Uses of Class
org.orekit.time.AbsoluteDate

Packages that use AbsoluteDate

Package	Description
org.orekit.attitudes	This package provides classes to represent simple attitudes.
org.orekit.bodies	This package provides interface to represent the position and geometry of space objects such as stars, planets or asteroids.
org.orekit.data	This package provide base classes for exploring the configured data directory tree and read external data that can be used by the library.
org.orekit.files.ccsds	This package provides a parser for orbit data stored in CCSDS Orbit Data Message format.
org.orekit.files.general	This package provides interfaces for orbit file representations and corresponding parsers.
org.orekit.files.sp3	This package provides a parser for orbit data stored in SP3 format.
org.orekit.forces	This package provides the interface for force models that will be used by the NumericalPropagator, as well as some classical spacecraft models for surface forces (spherical, box and solar array ...).
org.orekit.forces.drag
org.orekit.forces.gravity	This package provides all gravity-related forces.
org.orekit.forces.gravity.potential	This package provides classes to read gravity field files and supports several different formats.
org.orekit.forces.maneuvers	This package provides models of simple maneuvers.
org.orekit.forces.radiation
org.orekit.frames	This package provides classes to handle frames and transforms between them.
org.orekit.orbits	This package provides classes to represent orbits.
org.orekit.propagation	This package provides tools to propagate orbital states with different methods.
org.orekit.propagation.analytical
org.orekit.propagation.analytical.tle	This package provides classes to read and extrapolate tle's.
org.orekit.propagation.conversion	This package provides tools to convert a given propagator or a set of SpacecraftState into another propagator.
org.orekit.propagation.events	This package provides interfaces and classes dealing with events occurring during propagation.
org.orekit.propagation.integration
org.orekit.propagation.numerical
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
org.orekit.propagation.semianalytical.dsst.utilities
org.orekit.time	This independent package provides classes to handle epochs, time scales, and to compare instants together.
org.orekit.utils	This package provides useful objects.

Uses of AbsoluteDate in org.orekit.attitudes

Methods in org.orekit.attitudes that return AbsoluteDate

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

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

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

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

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

Uses of AbsoluteDate in org.orekit.bodies

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

Modifier and Type	Method and Description
GeodeticPoint	OneAxisEllipsoid.getIntersectionPoint(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.
Vector3D	IAUPole.getPole(AbsoluteDate date) Get the body North pole direction in ICRF frame.
double	IAUPole.getPrimeMeridianAngle(AbsoluteDate date) Get the prime meridian angle.
PVCoordinates	JPLEphemeridesLoader.RawPVProvider.getRawPV(AbsoluteDate date) Get the position-velocity at date.
Vector3D	OneAxisEllipsoid.projectToGround(Vector3D point, AbsoluteDate date, Frame frame) Project a point to the ground.
Vector3D	BodyShape.projectToGround(Vector3D point, AbsoluteDate date, Frame frame) Project a point to the ground.
GeodeticPoint	OneAxisEllipsoid.transform(Vector3D point, Frame frame, AbsoluteDate date) Transform a cartesian point to a surface-relative point.
GeodeticPoint	BodyShape.transform(Vector3D 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 and Description
AbsoluteDate	FieldDelaunayArguments.getDate() Get the date.
AbsoluteDate	DelaunayArguments.getDate() Get the date.

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

Modifier and Type	Method and Description
BodiesElements	FundamentalNutationArguments.evaluateAll(AbsoluteDate date) Evaluate all fundamental arguments for the current date (Delaunay plus planetary).
FieldBodiesElements<DerivativeStructure>	FundamentalNutationArguments.evaluateDerivative(AbsoluteDate date) Evaluate all fundamental arguments for the current date (Delaunay plus planetary), including the first time derivative.

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

Constructor and Description
BodiesElements(AbsoluteDate date, double tc, double gamma, double l, double lPrime, double f, double d, double omega, double lMe, double lVe, double lE, double lMa, double lJu, double lSa, double lUr, double lNe, double pa) Simple constructor.
DelaunayArguments(AbsoluteDate date, double tc, double gamma, double l, double lPrime, double f, double d, double omega) Simple constructor.
FieldBodiesElements(AbsoluteDate date, T tc, T gamma, T l, T lPrime, T f, T d, T omega, T lMe, T lVe, T lE, T lMa, T lJu, T lSa, T lUr, T lNe, T pa) Simple constructor.
FieldDelaunayArguments(AbsoluteDate date, T tc, T gamma, T l, T lPrime, T f, T d, T omega) Simple constructor.

Uses of AbsoluteDate in org.orekit.files.ccsds

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

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

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

Modifier and Type	Method and Description
OMMParser	OMMParser.withMissionReferenceDate(AbsoluteDate newMissionReferenceDate) Set initial date.
OPMParser	OPMParser.withMissionReferenceDate(AbsoluteDate newMissionReferenceDate) Set initial date.
abstract ODMParser	ODMParser.withMissionReferenceDate(AbsoluteDate newMissionReferenceDate) Set initial date.
OEMParser	OEMParser.withMissionReferenceDate(AbsoluteDate newMissionReferenceDate) Set initial date.

