Uses of Class
org.orekit.time.AbsoluteDate
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Packages that use AbsoluteDate Package Description org.orekit.attitudes This package provides classes to represent simple attitudes.org.orekit.bodies This package provides interface to represent the position and geometry of space objects such as stars, planets or asteroids.org.orekit.data This package provide base classes for exploring the configured data directory tree and read external data that can be used by the library.org.orekit.estimation.iod 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 theNumericalPropagator
, 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 classManeuver
.org.orekit.forces.maneuvers.trigger This package provides maneuver triggers' models intended to be used with classManeuver
.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 Propagationorg.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 ofSpacecraftState
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. -
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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
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.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
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.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.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<DerivativeStructure>
OneAxisEllipsoid. transform(PVCoordinates point, Frame frame, AbsoluteDate date)
Transform a Cartesian point to a surface-relative point. -
Uses of AbsoluteDate in org.orekit.data
Methods in org.orekit.data that return AbsoluteDate Modifier and Type Method Description AbsoluteDate
DelaunayArguments. getDate()
Get the date.Methods in org.orekit.data with parameters of type AbsoluteDate Modifier and Type Method Description BodiesElements
FundamentalNutationArguments. evaluateAll(AbsoluteDate date)
Evaluate all fundamental arguments for the current date (Delaunay plus planetary).Constructors in org.orekit.data with parameters of type AbsoluteDate Constructor Description BodiesElements(AbsoluteDate date, double tc, double gamma, double gammaDot, double l, double lDot, double lPrime, double lPrimeDot, double f, double fDot, double d, double dDot, double omega, double omegaDot, double lMe, double lMeDot, double lVe, double lVeDot, double lE, double lEDot, double lMa, double lMaDot, double lJu, double lJuDot, double lSa, double lSaDot, double lUr, double lUrDot, double lNe, double lNeDot, double pa, double paDot)
Simple constructor.DelaunayArguments(AbsoluteDate date, double tc, double gamma, double gammaDot, double l, double lDot, double lPrime, double lPrimeDot, double f, double fDot, double d, double dDot, double omega, double omegaDot)
Simple constructor. -
Uses of AbsoluteDate in org.orekit.estimation.iod
Methods in org.orekit.estimation.iod with parameters of type AbsoluteDate Modifier and Type Method Description 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 thesimulated 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 theTransform
corresponding to specified date.void
EstimatedMeasurement. setParameterDerivatives(ParameterDriver driver, AbsoluteDate date, double... parameterDerivatives)
Set the partial derivatives of thesimulated measurement
with respect to parameter.static double
AbstractMeasurement. signalTimeOfFlight(PVCoordinatesProvider adjustableEmitter, AbsoluteDate approxEmissionDate, Vector3D receiverPosition, AbsoluteDate signalArrivalDate, Frame receiverFrame)
Compute propagation delay on a link leg (typically downlink or uplink).static double
AbstractMeasurement. signalTimeOfFlight(TimeStampedPVCoordinates adjustableEmitterPV, Vector3D receiverPosition, AbsoluteDate signalArrivalDate)
static double
AbstractMeasurement. signalTimeOfFlight(TimeStampedPVCoordinates adjustableEmitterPV, Vector3D receiverPosition, AbsoluteDate signalArrivalDate, Frame receiverFrame)
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 AngularAzEl
AngularAzElBuilder. build(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)
Generate a single measurement.AngularRaDec
AngularRaDecBuilder. build(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)
Generate a single measurement.BistaticRange
BistaticRangeBuilder. build(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)
Generate a single measurement.BistaticRangeRate
BistaticRangeRateBuilder. build(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)
Generate a single measurement.FDOA
FDOABuilder. build(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)
Generate a single measurement.InterSatellitesOneWayRangeRate
InterSatellitesOneWayRangeRateBuilder. build(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)
Generate a single measurement.InterSatellitesPhase
InterSatellitesPhaseBuilder. build(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)
Generate a single measurement.InterSatellitesRange
InterSatellitesRangeBuilder. build(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)
Generate a single measurement.T
MeasurementBuilder. build(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)
Generate a single measurement.default T
MeasurementBuilder. build(AbsoluteDate date, SpacecraftState[] states)
