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.estimation.iod
org.orekit.estimation.measurements	The measurements package defines everything that is related to orbit determination measurements.
org.orekit.files.ccsds	This package provides a parser for orbit data stored in CCSDS Orbit Data Message format.
org.orekit.files.general	This package provides interfaces for orbit file representations and corresponding parsers.
org.orekit.files.sp3	This package provides a parser for orbit data stored in SP3 format.
org.orekit.forces	This package provides the interface for force models that will be used by the NumericalPropagator, as well as some classical spacecraft models for surface forces (spherical, box and solar array ...).
org.orekit.forces.drag	This package provides all drag-related forces.
org.orekit.forces.drag.atmosphere	This package provides the atmosphere model interface and several implementations.
org.orekit.forces.gravity	This package provides all gravity-related forces.
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.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.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.tle	This package provides classes to read and extrapolate tle's.
org.orekit.propagation.conversion	This package provides tools to convert a given propagator or a set of SpacecraftState into another propagator.
org.orekit.propagation.events	This package provides interfaces and classes dealing with events occurring during propagation.
org.orekit.propagation.integration	Utilities for integration-based propagators (both numerical and semi-analytical).
org.orekit.propagation.numerical	Top level package for numerical propagators.
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	Attitude.getReferenceFrame()	Get the reference frame.
Frame	FieldAttitude.getReferenceFrame()	Get the reference frame.

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

Modifier and Type	Method	Description
<T extends RealFieldElement<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.
<T extends RealFieldElement<T>> FieldAttitude<T>	AttitudesSequence.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
Attitude	AttitudesSequence.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.
<T extends RealFieldElement<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 RealFieldElement<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 RealFieldElement<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 RealFieldElement<T>> FieldAttitude<T>	InertialProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
Attitude	InertialProvider.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.
<T extends RealFieldElement<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 RealFieldElement<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 RealFieldElement<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 RealFieldElement<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 RealFieldElement<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 RealFieldElement<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 RealFieldElement<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 RealFieldElement<T>> FieldAttitude<T>	YawCompensation.getBaseState(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the base system state at given date, without compensation.
Attitude	YawCompensation.getBaseState(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the base system state at given date, without compensation.
<T extends RealFieldElement<T>> FieldAttitude<T>	YawSteering.getBaseState(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the base system state at given date, without compensation.
Attitude	YawSteering.getBaseState(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the base system state at given date, without compensation.
<T extends RealFieldElement<T>> TimeStampedFieldPVCoordinates<T>	BodyCenterPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the target point position/velocity in specified frame.
TimeStampedPVCoordinates	BodyCenterPointing.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position/velocity in specified frame.
abstract <T extends RealFieldElement<T>> TimeStampedFieldPVCoordinates<T>	GroundPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the target point position/velocity in specified frame.
abstract TimeStampedPVCoordinates	GroundPointing.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position/velocity in specified frame.
<T extends RealFieldElement<T>> TimeStampedFieldPVCoordinates<T>	LofOffsetPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the target point position/velocity in specified frame.
TimeStampedPVCoordinates	LofOffsetPointing.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position/velocity in specified frame.
<T extends RealFieldElement<T>> TimeStampedFieldPVCoordinates<T>	NadirPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the target point position/velocity in specified frame.
TimeStampedPVCoordinates	NadirPointing.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position/velocity in specified frame.
<T extends RealFieldElement<T>> TimeStampedFieldPVCoordinates<T>	TargetPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the target point position/velocity in specified frame.
TimeStampedPVCoordinates	TargetPointing.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position/velocity in specified frame.
<T extends RealFieldElement<T>> TimeStampedFieldPVCoordinates<T>	YawCompensation.getTargetPV(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the target point position/velocity in specified frame.
TimeStampedPVCoordinates	YawCompensation.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position/velocity in specified frame.
<T extends RealFieldElement<T>> TimeStampedFieldPVCoordinates<T>	YawSteering.getTargetPV(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the target point position/velocity in specified frame.
TimeStampedPVCoordinates	YawSteering.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the target point position/velocity in specified frame.
<T extends RealFieldElement<T>> T	YawCompensation.getYawAngle(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the yaw compensation angle at date.
double	YawCompensation.getYawAngle(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the yaw compensation angle at date.
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
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.
BodyCenterPointing(Frame inertialFrame, Ellipsoid shape)	Creates new instance.
CelestialBodyPointed(Frame celestialFrame, PVCoordinatesProvider 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.
GroundPointing(Frame inertialFrame, Frame bodyFrame)	Default constructor.
LofOffset(Frame inertialFrame, LOFType type)	Create a LOF-aligned attitude.
LofOffset(Frame inertialFrame, LOFType type, 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, LOFType type, List<TimeStampedAngularCoordinates> table, int n, AngularDerivativesFilter filter)	Creates new instance.
TabulatedProvider(Frame referenceFrame, List<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, PVCoordinatesProvider 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	CelestialBody.getInertiallyOrientedFrame()	Get an inertially oriented, body centered frame.

