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	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.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.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.ilrs	This package provides parsers for laser ranging data stored in CDR and CPF formats.
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.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.maneuvers.propulsion	This package provides propulsion models intended to be used with class Maneuver.
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.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.gnss.clock	This package provides classes related to navigation clock files.
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.models.earth.weather	This package provides models that simulate global weather conditions on Earth.
org.orekit.orbits	This package provides classes to represent orbits.
org.orekit.propagation	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 and Description
Frame	GroundPointing.getBodyFrame() Get the body frame.
Frame	FieldAttitude.getReferenceFrame() Get the reference frame.
Frame	Attitude.getReferenceFrame() Get the reference frame.

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

Modifier and Type	Method and Description
<T extends CalculusFieldElement<T>> FieldAttitude<T>	AttitudeBuilder.build(Frame frame, FieldPVCoordinatesProvider<T> pvProv, TimeStampedFieldAngularCoordinates<T> 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	AttitudeBuilder.build(Frame frame, PVCoordinatesProvider pvProv, TimeStampedAngularCoordinates rawAttitude) Build a filtered attitude.
Attitude	FixedFrameBuilder.build(Frame frame, PVCoordinatesProvider pvProv, TimeStampedAngularCoordinates rawAttitude) Build a filtered attitude.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	TabulatedLofOffset.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> 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.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	YawSteering.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> 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.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	InertialProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> 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.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	TabulatedProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	AggregateBoundedAttitudeProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> 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.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	AttitudesSequence.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> 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.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	LofOffsetPointing.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> 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.
<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	TabulatedLofOffset.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	CelestialBodyPointed.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	YawSteering.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	LofOffset.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	InertialProvider.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	FixedRate.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	TabulatedProvider.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate 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.
Attitude	AttitudeProvider.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	AttitudesSequence.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	YawCompensation.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	LofOffsetPointing.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	SpinStabilized.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	GroundPointing.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	YawSteering.getBaseState(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the base system state at given date, without compensation.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	YawCompensation.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.
Attitude	YawCompensation.getBaseState(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the base system state at given date, without compensation.
<T extends CalculusFieldElement<T>> TimeStampedFieldPVCoordinates<T>	YawSteering.getTargetPV(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the target point position/velocity 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.
<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.
<T extends CalculusFieldElement<T>> TimeStampedFieldPVCoordinates<T>	YawCompensation.getTargetPV(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> 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.
<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.
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.
TimeStampedPVCoordinates	YawSteering.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate 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.
TimeStampedPVCoordinates	NadirPointing.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate 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.
TimeStampedPVCoordinates	TargetPointing.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the target point position/velocity in specified frame.
TimeStampedPVCoordinates	LofOffsetPointing.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the target point position/velocity in specified frame.
abstract TimeStampedPVCoordinates	GroundPointing.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the target point position/velocity in specified frame.
<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	InertialProvider.of(Frame satelliteFrame) Creates an attitude provider aligned with the given frame.
FieldAttitude<T>	FieldAttitude.withReferenceFrame(Frame newReferenceFrame) Get a similar attitude with a specific reference frame.
Attitude	Attitude.withReferenceFrame(Frame newReferenceFrame) Get a similar attitude with a specific reference frame.