Generate a single measurement.MultiplexedMeasurement
MultiplexedMeasurementBuilder. build(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)
Generate a single measurement.OneWayGNSSPhase
OneWayGNSSPhaseBuilder. build(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)
Generate a single measurement.OneWayGNSSRange
OneWayGNSSRangeBuilder. build(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)
Generate a single measurement.OneWayGNSSRangeRate
OneWayGNSSRangeRateBuilder. build(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)
Generate a single measurement.Position
PositionBuilder. build(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)
Generate a single measurement.PV
PVBuilder. build(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)
Generate a single measurement.Range
RangeBuilder. build(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)
Generate a single measurement.RangeRate
RangeRateBuilder. build(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)
Generate a single measurement.TDOA
TDOABuilder. build(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)
Generate a single measurement.TurnAroundRange
TurnAroundRangeBuilder. build(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)
Generate a single 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.Constructor parameters in org.orekit.estimation.measurements.generation with type arguments of type AbsoluteDate Constructor Description OneWayGNSSPhaseBuilder(CorrelatedRandomVectorGenerator noiseSource, ObservableSatellite local, ObservableSatellite remote, ToDoubleFunction<AbsoluteDate> remoteClockModel, double wavelength, double sigma, double baseWeight)
OneWayGNSSRangeBuilder(CorrelatedRandomVectorGenerator noiseSource, ObservableSatellite local, ObservableSatellite remote, ToDoubleFunction<AbsoluteDate> remoteClockModel, double sigma, double baseWeight)
Simple constructor. -
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(Frequency f)
Return the date of validity beginning of the detector.AbsoluteDate
CombinedObservationDataSet. getDate()
Get the date.AbsoluteDate
CycleSlipDetectorResults. getEndDate(Frequency f)
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<Frequency,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 Phase
PhaseBuilder. build(AbsoluteDate date, Map<ObservableSatellite,OrekitStepInterpolator> interpolators)
Generate a single measurement.protected void
AbstractCycleSlipDetector. cycleSlipDataSet(String nameSat, AbsoluteDate date, double value, Frequency freq)
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)
Deprecated.InterSatellitesPhase(ObservableSatellite local, ObservableSatellite remote, AbsoluteDate date, double phase, double wavelength, double sigma, double baseWeight, AmbiguityCache cache)
Constructor.OneWayGNSSPhase(PVCoordinatesProvider remote, double dtRemote, AbsoluteDate date, double phase, double wavelength, double sigma, double baseWeight, ObservableSatellite local)
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)
Deprecated.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 betweenCCSDS 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 thecovariance 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 themaneuver 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 thetrajectory 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 thecovariance 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 themaneuver 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 thetrajectory 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 inRange Units
.double
RangeUnitsConverter. ruToMeters(TdmMetadata metadata, AbsoluteDate date, double range)
Convert a range expressed inRange 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 theclock 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 theclock 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
SinexLoader. getCreationDate()
Get the creation date of the parsed SINEX file.AbsoluteDate
SinexEopEntry. getDate()
Get the date.AbsoluteDate
Station. getEpoch()
Get the coordinates reference epoch.AbsoluteDate
SinexLoader. getFileEpochEndTime()
Get the file epoch end time.AbsoluteDate
SinexLoader. getFileEpochStartTime()
Get the file epoch start time.AbsoluteDate
Dcb. getMaximumValidDateForObservationPair(String obs1, String obs2)
Get the maximum valid date for a given observation pair.AbsoluteDate
Dcb. getMaximumValidDateForObservationPair(ObservationType obs1, ObservationType obs2)
Get the maximum valid date for a given observation pair.AbsoluteDate
Dcb. getMinimumValidDateForObservationPair(String obs1, String obs2)
Get the minimum valid date for a given observation pair.AbsoluteDate
Dcb. getMinimumValidDateForObservationPair(ObservationType obs1, ObservationType obs2)
Get the minimum valid date for a given observation pair.AbsoluteDate
Station. getValidFrom()
Get start of validity.AbsoluteDate
Station. getValidUntil()
Get end of validity.Methods in org.orekit.files.sinex that return types with arguments of type AbsoluteDate Modifier and Type Method Description Map<AbsoluteDate,SinexEopEntry>
SinexLoader. getParsedEop()
Get the parsed EOP data.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.