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

Modifier and Type	Method	Description
<T extends RealFieldElement<T>> FieldGeodeticPoint<T>	BodyShape.getIntersectionPoint(FieldLine<T> line, FieldVector3D<T> close, Frame frame, FieldAbsoluteDate<T> date)	Get the intersection point of a line with the surface of the body.
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 RealFieldElement<T>> FieldGeodeticPoint<T>	OneAxisEllipsoid.getIntersectionPoint(FieldLine<T> line, FieldVector3D<T> close, Frame frame, FieldAbsoluteDate<T> date)	Get the intersection point of a line with the surface of the body.
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	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 RealFieldElement<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 RealFieldElement<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<DerivativeStructure>	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.
OneAxisEllipsoid(double ae, double f, Frame bodyFrame)	Simple 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
KeplerianOrbit	IodGibbs.estimate(Frame frame, Vector3D r1, AbsoluteDate date1, Vector3D r2, AbsoluteDate date2, Vector3D r3, AbsoluteDate date3)	Give an initial orbit estimation, assuming Keplerian motion.
KeplerianOrbit	IodGibbs.estimate(Frame frame, PV pv1, PV pv2, PV pv3)	Give an initial orbit estimation, assuming Keplerian motion.
KeplerianOrbit	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.

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

Constructor	Description
IodGooding(Frame frame, double mu)	Creator.

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
Transform	GroundStation.getOffsetToInertial(Frame inertial, AbsoluteDate date)	Get the transform between offset frame and inertial frame.
FieldTransform<DerivativeStructure>	GroundStation.getOffsetToInertial(Frame inertial, FieldAbsoluteDate<DerivativeStructure> date, DSFactory factory, Map<String,Integer> indices)	Get the transform between offset frame and inertial frame with derivatives.

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)	Simple constructor.
AngularRaDec(GroundStation station, Frame referenceFrame, AbsoluteDate date, double[] angular, double[] sigma, double[] baseWeight, int propagatorIndex)	Simple constructor.

Uses of Frame in org.orekit.files.ccsds

Subclasses of Frame in org.orekit.files.ccsds

Modifier and Type	Class	Description
class	CcsdsModifiedFrame	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 that return Frame

Modifier and Type	Method	Description
Frame	OGMFile.getCovRefFrame()	Get coordinate system for covariance matrix, for absolute frames.
Frame	CCSDSFrame.getFrame(IERSConventions conventions, boolean simpleEOP)	Get the frame corresponding to the CCSDS constant.
Frame	ODMMetaData.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).
Frame	OEMFile.CovarianceMatrix.getFrame()	Get coordinate system for covariance matrix, for absolute frames.
Frame	OEMFile.EphemeridesBlock.getFrame()
Frame	TDMFile.TDMMetaData.getReferenceFrame()	Get the the value of REFERENCE_FRAME as an Orekit Frame.
Frame	ODMMetaData.getRefFrame()	Get the the value of REF_FRAME as an Orekit Frame.
Frame	OPMFile.Maneuver.getRefFrame()	Get Coordinate system for velocity increment vector, for absolute frames.

