHandler.init(List<SpacecraftState> states0, AbsoluteDate t, double step)	Initialize step handler at the start of a propagation.
default void	MultiSatStepHandler.init(List<SpacecraftState> states0, AbsoluteDate t)	Initialize step handler at the start of a propagation.
void	MultisatStepNormalizer.init(List<SpacecraftState> s0, AbsoluteDate t)	Initialize step handler at the start of a propagation.
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	OrekitStepNormalizer.init(SpacecraftState s0, AbsoluteDate t)	Initialize step handler at the start of a propagation.
void	StepHandlerMultiplexer.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, PositionAngleType 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
default double[]	DSSTForceModel.extractParameters(double[] parameters, AbsoluteDate date)	Extract the proper parameter drivers' values from the array in input of the updateShortPeriodTerms method.
Map<String,double[]>	AbstractGaussianContribution.GaussianShortPeriodicCoefficients.getCoefficients(AbsoluteDate date, Set<String> selected)	Computes the coefficients involved in the contributions.
Map<String,double[]>	ShortPeriodTerms.getCoefficients(AbsoluteDate date, Set<String> selected)	Computes the coefficients involved in the contributions.
double	DSSTNewtonianAttraction.getMu(AbsoluteDate date)	Get the central attraction coefficient μ at specific date.
void	AbstractGaussianContribution.init(SpacecraftState initialState, AbsoluteDate target)	Initialize the force model at the start of propagation.
default void	DSSTForceModel.init(SpacecraftState initialState, AbsoluteDate target)	Initialize the force model at the start of propagation.

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.ssa.collision.shorttermencounter.probability.twod

Methods in org.orekit.ssa.collision.shorttermencounter.probability.twod that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	ShortTermEncounter2DDefinition.getTca()	Get the Time of Closest Approach.

Uses of AbsoluteDate in org.orekit.time

Fields in org.orekit.time declared as AbsoluteDate

Modifier and Type	Field	Description
static AbsoluteDate	AbsoluteDate.ARBITRARY_EPOCH	An arbitrary finite date.
static AbsoluteDate	AbsoluteDate.BEIDOU_EPOCH	Reference epoch for BeiDou weeks: 2006-01-01T00:00:00 UTC.
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 GST.
static AbsoluteDate	AbsoluteDate.GLONASS_EPOCH	Reference epoch for GLONASS four-year interval number: 1996-01-01T00:00:00 GLONASS time.
static AbsoluteDate	AbsoluteDate.GPS_EPOCH	Reference epoch for GPS weeks: 1980-01-06T00:00:00 GPS time.
static AbsoluteDate	AbsoluteDate.IRNSS_EPOCH	Reference epoch for IRNSS weeks: 1999-08-22T00:00:00 IRNSS 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.
static AbsoluteDate	AbsoluteDate.QZSS_EPOCH	Reference epoch for QZSS weeks: 1980-01-06T00:00:00 QZSS time.

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).
AbsoluteDate	AbstractTimeScales.createBesselianEpoch(double besselianEpoch)
AbsoluteDate	TimeScales.createBesselianEpoch(double besselianEpoch)	Build an instance corresponding to a Besselian Epoch (BE).
static AbsoluteDate	AbsoluteDate.createJDDate(int jd, double secondsSinceNoon, TimeScale timeScale)	Build an instance corresponding to a Julian Day date.
static AbsoluteDate	AbsoluteDate.createJDDate(int jd, double secondsSinceNoon, TimeScale timeScale, TimeScale pivotTimeScale)	Build an instance corresponding to a Julian Day date.
static AbsoluteDate	AbsoluteDate.createJulianEpoch(double julianEpoch)	Build an instance corresponding to a Julian Epoch (JE).
AbsoluteDate	AbstractTimeScales.createJulianEpoch(double julianEpoch)
AbsoluteDate	TimeScales.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.
static AbsoluteDate	AbsoluteDate.createMJDDate(int mjd, TimeOffset secondsInDay, TimeScale timeScale)	Build an instance corresponding to a Modified Julian Day date.
AbsoluteDate	SatelliteClockScale.dateAtCount(double count)	Compute date corresponding to some clock count.
