Uses of Class
org.orekit.frames.Frame

Packages that use Frame

Package	Description
org.orekit.attitudes	This package provides classes to represent simple attitudes.
org.orekit.bodies	This package provides interface to represent the position and geometry of space objects such as stars, planets or asteroids.
org.orekit.control.indirect.adjoint	This package provides routines to model the adjoint dynamics as in the Pontryagin Maximum Principle, as used in indirect control.
org.orekit.control.indirect.shooting.propagation	This package provides classes relative to the propagation part of indirect shooting.
org.orekit.estimation.iod	This package provides initial orbit determination methods.
org.orekit.estimation.measurements	The measurements package defines everything that is related to orbit determination measurements.
org.orekit.estimation.measurements.generation	This package provides Orbit Determination measurements generation.
org.orekit.estimation.measurements.modifiers	This package provides measurement modifier.
org.orekit.files.ccsds.definitions	This package contains definitions for CCSDS objects (frames, time systems...).
org.orekit.files.ccsds.ndm.adm	This package contains class managing CCSDS Attitude Data Message.
org.orekit.files.ccsds.ndm.adm.acm	This package contains class managing CCSDS Attitude Comprehensive Message.
org.orekit.files.ccsds.ndm.adm.aem	This package contains class managing CCSDS Attitude Ephemeris Message.
org.orekit.files.ccsds.ndm.adm.apm	This package contains class managing CCSDS Attitude Parameter Message.
org.orekit.files.ccsds.ndm.cdm	This package contains class managing CCSDS Conjunction Data Message.
org.orekit.files.ccsds.ndm.odm	This package contains class managing CCSDS Orbit Data Message.
org.orekit.files.ccsds.ndm.odm.ocm	This package contains class managing CCSDS Orbit Comprehensive Message.
org.orekit.files.ccsds.ndm.odm.oem	This package contains class managing CCSDS Orbit Ephemeris Message.
org.orekit.files.general	This package provides interfaces for orbit file representations and corresponding parsers.
org.orekit.files.iirv	This package provides parsers and writers for Improved Interrange Vector (IIRV) messages.
org.orekit.files.iirv.terms	This package collects classes representing the individual terms that make up an IIRV vector.
org.orekit.files.ilrs	This package provides parsers for laser ranging data stored in CDR and CPF formats.
org.orekit.files.rinex.clock	This package provides classes related to navigation clock files.
org.orekit.files.sp3	This package provides a parser for orbit data stored in SP3 format.
org.orekit.files.stk	This package provides a parser for STK ephemeris files.
org.orekit.forces.drag	This package provides all drag-related forces.
org.orekit.forces.gravity	This package provides all gravity-related forces.
org.orekit.forces.inertia	This package provides inertial force model.
org.orekit.forces.maneuvers	This package provides models of simple maneuvers.
org.orekit.forces.radiation	This package provides all radiation pressure related forces.
org.orekit.frames	This package provides classes to handle frames and transforms between them.
org.orekit.gnss	This package provides classes related to GNSS applications.
org.orekit.gnss.antenna	This package provides classes related to receiver and satellites antenna modeling.
org.orekit.gnss.attitude	This package provides classes related to navigation satellites attitude modeling.
org.orekit.models.earth	This package provides models that simulate certain physical phenomena of Earth and the near-Earth environment.
org.orekit.models.earth.atmosphere	This package provides the atmosphere model interface and several implementations.
org.orekit.models.earth.displacement	This package provides models computing reference points displacements on Earth surface.
org.orekit.orbits	This package provides classes to represent orbits.
org.orekit.propagation	Propagation
org.orekit.propagation.analytical	Top level package for analytical propagators.
org.orekit.propagation.analytical.gnss	This package provides classes to propagate GNSS orbits.
org.orekit.propagation.analytical.gnss.data	This package provides classes related to navigation data containing in GNSS almanacs and navigation messages.
org.orekit.propagation.analytical.intelsat	This package provides classes to propagate Intelsat's 11 elements.
org.orekit.propagation.analytical.tle	This package provides classes to read and extrapolate tle's.
org.orekit.propagation.analytical.tle.generation	This package provides classes related to TLE generation.
org.orekit.propagation.conversion	This package provides tools to convert a given propagator or a set of SpacecraftState into another propagator.
org.orekit.propagation.conversion.averaging	This package wraps methods from various (semi)analytical models in Orekit to convert back and forth between an averaged orbital state and an osculating one.
org.orekit.propagation.conversion.osc2mean	This package provides the ability to convert osculating orbits into mean orbits according to different theories (Brouwer-Lyddane, Eckstein-Hechler, SGP4/SDP4, DSST) with different conversion algorithms (fixed-point, least-squares).
org.orekit.propagation.events	This package provides interfaces and classes dealing with events occurring during propagation.
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.utils	This package provides useful objects.

Uses of Frame in org.orekit.attitudes

Methods in org.orekit.attitudes that return Frame

Modifier and Type	Method	Description
Frame	GroundPointing.getBodyFrame()	Get the body frame.
Frame	LofOffset.getInertialFrame()	Get the inertial frame.
Frame	Attitude.getReferenceFrame()	Get the reference frame.
Frame	AttitudeInterpolator.getReferenceFrame()	Get reference frame from which attitude is defined.
Frame	FieldAttitude.getReferenceFrame()	Get the reference frame.
Frame	FieldAttitudeInterpolator.getReferenceFrame()	Get reference frame from which attitude is defined.

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

Modifier and Type	Method	Description
<T extends CalculusFieldElement<T>> FieldAttitude<T>	AttitudeBuilder.build(Frame frame, FieldPVCoordinatesProvider<T> pvProv, TimeStampedFieldAngularCoordinates<T> rawAttitude)	Build a filtered attitude.
Attitude	AttitudeBuilder.build(Frame frame, PVCoordinatesProvider pvProv, TimeStampedAngularCoordinates rawAttitude)	Build a filtered attitude.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	FixedFrameBuilder.build(Frame frame, FieldPVCoordinatesProvider<T> pvProv, TimeStampedFieldAngularCoordinates<T> rawAttitude)	Build a filtered attitude.
Attitude	FixedFrameBuilder.build(Frame frame, PVCoordinatesProvider pvProv, TimeStampedAngularCoordinates rawAttitude)	Build a filtered attitude.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	AggregateBoundedAttitudeProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
Attitude	AggregateBoundedAttitudeProvider.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	AlignedAndConstrained.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
Attitude	AlignedAndConstrained.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	AttitudeProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> 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.
default <T extends CalculusFieldElement<T>> FieldAttitude<T>	AttitudeProviderModifier.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
default Attitude	AttitudeProviderModifier.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	CelestialBodyPointed.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> 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.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	FixedRate.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> 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.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	FrameAlignedProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
Attitude	FrameAlignedProvider.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	GroundPointing.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> 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.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	LofOffset.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> 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.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	LofOffsetPointing.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> 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.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	SpinStabilized.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> 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.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	TabulatedLofOffset.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
Attitude	TabulatedLofOffset.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	TabulatedProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> 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.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	TorqueFree.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
Attitude	TorqueFree.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	YawCompensation.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
Attitude	YawCompensation.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	YawSteering.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> 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.
<T extends CalculusFieldElement<T>> FieldRotation<T>	AggregateBoundedAttitudeProvider.getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
Rotation	AggregateBoundedAttitudeProvider.getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldRotation<T>	AlignedAndConstrained.getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
Rotation	AlignedAndConstrained.getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
default <T extends CalculusFieldElement<T>> FieldRotation<T>	AttitudeProvider.getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
default Rotation	AttitudeProvider.getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldRotation<T>	CelestialBodyPointed.getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
Rotation	CelestialBodyPointed.getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldRotation<T>	FixedRate.getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
Rotation	FixedRate.getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldRotation<T>	FrameAlignedProvider.getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
Rotation	FrameAlignedProvider.getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldRotation<T>	GroundPointing.getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
Rotation	GroundPointing.getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldRotation<T>	LofOffset.getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
Rotation	LofOffset.getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldRotation<T>	LofOffsetPointing.getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
Rotation	LofOffsetPointing.getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldRotation<T>	SpinStabilized.getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
Rotation	SpinStabilized.getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude-related rotation corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	GroundPointingAttitudeModifier.getBaseState(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the base system state at given date, without modifications.
Attitude	GroundPointingAttitudeModifier.getBaseState(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the base system state at given date, without modifications.
<T extends CalculusFieldElement<T>> FieldVector3D<FieldUnivariateDerivative2<T>>	GroundPointTarget.getDerivative2TargetDirection(ExtendedPositionProvider sun, OneAxisEllipsoid earth, TimeStampedFieldPVCoordinates<T> pv, Frame frame)	Get a target vector.
FieldVector3D<UnivariateDerivative2>	GroundPointTarget.getDerivative2TargetDirection(ExtendedPositionProvider sun, OneAxisEllipsoid earth, TimeStampedPVCoordinates pv, Frame frame)	Get a target vector.
default <T extends CalculusFieldElement<T>> FieldVector3D<FieldUnivariateDerivative2<T>>	TargetProvider.getDerivative2TargetDirection(ExtendedPositionProvider sun, OneAxisEllipsoid earth, TimeStampedFieldPVCoordinates<T> pv, Frame frame)	Get a target vector.
default FieldVector3D<UnivariateDerivative2>	TargetProvider.getDerivative2TargetDirection(ExtendedPositionProvider sun, OneAxisEllipsoid earth, TimeStampedPVCoordinates pv, Frame frame)	Get a target vector.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	GroundPointTarget.getTargetDirection(ExtendedPositionProvider sun, OneAxisEllipsoid earth, TimeStampedFieldPVCoordinates<T> pv, Frame frame)	Get a target vector.
Vector3D	GroundPointTarget.getTargetDirection(ExtendedPositionProvider sun, OneAxisEllipsoid earth, TimeStampedPVCoordinates pv, Frame frame)	Get a target vector.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	TargetProvider.getTargetDirection(ExtendedPositionProvider sun, OneAxisEllipsoid earth, TimeStampedFieldPVCoordinates<T> pv, Frame frame)	Get a target vector.
default Vector3D	TargetProvider.getTargetDirection(ExtendedPositionProvider sun, OneAxisEllipsoid earth, TimeStampedPVCoordinates pv, Frame frame)	Get a target vector.
protected <T extends CalculusFieldElement<T>> FieldVector3D<T>	BodyCenterPointing.getTargetPosition(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the target point position in specified frame.
protected Vector3D	BodyCenterPointing.getTargetPosition(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position in specified frame.
protected <T extends CalculusFieldElement<T>> FieldVector3D<T>	GroundPointing.getTargetPosition(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the target point position in specified frame.
protected Vector3D	GroundPointing.getTargetPosition(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position in specified frame.
protected <T extends CalculusFieldElement<T>> FieldVector3D<T>	GroundPointingAttitudeModifier.getTargetPosition(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the target point position in specified frame.
protected Vector3D	GroundPointingAttitudeModifier.getTargetPosition(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position in specified frame.
protected <T extends CalculusFieldElement<T>> FieldVector3D<T>	LofOffsetPointing.getTargetPosition(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the target point position in specified frame.
protected Vector3D	LofOffsetPointing.getTargetPosition(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position in specified frame.
protected <T extends CalculusFieldElement<T>> FieldVector3D<T>	NadirPointing.getTargetPosition(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the target point position in specified frame.
protected Vector3D	NadirPointing.getTargetPosition(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position in specified frame.
protected <T extends CalculusFieldElement<T>> FieldVector3D<T>	TargetPointing.getTargetPosition(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the target point position in specified frame.
protected Vector3D	TargetPointing.getTargetPosition(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position in specified frame.
<T extends CalculusFieldElement<T>> TimeStampedFieldPVCoordinates<T>	BodyCenterPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the target point position/velocity in specified frame.
TimeStampedPVCoordinates	BodyCenterPointing.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position/velocity in specified frame.
protected abstract <T extends CalculusFieldElement<T>> TimeStampedFieldPVCoordinates<T>	GroundPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> 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.
<T extends CalculusFieldElement<T>> TimeStampedFieldPVCoordinates<T>	GroundPointingAttitudeModifier.getTargetPV(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the target point position/velocity in specified frame.
TimeStampedPVCoordinates	GroundPointingAttitudeModifier.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position/velocity in specified frame.
<T extends CalculusFieldElement<T>> TimeStampedFieldPVCoordinates<T>	LofOffsetPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the target point position/velocity in specified frame.
TimeStampedPVCoordinates	LofOffsetPointing.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position/velocity in specified frame.
<T extends CalculusFieldElement<T>> TimeStampedFieldPVCoordinates<T>	NadirPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the target point position/velocity in specified frame.
TimeStampedPVCoordinates	NadirPointing.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position/velocity in specified frame.
<T extends CalculusFieldElement<T>> TimeStampedFieldPVCoordinates<T>	TargetPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the target point position/velocity in specified frame.
TimeStampedPVCoordinates	TargetPointing.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position/velocity in specified frame.
<T extends CalculusFieldElement<T>> TimeStampedFieldPVCoordinates<T>	NadirPointing.getTargetPVViaInterpolation(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute target position-velocity-acceleration vector via interpolation (Field version).
TimeStampedPVCoordinates	NadirPointing.getTargetPVViaInterpolation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute target position-velocity-acceleration vector via interpolation.
<T extends CalculusFieldElement<T>> T	YawCompensation.getYawAngle(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the yaw compensation angle at date.
double	YawCompensation.getYawAngle(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the yaw compensation angle at date.
static AttitudeProvider	FrameAlignedProvider.of(Frame satelliteFrame)	Creates an attitude provider aligned with the given frame.
Attitude	Attitude.withReferenceFrame(Frame newReferenceFrame)	Get a similar attitude with a specific reference frame.
FieldAttitude<T>	FieldAttitude.withReferenceFrame(Frame newReferenceFrame)	Get a similar attitude with a specific reference frame.