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

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

Uses of AbsoluteDate in org.orekit.files.general

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

Modifier and Type	Method and Description
AbsoluteDate	SatelliteTimeCoordinate.getDate() Get the date.
AbsoluteDate	SatelliteTimeCoordinate.getEpoch() Returns the epoch for this coordinate.
AbsoluteDate	OrbitFile.getEpoch() Returns the start epoch of the orbit file.

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

Modifier and Type	Method and Description
void	SatelliteTimeCoordinate.setEpoch(AbsoluteDate epoch) Set the epoch for this coordinate.

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

Constructor and Description
SatelliteTimeCoordinate(AbsoluteDate time, PVCoordinates coord) Creates a new SatelliteTimeCoordinate instance with a given epoch and coordinate.
SatelliteTimeCoordinate(AbsoluteDate time, PVCoordinates coord, double clockCorr, double rateChange) Creates a new SatelliteTimeCoordinate instance with a given epoch, coordinate and clock value / rate change.
SatelliteTimeCoordinate(AbsoluteDate time, Vector3D pos, double clock) Creates a new SatelliteTimeCoordinate object with a given epoch and position coordinate.

Uses of AbsoluteDate in org.orekit.files.sp3

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

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

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

Modifier and Type	Method and Description
void	SP3File.setEpoch(AbsoluteDate time) Set the epoch of the SP3 file.

Uses of AbsoluteDate in org.orekit.forces

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

Modifier and Type	Method and Description
FieldVector3D<DerivativeStructure>	ForceModel.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
FieldVector3D<DerivativeStructure>	BoxAndSolarArraySpacecraft.dragAcceleration(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass, double density, FieldVector3D<DerivativeStructure> relativeVelocity) Compute the acceleration due to drag, with state derivatives.
FieldVector3D<DerivativeStructure>	SphericalSpacecraft.dragAcceleration(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass, double density, FieldVector3D<DerivativeStructure> relativeVelocity) Compute the acceleration due to drag, with state derivatives.
Vector3D	BoxAndSolarArraySpacecraft.dragAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, double density, Vector3D relativeVelocity) Compute the acceleration due to drag.
Vector3D	SphericalSpacecraft.dragAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, double density, Vector3D relativeVelocity) Compute the acceleration due to drag.
FieldVector3D<DerivativeStructure>	BoxAndSolarArraySpacecraft.dragAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, double density, Vector3D relativeVelocity, String paramName) Compute acceleration due to drag, with parameters derivatives.
FieldVector3D<DerivativeStructure>	SphericalSpacecraft.dragAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, double density, Vector3D relativeVelocity, String paramName) Compute acceleration due to drag, with parameters derivatives.
FieldVector3D<DerivativeStructure>	BoxAndSolarArraySpacecraft.getNormal(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldRotation<DerivativeStructure> rotation) Get solar array normal in spacecraft frame.
Vector3D	BoxAndSolarArraySpacecraft.getNormal(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation) Get solar array normal in spacecraft frame.
FieldVector3D<DerivativeStructure>	BoxAndSolarArraySpacecraft.radiationPressureAcceleration(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass, FieldVector3D<DerivativeStructure> flux) Compute the acceleration due to radiation pressure, with state derivatives.
FieldVector3D<DerivativeStructure>	SphericalSpacecraft.radiationPressureAcceleration(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass, FieldVector3D<DerivativeStructure> flux) Compute the acceleration due to radiation pressure, with state derivatives.
Vector3D	BoxAndSolarArraySpacecraft.radiationPressureAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, Vector3D flux) Compute the acceleration due to radiation pressure.
Vector3D	SphericalSpacecraft.radiationPressureAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, Vector3D flux) Compute the acceleration due to radiation pressure.
FieldVector3D<DerivativeStructure>	BoxAndSolarArraySpacecraft.radiationPressureAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, Vector3D flux, String paramName) Compute the acceleration due to radiation pressure, with parameters derivatives.
FieldVector3D<DerivativeStructure>	SphericalSpacecraft.radiationPressureAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, Vector3D flux, String paramName) Compute the acceleration due to radiation pressure, with parameters derivatives.

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

Constructor and Description
BoxAndSolarArraySpacecraft(BoxAndSolarArraySpacecraft.Facet[] facets, PVCoordinatesProvider sun, double solarArrayArea, Vector3D solarArrayAxis, AbsoluteDate referenceDate, Vector3D referenceNormal, double rotationRate, double dragCoeff, double absorptionCoeff, double reflectionCoeff) Build a spacecraft model with linear rotation of solar array.
BoxAndSolarArraySpacecraft(double xLength, double yLength, double zLength, PVCoordinatesProvider sun, double solarArrayArea, Vector3D solarArrayAxis, AbsoluteDate referenceDate, Vector3D referenceNormal, double rotationRate, double dragCoeff, double absorptionCoeff, double reflectionCoeff) Build a spacecraft model with linear rotation of solar array.