AbsoluteDate	AbstractTimeScales.getBeidouEpoch()
AbsoluteDate	TimeScales.getBeidouEpoch()	Reference epoch for BeiDou weeks: 2006-01-01T00:00:00 UTC.
AbsoluteDate	AbstractTimeScales.getCcsdsEpoch()
AbsoluteDate	TimeScales.getCcsdsEpoch()	Reference epoch for CCSDS Time Code Format (CCSDS 301.0-B-4): 1958-01-01T00:00:00 International Atomic Time (not UTC).
static AbsoluteDate	AbstractTimeInterpolator.getCentralDate(AbsoluteDate date, AbsoluteDate minDate, AbsoluteDate maxDate, double threshold)	Get the central date to use to find neighbors while taking into account extrapolation threshold.
static <T extends TimeStamped> AbsoluteDate	AbstractTimeInterpolator.getCentralDate(AbsoluteDate date, ImmutableTimeStampedCache<T> cachedSamples, double threshold)	Get the central date to use to find neighbors while taking into account extrapolation threshold.
AbsoluteDate	AbsoluteDate.getDate()	Get the date.
AbsoluteDate	ClockOffset.getDate()	Get the date.
AbsoluteDate	GLONASSDate.getDate()
AbsoluteDate	GNSSDate.getDate()	Get the date.
AbsoluteDate	TimeStamped.getDate()	Get the date.
AbsoluteDate	TimeStampedDouble.getDate()	Get the date.
AbsoluteDate	TimeStampedPair.getDate()	Get the date.
AbsoluteDate	UTCTAIOffset.getDate()	Get the date of the start of the leap.
AbsoluteDate	AbstractTimeScales.getFiftiesEpoch()
AbsoluteDate	TimeScales.getFiftiesEpoch()	Reference epoch for 1950 dates: 1950-01-01T00:00:00 Terrestrial Time.
AbsoluteDate	UTCScale.getFirstKnownLeapSecond()	Get the date of the first known leap second.
AbsoluteDate	AbstractTimeScales.getFutureInfinity()
AbsoluteDate	TimeScales.getFutureInfinity()	Dummy date at infinity in the future direction.
AbsoluteDate	AbstractTimeScales.getGalileoEpoch()
AbsoluteDate	TimeScales.getGalileoEpoch()	Reference epoch for Galileo System Time: 1999-08-22T00:00:00 GST.
AbsoluteDate	AbstractTimeScales.getGlonassEpoch()
AbsoluteDate	TimeScales.getGlonassEpoch()	Reference epoch for GLONASS four-year interval number: 1996-01-01T00:00:00 GLONASS time.
AbsoluteDate	AbstractTimeScales.getGpsEpoch()
AbsoluteDate	TimeScales.getGpsEpoch()	Reference epoch for GPS weeks: 1980-01-06T00:00:00 GPS time.
AbsoluteDate	AbstractTimeInterpolator.InterpolationData.getInterpolationDate()	Get interpolation date.
AbsoluteDate	AbstractTimeScales.getIrnssEpoch()
AbsoluteDate	TimeScales.getIrnssEpoch()	Reference epoch for IRNSS weeks: 1999-08-22T00:00:00 IRNSS time.
AbsoluteDate	AbstractTimeScales.getJ2000Epoch()
AbsoluteDate	TimeScales.getJ2000Epoch()	J2000.0 Reference epoch: 2000-01-01T12:00:00 Terrestrial Time (not UTC).
AbsoluteDate	AbstractTimeScales.getJavaEpoch()
AbsoluteDate	TimeScales.getJavaEpoch()	Java Reference epoch: 1970-01-01T00:00:00 Universal Time Coordinate.
AbsoluteDate	AbstractTimeScales.getJulianEpoch()
AbsoluteDate	TimeScales.getJulianEpoch()	Reference epoch for julian dates: -4712-01-01T12:00:00 Terrestrial Time.
AbsoluteDate	UTCScale.getLastKnownLeapSecond()	Get the date of the last known leap second.
