Uses of Class
org.orekit.time.FieldAbsoluteDate

Packages that use FieldAbsoluteDate

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.measurements	The measurements package defines everything that is related to orbit determination measurements.
org.orekit.forces	This package provides the interface for force models that will be used by the NumericalPropagator, as well as some classical spacecraft models for surface forces (spherical, box and solar array ...).
org.orekit.forces.drag	This package provides all drag-related forces.
org.orekit.forces.gravity	This package provides all gravity-related forces.
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.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.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.orbits	This package provides classes to represent orbits.
org.orekit.propagation	Propagation
org.orekit.propagation.analytical	Top level package for analytical propagators.
org.orekit.propagation.events	This package provides interfaces and classes dealing with events occurring during propagation.
org.orekit.propagation.events.handlers	This package provides an interface and classes dealing with events occurrence only.
org.orekit.propagation.integration	Utilities for integration-based propagators (both numerical and semi-analytical).
org.orekit.propagation.numerical	Top level package for numerical propagators.
org.orekit.propagation.sampling	This package provides interfaces and classes dealing with step handling during propagation.
org.orekit.propagation.semianalytical.dsst	This package provides an implementation of the Draper Semi-analytical Satellite Theory (DSST).
org.orekit.propagation.semianalytical.dsst.forces	This package provides force models for Draper Semi-analytical Satellite Theory (DSST).
org.orekit.propagation.semianalytical.dsst.utilities	This package provides utilities for Draper Semi-analytical Satellite Theory (DSST).
org.orekit.time	This independent package provides classes to handle epochs, time scales, and to compare instants together.
org.orekit.utils	This package provides useful objects.

Uses of FieldAbsoluteDate in org.orekit.attitudes

Methods in org.orekit.attitudes that return FieldAbsoluteDate

Modifier and Type	Method and Description
FieldAbsoluteDate<T>	FieldAttitude.getDate() Get the date of attitude parameters.

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

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

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

Constructor and Description
FieldAttitude(FieldAbsoluteDate<T> date, Frame referenceFrame, FieldAngularCoordinates<T> orientation) Creates a new instance.
FieldAttitude(FieldAbsoluteDate<T> date, Frame referenceFrame, FieldRotation<T> attitude, FieldVector3D<T> spin, FieldVector3D<T> acceleration) Creates a new instance.
FieldAttitude(FieldAbsoluteDate<T> date, Frame referenceFrame, Rotation attitude, Vector3D spin, Vector3D acceleration, Field<T> field) Creates a new instance.

Uses of FieldAbsoluteDate in org.orekit.bodies

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

Modifier and Type	Method and Description
<T extends RealFieldElement<T>> FieldVector3D<T>	OneAxisEllipsoid.getCartesianIntersectionPoint(FieldLine<T> line, FieldVector3D<T> close, Frame frame, FieldAbsoluteDate<T> date) Get the intersection point of a line with the surface of the body.
<T extends RealFieldElement<T>> FieldGeodeticPoint<T>	OneAxisEllipsoid.getIntersectionPoint(FieldLine<T> line, FieldVector3D<T> close, Frame frame, FieldAbsoluteDate<T> date) Get the intersection point of a line with the surface of the body.
<T extends RealFieldElement<T>> FieldGeodeticPoint<T>	BodyShape.getIntersectionPoint(FieldLine<T> line, FieldVector3D<T> close, Frame frame, FieldAbsoluteDate<T> date) Get the intersection point of a line with the surface of the body.
default <T extends RealFieldElement<T>> FieldVector3D<T>	IAUPole.getNode(FieldAbsoluteDate<T> date) Get the body Q Node direction in ICRF frame.
<T extends RealFieldElement<T>> FieldVector3D<T>	IAUPole.getPole(FieldAbsoluteDate<T> date) Get the body North pole direction in ICRF frame.
<T extends RealFieldElement<T>> T	IAUPole.getPrimeMeridianAngle(FieldAbsoluteDate<T> date) Get the prime meridian angle.
<T extends RealFieldElement<T>> FieldPVCoordinates<T>	JPLEphemeridesLoader.RawPVProvider.getRawPV(FieldAbsoluteDate<T> date) Get the position-velocity at date.
<T extends RealFieldElement<T>> FieldGeodeticPoint<T>	OneAxisEllipsoid.transform(FieldVector3D<T> point, Frame frame, FieldAbsoluteDate<T> date) Transform a Cartesian point to a surface-relative point.
<T extends RealFieldElement<T>> FieldGeodeticPoint<T>	BodyShape.transform(FieldVector3D<T> point, Frame frame, FieldAbsoluteDate<T> date) Transform a Cartesian point to a surface-relative point.

Uses of FieldAbsoluteDate in org.orekit.data

Methods in org.orekit.data that return FieldAbsoluteDate

Modifier and Type	Method and Description
FieldAbsoluteDate<T>	FieldDelaunayArguments.getDate() Get the date.

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

Modifier and Type	Method and Description
<T extends RealFieldElement<T>> FieldBodiesElements<T>	FundamentalNutationArguments.evaluateAll(FieldAbsoluteDate<T> date) Evaluate all fundamental arguments for the current date (Delaunay plus planetary).

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

Constructor and Description
FieldBodiesElements(FieldAbsoluteDate<T> date, T tc, T gamma, T gammaDot, T l, T lDot, T lPrime, T lPrimeDot, T f, T fDot, T d, T dDot, T omega, T omegaDot, T lMe, T lMeDot, T lVe, T lVeDot, T lE, T lEDot, T lMa, T lMaDot, T lJu, T lJuDot, T lSa, T lSaDot, T lUr, T lUrDot, T lNe, T lNeDot, T pa, T paDot) Simple constructor.
FieldDelaunayArguments(FieldAbsoluteDate<T> date, T tc, T gamma, T gammaDot, T l, T lDot, T lPrime, T lPrimeDot, T f, T fDot, T d, T dDot, T omega, T omegaDot) Simple constructor.

Uses of FieldAbsoluteDate in org.orekit.estimation.measurements

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

Modifier and Type	Method and Description
FieldTransform<DerivativeStructure>	GroundStation.getOffsetToInertial(Frame inertial, FieldAbsoluteDate<DerivativeStructure> offsetCompensatedDate, DSFactory factory, Map<String,Integer> indices) Get the transform between offset frame and inertial frame with derivatives.
FieldTransform<DerivativeStructure>	EstimatedEarthFrameProvider.getTransform(FieldAbsoluteDate<DerivativeStructure> date, DSFactory factory, Map<String,Integer> indices) Get the transform with derivatives.
<T extends RealFieldElement<T>> FieldTransform<T>	EstimatedEarthFrameProvider.getTransform(FieldAbsoluteDate<T> date) Get the FieldTransform corresponding to specified date.
static <T extends RealFieldElement<T>> T	AbstractMeasurement.signalTimeOfFlight(TimeStampedFieldPVCoordinates<T> adjustableEmitterPV, FieldVector3D<T> receiverPosition, FieldAbsoluteDate<T> signalArrivalDate) Compute propagation delay on a link leg (typically downlink or uplink).