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

Constructor	Description
AlignedAndConstrained(Vector3D primarySat, TargetProvider primaryTarget, Vector3D secondarySat, TargetProvider secondaryTarget, Frame inertialFrame, ExtendedPositionProvider sun, OneAxisEllipsoid earth)	Simple constructor.
Attitude(Frame referenceFrame, TimeStampedAngularCoordinates orientation)	Creates a new instance.
Attitude(AbsoluteDate date, Frame referenceFrame, Rotation attitude, Vector3D spin, Vector3D acceleration)	Creates a new instance.
Attitude(AbsoluteDate date, Frame referenceFrame, AngularCoordinates orientation)	Creates a new instance.
AttitudeInterpolator(Frame referenceFrame, TimeInterpolator<TimeStampedAngularCoordinates> interpolator)	Constructor.
BodyCenterPointing(Frame inertialFrame, Ellipsoid shape)	Creates new instance.
CelestialBodyPointed(Frame celestialFrame, ExtendedPositionProvider pointedBody, Vector3D phasingCel, Vector3D pointingSat, Vector3D phasingSat)	Creates new instance.
FieldAttitude(Frame referenceFrame, TimeStampedFieldAngularCoordinates<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.
FieldAttitude(FieldAbsoluteDate<T> date, Frame referenceFrame, FieldAngularCoordinates<T> orientation)	Creates a new instance.
FieldAttitudeInterpolator(Frame referenceFrame, FieldTimeInterpolator<TimeStampedFieldAngularCoordinates<KK>,KK> interpolator)	Constructor.
FixedFrameBuilder(Frame referenceFrame)	Creates new instance.
FrameAlignedProvider(Rotation rotation, Frame reference)	Creates new instance with a fixed attitude in the given frame.
FrameAlignedProvider(Frame frame)	Creates new instance aligned with the given frame.
GroundPointing(Frame inertialFrame, Frame bodyFrame)	Default constructor.
GroundPointingAttitudeModifier(Frame inertialFrame, Frame bodyFrame, GroundPointing groundPointingLaw)	Constructor.
LofOffset(Frame inertialFrame, LOF lof)	Create a LOF-aligned attitude.
LofOffset(Frame inertialFrame, LOF lof, RotationOrder order, double alpha1, double alpha2, double alpha3)	Creates new instance.
LofOffsetPointing(Frame inertialFrame, BodyShape shape, AttitudeProvider attLaw, Vector3D satPointingVector)	Creates new instance.
NadirPointing(Frame inertialFrame, BodyShape shape)	Creates new instance.
TabulatedLofOffset(Frame inertialFrame, LOF lof, List<? extends TimeStampedAngularCoordinates> table, int n, AngularDerivativesFilter filter)	Creates new instance.
TabulatedLofOffset(Frame inertialFrame, LOF lof, List<? extends TimeStampedAngularCoordinates> table, int n, AngularDerivativesFilter filter, AbsoluteDate minDate, AbsoluteDate maxDate)	Creates new instance.
TabulatedProvider(Frame referenceFrame, List<? extends TimeStampedAngularCoordinates> table, int n, AngularDerivativesFilter filter)	Creates new instance.
TargetPointing(Frame inertialFrame, GeodeticPoint targetGeo, BodyShape shape)	Creates a new instance from body shape and target expressed in geodetic coordinates.
TargetPointing(Frame inertialFrame, Frame bodyFrame, Vector3D target)	Creates a new instance from body frame and target expressed in Cartesian coordinates.
YawCompensation(Frame inertialFrame, GroundPointing groundPointingLaw)	Creates a new instance.
YawSteering(Frame inertialFrame, GroundPointing groundPointingLaw, ExtendedPositionProvider sun, Vector3D phasingAxis)	Creates a new instance.

Uses of Frame in org.orekit.bodies

Methods in org.orekit.bodies that return Frame

Modifier and Type	Method	Description
Frame	BodyShape.getBodyFrame()	Get body frame related to body shape.
Frame	OneAxisEllipsoid.getBodyFrame()	Get body frame related to body shape.
Frame	CelestialBody.getBodyOrientedFrame()	Get a body oriented, body centered frame.
Frame	Ellipse.getFrame()	Get the defining frame.
Frame	Ellipsoid.getFrame()	Get the ellipsoid central frame.
Frame	FieldEllipse.getFrame()	Get the defining frame.
Frame	CelestialBody.getInertiallyOrientedFrame()	Get an inertially oriented, body centered frame.
Frame	CR3BPSystem.getRotatingFrame()	Get the CR3BP Rotating Frame.

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

Modifier and Type	Method	Description
<T extends CalculusFieldElement<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.
Vector3D	OneAxisEllipsoid.getCartesianIntersectionPoint(Line line, Vector3D close, Frame frame, AbsoluteDate date)	Get the intersection point of a line with the surface of the body.
<T extends CalculusFieldElement<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.
GeodeticPoint	BodyShape.getIntersectionPoint(Line line, Vector3D close, Frame frame, AbsoluteDate date)	Get the intersection point of a line with the surface of the body.
<T extends CalculusFieldElement<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.
GeodeticPoint	OneAxisEllipsoid.getIntersectionPoint(Line line, Vector3D close, Frame frame, AbsoluteDate date)	Get the intersection point of a line with the surface of the body.
Vector3D	AnalyticalSolarPositionProvider.getPosition(AbsoluteDate date, Frame frame)	Get the position of the body in the selected frame.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	AnalyticalSolarPositionProvider.getPosition(FieldAbsoluteDate<T> date, Frame frame)	Get the position in the selected frame.
AbsolutePVCoordinates	CR3BPSystem.getRealAPV(AbsolutePVCoordinates apv0, AbsoluteDate initialDate, Frame outputFrame)	Get the AbsolutePVCoordinates from normalized units to standard units in an output frame.
Vector3D	BodyShape.projectToGround(Vector3D point, AbsoluteDate date, Frame frame)	Project a point to the ground.
TimeStampedPVCoordinates	BodyShape.projectToGround(TimeStampedPVCoordinates pv, Frame frame)	Project a moving point to the ground.
Vector3D	OneAxisEllipsoid.projectToGround(Vector3D point, AbsoluteDate date, Frame frame)	Project a point to the ground.
TimeStampedPVCoordinates	OneAxisEllipsoid.projectToGround(TimeStampedPVCoordinates pv, Frame frame)	Project a moving point to the ground.
<T extends CalculusFieldElement<T>> FieldGeodeticPoint<T>	BodyShape.transform(FieldVector3D<T> point, Frame frame, FieldAbsoluteDate<T> 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.
<T extends CalculusFieldElement<T>> FieldGeodeticPoint<T>	OneAxisEllipsoid.transform(FieldVector3D<T> point, Frame frame, FieldAbsoluteDate<T> date)	Transform a Cartesian point to a surface-relative point.
GeodeticPoint	OneAxisEllipsoid.transform(Vector3D point, Frame frame, AbsoluteDate date)	Transform a Cartesian point to a surface-relative point.
FieldGeodeticPoint<UnivariateDerivative2>	OneAxisEllipsoid.transform(PVCoordinates point, Frame frame, AbsoluteDate date)	Transform a Cartesian point to a surface-relative point.

Constructors in org.orekit.bodies with parameters of type Frame

Constructor	Description
Ellipse(Vector3D center, Vector3D u, Vector3D v, double a, double b, Frame frame)	Simple constructor.
Ellipsoid(Frame frame, double a, double b, double c)	Simple constructor.
FieldEllipse(FieldVector3D<T> center, FieldVector3D<T> u, FieldVector3D<T> v, T a, T b, Frame frame)	Simple constructor.
JPLEphemeridesLoader(String supportedNames, JPLEphemeridesLoader.EphemerisType generateType, DataProvidersManager dataProvidersManager, TimeScales timeScales, Frame gcrf)	Create a loader for JPL ephemerides binary files.
LazyLoadedCelestialBodies(DataProvidersManager dataProvidersManager, TimeScales timeScales, Frame gcrf)	Create a celestial body factory with the given auxiliary data sources.
OneAxisEllipsoid(double ae, double f, Frame bodyFrame)	Simple constructor.

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

Methods in org.orekit.control.indirect.adjoint that return Frame

Modifier and Type	Method	Description
Frame	CartesianAdjointInertialTerm.getReferenceInertialFrame()	Getter for reference frame.

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

Modifier and Type	Method	Description
protected <T extends CalculusFieldElement<T>> T[]	AbstractCartesianAdjointNonCentralBodyTerm.formFieldRelativePosition(FieldAbsoluteDate<T> date, T[] stateVariables, Frame frame)	Form relative position vector w.r.t. body.
protected double[]	AbstractCartesianAdjointNonCentralBodyTerm.formRelativePosition(AbsoluteDate date, double[] stateVariables, Frame frame)	Form relative position vector w.r.t. body.
protected abstract Vector3D	AbstractCartesianAdjointEquationTerm.getAcceleration(AbsoluteDate date, double[] stateVariables, Frame frame)	Compute the acceleration vector.
protected Vector3D	CartesianAdjointInertialTerm.getAcceleration(AbsoluteDate date, double[] stateVariables, Frame frame)	Compute the acceleration vector.
Vector3D	CartesianAdjointJ2Term.getAcceleration(AbsoluteDate date, double[] stateVariables, Frame frame)	Compute the acceleration vector.
protected Vector3D	CartesianAdjointKeplerianTerm.getAcceleration(AbsoluteDate date, double[] stateVariables, Frame frame)	Compute the acceleration vector.
Vector3D	CartesianAdjointSingleBodyTerm.getAcceleration(AbsoluteDate date, double[] stateVariables, Frame frame)	Compute the acceleration vector.
Vector3D	CartesianAdjointThirdBodyTerm.getAcceleration(AbsoluteDate date, double[] stateVariables, Frame frame)	Compute the acceleration vector.
protected Vector3D	AbstractCartesianAdjointNonCentralBodyTerm.getBodyPosition(AbsoluteDate date, Frame frame)	Get body's position.
protected abstract <T extends CalculusFieldElement<T>> FieldVector3D<T>	AbstractCartesianAdjointEquationTerm.getFieldAcceleration(FieldAbsoluteDate<T> date, T[] stateVariables, Frame frame)	Compute the acceleration vector.
protected <T extends CalculusFieldElement<T>> FieldVector3D<T>	CartesianAdjointInertialTerm.getFieldAcceleration(FieldAbsoluteDate<T> date, T[] stateVariables, Frame frame)	Compute the acceleration vector.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	CartesianAdjointJ2Term.getFieldAcceleration(FieldAbsoluteDate<T> date, T[] stateVariables, Frame frame)	Compute the acceleration vector.
protected <T extends CalculusFieldElement<T>> FieldVector3D<T>	CartesianAdjointKeplerianTerm.getFieldAcceleration(FieldAbsoluteDate<T> date, T[] stateVariables, Frame frame)	Compute the acceleration vector.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	CartesianAdjointSingleBodyTerm.getFieldAcceleration(FieldAbsoluteDate<T> date, T[] stateVariables, Frame frame)	Compute the acceleration vector.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	CartesianAdjointThirdBodyTerm.getFieldAcceleration(FieldAbsoluteDate<T> date, T[] stateVariables, Frame frame)	Compute the acceleration vector.
protected <T extends CalculusFieldElement<T>> FieldVector3D<T>	AbstractCartesianAdjointNonCentralBodyTerm.getFieldBodyPosition(FieldAbsoluteDate<T> date, Frame frame)	Get body's position.
<T extends CalculusFieldElement<T>> T	AbstractCartesianAdjointEquationTerm.getFieldHamiltonianContribution(FieldAbsoluteDate<T> date, T[] stateVariables, T[] adjointVariables, Frame frame)	Computes the contribution to the Hamiltonian.
<T extends CalculusFieldElement<T>> T	CartesianAdjointEquationTerm.getFieldHamiltonianContribution(FieldAbsoluteDate<T> date, T[] stateVariables, T[] adjointVariables, Frame frame)	Computes the contribution to the Hamiltonian.
<T extends CalculusFieldElement<T>> T[]	AbstractCartesianAdjointEquationTerm.getFieldRatesContribution(FieldAbsoluteDate<T> date, T[] stateVariables, T[] adjointVariables, Frame frame)	Computes the contribution to the rates of the adjoint variables.
<T extends CalculusFieldElement<T>> T[]	AbstractCartesianAdjointGravitationalTerm.getFieldRatesContribution(FieldAbsoluteDate<T> date, T[] stateVariables, T[] adjointVariables, Frame frame)	Computes the contribution to the rates of the adjoint variables.
<T extends CalculusFieldElement<T>> T[]	CartesianAdjointEquationTerm.getFieldRatesContribution(FieldAbsoluteDate<T> date, T[] stateVariables, T[] adjointVariables, Frame frame)	Computes the contribution to the rates of the adjoint variables.
<T extends CalculusFieldElement<T>> T[]	CartesianAdjointInertialTerm.getFieldRatesContribution(FieldAbsoluteDate<T> date, T[] stateVariables, T[] adjointVariables, Frame frame)	Computes the contribution to the rates of the adjoint variables.
double	AbstractCartesianAdjointEquationTerm.getHamiltonianContribution(AbsoluteDate date, double[] stateVariables, double[] adjointVariables, Frame frame)	Computes the contribution to the Hamiltonian.
double	CartesianAdjointEquationTerm.getHamiltonianContribution(AbsoluteDate date, double[] stateVariables, double[] adjointVariables, Frame frame)	Computes the contribution to the Hamiltonian.
protected abstract double[]	AbstractCartesianAdjointGravitationalTerm.getPositionAdjointContribution(AbsoluteDate date, double[] stateVariables, double[] adjointVariables, Frame frame)	Computes the contribution to position adjoint derivatives.
double[]	AbstractCartesianAdjointNonCentralBodyTerm.getPositionAdjointContribution(AbsoluteDate date, double[] stateVariables, double[] adjointVariables, Frame frame)	Computes the contribution to position adjoint derivatives.
double[]	CartesianAdjointJ2Term.getPositionAdjointContribution(AbsoluteDate date, double[] stateVariables, double[] adjointVariables, Frame frame)	Computes the contribution to position adjoint derivatives.
double[]	CartesianAdjointKeplerianTerm.getPositionAdjointContribution(AbsoluteDate date, double[] stateVariables, double[] adjointVariables, Frame frame)	Computes the contribution to position adjoint derivatives.
protected abstract <T extends CalculusFieldElement<T>> T[]	AbstractCartesianAdjointGravitationalTerm.getPositionAdjointFieldContribution(FieldAbsoluteDate<T> date, T[] stateVariables, T[] adjointVariables, Frame frame)	Computes the contribution to position adjoint derivatives.
<T extends CalculusFieldElement<T>> T[]	AbstractCartesianAdjointNonCentralBodyTerm.getPositionAdjointFieldContribution(FieldAbsoluteDate<T> date, T[] stateVariables, T[] adjointVariables, Frame frame)	Computes the contribution to position adjoint derivatives.
<T extends CalculusFieldElement<T>> T[]	CartesianAdjointJ2Term.getPositionAdjointFieldContribution(FieldAbsoluteDate<T> date, T[] stateVariables, T[] adjointVariables, Frame frame)	Computes the contribution to position adjoint derivatives.
<T extends CalculusFieldElement<T>> T[]	CartesianAdjointKeplerianTerm.getPositionAdjointFieldContribution(FieldAbsoluteDate<T> date, T[] stateVariables, T[] adjointVariables, Frame frame)	Computes the contribution to position adjoint derivatives.
double[]	AbstractCartesianAdjointEquationTerm.getRatesContribution(AbsoluteDate date, double[] stateVariables, double[] adjointVariables, Frame frame)	Computes the contribution to the rates of the adjoint variables.
double[]	AbstractCartesianAdjointGravitationalTerm.getRatesContribution(AbsoluteDate date, double[] stateVariables, double[] adjointVariables, Frame frame)	Computes the contribution to the rates of the adjoint variables.
double[]	CartesianAdjointEquationTerm.getRatesContribution(AbsoluteDate date, double[] stateVariables, double[] adjointVariables, Frame frame)	Computes the contribution to the rates of the adjoint variables.
double[]	CartesianAdjointInertialTerm.getRatesContribution(AbsoluteDate date, double[] stateVariables, double[] adjointVariables, Frame frame)	Computes the contribution to the rates of the adjoint variables.