AbsoluteDate	AbstractTimeScales.getModifiedJulianEpoch()
AbsoluteDate	TimeScales.getModifiedJulianEpoch()	Reference epoch for modified julian dates: 1858-11-17T00:00:00 Terrestrial Time.
AbsoluteDate	AbstractTimeScales.getPastInfinity()
AbsoluteDate	TimeScales.getPastInfinity()	Dummy date at infinity in the past direction.
AbsoluteDate	AbstractTimeScales.getQzssEpoch()
AbsoluteDate	TimeScales.getQzssEpoch()	Reference epoch for QZSS weeks: 1980-01-06T00:00:00 QZSS time.
AbsoluteDate	AggregatedClockModel.getValidityEnd()	Get validity end.
AbsoluteDate	ClockModel.getValidityEnd()	Get validity end.
AbsoluteDate	PerfectClockModel.getValidityEnd()	Get validity end.
AbsoluteDate	SampledClockModel.getValidityEnd()	Get validity end.
AbsoluteDate	AggregatedClockModel.getValidityStart()	Get validity start.
AbsoluteDate	ClockModel.getValidityStart()	Get validity start.
AbsoluteDate	PerfectClockModel.getValidityStart()	Get validity start.
AbsoluteDate	SampledClockModel.getValidityStart()	Get validity start.
AbsoluteDate	UTCTAIOffset.getValidityStart()	Get the start time of validity for this offset.
static AbsoluteDate	AbsoluteDate.parseCCSDSCalendarSegmentedTimeCode(byte preambleField, byte[] timeField)	Build an instance from a CCSDS Calendar Segmented Time Code (CCS).
static AbsoluteDate	AbsoluteDate.parseCCSDSCalendarSegmentedTimeCode(byte preambleField, byte[] timeField, TimeScale utc)	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.parseCCSDSDaySegmentedTimeCode(byte preambleField, byte[] timeField, DateComponents agencyDefinedEpoch, TimeScale utc)	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).
static AbsoluteDate	AbsoluteDate.parseCCSDSUnsegmentedTimeCode(byte preambleField1, byte preambleField2, byte[] timeField, AbsoluteDate agencyDefinedEpoch, AbsoluteDate ccsdsEpoch)	Build an instance from a CCSDS Unsegmented Time Code (CUC).
AbsoluteDate	AbsoluteDate.shiftedBy(double dt)	Get a time-shifted instance.
AbsoluteDate	AbsoluteDate.shiftedBy(long dt, TimeUnit timeUnit)	Get a time-shifted date.
AbsoluteDate	AbsoluteDate.shiftedBy(TimeOffset dt)	Get a time-shifted instance.
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
TimeOffset	AbsoluteDate.accurateDurationFrom(AbsoluteDate instant)	Compute the physically elapsed duration between two instants.
TimeOffset	AbsoluteDate.accurateOffsetFrom(AbsoluteDate instant, TimeScale timeScale)	Compute the apparent clock offset between two instant in the perspective of a specific time scale.
static void	TimeStampedPair.checkDatesConsistency(AbsoluteDate firstDate, AbsoluteDate secondDate, double dateEqualityThreshold)	Check date consistency.
double	SatelliteClockScale.countAtDate(AbsoluteDate date)	Compute clock count corresponding to some date.
double	AbsoluteDate.durationFrom(AbsoluteDate instant)	Compute the physically elapsed duration between two instants.
long	AbsoluteDate.durationFrom(AbsoluteDate instant, TimeUnit timeUnit)	Compute the physically elapsed duration between two instants.
T	FieldAbsoluteDate.durationFrom(AbsoluteDate instant)	Compute the physically elapsed duration between two instants.
T	FieldAbsoluteDate.durationFrom(AbsoluteDate instant, TimeUnit timeUnit)	Compute the physically elapsed duration between two instants.
static AbsoluteDate	AbstractTimeInterpolator.getCentralDate(AbsoluteDate date, AbsoluteDate minDate, AbsoluteDate maxDate, double threshold)	Get the central date to use to find neighbors while taking into account extrapolation threshold.
static <T extends TimeStamped> AbsoluteDate	AbstractTimeInterpolator.getCentralDate(AbsoluteDate date, ImmutableTimeStampedCache<T> cachedSamples, double threshold)	Get the central date to use to find neighbors while taking into account extrapolation threshold.