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

Modifier and Type	Method	Description
StreamingOemWriter.Segment	StreamingOemWriter.newSegment(Frame frame, Map<Keyword,String> segmentMetadata)	Create a writer for a new OEM ephemeris segment.
void	TDMFile.TDMMetaData.setReferenceFrame(Frame refFrame)	Set the reference frame in which data are given: used for RADEC tracking data.
void	OPMFile.Maneuver.setRefFrame(Frame refFrame)	Set Coordinate system for velocity increment vector, for absolute frames.

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()

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

Constructor	Description
OrekitEphemerisSegment(List<TimeStampedPVCoordinates> coordinates, Frame frame, String frameCenterString, double mu, TimeScale timeScale, int samples)	constructor for OrekitEphemerisSegment.

Uses of Frame in org.orekit.files.sp3

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

Modifier and Type	Method	Description
Frame	SP3File.SP3Ephemeris.getFrame()

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.

Uses of Frame in org.orekit.forces

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

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

Uses of Frame in org.orekit.forces.drag

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

Modifier and Type	Method	Description
Vector3D	DragSensitive.dragAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, double density, Vector3D relativeVelocity, double[] parameters)	Compute the acceleration due to drag.
FieldVector3D<DerivativeStructure>	DragSensitive.dragAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, double density, Vector3D relativeVelocity, double[] parameters, String paramName)	Compute acceleration due to drag, with parameters derivatives.
<T extends RealFieldElement<T>> FieldVector3D<T>	DragSensitive.dragAcceleration(FieldAbsoluteDate<T> date, Frame frame, FieldVector3D<T> position, FieldRotation<T> rotation, T mass, T density, FieldVector3D<T> relativeVelocity, T[] parameters)	Compute the acceleration due to drag.
Vector3D	IsotropicDrag.dragAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, double density, Vector3D relativeVelocity, double[] parameters)	Compute the acceleration due to drag.
FieldVector3D<DerivativeStructure>	IsotropicDrag.dragAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, double density, Vector3D relativeVelocity, double[] parameters, String paramName)	Compute acceleration due to drag, with parameters derivatives.
<T extends RealFieldElement<T>> FieldVector3D<T>	IsotropicDrag.dragAcceleration(FieldAbsoluteDate<T> date, Frame frame, FieldVector3D<T> position, FieldRotation<T> rotation, T mass, T density, FieldVector3D<T> relativeVelocity, T[] parameters)	Compute the acceleration due to drag.

Uses of Frame in org.orekit.forces.drag.atmosphere

Methods in org.orekit.forces.drag.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.forces.drag.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 RealFieldElement<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 RealFieldElement<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 RealFieldElement<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 RealFieldElement<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 RealFieldElement<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 RealFieldElement<T>> T	SimpleExponentialAtmosphere.getDensity(FieldAbsoluteDate<T> date, FieldVector3D<T> position, Frame frame)
default Vector3D	Atmosphere.getVelocity(AbsoluteDate date, Vector3D position, Frame frame)	Get the inertial velocity of atmosphere molecules.
default <T extends RealFieldElement<T>> FieldVector3D<T>	Atmosphere.getVelocity(FieldAbsoluteDate<T> date, FieldVector3D<T> position, Frame frame)	Get the inertial velocity of atmosphere molecules.

Uses of Frame in org.orekit.forces.gravity

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

Constructor	Description
HolmesFeatherstoneAttractionModel(Frame centralBodyFrame, NormalizedSphericalHarmonicsProvider provider)	Creates a new instance.
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, 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.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.