Uses of FieldAbsoluteDate in org.orekit.forces

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

Modifier and Type	Method and Description
<T extends RealFieldElement<T>> FieldVector3D<T>	BoxAndSolarArraySpacecraft.dragAcceleration(FieldAbsoluteDate<T> date, Frame frame, FieldVector3D<T> position, FieldRotation<T> rotation, T mass, T density, FieldVector3D<T> relativeVelocity, T[] parameters) Compute the acceleration due to drag.
<T extends RealFieldElement<T>> FieldVector3D<T>	BoxAndSolarArraySpacecraft.getNormal(FieldAbsoluteDate<T> date, Frame frame, FieldVector3D<T> position, FieldRotation<T> rotation) Get solar array normal in spacecraft frame.
<T extends RealFieldElement<T>> FieldVector3D<T>	BoxAndSolarArraySpacecraft.radiationPressureAcceleration(FieldAbsoluteDate<T> date, Frame frame, FieldVector3D<T> position, FieldRotation<T> rotation, T mass, FieldVector3D<T> flux, T[] parameters) Compute the acceleration due to radiation pressure.

Uses of FieldAbsoluteDate in org.orekit.forces.drag

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

Modifier and Type	Method and Description
<T extends RealFieldElement<T>> FieldVector3D<T>	DragSensitive.dragAcceleration(FieldAbsoluteDate<T> date, Frame frame, FieldVector3D<T> position, FieldRotation<T> rotation, T mass, T density, FieldVector3D<T> relativeVelocity, T[] parameters) Compute the acceleration due to drag.
<T extends RealFieldElement<T>> FieldVector3D<T>	IsotropicDrag.dragAcceleration(FieldAbsoluteDate<T> date, Frame frame, FieldVector3D<T> position, FieldRotation<T> rotation, T mass, T density, FieldVector3D<T> relativeVelocity, T[] parameters) Compute the acceleration due to drag.

Uses of FieldAbsoluteDate in org.orekit.forces.gravity

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

Modifier and Type	Method and Description
<T extends RealFieldElement<T>> T[]	HolmesFeatherstoneAttractionModel.gradient(FieldAbsoluteDate<T> date, FieldVector3D<T> position, T mu) Compute the gradient of the non-central part of the gravity field.

Uses of FieldAbsoluteDate in org.orekit.forces.radiation

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

Modifier and Type	Method and Description
<T extends RealFieldElement<T>> T	SolarRadiationPressure.getLightingRatio(FieldVector3D<T> position, Frame frame, FieldAbsoluteDate<T> date) Get the lighting ratio ([0-1]).
<T extends RealFieldElement<T>> FieldVector3D<T>	IsotropicRadiationSingleCoefficient.radiationPressureAcceleration(FieldAbsoluteDate<T> date, Frame frame, FieldVector3D<T> position, FieldRotation<T> rotation, T mass, FieldVector3D<T> flux, T[] parameters) Compute the acceleration due to radiation pressure.
<T extends RealFieldElement<T>> FieldVector3D<T>	RadiationSensitive.radiationPressureAcceleration(FieldAbsoluteDate<T> date, Frame frame, FieldVector3D<T> position, FieldRotation<T> rotation, T mass, FieldVector3D<T> flux, T[] parameters) Compute the acceleration due to radiation pressure.
<T extends RealFieldElement<T>> FieldVector3D<T>	IsotropicRadiationClassicalConvention.radiationPressureAcceleration(FieldAbsoluteDate<T> date, Frame frame, FieldVector3D<T> position, FieldRotation<T> rotation, T mass, FieldVector3D<T> flux, T[] parameters) Compute the acceleration due to radiation pressure.
<T extends RealFieldElement<T>> FieldVector3D<T>	IsotropicRadiationCNES95Convention.radiationPressureAcceleration(FieldAbsoluteDate<T> date, Frame frame, FieldVector3D<T> position, FieldRotation<T> rotation, T mass, FieldVector3D<T> flux, T[] parameters) Compute the acceleration due to radiation pressure.

Uses of FieldAbsoluteDate in org.orekit.frames

Methods in org.orekit.frames that return FieldAbsoluteDate

Modifier and Type	Method and Description
FieldAbsoluteDate<T>	FieldTransform.getFieldDate() Get the date.

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

Modifier and Type	Method and Description
<T extends RealFieldElement<T>> T	TopocentricFrame.getAzimuth(FieldVector3D<T> extPoint, Frame frame, FieldAbsoluteDate<T> date) Get the azimuth of a point with regards to the topocentric frame center point.
<T extends RealFieldElement<T>> T	TopocentricFrame.getElevation(FieldVector3D<T> extPoint, Frame frame, FieldAbsoluteDate<T> date) Get the elevation of a point with regards to the local point.
<T extends RealFieldElement<T>> T[]	EOPHistory.getEquinoxNutationCorrection(FieldAbsoluteDate<T> date) Get the correction to the nutation parameters for equinox-based paradigm.
<T extends RealFieldElement<T>> T	EOPHistory.getLOD(FieldAbsoluteDate<T> date) Get the LoD (Length of Day) value.
static <T extends RealFieldElement<T>> FieldTransform<T>	FramesFactory.getNonInterpolatingTransform(Frame from, Frame to, FieldAbsoluteDate<T> date) Get the transform between two frames, suppressing all interpolation.
<T extends RealFieldElement<T>> T[]	EOPHistory.getNonRotatinOriginNutationCorrection(FieldAbsoluteDate<T> date) Get the correction to the nutation parameters for Non-Rotating Origin paradigm.
<T extends RealFieldElement<T>> FieldPoleCorrection<T>	EOPHistory.getPoleCorrection(FieldAbsoluteDate<T> date) Get the pole IERS Reference Pole correction.
<T extends RealFieldElement<T>> T	TopocentricFrame.getRange(FieldVector3D<T> extPoint, Frame frame, FieldAbsoluteDate<T> date) Get the range of a point with regards to the topocentric frame center point.
<T extends RealFieldElement<T>> T	TopocentricFrame.getRangeRate(FieldPVCoordinates<T> extPV, Frame frame, FieldAbsoluteDate<T> date) Get the range rate of a point with regards to the topocentric frame center point.
<T extends RealFieldElement<T>> FieldTransform<T>	FixedTransformProvider.getTransform(FieldAbsoluteDate<T> date) Get the FieldTransform corresponding to specified date.
<T extends RealFieldElement<T>> FieldTransform<T>	EclipticProvider.getTransform(FieldAbsoluteDate<T> date)
<T extends RealFieldElement<T>> FieldTransform<T>	TransformProvider.getTransform(FieldAbsoluteDate<T> date) Get the FieldTransform corresponding to specified date.
<T extends RealFieldElement<T>> FieldTransform<T>	InterpolatingTransformProvider.getTransform(FieldAbsoluteDate<T> date) Get the FieldTransform corresponding to specified date.
<T extends RealFieldElement<T>> FieldTransform<T>	L1TransformProvider.getTransform(FieldAbsoluteDate<T> date) Get the FieldTransform corresponding to specified date.
<T extends RealFieldElement<T>> FieldTransform<T>	GTODProvider.getTransform(FieldAbsoluteDate<T> date) Get the FieldTransform corresponding to specified date.
<T extends RealFieldElement<T>> FieldTransform<T>	HelmertTransformation.getTransform(FieldAbsoluteDate<T> date) Get the FieldTransform corresponding to specified date.
<T extends RealFieldElement<T>> FieldTransform<T>	ITRFVersion.Converter.getTransform(FieldAbsoluteDate<T> date) Get the FieldTransform corresponding to specified date.
<T extends RealFieldElement<T>> FieldTransform<T>	ShiftingTransformProvider.getTransform(FieldAbsoluteDate<T> date) Get the FieldTransform corresponding to specified date.
<T extends RealFieldElement<T>> FieldTransform<T>	Frame.getTransformTo(Frame destination, FieldAbsoluteDate<T> date) Get the transform from the instance to another frame.
<T extends RealFieldElement<T>> T	EOPHistory.getUT1MinusUTC(FieldAbsoluteDate<T> date) Get the UT1-UTC value.
static <T extends RealFieldElement<T>> FieldTransform<T>	FieldTransform.interpolate(FieldAbsoluteDate<T> date, CartesianDerivativesFilter cFilter, AngularDerivativesFilter aFilter, Collection<FieldTransform<T>> sample) Interpolate a transform from a sample set of existing transforms.
static <T extends RealFieldElement<T>> FieldTransform<T>	FieldTransform.interpolate(FieldAbsoluteDate<T> date, CartesianDerivativesFilter cFilter, AngularDerivativesFilter aFilter, Stream<FieldTransform<T>> sample) Interpolate a transform from a sample set of existing transforms.
static <T extends RealFieldElement<T>> FieldTransform<T>	FieldTransform.interpolate(FieldAbsoluteDate<T> interpolationDate, Collection<FieldTransform<T>> sample) Interpolate a transform from a sample set of existing transforms.
<T extends RealFieldElement<T>> FieldTransform<T>	LOFType.transformFromInertial(FieldAbsoluteDate<T> date, FieldPVCoordinates<T> pv) Get the transform from an inertial frame defining position-velocity and the local orbital frame.