TimeOffset	GLONASSScale.getLeap(AbsoluteDate date)	Get the value of the previous leap.
default TimeOffset	TimeScale.getLeap(AbsoluteDate date)	Get the value of the previous leap.
TimeOffset	UTCScale.getLeap(AbsoluteDate date)	Get the value of the previous leap.
ClockOffset	AggregatedClockModel.getOffset(AbsoluteDate date)	Get the clock offset at date.
ClockOffset	ClockModel.getOffset(AbsoluteDate date)	Get the clock offset at date.
ClockOffset	PerfectClockModel.getOffset(AbsoluteDate date)	Get the clock offset at date.
ClockOffset	SampledClockModel.getOffset(AbsoluteDate date)	Get the clock offset at date.
TimeOffset	UTCTAIOffset.getOffset(AbsoluteDate date)	Get the TAI - UTC offset in seconds.
protected double	AbstractTimeInterpolator.getTimeParameter(AbsoluteDate interpolatingTime, AbsoluteDate previousDate, AbsoluteDate nextDate)	Get the time parameter which lies between [0:1] by normalizing the difference between interpolating time and previous date by the Δt between tabulated values.
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.
T	AbstractTimeInterpolator.interpolate(AbsoluteDate interpolationDate, Collection<T> sample)	Get an interpolated instance.
T	AbstractTimeInterpolator.interpolate(AbsoluteDate interpolationDate, Stream<T> sample)	Get an interpolated instance.
default T	FieldTimeInterpolator.interpolate(AbsoluteDate interpolationDate, Collection<T> sample)	Get an interpolated instance.
default T	FieldTimeInterpolator.interpolate(AbsoluteDate interpolationDate, Stream<T> sample)	Get an interpolated instance.
T	TimeInterpolator.interpolate(AbsoluteDate interpolationDate, Collection<T> sample)	Get an interpolated instance.
T	TimeInterpolator.interpolate(AbsoluteDate interpolationDate, 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.
TimeOffset	ClockTimeScale.offsetFromTAI(AbsoluteDate date)	Get the offset to convert locations from TAIScale to instance.
TimeOffset	ConstantOffsetTimeScale.offsetFromTAI(AbsoluteDate date)	Get the offset to convert locations from TAIScale to instance.
TimeOffset	GLONASSScale.offsetFromTAI(AbsoluteDate date)	Get the offset to convert locations from TAIScale to instance.
TimeOffset	GMSTScale.offsetFromTAI(AbsoluteDate date)	Get the offset to convert locations from TAIScale to instance.
TimeOffset	SatelliteClockScale.offsetFromTAI(AbsoluteDate date)	Get the offset to convert locations from TAIScale to instance.
TimeOffset	TCBScale.offsetFromTAI(AbsoluteDate date)	Get the offset to convert locations from TAIScale to instance.
TimeOffset	TCGScale.offsetFromTAI(AbsoluteDate date)	Get the offset to convert locations from TAIScale to instance.
TimeOffset	TDBScale.offsetFromTAI(AbsoluteDate date)	Get the offset to convert locations from TAIScale to instance.
TimeOffset	TimeScale.offsetFromTAI(AbsoluteDate date)	Get the offset to convert locations from TAIScale to instance.
TimeOffset	UT1Scale.offsetFromTAI(AbsoluteDate date)	Get the offset to convert locations from TAIScale to instance.
TimeOffset	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).
static AbsoluteDate	AbsoluteDate.parseCCSDSUnsegmentedTimeCode(byte preambleField1, byte preambleField2, byte[] timeField, AbsoluteDate agencyDefinedEpoch, AbsoluteDate ccsdsEpoch)	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 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.
AbsoluteDate(AbsoluteDate since, long elapsedDuration, TimeUnit timeUnit)	Build an instance from an elapsed duration since another instant.
AbsoluteDate(AbsoluteDate since, TimeOffset elapsedDuration)	Build an instance from an elapsed duration since another instant.
AbsoluteDate(AbsoluteDate reference, TimeOffset apparentOffset, TimeScale timeScale)	Build an instance from an apparent clock offset with respect to another instant in the perspective of a specific time scale.