Uses of AbsoluteDate in org.orekit.forces.drag

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

Modifier and Type	Method and Description
AbsoluteDate	MarshallSolarActivityFutureEstimation.getMaxDate() Gets the available data range maximum date.
AbsoluteDate	DTM2000InputParameters.getMaxDate() Gets the available data range maximum date.
AbsoluteDate	JB2006InputParameters.getMaxDate() Gets the available data range maximum date.
AbsoluteDate	MarshallSolarActivityFutureEstimation.getMinDate() Gets the available data range minimum date.
AbsoluteDate	DTM2000InputParameters.getMinDate() Gets the available data range minimum date.
AbsoluteDate	JB2006InputParameters.getMinDate() Gets the available data range minimum date.

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

Modifier and Type	Method and Description
FieldVector3D<DerivativeStructure>	DragForce.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
FieldVector3D<DerivativeStructure>	DragSensitive.dragAcceleration(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass, double density, FieldVector3D<DerivativeStructure> relativeVelocity) Compute the acceleration due to drag, with state derivatives.
Vector3D	DragSensitive.dragAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, double density, Vector3D relativeVelocity) Compute the acceleration due to drag.
FieldVector3D<DerivativeStructure>	DragSensitive.dragAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, double density, Vector3D relativeVelocity, String paramName) Compute acceleration due to drag, with parameters derivatives.
double	MarshallSolarActivityFutureEstimation.get24HoursKp(AbsoluteDate date) The Kp index is derived from the Ap index.
double	DTM2000InputParameters.get24HoursKp(AbsoluteDate date) Get the last 24H mean geomagnetic index.
double	JB2006InputParameters.getAp(AbsoluteDate date) Get the Geomagnetic planetary 3-hour index Ap.
double	DTM2000.getDensity(AbsoluteDate date, Vector3D position, Frame frame) Get the local density.
double	Atmosphere.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	JB2006.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	JB2006InputParameters.getF10(AbsoluteDate date) Get the value of the instantaneous solar flux index (1e-22*Watt/(m²*Hertz)).
double	JB2006InputParameters.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	MarshallSolarActivityFutureEstimation.getInstantFlux(AbsoluteDate date) Get the value of the instantaneous solar flux.
double	DTM2000InputParameters.getInstantFlux(AbsoluteDate date) Get the value of the instantaneous solar flux.
double	MarshallSolarActivityFutureEstimation.getMeanFlux(AbsoluteDate date) Get the value of the mean solar flux.
double	DTM2000InputParameters.getMeanFlux(AbsoluteDate date) Get the value of the mean solar flux.
double	JB2006InputParameters.getS10(AbsoluteDate date) Get the EUV index (26-34 nm) scaled to F10.
double	JB2006InputParameters.getS10B(AbsoluteDate date) Get the EUV 81-day averaged centered index.
double	MarshallSolarActivityFutureEstimation.getThreeHourlyKP(AbsoluteDate date) Get the value of the 3 hours geomagnetic index.
double	DTM2000InputParameters.getThreeHourlyKP(AbsoluteDate date) Get the value of the 3 hours geomagnetic index.
Vector3D	DTM2000.getVelocity(AbsoluteDate date, Vector3D position, Frame frame) Get the inertial velocity of atmosphere molecules.
Vector3D	Atmosphere.getVelocity(AbsoluteDate date, Vector3D position, Frame frame) Get the inertial velocity of atmosphere molecules.
Vector3D	HarrisPriester.getVelocity(AbsoluteDate date, Vector3D position, Frame frame) Get the inertial velocity of atmosphere molecules.
Vector3D	JB2006.getVelocity(AbsoluteDate date, Vector3D position, Frame frame) Get the inertial velocity of atmosphere molecules.
Vector3D	SimpleExponentialAtmosphere.getVelocity(AbsoluteDate date, Vector3D position, Frame frame) Get the inertial velocity of atmosphere molecules.
double	JB2006InputParameters.getXM10(AbsoluteDate date) Get the MG2 index scaled to F10.
double	JB2006InputParameters.getXM10B(AbsoluteDate date) Get the MG2 81-day average centered index.

Uses of AbsoluteDate in org.orekit.forces.gravity

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

Modifier and Type	Method and Description
FieldVector3D<DerivativeStructure>	SolidTides.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
FieldVector3D<DerivativeStructure>	CunninghamAttractionModel.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
FieldVector3D<DerivativeStructure>	Relativity.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass)
FieldVector3D<DerivativeStructure>	ThirdBodyAttraction.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
FieldVector3D<DerivativeStructure>	OceanTides.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
FieldVector3D<DerivativeStructure>	DrozinerAttractionModel.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
FieldVector3D<DerivativeStructure>	HolmesFeatherstoneAttractionModel.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
FieldVector3D<DerivativeStructure>	NewtonianAttraction.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
double[]	HolmesFeatherstoneAttractionModel.gradient(AbsoluteDate date, Vector3D position) Compute the gradient of the non-central part of the gravity field.
HolmesFeatherstoneAttractionModel.GradientHessian	HolmesFeatherstoneAttractionModel.gradientHessian(AbsoluteDate date, Vector3D position) Compute both the gradient and the hessian of the non-central part of the gravity field.
double	HolmesFeatherstoneAttractionModel.nonCentralPart(AbsoluteDate date, Vector3D position) Compute the non-central part of the gravity field.
double	HolmesFeatherstoneAttractionModel.value(AbsoluteDate date, Vector3D position) 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 and Description
AbsoluteDate	SphericalHarmonicsProvider.getReferenceDate() Get the reference date for the harmonics.
AbsoluteDate	CachedNormalizedSphericalHarmonicsProvider.getReferenceDate() Get the reference date for the harmonics.