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

Constructor and Description
FieldTransform(FieldAbsoluteDate<T> date, FieldAngularCoordinates<T> angular) Build a rotation transform.
FieldTransform(FieldAbsoluteDate<T> date, FieldPVCoordinates<T> cartesian) Build a translation transform, with its first time derivative.
FieldTransform(FieldAbsoluteDate<T> date, FieldRotation<T> rotation) Build a rotation transform.
FieldTransform(FieldAbsoluteDate<T> date, FieldRotation<T> rotation, FieldVector3D<T> rotationRate) Build a rotation transform.
FieldTransform(FieldAbsoluteDate<T> date, FieldRotation<T> rotation, FieldVector3D<T> rotationRate, FieldVector3D<T> rotationAcceleration) Build a rotation transform.
FieldTransform(FieldAbsoluteDate<T> date, FieldTransform<T> first, FieldTransform<T> second) Build a transform by combining two existing ones.
FieldTransform(FieldAbsoluteDate<T> date, FieldVector3D<T> translation) Build a translation transform.
FieldTransform(FieldAbsoluteDate<T> date, FieldVector3D<T> translation, FieldVector3D<T> velocity) Build a translation transform, with its first time derivative.
FieldTransform(FieldAbsoluteDate<T> date, FieldVector3D<T> translation, FieldVector3D<T> velocity, FieldVector3D<T> acceleration) Build a translation transform, with its first and second time derivatives.

Uses of FieldAbsoluteDate in org.orekit.models.earth

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

Modifier and Type	Method and Description
<T extends RealFieldElement<T>> FieldGeodeticPoint<T>	Geoid.getIntersectionPoint(FieldLine<T> lineInFrame, FieldVector3D<T> closeInFrame, Frame frame, FieldAbsoluteDate<T> date) Get the intersection point of a line with the surface of the body.
<T extends RealFieldElement<T>> FieldGeodeticPoint<T>	Geoid.transform(FieldVector3D<T> point, Frame frame, FieldAbsoluteDate<T> date) Transform a Cartesian point to a surface-relative point.

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

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

Modifier and Type	Method and Description
<T extends RealFieldElement<T>> T	Atmosphere.getDensity(FieldAbsoluteDate<T> date, FieldVector3D<T> position, Frame frame) Get the local density.
<T extends RealFieldElement<T>> T	SimpleExponentialAtmosphere.getDensity(FieldAbsoluteDate<T> date, FieldVector3D<T> position, Frame frame)
<T extends RealFieldElement<T>> T	NRLMSISE00.getDensity(FieldAbsoluteDate<T> date, FieldVector3D<T> position, Frame frame) Get the local density.
<T extends RealFieldElement<T>> T	DTM2000.getDensity(FieldAbsoluteDate<T> date, FieldVector3D<T> position, Frame frame) Get the local density.
<T extends RealFieldElement<T>> T	HarrisPriester.getDensity(FieldAbsoluteDate<T> date, FieldVector3D<T> position, Frame frame) Get the local density at some position.
<T extends RealFieldElement<T>> T	JB2008.getDensity(FieldAbsoluteDate<T> date, FieldVector3D<T> position, Frame frame) Get the local density.
default <T extends RealFieldElement<T>> FieldVector3D<T>	Atmosphere.getVelocity(FieldAbsoluteDate<T> date, FieldVector3D<T> position, Frame frame) Get the inertial velocity of atmosphere molecules.

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

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

Modifier and Type	Method and Description
<T extends RealFieldElement<T>> T	GlobalIonosphereMapModel.getTEC(FieldAbsoluteDate<T> date, GeodeticPoint recPoint) Computes the Total Electron Content (TEC) at a given date by performing a temporal interpolation with the two closest date in the IONEX file.
<T extends RealFieldElement<T>> T	KlobucharIonoModel.pathDelay(FieldAbsoluteDate<T> date, FieldGeodeticPoint<T> geo, T elevation, T azimuth, double frequency, T[] parameters) Calculates the ionospheric path delay for the signal path from a ground station to a satellite.
<T extends RealFieldElement<T>> T	GlobalIonosphereMapModel.pathDelay(FieldAbsoluteDate<T> date, GeodeticPoint geo, T elevation, double frequency) Calculates the ionospheric path delay for the signal path from a ground station to a satellite.

