Uses of Class
org.orekit.frames.Frame
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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.estimation.measurements.modifiers This package provides measurement modifier.org.orekit.files.ccsds.definitions This package contains definitions for CCSDS objects (frames, time systems...).org.orekit.files.ccsds.ndm.adm This package contains class managing CCSDS Attitude Data Message.org.orekit.files.ccsds.ndm.adm.acm This package contains class managing CCSDS Attitude Comprehensive Message.org.orekit.files.ccsds.ndm.adm.aem This package contains class managing CCSDS Attitude Ephemeris Message.org.orekit.files.ccsds.ndm.adm.apm This package contains class managing CCSDS Attitude Parameter Message.org.orekit.files.ccsds.ndm.cdm This package contains class managing CCSDS Conjunction Data Message.org.orekit.files.ccsds.ndm.odm This package contains class managing CCSDS Orbit Data Message.org.orekit.files.ccsds.ndm.odm.ocm This package contains class managing CCSDS Orbit Comprehensive Message.org.orekit.files.ccsds.ndm.odm.oem This package contains class managing CCSDS Orbit Ephemeris Message.org.orekit.files.general This package provides interfaces for orbit file representations and corresponding parsers.org.orekit.files.ilrs This package provides parsers for laser ranging data stored in CDR and CPF formats.org.orekit.files.rinex.clock This package provides classes related to navigation clock files.org.orekit.files.sp3 This package provides a parser for orbit data stored in SP3 format.org.orekit.files.stk This package provides a parser for STK ephemeris files.org.orekit.forces.drag This package provides all drag-related forces.org.orekit.forces.gravity This package provides all gravity-related forces.org.orekit.forces.inertia This package provides inertial force model.org.orekit.forces.maneuvers This package provides models of simple maneuvers.org.orekit.forces.maneuvers.propulsion This package provides propulsion models intended to be used with classManeuver
.org.orekit.forces.radiation This package provides all radiation pressure related forces.org.orekit.frames This package provides classes to handle frames and transforms between them.org.orekit.gnss This package provides classes related to GNSS applications.org.orekit.gnss.antenna This package provides classes related to receiver and satellites antenna modeling.org.orekit.gnss.attitude This package provides classes related to navigation satellites attitude modeling.org.orekit.models.earth This package provides models that simulate certain physical phenomena of Earth and the near-Earth environment.org.orekit.models.earth.atmosphere This package provides the atmosphere model interface and several implementations.org.orekit.models.earth.displacement This package provides models computing reference points displacements on Earth surface.org.orekit.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 Propagationorg.orekit.propagation.analytical Top level package for analytical propagators.org.orekit.propagation.analytical.gnss This package provides classes to propagate GNSS orbits.org.orekit.propagation.analytical.gnss.data This package provides classes related to navigation data containing in GNSS almanacs and navigation messages.org.orekit.propagation.analytical.intelsat This package provides classes to propagate Intelsat's 11 elements.org.orekit.propagation.analytical.tle This package provides classes to read and extrapolate tle's.org.orekit.propagation.analytical.tle.generation This package provides classes related to TLE generation.org.orekit.propagation.conversion This package provides tools to convert a given propagator or a set ofSpacecraftState
into another propagator.org.orekit.propagation.conversion.averaging This package wraps methods from various (semi)analytical models in Orekit to convert back and forth between an averaged orbital state and an osculating one.org.orekit.propagation.events This package provides interfaces and classes dealing with events occurring during propagation.org.orekit.propagation.integration Utilities for integration-based propagators (both numerical and semi-analytical).org.orekit.propagation.numerical Top level package for numerical propagators.org.orekit.propagation.sampling This package provides interfaces and classes dealing with step handling during propagation.org.orekit.propagation.semianalytical.dsst This package provides an implementation of the Draper Semi-analytical Satellite Theory (DSST).org.orekit.propagation.semianalytical.dsst.forces This package provides force models for Draper Semi-analytical Satellite Theory (DSST).org.orekit.propagation.semianalytical.dsst.utilities This package provides utilities for Draper Semi-analytical Satellite Theory (DSST).org.orekit.utils This package provides useful objects. -
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Uses of Frame in org.orekit.attitudes
Methods in org.orekit.attitudes that return Frame Modifier and Type Method Description Frame
GroundPointing. getBodyFrame()
Get the body frame.Frame
LofOffset. getInertialFrame()
Get the inertial frame.Frame
Attitude. getReferenceFrame()
Get the reference frame.Frame
AttitudeInterpolator. getReferenceFrame()
Get reference frame from which attitude is defined.Frame
FieldAttitude. getReferenceFrame()
Get the reference frame.Frame
FieldAttitudeInterpolator. getReferenceFrame()
Get reference frame from which attitude is defined.Methods in org.orekit.attitudes with parameters of type Frame Modifier and Type Method Description <T extends CalculusFieldElement<T>>
FieldAttitude<T>AttitudeBuilder. build(Frame frame, FieldPVCoordinatesProvider<T> pvProv, TimeStampedFieldAngularCoordinates<T> rawAttitude)
Build a filtered attitude.Attitude
AttitudeBuilder. build(Frame frame, PVCoordinatesProvider pvProv, TimeStampedAngularCoordinates rawAttitude)
Build a filtered attitude.<T extends CalculusFieldElement<T>>
FieldAttitude<T>FixedFrameBuilder. build(Frame frame, FieldPVCoordinatesProvider<T> pvProv, TimeStampedFieldAngularCoordinates<T> rawAttitude)
Build a filtered attitude.Attitude
FixedFrameBuilder. build(Frame frame, PVCoordinatesProvider pvProv, TimeStampedAngularCoordinates rawAttitude)
Build a filtered attitude.<T extends CalculusFieldElement<T>>
FieldAttitude<T>AggregateBoundedAttitudeProvider. getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude corresponding to an orbital state.Attitude
AggregateBoundedAttitudeProvider. getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the attitude corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldAttitude<T>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 CalculusFieldElement<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 CalculusFieldElement<T>>
FieldAttitude<T>CelestialBodyPointed. getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude corresponding to an orbital state.Attitude
CelestialBodyPointed. getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the attitude corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldAttitude<T>FixedRate. getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude corresponding to an orbital state.Attitude
FixedRate. getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the attitude corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldAttitude<T>FrameAlignedProvider. getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude corresponding to an orbital state.Attitude
FrameAlignedProvider. getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the attitude corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldAttitude<T>GroundPointing. getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude corresponding to an orbital state.Attitude
GroundPointing. getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the attitude corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldAttitude<T>LofOffset. getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude corresponding to an orbital state.Attitude
LofOffset. getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the attitude corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldAttitude<T>LofOffsetPointing. getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude corresponding to an orbital state.Attitude
LofOffsetPointing. getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the attitude corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldAttitude<T>SpinStabilized. getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude corresponding to an orbital state.Attitude
SpinStabilized. getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the attitude corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldAttitude<T>TabulatedLofOffset. getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude corresponding to an orbital state.Attitude