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

Modifier and Type	Method and Description
double	SphericalHarmonicsProvider.getOffset(AbsoluteDate date) Get the offset from reference date for the harmonics.
double	CachedNormalizedSphericalHarmonicsProvider.getOffset(AbsoluteDate date) Get the offset from reference date for the harmonics.
UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics	UnnormalizedSphericalHarmonicsProvider.onDate(AbsoluteDate date) Get the un-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.
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.

Uses of AbsoluteDate in org.orekit.forces.maneuvers

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

Modifier and Type	Method and Description
AbsoluteDate	SmallManeuverAnalyticalModel.getDate() Get the date of the maneuver.

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

Modifier and Type	Method and Description
FieldVector3D<DerivativeStructure>	ConstantThrustManeuver.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
void	ImpulseManeuver.init(SpacecraftState s0, AbsoluteDate t) Initialize event handler at the start of a propagation.

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

Constructor and Description
ConstantThrustManeuver(AbsoluteDate date, double duration, double thrust, double isp, Vector3D direction) Simple constructor for a constant direction and constant thrust.

Uses of AbsoluteDate in org.orekit.forces.radiation

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

Modifier and Type	Method and Description
FieldVector3D<DerivativeStructure>	SolarRadiationPressure.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
double	SolarRadiationPressure.getLightningRatio(Vector3D position, Frame frame, AbsoluteDate date) Get the lightning ratio ([0-1]).
FieldVector3D<DerivativeStructure>	RadiationSensitive.radiationPressureAcceleration(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass, FieldVector3D<DerivativeStructure> flux) Compute the acceleration due to radiation pressure, with state derivatives.
Vector3D	RadiationSensitive.radiationPressureAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, Vector3D flux) Compute the acceleration due to radiation pressure.
FieldVector3D<DerivativeStructure>	RadiationSensitive.radiationPressureAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, Vector3D flux, String paramName) Compute the acceleration due to radiation pressure, with parameters derivatives.

Uses of AbsoluteDate in org.orekit.frames

Methods in org.orekit.frames that return AbsoluteDate

Modifier and Type	Method and Description
AbsoluteDate	EOPEntry.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 and Description
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.
double	EOPHistory.getLOD(AbsoluteDate date) Get the LoD (Length of Day) value.
protected List<EOPEntry>	EOPHistory.getNeighbors(AbsoluteDate central) Get the entries surrounding a central date.
static Transform	FramesFactory.getNonInterpolatingTransform(Frame from, Frame to, AbsoluteDate date) Get the transform between two frames, suppressing all interpolation.
double[]	EOPHistory.getNonRotatinOriginNutationCorrection(AbsoluteDate date) Get the correction to the nutation parameters for Non-Rotating Origin paradigm.
PoleCorrection	EOPHistory.getPoleCorrection(AbsoluteDate date) Get the pole IERS Reference Pole correction.
TimeStampedPVCoordinates	TopocentricFrame.getPVCoordinates(AbsoluteDate date, Frame frame) Get the PVCoordinates of the topocentric frame origin in the selected frame.
double	TopocentricFrame.getRange(Vector3D extPoint, Frame frame, AbsoluteDate date) Get the range of a point with regards to the topocentric frame center point.
double	TopocentricFrame.getRangeRate(PVCoordinates extPV, Frame frame, AbsoluteDate date) Get the range rate of a point with regards to the topocentric frame center point.
Transform	InterpolatingTransformProvider.getTransform(AbsoluteDate date) Get the Transform corresponding to specified date.
Transform	EclipticProvider.getTransform(AbsoluteDate date)
Transform	HelmertTransformation.getTransform(AbsoluteDate date) Compute the transform at some date.
Transform	GTODProvider.getTransform(AbsoluteDate date) Get the transform from TOD at specified date.
Transform	FixedTransformProvider.getTransform(AbsoluteDate date) Get the Transform corresponding to specified date.
Transform	TransformProvider.getTransform(AbsoluteDate date) Get the Transform corresponding to specified date.
Transform	Frame.getTransformTo(Frame destination, AbsoluteDate date) Get the transform from the instance to another frame.
double	EOPHistory.getUT1MinusUTC(AbsoluteDate date) Get the UT1-UTC value.
protected boolean	EOPHistory.hasDataFor(AbsoluteDate date) Check if the cache has data for the given date using EOPHistory.getStartDate() and EOPHistory.getEndDate().
static Transform	Transform.interpolate(AbsoluteDate date, boolean useVelocities, boolean useRotationRates, Collection<Transform> sample) Deprecated. as of 7.0, replaced with Transform.interpolate(AbsoluteDate, CartesianDerivativesFilter, AngularDerivativesFilter, Collection)
static Transform	Transform.interpolate(AbsoluteDate date, CartesianDerivativesFilter cFilter, AngularDerivativesFilter aFilter, Collection<Transform> sample) Interpolate a transform from a sample set of existing transforms.
Transform	Transform.interpolate(AbsoluteDate interpolationDate, Collection<Transform> sample) Get an interpolated instance.
Transform	LOFType.transformFromInertial(AbsoluteDate date, PVCoordinates pv) Get the transform from an inertial frame defining position-velocity and the local orbital frame.
void	UpdatableFrame.updateTransform(Frame f1, Frame f2, Transform f1Tof2, AbsoluteDate date) Update the transform from parent frame implicitly according to two other frames.