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

Constructor and Description
Attitude(AbsoluteDate date, Frame referenceFrame, AngularCoordinates orientation) Creates a new instance.
Attitude(AbsoluteDate date, Frame referenceFrame, Rotation attitude, Vector3D spin, Vector3D acceleration) Creates a new instance.
Attitude(Frame referenceFrame, TimeStampedAngularCoordinates 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(FieldAbsoluteDate<T> date, Frame referenceFrame, FieldAngularCoordinates<T> orientation) Creates a new instance.
FieldAttitude(FieldAbsoluteDate<T> date, Frame referenceFrame, FieldRotation<T> attitude, FieldVector3D<T> spin, FieldVector3D<T> acceleration) Creates a new instance.
FieldAttitude(FieldAbsoluteDate<T> date, Frame referenceFrame, Rotation attitude, Vector3D spin, Vector3D acceleration, Field<T> field) Creates a new instance.
FieldAttitude(Frame referenceFrame, TimeStampedFieldAngularCoordinates<T> orientation) Creates a new instance.
FixedFrameBuilder(Frame referenceFrame) Creates new instance.
GroundPointing(Frame inertialFrame, Frame bodyFrame) Default constructor.
InertialProvider(Frame frame) Creates new instance aligned with the given frame.
InertialProvider(Rotation rotation, Frame reference) Creates new instance with a fixed attitude in the given frame.
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<? extends TimeStampedAngularCoordinates> table, int n, AngularDerivativesFilter filter) Creates new instance.
TabulatedLofOffset(Frame inertialFrame, LOFType type, 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, Frame bodyFrame, Vector3D target) Creates a new instance from body frame and target expressed in Cartesian coordinates.
TargetPointing(Frame inertialFrame, GeodeticPoint targetGeo, BodyShape shape) Creates a new instance from body shape and target expressed in geodetic 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 and Description
Frame	OneAxisEllipsoid.getBodyFrame() Get body frame related to body shape.
Frame	BodyShape.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.
Frame	CR3BPSystem.getRotatingFrame() Get the CR3BP Rotating Frame.

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

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

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

Modifier and Type	Method and Description
KeplerianOrbit	IodGooding.estimate(Frame frame, AngularRaDec raDec1, AngularRaDec raDec2, AngularRaDec raDec3, double rho1init, double rho3init) Orbit got from three angular observations.
KeplerianOrbit	IodGooding.estimate(Frame frame, AngularRaDec raDec1, AngularRaDec raDec2, AngularRaDec raDec3, double rho1init, double rho3init, int nRev, boolean direction) Orbit got from three angular observations.
KeplerianOrbit	IodLambert.estimate(Frame frame, boolean posigrade, int nRev, Position p1, Position p2) Estimate an initial orbit from two position measurements.
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.
KeplerianOrbit	IodGibbs.estimate(Frame frame, Position p1, Position p2, Position p3) Give an initial orbit estimation, assuming Keplerian motion.
CartesianOrbit	IodLaplace.estimate(Frame frame, PVCoordinates obsPva, AbsoluteDate obsDate1, Vector3D los1, AbsoluteDate obsDate2, Vector3D los2, AbsoluteDate obsDate3, Vector3D los3) Estimate orbit from three line of sight angles from the same location.
CartesianOrbit	IodLaplace.estimate(Frame frame, PVCoordinates obsPva, AngularRaDec raDec1, AngularRaDec raDec2, AngularRaDec raDec3) Estimate the orbit from three angular observations at the same location.
KeplerianOrbit	IodGibbs.estimate(Frame frame, PV pv1, PV pv2, PV pv3) Give an initial orbit estimation, assuming Keplerian motion.
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	IodGooding.estimate(Frame frame, Vector3D O1, Vector3D O2, Vector3D O3, Vector3D lineOfSight1, AbsoluteDate dateObs1, Vector3D lineOfSight2, AbsoluteDate dateObs2, Vector3D lineOfSight3, AbsoluteDate dateObs3, double rho1init, double rho3init) Orbit got from Observed Three Lines of Sight (angles only).
KeplerianOrbit	IodGooding.estimate(Frame frame, 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) Orbit got from Observed Three Lines of Sight (angles only).

Uses of Frame in org.orekit.estimation.measurements

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

Modifier and Type	Method and 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 and Description
Transform	GroundStation.getOffsetToInertial(Frame inertial, AbsoluteDate clockDate) 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.

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

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

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

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

Modifier and Type	Class and 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 and 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 and 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 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.
static CelestialBodyFrame	CelestialBodyFrame.map(Frame frame) Map an Orekit frame to a CCSDS frame.

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

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

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 and 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 and Description
Attitude	ApmQuaternion.getAttitude(Frame frame, PVCoordinatesProvider pvProvider) Get the attitude.
Attitude	Apm.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 and 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 and Description
Frame	CommonMetadata.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 and 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 and Description
Frame	TrajectoryStateHistory.getFrame() Get the reference frame for this ephemeris segment.