Uses of Frame in org.orekit.forces.radiation

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

Modifier and Type	Method	Description
<T extends RealFieldElement<T>> T	SolarRadiationPressure.getLightingRatio(FieldVector3D<T> position, Frame frame, FieldAbsoluteDate<T> date)	Get the lighting ratio ([0-1]).
double	SolarRadiationPressure.getLightingRatio(Vector3D position, Frame frame, AbsoluteDate date)	Get the lighting ratio ([0-1]).
Vector3D	IsotropicRadiationClassicalConvention.radiationPressureAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, Vector3D flux, double[] parameters)	Compute the acceleration due to radiation pressure.
FieldVector3D<DerivativeStructure>	IsotropicRadiationClassicalConvention.radiationPressureAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, Vector3D flux, double[] parameters, String paramName)	Compute the acceleration due to radiation pressure, with parameters derivatives.
<T extends RealFieldElement<T>> FieldVector3D<T>	IsotropicRadiationClassicalConvention.radiationPressureAcceleration(FieldAbsoluteDate<T> date, Frame frame, FieldVector3D<T> position, FieldRotation<T> rotation, T mass, FieldVector3D<T> flux, T[] parameters)	Compute the acceleration due to radiation pressure.
Vector3D	IsotropicRadiationCNES95Convention.radiationPressureAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, Vector3D flux, double[] parameters)	Compute the acceleration due to radiation pressure.
FieldVector3D<DerivativeStructure>	IsotropicRadiationCNES95Convention.radiationPressureAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, Vector3D flux, double[] parameters, String paramName)	Compute the acceleration due to radiation pressure, with parameters derivatives.
<T extends RealFieldElement<T>> FieldVector3D<T>	IsotropicRadiationCNES95Convention.radiationPressureAcceleration(FieldAbsoluteDate<T> date, Frame frame, FieldVector3D<T> position, FieldRotation<T> rotation, T mass, FieldVector3D<T> flux, T[] parameters)	Compute the acceleration due to radiation pressure.
Vector3D	IsotropicRadiationSingleCoefficient.radiationPressureAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, Vector3D flux, double[] parameters)	Compute the acceleration due to radiation pressure.
FieldVector3D<DerivativeStructure>	IsotropicRadiationSingleCoefficient.radiationPressureAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, Vector3D flux, double[] parameters, String paramName)	Compute the acceleration due to radiation pressure, with parameters derivatives.
<T extends RealFieldElement<T>> FieldVector3D<T>	IsotropicRadiationSingleCoefficient.radiationPressureAcceleration(FieldAbsoluteDate<T> date, Frame frame, FieldVector3D<T> position, FieldRotation<T> rotation, T mass, FieldVector3D<T> flux, T[] parameters)	Compute the acceleration due to radiation pressure.
Vector3D	RadiationSensitive.radiationPressureAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, Vector3D flux, double[] parameters)	Compute the acceleration due to radiation pressure.
FieldVector3D<DerivativeStructure>	RadiationSensitive.radiationPressureAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, Vector3D flux, double[] parameters, String paramName)	Compute the acceleration due to radiation pressure, with parameters derivatives.
<T extends RealFieldElement<T>> FieldVector3D<T>	RadiationSensitive.radiationPressureAcceleration(FieldAbsoluteDate<T> date, Frame frame, FieldVector3D<T> position, FieldRotation<T> rotation, T mass, FieldVector3D<T> flux, T[] parameters)	Compute the acceleration due to radiation pressure.