Constructors in org.orekit.control.indirect.adjoint with parameters of type Frame

Constructor	Description
CartesianAdjointInertialTerm(Frame referenceInertialFrame)	Constructor.
CartesianAdjointJ2Term(double mu, double rEq, double j2, Frame j2Frame)	Constructor.

Uses of Frame in org.orekit.control.indirect.shooting.propagation

Methods in org.orekit.control.indirect.shooting.propagation that return Frame

Modifier and Type	Method	Description
Frame	ShootingPropagationSettings.getPropagationFrame()	Getter for the propagation frame.

Constructors in org.orekit.control.indirect.shooting.propagation with parameters of type Frame

Constructor	Description
ShootingPropagationSettings(List<ForceModel> forceModels, AdjointDynamicsProvider adjointDynamicsProvider, Frame propagationFrame, ShootingIntegrationSettings integrationSettings, AttitudeProvider attitudeProvider)	Constructor.

Uses of Frame in org.orekit.estimation.iod

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

Modifier and Type	Method	Description
Orbit	IodGauss.estimate(Frame outputFrame, Vector3D obsP1, AbsoluteDate obsDate1, Vector3D los1, Vector3D obsP2, AbsoluteDate obsDate2, Vector3D los2, Vector3D obsP3, AbsoluteDate obsDate3, Vector3D los3)	Estimate and orbit based on Gauss Intial Orbit Determination method.
Orbit	IodGauss.estimate(Frame outputFrame, AngularAzEl azEl1, AngularAzEl azEl2, AngularAzEl azEl3)	Estimate and orbit based on Gauss Intial Orbit Determination method.
Orbit	IodGauss.estimate(Frame outputFrame, AngularRaDec raDec1, AngularRaDec raDec2, AngularRaDec raDec3)	Estimate and orbit based on Gauss Intial Orbit Determination method.
Orbit	IodGibbs.estimate(Frame frame, Vector3D r1, AbsoluteDate date1, Vector3D r2, AbsoluteDate date2, Vector3D r3, AbsoluteDate date3)	Give an initial orbit estimation, assuming Keplerian motion.
Orbit	IodGibbs.estimate(Frame frame, Position p1, Position p2, Position p3)	Give an initial orbit estimation, assuming Keplerian motion.
Orbit	IodGibbs.estimate(Frame frame, PV pv1, PV pv2, PV pv3)	Give an initial orbit estimation, assuming Keplerian motion.
Orbit	IodGooding.estimate(Frame outputFrame, Vector3D O1, Vector3D O2, Vector3D O3, Vector3D lineOfSight1, AbsoluteDate dateObs1, Vector3D lineOfSight2, AbsoluteDate dateObs2, Vector3D lineOfSight3, AbsoluteDate dateObs3, double rho1init, double rho3init)	Estimate orbit from three line of sight.
Orbit	IodGooding.estimate(Frame outputFrame, Vector3D O1, Vector3D O2, Vector3D O3, Vector3D lineOfSight1, AbsoluteDate dateObs1, Vector3D lineOfSight2, AbsoluteDate dateObs2, Vector3D lineOfSight3, AbsoluteDate dateObs3, double rho1init, double rho3init, int nRev, boolean direction)	Estimate orbit from three line of sight.
Orbit	IodGooding.estimate(Frame outputFrame, AngularAzEl azEl1, AngularAzEl azEl2, AngularAzEl azEl3)	Estimate orbit from three angular (i.e., azimuth - elevation) observations.
Orbit	IodGooding.estimate(Frame outputFrame, AngularAzEl azEl1, AngularAzEl azEl2, AngularAzEl azEl3, double rho1init, double rho3init)	Estimate orbit from three angular observations.
Orbit	IodGooding.estimate(Frame outputFrame, AngularAzEl azEl1, AngularAzEl azEl2, AngularAzEl azEl3, double rho1init, double rho3init, int nRev, boolean direction)	Estimate orbit from three angular observations.
Orbit	IodGooding.estimate(Frame outputFrame, AngularAzEl azEl1, AngularAzEl azEl2, AngularAzEl azEl3, int nRev, boolean direction)	Estimate orbit from three angular (i.e., azimuth - elevation) observations.
Orbit	IodGooding.estimate(Frame outputFrame, AngularRaDec raDec1, AngularRaDec raDec2, AngularRaDec raDec3)	Estimate orbit from three angular (i.e., right ascension - declination) observations.
Orbit	IodGooding.estimate(Frame outputFrame, AngularRaDec raDec1, AngularRaDec raDec2, AngularRaDec raDec3, double rho1init, double rho3init)	Estimate orbit from three angular observations.
Orbit	IodGooding.estimate(Frame outputFrame, AngularRaDec raDec1, AngularRaDec raDec2, AngularRaDec raDec3, double rho1init, double rho3init, int nRev, boolean direction)	Estimate orbit from three angular observations.
Orbit	IodGooding.estimate(Frame outputFrame, AngularRaDec raDec1, AngularRaDec raDec2, AngularRaDec raDec3, int nRev, boolean direction)	Estimate orbit from three angular (i.e., right ascension - declination) observations.
Orbit	IodLambert.estimate(Frame frame, boolean posigrade, int nRev, Vector3D p1, AbsoluteDate t1, Vector3D p2, AbsoluteDate t2)	Estimate a Keplerian orbit given two position vectors and a duration.
Orbit	IodLambert.estimate(Frame frame, boolean posigrade, int nRev, Position p1, Position p2)	Estimate an initial orbit from two position measurements.
Orbit	IodLambert.estimate(Frame frame, boolean posigrade, int nRev, PV pv1, PV pv2)	Estimate an initial orbit from two PV measurements.
Orbit	IodLaplace.estimate(Frame outputFrame, AngularAzEl azEl1, AngularAzEl azEl2, AngularAzEl azEl3)	Estimate the orbit from three angular observations at the same location.
Orbit	IodLaplace.estimate(Frame outputFrame, AngularRaDec raDec1, AngularRaDec raDec2, AngularRaDec raDec3)	Estimate the orbit from three angular observations at the same location.
Orbit	IodLaplace.estimate(Frame outputFrame, PVCoordinates obsPva, AbsoluteDate obsDate1, Vector3D los1, AbsoluteDate obsDate2, Vector3D los2, AbsoluteDate obsDate3, Vector3D los3)	Estimate orbit from three line of sight angles at the same location.

Uses of Frame in org.orekit.estimation.measurements

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

Modifier and Type	Method	Description
Frame	GroundStation.getEstimatedEarthFrame()	Get the estimated Earth frame, including the estimated linear models for pole and prime meridian.
Frame	AngularRaDec.getReferenceFrame()	Get the reference frame in which the right ascension - declination angles are given.

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

Modifier and Type	Method	Description
PVCoordinates	GroundReceiverMeasurement.getGroundStationCoordinates(Frame frame)	Get the station coordinates for a given frame.
Vector3D	GroundReceiverMeasurement.getGroundStationPosition(Frame frame)	Get the station position for a given frame.
Vector3D	AngularAzEl.getObservedLineOfSight(Frame outputFrame)	Calculate the Line Of Sight of the given measurement.
Vector3D	AngularRaDec.getObservedLineOfSight(Frame outputFrame)	Calculate the Line Of Sight of the given measurement.
Transform	GroundStation.getOffsetToInertial(Frame inertial, AbsoluteDate date, boolean clockOffsetAlreadyApplied)	Get the transform between offset frame and inertial frame.
FieldTransform<Gradient>	GroundStation.getOffsetToInertial(Frame inertial, AbsoluteDate clockDate, int freeParameters, Map<String,Integer> indices)	Get the transform between offset frame and inertial frame with derivatives.
FieldTransform<Gradient>	GroundStation.getOffsetToInertial(Frame inertial, FieldAbsoluteDate<Gradient> offsetCompensatedDate, int freeParameters, Map<String,Integer> indices)	Get the transform between offset frame and inertial frame with derivatives.
static <T extends CalculusFieldElement<T>> T	AbstractMeasurement.signalTimeOfFlightAdjustableEmitter(FieldPVCoordinatesProvider<T> adjustableEmitter, FieldAbsoluteDate<T> approxEmissionDate, FieldVector3D<T> receiverPosition, FieldAbsoluteDate<T> signalArrivalDate, Frame frame)	Compute propagation delay on a link leg (typically downlink or uplink).
static double	AbstractMeasurement.signalTimeOfFlightAdjustableEmitter(PVCoordinatesProvider adjustableEmitter, AbsoluteDate approxEmissionDate, Vector3D receiverPosition, AbsoluteDate signalArrivalDate, Frame frame)	Compute propagation delay on a link leg (typically downlink or uplink).
static <T extends CalculusFieldElement<T>> T	AbstractMeasurement.signalTimeOfFlightAdjustableEmitter(TimeStampedFieldPVCoordinates<T> adjustableEmitterPV, FieldVector3D<T> receiverPosition, FieldAbsoluteDate<T> signalArrivalDate, Frame frame)	Compute propagation delay on a link leg (typically downlink or uplink).
static double	AbstractMeasurement.signalTimeOfFlightAdjustableEmitter(TimeStampedPVCoordinates adjustableEmitterPV, Vector3D receiverPosition, AbsoluteDate signalArrivalDate, Frame frame)	Compute propagation delay on a link leg (typically downlink or uplink).
static <T extends CalculusFieldElement<T>> T	AbstractMeasurement.signalTimeOfFlightAdjustableReceiver(FieldVector3D<T> emitterPosition, FieldAbsoluteDate<T> emissionDate, FieldPVCoordinatesProvider<T> adjustableReceiver, FieldAbsoluteDate<T> approxReceptionDate, Frame frame)	Compute propagation delay on a link leg (typically downlink or uplink).
static <T extends CalculusFieldElement<T>> T	AbstractMeasurement.signalTimeOfFlightAdjustableReceiver(FieldVector3D<T> emitterPosition, FieldAbsoluteDate<T> emissionDate, TimeStampedFieldPVCoordinates<T> adjustableReceiverPV, FieldAbsoluteDate<T> approxReceptionDate, Frame frame)	Compute propagation delay on a link leg (typically downlink or uplink).
static double	AbstractMeasurement.signalTimeOfFlightAdjustableReceiver(Vector3D emitterPosition, AbsoluteDate emissionDate, PVCoordinatesProvider adjustableReceiver, AbsoluteDate approxReceptionDate, Frame frame)	Compute propagation delay on a link leg (typically downlink or uplink).
static double	AbstractMeasurement.signalTimeOfFlightAdjustableReceiver(Vector3D emitterPosition, AbsoluteDate emissionDate, TimeStampedPVCoordinates adjustableReceiverPV, AbsoluteDate approxReceptionDate, Frame frame)	Compute propagation delay on a link leg (typically downlink or uplink).

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

Constructor	Description
AngularRaDec(GroundStation station, Frame referenceFrame, AbsoluteDate date, double[] angular, double[] sigma, double[] baseWeight, ObservableSatellite satellite)	Simple constructor.

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

Constructors in org.orekit.estimation.measurements.generation with parameters of type Frame

Constructor	Description
AngularRaDecBuilder(CorrelatedRandomVectorGenerator noiseSource, GroundStation station, Frame referenceFrame, double[] sigma, double[] baseWeight, ObservableSatellite satellite)	Simple constructor.

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

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

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

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

Subclasses of Frame in org.orekit.files.ccsds.definitions

Modifier and Type	Class	Description
class	ModifiedFrame	A reference frame created from the REF_FRAME and CENTER_NAME is a CCSDS OPM, OMM, or OEM file.

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

Modifier and Type	Method	Description
Frame	FrameFacade.asFrame()	Get the associated frame tree node.
abstract Frame	CelestialBodyFrame.getFrame(IERSConventions conventions, boolean simpleEOP, DataContext dataContext)	Get the frame corresponding to the CCSDS constant.

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

Modifier and Type	Method	Description
static Transform	FrameFacade.getTransform(FrameFacade frameIn, FrameFacade frameOut, Frame inertialPivotFrame, AbsoluteDate date, PVCoordinatesProvider pv)	Get the transform between CCSDS frames.
static String	CenterName.guessCenter(Frame frame)	Guess the name of the center of the reference frame.
static String	CelestialBodyFrame.guessFrame(Frame frame)	Guesses names from ODM Table 5-3 and Annex A.
static CelestialBodyFrame	CelestialBodyFrame.map(Frame frame)	Map an Orekit frame to a CCSDS frame.
static CenterName	CenterName.map(Frame frame)	Map an Orekit frame to a CCSDS center.
static FrameFacade	FrameFacade.map(Frame frame)	Map an Orekit frame to a CCSDS frame facade.

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

Constructor	Description
FrameFacade(Frame frame, CelestialBodyFrame celestialBodyFrame, OrbitRelativeFrame orbitRelativeFrame, SpacecraftBodyFrame spacecraftBodyFrame, String name)	Simple constructor.
ModifiedFrame(Frame frame, CelestialBodyFrame refFrame, CelestialBody body, String centerName)	Create a CCSDS reference frame by changing the origin of an existing frame.

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

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

Modifier and Type	Method	Description
<T extends CalculusFieldElement<T>> FieldAttitude<T>	AttitudeEndpoints.build(Frame frame, FieldPVCoordinatesProvider<T> pvProv, TimeStampedFieldAngularCoordinates<T> rawAttitude)	Build a filtered attitude.
Attitude	AttitudeEndpoints.build(Frame frame, PVCoordinatesProvider pvProv, TimeStampedAngularCoordinates rawAttitude)	Build a filtered attitude.

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

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

Modifier and Type	Method	Description
Frame	AttitudeStateHistory.getReferenceFrame()	Get the reference frame from which attitude is defined.

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

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

Modifier and Type	Method	Description
Frame	AemSegment.getReferenceFrame()	Get the reference frame from which attitude is defined.

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

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

Modifier and Type	Method	Description
Attitude	Apm.getAttitude(Frame frame, PVCoordinatesProvider pvProvider)	Get the attitude.
Attitude	ApmData.getAttitude(Frame frame, PVCoordinatesProvider pvProvider)	Get the attitude.

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

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

Modifier and Type	Method	Description
Frame	CdmMetadata.getFrame()	Get the reference frame in which data are given: used for state vector and Keplerian elements data (and for the covariance reference frame if none is given).

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

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

Modifier and Type	Method	Description
Frame	OdmCommonMetadata.getFrame()	Get the reference frame in which data are given: used for state vector and Keplerian elements data (and for the covariance reference frame if none is given).

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

Modifier and Type	Method	Description
KeplerianOrbit	KeplerianElements.generateKeplerianOrbit(Frame frame)	Generate a keplerian orbit.

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

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

Modifier and Type	Method	Description
Frame	TrajectoryStateHistory.getFrame()	Get the reference frame for this ephemeris segment.

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

Modifier and Type	Method	Description
double[]	OrbitElementsType.toRawElements(TimeStampedPVCoordinates pv, Frame frame, OneAxisEllipsoid body, double mu)	Convert to raw elements array.