TabulatedLofOffset. getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the attitude corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldAttitude<T>TabulatedProvider. getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude corresponding to an orbital state.Attitude
TabulatedProvider. getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the attitude corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldAttitude<T>TorqueFree. getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude corresponding to an orbital state.Attitude
TorqueFree. getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the attitude corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldAttitude<T>YawCompensation. getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude corresponding to an orbital state.Attitude
YawCompensation. getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the attitude corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldAttitude<T>YawSteering. getAttitude(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude corresponding to an orbital state.Attitude
YawSteering. getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the attitude corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldRotation<T>AggregateBoundedAttitudeProvider. getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.Rotation
AggregateBoundedAttitudeProvider. getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.default <T extends CalculusFieldElement<T>>
FieldRotation<T>AttitudeProvider. getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.default Rotation
AttitudeProvider. getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldRotation<T>AttitudesSequence. getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Rotation
AttitudesSequence. getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldRotation<T>CelestialBodyPointed. getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.Rotation
CelestialBodyPointed. getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldRotation<T>FrameAlignedProvider. getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.Rotation
FrameAlignedProvider. getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldRotation<T>GroundPointing. getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.Rotation
GroundPointing. getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldRotation<T>LofOffset. getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.Rotation
LofOffset. getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldRotation<T>LofOffsetPointing. getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.Rotation
LofOffsetPointing. getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldRotation<T>SpinStabilized. getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.Rotation
SpinStabilized. getAttitudeRotation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.<T extends CalculusFieldElement<T>>
FieldAttitude<T>GroundPointingAttitudeModifier. getBaseState(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the base system state at given date, without modifications.Attitude
GroundPointingAttitudeModifier. getBaseState(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the base system state at given date, without modifications.protected <T extends CalculusFieldElement<T>>
FieldVector3D<T>BodyCenterPointing. getTargetPosition(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the target point position in specified frame.protected Vector3D
BodyCenterPointing. getTargetPosition(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the target point position in specified frame.protected <T extends CalculusFieldElement<T>>
FieldVector3D<T>GroundPointing. getTargetPosition(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the target point position in specified frame.protected Vector3D
GroundPointing. getTargetPosition(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the target point position in specified frame.protected <T extends CalculusFieldElement<T>>
FieldVector3D<T>GroundPointingAttitudeModifier. getTargetPosition(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the target point position in specified frame.protected Vector3D
GroundPointingAttitudeModifier. getTargetPosition(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the target point position in specified frame.protected <T extends CalculusFieldElement<T>>
FieldVector3D<T>LofOffsetPointing. getTargetPosition(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the target point position in specified frame.protected Vector3D
LofOffsetPointing. getTargetPosition(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the target point position in specified frame.protected <T extends CalculusFieldElement<T>>
FieldVector3D<T>NadirPointing. getTargetPosition(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the target point position in specified frame.protected Vector3D
NadirPointing. getTargetPosition(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the target point position in specified frame.protected <T extends CalculusFieldElement<T>>
FieldVector3D<T>TargetPointing. getTargetPosition(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the target point position in specified frame.protected Vector3D
TargetPointing. getTargetPosition(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the target point position in specified frame.<T extends CalculusFieldElement<T>>
TimeStampedFieldPVCoordinates<T>BodyCenterPointing. getTargetPV(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the target point position/velocity in specified frame.TimeStampedPVCoordinates
BodyCenterPointing. getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the target point position/velocity in specified frame.protected abstract <T extends CalculusFieldElement<T>>
TimeStampedFieldPVCoordinates<T>GroundPointing. getTargetPV(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the target point position/velocity in specified frame.protected abstract TimeStampedPVCoordinates
GroundPointing. getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the target point position/velocity in specified frame.<T extends CalculusFieldElement<T>>
TimeStampedFieldPVCoordinates<T>GroundPointingAttitudeModifier. getTargetPV(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the target point position/velocity in specified frame.TimeStampedPVCoordinates
GroundPointingAttitudeModifier. getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the target point position/velocity in specified frame.<T extends CalculusFieldElement<T>>
TimeStampedFieldPVCoordinates<T>LofOffsetPointing. getTargetPV(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the target point position/velocity in specified frame.TimeStampedPVCoordinates
LofOffsetPointing. getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the target point position/velocity in specified frame.<T extends CalculusFieldElement<T>>
TimeStampedFieldPVCoordinates<T>NadirPointing. getTargetPV(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the target point position/velocity in specified frame.TimeStampedPVCoordinates
NadirPointing. getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the target point position/velocity in specified frame.<T extends CalculusFieldElement<T>>
TimeStampedFieldPVCoordinates<T>TargetPointing. getTargetPV(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the target point position/velocity in specified frame.TimeStampedPVCoordinates
TargetPointing. getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the target point position/velocity in specified frame.<T extends CalculusFieldElement<T>>
TimeStampedFieldPVCoordinates<T>NadirPointing. getTargetPVViaInterpolation(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute target position-velocity-acceleration vector via interpolation (Field version).TimeStampedPVCoordinates
NadirPointing. getTargetPVViaInterpolation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute target position-velocity-acceleration vector via interpolation.<T extends CalculusFieldElement<T>>
TYawCompensation. getYawAngle(FieldPVCoordinatesProvider<T> pvProv, FieldAbsoluteDate<T> date, Frame frame)
Compute the yaw compensation angle at date.double
YawCompensation. getYawAngle(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Compute the yaw compensation angle at date.static AttitudeProvider
FrameAlignedProvider. of(Frame satelliteFrame)
Creates an attitude provider aligned with the given frame.Attitude
Attitude. withReferenceFrame(Frame newReferenceFrame)
Get a similar attitude with a specific reference frame.FieldAttitude<T>
FieldAttitude. withReferenceFrame(Frame newReferenceFrame)