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

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

Modifier and Type	Method and Description
<T extends RealFieldElement<T>> T[]	EstimatedTroposphericModel.computeZenithDelay(T height, T[] parameters, FieldAbsoluteDate<T> date) This method allows the computation of the zenith hydrostatic and zenith total delays.
<T extends RealFieldElement<T>> T[]	DiscreteTroposphericModel.computeZenithDelay(T height, T[] parameters, FieldAbsoluteDate<T> date) This method allows the computation of the zenith hydrostatic and zenith wet delay.
<T extends RealFieldElement<T>> T[]	ViennaOneModel.computeZenithDelay(T height, T[] parameters, FieldAbsoluteDate<T> date) This method allows the computation of the zenith hydrostatic and zenith wet delay.
<T extends RealFieldElement<T>> T[]	MendesPavlisModel.computeZenithDelay(T height, T[] parameters, FieldAbsoluteDate<T> date) This method allows the computation of the zenith hydrostatic and zenith wet delay.
<T extends RealFieldElement<T>> T[]	FixedTroposphericDelay.computeZenithDelay(T height, T[] parameters, FieldAbsoluteDate<T> date)
<T extends RealFieldElement<T>> T[]	SaastamoinenModel.computeZenithDelay(T height, T[] parameters, FieldAbsoluteDate<T> date)
<T extends RealFieldElement<T>> T[]	ViennaThreeModel.computeZenithDelay(T height, T[] parameters, FieldAbsoluteDate<T> date) This method allows the computation of the zenith hydrostatic and zenith wet delay.
<T extends RealFieldElement<T>> T[]	MariniMurrayModel.computeZenithDelay(T height, T[] parameters, FieldAbsoluteDate<T> date)
<T extends RealFieldElement<T>> T[]	GlobalMappingFunctionModel.mappingFactors(T elevation, T height, T[] parameters, FieldAbsoluteDate<T> date) This method allows the computation of the hydrostatic and wet mapping functions.
<T extends RealFieldElement<T>> T[]	NiellMappingFunctionModel.mappingFactors(T elevation, T height, T[] parameters, FieldAbsoluteDate<T> date)
<T extends RealFieldElement<T>> T[]	MappingFunction.mappingFactors(T elevation, T height, T[] parameters, FieldAbsoluteDate<T> date) This method allows the computation of the hydrostatic and wet mapping functions.
<T extends RealFieldElement<T>> T[]	EstimatedTroposphericModel.mappingFactors(T elevation, T height, T[] parameters, FieldAbsoluteDate<T> date)
<T extends RealFieldElement<T>> T[]	ViennaOneModel.mappingFactors(T elevation, T height, T[] parameters, FieldAbsoluteDate<T> date) This method allows the computation of the hydrostatic and wet mapping functions.
<T extends RealFieldElement<T>> T[]	MendesPavlisModel.mappingFactors(T elevation, T height, T[] parameters, FieldAbsoluteDate<T> date) This method allows the computation of the hydrostatic and wet mapping functions.
<T extends RealFieldElement<T>> T[]	FixedTroposphericDelay.mappingFactors(T elevation, T height, T[] parameters, FieldAbsoluteDate<T> date)
<T extends RealFieldElement<T>> T[]	SaastamoinenModel.mappingFactors(T elevation, T height, T[] parameters, FieldAbsoluteDate<T> date)
<T extends RealFieldElement<T>> T[]	ViennaThreeModel.mappingFactors(T elevation, T height, T[] parameters, FieldAbsoluteDate<T> date) This method allows the computation of the hydrostatic and wet mapping functions.
<T extends RealFieldElement<T>> T[]	MariniMurrayModel.mappingFactors(T elevation, T height, T[] parameters, FieldAbsoluteDate<T> date)
<T extends RealFieldElement<T>> T	EstimatedTroposphericModel.pathDelay(T elevation, T height, T[] parameters, FieldAbsoluteDate<T> date)
<T extends RealFieldElement<T>> T	DiscreteTroposphericModel.pathDelay(T elevation, T height, T[] parameters, FieldAbsoluteDate<T> date) Calculates the tropospheric path delay for the signal path from a ground station to a satellite.
<T extends RealFieldElement<T>> T	ViennaOneModel.pathDelay(T elevation, T height, T[] parameters, FieldAbsoluteDate<T> date) Calculates the tropospheric path delay for the signal path from a ground station to a satellite.
<T extends RealFieldElement<T>> T	MendesPavlisModel.pathDelay(T elevation, T height, T[] parameters, FieldAbsoluteDate<T> date) Calculates the tropospheric path delay for the signal path from a ground station to a satellite.
<T extends RealFieldElement<T>> T	FixedTroposphericDelay.pathDelay(T elevation, T height, T[] parameters, FieldAbsoluteDate<T> date) Calculates the tropospheric path delay for the signal path from a ground station to a satellite.
<T extends RealFieldElement<T>> T	SaastamoinenModel.pathDelay(T elevation, T height, T[] parameters, FieldAbsoluteDate<T> date) Calculates the tropospheric path delay for the signal path from a ground station to a satellite.
<T extends RealFieldElement<T>> T	ViennaThreeModel.pathDelay(T elevation, T height, T[] parameters, FieldAbsoluteDate<T> date) Calculates the tropospheric path delay for the signal path from a ground station to a satellite.
<T extends RealFieldElement<T>> T	MariniMurrayModel.pathDelay(T elevation, T height, T[] parameters, FieldAbsoluteDate<T> date)

Uses of FieldAbsoluteDate in org.orekit.orbits

Methods in org.orekit.orbits that return FieldAbsoluteDate

Modifier and Type	Method and Description
FieldAbsoluteDate<T>	FieldOrbit.getDate() Get the date of orbital parameters.

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

Modifier and Type	Method and Description
TimeStampedFieldPVCoordinates<T>	FieldOrbit.getPVCoordinates(FieldAbsoluteDate<T> otherDate, Frame otherFrame) Get the FieldPVCoordinates of the body in the selected frame.
FieldCircularOrbit<T>	FieldCircularOrbit.interpolate(FieldAbsoluteDate<T> date, Stream<FieldOrbit<T>> sample) Get an interpolated instance.
FieldCartesianOrbit<T>	FieldCartesianOrbit.interpolate(FieldAbsoluteDate<T> date, Stream<FieldOrbit<T>> sample) Get an interpolated instance.
FieldEquinoctialOrbit<T>	FieldEquinoctialOrbit.interpolate(FieldAbsoluteDate<T> date, Stream<FieldOrbit<T>> sample) Get an interpolated instance.
FieldKeplerianOrbit<T>	FieldKeplerianOrbit.interpolate(FieldAbsoluteDate<T> date, Stream<FieldOrbit<T>> sample) Get an interpolated instance.
abstract <T extends RealFieldElement<T>> FieldOrbit<T>	OrbitType.mapArrayToOrbit(T[] array, T[] arrayDot, PositionAngle type, FieldAbsoluteDate<T> date, T mu, Frame frame) Convert state array to orbital parameters.