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

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

Modifier and Type	Method	Description
Frame	OemSegment.getFrame()	Get the reference frame for this ephemeris segment.
Frame	OemSegment.getInertialFrame()	Get the inertial reference frame for this ephemeris segment.

Uses of Frame in org.orekit.files.general

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

Modifier and Type	Method	Description
Frame	EphemerisFile.EphemerisSegment.getFrame()	Get the reference frame for this ephemeris segment.
Frame	OrekitEphemerisFile.OrekitEphemerisSegment.getFrame()	Get the reference frame for this ephemeris segment.
default Frame	EphemerisFile.EphemerisSegment.getInertialFrame()	Get the inertial reference frame for this ephemeris segment.
Frame	OrekitEphemerisFile.OrekitEphemerisSegment.getInertialFrame()	Get the inertial reference frame for this ephemeris segment.
Frame	AttitudeEphemerisFile.AttitudeEphemerisSegment.getReferenceFrame()	Get the reference frame from which attitude is defined.
Frame	OrekitAttitudeEphemerisFile.OrekitAttitudeEphemerisSegment.getReferenceFrame()	Get the reference frame from which attitude is defined.

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

Modifier and Type	Method	Description
Vector3D	EphemerisSegmentPropagator.getPosition(AbsoluteDate date, Frame frame)
TimeStampedPVCoordinates	EphemerisSegmentPropagator.getPVCoordinates(AbsoluteDate date, Frame frame)

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

Constructor	Description
OrekitAttitudeEphemerisSegment(List<TimeStampedAngularCoordinates> attitudeDataLines, String interpolationMethod, int interpolationSamples, Frame referenceFrame, AngularDerivativesFilter availableDerivatives)	Constructor for OrekitAttitudeEphemerisSegment.
OrekitEphemerisSegment(List<TimeStampedPVCoordinates> coordinates, Frame frame, double mu, int interpolationSamples)	constructor for OrekitEphemerisSegment.

Uses of Frame in org.orekit.files.iirv

Methods in org.orekit.files.iirv that return Frame

Modifier and Type	Method	Description
Frame	IIRVSegment.getFrame()	Get the reference frame for this ephemeris segment.
Frame	IIRVVector.getFrame()	Returns the Frame associated with the IIRV vector based on its CoordinateSystemTerm.
Frame	IIRVVector.getFrame(DataContext context)	Returns the Frame associated with the IIRV vector based on its CoordinateSystemTerm.

Uses of Frame in org.orekit.files.iirv.terms

Methods in org.orekit.files.iirv.terms that return Frame

Modifier and Type	Method	Description
Frame	CoordinateSystemTerm.getFrame()	Returns the Frame specified within the IIRV using the default data context.
Frame	CoordinateSystemTerm.getFrame(DataContext context)	Returns the Frame specified within the IIRV.

Uses of Frame in org.orekit.files.ilrs

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

Modifier and Type	Method	Description
Frame	CPF.CPFEphemeris.getFrame()	Get the reference frame for this ephemeris segment.
Frame	CPFHeader.getRefFrame()	Get the reference frame.

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

Modifier and Type	Method	Description
StreamingCpfWriter.Segment	StreamingCpfWriter.newSegment(Frame frame)	Create a writer for a new CPF ephemeris segment.
void	CPFHeader.setRefFrame(Frame refFrame)	Set the reference frame.

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

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

Modifier and Type	Method	Description
Frame	RinexClock.getFrame()	Get the reference frame for the station positions.

Constructor parameters in org.orekit.files.rinex.clock with type arguments of type Frame

Constructor	Description
RinexClock(Function<? super String,? extends Frame> frameBuilder)	Constructor.
RinexClockParser(Function<? super String,? extends Frame> frameBuilder)	Create a clock file parser and specify the frame builder.
RinexClockParser(Function<? super String,? extends Frame> frameBuilder, Function<? super String,? extends ObservationType> typeBuilder, TimeScales timeScales)	Constructor, build the IGS clock file parser.

Uses of Frame in org.orekit.files.sp3

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

Modifier and Type	Method	Description
Frame	SP3Ephemeris.getFrame()	Get the reference frame.
Frame	SP3Segment.getFrame()	Get the reference frame for this ephemeris segment.

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

Modifier and Type	Method	Description
static SP3	SP3.changeFrame(SP3 original, Frame newFrame)	Change the frame of an SP3 file.

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

Constructor	Description
SP3(double mu, int interpolationSamples, Frame frame)	Create a new SP3 file object.
SP3(SP3Header header, double mu, int interpolationSamples, Frame frame)	Create a new SP3 file object.
SP3Ephemeris(String id, double mu, Frame frame, int interpolationSamples, CartesianDerivativesFilter filter)	Create an ephemeris for a single satellite.
SP3Segment(double mu, Frame frame, int interpolationSamples, CartesianDerivativesFilter filter)	Simple constructor.

Constructor parameters in org.orekit.files.sp3 with type arguments of type Frame

Constructor	Description
SP3Parser(double mu, int interpolationSamples, Function<? super String,? extends Frame> frameBuilder)	Create an SP3 parser and specify the extra information needed to create a Propagator from the ephemeris data.
SP3Parser(double mu, int interpolationSamples, Function<? super String,? extends Frame> frameBuilder, TimeScales timeScales)	Create an SP3 parser and specify the extra information needed to create a Propagator from the ephemeris data.

Uses of Frame in org.orekit.files.stk

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

Modifier and Type	Method	Description
Frame	STKEphemerisFile.STKEphemerisSegment.getFrame()

Constructors in org.orekit.files.stk with parameters of type Frame

Constructor	Description
STKEphemerisSegment(double mu, Frame frame, int interpolationSamples, CartesianDerivativesFilter cartesianDerivativesFilter, List<TimeStampedPVCoordinates> timeStampedPVCoordinates)	Constructs a STKEphemerisFile.STKEphemerisSegment instance.

Constructor parameters in org.orekit.files.stk with type arguments of type Frame

Constructor	Description
STKEphemerisFileParser(String satelliteId, double mu, UTCScale utc, Map<STKEphemerisFile.STKCoordinateSystem,Frame> frameMapping)	Constructs a STKEphemerisFileParser instance.

Uses of Frame in org.orekit.forces.drag

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

Modifier and Type	Method	Description
protected DerivativeStructure	AbstractDragForceModel.getDSDensityWrtState(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position)	Compute density and its derivatives.
protected DerivativeStructure	AbstractDragForceModel.getDSDensityWrtStateUsingFiniteDifferences(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position)	Compute density and its derivatives.
protected Gradient	AbstractDragForceModel.getGradientDensityWrtState(AbsoluteDate date, Frame frame, FieldVector3D<Gradient> position)	Compute density and its derivatives.
protected Gradient	AbstractDragForceModel.getGradientDensityWrtStateUsingFiniteDifferences(AbsoluteDate date, Frame frame, FieldVector3D<Gradient> position)	Compute density and its derivatives.

Uses of Frame in org.orekit.forces.gravity

Methods in org.orekit.forces.gravity that return Frame

Modifier and Type	Method	Description
Frame	J2OnlyPerturbation.getFrame()	Getter for frame.

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

Modifier and Type	Method	Description
protected Vector3D	AbstractBodyAttraction.getBodyPosition(AbsoluteDate date, Frame frame)	Get the body's position vector.
protected <T extends CalculusFieldElement<T>> FieldVector3D<T>	AbstractBodyAttraction.getBodyPosition(FieldAbsoluteDate<T> date, Frame frame)	Get the body's position vector.
protected TimeStampedPVCoordinates	AbstractBodyAttraction.getBodyPVCoordinates(AbsoluteDate date, Frame frame)	Get the body's position-velocity-acceleration vector.
protected <T extends CalculusFieldElement<T>> TimeStampedFieldPVCoordinates<T>	AbstractBodyAttraction.getBodyPVCoordinates(FieldAbsoluteDate<T> date, Frame frame)	Get the body's position-velocity-acceleration vector.

Constructors in org.orekit.forces.gravity with parameters of type Frame

Constructor	Description
HolmesFeatherstoneAttractionModel(Frame centralBodyFrame, NormalizedSphericalHarmonicsProvider provider)	Creates a new instance.
J2OnlyPerturbation(double mu, double rEq, double constantJ2, Frame frame)	Constructor with constant J2.
J2OnlyPerturbation(double mu, double rEq, TimeScalarFunction j2OverTime, Frame frame)	Constructor with TimeScalarFunction.
J2OnlyPerturbation(UnnormalizedSphericalHarmonicsProvider harmonicsProvider, Frame frame)	Constructor with spherical harmonics provider.
LenseThirringRelativity(double gm, Frame bodyFrame)	Constructor.
OceanTides(Frame centralBodyFrame, double ae, double mu, boolean poleTide, double step, int nbPoints, int degree, int order, IERSConventions conventions, UT1Scale ut1)	Simple constructor.
OceanTides(Frame centralBodyFrame, double ae, double mu, boolean poleTide, double step, int nbPoints, int degree, int order, IERSConventions conventions, UT1Scale ut1, GravityFields gravityFields)	Simple constructor.
OceanTides(Frame centralBodyFrame, double ae, double mu, int degree, int order, IERSConventions conventions, UT1Scale ut1)	Simple constructor.
SolidTides(Frame centralBodyFrame, double ae, double mu, TideSystem centralTideSystem, boolean poleTide, double step, int nbPoints, IERSConventions conventions, UT1Scale ut1, CelestialBody... bodies)	Simple constructor.
SolidTides(Frame centralBodyFrame, double ae, double mu, TideSystem centralTideSystem, IERSConventions conventions, UT1Scale ut1, CelestialBody... bodies)	Simple constructor.

Uses of Frame in org.orekit.forces.inertia

Constructors in org.orekit.forces.inertia with parameters of type Frame

Constructor	Description
InertialForces(Frame referenceInertialFrame)	Simple constructor.

Uses of Frame in org.orekit.forces.maneuvers

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

Modifier and Type	Method	Description
Frame	SmallManeuverAnalyticalModel.getInertialFrame()	Get the inertial frame in which the velocity increment is defined.

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

Constructor	Description
SmallManeuverAnalyticalModel(SpacecraftState state0, Frame frame, Vector3D dV, double isp)	Build a maneuver defined in user-specified frame.
SmallManeuverAnalyticalModel(SpacecraftState state0, OrbitType orbitType, Frame frame, Vector3D dV, double isp)	Build a maneuver defined in user-specified frame.

Uses of Frame in org.orekit.forces.radiation

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

Modifier and Type	Method	Description
protected Vector3D	AbstractLightFluxModel.getOccultedBodyPosition(AbsoluteDate date, Frame frame)	Method computing the occulted body's position at a given date and frame.
protected <T extends CalculusFieldElement<T>> FieldVector3D<T>	AbstractLightFluxModel.getOccultedBodyPosition(FieldAbsoluteDate<T> date, Frame frame)	Method computing the occulted body's position at a given date and frame.

Uses of Frame in org.orekit.frames

Subclasses of Frame in org.orekit.frames

Modifier and Type	Class	Description
class	CR3BPRotatingFrame	Class creating the rotating frame centered on the barycenter of the CR3BP System.
class	FactoryManagedFrame	Base class for the predefined frames that are managed by Frames.
class	L1Frame	Class to create a L1 centered frame with L1TransformProvider.
class	L2Frame	Class to create a L2 centered frame with L2TransformProvider.
class	LocalOrbitalFrame	Class for frames moving with an orbiting satellite.
class	TopocentricFrame	Topocentric frame.
class	TwoBodiesBaryFrame	Class creating the inertial barycenter frame from two bodies.
class	UpdatableFrame	Frame whose transform from its parent can be updated.
class	VersionedITRF	Specific version of International Terrestrial Reference Frame.

Methods in org.orekit.frames that return Frame

Modifier and Type	Method	Description
Frame	AbstractFrames.buildUncachedITRF(UT1Scale ut1)
Frame	Frames.buildUncachedITRF(UT1Scale ut1)	Build an uncached International Terrestrial Reference Frame with specific EOP history.
static Frame	FramesFactory.buildUncachedITRF(EOPHistory eopHistory, UTCScale utc)	Build an uncached International Terrestrial Reference Frame with specific EOP history.
Frame	HelmertTransformation.Predefined.createTransformedITRF(Frame parent, String name)	Create an ITRF frame by transforming another ITRF frame.
Frame	HelmertTransformation.Predefined.createTransformedITRF(Frame parent, String name, TimeScale tt)	Create an ITRF frame by transforming another ITRF frame.
Frame	Frame.getAncestor(int n)	Get the nth ancestor of the frame.
Frame	AbstractFrames.getEcliptic(IERSConventions conventions)
Frame	Frames.getEcliptic(IERSConventions conventions)	Get the ecliptic frame.
static Frame	FramesFactory.getEcliptic(IERSConventions conventions)	Get the ecliptic frame.
Frame	AbstractFrames.getFrame(Predefined factoryKey)
Frame	Frames.getFrame(Predefined factoryKey)	Get one of the predefined frames.
static Frame	FramesFactory.getFrame(Predefined factoryKey)	Get one of the predefined frames.
Frame	OrphanFrame.getFrame()	Get the associated frame.
Frame	Frame.getFrozenFrame(Frame reference, AbsoluteDate freezingDate, String frozenName)	Get a new version of the instance, frozen with respect to a reference frame.
Frame	AbstractFrames.getGCRF()
Frame	Frames.getGCRF()	Get the unique GCRF frame.
static Frame	FramesFactory.getGCRF()	Get the unique GCRF frame.
Frame	AbstractFrames.getICRF()
Frame	Frames.getICRF()	Get the unique ICRF frame.
static Frame	FramesFactory.getICRF()	Get the unique ICRF frame.
Frame	LocalMagneticFieldFrame.getInertialFrame()	Get interlai frame.
Frame	Frame.getParent()	Get the parent frame.
static Frame	Frame.getRoot()	Get the unique root frame.