ClockOffset(AbsoluteDate date, double offset, double rate, double acceleration)	Simple constructor.
FieldAbsoluteDate(Field<T> field, AbsoluteDate date)	Build an instance from an AbsoluteDate.
FieldAbsoluteDate(AbsoluteDate since, long elapsedDuration, TimeUnit timeUnit, Field<T> field)	Build an instance from an elapsed duration since another instant.
FieldAbsoluteDate(AbsoluteDate since, T elapsedDuration)	Build an instance from an elapsed duration since another instant.
GLONASSDate(AbsoluteDate date)	Build an instance from an absolute date.
GLONASSDate(AbsoluteDate date, TimeScale glonass)	Build an instance from an absolute date.
GNSSDate(AbsoluteDate date, SatelliteSystem system)	Build an instance from an absolute date.
GNSSDate(AbsoluteDate date, SatelliteSystem system, TimeScales timeScales)	Build an instance from an absolute date.
InterpolationData(AbsoluteDate interpolationDate, Collection<T> sample)	Constructor.
SatelliteClockScale(String name, AbsoluteDate epoch, TimeScale epochScale, double countAtEpoch, double drift)	Create a linear model for satellite clock.
TimeStampedDouble(double value, AbsoluteDate date)	Constructor.
TimeStampedDoubleAndDerivative(double value, double derivative, AbsoluteDate date)	Constructor.
TimeStampedField(KK value, AbsoluteDate date)	Constructor with normal date.

Uses of AbsoluteDate in org.orekit.utils

Methods in org.orekit.utils that return AbsoluteDate

Modifier and Type	Method	Description
AbsoluteDate	DateDriver.getBaseDate()	Get the base (unshifted) date.
AbsoluteDate	DateDriver.getDate()	Get the shifted date.
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	AggregatedPVCoordinatesProvider.getMaxDate()	Get the last date of the range.
AbsoluteDate	AggregatedPVCoordinatesProvider.getMinDate()	Get the first date of the range.
AbsoluteDate	IERSConventions.getNutationReferenceEpoch()	Get the reference epoch for fundamental nutation arguments.
AbsoluteDate	IERSConventions.getNutationReferenceEpoch(TimeScales timeScales)	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.
AbsoluteDate[]	ParameterDriver.getTransitionDates()	Get the dates of the transitions for the drag sensitive models TimeSpanMap.

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.
AggregatedPVCoordinatesProvider.Builder	AggregatedPVCoordinatesProvider.Builder.addPVProviderAfter(AbsoluteDate date, PVCoordinatesProvider pvProv, boolean erasesLater)	Add a PVCoordinatesProvider to the collection.
AggregatedPVCoordinatesProvider.Builder	AggregatedPVCoordinatesProvider.Builder.addPVProviderBefore(AbsoluteDate date, PVCoordinatesProvider pvProv, boolean erasesEarlier)	Add a PVCoordinatesProvider to the collection.
void	ParameterDriver.addSpanAtDate(AbsoluteDate spanStartDate)	Create a new span in values and names time span map given a start date.
void	ParameterDriver.addSpans(AbsoluteDate orbitDeterminationStartDate, AbsoluteDate orbitDeterminationEndDate, double validityPeriodForDriver)	Cut values and names time span map given orbit determination start and end and driver periodicity.
TimeSpanMap.Span<T>	TimeSpanMap.addValidAfter(T entry, AbsoluteDate earliestValidityDate, boolean erasesLater)	Add an entry valid after a limit date.
TimeSpanMap.Span<T>	TimeSpanMap.addValidBefore(T entry, AbsoluteDate latestValidityDate, boolean erasesEarlier)	Add an entry valid before a limit date.
TimeSpanMap.Span<T>	TimeSpanMap.addValidBetween(T entry, AbsoluteDate earliestValidityDate, AbsoluteDate latestValidityDate)	Add an entry valid between two limit dates.
WaypointPVBuilder	WaypointPVBuilder.addWaypoint(GeodeticPoint point, AbsoluteDate date)	Add a waypoint.
void	SecularAndHarmonic.addWeightedPoint(AbsoluteDate date, double osculatingValue, double weight)	Add a weighted fitting point.