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

Constructor and Description
FieldCartesianOrbit(FieldPVCoordinates<T> pvaCoordinates, Frame frame, FieldAbsoluteDate<T> date, T mu) Constructor from Cartesian parameters.
FieldCircularOrbit(FieldPVCoordinates<T> PVCoordinates, Frame frame, FieldAbsoluteDate<T> date, T mu) Constructor from Cartesian parameters.
FieldCircularOrbit(T a, T ex, T ey, T i, T raan, T alpha, PositionAngle type, Frame frame, FieldAbsoluteDate<T> date, T mu) Creates a new instance.
FieldCircularOrbit(T a, T ex, T ey, T i, T raan, T alpha, T aDot, T exDot, T eyDot, T iDot, T raanDot, T alphaDot, PositionAngle type, Frame frame, FieldAbsoluteDate<T> date, T mu) Creates a new instance.
FieldEquinoctialOrbit(FieldPVCoordinates<T> pvCoordinates, Frame frame, FieldAbsoluteDate<T> date, T mu) Constructor from Cartesian parameters.
FieldEquinoctialOrbit(T a, T ex, T ey, T hx, T hy, T l, PositionAngle type, Frame frame, FieldAbsoluteDate<T> date, T mu) Creates a new instance.
FieldEquinoctialOrbit(T a, T ex, T ey, T hx, T hy, T l, T aDot, T exDot, T eyDot, T hxDot, T hyDot, T lDot, PositionAngle type, Frame frame, FieldAbsoluteDate<T> date, T mu) Creates a new instance.
FieldKeplerianOrbit(FieldPVCoordinates<T> FieldPVCoordinates, Frame frame, FieldAbsoluteDate<T> date, T mu) Constructor from Cartesian parameters.
FieldKeplerianOrbit(T a, T e, T i, T pa, T raan, T anomaly, PositionAngle type, Frame frame, FieldAbsoluteDate<T> date, T mu) Creates a new instance.
FieldKeplerianOrbit(T a, T e, T i, T pa, T raan, T anomaly, T aDot, T eDot, T iDot, T paDot, T raanDot, T anomalyDot, PositionAngle type, Frame frame, FieldAbsoluteDate<T> date, T mu) Creates a new instance.
FieldOrbit(Frame frame, FieldAbsoluteDate<T> date, T mu) Default constructor.

Uses of FieldAbsoluteDate in org.orekit.propagation

Methods in org.orekit.propagation that return FieldAbsoluteDate

Modifier and Type	Method and Description
FieldAbsoluteDate<T>	FieldSpacecraftState.getDate() Get the date.
FieldAbsoluteDate<T>	FieldBoundedPropagator.getMaxDate() Get the last date of the range.
FieldAbsoluteDate<T>	FieldBoundedPropagator.getMinDate() Get the first date of the range.
protected FieldAbsoluteDate<T>	FieldAbstractPropagator.getStartDate() Get the start date.

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

Modifier and Type	Method and Description
TimeStampedFieldPVCoordinates<T>	FieldAbstractPropagator.getPVCoordinates(FieldAbsoluteDate<T> date, Frame frame) Get the FieldPVCoordinates of the body in the selected frame.
FieldSpacecraftState<T>	FieldSpacecraftState.interpolate(FieldAbsoluteDate<T> date, Stream<FieldSpacecraftState<T>> sample) Get an interpolated instance.
FieldSpacecraftState<T>	FieldPropagator.propagate(FieldAbsoluteDate<T> target) Propagate towards a target date.
FieldSpacecraftState<T>	FieldAbstractPropagator.propagate(FieldAbsoluteDate<T> target) Propagate towards a target date.
FieldSpacecraftState<T>	FieldPropagator.propagate(FieldAbsoluteDate<T> start, FieldAbsoluteDate<T> target) Propagate from a start date towards a target date.
FieldSpacecraftState<T>	FieldPropagator.propagate(FieldAbsoluteDate<T> start, FieldAbsoluteDate<T> target) Propagate from a start date towards a target date.
protected void	FieldAbstractPropagator.setStartDate(FieldAbsoluteDate<T> startDate) Set a start date.

Uses of FieldAbsoluteDate in org.orekit.propagation.analytical

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

Modifier and Type	Method and Description
protected FieldSpacecraftState<T>	FieldAbstractAnalyticalPropagator.acceptStep(org.orekit.propagation.analytical.FieldAbstractAnalyticalPropagator.FieldBasicStepInterpolator interpolator, FieldAbsoluteDate<T> target, double epsilon) Accept a step, triggering events and step handlers.
protected FieldSpacecraftState<T>	FieldAbstractAnalyticalPropagator.basicPropagate(FieldAbsoluteDate<T> date) Propagate an orbit without any fancy features.
protected abstract T	FieldAbstractAnalyticalPropagator.getMass(FieldAbsoluteDate<T> date) Get the mass.
protected T	FieldKeplerianPropagator.getMass(FieldAbsoluteDate<T> date) Get the mass.
protected T	FieldEcksteinHechlerPropagator.getMass(FieldAbsoluteDate<T> date) Get the mass.
FieldSpacecraftState<T>	FieldAbstractAnalyticalPropagator.propagate(FieldAbsoluteDate<T> start, FieldAbsoluteDate<T> target) Propagate from a start date towards a target date.
FieldSpacecraftState<T>	FieldAbstractAnalyticalPropagator.propagate(FieldAbsoluteDate<T> start, FieldAbsoluteDate<T> target) Propagate from a start date towards a target date.
protected abstract FieldOrbit<T>	FieldAbstractAnalyticalPropagator.propagateOrbit(FieldAbsoluteDate<T> date) Extrapolate an orbit up to a specific target date.
protected FieldOrbit<T>	FieldKeplerianPropagator.propagateOrbit(FieldAbsoluteDate<T> date) Extrapolate an orbit up to a specific target date.
FieldCartesianOrbit<T>	FieldEcksteinHechlerPropagator.propagateOrbit(FieldAbsoluteDate<T> date) Extrapolate an orbit up to a specific target date.

Uses of FieldAbsoluteDate in org.orekit.propagation.events

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

Modifier and Type	Method and Description
FieldAbsoluteDate<T>	FieldDateDetector.getDate() Get the current event date according to the propagator.
FieldAbsoluteDate<T>	FieldEventState.getEventDate() Get the occurrence time of the event triggered in the current step.
FieldAbsoluteDate<T>	FieldEventState.EventOccurrence.getStopDate() Get the new time for a stop action.

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

Modifier and Type	Method and Description
void	FieldDateDetector.addEventDate(FieldAbsoluteDate<T> target) Add an event date.
void	FieldAbstractDetector.init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t) Initialize event handler at the start of a propagation.
void	FieldEventState.init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t) Initialize event handler at the start of a propagation.
default void	FieldEventDetector.init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t) Initialize event handler at the start of a propagation.

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

Constructor and Description
FieldDateDetector(FieldAbsoluteDate<T> target) Build a new instance.

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

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

Modifier and Type	Method and Description
default void	FieldEventHandler.init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target) Initialize event handler at the start of a propagation.

Uses of FieldAbsoluteDate in org.orekit.propagation.integration

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

Modifier and Type	Method and Description
FieldAbsoluteDate<T>	FieldIntegratedEphemeris.getMaxDate() Get the last date of the range.
FieldAbsoluteDate<T>	FieldIntegratedEphemeris.getMinDate() Get the first date of the range.
FieldAbsoluteDate<T>	FieldStateMapper.getReferenceDate() Get reference date.
FieldAbsoluteDate<T>	FieldStateMapper.mapDoubleToDate(T t) Map the raw double time offset to a date.
FieldAbsoluteDate<T>	FieldStateMapper.mapDoubleToDate(T t, FieldAbsoluteDate<T> date) Map the raw double time offset to a date.