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

Constructor and Description
HelmertTransformation(AbsoluteDate epoch, double t1, double t2, double t3, double r1, double r2, double r3, double t1Dot, double t2Dot, double t3Dot, double r1Dot, double r2Dot, double r3Dot) Build a transform from its primitive operations.
InterpolatingTransformProvider(TransformProvider rawProvider, boolean useVelocities, boolean useRotationRates, AbsoluteDate earliest, AbsoluteDate latest, int gridPoints, double step, int maxSlots, double maxSpan, double newSlotInterval) Deprecated. as of 7.0, replaced with InterpolatingTransformProvider.InterpolatingTransformProvider(TransformProvider, CartesianDerivativesFilter, AngularDerivativesFilter, AbsoluteDate, AbsoluteDate, int, double, int, double, double)
InterpolatingTransformProvider(TransformProvider rawProvider, CartesianDerivativesFilter cFilter, AngularDerivativesFilter aFilter, AbsoluteDate earliest, AbsoluteDate latest, int gridPoints, double step, int maxSlots, double maxSpan, double newSlotInterval) Simple constructor.
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, 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, Transform first, Transform second) Build a transform by combining two existing ones.
Transform(AbsoluteDate date, Vector3D translation) Build a translation 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.

Uses of AbsoluteDate in org.orekit.orbits

Methods in org.orekit.orbits that return AbsoluteDate

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

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

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

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

Constructor and 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, PositionAngle type, Frame frame, AbsoluteDate date, double mu) Creates a new instance.
CircularOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu) Constructor from cartesian parameters.
EquinoctialOrbit(double a, double ex, double ey, double hx, double hy, double l, PositionAngle type, Frame frame, AbsoluteDate date, double mu) Creates a new instance.
EquinoctialOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu) Constructor from cartesian parameters.
KeplerianOrbit(double a, double e, double i, double pa, double raan, double anomaly, PositionAngle type, Frame frame, AbsoluteDate date, double mu) Creates a new instance.
KeplerianOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu) Constructor from cartesian parameters.
Orbit(Frame frame, AbsoluteDate date, double mu) Default constructor.

Uses of AbsoluteDate in org.orekit.propagation

Methods in org.orekit.propagation that return AbsoluteDate

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

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

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

Uses of AbsoluteDate in org.orekit.propagation.analytical

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

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

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

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

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

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

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

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

Modifier and Type	Method and Description
TLE	TLESeries.getClosestTLE(AbsoluteDate date) Get the closest TLE to the selected date.
protected double	TLEPropagator.getMass(AbsoluteDate date) Get the mass.
PVCoordinates	TLESeries.getPVCoordinates(AbsoluteDate date) Get the extrapolated position and velocity from an initial date.
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 and Description

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

Uses of AbsoluteDate in org.orekit.propagation.conversion

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

Modifier and Type	Method and Description
protected AbsoluteDate	AbstractPropagatorConverter.getDate() Get the date of the initial state.

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

Modifier and Type	Method and Description
Propagator	PropagatorBuilder.buildPropagator(AbsoluteDate date, double[] parameters) Build a propagator.
NumericalPropagator	NumericalPropagatorBuilder.buildPropagator(AbsoluteDate date, double[] parameters) Build a propagator.
Propagator	TLEPropagatorBuilder.buildPropagator(AbsoluteDate date, double[] parameters) Build a propagator.
Propagator	KeplerianPropagatorBuilder.buildPropagator(AbsoluteDate date, double[] parameters) Build a propagator.
Propagator	EcksteinHechlerPropagatorBuilder.buildPropagator(AbsoluteDate date, double[] parameters) Build a propagator.

Uses of AbsoluteDate in org.orekit.propagation.events

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

Modifier and Type	Method and Description
AbsoluteDate	DateDetector.getDate() Get the current event date according to the propagator.
AbsoluteDate	EventState.getEventTime() Get the occurrence time of the event triggered in the current step.

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

Modifier and Type	Method and Description
void	DateDetector.addEventDate(AbsoluteDate target) Add an event date.
void	EventState.init(SpacecraftState s0, AbsoluteDate t) Initialize event handler at the start of a propagation.
void	EventFilter.init(SpacecraftState s0, AbsoluteDate t) Initialize event handler at the start of a propagation.
void	AbstractDetector.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	EventDetector.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 and Description
DateDetector(AbsoluteDate target) Build a new instance.