UsingaddAntennaTypeValidAfter(entry, t)
will makeentry
valid in [t, +∞[ (note the closed bracket).void
Station. addAntennaTypeValidBefore(String entry, AbsoluteDate latestValidityDate)
Add a antenna type entry valid before a limit date.
UsingaddAntennaTypeValidBefore(entry, t)
will makeentry
valid in ]-∞, t[ (note the open bracket).void
Dcb. addDcbLine(String obs1, String obs2, AbsoluteDate spanBegin, AbsoluteDate spanEnd, double biasValue)
Add the content of a DCB line to the DCBSatellite object.void
Station. addPsdCorrectionValidAfter(PsdCorrection entry, AbsoluteDate earliestValidityDate)
Add a Post-Seismic Deformation entry valid after a limit date.
UsingaddPsdCorrectionValidAfter(entry, t)
will makeentry
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.
UsingaddStationEccentricitiesValidAfter(entry, t)
will makeentry
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.
UsingaddStationEccentricitiesValidBefore(entry, t)
will makeentry
valid in ]-∞, t[ (note the open bracket).String
Station. getAntennaType(AbsoluteDate date)
Get the antenna type for the given epoch.double
Dcb. getDcb(String obs1, String obs2, AbsoluteDate date)
Get the value of the Differential Code Bias for a given observation pair and a at a given date.double
Dcb. getDcb(ObservationType obs1, ObservationType obs2, AbsoluteDate date)
Get the value of the Differential Code Bias for a given observation pair and a 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 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.
UsingaddDragSensitiveValidAfter(entry, t)
will makeentry
valid in [t, +∞[ (note the closed bracket).void
TimeSpanDragForce. addDragSensitiveValidBefore(DragSensitive dragSensitive, AbsoluteDate latestValidityDate)
Deprecated.Add a DragSensitive entry valid before a limit date.
UsingaddDragSensitiveValidBefore(entry, t)
will makeentry
valid in ]-∞, t[ (note the open bracket).TimeSpanMap<DragSensitive>
TimeSpanDragForce. extractDragSensitiveRange(AbsoluteDate start, AbsoluteDate end)
Deprecated.Extract a range of theDragSensitive
map.double[]
TimeSpanDragForce. extractParameters(double[] parameters, AbsoluteDate date)
Deprecated.Extract the proper parameter drivers' values from the array in input of theacceleration
method.DragSensitive
TimeSpanDragForce. getDragSensitive(AbsoluteDate date)
Deprecated.Get theDragSensitive
model valid at a date.TimeSpanMap.Span<DragSensitive>
TimeSpanDragForce. getDragSensitiveSpan(AbsoluteDate date)
Deprecated.Get theDragSensitive
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 theAccelerationModel
map.double[]
TimeSpanParametricAcceleration. extractParameters(double[] parameters, AbsoluteDate date)
Extract the proper parameter drivers' values from the array in input of theacceleration
method.AccelerationModel
TimeSpanParametricAcceleration. getAccelerationModel(AbsoluteDate date)
Get theAccelerationModel
model valid at a date.TimeSpanMap.Span<AccelerationModel>
TimeSpanParametricAcceleration. getAccelerationModelSpan(AbsoluteDate date)
Get theAccelerationModel
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 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. -
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 thePVCoordinates
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 theTransform
corresponding to specified date.Transform
GTODProvider. getTransform(AbsoluteDate date)
Get theTransform
corresponding to specified date.Transform
HelmertTransformation. getTransform(AbsoluteDate date)
Get theTransform
corresponding to specified date.Transform
InterpolatingTransformProvider. getTransform(AbsoluteDate date)
Get theTransform