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

Modifier and Type	Method and Description
protected FieldSpacecraftState<T>	FieldIntegratedEphemeris.basicPropagate(FieldAbsoluteDate<T> date) Propagate an orbit without any fancy features.
protected void	FieldAbstractIntegratedPropagator.beforeIntegration(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> tEnd) Method called just before integration.
protected abstract FieldStateMapper<T>	FieldAbstractIntegratedPropagator.createMapper(FieldAbsoluteDate<T> referenceDate, T mu, OrbitType orbitType, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame) Create a mapper between raw double components and spacecraft state.
protected T	FieldIntegratedEphemeris.getMass(FieldAbsoluteDate<T> date) Get the mass.
TimeStampedFieldPVCoordinates<T>	FieldIntegratedEphemeris.getPVCoordinates(FieldAbsoluteDate<T> date, Frame frame) Get the FieldPVCoordinates of the body in the selected frame.
default void	FieldAdditionalEquations.init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target) Initialize the equations at the start of propagation.
void	FieldAbstractIntegratedPropagator.MainStateEquations.init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target) Initialize the equations at the start of propagation.
void	FieldModeHandler.initialize(boolean activateHandlers, FieldAbsoluteDate<T> targetDate) Initialize the mode handler.
abstract FieldSpacecraftState<T>	FieldStateMapper.mapArrayToState(FieldAbsoluteDate<T> date, T[] y, T[] yDot, PropagationType type) Map the raw double components to a spacecraft state.
T	FieldStateMapper.mapDateToDouble(FieldAbsoluteDate<T> date) Map a date to a raw double time offset.
FieldAbsoluteDate<T>	FieldStateMapper.mapDoubleToDate(T t, FieldAbsoluteDate<T> date) Map the raw double time offset to a date.
FieldSpacecraftState<T>	FieldAbstractIntegratedPropagator.propagate(FieldAbsoluteDate<T> target) Propagate towards a target date.
protected FieldSpacecraftState<T>	FieldAbstractIntegratedPropagator.propagate(FieldAbsoluteDate<T> tEnd, boolean activateHandlers) Propagation with or without event detection.
FieldSpacecraftState<T>	FieldAbstractIntegratedPropagator.propagate(FieldAbsoluteDate<T> tStart, FieldAbsoluteDate<T> tEnd) Propagate from a start date towards a target date.
FieldSpacecraftState<T>	FieldAbstractIntegratedPropagator.propagate(FieldAbsoluteDate<T> tStart, FieldAbsoluteDate<T> tEnd) Propagate from a start date towards a target date.
protected FieldOrbit<T>	FieldIntegratedEphemeris.propagateOrbit(FieldAbsoluteDate<T> date) Extrapolate an orbit up to a specific target date.

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

Constructor and Description
FieldIntegratedEphemeris(FieldAbsoluteDate<T> startDate, FieldAbsoluteDate<T> minDate, FieldAbsoluteDate<T> maxDate, FieldStateMapper<T> mapper, PropagationType type, FieldDenseOutputModel<T> model, Map<String,T[]> unmanaged, List<FieldAdditionalStateProvider<T>> providers, String[] equations) Creates a new instance of IntegratedEphemeris.
FieldIntegratedEphemeris(FieldAbsoluteDate<T> startDate, FieldAbsoluteDate<T> minDate, FieldAbsoluteDate<T> maxDate, FieldStateMapper<T> mapper, PropagationType type, FieldDenseOutputModel<T> model, Map<String,T[]> unmanaged, List<FieldAdditionalStateProvider<T>> providers, String[] equations) Creates a new instance of IntegratedEphemeris.
FieldIntegratedEphemeris(FieldAbsoluteDate<T> startDate, FieldAbsoluteDate<T> minDate, FieldAbsoluteDate<T> maxDate, FieldStateMapper<T> mapper, PropagationType type, FieldDenseOutputModel<T> model, Map<String,T[]> unmanaged, List<FieldAdditionalStateProvider<T>> providers, String[] equations) Creates a new instance of IntegratedEphemeris.
FieldStateMapper(FieldAbsoluteDate<T> referenceDate, T mu, OrbitType orbitType, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame) Simple constructor.

Uses of FieldAbsoluteDate in org.orekit.propagation.numerical

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

Modifier and Type	Method and Description
protected FieldStateMapper<T>	FieldNumericalPropagator.createMapper(FieldAbsoluteDate<T> referenceDate, T mu, OrbitType orbitType, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame) Create a mapper between raw double components and spacecraft state.
TimeStampedFieldPVCoordinates<T>	FieldNumericalPropagator.getPVCoordinates(FieldAbsoluteDate<T> date, Frame frame) Get the FieldPVCoordinates of the body in the selected frame.

Uses of FieldAbsoluteDate in org.orekit.propagation.sampling

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

Modifier and Type	Method and Description
FieldSpacecraftState<T>	FieldOrekitStepInterpolator.getInterpolatedState(FieldAbsoluteDate<T> date) Get the state at interpolated date.
void	FieldOrekitStepNormalizer.init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t) Initialize step handler at the start of a propagation.
void	FieldOrekitStepHandlerMultiplexer.init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t) Initialize step handler at the start of a propagation.
void	FieldOrekitStepHandler.init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t) Initialize step handler at the start of a propagation.
default void	FieldOrekitFixedStepHandler.init(FieldSpacecraftState<T> s0, FieldAbsoluteDate<T> t, T step) Initialize step handler at the start of a propagation.

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

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

Modifier and Type	Method and Description
protected void	FieldDSSTPropagator.beforeIntegration(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> tEnd) Method called just before integration.
protected FieldStateMapper<T>	FieldDSSTPropagator.createMapper(FieldAbsoluteDate<T> referenceDate, T mu, OrbitType ignoredOrbitType, PositionAngle ignoredPositionAngleType, AttitudeProvider attitudeProvider, Frame frame) Create a mapper between raw double components and spacecraft state.

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

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

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

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

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

Modifier and Type	Method and Description
FieldAbsoluteDate<T>	FieldAuxiliaryElements.getDate() Get the date of the orbit.

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

Modifier and Type	Method and Description
void	FieldShortPeriodicsInterpolatedCoefficient.addGridPoint(FieldAbsoluteDate<T> date, T[] value) Add a point to the interpolation grid.
T[]	FieldShortPeriodicsInterpolatedCoefficient.value(FieldAbsoluteDate<T> date) Compute the value of the coefficient.