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

Modifier and Type	Method	Description
void	OrphanFrame.attachTo(Frame parent, Transform transform, boolean isPseudoInertial)	Attach the instance (and all its children down to leafs) to the main tree.
void	OrphanFrame.attachTo(Frame parent, TransformProvider transformProvider, boolean isPseudoInertial)	Attach the instance (and all its children down to leafs) to the main tree.
Frame	HelmertTransformation.Predefined.createTransformedITRF(Frame parent, String name)	Create an ITRF frame by transforming another ITRF frame.
Frame	HelmertTransformation.Predefined.createTransformedITRF(Frame parent, String name, TimeScale tt)	Create an ITRF frame by transforming another ITRF frame.
static EOPHistory	FramesFactory.findEOP(Frame start)	Retrieve EOP from a frame hierarchy.
<T extends CalculusFieldElement<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.
double	TopocentricFrame.getAzimuth(Vector3D extPoint, Frame frame, AbsoluteDate date)	Get the azimuth of a point with regards to the topocentric frame center point.
<T extends CalculusFieldElement<T>> T	TopocentricFrame.getElevation(FieldVector3D<T> extPoint, Frame frame, FieldAbsoluteDate<T> date)	Get the elevation of a point with regards to the local point.
double	TopocentricFrame.getElevation(Vector3D extPoint, Frame frame, AbsoluteDate date)	Get the elevation of a point with regards to the local point.
Frame	Frame.getFrozenFrame(Frame reference, AbsoluteDate freezingDate, String frozenName)	Get a new version of the instance, frozen with respect to a reference frame.
KinematicTransform	Frame.getKinematicTransformTo(Frame destination, AbsoluteDate date)	Get the kinematic portion of the transform from the instance to another frame.
<T extends CalculusFieldElement<T>> FieldKinematicTransform<T>	Frame.getKinematicTransformTo(Frame destination, FieldAbsoluteDate<T> date)	Get the kinematic portion of the transform from the instance to another frame.
static Transform	FramesFactory.getNonInterpolatingTransform(Frame from, Frame to, AbsoluteDate date)	Get the transform between two frames, suppressing all interpolation.
static <T extends CalculusFieldElement<T>> FieldTransform<T>	FramesFactory.getNonInterpolatingTransform(Frame from, Frame to, FieldAbsoluteDate<T> date)	Get the transform between two frames, suppressing all interpolation.
Vector3D	TopocentricFrame.getPosition(AbsoluteDate date, Frame frame)	Get the position of the body in the selected frame.
TimeStampedPVCoordinates	TopocentricFrame.getPVCoordinates(AbsoluteDate date, Frame frame)	Get the PVCoordinates of the topocentric frame origin in the selected frame.
<T extends CalculusFieldElement<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.
double	TopocentricFrame.getRange(Vector3D extPoint, Frame frame, AbsoluteDate date)	Get the range of a point with regards to the topocentric frame center point.
<T extends CalculusFieldElement<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.
double	TopocentricFrame.getRangeRate(PVCoordinates extPV, Frame frame, AbsoluteDate date)	Get the range rate of a point with regards to the topocentric frame center point.
StaticTransform	Frame.getStaticTransformTo(Frame destination, AbsoluteDate date)	Get the static portion of the transform from the instance to another frame.
<T extends CalculusFieldElement<T>> FieldStaticTransform<T>	Frame.getStaticTransformTo(Frame destination, FieldAbsoluteDate<T> date)	Get the static portion of the transform from the instance to another frame.
<T extends CalculusFieldElement<T>> FieldTrackingCoordinates<T>	TopocentricFrame.getTrackingCoordinates(FieldVector3D<T> extPoint, Frame frame, FieldAbsoluteDate<T> date)	Get the tracking coordinates of a point with regards to the local point.
TrackingCoordinates	TopocentricFrame.getTrackingCoordinates(Vector3D extPoint, Frame frame, AbsoluteDate date)	Get the tracking coordinates of a point with regards to the local point.
Transform	Frame.getTransformTo(Frame destination, AbsoluteDate date)	Get the transform from the instance to another frame.
<T extends CalculusFieldElement<T>> FieldTransform<T>	Frame.getTransformTo(Frame destination, FieldAbsoluteDate<T> date)	Get the transform from the instance to another frame.
boolean	Frame.isChildOf(Frame potentialAncestor)	Determine if a Frame is a child of another one.
void	UpdatableFrame.updateTransform(Frame f1, Frame f2, Transform f1Tof2, AbsoluteDate date)	Update the transform from parent frame implicitly according to two other frames.

Method parameters in org.orekit.frames with type arguments of type Frame

Modifier and Type	Method	Description
static Frames	Frames.of(TimeScales timeScales, Supplier<Frame> icrfSupplier)	Create a set of frames from the given data.

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

Constructor	Description
FactoryManagedFrame(Frame parent, TransformProvider transformProvider, boolean pseudoInertial, Predefined factoryKey)	Simple constructor.
Frame(Frame parent, TransformProvider transformProvider, String name)	Build a non-inertial frame from its transform with respect to its parent.
Frame(Frame parent, TransformProvider transformProvider, String name, boolean pseudoInertial)	Build a frame from its transform with respect to its parent.
Frame(Frame parent, Transform transform, String name)	Build a non-inertial frame from its transform with respect to its parent.
Frame(Frame parent, Transform transform, String name, boolean pseudoInertial)	Build a frame from its transform with respect to its parent.
LocalMagneticFieldFrame(Frame inertialFrame, GeoMagneticField magneticField, Frame bodyFrame)	Constructor with default definition of the local orbital frame: x: Magnetic field y: Completes orthonormal frame z: Cross product of the magnetic field with the orbital momentum .
LocalMagneticFieldFrame(Frame inertialFrame, GeoMagneticField magneticField, LocalMagneticFieldFrame.LOFBuilderVector lofBuilderVector, Frame bodyFrame)	Constructor with custom definition of the local orbital frame: x: Magnetic field y: Completes orthonormal frame z: Cross product of the magnetic field with chosen vector For near-polar orbits, it is suggested to use the orbital momentum to define the local orbital frame.
LocalOrbitalFrame(Frame parent, LOF lof, PVCoordinatesProvider provider, String name)	Build a new instance.
UpdatableFrame(Frame parent, Transform transform, String name)	Build a non-inertial frame from its transform with respect to its parent.
UpdatableFrame(Frame parent, Transform transform, String name, boolean pseudoInertial)	Build a frame from its transform with respect to its parent.

Constructor parameters in org.orekit.frames with type arguments of type Frame

Constructor	Description
AbstractFrames(TimeScales timeScales, Supplier<Frame> icrfSupplier)	Simple constructor.

Uses of Frame in org.orekit.gnss

Methods in org.orekit.gnss that return Frame

Modifier and Type	Method	Description
static Frame	IGSUtils.guessFrame(String name)	Default string to Frame conversion for SP3Parser or RinexClockParser.
static Frame	IGSUtils.guessFrame(Frames frames, String name)	Default string to Frame conversion for SP3Parser or RinexClockParser.

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

Modifier and Type	Method	Description
static String	IGSUtils.frameName(Frame frame)	Guess a frame name.

Uses of Frame in org.orekit.gnss.antenna

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

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

Uses of Frame in org.orekit.gnss.attitude

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

Constructor	Description
BeidouGeo(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPositionProvider sun, Frame inertialFrame)	Simple constructor.
BeidouIGSO(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPositionProvider sun, Frame inertialFrame)	Simple constructor.
BeidouMeo(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPositionProvider sun, Frame inertialFrame)	Simple constructor.
Galileo(double yawRate, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPositionProvider sun, Frame inertialFrame)	Simple constructor.
GenericGNSS(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPositionProvider sun, Frame inertialFrame)	Simple constructor.
Glonass(double yawRate, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPositionProvider sun, Frame inertialFrame)	Simple constructor.
GPSBlockIIA(double yawRate, double yawBias, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPositionProvider sun, Frame inertialFrame)	Simple constructor.
GPSBlockIIF(double yawRate, double yawBias, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPositionProvider sun, Frame inertialFrame)	Simple constructor.
GPSBlockIIR(double yawRate, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPositionProvider sun, Frame inertialFrame)	Simple constructor.

Uses of Frame in org.orekit.models.earth

Methods in org.orekit.models.earth that return Frame

Modifier and Type	Method	Description
Frame	Geoid.getBodyFrame()

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

Modifier and Type	Method	Description
static ReferenceEllipsoid	ReferenceEllipsoid.getGrs80(Frame bodyFrame)	Get the GRS80 ellipsoid, attached to the given body frame.
static ReferenceEllipsoid	ReferenceEllipsoid.getIers2003(Frame bodyFrame)	Get the IERS2003 ellipsoid, attached to the given body frame.
static ReferenceEllipsoid	ReferenceEllipsoid.getIers2010(Frame bodyFrame)	Get the IERS2010 ellipsoid, attached to the given body frame.
static ReferenceEllipsoid	ReferenceEllipsoid.getIers96(Frame bodyFrame)	Get the IERS96 ellipsoid, attached to the given body frame.
<T extends CalculusFieldElement<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.
GeodeticPoint	Geoid.getIntersectionPoint(Line lineInFrame, Vector3D closeInFrame, Frame frame, AbsoluteDate date)	Get the intersection point of a line with the surface of the body.
static ReferenceEllipsoid	ReferenceEllipsoid.getWgs84(Frame bodyFrame)	Get the WGS84 ellipsoid, attached to the given body frame.
Vector3D	Geoid.projectToGround(Vector3D point, AbsoluteDate date, Frame frame)
TimeStampedPVCoordinates	Geoid.projectToGround(TimeStampedPVCoordinates pv, Frame frame)
<T extends CalculusFieldElement<T>> FieldGeodeticPoint<T>	Geoid.transform(FieldVector3D<T> point, Frame frame, FieldAbsoluteDate<T> date)	Transform a Cartesian point to a surface-relative point.
GeodeticPoint	Geoid.transform(Vector3D point, Frame frame, AbsoluteDate date)	Transform a Cartesian point to a surface-relative point.

Constructors in org.orekit.models.earth with parameters of type Frame

Constructor	Description
ReferenceEllipsoid(double ae, double f, Frame bodyFrame, double GM, double spin)	Creates a new geodetic Reference Ellipsoid from four defining parameters.

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

Methods in org.orekit.models.earth.atmosphere that return Frame

Modifier and Type	Method	Description
Frame	Atmosphere.getFrame()	Get the frame of the central body.
Frame	DTM2000.getFrame()	Get the frame of the central body.
Frame	HarrisPriester.getFrame()	Get the frame of the central body.
Frame	JB2008.getFrame()	Get the frame of the central body.
Frame	NRLMSISE00.getFrame()	Get the frame of the central body.
Frame	SimpleExponentialAtmosphere.getFrame()	Get the frame of the central body.

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

Modifier and Type	Method	Description
double	Atmosphere.getDensity(AbsoluteDate date, Vector3D position, Frame frame)	Get the local density.
<T extends CalculusFieldElement<T>> T	Atmosphere.getDensity(FieldAbsoluteDate<T> date, FieldVector3D<T> position, Frame frame)	Get the local density.
double	DTM2000.getDensity(AbsoluteDate date, Vector3D position, Frame frame)	Get the local density.
<T extends CalculusFieldElement<T>> T	DTM2000.getDensity(FieldAbsoluteDate<T> date, FieldVector3D<T> position, Frame frame)	Get the local density.
double	HarrisPriester.getDensity(AbsoluteDate date, Vector3D position, Frame frame)	Get the local density at some position.
<T extends CalculusFieldElement<T>> T	HarrisPriester.getDensity(FieldAbsoluteDate<T> date, FieldVector3D<T> position, Frame frame)	Get the local density at some position.
double	JB2008.getDensity(AbsoluteDate date, Vector3D position, Frame frame)	Get the local density.
<T extends CalculusFieldElement<T>> T	JB2008.getDensity(FieldAbsoluteDate<T> date, FieldVector3D<T> position, Frame frame)	Get the local density.
double	NRLMSISE00.getDensity(AbsoluteDate date, Vector3D position, Frame frame)	Get the local density.
<T extends CalculusFieldElement<T>> T	NRLMSISE00.getDensity(FieldAbsoluteDate<T> date, FieldVector3D<T> position, Frame frame)	Get the local density.
double	SimpleExponentialAtmosphere.getDensity(AbsoluteDate date, Vector3D position, Frame frame)	Get the local density.
<T extends CalculusFieldElement<T>> T	SimpleExponentialAtmosphere.getDensity(FieldAbsoluteDate<T> date, FieldVector3D<T> position, Frame frame)
protected Vector3D	AbstractSunInfluencedAtmosphere.getSunPosition(AbsoluteDate date, Frame frame)	Method returning the Sun's position vector.
protected <T extends CalculusFieldElement<T>> FieldVector3D<T>	AbstractSunInfluencedAtmosphere.getSunPosition(FieldAbsoluteDate<T> date, Frame frame)	Method returning the Sun's position vector (Field version).
default Vector3D	Atmosphere.getVelocity(AbsoluteDate date, Vector3D position, Frame frame)	Get the inertial velocity of atmosphere molecules.
default <T extends CalculusFieldElement<T>> FieldVector3D<T>	Atmosphere.getVelocity(FieldAbsoluteDate<T> date, FieldVector3D<T> position, Frame frame)	Get the inertial velocity of atmosphere molecules.

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

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

Modifier and Type	Method	Description
Vector3D	OceanLoading.displacement(BodiesElements elements, Frame earthFrame, Vector3D referencePoint)	Compute displacement of a ground reference point.
Vector3D	PostSeismicDeformation.displacement(BodiesElements elements, Frame earthFrame, Vector3D referencePoint)	Compute displacement of a ground reference point.
Vector3D	StationDisplacement.displacement(BodiesElements elements, Frame earthFrame, Vector3D referencePoint)	Compute displacement of a ground reference point.
Vector3D	TectonicsDisplacement.displacement(BodiesElements elements, Frame earthFrame, Vector3D referencePoint)	Compute displacement of a ground reference point.
Vector3D	TidalDisplacement.displacement(BodiesElements elements, Frame earthFrame, Vector3D referencePoint)	Compute displacement of a ground reference point.

Uses of Frame in org.orekit.orbits

Methods in org.orekit.orbits that return Frame

Modifier and Type	Method	Description
Frame	FieldOrbit.getFrame()	Get the frame in which the orbital parameters are defined.
Frame	Orbit.getFrame()	Get the frame in which the orbital parameters are defined.
Frame	AbstractFieldOrbitInterpolator.getOutputInertialFrame()	Get output inertial frame.
Frame	AbstractOrbitInterpolator.getOutputInertialFrame()	Get output inertial frame.