corresponding to specified date.Transform
ITRFVersion.Converter. getTransform(AbsoluteDate date)
Get theTransform
corresponding to specified date.Transform
L1TransformProvider. getTransform(AbsoluteDate date)
Get theTransform
corresponding to specified date.Transform
ShiftingTransformProvider. getTransform(AbsoluteDate date)
Get theTransform
corresponding to specified date.Transform
TransformProvider. getTransform(AbsoluteDate date)
Get theTransform
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 usingEOPHistory.getStartDate()
andEOPHistory.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 inputlocal orbital frame
to the instance.static Rotation
LOF. rotationFromLOFInToLOFOut(LOF in, LOF out, AbsoluteDate date, PVCoordinates pv)
Get the rotation from input to outputlocal 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 inputlocal orbital frame
to the instance.static Transform
LOF. transformFromLOFInToLOFOut(LOF in, LOF out, AbsoluteDate date, PVCoordinates pv)
Get the transform from input to outputlocal 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 theDOP
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, ExtendedPVCoordinatesProvider sun, Frame inertialFrame, int prnNumber)
Build an attitude provider suitable for this satellite type.Constructors in org.orekit.gnss.antenna with parameters of type AbsoluteDate Constructor Description SatelliteAntenna(String type, String sinexCode, Map<Frequency,FrequencyPattern> patterns, SatelliteSystem satelliteSystem, int prnNumber, 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, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)
Simple constructor.BeidouIGSO(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)
Simple constructor.BeidouMeo(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)
Simple constructor.Galileo(double yawRate, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)
Simple constructor.GenericGNSS(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)
Simple constructor.Glonass(double yawRate, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)
Simple constructor.GPSBlockIIA(double yawRate, double yawBias, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)
Simple constructor.GPSBlockIIF(double yawRate, double yawBias, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)
Simple constructor.GPSBlockIIR(double yawRate, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)
Simple constructor. -
Uses of AbsoluteDate in org.orekit.models.earth
Methods in org.orekit.models.earth with parameters of type AbsoluteDate Modifier and Type Method Description 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.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.
UsingaddTroposphericModelValidAfter(entry, t)
will makeentry
valid in [t, +∞[ (note the closed bracket).void
TimeSpanEstimatedTroposphericModel. addTroposphericModelValidAfter(EstimatedTroposphericModel model, AbsoluteDate earliestValidityDate)
Deprecated.Add a EstimatedTroposphericModel entry valid after a limit date.
UsingaddTroposphericModelValidAfter(entry, t)
will makeentry
valid in [t, +∞[ (note the closed bracket).void
TimeSpanEstimatedModel. addTroposphericModelValidBefore(EstimatedModel model, AbsoluteDate latestValidityDate)
Add an EstimatedTroposphericModel entry valid before a limit date.
UsingaddTroposphericValidBefore(entry, t)
will makeentry
valid in ]-∞, t[ (note the open bracket).void
TimeSpanEstimatedTroposphericModel. addTroposphericModelValidBefore(EstimatedTroposphericModel model, AbsoluteDate latestValidityDate)
Deprecated.Add an EstimatedTroposphericModel entry valid before a limit date.