Get a similar attitude with a specific reference frame.Constructors in org.orekit.attitudes with parameters of type Frame Constructor Description Attitude(Frame referenceFrame, TimeStampedAngularCoordinates orientation)
Creates a new instance.Attitude(AbsoluteDate date, Frame referenceFrame, Rotation attitude, Vector3D spin, Vector3D acceleration)
Creates a new instance.Attitude(AbsoluteDate date, Frame referenceFrame, AngularCoordinates orientation)
Creates a new instance.AttitudeInterpolator(Frame referenceFrame, TimeInterpolator<TimeStampedAngularCoordinates> interpolator)
Constructor.BodyCenterPointing(Frame inertialFrame, Ellipsoid shape)
Creates new instance.CelestialBodyPointed(Frame celestialFrame, 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.FieldAttitudeInterpolator(Frame referenceFrame, FieldTimeInterpolator<TimeStampedFieldAngularCoordinates<KK>,KK> interpolator)
Constructor.FixedFrameBuilder(Frame referenceFrame)
Creates new instance.FrameAlignedProvider(Rotation rotation, Frame reference)
Creates new instance with a fixed attitude in the given frame.FrameAlignedProvider(Frame frame)
Creates new instance aligned with the given frame.GroundPointing(Frame inertialFrame, Frame bodyFrame)
Default constructor.GroundPointingAttitudeModifier(Frame inertialFrame, Frame bodyFrame, GroundPointing groundPointingLaw)
Constructor.LofOffset(Frame inertialFrame, LOF lof)
Create a LOF-aligned attitude.LofOffset(Frame inertialFrame, LOF lof, RotationOrder order, double alpha1, double alpha2, double alpha3)
Creates new instance.LofOffsetPointing(Frame inertialFrame, BodyShape shape, AttitudeProvider attLaw, Vector3D satPointingVector)
Creates new instance.NadirPointing(Frame inertialFrame, BodyShape shape)
Creates new instance.TabulatedLofOffset(Frame inertialFrame, LOF lof, List<? extends TimeStampedAngularCoordinates> table, int n, AngularDerivativesFilter filter)
Creates new instance.TabulatedLofOffset(Frame inertialFrame, LOF lof, List<? extends TimeStampedAngularCoordinates> table, int n, AngularDerivativesFilter filter, AbsoluteDate minDate, AbsoluteDate maxDate)
Creates new instance.TabulatedProvider(Frame referenceFrame, List<? extends TimeStampedAngularCoordinates> table, int n, AngularDerivativesFilter filter)
Creates new instance.TargetPointing(Frame inertialFrame, GeodeticPoint targetGeo, BodyShape shape)
Creates a new instance from body shape and target expressed in geodetic coordinates.TargetPointing(Frame inertialFrame, Frame bodyFrame, Vector3D target)
Creates a new instance from body frame and target expressed in Cartesian coordinates.YawCompensation(Frame inertialFrame, GroundPointing groundPointingLaw)
Creates a new instance.YawSteering(Frame inertialFrame, GroundPointing groundPointingLaw, 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
FieldEllipse. getFrame()
Get the defining frame.Frame
CelestialBody. getInertiallyOrientedFrame()
Get an inertially oriented, body centered frame.Frame
CR3BPSystem. getRotatingFrame()
Get the CR3BP Rotating Frame.Methods in org.orekit.bodies with parameters of type Frame Modifier and Type Method Description <T extends CalculusFieldElement<T>>
FieldVector3D<T>OneAxisEllipsoid. getCartesianIntersectionPoint(FieldLine<T> line, FieldVector3D<T> close, Frame frame, FieldAbsoluteDate<T> date)
Get the intersection point of a line with the surface of the body.Vector3D
OneAxisEllipsoid. getCartesianIntersectionPoint(Line line, Vector3D close, Frame frame, AbsoluteDate date)
Get the intersection point of a line with the surface of the body.<T extends CalculusFieldElement<T>>
FieldGeodeticPoint<T>BodyShape. getIntersectionPoint(FieldLine<T> line, FieldVector3D<T> close, Frame frame, FieldAbsoluteDate<T> date)
Get the intersection point of a line with the surface of the body.GeodeticPoint
BodyShape. getIntersectionPoint(Line line, Vector3D close, Frame frame, AbsoluteDate date)
Get the intersection point of a line with the surface of the body.<T extends CalculusFieldElement<T>>
FieldGeodeticPoint<T>OneAxisEllipsoid. getIntersectionPoint(FieldLine<T> line, FieldVector3D<T> close, Frame frame, FieldAbsoluteDate<T> date)
Get the intersection point of a line with the surface of the body.GeodeticPoint
OneAxisEllipsoid. getIntersectionPoint(Line line, Vector3D close, Frame frame, AbsoluteDate date)
Get the intersection point of a line with the surface of the body.AbsolutePVCoordinates
CR3BPSystem. getRealAPV(AbsolutePVCoordinates apv0, AbsoluteDate initialDate, Frame outputFrame)
Get the AbsolutePVCoordinates from normalized units to standard units in an output frame.Vector3D
BodyShape. projectToGround(Vector3D point, AbsoluteDate date, Frame frame)
Project a point to the ground.TimeStampedPVCoordinates
BodyShape. projectToGround(TimeStampedPVCoordinates pv, Frame frame)
Project a moving point to the ground.Vector3D
OneAxisEllipsoid. projectToGround(Vector3D point, AbsoluteDate date, Frame frame)
Project a point to the ground.TimeStampedPVCoordinates
OneAxisEllipsoid. projectToGround(TimeStampedPVCoordinates pv, Frame frame)
Project a moving point to the ground.<T extends CalculusFieldElement<T>>
FieldGeodeticPoint<T>BodyShape. transform(FieldVector3D<T> point, Frame frame, FieldAbsoluteDate<T> date)
Transform a Cartesian point to a surface-relative point.GeodeticPoint
BodyShape. transform(Vector3D point, Frame frame, AbsoluteDate date)
Transform a Cartesian point to a surface-relative point.<T extends CalculusFieldElement<T>>
FieldGeodeticPoint<T>OneAxisEllipsoid. transform(FieldVector3D<T> point, Frame frame, FieldAbsoluteDate<T> date)
Transform a Cartesian point to a surface-relative point.GeodeticPoint
OneAxisEllipsoid. transform(Vector3D point, Frame frame, AbsoluteDate date)
Transform a Cartesian point to a surface-relative point.FieldGeodeticPoint<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.FieldEllipse(FieldVector3D<T> center, FieldVector3D<T> u, FieldVector3D<T> v, T a, T b, Frame frame)
Simple constructor.JPLEphemeridesLoader(String supportedNames, JPLEphemeridesLoader.EphemerisType generateType, DataProvidersManager dataProvidersManager, TimeScales timeScales, Frame gcrf)
Create a loader for JPL ephemerides binary files.LazyLoadedCelestialBodies(DataProvidersManager dataProvidersManager, TimeScales timeScales, Frame gcrf)
Create a celestial body factory with the given auxiliary data sources.OneAxisEllipsoid(double ae, double f, Frame bodyFrame)
Simple constructor. -
Uses of Frame in org.orekit.estimation.iod
Methods in org.orekit.estimation.iod with parameters of type Frame Modifier and Type Method Description Orbit
IodGauss. estimate(Frame outputFrame, Vector3D obsP1, AbsoluteDate obsDate1, Vector3D los1, Vector3D obsP2, AbsoluteDate obsDate2, Vector3D los2, Vector3D obsP3, AbsoluteDate obsDate3, Vector3D los3)
Estimate and orbit based on Gauss Intial Orbit Determination method.Orbit
IodGauss. estimate(Frame outputFrame, AngularAzEl azEl1, AngularAzEl azEl2, AngularAzEl azEl3)
Estimate and orbit based on Gauss Intial Orbit Determination method.Orbit
IodGauss. estimate(Frame outputFrame, AngularRaDec raDec1, AngularRaDec raDec2, AngularRaDec raDec3)
Estimate and orbit based on Gauss Intial Orbit Determination method.Orbit
IodGibbs. estimate(Frame frame, Vector3D r1, AbsoluteDate date1, Vector3D r2, AbsoluteDate date2, Vector3D r3, AbsoluteDate date3)
Give an initial orbit estimation, assuming Keplerian motion.Orbit
IodGibbs. estimate(Frame frame, Position p1, Position p2, Position p3)
Give an initial orbit estimation, assuming Keplerian motion.Orbit
IodGibbs. estimate(Frame frame, PV pv1, PV pv2, PV pv3)
Give an initial orbit estimation, assuming Keplerian motion.Orbit
IodGooding. estimate(Frame outputFrame, Vector3D O1, Vector3D O2, Vector3D O3, Vector3D lineOfSight1, AbsoluteDate dateObs1, Vector3D lineOfSight2, AbsoluteDate dateObs2, Vector3D lineOfSight3, AbsoluteDate dateObs3, double rho1init, double rho3init)
Estimate orbit from three line of sight.Orbit
IodGooding. estimate(Frame outputFrame, Vector3D O1, Vector3D O2, Vector3D O3, Vector3D lineOfSight1, AbsoluteDate dateObs1, Vector3D lineOfSight2, AbsoluteDate dateObs2, Vector3D lineOfSight3, AbsoluteDate dateObs3, double rho1init, double rho3init, int nRev, boolean direction)
Estimate orbit from three line of sight.Orbit
IodGooding. estimate(Frame outputFrame, AngularAzEl azEl1, AngularAzEl azEl2, AngularAzEl azEl3, double rho1init, double rho3init)
Estimate orbit from three angular observations.Orbit
IodGooding. estimate(Frame outputFrame, AngularAzEl azEl1, AngularAzEl azEl2, AngularAzEl azEl3, double rho1init, double rho3init, int nRev, boolean direction)
Estimate orbit from three angular observations.Orbit
IodGooding. estimate(Frame outputFrame, AngularRaDec raDec1, AngularRaDec raDec2, AngularRaDec raDec3, double rho1init, double rho3init)