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

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

Constructor and 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.ilrs

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

Modifier and Type	Method and 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 and 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.sp3

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

Modifier and Type	Method and Description
Frame	SP3.SP3Ephemeris.getFrame()

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

Constructor and Description
SP3(double mu, int interpolationSamples, Function<? super String,? extends Frame> frameBuilder) Create a new SP3 file object.
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.forces

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

Modifier and Type	Method and 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.
<T extends CalculusFieldElement<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.
Vector3D	BoxAndSolarArraySpacecraft.getNormal(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation) Get solar array normal in spacecraft frame.
<T extends CalculusFieldElement<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.
<T extends CalculusFieldElement<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 and 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.
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.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	DragSensitive.dragAcceleration(FieldAbsoluteDate<T> date, Frame frame, FieldVector3D<T> position, FieldRotation<T> rotation, T mass, T density, FieldVector3D<T> relativeVelocity, T[] parameters) Compute the acceleration due to drag.
<T extends CalculusFieldElement<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.
protected DerivativeStructure	AbstractDragForceModel.getDSDensityWrtStateUsingFiniteDifferences(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> 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

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

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

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

Modifier and Type	Method and Description
static ThrustDirectionAndAttitudeProvider	ThrustDirectionAndAttitudeProvider.buildFromDirectionInFrame(Frame thrustDirectionFrame, ThrustDirectionProvider variableDirectionInFrame, Vector3D thrusterAxisInSatelliteFrame) Build a ThrustDirectionAndAttitudeProvider by a variable direction in a custom frame.
Vector3D	ConstantThrustDirectionProvider.computeThrustDirection(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Vector3D	ThrustDirectionProvider.computeThrustDirection(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the thrust direction corresponding to an orbital state.
<T extends CalculusFieldElement<T>> FieldAttitude<T>	ThrustDirectionAndAttitudeProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	ThrustDirectionAndAttitudeProvider.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
protected Attitude	ThrustDirectionAndAttitudeProvider.getAttitudeFromFrame(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude for DIRECTION_IN_FRAME or DIRECTION_IN_LOF types.

Uses of Frame in org.orekit.forces.radiation

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

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

Uses of Frame in org.orekit.frames

Subclasses of Frame in org.orekit.frames

Modifier and Type	Class and 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 and Description
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	OrphanFrame.getFrame() Get the associated 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	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	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 and 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.
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.
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.
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 and 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 and 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.

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

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

Uses of Frame in org.orekit.gnss.antenna

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

Modifier and Type	Method and Description
abstract GNSSAttitudeProvider	SatelliteType.buildAttitudeProvider(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider 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 and Description
BeidouGeo(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame) Simple constructor.
BeidouIGSO(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame) Simple constructor.
BeidouMeo(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame) Simple constructor.
Galileo(double yawRate, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame) Simple constructor.
GenericGNSS(AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame) Simple constructor.
Glonass(double yawRate, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame) Simple constructor.
GPSBlockIIA(double yawRate, double yawBias, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame) Simple constructor.
GPSBlockIIF(double yawRate, double yawBias, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame) Simple constructor.
GPSBlockIIR(double yawRate, AbsoluteDate validityStart, AbsoluteDate validityEnd, ExtendedPVCoordinatesProvider sun, Frame inertialFrame) Simple constructor.

Uses of Frame in org.orekit.gnss.clock

Methods in org.orekit.gnss.clock that return Frame

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

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

Constructor and 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, TimeScales timeScales) Constructor, build the IGS clock file parser.

Uses of Frame in org.orekit.models.earth

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

Modifier and Type	Method and Description
Frame	Geoid.getBodyFrame()

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

Modifier and Type	Method and 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.
TimeStampedPVCoordinates	Geoid.projectToGround(TimeStampedPVCoordinates pv, Frame frame)
Vector3D	Geoid.projectToGround(Vector3D point, AbsoluteDate date, 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 and 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 and Description
Frame	HarrisPriester.getFrame() Get the frame of the central body.
Frame	JB2008.getFrame() Get the frame of the central body.
Frame	DTM2000.getFrame() Get the frame of the central body.
Frame	Atmosphere.getFrame() Get the frame of the central body.
Frame	SimpleExponentialAtmosphere.getFrame() Get the frame of the central body.
Frame	NRLMSISE00.getFrame() Get the frame of the central body.