UsingaddTroposphericValidBefore(entry, t)
will makeentry
valid in ]-∞, t[ (note the open bracket).double[]
MendesPavlisModel. computeZenithDelay(GeodeticPoint point, double[] parameters, AbsoluteDate date)
This method allows the computation of the zenith hydrostatic and zenith wet delay.double[]
ViennaOneModel. computeZenithDelay(GeodeticPoint point, double[] parameters, AbsoluteDate date)
Deprecated.This method allows the computation of the zenith hydrostatic and zenith wet delay.double[]
ViennaThreeModel. computeZenithDelay(GeodeticPoint point, double[] parameters, AbsoluteDate date)
Deprecated.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 thepathDelay
method.double[]
TimeSpanEstimatedTroposphericModel. extractParameters(double[] parameters, AbsoluteDate date)
Deprecated.Extract the proper parameter drivers' values from the array in input of thepathDelay
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 theEstimatedModel
model valid at a date.EstimatedTroposphericModel
TimeSpanEstimatedTroposphericModel. getTroposphericModel(AbsoluteDate date)
Deprecated.Get theEstimatedTroposphericModel
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(double elevation, GeodeticPoint point, AbsoluteDate date)
Deprecated.double[]
GlobalMappingFunctionModel. mappingFactors(TrackingCoordinates trackingCoordinates, GeodeticPoint point, PressureTemperatureHumidity weather, AbsoluteDate date)
This method allows the computation of the hydrostatic and wet mapping functions.double[]
MappingFunction. mappingFactors(double elevation, GeodeticPoint point, AbsoluteDate date)
Deprecated.This method allows the computation of the hydrostatic and wet mapping functions.double[]
MendesPavlisModel. mappingFactors(double elevation, GeodeticPoint point, AbsoluteDate date)
Deprecated.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(double elevation, GeodeticPoint point, AbsoluteDate date)
Deprecated.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[]
TroposphereMappingFunctionAdapter. mappingFactors(TrackingCoordinates trackingCoordinates, GeodeticPoint point, PressureTemperatureHumidity weather, AbsoluteDate date)
Deprecated.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[]
ViennaOneModel. mappingFactors(double elevation, GeodeticPoint point, AbsoluteDate date)
Deprecated.double[]
ViennaThree. mappingFactors(TrackingCoordinates trackingCoordinates, GeodeticPoint point, PressureTemperatureHumidity weather, AbsoluteDate date)
This method allows the computation of the hydrostatic and wet mapping functions.double[]
ViennaThreeModel. mappingFactors(double elevation, GeodeticPoint point, AbsoluteDate date)
Deprecated.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.double
DiscreteTroposphericModel. pathDelay(double elevation, GeodeticPoint point, double[] parameters, AbsoluteDate date)
Deprecated.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.double
EstimatedTroposphericModel. pathDelay(double elevation, GeodeticPoint point, double[] parameters, AbsoluteDate date)
Deprecated.double
FixedTroposphericDelay. pathDelay(double elevation, GeodeticPoint point, double[] parameters, AbsoluteDate date)
Deprecated.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.double
MariniMurrayModel. pathDelay(double elevation, GeodeticPoint point, double[] parameters, AbsoluteDate date)
Deprecated.Calculates the tropospheric path delay for the signal path from a ground station to a satellite.double
MendesPavlisModel. pathDelay(double elevation, GeodeticPoint point, double[] parameters, AbsoluteDate date)
Deprecated.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.double
ModifiedSaastamoinenModel. pathDelay(double elevation, GeodeticPoint point, 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.double
SaastamoinenModel. pathDelay(double elevation, GeodeticPoint point, double[] parameters, AbsoluteDate date)
Deprecated.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.double
TimeSpanEstimatedTroposphericModel. pathDelay(double elevation, GeodeticPoint point, double[] parameters, AbsoluteDate date)
Deprecated.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.TroposphericDelay
TroposphericModelAdapter. pathDelay(TrackingCoordinates trackingCoordinates, GeodeticPoint point, PressureTemperatureHumidity weather, double[] parameters, AbsoluteDate date)
Deprecated.Calculates the tropospheric path delay for the signal path from a ground station to a satellite.double