Uses of AbsoluteDate in org.orekit.propagation.integration

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

Modifier and Type	Method and 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.

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

Modifier and Type	Method and Description
protected SpacecraftState	IntegratedEphemeris.basicPropagate(AbsoluteDate date) Propagate an orbit without any fancy features.
protected void	AbstractIntegratedPropagator.beforeIntegration(SpacecraftState initialState, AbsoluteDate tEnd) Method called just before integration.
protected abstract StateMapper	AbstractIntegratedPropagator.createMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame) Create a mapper between raw double components and spacecraft state.
protected double	IntegratedEphemeris.getMass(AbsoluteDate date) Get the mass.
TimeStampedPVCoordinates	IntegratedEphemeris.getPVCoordinates(AbsoluteDate date, Frame frame) Get the PVCoordinates of the body in the selected frame.
double	StateMapper.mapDateToDouble(AbsoluteDate date) Map a date to a raw double time offset.
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 SpacecraftState	AbstractIntegratedPropagator.propagate(AbsoluteDate tEnd, boolean activateHandlers) Propagation with or without event detection.
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 and Description
IntegratedEphemeris(AbsoluteDate startDate, AbsoluteDate minDate, AbsoluteDate maxDate, StateMapper mapper, boolean meanOrbit, ContinuousOutputModel model, Map<String,double[]> unmanaged, List<AdditionalStateProvider> providers, String[] equations) Creates a new instance of IntegratedEphemeris.
StateMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame) Simple constructor.

Uses of AbsoluteDate in org.orekit.propagation.numerical

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

Modifier and Type	Method and Description
FieldVector3D<DerivativeStructure>	Jacobianizer.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration and derivatives with respect to state.
protected StateMapper	NumericalPropagator.createMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame) Create a mapper between raw double components and spacecraft state.
TimeStampedPVCoordinates	NumericalPropagator.getPVCoordinates(AbsoluteDate date, Frame frame) Get the PVCoordinates of the body in the selected frame.

Uses of AbsoluteDate in org.orekit.propagation.sampling

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

Modifier and Type	Method and Description
AbsoluteDate	OrekitStepInterpolator.getCurrentDate() Get the current grid date.
AbsoluteDate	OrekitStepInterpolator.getInterpolatedDate() Get the interpolated date.
AbsoluteDate	OrekitStepInterpolator.getPreviousDate() Get the previous grid date.

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

Modifier and Type	Method and Description
void	OrekitStepHandlerMultiplexer.init(SpacecraftState s0, AbsoluteDate t) Initialize step handler at the start of a propagation.
void	OrekitStepNormalizer.init(SpacecraftState s0, AbsoluteDate t) Initialize step handler at the start of a propagation.
void	OrekitFixedStepHandler.init(SpacecraftState s0, AbsoluteDate t) Initialize step handler at the start of a propagation.
void	OrekitStepHandler.init(SpacecraftState s0, AbsoluteDate t) Initialize step handler at the start of a propagation.
void	OrekitStepInterpolator.setInterpolatedDate(AbsoluteDate date) Set the interpolated date.

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 and Description
protected void	DSSTPropagator.beforeIntegration(SpacecraftState initialState, AbsoluteDate tEnd) Method called just before integration.
protected StateMapper	DSSTPropagator.createMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngle positionAngleType, 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 and Description
double[]	AbstractGaussianContribution.getShortPeriodicVariations(AbsoluteDate date, double[] meanElements) Computes the short periodic variations.
double[]	DSSTThirdBody.getShortPeriodicVariations(AbsoluteDate date, double[] meanElements) Computes the short periodic variations.
double[]	DSSTCentralBody.getShortPeriodicVariations(AbsoluteDate date, double[] meanElements) Computes the short periodic variations.
double[]	DSSTForceModel.getShortPeriodicVariations(AbsoluteDate date, double[] meanElements) Computes the short periodic variations.

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

Uses of AbsoluteDate in org.orekit.time

Fields in org.orekit.time declared as AbsoluteDate

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

Methods in org.orekit.time that return AbsoluteDate

Modifier and Type	Method and Description
static AbsoluteDate	AbsoluteDate.createBesselianEpoch(double besselianEpoch) Build an instance corresponding to a Besselian Epoch (BE).
static AbsoluteDate	AbsoluteDate.createGPSDate(int weekNumber, double milliInWeek) Build an instance corresponding to a GPS date.
static AbsoluteDate	AbsoluteDate.createJulianEpoch(double julianEpoch) Build an instance corresponding to a Julian Epoch (JE).
AbsoluteDate	AbsoluteDate.getDate() Get the date.
AbsoluteDate	TimeStamped.getDate() Get the date.
AbsoluteDate	UTCScale.getFirstKnownLeapSecond() Get the date of the first known leap second.
AbsoluteDate	UTCScale.getLastKnownLeapSecond() Get the date of the last known leap second.
static AbsoluteDate	AbsoluteDate.parseCCSDSCalendarSegmentedTimeCode(byte preambleField, byte[] timeField) Build an instance from a CCSDS Calendar Segmented Time Code (CCS).
static AbsoluteDate	AbsoluteDate.parseCCSDSDaySegmentedTimeCode(byte preambleField, byte[] timeField, DateComponents agencyDefinedEpoch) Build an instance from a CCSDS Day Segmented Time Code (CDS).
static AbsoluteDate	AbsoluteDate.parseCCSDSUnsegmentedTimeCode(byte preambleField1, byte preambleField2, byte[] timeField, AbsoluteDate agencyDefinedEpoch) Build an instance from a CCSDS Unsegmented Time Code (CUC).
AbsoluteDate	AbsoluteDate.shiftedBy(double dt) Get a time-shifted date.