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

Modifier and Type	Method and Description
double	HarrisPriester.getDensity(AbsoluteDate date, Vector3D position, Frame frame) Get the local density at some position.
double	JB2008.getDensity(AbsoluteDate date, Vector3D position, Frame frame) Get the local density.
double	DTM2000.getDensity(AbsoluteDate date, Vector3D position, Frame frame) Get the local density.
double	Atmosphere.getDensity(AbsoluteDate date, Vector3D position, Frame frame) Get the local density.
double	SimpleExponentialAtmosphere.getDensity(AbsoluteDate date, Vector3D 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	HarrisPriester.getDensity(FieldAbsoluteDate<T> date, FieldVector3D<T> position, Frame frame) Get the local density at some position.
<T extends CalculusFieldElement<T>> T	JB2008.getDensity(FieldAbsoluteDate<T> date, FieldVector3D<T> 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.
<T extends CalculusFieldElement<T>> T	Atmosphere.getDensity(FieldAbsoluteDate<T> date, FieldVector3D<T> position, Frame frame) Get the local density.
<T extends CalculusFieldElement<T>> T	SimpleExponentialAtmosphere.getDensity(FieldAbsoluteDate<T> date, FieldVector3D<T> position, Frame frame)
<T extends CalculusFieldElement<T>> T	NRLMSISE00.getDensity(FieldAbsoluteDate<T> date, FieldVector3D<T> position, Frame frame) Get the local density.
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 and Description
Vector3D	TidalDisplacement.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	OceanLoading.displacement(BodiesElements elements, Frame earthFrame, Vector3D referencePoint) Compute displacement of a ground reference point.

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

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

Constructor and Description
GlobalPressureTemperatureModel(double latitude, double longitude, Frame bodyFrame) Build a new instance.
GlobalPressureTemperatureModel(double latitude, double longitude, Frame bodyFrame, DataContext dataContext) Build a new instance.

Uses of Frame in org.orekit.orbits

Methods in org.orekit.orbits that return Frame

Modifier and Type	Method and 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 and Description
TimeStampedPVCoordinates	Orbit.getPVCoordinates(AbsoluteDate otherDate, Frame otherFrame) Get the PVCoordinates of the body in the selected frame.
TimeStampedFieldPVCoordinates<T>	FieldOrbit.getPVCoordinates(FieldAbsoluteDate<T> otherDate, Frame otherFrame) Get the FieldPVCoordinates of the body in the selected frame.
TimeStampedFieldPVCoordinates<T>	FieldOrbit.getPVCoordinates(Frame outputFrame) Get the TimeStampedPVCoordinates in a specified frame.
TimeStampedPVCoordinates	Orbit.getPVCoordinates(Frame outputFrame) Get the TimeStampedPVCoordinates in a specified 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 CalculusFieldElement<T>> FieldOrbit<T>	OrbitType.mapArrayToOrbit(T[] array, T[] arrayDot, PositionAngle type, FieldAbsoluteDate<T> date, T mu, Frame frame) Convert state array to orbital parameters.

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

Constructor and 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, 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, PositionAngle type, Frame frame, FieldAbsoluteDate<T> date, T mu) Creates a new instance.
FieldCircularOrbit(T a, T ex, T ey, T i, T raan, T alpha, T aDot, T exDot, T eyDot, T iDot, T raanDot, T alphaDot, PositionAngle type, Frame frame, FieldAbsoluteDate<T> date, T mu) Creates a new instance.
FieldEquinoctialOrbit(FieldPVCoordinates<T> pvCoordinates, Frame frame, FieldAbsoluteDate<T> date, T mu) Constructor from Cartesian parameters.
FieldEquinoctialOrbit(TimeStampedFieldPVCoordinates<T> pvCoordinates, Frame frame, T mu) Constructor from Cartesian parameters.
FieldEquinoctialOrbit(T a, T ex, T ey, T hx, T hy, T l, PositionAngle type, Frame frame, FieldAbsoluteDate<T> date, T mu) Creates a new instance.
FieldEquinoctialOrbit(T a, T ex, T ey, T hx, T hy, T l, T aDot, T exDot, T eyDot, T hxDot, T hyDot, T lDot, PositionAngle type, Frame frame, FieldAbsoluteDate<T> date, T mu) Creates a new instance.
FieldKeplerianOrbit(FieldPVCoordinates<T> FieldPVCoordinates, Frame frame, FieldAbsoluteDate<T> date, T mu) Constructor from Cartesian parameters.
FieldKeplerianOrbit(TimeStampedFieldPVCoordinates<T> pvCoordinates, Frame frame, T mu) Constructor from Cartesian parameters.
FieldKeplerianOrbit(T a, T e, T i, T pa, T raan, T anomaly, PositionAngle type, Frame frame, FieldAbsoluteDate<T> date, T mu) Creates a new instance.
FieldKeplerianOrbit(T a, T e, T i, T pa, T raan, T anomaly, T aDot, T eDot, T iDot, T paDot, T raanDot, T anomalyDot, PositionAngle type, Frame frame, FieldAbsoluteDate<T> date, T mu) Creates a new instance.
FieldOrbit(Frame frame, FieldAbsoluteDate<T> date, T mu) Default constructor.
FieldOrbit(TimeStampedFieldPVCoordinates<T> FieldPVCoordinates, Frame frame, T 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 and Description
Frame	Propagator.getFrame() Get the frame in which the orbit is propagated.
Frame	FieldSpacecraftState.getFrame() Get the defining frame.
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	StateCovariance.getFrame() Get the covariance frame.
Frame	SpacecraftState.getFrame() Get the defining frame.
Frame	AbstractPropagator.getFrame() Get the frame in which the orbit is propagated.