ViennaOneModel. pathDelay(double elevation, GeodeticPoint point, double[] parameters, AbsoluteDate date)
Deprecated.double
ViennaThreeModel. pathDelay(double elevation, GeodeticPoint point, double[] parameters, AbsoluteDate date)
Deprecated. -
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 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. getWeatherParamerers(GeodeticPoint location, AbsoluteDate date)
Provide weather parameters.PressureTemperatureHumidity
ConstantPressureTemperatureHumidityProvider. getWeatherParamerers(GeodeticPoint location, AbsoluteDate date)
Provide weather parameters.PressureTemperatureHumidity
PressureTemperatureHumidityProvider. getWeatherParamerers(GeodeticPoint location, AbsoluteDate date)
Provide weather parameters.PressureTemperature
GlobalPressureTemperature. getWeatherParameters(GeodeticPoint location, AbsoluteDate date)
Provide weather parameters.void
GlobalPressureTemperature2Model. weatherParameters(double stationHeight, AbsoluteDate currentDate)
Deprecated.void
GlobalPressureTemperatureModel. weatherParameters(double height, AbsoluteDate date)
Deprecated.void
WeatherModel. weatherParameters(double stationHeight, AbsoluteDate currentDate)
Deprecated.Calculates the weather parameters of the model. -
Uses of AbsoluteDate in org.orekit.orbits
Methods in org.orekit.orbits that return AbsoluteDate Modifier and Type Method Description AbsoluteDate
Orbit. getDate()
Get the date of orbital parameters.Methods in org.orekit.orbits with parameters of type AbsoluteDate Modifier and Type Method Description 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 thePVCoordinates
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 thePVCoordinates
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 that return types with arguments of type AbsoluteDate Modifier and Type Method Description NavigableMap<AbsoluteDate,BoundedPropagator>
AggregateBoundedPropagator. getPropagators()
Deprecated.as of 12.1, replaced byAggregateBoundedPropagator.getPropagatorsMap()
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 inECEF frame
.PVCoordinates
GNSSPropagator. propagateInEcef(AbsoluteDate date)
Gets the PVCoordinates of the GNSS SV inECEF frame
.PVCoordinates
SBASPropagator. propagateInEcef(AbsoluteDate date)
Gets the PVCoordinates of the GNSS SV inECEF 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 thePVCoordinates
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 theupdateShortPeriodTerms
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.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 <T extends TimeStamped>
AbsoluteDateAbstractTimeInterpolator. 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>
AbsoluteDateAbstractTimeInterpolator. getCentralDate(AbsoluteDate date, ImmutableTimeStampedCache<T> cachedSamples, double threshold)
Get the central date to use to find neighbors while taking into account extrapolation threshold.protected AbsoluteDate
AbstractTimeInterpolator.InterpolationData. getCentralDate(AbsoluteDate date)
Deprecated.This method appears to be unused and may be removed in Orekit 13.0.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 date.AbsoluteDate
AbsoluteDate. shiftedBy(long dt, TimeUnit timeUnit)
Get a time-shifted date.AbsoluteDate
FieldAbsoluteDate. toAbsoluteDate()
Transform the FieldAbsoluteDate in an AbsoluteDate.Methods in org.orekit.time that return types with arguments of type AbsoluteDate Modifier and Type Method Description List<AbsoluteDate>
BurstSelector. selectDates(AbsoluteDate start, AbsoluteDate end)
Select dates within an interval.List<AbsoluteDate>
DatesSelector. selectDates(AbsoluteDate start, AbsoluteDate end)
Select dates within an interval.List<AbsoluteDate>
FixedStepSelector. selectDates(AbsoluteDate start, AbsoluteDate end)
Select dates within an interval.Methods in org.orekit.time with parameters of type AbsoluteDate Modifier and Type Method Description static void
TimeStampedPair. checkDatesConsistency(AbsoluteDate firstDate, AbsoluteDate secondDate, double dateEqualityThreshold)
Check date consistency.int
AbsoluteDate. compareTo(AbsoluteDate date)
Compare the instance with another date.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 <T extends TimeStamped>
AbsoluteDateAbstractTimeInterpolator. 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>
AbsoluteDateAbstractTimeInterpolator. getCentralDate(AbsoluteDate date, ImmutableTimeStampedCache<T> cachedSamples, double threshold)