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.
static RealMatrix	CartesianCovarianceUtils.changeReferenceFrame(Frame inputFrame, RealMatrix covarianceMatrix, AbsoluteDate date, Frame outputFrame)	Convert input position-velocity covariance matrix between reference frames.
PVCoordinatesProvider	WaypointPVBuilder.InterpolationFactory.create(AbsoluteDate date1, GeodeticPoint point1, AbsoluteDate date2, GeodeticPoint point2, OneAxisEllipsoid body)	Create a PVCoordinatesProvider which interpolates between the provided waypoints.
double	IERSConventions.evaluateTC(AbsoluteDate date)	Evaluate the date offset between the current date and the reference date.
double	IERSConventions.evaluateTC(AbsoluteDate date, TimeScales timeScales)	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.
String	ParameterDriver.getNameSpan(AbsoluteDate date)	Get name of the parameter span for a specific date.
Stream<T>	GenericTimeStampedCache.getNeighbors(AbsoluteDate central, int n)	Get the entries surrounding a central date.
Stream<T>	ImmutableTimeStampedCache.getNeighbors(AbsoluteDate central, int n)	Get the entries surrounding a central date.
default Stream<T>	TimeStampedCache.getNeighbors(AbsoluteDate central)	Get the entries surrounding a central date.
Stream<T>	TimeStampedCache.getNeighbors(AbsoluteDate central, int n)	Get the entries surrounding a central date.
<T extends TimeStamped> List<T>	SortedListTrimmer.getNeighborsSubList(AbsoluteDate central, List<T> data)	Get the entries surrounding a central date.
double	ParameterDriver.getNormalizedValue(AbsoluteDate date)	Get normalized value at specific date.
default double[]	ParameterDriversProvider.getParameters(AbsoluteDate date)	Get model parameters.
Vector3D	AggregatedPVCoordinatesProvider.getPosition(AbsoluteDate date, Frame frame)
Vector3D	ConstantPVCoordinatesProvider.getPosition(AbsoluteDate date, Frame frame)
Vector3D	FrameAdapter.getPosition(AbsoluteDate date, Frame frame)	Get the position of the body in the selected frame.
default Vector3D	PVCoordinatesProvider.getPosition(AbsoluteDate date, Frame frame)	Get the position of the body in the selected frame.
TimeStampedPVCoordinates	AbsolutePVCoordinates.getPVCoordinates(AbsoluteDate otherDate, Frame outputFrame)
TimeStampedPVCoordinates	AggregatedPVCoordinatesProvider.getPVCoordinates(AbsoluteDate date, Frame frame)
TimeStampedPVCoordinates	AggregatedPVCoordinatesProvider.InvalidPVProvider.getPVCoordinates(AbsoluteDate date, Frame frame)
TimeStampedPVCoordinates	ConstantPVCoordinatesProvider.getPVCoordinates(AbsoluteDate date, Frame frame)
default TimeStampedPVCoordinates	ExtendedPositionProvider.getPVCoordinates(AbsoluteDate date, Frame frame)	Get the PVCoordinates of the body in the selected frame.
TimeStampedPVCoordinates	FrameAdapter.getPVCoordinates(AbsoluteDate date, Frame frame)	Get the PVCoordinates of the body in the selected frame.
TimeStampedPVCoordinates	PVCoordinatesProvider.getPVCoordinates(AbsoluteDate date, Frame frame)	Get the PVCoordinates of the body in the selected frame.
TimeStampedPVCoordinates	ShiftingPVCoordinatesProvider.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.
Gradient	ParameterDriver.getValue(int freeParameters, Map<String,Integer> indices, AbsoluteDate date)	Get the value as a gradient at special date.
double	ParameterDriver.getValue(AbsoluteDate date)	Get current parameter value at specific date, depending on isContinuousEstimation value, the value returned will be obtained by step estimation or continuous estimation.
double	ParameterDriver.getValueContinuousEstimation(AbsoluteDate date)	Get current parameter value at specific date with continuous estimation.
double	ParameterDriver.getValueStepEstimation(AbsoluteDate date)	Get current parameter value at specific date with step estimation.