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

Modifier and Type	Method	Description
FieldVector3D<T>	FieldOrbit.getPosition(Frame outputFrame)	Get the position in a specified frame.
FieldVector3D<T>	FieldOrbit.getPosition(FieldAbsoluteDate<T> otherDate, Frame otherFrame)	Get the position of the body in the selected frame.
Vector3D	Orbit.getPosition(Frame outputFrame)	Get the position in a specified frame.
Vector3D	Orbit.getPosition(AbsoluteDate otherDate, Frame otherFrame)	Get the position of the body in the selected frame.
TimeStampedFieldPVCoordinates<T>	FieldOrbit.getPVCoordinates(Frame outputFrame)	Get the TimeStampedPVCoordinates in a specified frame.
TimeStampedFieldPVCoordinates<T>	FieldOrbit.getPVCoordinates(FieldAbsoluteDate<T> otherDate, Frame otherFrame)	Get the FieldPVCoordinates of the body in the selected frame.
TimeStampedPVCoordinates	Orbit.getPVCoordinates(Frame outputFrame)	Get the TimeStampedPVCoordinates in a specified frame.
TimeStampedPVCoordinates	Orbit.getPVCoordinates(AbsoluteDate otherDate, Frame otherFrame)	Get the PVCoordinates of the body in the selected frame.
CartesianOrbit	CartesianOrbit.inFrame(Frame inertialFrame)	Create a new object representing the same physical orbital state, but attached to a different reference frame.
CircularOrbit	CircularOrbit.inFrame(Frame inertialFrame)	Create a new object representing the same physical orbital state, but attached to a different reference frame.
EquinoctialOrbit	EquinoctialOrbit.inFrame(Frame inertialFrame)	Create a new object representing the same physical orbital state, but attached to a different reference frame.
FieldCartesianOrbit<T>	FieldCartesianOrbit.inFrame(Frame inertialFrame)	Create a new object representing the same physical orbital state, but attached to a different reference frame.
FieldCircularOrbit<T>	FieldCircularOrbit.inFrame(Frame inertialFrame)	Create a new object representing the same physical orbital state, but attached to a different reference frame.
FieldEquinoctialOrbit<T>	FieldEquinoctialOrbit.inFrame(Frame inertialFrame)	Create a new object representing the same physical orbital state, but attached to a different reference frame.
FieldKeplerianOrbit<T>	FieldKeplerianOrbit.inFrame(Frame inertialFrame)	Create a new object representing the same physical orbital state, but attached to a different reference frame.
abstract FieldOrbit<T>	FieldOrbit.inFrame(Frame inertialFrame)	Create a new object representing the same physical orbital state, but attached to a different reference frame.
KeplerianOrbit	KeplerianOrbit.inFrame(Frame inertialFrame)	Create a new object representing the same physical orbital state, but attached to a different reference frame.
abstract Orbit	Orbit.inFrame(Frame inertialFrame)	Create a new object representing the same physical orbital state, but attached to a different reference frame.
abstract Orbit	OrbitType.mapArrayToOrbit(double[] array, double[] arrayDot, PositionAngleType type, AbsoluteDate date, double mu, Frame frame)	Convert state array to orbital parameters.
abstract <T extends CalculusFieldElement<T>> FieldOrbit<T>	OrbitType.mapArrayToOrbit(T[] array, T[] arrayDot, PositionAngleType type, FieldAbsoluteDate<T> date, T mu, Frame frame)	Convert state array to orbital parameters.

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

Constructor	Description
AbstractFieldOrbitInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputInertialFrame)	Constructor.
AbstractOrbitInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputInertialFrame)	Constructor.
CartesianOrbit(PVCoordinates pvaCoordinates, Frame frame, AbsoluteDate date, double mu)	Constructor from Cartesian parameters.
CartesianOrbit(TimeStampedPVCoordinates pvaCoordinates, Frame frame, double mu)	Constructor from Cartesian parameters.
CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, double aDot, double exDot, double eyDot, double iDot, double raanDot, double alphaDot, PositionAngleType type, Frame frame, AbsoluteDate date, double mu)	Creates a new instance with derivatives and with cached position angle same as value inputted.
CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, double aDot, double exDot, double eyDot, double iDot, double raanDot, double alphaDot, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, AbsoluteDate date, double mu)	Creates a new instance.
CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, PositionAngleType type, Frame frame, AbsoluteDate date, double mu)	Creates a new instance without derivatives and with cached position angle same as value inputted.
CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, AbsoluteDate date, double mu)	Creates a new instance.
CircularOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu)	Constructor from Cartesian parameters.
CircularOrbit(TimeStampedPVCoordinates pvCoordinates, Frame frame, double mu)	Constructor from Cartesian parameters.
EquinoctialOrbit(double a, double ex, double ey, double hx, double hy, double l, double aDot, double exDot, double eyDot, double hxDot, double hyDot, double lDot, PositionAngleType type, Frame frame, AbsoluteDate date, double mu)	Creates a new instance with derivatives and with cached position angle same as value inputted.
EquinoctialOrbit(double a, double ex, double ey, double hx, double hy, double l, double aDot, double exDot, double eyDot, double hxDot, double hyDot, double lDot, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, AbsoluteDate date, double mu)	Creates a new instance.
EquinoctialOrbit(double a, double ex, double ey, double hx, double hy, double l, PositionAngleType type, Frame frame, AbsoluteDate date, double mu)	Creates a new instance without derivatives and with cached position angle same as value inputted.
EquinoctialOrbit(double a, double ex, double ey, double hx, double hy, double l, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, AbsoluteDate date, double mu)	Creates a new instance.
EquinoctialOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu)	Constructor from Cartesian parameters.
EquinoctialOrbit(TimeStampedPVCoordinates pvCoordinates, Frame frame, double mu)	Constructor from Cartesian parameters.
FieldCartesianOrbit(FieldPVCoordinates<T> pvaCoordinates, Frame frame, FieldAbsoluteDate<T> date, T mu)	Constructor from Cartesian parameters.
FieldCartesianOrbit(TimeStampedFieldPVCoordinates<T> pvaCoordinates, Frame frame, T mu)	Constructor from Cartesian parameters.
FieldCircularOrbit(FieldPVCoordinates<T> PVCoordinates, Frame frame, FieldAbsoluteDate<T> date, T mu)	Constructor from Cartesian parameters.
FieldCircularOrbit(TimeStampedFieldPVCoordinates<T> pvCoordinates, Frame frame, T mu)	Constructor from Cartesian parameters.
FieldCircularOrbit(T a, T ex, T ey, T i, T raan, T alpha, PositionAngleType type, Frame frame, FieldAbsoluteDate<T> date, T mu)	Creates a new instance without derivatives and with cached position angle same as value inputted.
FieldCircularOrbit(T a, T ex, T ey, T i, T raan, T alpha, PositionAngleType type, PositionAngleType cachedPositionAngleType, 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, PositionAngleType 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, PositionAngleType type, PositionAngleType cachedPositionAngleType, 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(TimeStampedFieldPVCoordinates<T> pvCoordinates, Frame frame, T mu)	Constructor from Cartesian parameters.
FieldEquinoctialOrbit(T a, T ex, T ey, T hx, T hy, T l, PositionAngleType 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, PositionAngleType type, PositionAngleType cachedPositionAngleType, 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, PositionAngleType 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, PositionAngleType type, PositionAngleType cachedPositionAngleType, 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(TimeStampedFieldPVCoordinates<T> pvCoordinates, Frame frame, T mu)	Constructor from Cartesian parameters.
FieldKeplerianOrbit(T a, T e, T i, T pa, T raan, T anomaly, PositionAngleType 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, PositionAngleType type, PositionAngleType cachedPositionAngleType, 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, PositionAngleType 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, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, FieldAbsoluteDate<T> date, T mu)	Creates a new instance.
FieldOrbit(Frame frame, FieldAbsoluteDate<T> date, T mu)	Default constructor.
FieldOrbit(TimeStampedFieldPVCoordinates<T> fieldPVCoordinates, Frame frame, T mu)	Set the orbit from Cartesian parameters.
FieldOrbitBlender(SmoothStepFactory.FieldSmoothStepFunction<KK> blendingFunction, FieldAbstractAnalyticalPropagator<KK> analyticalPropagator, Frame outputInertialFrame)	Default constructor.
FieldOrbitHermiteInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputInertialFrame, CartesianDerivativesFilter pvaFilter)	Constructor.
FieldOrbitHermiteInterpolator(int interpolationPoints, Frame outputInertialFrame)	Constructor with : Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s) Use of position and two time derivatives during interpolation As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).
FieldOrbitHermiteInterpolator(int interpolationPoints, Frame outputInertialFrame, CartesianDerivativesFilter pvaFilter)	Constructor with default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s).
FieldOrbitHermiteInterpolator(Frame outputInertialFrame)	Constructor with : Default number of interpolation points of DEFAULT_INTERPOLATION_POINTS Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s) Use of position and two time derivatives during interpolation As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).
KeplerianOrbit(double a, double e, double i, double pa, double raan, double anomaly, double aDot, double eDot, double iDot, double paDot, double raanDot, double anomalyDot, PositionAngleType type, Frame frame, AbsoluteDate date, double mu)	Creates a new instance with cached position angle same as value inputted.
KeplerianOrbit(double a, double e, double i, double pa, double raan, double anomaly, double aDot, double eDot, double iDot, double paDot, double raanDot, double anomalyDot, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, AbsoluteDate date, double mu)	Creates a new instance.
KeplerianOrbit(double a, double e, double i, double pa, double raan, double anomaly, PositionAngleType type, Frame frame, AbsoluteDate date, double mu)	Creates a new instance without derivatives and with cached position angle same as value inputted.
KeplerianOrbit(double a, double e, double i, double pa, double raan, double anomaly, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, AbsoluteDate date, double mu)	Creates a new instance.
KeplerianOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu)	Constructor from Cartesian parameters.
KeplerianOrbit(TimeStampedPVCoordinates pvCoordinates, Frame frame, double mu)	Constructor from Cartesian parameters.
Orbit(Frame frame, AbsoluteDate date, double mu)	Default constructor.
Orbit(TimeStampedPVCoordinates pvCoordinates, Frame frame, double mu)	Set the orbit from Cartesian parameters.
OrbitBlender(SmoothStepFactory.SmoothStepFunction blendingFunction, Propagator blendingPropagator, Frame outputInertialFrame)	Default constructor.
OrbitHermiteInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputInertialFrame, CartesianDerivativesFilter pvaFilter)	Constructor.
OrbitHermiteInterpolator(int interpolationPoints, Frame outputInertialFrame)	Constructor with : Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s) Use of position and two time derivatives during interpolation As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).
OrbitHermiteInterpolator(int interpolationPoints, Frame outputInertialFrame, CartesianDerivativesFilter pvaFilter)	Constructor with default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s).
OrbitHermiteInterpolator(Frame outputInertialFrame)	Constructor with : Default number of interpolation points of DEFAULT_INTERPOLATION_POINTS Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s) Use of position and two time derivatives during interpolation As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).

Uses of Frame in org.orekit.propagation

Methods in org.orekit.propagation that return Frame

Modifier and Type	Method	Description
Frame	AbstractPropagator.getFrame()	Get the frame in which the orbit is propagated.
Frame	FieldAbstractPropagator.getFrame()	Get the frame in which the orbit is propagated.
Frame	FieldPropagator.getFrame()	Get the frame in which the orbit is propagated.
Frame	FieldSpacecraftState.getFrame()	Get the defining frame.
Frame	FieldStateCovariance.getFrame()	Get the covariance frame.
Frame	Propagator.getFrame()	Get the frame in which the orbit is propagated.
Frame	SpacecraftState.getFrame()	Get the defining frame.
Frame	StateCovariance.getFrame()	Get the covariance frame.
Frame	AbstractStateCovarianceInterpolator.getOutFrame()	Get output frame.
Frame	FieldSpacecraftStateInterpolator.getOutputFrame()	Get output frame.
Frame	SpacecraftStateInterpolator.getOutputFrame()	Get output frame.

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

Modifier and Type	Method	Description
FieldStateCovariance<T>	FieldStateCovariance.changeCovarianceFrame(FieldOrbit<T> orbit, Frame frameOut)	Get the covariance in the output frame.
StateCovariance	StateCovariance.changeCovarianceFrame(Orbit orbit, Frame frameOut)	Get the covariance in the output frame.
static void	StateCovariance.checkFrameAndOrbitTypeConsistency(Frame covarianceFrame, OrbitType inputType)	Check constructor's inputs consistency.
default FieldVector3D<T>	FieldPropagator.getPosition(FieldAbsoluteDate<T> date, Frame frame)	Get the position of the body in the selected frame.
FieldVector3D<T>	FieldSpacecraftState.getPosition(Frame outputFrame)	Get the position in given output frame.
default Vector3D	Propagator.getPosition(AbsoluteDate date, Frame frame)	Get the position of the body in the selected frame.
Vector3D	SpacecraftState.getPosition(Frame outputFrame)	Get the position in given output frame.
default TimeStampedFieldPVCoordinates<T>	FieldPropagator.getPVCoordinates(FieldAbsoluteDate<T> date, Frame frame)	Get the FieldPVCoordinates of the body in the selected frame.
TimeStampedFieldPVCoordinates<T>	FieldSpacecraftState.getPVCoordinates(Frame outputFrame)	Get the TimeStampedFieldPVCoordinates in given output frame.
default TimeStampedPVCoordinates	Propagator.getPVCoordinates(AbsoluteDate date, Frame frame)	Get the PVCoordinates of the body in the selected frame.
TimeStampedPVCoordinates	SpacecraftState.getPVCoordinates(Frame outputFrame)	Get the TimeStampedPVCoordinates in given output frame.
StateCovariance	StateCovarianceMatrixProvider.getStateCovariance(SpacecraftState state, Frame frame)	Get the state covariance expressed in a given frame.

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

Constructor	Description
AbstractStateCovarianceInterpolator(int interpolationPoints, double extrapolationThreshold, TimeInterpolator<Orbit> orbitInterpolator, Frame outFrame, OrbitType outOrbitType, PositionAngleType outPositionAngleType)	Constructor.
FieldSpacecraftStateInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputFrame)	Constructor to create a customizable Hermite interpolator for every spacecraft state field.
FieldSpacecraftStateInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputFrame, Frame attitudeReferenceFrame)	Constructor to create a customizable Hermite interpolator for every spacecraft state field.
FieldSpacecraftStateInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputFrame, Frame attitudeReferenceFrame, CartesianDerivativesFilter pvaFilter, AngularDerivativesFilter angularFilter)	Constructor.
FieldSpacecraftStateInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputFrame, FieldTimeInterpolator<FieldOrbit<KK>,KK> orbitInterpolator, FieldTimeInterpolator<FieldAbsolutePVCoordinates<KK>,KK> absPVAInterpolator, FieldTimeInterpolator<TimeStampedField<KK>,KK> massInterpolator, FieldTimeInterpolator<FieldAttitude<KK>,KK> attitudeInterpolator, FieldTimeInterpolator<TimeStampedField<KK>,KK> additionalStateInterpolator)	Constructor.
FieldSpacecraftStateInterpolator(int interpolationPoints, Frame outputFrame)	Constructor to create a customizable Hermite interpolator for every spacecraft state field.
FieldSpacecraftStateInterpolator(int interpolationPoints, Frame outputFrame, Frame attitudeReferenceFrame)	Constructor to create a customizable Hermite interpolator for every spacecraft state field.
FieldSpacecraftStateInterpolator(Frame outputFrame)	Simplest constructor to create a default Hermite interpolator for every spacecraft state field.
FieldStateCovariance(FieldMatrix<T> orbitalCovariance, FieldAbsoluteDate<T> epoch, Frame covarianceFrame, OrbitType orbitType, PositionAngleType angleType)	Constructor.
SpacecraftStateInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputFrame)	Constructor to create a customizable Hermite interpolator for every spacecraft state field.
SpacecraftStateInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputFrame, Frame attitudeReferenceFrame)	Constructor to create a customizable Hermite interpolator for every spacecraft state field.
SpacecraftStateInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputFrame, Frame attitudeReferenceFrame, CartesianDerivativesFilter pvaFilter, AngularDerivativesFilter angularFilter)	Constructor to create a customizable Hermite interpolator for every spacecraft state field.
SpacecraftStateInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputFrame, TimeInterpolator<Orbit> orbitInterpolator, TimeInterpolator<AbsolutePVCoordinates> absPVAInterpolator, TimeInterpolator<TimeStampedDouble> massInterpolator, TimeInterpolator<Attitude> attitudeInterpolator, TimeInterpolator<TimeStampedDouble> additionalStateInterpolator)	Constructor.
SpacecraftStateInterpolator(int interpolationPoints, Frame outputFrame)	Constructor to create a customizable Hermite interpolator for every spacecraft state field.
SpacecraftStateInterpolator(int interpolationPoints, Frame outputFrame, Frame attitudeReferenceFrame)	Constructor to create a customizable Hermite interpolator for every spacecraft state field.
SpacecraftStateInterpolator(Frame outputFrame)	Simplest constructor to create a default Hermite interpolator for every spacecraft state field.
StateCovariance(RealMatrix orbitalCovariance, AbsoluteDate epoch, Frame covarianceFrame, OrbitType orbitType, PositionAngleType angleType)	Constructor.
StateCovarianceBlender(SmoothStepFactory.SmoothStepFunction blendingFunction, TimeInterpolator<Orbit> orbitInterpolator, Frame outFrame, OrbitType outOrbitType, PositionAngleType outPositionAngleType)	Constructor.
StateCovarianceKeplerianHermiteInterpolator(int interpolationPoints, double extrapolationThreshold, TimeInterpolator<Orbit> orbitInterpolator, CartesianDerivativesFilter filter, Frame outFrame, OrbitType outOrbitType, PositionAngleType outPositionAngleType)	Constructor using an output frame.
StateCovarianceKeplerianHermiteInterpolator(int interpolationPoints, TimeInterpolator<Orbit> orbitInterpolator, Frame outFrame, OrbitType outOrbitType, PositionAngleType outPositionAngleType)	Constructor using an output frame and : Default number of interpolation points of DEFAULT_INTERPOLATION_POINTS Use of position and two time derivatives during interpolation As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).
StateCovarianceKeplerianHermiteInterpolator(int interpolationPoints, TimeInterpolator<Orbit> orbitInterpolator, CartesianDerivativesFilter filter, Frame outFrame, OrbitType outOrbitType, PositionAngleType outPositionAngleType)	Constructor using an output frame and : Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s) As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).
StateCovarianceKeplerianHermiteInterpolator(TimeInterpolator<Orbit> orbitInterpolator, Frame outFrame, OrbitType outOrbitType, PositionAngleType outPositionAngleType)	Constructor using an output frame and : Default number of interpolation points of DEFAULT_INTERPOLATION_POINTS Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s) Use of position and two time derivatives during interpolation As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).