Estimate orbit from three angular observations.Orbit
IodGooding. estimate(Frame outputFrame, AngularRaDec raDec1, AngularRaDec raDec2, AngularRaDec raDec3, double rho1init, double rho3init, int nRev, boolean direction)
Estimate orbit from three angular observations.Orbit
IodLambert. estimate(Frame frame, boolean posigrade, int nRev, Vector3D p1, AbsoluteDate t1, Vector3D p2, AbsoluteDate t2)
Estimate a Keplerian orbit given two position vectors and a duration.Orbit
IodLambert. estimate(Frame frame, boolean posigrade, int nRev, Position p1, Position p2)
Estimate an initial orbit from two position measurements.Orbit
IodLambert. estimate(Frame frame, boolean posigrade, int nRev, PV pv1, PV pv2)
Estimate an initial orbit from two PV measurements.Orbit
IodLaplace. estimate(Frame outputFrame, AngularAzEl azEl1, AngularAzEl azEl2, AngularAzEl azEl3)
Estimate the orbit from three angular observations at the same location.Orbit
IodLaplace. estimate(Frame outputFrame, AngularRaDec raDec1, AngularRaDec raDec2, AngularRaDec raDec3)
Estimate the orbit from three angular observations at the same location.Orbit
IodLaplace. estimate(Frame outputFrame, PVCoordinates obsPva, AbsoluteDate obsDate1, Vector3D los1, AbsoluteDate obsDate2, Vector3D los2, AbsoluteDate obsDate3, Vector3D los3)
Estimate orbit from three line of sight angles at the same location. -
Uses of Frame in org.orekit.estimation.measurements
Methods in org.orekit.estimation.measurements that return Frame Modifier and Type Method Description Frame
GroundStation. getEstimatedEarthFrame()
Get the estimated Earth frame, including the estimated linear models for pole and prime meridian.Frame
AngularRaDec. getReferenceFrame()
Get the reference frame in which the right ascension - declination angles are given.Methods in org.orekit.estimation.measurements with parameters of type Frame Modifier and Type Method Description PVCoordinates
GroundReceiverMeasurement. getGroundStationCoordinates(Frame frame)
Get the station coordinates for a given frame.Vector3D
GroundReceiverMeasurement. getGroundStationPosition(Frame frame)
Get the station position for a given frame.Vector3D
AngularAzEl. getObservedLineOfSight(Frame outputFrame)
Calculate the Line Of Sight of the given measurement.Vector3D
AngularRaDec. getObservedLineOfSight(Frame outputFrame)
Calculate the Line Of Sight of the given measurement.Transform
GroundStation. getOffsetToInertial(Frame inertial, AbsoluteDate date, boolean clockOffsetAlreadyApplied)
Get the transform between offset frame and inertial frame.FieldTransform<Gradient>
GroundStation. getOffsetToInertial(Frame inertial, AbsoluteDate clockDate, int freeParameters, Map<String,Integer> indices)
Get the transform between offset frame and inertial frame with derivatives.FieldTransform<Gradient>
GroundStation. getOffsetToInertial(Frame inertial, FieldAbsoluteDate<Gradient> offsetCompensatedDate, int freeParameters, Map<String,Integer> indices)
Get the transform between offset frame and inertial frame with derivatives.static <T extends CalculusFieldElement<T>>
TAbstractMeasurement. signalTimeOfFlight(FieldPVCoordinatesProvider<T> adjustableEmitter, FieldAbsoluteDate<T> approxEmissionDate, FieldVector3D<T> receiverPosition, FieldAbsoluteDate<T> signalArrivalDate, Frame receiverFrame)
Compute propagation delay on a link leg (typically downlink or uplink).static double
AbstractMeasurement. signalTimeOfFlight(PVCoordinatesProvider adjustableEmitter, AbsoluteDate approxEmissionDate, Vector3D receiverPosition, AbsoluteDate signalArrivalDate, Frame receiverFrame)
Compute propagation delay on a link leg (typically downlink or uplink).static <T extends CalculusFieldElement<T>>
TAbstractMeasurement. signalTimeOfFlight(TimeStampedFieldPVCoordinates<T> adjustableEmitterPV, FieldVector3D<T> receiverPosition, FieldAbsoluteDate<T> signalArrivalDate, Frame receiverFrame)
Compute propagation delay on a link leg (typically downlink or uplink).static double
AbstractMeasurement. signalTimeOfFlight(TimeStampedPVCoordinates adjustableEmitterPV, Vector3D receiverPosition, AbsoluteDate signalArrivalDate, Frame receiverFrame)
Compute propagation delay on a link leg (typically downlink or uplink).Constructors in org.orekit.estimation.measurements with parameters of type Frame Constructor Description AngularRaDec(GroundStation station, Frame referenceFrame, AbsoluteDate date, double[] angular, double[] sigma, double[] baseWeight, ObservableSatellite satellite)
Simple constructor. -
Uses of Frame in org.orekit.estimation.measurements.generation
Constructors in org.orekit.estimation.measurements.generation with parameters of type Frame Constructor Description AngularRaDecBuilder(CorrelatedRandomVectorGenerator noiseSource, GroundStation station, Frame referenceFrame, double[] sigma, double[] baseWeight, ObservableSatellite satellite)
Simple constructor. -
Uses of Frame in org.orekit.estimation.measurements.modifiers
Methods in org.orekit.estimation.measurements.modifiers with parameters of type Frame Modifier and Type Method Description static Gradient[]
AberrationModifier. fieldNaturalToProper(Gradient[] naturalRaDec, FieldTransform<Gradient> stationToInertial, Frame frame)
Natural to proper correction for aberration of light.static Gradient[]
AberrationModifier. fieldNaturalToProper(Gradient[] naturalRaDec, FieldTransform<Gradient> stationToInertial, Frame frame, DataContext context)
Natural to proper correction for aberration of light.static Gradient[]
AberrationModifier. fieldProperToNatural(Gradient[] properRaDec, FieldTransform<Gradient> stationToInertial, Frame frame)
Proper to natural correction for aberration of light.static Gradient[]
AberrationModifier. fieldProperToNatural(Gradient[] properRaDec, FieldTransform<Gradient> stationToInertial, Frame frame, DataContext context)
Proper to natural correction for aberration of light.static double[]
AberrationModifier. naturalToProper(double[] naturalRaDec, GroundStation station, AbsoluteDate date, Frame frame)
Natural to proper correction for aberration of light.static double[]
AberrationModifier. naturalToProper(double[] naturalRaDec, GroundStation station, AbsoluteDate date, Frame frame, DataContext context)
Natural to proper correction for aberration of light.static double[]
AberrationModifier. properToNatural(double[] properRaDec, GroundStation station, AbsoluteDate date, Frame frame)
Proper to natural correction for aberration of light.static double[]
AberrationModifier. properToNatural(double[] properRaDec, GroundStation station, AbsoluteDate date, Frame frame, DataContext context)
Proper to natural correction for aberration of light. -
Uses of Frame in org.orekit.files.ccsds.definitions
Subclasses of Frame in org.orekit.files.ccsds.definitions Modifier and Type Class Description class
ModifiedFrame
A reference frame created from theREF_FRAME
andCENTER_NAME
is a CCSDS OPM, OMM, or OEM file.Methods in org.orekit.files.ccsds.definitions that return Frame Modifier and Type Method Description Frame
FrameFacade. asFrame()
Get the associated frame tree node.abstract Frame
CelestialBodyFrame. getFrame(IERSConventions conventions, boolean simpleEOP, DataContext dataContext)
Get the frame corresponding to the CCSDS constant.Methods in org.orekit.files.ccsds.definitions with parameters of type Frame Modifier and Type Method Description static Transform
FrameFacade. getTransform(FrameFacade frameIn, FrameFacade frameOut, Frame inertialPivotFrame, AbsoluteDate date, PVCoordinatesProvider pv)
Get the transform betweenCCSDS frames
.static String
CenterName. guessCenter(Frame frame)
Guess the name of the center of the reference frame.static String
CelestialBodyFrame. guessFrame(Frame frame)
Guesses names from ODM Table 5-3 and Annex A.static CelestialBodyFrame
CelestialBodyFrame. map(Frame frame)
Map an Orekit frame to a CCSDS frame.static CenterName
CenterName. map(Frame frame)
Map an Orekit frame to a CCSDS center.static FrameFacade
FrameFacade. map(Frame frame)
Map an Orekit frame to a CCSDS frame facade.Constructors in org.orekit.files.ccsds.definitions with parameters of type Frame Constructor Description FrameFacade(Frame frame, CelestialBodyFrame celestialBodyFrame, OrbitRelativeFrame orbitRelativeFrame, SpacecraftBodyFrame spacecraftBodyFrame, String name)
Simple constructor.ModifiedFrame(Frame frame, CelestialBodyFrame refFrame, CelestialBody body, String centerName)
Create a CCSDS reference frame by changing the origin of an existing frame. -
Uses of Frame in org.orekit.files.ccsds.ndm.adm
Methods in org.orekit.files.ccsds.ndm.adm with parameters of type Frame Modifier and Type Method Description <T extends CalculusFieldElement<T>>
FieldAttitude<T>AttitudeEndpoints. build(Frame frame, FieldPVCoordinatesProvider<T> pvProv, TimeStampedFieldAngularCoordinates<T> rawAttitude)