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

Modifier and Type	Method and Description
StateCovariance	StateCovariance.changeCovarianceFrame(Orbit orbit, Frame frameOut) Get the covariance in the output frame.
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.
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 and Description
StateCovariance(RealMatrix orbitalCovariance, AbsoluteDate epoch, Frame covarianceFrame, OrbitType orbitType, PositionAngle angleType) Constructor.

Uses of Frame in org.orekit.propagation.analytical

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

Modifier and Type	Method and Description
Frame	Ephemeris.getFrame()

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

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

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

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

Modifier and Type	Method and 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 and Description
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 TLEPropagator	TLEPropagator.selectExtrapolator(TLE tle, AttitudeProvider attitudeProvider, double mass, Frame teme) Selects the extrapolator to use with the selected TLE.
static <T extends CalculusFieldElement<T>> FieldTLE<T>	FieldTLE.stateToTLE(FieldSpacecraftState<T> state, FieldTLE<T> templateTLE, TimeScale utc, Frame teme) Convert Spacecraft State into TLE.
static <T extends CalculusFieldElement<T>> FieldTLE<T>	FieldTLE.stateToTLE(FieldSpacecraftState<T> state, FieldTLE<T> templateTLE, TimeScale utc, Frame teme, double epsilon, int maxIterations) Convert Spacecraft State into TLE.
static TLE	TLE.stateToTLE(SpacecraftState state, TLE templateTLE, TimeScale utc, Frame teme) Convert Spacecraft State into TLE.
static TLE	TLE.stateToTLE(SpacecraftState state, TLE templateTLE, TimeScale utc, Frame teme, double epsilon, int maxIterations) Convert Spacecraft State into TLE.

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

Constructor and 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.conversion

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

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

Uses of Frame in org.orekit.propagation.events

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

Modifier and Type	Method and Description
Frame	GroundFieldOfViewDetector.getFrame() Get the sensor reference frame.
Frame	NodeDetector.getFrame() Get the frame in which the equator is defined.
Frame	FieldNodeDetector.getFrame() Get the frame in which the equator is defined.

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

Constructor and 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(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 and Description
Frame	IntegratedEphemeris.getFrame()
Frame	FieldStateMapper.getFrame() Get the inertial frame.
Frame	FieldIntegratedEphemeris.getFrame()
Frame	StateMapper.getFrame() Get the inertial frame.

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

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

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

Constructor and Description
FieldStateMapper(FieldAbsoluteDate<T> referenceDate, T 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 and Description
protected StateMapper	GLONASSNumericalPropagator.createMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame)
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.
protected FieldStateMapper<T>	FieldNumericalPropagator.createMapper(FieldAbsoluteDate<T> referenceDate, T mu, OrbitType orbitType, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame) Create a mapper between raw double components and spacecraft state.
GLONASSNumericalPropagatorBuilder	GLONASSNumericalPropagatorBuilder.eci(Frame inertial) Sets the Earth Centered Inertial frame used for propagation.
TimeStampedPVCoordinates	NumericalPropagator.getPVCoordinates(AbsoluteDate date, Frame frame) Get the PVCoordinates of the body in the selected frame.
TimeStampedFieldPVCoordinates<T>	FieldNumericalPropagator.getPVCoordinates(FieldAbsoluteDate<T> date, Frame frame) Get the FieldPVCoordinates of the body in the selected frame.