Uses of Frame in org.orekit.propagation.analytical

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

Modifier and Type	Method	Description
Frame	Ephemeris.getFrame()	Get the frame in which the orbit is propagated.

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

Modifier and Type	Method	Description
Vector3D	AggregateBoundedPropagator.getPosition(AbsoluteDate date, Frame frame)
TimeStampedPVCoordinates	AggregateBoundedPropagator.getPVCoordinates(AbsoluteDate date, Frame frame)

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

Methods in org.orekit.propagation.analytical.gnss that return Frame

Modifier and Type	Method	Description
Frame	FieldGnssPropagator.getECEF()	Gets the Earth Centered Earth Fixed frame used to propagate GNSS orbits according to the Interface Control Document.
Frame	GLONASSAnalyticalPropagator.getECEF()	Gets the Earth Centered Earth Fixed frame used to propagate GLONASS orbits.
Frame	GNSSPropagator.getECEF()	Gets the Earth Centered Earth Fixed frame used to propagate GNSS orbits according to the Interface Control Document.
Frame	SBASPropagator.getECEF()	Gets the Earth Centered Earth Fixed frame used to propagate GNSS orbits.
Frame	FieldGnssPropagator.getECI()	Gets the Earth Centered Inertial frame used to propagate the orbit.
Frame	GLONASSAnalyticalPropagator.getECI()	Gets the Earth Centered Inertial frame used to propagate the orbit.
Frame	GNSSPropagator.getECI()	Gets the Earth Centered Inertial frame used to propagate the orbit.
Frame	SBASPropagator.getECI()	Gets the Earth Centered Inertial frame used to propagate the orbit.
Frame	FieldGnssPropagator.getFrame()	Get the frame in which the orbit is propagated.
Frame	GLONASSAnalyticalPropagator.getFrame()	Get the frame in which the orbit is propagated.
Frame	GNSSPropagator.getFrame()	Get the frame in which the orbit is propagated.
Frame	SBASPropagator.getFrame()	Get the frame in which the orbit is propagated.

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

Modifier and Type	Method	Description
FieldGnssPropagatorBuilder<T>	FieldGnssPropagatorBuilder.ecef(Frame bodyFixed)	Sets the Earth Centered Earth Fixed frame assimilated to the WGS84 ECEF.
GLONASSAnalyticalPropagatorBuilder	GLONASSAnalyticalPropagatorBuilder.ecef(Frame bodyFixed)	Sets the Earth Centered Earth Fixed frame assimilated to the WGS84 ECEF.
GNSSPropagatorBuilder	GNSSPropagatorBuilder.ecef(Frame bodyFixed)	Sets the Earth Centered Earth Fixed frame assimilated to the WGS84 ECEF.
SBASPropagatorBuilder	SBASPropagatorBuilder.ecef(Frame bodyFixed)	Sets the Earth Centered Earth Fixed frame assimilated to the WGS84 ECEF.
FieldGnssPropagatorBuilder<T>	FieldGnssPropagatorBuilder.eci(Frame inertial)	Sets the Earth Centered Inertial frame used for propagation.
GLONASSAnalyticalPropagatorBuilder	GLONASSAnalyticalPropagatorBuilder.eci(Frame inertial)	Sets the Earth Centered Inertial frame used for propagation.
GNSSPropagatorBuilder	GNSSPropagatorBuilder.eci(Frame inertial)	Sets the Earth Centered Inertial frame used for propagation.
SBASPropagatorBuilder	SBASPropagatorBuilder.eci(Frame inertial)	Sets the Earth Centered Inertial frame used for propagation.

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

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

Modifier and Type	Method	Description
GNSSPropagator	AbstractAlmanac.getPropagator(Frames frames, AttitudeProvider provider, Frame inertial, Frame bodyFixed, double mass)	Get the propagator corresponding to the navigation message.
FieldGnssPropagator<T>	FieldAbstractAlmanac.getPropagator(Frames frames, AttitudeProvider provider, Frame inertial, Frame bodyFixed, T mass)	Get the propagator corresponding to the navigation message.
GLONASSAnalyticalPropagator	GLONASSAlmanac.getPropagator(DataContext context, AttitudeProvider provider, Frame inertial, Frame bodyFixed, double mass)	Get the propagator corresponding to the navigation message.
GLONASSNumericalPropagator	GLONASSNavigationMessage.getPropagator(double step, DataContext context, AttitudeProvider provider, Frame inertial, double mass)	Get the propagator corresponding to the navigation message.
SBASPropagator	SBASNavigationMessage.getPropagator(Frames frames, AttitudeProvider provider, Frame inertial, Frame bodyFixed, double mass, double mu)	Get the propagator corresponding to the navigation message.

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

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

Modifier and Type	Method	Description
Frame	FieldIntelsatElevenElementsPropagator.getFrame()	Get the frame in which the orbit is propagated.
Frame	IntelsatElevenElementsPropagator.getFrame()	Get the frame in which the orbit is propagated.

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

Constructor	Description
FieldIntelsatElevenElementsPropagator(FieldIntelsatElevenElements<T> elements, Frame inertialFrame, Frame ecefFrame)	Constructor.
FieldIntelsatElevenElementsPropagator(FieldIntelsatElevenElements<T> elements, Frame inertialFrame, Frame ecefFrame, AttitudeProvider attitudeProvider, T mass)	Constructor.
IntelsatElevenElementsPropagator(IntelsatElevenElements elements, Frame inertialFrame, Frame ecefFrame)	Constructor.
IntelsatElevenElementsPropagator(IntelsatElevenElements elements, Frame inertialFrame, Frame ecefFrame, AttitudeProvider attitudeProvider, double mass)	Constructor.

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

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

Modifier and Type	Method	Description
Frame	FieldTLEPropagator.getFrame()	Get the frame in which the orbit is propagated.
Frame	TLEPropagator.getFrame()	Get the frame in which the orbit is propagated.

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

Modifier and Type	Method	Description
static TleGenerationAlgorithm	TLEPropagator.getDefaultTleGenerationAlgorithm(TimeScale utc, Frame teme)	Get the default TLE generation algorithm.
static <T extends CalculusFieldElement<T>> FieldTLEPropagator<T>	FieldTLEPropagator.selectExtrapolator(FieldTLE<T> tle, AttitudeProvider attitudeProvider, T mass, Frame teme, T[] parameters)	Selects the extrapolator to use with the selected TLE.
static <T extends CalculusFieldElement<T>> FieldTLEPropagator<T>	FieldTLEPropagator.selectExtrapolator(FieldTLE<T> tle, Frame teme, T[] parameters)	Selects the extrapolator to use with the selected TLE.
static TLEPropagator	TLEPropagator.selectExtrapolator(TLE tle, AttitudeProvider attitudeProvider, double mass, Frame teme)	Selects the extrapolator to use with the selected TLE.
static TLEPropagator	TLEPropagator.selectExtrapolator(TLE tle, Frame teme)	Selects the extrapolator to use with the selected TLE.
static TLEPropagator	TLEPropagator.selectExtrapolator(TLE tle, Frame teme, AttitudeProvider attitudeProvider)	Selects the extrapolator to use with the selected TLE.

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

Constructor	Description
DeepSDP4(TLE initialTLE, AttitudeProvider attitudeProvider, double mass, Frame teme)	Constructor for a unique initial TLE.
FieldDeepSDP4(FieldTLE<T> initialTLE, AttitudeProvider attitudeProvider, T mass, Frame teme, T[] parameters)	Constructor for a unique initial TLE.
FieldSGP4(FieldTLE<T> initialTLE, AttitudeProvider attitudeProvider, T mass, Frame teme, T[] parameters)	Constructor for a unique initial TLE.
FieldTLEPropagator(FieldTLE<T> initialTLE, AttitudeProvider attitudeProvider, T mass, Frame teme, T[] parameters)	Protected constructor for derived classes.
SGP4(TLE initialTLE, AttitudeProvider attitudeProvider, double mass, Frame teme)	Constructor for a unique initial TLE.
TLEPropagator(TLE initialTLE, AttitudeProvider attitudeProvider, double mass, Frame teme)	Protected constructor for derived classes.

Uses of Frame in org.orekit.propagation.analytical.tle.generation

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

Constructor	Description
FixedPointTleGenerationAlgorithm(double epsilon, int maxIterations, double scale, TimeScale utc, Frame teme)	Constructor.
LeastSquaresTleGenerationAlgorithm(int maxIterations, TimeScale utc, Frame teme)	Constructor.
LeastSquaresTleGenerationAlgorithm(TimeScale utc, Frame teme, LeastSquaresConverter converter)	Constructor.

Uses of Frame in org.orekit.propagation.conversion

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

Modifier and Type	Method	Description
Frame	AbstractPropagatorBuilder.getFrame()	Get the frame in which the orbit is propagated.
protected Frame	AbstractPropagatorConverter.getFrame()	Get the frame of the initial state.
Frame	PropagatorBuilder.getFrame()	Get the frame in which the orbit is propagated.

Uses of Frame in org.orekit.propagation.conversion.averaging

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

Modifier and Type	Method	Description
Frame	AbstractAveragedOrbitalState.getFrame()	Getter for the reference frame.
Frame	AveragedOrbitalState.getFrame()	Getter for the reference frame.

Methods in org.orekit.propagation.conversion.averaging with parameters of type Frame

Modifier and Type	Method	Description
static SGP4OrbitalState	SGP4OrbitalState.of(TLE tle, Frame teme)	Static constructor.

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

Constructor	Description
AbstractAveragedOrbitalState(AbsoluteDate date, Frame frame)	Protected constructor.
BrouwerLyddaneOrbitalState(AbsoluteDate date, AveragedKeplerianWithMeanAngle elements, Frame frame, UnnormalizedSphericalHarmonicsProvider harmonicsProvider)	Constructor.
DSST6X0OrbitalState(AbsoluteDate date, AveragedEquinoctialWithMeanAngle elements, Frame frame, UnnormalizedSphericalHarmonicsProvider harmonicsProvider)	Constructor.
EcksteinHechlerOrbitalState(AbsoluteDate date, AveragedCircularWithMeanAngle elements, Frame frame, UnnormalizedSphericalHarmonicsProvider harmonicsProvider)	Constructor.

Uses of Frame in org.orekit.propagation.conversion.osc2mean

Constructors in org.orekit.propagation.conversion.osc2mean with parameters of type Frame

Constructor	Description
TLETheory(FieldTLE<T> template, TimeScale utc, Frame teme)	Constructor.
TLETheory(TLE template, TimeScale utc, Frame teme)	Constructor.
TLETheory(TimeScale utc, Frame teme)	Constructor.

Uses of Frame in org.orekit.propagation.events

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

Modifier and Type	Method	Description
Frame	FieldNodeDetector.getFrame()	Get the frame in which the equator is defined.
Frame	GroundFieldOfViewDetector.getFrame()	Get the sensor reference frame.
Frame	NodeDetector.getFrame()	Get the frame in which the equator is defined.
Frame	BetaAngleDetector.getInertialFrame()	The inertial frame in which beta angle is computed.
Frame	FieldBetaAngleDetector.getInertialFrame()	The inertial frame in which beta angle is computed.

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

Modifier and Type	Method	Description
static double	BetaAngleDetector.calculateBetaAngle(SpacecraftState state, PVCoordinatesProvider celestialBodyProvider, Frame frame)	Calculate the beta angle between the orbit plane and the celestial body.
static <T extends CalculusFieldElement<T>> T	FieldBetaAngleDetector.calculateBetaAngle(FieldSpacecraftState<T> state, FieldPVCoordinatesProvider<T> celestialBodyProvider, Frame frame)	Calculate the beta angle between the orbit plane and the celestial body.
BetaAngleDetector	BetaAngleDetector.withInertialFrame(Frame newFrame)	Create a new instance with the provided inertial frame.
FieldBetaAngleDetector<T>	FieldBetaAngleDetector.withInertialFrame(Frame newFrame)	Create a new instance with the provided inertial frame.