Build a filtered attitude.Attitude
AttitudeEndpoints. build(Frame frame, PVCoordinatesProvider pvProv, TimeStampedAngularCoordinates rawAttitude)
Build a filtered attitude. -
Uses of Frame in org.orekit.files.ccsds.ndm.adm.acm
Methods in org.orekit.files.ccsds.ndm.adm.acm that return Frame Modifier and Type Method Description Frame
AttitudeStateHistory. getReferenceFrame()
Get the reference frame from which attitude is defined. -
Uses of Frame in org.orekit.files.ccsds.ndm.adm.aem
Methods in org.orekit.files.ccsds.ndm.adm.aem that return Frame Modifier and Type Method Description Frame
AemSegment. getReferenceFrame()
Get the reference frame from which attitude is defined. -
Uses of Frame in org.orekit.files.ccsds.ndm.adm.apm
Methods in org.orekit.files.ccsds.ndm.adm.apm with parameters of type Frame Modifier and Type Method Description Attitude
Apm. getAttitude(Frame frame, PVCoordinatesProvider pvProvider)
Get the attitude.Attitude
ApmData. getAttitude(Frame frame, PVCoordinatesProvider pvProvider)
Get the attitude. -
Uses of Frame in org.orekit.files.ccsds.ndm.cdm
Methods in org.orekit.files.ccsds.ndm.cdm that return Frame Modifier and Type Method Description Frame
CdmMetadata. getFrame()
Get the reference frame in which data are given: used for state vector and Keplerian elements data (and for the covariance reference frame if none is given). -
Uses of Frame in org.orekit.files.ccsds.ndm.odm
Methods in org.orekit.files.ccsds.ndm.odm that return Frame Modifier and Type Method Description Frame
OdmCommonMetadata. getFrame()
Get the reference frame in which data are given: used for state vector and Keplerian elements data (and for the covariance reference frame if none is given).Methods in org.orekit.files.ccsds.ndm.odm with parameters of type Frame Modifier and Type Method Description KeplerianOrbit
KeplerianElements. generateKeplerianOrbit(Frame frame)
Generate a keplerian orbit. -
Uses of Frame in org.orekit.files.ccsds.ndm.odm.ocm
Methods in org.orekit.files.ccsds.ndm.odm.ocm that return Frame Modifier and Type Method Description Frame
TrajectoryStateHistory. getFrame()
Get the reference frame for this ephemeris segment.Methods in org.orekit.files.ccsds.ndm.odm.ocm with parameters of type Frame Modifier and Type Method Description double[]
OrbitElementsType. toRawElements(TimeStampedPVCoordinates pv, Frame frame, OneAxisEllipsoid body, double mu)
Convert to raw elements array. -
Uses of Frame in org.orekit.files.ccsds.ndm.odm.oem
Methods in org.orekit.files.ccsds.ndm.odm.oem that return Frame Modifier and Type Method Description Frame
OemSegment. getFrame()
Get the reference frame for this ephemeris segment.Frame
OemSegment. getInertialFrame()
Get the inertial reference frame for this ephemeris segment. -
Uses of Frame in org.orekit.files.general
Methods in org.orekit.files.general that return Frame Modifier and Type Method Description Frame
EphemerisFile.EphemerisSegment. getFrame()
Get the reference frame for this ephemeris segment.Frame
OrekitEphemerisFile.OrekitEphemerisSegment. getFrame()
Get the reference frame for this ephemeris segment.default Frame
EphemerisFile.EphemerisSegment. getInertialFrame()
Get the inertial reference frame for this ephemeris segment.Frame
OrekitEphemerisFile.OrekitEphemerisSegment. getInertialFrame()
Get the inertial reference frame for this ephemeris segment.Frame
AttitudeEphemerisFile.AttitudeEphemerisSegment. getReferenceFrame()
Get the reference frame from which attitude is defined.Frame
OrekitAttitudeEphemerisFile.OrekitAttitudeEphemerisSegment. getReferenceFrame()
Get the reference frame from which attitude is defined.Methods in org.orekit.files.general with parameters of type Frame Modifier and Type Method Description Vector3D
EphemerisSegmentPropagator. getPosition(AbsoluteDate date, Frame frame)
TimeStampedPVCoordinates
EphemerisSegmentPropagator. getPVCoordinates(AbsoluteDate date, Frame frame)
Constructors in org.orekit.files.general with parameters of type Frame Constructor Description OrekitAttitudeEphemerisSegment(List<TimeStampedAngularCoordinates> attitudeDataLines, String interpolationMethod, int interpolationSamples, Frame referenceFrame, AngularDerivativesFilter availableDerivatives)
Constructor for OrekitAttitudeEphemerisSegment.OrekitEphemerisSegment(List<TimeStampedPVCoordinates> coordinates, Frame frame, double mu, int interpolationSamples)
constructor for OrekitEphemerisSegment. -
Uses of Frame in org.orekit.files.ilrs
Methods in org.orekit.files.ilrs that return Frame Modifier and Type Method Description Frame
CPF.CPFEphemeris. getFrame()
Get the reference frame for this ephemeris segment.Frame
CPFHeader. getRefFrame()
Get the reference frame.Methods in org.orekit.files.ilrs with parameters of type Frame Modifier and Type Method Description StreamingCpfWriter.Segment
StreamingCpfWriter. newSegment(Frame frame)
Create a writer for a new CPF ephemeris segment.void
CPFHeader. setRefFrame(Frame refFrame)
Set the reference frame. -
Uses of Frame in org.orekit.files.rinex.clock
Methods in org.orekit.files.rinex.clock that return Frame Modifier and Type Method Description Frame
RinexClock. getFrame()
Get the reference frame for the station positions.Constructor parameters in org.orekit.files.rinex.clock with type arguments of type Frame Constructor Description RinexClock(Function<? super String,? extends Frame> frameBuilder)
Constructor.RinexClockParser(Function<? super String,? extends Frame> frameBuilder)
Create a clock file parser and specify the frame builder.RinexClockParser(Function<? super String,? extends Frame> frameBuilder, TimeScales timeScales)
Constructor, build the IGS clock file parser. -
Uses of Frame in org.orekit.files.sp3
Methods in org.orekit.files.sp3 that return Frame Modifier and Type Method Description Frame
SP3Ephemeris. getFrame()
Get the reference frame.Frame
SP3Segment. getFrame()
Get the reference frame for this ephemeris segment.static Frame
SP3Parser. guessFrame(String name)
Deprecated.as of 12.1, replaced byIGSUtils.guessFrame(String)
Methods in org.orekit.files.sp3 with parameters of type Frame Modifier and Type Method Description static SP3
SP3. changeFrame(SP3 original, Frame newFrame)
Change the frame of an SP3 file.Constructors in org.orekit.files.sp3 with parameters of type Frame Constructor Description SP3(double mu, int interpolationSamples, Frame frame)
Create a new SP3 file object.SP3(SP3Header header, double mu, int interpolationSamples, Frame frame)
Create a new SP3 file object.SP3Ephemeris(String id, double mu, Frame frame, int interpolationSamples, CartesianDerivativesFilter filter)
Create an ephemeris for a single satellite.SP3Segment(double mu, Frame frame, int interpolationSamples, CartesianDerivativesFilter filter)
Simple constructor.Constructor parameters in org.orekit.files.sp3 with type arguments of type Frame Constructor Description SP3Parser(double mu, int interpolationSamples, Function<? super String,? extends Frame> frameBuilder)
Create an SP3 parser and specify the extra information needed to create aPropagator
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 aPropagator
from the ephemeris data. -
Uses of Frame in org.orekit.files.stk
Methods in org.orekit.files.stk that return Frame Modifier and Type Method Description Frame
STKEphemerisFile.STKEphemerisSegment. getFrame()
Constructors in org.orekit.files.stk with parameters of type Frame Constructor Description STKEphemerisSegment(double mu, Frame frame, int interpolationSamples, CartesianDerivativesFilter cartesianDerivativesFilter, List<TimeStampedPVCoordinates> timeStampedPVCoordinates)
Constructs aSTKEphemerisFile.STKEphemerisSegment
instance.Constructor parameters in org.orekit.files.stk with type arguments of type Frame Constructor Description STKEphemerisFileParser(String satelliteId, double mu, UTCScale utc, Map<STKEphemerisFile.STKCoordinateSystem,Frame> frameMapping)
Constructs aSTKEphemerisFileParser
instance. -
Uses of Frame in org.orekit.forces.drag
Methods in org.orekit.forces.drag with parameters of type Frame Modifier and Type Method Description protected DerivativeStructure
AbstractDragForceModel. getDSDensityWrtState(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position)
Compute density and its derivatives.protected DerivativeStructure
AbstractDragForceModel. getDSDensityWrtStateUsingFiniteDifferences(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position)
Compute density and its derivatives.protected Gradient
AbstractDragForceModel. getGradientDensityWrtState(AbsoluteDate date, Frame frame, FieldVector3D<Gradient> position)
Compute density and its derivatives.protected Gradient
AbstractDragForceModel. getGradientDensityWrtStateUsingFiniteDifferences(AbsoluteDate date, Frame frame, FieldVector3D<Gradient> position)