Uses of FieldAbsoluteDate in org.orekit.time

Methods in org.orekit.time that return FieldAbsoluteDate

Modifier and Type	Method and Description
static <T extends RealFieldElement<T>> FieldAbsoluteDate<T>	FieldAbsoluteDate.createBesselianEpoch(T besselianEpoch) Build an instance corresponding to a Besselian Epoch (BE).
static <T extends RealFieldElement<T>> FieldAbsoluteDate<T>	FieldAbsoluteDate.createGPSDate(int weekNumber, T milliInWeek) Build an instance corresponding to a GPS date.
static <T extends RealFieldElement<T>> FieldAbsoluteDate<T>	FieldAbsoluteDate.createJDDate(int jd, T secondsSinceNoon, TimeScale timeScale) Build an instance corresponding to a Julian Day date.
static <T extends RealFieldElement<T>> FieldAbsoluteDate<T>	FieldAbsoluteDate.createJulianEpoch(T julianEpoch) Build an instance corresponding to a Julian Epoch (JE).
static <T extends RealFieldElement<T>> FieldAbsoluteDate<T>	FieldAbsoluteDate.createMJDDate(int mjd, T secondsInDay, TimeScale timeScale) Build an instance corresponding to a Modified Julian Day date.
static <T extends RealFieldElement<T>> FieldAbsoluteDate<T>	FieldAbsoluteDate.getCCSDSEpoch(Field<T> field) Reference epoch for CCSDS Time Code Format (CCSDS 301.0-B-4): 1958-01-01T00:00:00 International Atomic Time (not UTC).
FieldAbsoluteDate<T>	FieldAbsoluteDate.getDate() Get the date.
FieldAbsoluteDate<T>	FieldTimeStamped.getDate() Get the date.
static <T extends RealFieldElement<T>> FieldAbsoluteDate<T>	FieldAbsoluteDate.getFiftiesEpoch(Field<T> field) Reference epoch for 1950 dates: 1950-01-01T00:00:00 Terrestrial Time.
static <T extends RealFieldElement<T>> FieldAbsoluteDate<T>	FieldAbsoluteDate.getFutureInfinity(Field<T> field) Dummy date at infinity in the future direction.
static <T extends RealFieldElement<T>> FieldAbsoluteDate<T>	FieldAbsoluteDate.getGalileoEpoch(Field<T> field) Reference epoch for Galileo System Time: 1999-08-22T00:00:00 UTC.
static <T extends RealFieldElement<T>> FieldAbsoluteDate<T>	FieldAbsoluteDate.getGPSEpoch(Field<T> field) Reference epoch for GPS weeks: 1980-01-06T00:00:00 GPS time.
static <T extends RealFieldElement<T>> FieldAbsoluteDate<T>	FieldAbsoluteDate.getJ2000Epoch(Field<T> field) J2000.0 Reference epoch: 2000-01-01T12:00:00 Terrestrial Time (not UTC).
static <T extends RealFieldElement<T>> FieldAbsoluteDate<T>	FieldAbsoluteDate.getJavaEpoch(Field<T> field) Java Reference epoch: 1970-01-01T00:00:00 Universal Time Coordinate.
static <T extends RealFieldElement<T>> FieldAbsoluteDate<T>	FieldAbsoluteDate.getJulianEpoch(Field<T> field) Reference epoch for julian dates: -4712-01-01T12:00:00 Terrestrial Time.
static <T extends RealFieldElement<T>> FieldAbsoluteDate<T>	FieldAbsoluteDate.getModifiedJulianEpoch(Field<T> field) Reference epoch for modified julian dates: 1858-11-17T00:00:00 Terrestrial Time.
static <T extends RealFieldElement<T>> FieldAbsoluteDate<T>	FieldAbsoluteDate.getPastInfinity(Field<T> field) Dummy date at infinity in the past direction.
FieldAbsoluteDate<T>	FieldAbsoluteDate.parseCCSDSCalendarSegmentedTimeCode(byte preambleField, byte[] timeField) Build an instance from a CCSDS Calendar Segmented Time Code (CCS).
static <T extends RealFieldElement<T>> FieldAbsoluteDate<T>	FieldAbsoluteDate.parseCCSDSDaySegmentedTimeCode(Field<T> field, byte preambleField, byte[] timeField, DateComponents agencyDefinedEpoch) Build an instance from a CCSDS Day Segmented Time Code (CDS).
static <T extends RealFieldElement<T>> FieldAbsoluteDate<T>	FieldAbsoluteDate.parseCCSDSUnsegmentedTimeCode(Field<T> field, byte preambleField1, byte preambleField2, byte[] timeField, FieldAbsoluteDate<T> agencyDefinedEpoch) Build an instance from a CCSDS Unsegmented Time Code (CUC).
FieldAbsoluteDate<T>	FieldAbsoluteDate.shiftedBy(double dt) Get a time-shifted date.
FieldAbsoluteDate<T>	FieldAbsoluteDate.shiftedBy(T dt) Get a time-shifted date.

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

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

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

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

Uses of FieldAbsoluteDate in org.orekit.utils

Methods in org.orekit.utils that return FieldAbsoluteDate

Modifier and Type	Method and Description
FieldAbsoluteDate<D>	FieldTimeSpanMap.Transition.getAbsoluteDate() Get the transition field absolute date.
FieldAbsoluteDate<T>	TimeStampedFieldPVCoordinates.getDate() Get the date.
FieldAbsoluteDate<T>	TimeStampedFieldAngularCoordinates.getDate() Get the date.

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

Modifier and Type	Method and Description
void	FieldTimeSpanMap.addValidAfter(T entry, FieldAbsoluteDate<D> earliestValidityDate) Add an entry valid after a limit date.
void	FieldTimeSpanMap.addValidBefore(T entry, FieldAbsoluteDate<D> latestValidityDate) Add an entry valid before a limit date.
<T extends RealFieldElement<T>> T	IERSConventions.evaluateTC(FieldAbsoluteDate<T> date) Evaluate the date offset between the current date and the reference date.
T	FieldTimeSpanMap.get(FieldAbsoluteDate<D> date) Get the entry valid at a specified date.
TimeStampedFieldPVCoordinates<T>	FieldAbsolutePVCoordinates.getPVCoordinates(FieldAbsoluteDate<T> otherDate, Frame outputFrame)
TimeStampedFieldPVCoordinates<T>	FieldPVCoordinatesProvider.getPVCoordinates(FieldAbsoluteDate<T> date, Frame frame) Get the FieldPVCoordinates of the body in the selected frame.
<T extends RealFieldElement<T>> TimeStampedFieldPVCoordinates<T>	ExtendedPVCoordinatesProvider.getPVCoordinates(FieldAbsoluteDate<T> date, Frame frame) Get the FieldPVCoordinates of the body in the selected frame.
static <T extends RealFieldElement<T>> TimeStampedFieldAngularCoordinates<T>	TimeStampedFieldAngularCoordinates.interpolate(FieldAbsoluteDate<T> date, AngularDerivativesFilter filter, Collection<TimeStampedFieldAngularCoordinates<T>> sample) Interpolate angular coordinates.
static <T extends RealFieldElement<T>> TimeStampedFieldPVCoordinates<T>	TimeStampedFieldPVCoordinates.interpolate(FieldAbsoluteDate<T> date, CartesianDerivativesFilter filter, Collection<TimeStampedFieldPVCoordinates<T>> sample) Interpolate position-velocity.
static <T extends RealFieldElement<T>> TimeStampedFieldPVCoordinates<T>	TimeStampedFieldPVCoordinates.interpolate(FieldAbsoluteDate<T> date, CartesianDerivativesFilter filter, Stream<TimeStampedFieldPVCoordinates<T>> sample) Interpolate position-velocity.
FieldAbsolutePVCoordinates<T>	FieldAbsolutePVCoordinates.interpolate(FieldAbsoluteDate<T> date, Stream<FieldAbsolutePVCoordinates<T>> sample)
static <T extends RealFieldElement<T>> FieldAbsolutePVCoordinates<T>	FieldAbsolutePVCoordinates.interpolate(Frame frame, FieldAbsoluteDate<T> date, CartesianDerivativesFilter filter, Stream<FieldAbsolutePVCoordinates<T>> sample) Interpolate position-velocity.