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

Modifier and Type	Method and Description
int	AbsoluteDate.compareTo(AbsoluteDate date) Compare the instance with another date.
double	AbsoluteDate.durationFrom(AbsoluteDate instant) Compute the physically elapsed duration between two instants.
double	UTCScale.getLeap(AbsoluteDate date) Get the value of the previous leap.
boolean	UTCScale.insideLeap(AbsoluteDate date) Check if date is within a leap second introduction.
T	TimeInterpolable.interpolate(AbsoluteDate date, Collection<T> sample) Get an interpolated instance.
double	AbsoluteDate.offsetFrom(AbsoluteDate instant, TimeScale timeScale) Compute the apparent clock offset between two instant in the perspective of a specific time scale.
double	GMSTScale.offsetFromTAI(AbsoluteDate date) Get the offset to convert locations from TAIScale to instance.
double	GalileoScale.offsetFromTAI(AbsoluteDate date) Get the offset to convert locations from TAIScale to instance.
double	UTCScale.offsetFromTAI(AbsoluteDate date) Get the offset to convert locations from TAIScale to instance.
double	TAIScale.offsetFromTAI(AbsoluteDate taiTime) Get the offset to convert locations from TAIScale to instance.
double	TCGScale.offsetFromTAI(AbsoluteDate date) Get the offset to convert locations from TAIScale to instance.
double	TimeScale.offsetFromTAI(AbsoluteDate date) Get the offset to convert locations from TAIScale to instance.
double	UT1Scale.offsetFromTAI(AbsoluteDate date) Get the offset to convert locations from TAIScale to instance.
double	GPSScale.offsetFromTAI(AbsoluteDate date) Get the offset to convert locations from TAIScale to instance.
double	TCBScale.offsetFromTAI(AbsoluteDate date) Get the offset to convert locations from TAIScale to instance.
double	TDBScale.offsetFromTAI(AbsoluteDate date) Get the offset to convert locations from TAIScale to instance.
double	TTScale.offsetFromTAI(AbsoluteDate date) Get the offset to convert locations from TAIScale to instance.
static AbsoluteDate	AbsoluteDate.parseCCSDSUnsegmentedTimeCode(byte preambleField1, byte preambleField2, byte[] timeField, AbsoluteDate agencyDefinedEpoch) Build an instance from a CCSDS Unsegmented Time Code (CUC).
T	TimeFunction.value(AbsoluteDate date) Compute a function of time.

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

Constructor and Description
AbsoluteDate(AbsoluteDate since, double elapsedDuration) Build an instance from an elapsed duration since to another instant.
AbsoluteDate(AbsoluteDate reference, double apparentOffset, TimeScale timeScale) Build an instance from an apparent clock offset with respect to another instant in the perspective of a specific time scale.

Uses of AbsoluteDate in org.orekit.utils

Methods in org.orekit.utils that return AbsoluteDate

Modifier and Type	Method and Description
AbsoluteDate	TimeStampedFieldPVCoordinates.getDate() Get the date.
AbsoluteDate	TimeStampedFieldAngularCoordinates.getDate() Get the date.
AbsoluteDate	TimeStampedAngularCoordinates.getDate() Get the date.
AbsoluteDate	TimeStampedPVCoordinates.getDate() Get the date.
AbsoluteDate	IERSConventions.getNutationReferenceEpoch() Get the reference epoch for fundamental nutation arguments.
AbsoluteDate	SecularAndHarmonic.getReferenceDate() Get the reference date.