Compute density and its derivatives. -
Uses of Frame in org.orekit.forces.gravity
Methods in org.orekit.forces.gravity that return Frame Modifier and Type Method Description Frame
J2OnlyPerturbation. getFrame()
Getter for frame.Constructors in org.orekit.forces.gravity with parameters of type Frame Constructor Description HolmesFeatherstoneAttractionModel(Frame centralBodyFrame, NormalizedSphericalHarmonicsProvider provider)
Creates a new instance.J2OnlyPerturbation(double mu, double rEq, double constantJ2, Frame frame)
Constructor with constant J2.J2OnlyPerturbation(double mu, double rEq, TimeScalarFunction j2OverTime, Frame frame)
Constructor withTimeScalarFunction
.J2OnlyPerturbation(UnnormalizedSphericalHarmonicsProvider harmonicsProvider, Frame frame)
Constructor with spherical harmonics provider.LenseThirringRelativity(double gm, Frame bodyFrame)
Constructor.OceanTides(Frame centralBodyFrame, double ae, double mu, boolean poleTide, double step, int nbPoints, int degree, int order, IERSConventions conventions, UT1Scale ut1)
Simple constructor.OceanTides(Frame centralBodyFrame, double ae, double mu, boolean poleTide, double step, int nbPoints, int degree, int order, IERSConventions conventions, UT1Scale ut1, GravityFields gravityFields)
Simple constructor.OceanTides(Frame centralBodyFrame, double ae, double mu, int degree, int order, IERSConventions conventions, UT1Scale ut1)
Simple constructor.SolidTides(Frame centralBodyFrame, double ae, double mu, TideSystem centralTideSystem, boolean poleTide, double step, int nbPoints, IERSConventions conventions, UT1Scale ut1, CelestialBody... bodies)
Simple constructor.SolidTides(Frame centralBodyFrame, double ae, double mu, TideSystem centralTideSystem, IERSConventions conventions, UT1Scale ut1, CelestialBody... bodies)
Simple constructor. -
Uses of Frame in org.orekit.forces.inertia
Constructors in org.orekit.forces.inertia with parameters of type Frame Constructor Description InertialForces(Frame referenceInertialFrame)
Simple constructor. -
Uses of Frame in org.orekit.forces.maneuvers
Methods in org.orekit.forces.maneuvers that return Frame Modifier and Type Method Description Frame
SmallManeuverAnalyticalModel. getInertialFrame()
Get the inertial frame in which the velocity increment is defined.Constructors in org.orekit.forces.maneuvers with parameters of type Frame Constructor Description SmallManeuverAnalyticalModel(SpacecraftState state0, Frame frame, Vector3D dV, double isp)
Build a maneuver defined in user-specified frame.SmallManeuverAnalyticalModel(SpacecraftState state0, OrbitType orbitType, Frame frame, Vector3D dV, double isp)
Build a maneuver defined in user-specified frame. -
Uses of Frame in org.orekit.forces.maneuvers.propulsion
Methods in org.orekit.forces.maneuvers.propulsion with parameters of type Frame Modifier and Type Method 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 Description protected Vector3D
AbstractLightFluxModel. getOccultedBodyPosition(AbsoluteDate date, Frame frame)
Method computing the occulted body's position at a given date and frame.protected <T extends CalculusFieldElement<T>>
FieldVector3D<T>AbstractLightFluxModel. getOccultedBodyPosition(FieldAbsoluteDate<T> date, Frame frame)
Method computing the occulted body's position at a given date and frame. -
Uses of Frame in org.orekit.frames
Subclasses of Frame in org.orekit.frames Modifier and Type Class Description class
CR3BPRotatingFrame
Class creating the rotating frame centered on the barycenter of the CR3BP System.class
FactoryManagedFrame
Base class for the predefined frames that are managed byFrames
.class
L1Frame
Class to create a L1 centered frame withL1TransformProvider
.class
L2Frame
Class to create a L2 centered frame withL2TransformProvider
.class
LocalOrbitalFrame
Class for frames moving with an orbiting satellite.class
TopocentricFrame
Topocentric frame.class
TwoBodiesBaryFrame
Class creating the inertial barycenter frame from two bodies.class
UpdatableFrame
Frame whose transform from its parent can be updated.class
VersionedITRF
Specific version of International Terrestrial Reference Frame.Methods in org.orekit.frames that return Frame Modifier and Type Method Description Frame
AbstractFrames. buildUncachedITRF(UT1Scale ut1)
Frame
Frames. buildUncachedITRF(UT1Scale ut1)
Build an uncached International Terrestrial Reference Frame with specificEOP history
.static Frame
FramesFactory. buildUncachedITRF(EOPHistory eopHistory, UTCScale utc)
Build an uncached International Terrestrial Reference Frame with specificEOP history
.Frame
HelmertTransformation.Predefined. createTransformedITRF(Frame parent, String name)
Create an ITRF frame by transforming another ITRF frame.Frame
HelmertTransformation.Predefined. createTransformedITRF(Frame parent, String name, TimeScale tt)
Create an ITRF frame by transforming another ITRF frame.Frame
Frame. getAncestor(int n)
Get the nth ancestor of the frame.Frame
AbstractFrames. getEcliptic(IERSConventions conventions)
Frame
Frames. getEcliptic(IERSConventions conventions)
Get the ecliptic frame.static Frame
FramesFactory. getEcliptic(IERSConventions conventions)
Get the ecliptic frame.Frame
AbstractFrames. getFrame(Predefined factoryKey)
Frame
Frames. getFrame(Predefined factoryKey)
Get one of the predefined frames.static Frame
FramesFactory. getFrame(Predefined factoryKey)
Get one of the predefined frames.Frame
OrphanFrame. getFrame()
Get the associatedframe
.Frame
Frame. getFrozenFrame(Frame reference, AbsoluteDate freezingDate, String frozenName)
Get a new version of the instance, frozen with respect to a reference frame.Frame
AbstractFrames. getGCRF()
Frame
Frames. getGCRF()
Get the unique GCRF frame.static Frame
FramesFactory. getGCRF()
Get the unique GCRF frame.Frame
AbstractFrames. getICRF()
Frame
Frames. getICRF()
Get the unique ICRF frame.static Frame
FramesFactory. getICRF()
Get the unique ICRF frame.Frame
LocalMagneticFieldFrame. getInertialFrame()
Get interlai frame.Frame
Frame. getParent()
Get the parent frame.static Frame
Frame. getRoot()
Get the unique root frame.Methods in org.orekit.frames with parameters of type Frame Modifier and Type Method Description void
OrphanFrame. attachTo(Frame parent, Transform transform, boolean isPseudoInertial)
Attach the instance (and all its children down to leafs) to the main tree.void
OrphanFrame. attachTo(Frame parent, TransformProvider transformProvider, boolean isPseudoInertial)
Attach the instance (and all its children down to leafs) to the main tree.Frame
HelmertTransformation.Predefined. createTransformedITRF(Frame parent, String name)
Create an ITRF frame by transforming another ITRF frame.Frame
HelmertTransformation.Predefined. createTransformedITRF(Frame parent, String name, TimeScale tt)
Create an ITRF frame by transforming another ITRF frame.static EOPHistory
FramesFactory. findEOP(Frame start)
Retrieve EOP from a frame hierarchy.<T extends CalculusFieldElement<T>>
TTopocentricFrame. 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>>
TTopocentricFrame. getElevation(FieldVector3D<T> extPoint, Frame frame, FieldAbsoluteDate<T> date)
Get the elevation of a point with regards to the local point.double
TopocentricFrame. getElevation(Vector3D extPoint, Frame frame, AbsoluteDate date)
Get the elevation of a point with regards to the local point.Frame
Frame. getFrozenFrame(Frame reference, AbsoluteDate freezingDate, String frozenName)
Get a new version of the instance, frozen with respect to a reference frame.KinematicTransform
Frame. getKinematicTransformTo(Frame destination, AbsoluteDate date)
Get the kinematic portion of the transform from the instance to another frame.<T extends CalculusFieldElement<T>>
FieldKinematicTransform<T>Frame. getKinematicTransformTo(Frame destination, FieldAbsoluteDate<T> date)
Get the kinematic portion of the transform from the instance to another frame.static Transform
FramesFactory. getNonInterpolatingTransform(Frame from, Frame to, AbsoluteDate date)
Get the transform between two frames, suppressing all interpolation.static <T extends CalculusFieldElement<T>>
FieldTransform<T>FramesFactory. getNonInterpolatingTransform(Frame from, Frame to, FieldAbsoluteDate<T> date)
Get the transform between two frames, suppressing all interpolation.Vector3D
TopocentricFrame. getPosition(AbsoluteDate date, Frame frame)
Get the position of the body in the selected frame.TimeStampedPVCoordinates
TopocentricFrame. getPVCoordinates(AbsoluteDate date, Frame frame)
Get thePVCoordinates
of the topocentric frame origin in the selected frame.<T extends CalculusFieldElement<T>>
TTopocentricFrame. 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>>
TTopocentricFrame. getRangeRate(FieldPVCoordinates<T> extPV, Frame frame, FieldAbsoluteDate<T> date)