AggregatedPVCoordinatesProvider.Builder	AggregatedPVCoordinatesProvider.Builder.invalidAfter(AbsoluteDate lastValidDate)	Indicate the date after which the resulting PVCoordinatesProvider is invalid.
AggregatedPVCoordinatesProvider.Builder	AggregatedPVCoordinatesProvider.Builder.invalidBefore(AbsoluteDate firstValidDate)	Indicate the date before which the resulting PVCoordinatesProvider is invalid.
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	TimeSpanMap.Transition.resetDate(AbsoluteDate newDate, boolean eraseOverridden)	Move transition.
void	SecularAndHarmonic.resetFitting(AbsoluteDate date, double... initialGuess)	Reset fitting.
void	ParameterDriver.setNormalizedValue(double normalized, AbsoluteDate date)	Set normalized value at specific date.
void	ParameterDriver.setReferenceDate(AbsoluteDate newReferenceDate)	Set reference date.
void	ParameterDriver.setValue(double newValue, AbsoluteDate date)	Set parameter value at specific 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.
double	ParameterFunction.value(ParameterDriver parameterDriver, AbsoluteDate date)	Evaluate the function.
void	ParameterObserver.valueChanged(double previousValue, ParameterDriver driver, AbsoluteDate date)	Notify that a parameter value has been changed.

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

Constructor	Description
AbsolutePVCoordinates(Frame frame, AbsoluteDate date, FieldVector3D<U> p)	Builds a AbsolutePVCoordinates triplet from a FieldVector3D<Derivative>.
AbsolutePVCoordinates(Frame frame, AbsoluteDate date, Vector3D position, Vector3D velocity)	Build from position and velocity.
AbsolutePVCoordinates(Frame frame, AbsoluteDate date, Vector3D position, Vector3D velocity, Vector3D acceleration)	Build from position, velocity, acceleration.
AbsolutePVCoordinates(Frame frame, AbsoluteDate date, PVCoordinates pva)	Build from frame, date and PVA coordinates.
AbsolutePVCoordinates(AbsoluteDate date, double a, AbsolutePVCoordinates AbsPva)	Multiplicative constructor
AbsolutePVCoordinates(AbsoluteDate date, double a1, AbsolutePVCoordinates absPv1, double a2, AbsolutePVCoordinates absPv2)	Linear constructor
AbsolutePVCoordinates(AbsoluteDate date, double a1, AbsolutePVCoordinates absPv1, double a2, AbsolutePVCoordinates absPv2, double a3, AbsolutePVCoordinates absPv3)	Linear constructor
AbsolutePVCoordinates(AbsoluteDate date, double a1, AbsolutePVCoordinates absPv1, double a2, AbsolutePVCoordinates absPv2, double a3, AbsolutePVCoordinates absPv3, double a4, AbsolutePVCoordinates absPv4)	Linear constructor
AbsolutePVCoordinates(AbsoluteDate date, AbsolutePVCoordinates start, AbsolutePVCoordinates end)	Subtractive constructor
AggregatedPVCoordinatesProvider(TimeSpanMap<PVCoordinatesProvider> map, AbsoluteDate minDate, AbsoluteDate maxDate)	Class constructor.
DateDriver(AbsoluteDate base, String name, boolean start)	Simple constructor.
TimeStampedAngularCoordinates(AbsoluteDate date, FieldRotation<U> r)	Builds a TimeStampedAngularCoordinates from a FieldRotation<Derivative>.
TimeStampedAngularCoordinates(AbsoluteDate date, Rotation rotation, Vector3D rotationRate, 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, FieldRotation<T> rotation, FieldVector3D<T> rotationRate, 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, FieldVector3D<T> position, FieldVector3D<T> velocity, 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, FieldVector3D<U> p)	Builds a TimeStampedPVCoordinates triplet from a FieldVector3D<Derivative>.
TimeStampedPVCoordinates(AbsoluteDate date, Vector3D position, Vector3D velocity)	Build from position and velocity.
TimeStampedPVCoordinates(AbsoluteDate date, Vector3D position, Vector3D velocity, 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