Uses of Frame in org.orekit.frames

Subclasses of Frame in org.orekit.frames

Modifier and Type	Class	Description
class	FactoryManagedFrame	Base class for the predefined frames that are managed by FramesFactory.
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	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	HelmertTransformation.Predefined.createTransformedITRF(Frame parent, String name)	Create an ITRF frame by transforming another ITRF frame.
Frame	Frame.getAncestor(int n)	Get the nth ancestor of the frame.
static Frame	FramesFactory.getEcliptic(IERSConventions conventions)	Get the ecliptic frame.
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.
static Frame	FramesFactory.getGCRF()	Get the unique GCRF frame.
static Frame	FramesFactory.getICRF()	Get the unique ICRF frame.
Frame	Frame.getParent()	Get the parent frame.
protected 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.
static EOPHistory	FramesFactory.findEOP(Frame start)	Retrieve EOP from a frame hierarchy.
double	TopocentricFrame.getAzimuth(Vector3D extPoint, Frame frame, AbsoluteDate date)	Get the azimuth of a point with regards to the topocentric frame center point.
double	TopocentricFrame.getElevation(Vector3D extPoint, Frame frame, AbsoluteDate date)	Get the elevation of a point with regards to the local point.
Frame	Frame.getFrozenFrame(Frame reference, AbsoluteDate freezingDate, String frozenName)	Get a new version of the instance, frozen with respect to a reference frame.
static Transform	FramesFactory.getNonInterpolatingTransform(Frame from, Frame to, AbsoluteDate date)	Get the transform between two frames, suppressing all interpolation.
static <T extends RealFieldElement<T>> FieldTransform<T>	FramesFactory.getNonInterpolatingTransform(Frame from, Frame to, FieldAbsoluteDate<T> date)	Get the transform between two frames, suppressing all interpolation.
TimeStampedPVCoordinates	TopocentricFrame.getPVCoordinates(AbsoluteDate date, Frame frame)	Get the PVCoordinates of the topocentric frame origin in the selected frame.
double	TopocentricFrame.getRange(Vector3D extPoint, Frame frame, AbsoluteDate date)	Get the range of a point with regards to the topocentric frame center point.
double	TopocentricFrame.getRangeRate(PVCoordinates extPV, Frame frame, AbsoluteDate date)	Get the range rate of a point with regards to the topocentric frame center point.
Transform	Frame.getTransformTo(Frame destination, AbsoluteDate date)	Get the transform from the instance to another frame.
<T extends RealFieldElement<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.

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.
LocalOrbitalFrame(Frame parent, LOFType type, 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.

Uses of Frame in org.orekit.gnss.attitude

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

Modifier and Type	Method	Description
<T extends RealFieldElement<T>> FieldAttitude<T>	AbstractGNSSAttitudeProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)	Compute the attitude corresponding to an orbital state.
Attitude	AbstractGNSSAttitudeProvider.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)	Compute the attitude corresponding to an orbital state.

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

Constructor	Description
AbstractGNSSAttitudeProvider(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)	Simple constructor.
BeidouGeo(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)	Simple constructor.
BeidouIGSO(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)	Simple constructor.
BeidouMeo(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)	Simple constructor.
Galileo(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)	Simple constructor.
GenericGNSS(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)	Simple constructor.
Glonass(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)	Simple constructor.
GPSBlockIIA(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame, int prnNumber)	Simple constructor.
GPSBlockIIF(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame)	Simple constructor.
GPSBlockIIR(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider 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.
<T extends RealFieldElement<T>> FieldGeodeticPoint<T>	Geoid.getIntersectionPoint(FieldLine<T> lineInFrame, FieldVector3D<T> closeInFrame, Frame frame, FieldAbsoluteDate<T> date)	Get the intersection point of a line with the surface of the body.
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 RealFieldElement<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.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	StationDisplacement.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.

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

Modifier and Type	Method	Description
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.
abstract Orbit	OrbitType.mapArrayToOrbit(double[] array, double[] arrayDot, PositionAngle type, AbsoluteDate date, double mu, Frame frame)	Convert state array to orbital parameters.
abstract <T extends RealFieldElement<T>> FieldOrbit<T>	OrbitType.mapArrayToOrbit(T[] array, T[] arrayDot, PositionAngle type, FieldAbsoluteDate<T> date, double mu, Frame frame)	Convert state array to orbital parameters.

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

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

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 inertial frame.
Frame	Propagator.getFrame()	Get the frame in which the orbit is propagated.
Frame	SpacecraftState.getFrame()	Get the inertial frame.

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

Modifier and Type	Method	Description
TimeStampedPVCoordinates	AbstractPropagator.getPVCoordinates(AbsoluteDate date, Frame frame)	Get the PVCoordinates of the body in the selected frame.
TimeStampedFieldPVCoordinates<T>	FieldAbstractPropagator.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.
TimeStampedPVCoordinates	SpacecraftState.getPVCoordinates(Frame outputFrame)	Get the TimeStampedPVCoordinates in given output frame.