Get the central date to use to find neighbors while taking into account extrapolation threshold.protected AbsoluteDate
AbstractTimeInterpolator.InterpolationData. getCentralDate(AbsoluteDate date)
Deprecated.This method appears to be unused and may be removed in Orekit 13.0.double
GLONASSScale. getLeap(AbsoluteDate date)
Get the value of the previous leap.default double
TimeScale. getLeap(AbsoluteDate date)
Get the value of the previous leap.double
UTCScale. getLeap(AbsoluteDate date)
Get the value of the previous leap.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.double
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 specifictime scale
.double
ClockTimeScale. offsetFromTAI(AbsoluteDate date)
Get the offset to convert locations fromTAIScale
to instance.double
ConstantOffsetTimeScale. offsetFromTAI(AbsoluteDate date)
Get the offset to convert locations fromTAIScale
to instance.double
GLONASSScale. offsetFromTAI(AbsoluteDate date)
Get the offset to convert locations fromTAIScale
to instance.double
GMSTScale. offsetFromTAI(AbsoluteDate date)
Get the offset to convert locations fromTAIScale
to instance.double
SatelliteClockScale. offsetFromTAI(AbsoluteDate date)
Get the offset to convert locations fromTAIScale
to instance.double
TCBScale. offsetFromTAI(AbsoluteDate date)
Get the offset to convert locations fromTAIScale
to instance.double
TCGScale. offsetFromTAI(AbsoluteDate date)
Get the offset to convert locations fromTAIScale
to instance.double
TDBScale. offsetFromTAI(AbsoluteDate date)
Get the offset to convert locations fromTAIScale
to instance.double
TimeScale. offsetFromTAI(AbsoluteDate date)
Get the offset to convert locations fromTAIScale
to instance.double
UT1Scale. offsetFromTAI(AbsoluteDate date)
Get the offset to convert locations fromTAIScale
to instance.double
UTCScale. offsetFromTAI(AbsoluteDate date)
Get the offset to convert locations fromTAIScale
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 to another instant.AbsoluteDate(AbsoluteDate reference, double apparentOffset, TimeScale timeScale)
Build an instance from an apparent clock offset with respect to another instant in the perspective of a specifictime scale
.AbsoluteDate(AbsoluteDate since, long elapsedDuration, TimeUnit timeUnit)
Build an instance from an elapsed duration since to another instant.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 to another instant.FieldAbsoluteDate(AbsoluteDate since, T elapsedDuration)
Build an instance from an elapsed duration since to 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 modelsTimeSpanMap
.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 aPVCoordinatesProvider
to the collection.AggregatedPVCoordinatesProvider.Builder
AggregatedPVCoordinatesProvider.Builder. addPVProviderBefore(AbsoluteDate date, PVCoordinatesProvider pvProv, boolean erasesEarlier)
Add aPVCoordinatesProvider
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.PVCoordinatesProvider
WaypointPVBuilder.InterpolationFactory. create(AbsoluteDate date1, GeodeticPoint point1, AbsoluteDate date2, GeodeticPoint point2, OneAxisEllipsoid body)
Create aPVCoordinatesProvider
which interpolates between the provided waypoints.protected PVCoordinatesProvider
WaypointPVBuilder. createFinal(AbsoluteDate lastDate, GeodeticPoint lastPoint)
Create the final provider.protected PVCoordinatesProvider
WaypointPVBuilder. createInitial(AbsoluteDate firstDate, GeodeticPoint firstPoint)
Create the initial provider.double
IERSConventions. evaluateTC(AbsoluteDate date)
Evaluate the date offset between the current date and thereference date
.double
IERSConventions. evaluateTC(AbsoluteDate date, TimeScales timeScales)
Evaluate the date offset between the current date and thereference 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)
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 thePVCoordinates
of the body in the selected frame.TimeStampedPVCoordinates
FrameAdapter. getPVCoordinates(AbsoluteDate date, Frame frame)
Get thePVCoordinates
of the body in the selected frame.TimeStampedPVCoordinates
PVCoordinatesProvider. getPVCoordinates(AbsoluteDate date, Frame frame)
Get thePVCoordinates
of the body in the selected frame.TimeStampedPVCoordinates
ShiftingPVCoordinatesProvider. getPVCoordinates(AbsoluteDate date, Frame frame)
Get thePVCoordinates
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
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.
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