Get the range rate of a point with regards to the topocentric frame center point.double
TopocentricFrame. getRangeRate(PVCoordinates extPV, Frame frame, AbsoluteDate date)
Get the range rate of a point with regards to the topocentric frame center point.StaticTransform
Frame. getStaticTransformTo(Frame destination, AbsoluteDate date)
Get the static portion of the transform from the instance to another frame.<T extends CalculusFieldElement<T>>
FieldStaticTransform<T>Frame. getStaticTransformTo(Frame destination, FieldAbsoluteDate<T> date)
Get the static portion of the transform from the instance to another frame.<T extends CalculusFieldElement<T>>
FieldTrackingCoordinates<T>TopocentricFrame. getTrackingCoordinates(FieldVector3D<T> extPoint, Frame frame, FieldAbsoluteDate<T> date)
Get the tracking coordinates of a point with regards to the local point.TrackingCoordinates
TopocentricFrame. getTrackingCoordinates(Vector3D extPoint, Frame frame, AbsoluteDate date)
Get the tracking coordinates of a point with regards to the local point.Transform
Frame. getTransformTo(Frame destination, AbsoluteDate date)
Get the transform from the instance to another frame.<T extends CalculusFieldElement<T>>
FieldTransform<T>Frame. getTransformTo(Frame destination, FieldAbsoluteDate<T> date)
Get the transform from the instance to another frame.boolean
Frame. isChildOf(Frame potentialAncestor)
Determine if a Frame is a child of another one.void
UpdatableFrame. updateTransform(Frame f1, Frame f2, Transform f1Tof2, AbsoluteDate date)
Update the transform from parent frame implicitly according to two other frames.Method parameters in org.orekit.frames with type arguments of type Frame Modifier and Type Method Description static Frames
Frames. of(TimeScales timeScales, Supplier<Frame> icrfSupplier)
Create a set of frames from the given data.Constructors in org.orekit.frames with parameters of type Frame Constructor Description FactoryManagedFrame(Frame parent, TransformProvider transformProvider, boolean pseudoInertial, Predefined factoryKey)
Simple constructor.Frame(Frame parent, TransformProvider transformProvider, String name)
Build a non-inertial frame from its transform with respect to its parent.Frame(Frame parent, TransformProvider transformProvider, String name, boolean pseudoInertial)
Build a frame from its transform with respect to its parent.Frame(Frame parent, Transform transform, String name)
Build a non-inertial frame from its transform with respect to its parent.Frame(Frame parent, Transform transform, String name, boolean pseudoInertial)
Build a frame from its transform with respect to its parent.LocalMagneticFieldFrame(Frame inertialFrame, GeoMagneticField magneticField, Frame bodyFrame)
Constructor with default definition of the local orbital frame: x: Magnetic field y: Completes orthonormal frame z: Cross product of the magnetic field with the orbital momentum .LocalMagneticFieldFrame(Frame inertialFrame, GeoMagneticField magneticField, LocalMagneticFieldFrame.LOFBuilderVector lofBuilderVector, Frame bodyFrame)
Constructor with custom definition of the local orbital frame: x: Magnetic field y: Completes orthonormal frame z: Cross product of the magnetic field with chosenvector
For near-polar orbits, it is suggested to use theorbital momentum
to define the local orbital frame.LocalOrbitalFrame(Frame parent, LOF lof, PVCoordinatesProvider provider, String name)
Build a new instance.UpdatableFrame(Frame parent, Transform transform, String name)
Build a non-inertial frame from its transform with respect to its parent.UpdatableFrame(Frame parent, Transform transform, String name, boolean pseudoInertial)
Build a frame from its transform with respect to its parent.Constructor parameters in org.orekit.frames with type arguments of type Frame Constructor Description AbstractFrames(TimeScales timeScales, Supplier<Frame> icrfSupplier)
Simple constructor. -
Uses of Frame in org.orekit.gnss
Methods in org.orekit.gnss that return Frame Modifier and Type Method Description static Frame
IGSUtils. guessFrame(String name)
static Frame
IGSUtils. guessFrame(Frames frames, String name)
Methods in org.orekit.gnss with parameters of type Frame Modifier and Type Method Description static String
IGSUtils. frameName(Frame frame)
Guess a frame name. -
Uses of Frame in org.orekit.gnss.antenna
Methods in org.orekit.gnss.antenna with parameters of type Frame Modifier and Type Method Description abstract GNSSAttitudeProvider
SatelliteType. buildAttitudeProvider(AbsoluteDate validityStart, AbsoluteDate validityEnd, 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 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.models.earth
Methods in org.orekit.models.earth that return Frame Modifier and Type Method Description Frame
Geoid. getBodyFrame()
Methods in org.orekit.models.earth with parameters of type Frame Modifier and Type Method Description static ReferenceEllipsoid
ReferenceEllipsoid. getGrs80(Frame bodyFrame)
Get the GRS80 ellipsoid, attached to the given body frame.static ReferenceEllipsoid
ReferenceEllipsoid. getIers2003(Frame bodyFrame)
Get the IERS2003 ellipsoid, attached to the given body frame.static ReferenceEllipsoid
ReferenceEllipsoid. getIers2010(Frame bodyFrame)
Get the IERS2010 ellipsoid, attached to the given body frame.static ReferenceEllipsoid
ReferenceEllipsoid. getIers96(Frame bodyFrame)
Get the IERS96 ellipsoid, attached to the given body frame.<T extends CalculusFieldElement<T>>
FieldGeodeticPoint<T>Geoid. getIntersectionPoint(FieldLine<T> lineInFrame, FieldVector3D<T> closeInFrame, Frame frame, FieldAbsoluteDate<T> date)
Get the intersection point of a line with the surface of the body.GeodeticPoint
Geoid. getIntersectionPoint(Line lineInFrame, Vector3D closeInFrame, Frame frame, AbsoluteDate date)
Get the intersection point of a line with the surface of the body.static ReferenceEllipsoid
ReferenceEllipsoid. getWgs84(Frame bodyFrame)
Get the WGS84 ellipsoid, attached to the given body frame.Vector3D
Geoid. projectToGround(Vector3D point, AbsoluteDate date, Frame frame)
TimeStampedPVCoordinates
Geoid. projectToGround(TimeStampedPVCoordinates pv, Frame frame)
<T extends CalculusFieldElement<T>>
FieldGeodeticPoint<T>Geoid. transform(FieldVector3D<T> point, Frame frame, FieldAbsoluteDate<T> date)
Transform a Cartesian point to a surface-relative point.GeodeticPoint
Geoid. transform(Vector3D point, Frame frame, AbsoluteDate date)
Transform a Cartesian point to a surface-relative point.Constructors in org.orekit.models.earth with parameters of type Frame Constructor Description ReferenceEllipsoid(double ae, double f, Frame bodyFrame, double GM, double spin)
Creates a new geodetic Reference Ellipsoid from four defining parameters. -
Uses of Frame in org.orekit.models.earth.atmosphere
Methods in org.orekit.models.earth.atmosphere that return Frame Modifier and Type Method Description Frame
Atmosphere. getFrame()
Get the frame of the central body.Frame
DTM2000. getFrame()
Get the frame of the central body.Frame
HarrisPriester. getFrame()
Get the frame of the central body.Frame
JB2008. getFrame()
Get the frame of the central body.Frame
NRLMSISE00. getFrame()
Get the frame of the central body.Frame
SimpleExponentialAtmosphere. getFrame()
Get the frame of the central body.Methods in org.orekit.models.earth.atmosphere with parameters of type Frame Modifier and Type Method Description double
Atmosphere. getDensity(AbsoluteDate date, Vector3D position, Frame frame)
Get the local density.<T extends CalculusFieldElement<T>>
TAtmosphere. getDensity(FieldAbsoluteDate<T> date, FieldVector3D<T> position, Frame frame)
Get the local density.double
DTM2000. getDensity(AbsoluteDate date, Vector3D position, Frame frame)
Get the local density.<T extends CalculusFieldElement<T>>
TDTM2000. getDensity(FieldAbsoluteDate<T> date, FieldVector3D<T> position, Frame frame)
Get the local density.double
HarrisPriester. getDensity(AbsoluteDate date, Vector3D position, Frame frame)
Get the local density at some position.<T extends CalculusFieldElement<T>>
THarrisPriester. getDensity(FieldAbsoluteDate<T> date, FieldVector3D<T> position, Frame frame)
Get the local density at some position.double
JB2008. getDensity(AbsoluteDate date, Vector3D position, Frame frame)
Get the local density.<T extends CalculusFieldElement<T>>
TJB2008. getDensity(FieldAbsoluteDate<T> date, FieldVector3D<T> position, Frame frame)
Get the local density.double
NRLMSISE00. getDensity(AbsoluteDate date, Vector3D position, Frame frame)
Get the local density.<T extends CalculusFieldElement<T>>
TNRLMSISE00. getDensity(FieldAbsoluteDate<T> date, FieldVector3D<T> position, Frame frame)
Get the local density.double