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()

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

Modifier and Type	Method	Description
TimeStampedPVCoordinates	AggregateBoundedPropagator.getPVCoordinates(AbsoluteDate date, Frame frame)
TimeStampedPVCoordinates	Ephemeris.getPVCoordinates(AbsoluteDate date, Frame f)	Get the PVCoordinates of the body in the selected 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	GPSPropagator.getECEF()	Gets the Earth Centered Earth Fixed frame used to propagate GPS orbits according to the GPS Interface Specification.
Frame	GPSPropagator.getECI()	Gets the Earth Centered Inertial frame used to propagate the orbit.
Frame	GPSPropagator.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
GPSPropagator.Builder	GPSPropagator.Builder.ecef(Frame bodyFixed)	Sets the Earth Centered Earth Fixed frame assimilated to the WGS84 ECEF.
GPSPropagator.Builder	GPSPropagator.Builder.eci(Frame inertial)	Sets the Earth Centered Inertial frame used for propagation.

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	TLEPropagator.getFrame()	Get the frame in which the orbit is propagated.

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.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.

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

Constructor	Description
FieldNodeDetector(FieldOrbit<T> orbit, Frame frame)	Build a new instance.
FieldNodeDetector(T threshold, FieldOrbit<T> orbit, Frame frame)	Build a new instance.
GroundFieldOfViewDetector(Frame frame, FieldOfView fov)	Build a new instance.
NodeDetector(double threshold, Orbit orbit, Frame frame)	Build a new instance.
NodeDetector(Orbit orbit, Frame frame)	Build a new instance.

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, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame)	Create a mapper between raw double components and spacecraft state.
protected abstract FieldStateMapper<T>	FieldAbstractIntegratedPropagator.createMapper(FieldAbsoluteDate<T> referenceDate, double mu, OrbitType orbitType, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame)	Create a mapper between raw double components and spacecraft state.
TimeStampedFieldPVCoordinates<T>	FieldIntegratedEphemeris.getPVCoordinates(FieldAbsoluteDate<T> date, Frame frame)	Get the FieldPVCoordinates of the body in the selected frame.
TimeStampedPVCoordinates	IntegratedEphemeris.getPVCoordinates(AbsoluteDate date, Frame frame)	Get the PVCoordinates of the body in the selected frame.

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

Constructor	Description
FieldStateMapper(FieldAbsoluteDate<T> referenceDate, double mu, OrbitType orbitType, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame)	Simple constructor.
StateMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngle 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, double mu, OrbitType orbitType, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame)	Create a mapper between raw double components and spacecraft state.
protected StateMapper	NumericalPropagator.createMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame)	Create a mapper between raw double components and spacecraft state.
TimeStampedFieldPVCoordinates<T>	FieldNumericalPropagator.getPVCoordinates(FieldAbsoluteDate<T> date, Frame frame)	Get the FieldPVCoordinates of the body in the selected frame.
TimeStampedPVCoordinates	NumericalPropagator.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, PositionAngle ignoredPositionAngleType, AttitudeProvider attitudeProvider, Frame frame)	Create a mapper between raw double components and spacecraft state.

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, int maxDegreeTesseralSP, int maxOrderTesseralSP, int maxEccPowTesseralSP, int maxFrequencyShortPeriodics, int maxDegreeMdailyTesseralSP, int maxOrderMdailyTesseralSP, int maxEccPowMdailyTesseralSP)	Simple 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.

Uses of Frame in org.orekit.utils

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

Modifier and Type	Method	Description
<T extends RealFieldElement<T>> TimeStampedFieldPVCoordinates<T>	ExtendedPVCoordinatesProvider.getPVCoordinates(FieldAbsoluteDate<T> date, Frame frame)	Get the FieldPVCoordinates of the body in the selected frame.
TimeStampedFieldPVCoordinates<T>	FieldPVCoordinatesProvider.getPVCoordinates(FieldAbsoluteDate<T> date, Frame frame)	Get the FieldPVCoordinates of the body in the selected frame.
TimeStampedPVCoordinates	PVCoordinatesProvider.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).