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

Constructor	Description
BetaAngleDetector(double betaAngleThreshold, PVCoordinatesProvider celestialBodyProvider, Frame inertialFrame)	Class constructor.
BetaAngleDetector(EventDetectionSettings detectionSettings, EventHandler handler, double betaAngleThreshold, PVCoordinatesProvider celestialBodyProvider, Frame inertialFrame)	Protected constructor with full parameters.
FieldBetaAngleDetector(Field<T> field, T betaAngleThreshold, FieldPVCoordinatesProvider<T> celestialBodyProvider, Frame inertialFrame)	Class constructor.
FieldBetaAngleDetector(FieldEventDetectionSettings<T> detectionSettings, FieldEventHandler<T> handler, T betaAngleThreshold, FieldPVCoordinatesProvider<T> celestialBodyProvider, Frame inertialFrame)	Protected constructor with full parameters.
FieldNodeDetector(FieldOrbit<T> orbit, Frame frame)	Build a new instance.
FieldNodeDetector(FieldEventDetectionSettings<T> detectionSettings, FieldEventHandler<T> handler, Frame frame)	Protected constructor with full parameters.
FieldNodeDetector(T threshold, FieldOrbit<T> orbit, Frame frame)	Build a new instance.
GroundFieldOfViewDetector(Frame frame, FieldOfView fov)	Build a new instance.
GroundFieldOfViewDetector(EventDetectionSettings detectionSettings, EventHandler handler, Frame frame, FieldOfView fov)	Protected constructor with full parameters.
NodeDetector(double threshold, Orbit orbit, Frame frame)	Build a new instance.
NodeDetector(Frame frame)	Build a new instance.
NodeDetector(Orbit orbit, Frame frame)	Build a new instance.
NodeDetector(EventDetectionSettings detectionSettings, EventHandler handler, Frame frame)	Protected constructor with full parameters.

Uses of Frame in org.orekit.propagation.integration

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

Modifier and Type	Method	Description
Frame	FieldIntegratedEphemeris.getFrame()
Frame	FieldStateMapper.getFrame()	Get the inertial frame.
Frame	IntegratedEphemeris.getFrame()
Frame	StateMapper.getFrame()	Get the inertial frame.

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

Modifier and Type	Method	Description
protected abstract StateMapper	AbstractIntegratedPropagator.createMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngleType positionAngleType, AttitudeProvider attitudeProvider, Frame frame)	Create a mapper between raw double components and spacecraft state. /** Simple constructor.
protected abstract FieldStateMapper<T>	FieldAbstractIntegratedPropagator.createMapper(FieldAbsoluteDate<T> referenceDate, T mu, OrbitType orbitType, PositionAngleType positionAngleType, AttitudeProvider attitudeProvider, Frame frame)	Create a mapper between raw double components and spacecraft state. /** Simple constructor.

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

Constructor	Description
FieldStateMapper(FieldAbsoluteDate<T> referenceDate, T mu, OrbitType orbitType, PositionAngleType positionAngleType, AttitudeProvider attitudeProvider, Frame frame)	Simple constructor.
StateMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngleType positionAngleType, AttitudeProvider attitudeProvider, Frame frame)	Simple constructor.

Uses of Frame in org.orekit.propagation.numerical

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

Modifier and Type	Method	Description
protected FieldStateMapper<T>	FieldNumericalPropagator.createMapper(FieldAbsoluteDate<T> referenceDate, T mu, OrbitType orbitType, PositionAngleType positionAngleType, AttitudeProvider attitudeProvider, Frame frame)	Create a mapper between raw double components and spacecraft state. /** Simple constructor.
protected StateMapper	GLONASSNumericalPropagator.createMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngleType positionAngleType, AttitudeProvider attitudeProvider, Frame frame)
protected StateMapper	NumericalPropagator.createMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngleType positionAngleType, AttitudeProvider attitudeProvider, Frame frame)	Create a mapper between raw double components and spacecraft state. /** Simple constructor.
GLONASSNumericalPropagatorBuilder	GLONASSNumericalPropagatorBuilder.eci(Frame inertial)	Sets the Earth Centered Inertial frame used for propagation.

Constructors in org.orekit.propagation.numerical with parameters of type Frame

Constructor	Description
GLONASSNumericalPropagator(ClassicalRungeKuttaIntegrator integrator, GLONASSOrbitalElements glonassOrbit, Frame eci, AttitudeProvider provider, double mass, DataContext context, boolean isAccAvailable)	Private constructor.

Uses of Frame in org.orekit.propagation.sampling

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

Modifier and Type	Method	Description
default TimeStampedFieldPVCoordinates<T>	FieldOrekitStepInterpolator.getPVCoordinates(FieldAbsoluteDate<T> date, Frame frame)	Get the FieldPVCoordinates of the body in the selected frame.
default TimeStampedPVCoordinates	OrekitStepInterpolator.getPVCoordinates(AbsoluteDate date, Frame frame)	Get the PVCoordinates of the body in the selected frame.

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

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

Modifier and Type	Method	Description
protected StateMapper	DSSTPropagator.createMapper(AbsoluteDate referenceDate, double mu, OrbitType ignoredOrbitType, PositionAngleType ignoredPositionAngleType, AttitudeProvider attitudeProvider, Frame frame)	Create a mapper between raw double components and spacecraft state. /** Simple constructor.
protected FieldStateMapper<T>	FieldDSSTPropagator.createMapper(FieldAbsoluteDate<T> referenceDate, T mu, OrbitType ignoredOrbitType, PositionAngleType ignoredPositionAngleType, AttitudeProvider attitudeProvider, Frame frame)	Create a mapper between raw double components and spacecraft state. /** Simple constructor.

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

Constructors in org.orekit.propagation.semianalytical.dsst.forces with parameters of type Frame

Constructor	Description
DSSTTesseral(Frame centralBodyFrame, double centralBodyRotationRate, UnnormalizedSphericalHarmonicsProvider provider)	Simple constructor with default reference values.
DSSTTesseral(Frame centralBodyFrame, double centralBodyRotationRate, UnnormalizedSphericalHarmonicsProvider provider, int maxDegreeTesseralSP, int maxOrderTesseralSP, int maxEccPowTesseralSP, int maxFrequencyShortPeriodics, int maxDegreeMdailyTesseralSP, int maxOrderMdailyTesseralSP, int maxEccPowMdailyTesseralSP)	Simple constructor.
DSSTZonal(Frame bodyFixedFrame, UnnormalizedSphericalHarmonicsProvider provider)	Constructor with default reference values.
DSSTZonal(Frame bodyFixedFrame, UnnormalizedSphericalHarmonicsProvider provider, int maxDegreeShortPeriodics, int maxEccPowShortPeriodics, int maxFrequencyShortPeriodics)	Constructor.

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

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

Modifier and Type	Method	Description
Frame	AuxiliaryElements.getFrame()	Get the definition frame of the orbit.
Frame	FieldAuxiliaryElements.getFrame()	Get the definition frame of the orbit.

Uses of Frame in org.orekit.utils

Subclasses of Frame in org.orekit.utils

Modifier and Type	Class	Description
class	ExtendedPositionProviderAdapter	Adapter from ExtendedPositionProvider to TransformProvider.

Methods in org.orekit.utils that return Frame

Modifier and Type	Method	Description
Frame	AbsolutePVCoordinates.getFrame()	Get the frame in which the coordinates are defined.
Frame	FieldAbsolutePVCoordinates.getFrame()	Get the frame in which the coordinates are defined.
Frame	AbsolutePVCoordinatesHermiteInterpolator.getOutputFrame()	Get output frame for the interpolated instance.
Frame	FieldAbsolutePVCoordinatesHermiteInterpolator.getOutputFrame()	Get output frame for the interpolated instance.

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

Modifier and Type	Method	Description
static RealMatrix	CartesianCovarianceUtils.changeReferenceFrame(Frame inputFrame, RealMatrix covarianceMatrix, AbsoluteDate date, Frame outputFrame)	Convert input position-velocity covariance matrix between reference frames.
Vector3D	AbsolutePVCoordinates.getPosition(Frame outputFrame)	Get the position in a specified frame.
Vector3D	AggregatedPVCoordinatesProvider.getPosition(AbsoluteDate date, Frame frame)
Vector3D	ConstantPVCoordinatesProvider.getPosition(AbsoluteDate date, Frame frame)
<T extends CalculusFieldElement<T>> FieldVector3D<T>	ExtendedPositionProvider.getPosition(FieldAbsoluteDate<T> date, Frame frame)	Get the position in the selected frame.
default <T extends CalculusFieldElement<T>> FieldVector3D<T>	ExtendedPVCoordinatesProvider.getPosition(FieldAbsoluteDate<T> date, Frame frame)	Deprecated. Get the position of the body in the selected frame.
FieldVector3D<T>	FieldAbsolutePVCoordinates.getPosition(Frame outputFrame)	Get the position in a specified frame.
default FieldVector3D<T>	FieldPVCoordinatesProvider.getPosition(FieldAbsoluteDate<T> date, Frame frame)	Get the position of the body in the selected frame.
Vector3D	FrameAdapter.getPosition(AbsoluteDate date, Frame frame)	Get the position of the body in the selected frame.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	FrameAdapter.getPosition(FieldAbsoluteDate<T> date, Frame frame)	Get the position in the selected frame.
default Vector3D	PVCoordinatesProvider.getPosition(AbsoluteDate date, Frame frame)	Get the position of the body in the selected frame.
TimeStampedPVCoordinates	AbsolutePVCoordinates.getPVCoordinates(Frame outputFrame)	Get the TimeStampedPVCoordinates in a specified frame.
TimeStampedPVCoordinates	AbsolutePVCoordinates.getPVCoordinates(AbsoluteDate otherDate, Frame outputFrame)
TimeStampedPVCoordinates	AggregatedPVCoordinatesProvider.getPVCoordinates(AbsoluteDate date, Frame frame)
TimeStampedPVCoordinates	AggregatedPVCoordinatesProvider.InvalidPVProvider.getPVCoordinates(AbsoluteDate date, Frame frame)
TimeStampedPVCoordinates	ConstantPVCoordinatesProvider.getPVCoordinates(AbsoluteDate date, Frame frame)
default TimeStampedPVCoordinates	ExtendedPositionProvider.getPVCoordinates(AbsoluteDate date, Frame frame)	Get the PVCoordinates of the body in the selected frame.
default <T extends CalculusFieldElement<T>> TimeStampedFieldPVCoordinates<T>	ExtendedPositionProvider.getPVCoordinates(FieldAbsoluteDate<T> date, Frame frame)	Get the position-velocity-acceleration in the selected frame.
<T extends CalculusFieldElement<T>> TimeStampedFieldPVCoordinates<T>	ExtendedPVCoordinatesProvider.getPVCoordinates(FieldAbsoluteDate<T> date, Frame frame)	Deprecated. Get the FieldPVCoordinates of the body in the selected frame.
TimeStampedFieldPVCoordinates<T>	FieldAbsolutePVCoordinates.getPVCoordinates(Frame outputFrame)	Get the TimeStampedFieldPVCoordinates in a specified frame.
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.
TimeStampedFieldPVCoordinates<T>	FieldShiftingPVCoordinatesProvider.getPVCoordinates(FieldAbsoluteDate<T> date, Frame frame)	Get the FieldPVCoordinates of the body in the selected frame.
TimeStampedPVCoordinates	FrameAdapter.getPVCoordinates(AbsoluteDate date, Frame frame)	Get the PVCoordinates of the body in the selected frame.
<T extends CalculusFieldElement<T>> TimeStampedFieldPVCoordinates<T>	FrameAdapter.getPVCoordinates(FieldAbsoluteDate<T> date, Frame frame)	Get the position-velocity-acceleration in the selected frame.
TimeStampedPVCoordinates	PVCoordinatesProvider.getPVCoordinates(AbsoluteDate date, Frame frame)	Get the PVCoordinates of the body in the selected frame.
TimeStampedPVCoordinates	ShiftingPVCoordinatesProvider.getPVCoordinates(AbsoluteDate date, Frame frame)	Get the PVCoordinates of the body in the selected frame.
PVCoordinatesProvider	TimeStampedPVCoordinates.toTaylorProvider(Frame instanceFrame)	Create a local provider using simply Taylor expansion through TimeStampedPVCoordinates.shiftedBy(double).

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

Constructor	Description
AbsolutePVCoordinates(Frame frame, AbsoluteDate date, FieldVector3D<U> p)	Builds a AbsolutePVCoordinates triplet from a FieldVector3D<Derivative>.
AbsolutePVCoordinates(Frame frame, AbsoluteDate date, Vector3D position, Vector3D velocity)	Build from position and velocity.
AbsolutePVCoordinates(Frame frame, AbsoluteDate date, Vector3D position, Vector3D velocity, Vector3D acceleration)	Build from position, velocity, acceleration.
AbsolutePVCoordinates(Frame frame, AbsoluteDate date, PVCoordinates pva)	Build from frame, date and PVA coordinates.
AbsolutePVCoordinates(Frame frame, TimeStampedPVCoordinates pva)	Build from frame and TimeStampedPVCoordinates.
AbsolutePVCoordinatesHermiteInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputFrame, CartesianDerivativesFilter filter)	Constructor.
AbsolutePVCoordinatesHermiteInterpolator(int interpolationPoints, Frame outputFrame)	Constructor with : Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s) Use of position and two time derivatives during interpolation As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).
AbsolutePVCoordinatesHermiteInterpolator(int interpolationPoints, Frame outputFrame, CartesianDerivativesFilter filter)	Constructor with default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s).
AbsolutePVCoordinatesHermiteInterpolator(Frame outputFrame)	Constructor with : Default number of interpolation points of DEFAULT_INTERPOLATION_POINTS Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s) Use of position and two time derivatives during interpolation As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).
ConstantPVCoordinatesProvider(Vector3D pos, Frame frame)	Create the PVCoordinatesProvider from a fixed point in a frame.
ConstantPVCoordinatesProvider(PVCoordinates pva, Frame frame)	Create the PVCoordinatesProvider from a fixed point in a frame.
ExtendedPositionProviderAdapter(Frame parent, ExtendedPositionProvider provider, String name)	Simple constructor.
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.
FieldAbsolutePVCoordinates(Frame frame, FieldAbsoluteDate<T> date, FieldVector3D<U> p)	Builds a FieldAbsolutePVCoordinates triplet from a FieldVector3D<DerivativeStructure>.
FieldAbsolutePVCoordinates(Frame frame, FieldAbsoluteDate<T> date, FieldPVCoordinates<T> pva)	Build from frame, date and FieldPVA coordinates.
FieldAbsolutePVCoordinates(Frame frame, TimeStampedFieldPVCoordinates<T> pva)	Build from frame and TimeStampedFieldPVCoordinates.
FieldAbsolutePVCoordinatesHermiteInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputFrame, CartesianDerivativesFilter filter)	Constructor.
FieldAbsolutePVCoordinatesHermiteInterpolator(int interpolationPoints, Frame outputFrame)	Constructor with : Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s) Use of position and two time derivatives during interpolation As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).
FieldAbsolutePVCoordinatesHermiteInterpolator(int interpolationPoints, Frame outputFrame, CartesianDerivativesFilter filter)	Constructor with default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s).
FieldAbsolutePVCoordinatesHermiteInterpolator(Frame outputFrame)	Constructor with : Default number of interpolation points of DEFAULT_INTERPOLATION_POINTS Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s) Use of position and two time derivatives during interpolation As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).
FieldShiftingPVCoordinatesProvider(TimeStampedFieldPVCoordinates<T> referencePV, Frame referenceFrame)	Simple constructor.
FrameAdapter(Frame originFrame)	Simple constructor.
ShiftingPVCoordinatesProvider(TimeStampedPVCoordinates referencePV, Frame referenceFrame)	Simple constructor.