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

Modifier and Type	Method and Description
void	SecularAndHarmonic.addPoint(AbsoluteDate date, double osculatingValue) Add a 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.
DerivativeStructure	IERSConventions.dsEvaluateTC(AbsoluteDate date) Evaluate the date offset between the current date and the reference date.
double	IERSConventions.evaluateTC(AbsoluteDate date) Evaluate the date offset between the current date and the reference date.
List<T>	TimeStampedGenerator.generate(T existing, AbsoluteDate date) Generate a chronologically sorted list of entries to be cached.
List<T>	GenericTimeStampedCache.getNeighbors(AbsoluteDate central) Get the entries surrounding a central date.
List<T>	ImmutableTimeStampedCache.getNeighbors(AbsoluteDate central) Get the entries surrounding a central date.
List<T>	TimeStampedCache.getNeighbors(AbsoluteDate central) Get the entries surrounding a central date.
TimeStampedPVCoordinates	PVCoordinatesProvider.getPVCoordinates(AbsoluteDate date, Frame frame) Get the PVCoordinates of the body in the selected frame.
static TimeStampedAngularCoordinates	TimeStampedAngularCoordinates.interpolate(AbsoluteDate date, AngularDerivativesFilter filter, Collection<TimeStampedAngularCoordinates> sample) Interpolate angular coordinates.
static <T extends RealFieldElement<T>> TimeStampedFieldAngularCoordinates<T>	TimeStampedFieldAngularCoordinates.interpolate(AbsoluteDate date, AngularDerivativesFilter filter, Collection<TimeStampedFieldAngularCoordinates<T>> sample) Interpolate angular coordinates.
static AngularCoordinates	AngularCoordinates.interpolate(AbsoluteDate date, boolean useRotationRates, Collection<Pair<AbsoluteDate,AngularCoordinates>> sample) Deprecated. since 7.0 replaced with TimeStampedAngularCoordinates.interpolate(AbsoluteDate, AngularDerivativesFilter, Collection)
static <T extends RealFieldElement<T>> FieldAngularCoordinates<T>	FieldAngularCoordinates.interpolate(AbsoluteDate date, boolean useRotationRates, Collection<Pair<AbsoluteDate,FieldAngularCoordinates<T>>> sample) Deprecated. since 7.0 replaced with TimeStampedFieldAngularCoordinates.interpolate(AbsoluteDate, AngularDerivativesFilter, Collection)
static <T extends RealFieldElement<T>> FieldPVCoordinates<T>	FieldPVCoordinates.interpolate(AbsoluteDate date, boolean useVelocities, Collection<Pair<AbsoluteDate,FieldPVCoordinates<T>>> sample) Deprecated. as of 7.0, replaced with TimeStampedFieldPVCoordinates.interpolate(AbsoluteDate, CartesianDerivativesFilter, Collection)
static PVCoordinates	PVCoordinates.interpolate(AbsoluteDate date, boolean useVelocities, Collection<Pair<AbsoluteDate,PVCoordinates>> sample) Deprecated. since 7.0 replaced with TimeStampedPVCoordinates.interpolate(AbsoluteDate, CartesianDerivativesFilter, Collection)
static <T extends RealFieldElement<T>> TimeStampedFieldPVCoordinates<T>	TimeStampedFieldPVCoordinates.interpolate(AbsoluteDate date, CartesianDerivativesFilter filter, Collection<TimeStampedFieldPVCoordinates<T>> sample) Interpolate position-velocity.
static TimeStampedPVCoordinates	TimeStampedPVCoordinates.interpolate(AbsoluteDate date, CartesianDerivativesFilter filter, Collection<TimeStampedPVCoordinates> sample) Interpolate position-velocity.
double	SecularAndHarmonic.meanDerivative(AbsoluteDate date, int degree, int harmonics) Get mean derivative, truncated to first components.
double	SecularAndHarmonic.meanSecondDerivative(AbsoluteDate date, int degree, int harmonics) Get mean second derivative, truncated to first components.
double	SecularAndHarmonic.meanValue(AbsoluteDate date, int degree, int harmonics) Get mean value, truncated to first components.
double	SecularAndHarmonic.osculatingDerivative(AbsoluteDate date) Get fitted osculating derivative.
double	SecularAndHarmonic.osculatingSecondDerivative(AbsoluteDate date) Get fitted osculating second derivative.
double	SecularAndHarmonic.osculatingValue(AbsoluteDate date) Get fitted osculating value.
void	SecularAndHarmonic.resetFitting(AbsoluteDate date, double... initialGuess) Reset fitting.
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.

Method parameters in org.orekit.utils with type arguments of type AbsoluteDate

Modifier and Type	Method and Description
static AngularCoordinates	AngularCoordinates.interpolate(AbsoluteDate date, boolean useRotationRates, Collection<Pair<AbsoluteDate,AngularCoordinates>> sample) Deprecated. since 7.0 replaced with TimeStampedAngularCoordinates.interpolate(AbsoluteDate, AngularDerivativesFilter, Collection)
static <T extends RealFieldElement<T>> FieldAngularCoordinates<T>	FieldAngularCoordinates.interpolate(AbsoluteDate date, boolean useRotationRates, Collection<Pair<AbsoluteDate,FieldAngularCoordinates<T>>> sample) Deprecated. since 7.0 replaced with TimeStampedFieldAngularCoordinates.interpolate(AbsoluteDate, AngularDerivativesFilter, Collection)
static <T extends RealFieldElement<T>> FieldPVCoordinates<T>	FieldPVCoordinates.interpolate(AbsoluteDate date, boolean useVelocities, Collection<Pair<AbsoluteDate,FieldPVCoordinates<T>>> sample) Deprecated. as of 7.0, replaced with TimeStampedFieldPVCoordinates.interpolate(AbsoluteDate, CartesianDerivativesFilter, Collection)
static PVCoordinates	PVCoordinates.interpolate(AbsoluteDate date, boolean useVelocities, Collection<Pair<AbsoluteDate,PVCoordinates>> sample) Deprecated. since 7.0 replaced with TimeStampedPVCoordinates.interpolate(AbsoluteDate, CartesianDerivativesFilter, Collection)

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

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