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

Constructor and Description
FieldAbsolutePVCoordinates(FieldAbsoluteDate<T> date, FieldAbsolutePVCoordinates<T> start, FieldAbsolutePVCoordinates<T> end) Subtractive constructor
FieldAbsolutePVCoordinates(FieldAbsoluteDate<T> date, T a, FieldAbsolutePVCoordinates<T> AbsPva) Multiplicative constructor
FieldAbsolutePVCoordinates(FieldAbsoluteDate<T> date, T a1, FieldAbsolutePVCoordinates<T> absPv1, T a2, FieldAbsolutePVCoordinates<T> absPv2) Linear constructor
FieldAbsolutePVCoordinates(FieldAbsoluteDate<T> date, T a1, FieldAbsolutePVCoordinates<T> absPv1, T a2, FieldAbsolutePVCoordinates<T> absPv2, T a3, FieldAbsolutePVCoordinates<T> absPv3) Linear constructor
FieldAbsolutePVCoordinates(FieldAbsoluteDate<T> date, T a1, FieldAbsolutePVCoordinates<T> absPv1, T a2, FieldAbsolutePVCoordinates<T> absPv2, T a3, FieldAbsolutePVCoordinates<T> absPv3, T a4, FieldAbsolutePVCoordinates<T> absPv4) Linear constructor
FieldAbsolutePVCoordinates(Frame frame, FieldAbsoluteDate<T> date, FieldPVCoordinates<T> pva) Build from frame, date and FieldPVA coordinates.
FieldAbsolutePVCoordinates(Frame frame, FieldAbsoluteDate<T> date, FieldVector3D<FieldDerivativeStructure<T>> p) Builds a FieldAbsolutePVCoordinates triplet from a FieldVector3D<DerivativeStructure>.
FieldAbsolutePVCoordinates(Frame frame, FieldAbsoluteDate<T> date, FieldVector3D<T> position, FieldVector3D<T> velocity) Build from position and velocity.
FieldAbsolutePVCoordinates(Frame frame, FieldAbsoluteDate<T> date, FieldVector3D<T> position, FieldVector3D<T> velocity, FieldVector3D<T> acceleration) Build from position, velocity, acceleration.
TimeStampedFieldAngularCoordinates(FieldAbsoluteDate<T> date, FieldPVCoordinates<T> u1, FieldPVCoordinates<T> u2, FieldPVCoordinates<T> v1, FieldPVCoordinates<T> v2, double tolerance) Build the rotation that transforms a pair of pv coordinates into another pair.
TimeStampedFieldAngularCoordinates(FieldAbsoluteDate<T> date, FieldRotation<FieldDerivativeStructure<T>> r) Builds a TimeStampedFieldAngularCoordinates from a FieldRotation<FieldDerivativeStructure>.
TimeStampedFieldAngularCoordinates(FieldAbsoluteDate<T> date, FieldRotation<T> rotation, FieldVector3D<T> rotationRate, FieldVector3D<T> rotationAcceleration) Builds a rotation/rotation rate pair.
TimeStampedFieldPVCoordinates(FieldAbsoluteDate<T> date, double a, FieldPVCoordinates<T> pv) Multiplicative constructor
TimeStampedFieldPVCoordinates(FieldAbsoluteDate<T> date, double a1, FieldPVCoordinates<T> pv1, double a2, FieldPVCoordinates<T> pv2) Linear constructor
TimeStampedFieldPVCoordinates(FieldAbsoluteDate<T> date, double a1, FieldPVCoordinates<T> pv1, double a2, FieldPVCoordinates<T> pv2, double a3, FieldPVCoordinates<T> pv3) Linear constructor
TimeStampedFieldPVCoordinates(FieldAbsoluteDate<T> date, double a1, FieldPVCoordinates<T> pv1, double a2, FieldPVCoordinates<T> pv2, double a3, FieldPVCoordinates<T> pv3, double a4, FieldPVCoordinates<T> pv4) Linear constructor
TimeStampedFieldPVCoordinates(FieldAbsoluteDate<T> date, FieldPVCoordinates<T> pv) Basic constructor.
TimeStampedFieldPVCoordinates(FieldAbsoluteDate<T> date, FieldPVCoordinates<T> start, FieldPVCoordinates<T> end) Subtractive constructor
TimeStampedFieldPVCoordinates(FieldAbsoluteDate<T> date, FieldVector3D<FieldDerivativeStructure<T>> p) Builds a TimeStampedFieldPVCoordinates triplet from a FieldVector3D<FieldDerivativeStructure>.
TimeStampedFieldPVCoordinates(FieldAbsoluteDate<T> date, FieldVector3D<T> position, FieldVector3D<T> velocity, FieldVector3D<T> acceleration) Builds a PVCoordinates pair.
TimeStampedFieldPVCoordinates(FieldAbsoluteDate<T> date, T a, FieldPVCoordinates<T> pv) Multiplicative constructor
TimeStampedFieldPVCoordinates(FieldAbsoluteDate<T> date, T a1, FieldPVCoordinates<T> pv1, T a2, FieldPVCoordinates<T> pv2) Linear constructor
TimeStampedFieldPVCoordinates(FieldAbsoluteDate<T> date, T a1, FieldPVCoordinates<T> pv1, T a2, FieldPVCoordinates<T> pv2, T a3, FieldPVCoordinates<T> pv3) Linear constructor
TimeStampedFieldPVCoordinates(FieldAbsoluteDate<T> date, T a1, FieldPVCoordinates<T> pv1, T a2, FieldPVCoordinates<T> pv2, T a3, FieldPVCoordinates<T> pv3, T a4, FieldPVCoordinates<T> pv4) Linear constructor
TimeStampedFieldPVCoordinates(FieldAbsoluteDate<T> date, T a, PVCoordinates pv) Multiplicative constructor
TimeStampedFieldPVCoordinates(FieldAbsoluteDate<T> date, T a1, PVCoordinates pv1, T a2, PVCoordinates pv2) Linear constructor
TimeStampedFieldPVCoordinates(FieldAbsoluteDate<T> date, T a1, PVCoordinates pv1, T a2, PVCoordinates pv2, T a3, PVCoordinates pv3) Linear constructor
TimeStampedFieldPVCoordinates(FieldAbsoluteDate<T> date, T a1, PVCoordinates pv1, T a2, PVCoordinates pv2, T a3, PVCoordinates pv3, T a4, PVCoordinates pv4) Linear constructor