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

Constructor and 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.semianalytical.dsst

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

Modifier and Type	Method and 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.
protected FieldStateMapper<T>	FieldDSSTPropagator.createMapper(FieldAbsoluteDate<T> referenceDate, T mu, OrbitType ignoredOrbitType, PositionAngle ignoredPositionAngleType, AttitudeProvider attitudeProvider, Frame frame) Create a mapper between raw double components and spacecraft state.

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

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

Constructor and 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.

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 and 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

Methods in org.orekit.utils that return Frame

Modifier and Type	Method and 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.

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

Modifier and Type	Method and Description
TimeStampedPVCoordinates	AggregatedPVCoordinatesProvider.getPVCoordinates(AbsoluteDate date, Frame frame)
TimeStampedPVCoordinates	AggregatedPVCoordinatesProvider.InvalidPVProvider.getPVCoordinates(AbsoluteDate date, Frame frame)
TimeStampedPVCoordinates	AbsolutePVCoordinates.getPVCoordinates(AbsoluteDate otherDate, Frame outputFrame)
TimeStampedPVCoordinates	ConstantPVCoordinatesProvider.getPVCoordinates(AbsoluteDate date, Frame frame)
TimeStampedPVCoordinates	PVCoordinatesProvider.getPVCoordinates(AbsoluteDate date, Frame frame) Get the PVCoordinates 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.
TimeStampedFieldPVCoordinates<T>	FieldAbsolutePVCoordinates.getPVCoordinates(FieldAbsoluteDate<T> otherDate, Frame outputFrame)
<T extends CalculusFieldElement<T>> TimeStampedFieldPVCoordinates<T>	ExtendedPVCoordinatesProvider.getPVCoordinates(FieldAbsoluteDate<T> date, Frame frame) Get the FieldPVCoordinates of the body in the selected frame.
TimeStampedPVCoordinates	AbsolutePVCoordinates.getPVCoordinates(Frame outputFrame) Get the TimeStampedPVCoordinates in a specified frame.
TimeStampedFieldPVCoordinates<T>	FieldAbsolutePVCoordinates.getPVCoordinates(Frame outputFrame) Get the TimeStampedFieldPVCoordinates in a specified frame.
static AbsolutePVCoordinates	AbsolutePVCoordinates.interpolate(Frame frame, AbsoluteDate date, CartesianDerivativesFilter filter, Stream<AbsolutePVCoordinates> sample) Interpolate position-velocity.
static <T extends CalculusFieldElement<T>> FieldAbsolutePVCoordinates<T>	FieldAbsolutePVCoordinates.interpolate(Frame frame, FieldAbsoluteDate<T> date, CartesianDerivativesFilter filter, Stream<FieldAbsolutePVCoordinates<T>> sample) Interpolate position-velocity.
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 and Description
AbsolutePVCoordinates(Frame frame, AbsoluteDate date, FieldVector3D<U> p) Builds a AbsolutePVCoordinates triplet from a FieldVector3D<Derivative>.
AbsolutePVCoordinates(Frame frame, AbsoluteDate date, PVCoordinates pva) Build from frame, date and PVA coordinates.
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, TimeStampedPVCoordinates pva) Build from frame and TimeStampedPVCoordinates.
ConstantPVCoordinatesProvider(PVCoordinates pva, Frame frame) Create the PVCoordinatesProvider from a fixed point in a frame.
ConstantPVCoordinatesProvider(Vector3D pos, Frame frame) Create the PVCoordinatesProvider from a fixed point in a frame.
FieldAbsolutePVCoordinates(Frame frame, FieldAbsoluteDate<T> date, FieldPVCoordinates<T> pva) Build from frame, date and FieldPVA coordinates.
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, TimeStampedFieldPVCoordinates<T> pva) Build from frame and TimeStampedFieldPVCoordinates.