SimpleExponentialAtmosphere. getDensity(AbsoluteDate date, Vector3D position, Frame frame)
Get the local density.<T extends CalculusFieldElement<T>>
TSimpleExponentialAtmosphere. 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 CalculusFieldElement<T>>
FieldVector3D<T>Atmosphere. getVelocity(FieldAbsoluteDate<T> date, FieldVector3D<T> position, Frame frame)
Get the inertial velocity of atmosphere molecules. -
Uses of Frame in org.orekit.models.earth.displacement
Methods in org.orekit.models.earth.displacement with parameters of type Frame Modifier and Type Method Description Vector3D
OceanLoading. displacement(BodiesElements elements, Frame earthFrame, Vector3D referencePoint)
Compute displacement of a ground reference point.Vector3D
PostSeismicDeformation. displacement(BodiesElements elements, Frame earthFrame, Vector3D referencePoint)
Compute displacement of a ground reference point.Vector3D
StationDisplacement. displacement(BodiesElements elements, Frame earthFrame, Vector3D referencePoint)
Compute displacement of a ground reference point.Vector3D
TectonicsDisplacement. displacement(BodiesElements elements, Frame earthFrame, Vector3D referencePoint)
Compute displacement of a ground reference point.Vector3D
TidalDisplacement. displacement(BodiesElements elements, Frame earthFrame, Vector3D referencePoint)
Compute displacement of a ground reference point. -
Uses of Frame in org.orekit.models.earth.weather
Constructors in org.orekit.models.earth.weather with parameters of type Frame Constructor Description GlobalPressureTemperatureModel(double latitude, double longitude, Frame bodyFrame)
Deprecated.Build a new instance.GlobalPressureTemperatureModel(double latitude, double longitude, Frame bodyFrame, DataContext dataContext)
Deprecated.Build a new instance. -
Uses of Frame in org.orekit.orbits
Methods in org.orekit.orbits that return Frame Modifier and Type Method Description Frame
FieldOrbit. getFrame()
Get the frame in which the orbital parameters are defined.Frame
Orbit. getFrame()
Get the frame in which the orbital parameters are defined.Frame
AbstractFieldOrbitInterpolator. getOutputInertialFrame()
Get output inertial frame.Frame
AbstractOrbitInterpolator. getOutputInertialFrame()
Get output inertial frame.Methods in org.orekit.orbits with parameters of type Frame Modifier and Type Method Description FieldVector3D<T>
FieldOrbit. getPosition(Frame outputFrame)
Get the position in a specified frame.FieldVector3D<T>
FieldOrbit. getPosition(FieldAbsoluteDate<T> otherDate, Frame otherFrame)
Get the position of the body in the selected frame.Vector3D
Orbit. getPosition(Frame outputFrame)
Get the position in a specified frame.Vector3D
Orbit. getPosition(AbsoluteDate otherDate, Frame otherFrame)
Get the position of the body in the selected frame.TimeStampedFieldPVCoordinates<T>
FieldOrbit. getPVCoordinates(Frame outputFrame)
Get theTimeStampedPVCoordinates
in a specified frame.TimeStampedFieldPVCoordinates<T>
FieldOrbit. getPVCoordinates(FieldAbsoluteDate<T> otherDate, Frame otherFrame)
Get theFieldPVCoordinates
of the body in the selected frame.TimeStampedPVCoordinates
Orbit. getPVCoordinates(Frame outputFrame)
Get theTimeStampedPVCoordinates
in a specified frame.TimeStampedPVCoordinates
Orbit. getPVCoordinates(AbsoluteDate otherDate, Frame otherFrame)
Get thePVCoordinates
of the body in the selected frame.abstract Orbit
OrbitType. mapArrayToOrbit(double[] array, double[] arrayDot, PositionAngleType type, AbsoluteDate date, double mu, Frame frame)
Convert state array to orbital parameters.abstract <T extends CalculusFieldElement<T>>
FieldOrbit<T>OrbitType. mapArrayToOrbit(T[] array, T[] arrayDot, PositionAngleType type, FieldAbsoluteDate<T> date, T mu, Frame frame)
Convert state array to orbital parameters.Constructors in org.orekit.orbits with parameters of type Frame Constructor Description AbstractFieldOrbitInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputInertialFrame)
Constructor.AbstractOrbitInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputInertialFrame)
Constructor.CartesianOrbit(PVCoordinates pvaCoordinates, Frame frame, AbsoluteDate date, double mu)
Constructor from Cartesian parameters.CartesianOrbit(TimeStampedPVCoordinates pvaCoordinates, Frame frame, double mu)
Constructor from Cartesian parameters.CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, double aDot, double exDot, double eyDot, double iDot, double raanDot, double alphaDot, PositionAngleType type, Frame frame, AbsoluteDate date, double mu)
Creates a new instance with derivatives and with cached position angle same as value inputted.CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, double aDot, double exDot, double eyDot, double iDot, double raanDot, double alphaDot, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, AbsoluteDate date, double mu)
Creates a new instance.CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, PositionAngleType type, Frame frame, AbsoluteDate date, double mu)
Creates a new instance without derivatives and with cached position angle same as value inputted.CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, AbsoluteDate date, double mu)
Creates a new instance.CircularOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu)
Constructor from Cartesian parameters.CircularOrbit(TimeStampedPVCoordinates pvCoordinates, Frame frame, double mu)
Constructor from Cartesian parameters.EquinoctialOrbit(double a, double ex, double ey, double hx, double hy, double l, double aDot, double exDot, double eyDot, double hxDot, double hyDot, double lDot, PositionAngleType type, Frame frame, AbsoluteDate date, double mu)
Creates a new instance with derivatives and with cached position angle same as value inputted.EquinoctialOrbit(double a, double ex, double ey, double hx, double hy, double l, double aDot, double exDot, double eyDot, double hxDot, double hyDot, double lDot, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, AbsoluteDate date, double mu)
Creates a new instance.EquinoctialOrbit(double a, double ex, double ey, double hx, double hy, double l, PositionAngleType type, Frame frame, AbsoluteDate date, double mu)
Creates a new instance without derivatives and with cached position angle same as value inputted.EquinoctialOrbit(double a, double ex, double ey, double hx, double hy, double l, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, AbsoluteDate date, double mu)
Creates a new instance.EquinoctialOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu)
Constructor from Cartesian parameters.EquinoctialOrbit(TimeStampedPVCoordinates pvCoordinates, Frame frame, double mu)
Constructor from Cartesian parameters.FieldCartesianOrbit(FieldPVCoordinates<T> pvaCoordinates, Frame frame, FieldAbsoluteDate<T> date, T mu)
Constructor from Cartesian parameters.FieldCartesianOrbit(TimeStampedFieldPVCoordinates<T> pvaCoordinates, Frame frame, T mu)
Constructor from Cartesian parameters.FieldCircularOrbit(FieldPVCoordinates<T> PVCoordinates, Frame frame, FieldAbsoluteDate<T> date, T mu)
Constructor from Cartesian parameters.FieldCircularOrbit(TimeStampedFieldPVCoordinates<T> pvCoordinates, Frame frame, T mu)
Constructor from Cartesian parameters.FieldCircularOrbit(T a, T ex, T ey, T i, T raan, T alpha, PositionAngleType type, Frame frame, FieldAbsoluteDate<T> date, T mu)
Creates a new instance without derivatives and with cached position angle same as value inputted.FieldCircularOrbit(T a, T ex, T ey, T i, T raan, T alpha, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, FieldAbsoluteDate<T> date, T mu)
Creates a new instance.FieldCircularOrbit(T a, T ex, T ey, T i, T raan, T alpha, T aDot, T exDot, T eyDot, T iDot, T raanDot, T alphaDot, PositionAngleType type, Frame frame, FieldAbsoluteDate<T> date, T mu)
Creates a new instance.FieldCircularOrbit(T a, T ex, T ey, T i, T raan, T alpha, T aDot, T exDot, T eyDot, T iDot, T raanDot, T alphaDot, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, FieldAbsoluteDate<T> date, T mu)
Creates a new instance.FieldEquinoctialOrbit(FieldPVCoordinates<T> pvCoordinates, Frame frame, FieldAbsoluteDate<T> date, T mu)
Constructor from Cartesian parameters.FieldEquinoctialOrbit(TimeStampedFieldPVCoordinates<T> pvCoordinates, Frame frame, T mu)
Constructor from Cartesian parameters.FieldEquinoctialOrbit(T a, T ex, T ey, T hx, T hy, T l, PositionAngleType type, Frame frame, FieldAbsoluteDate<T> date, T mu)
Creates a new instance.FieldEquinoctialOrbit(T a, T ex, T ey, T hx, T hy, T l, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, FieldAbsoluteDate<T> date, T mu)
Creates a new instance.FieldEquinoctialOrbit(T a, T ex, T ey, T hx, T hy, T l, T aDot, T exDot, T eyDot, T hxDot, T hyDot, T lDot, PositionAngleType type, Frame frame, FieldAbsoluteDate<T> date, T mu)
Creates a new instance.FieldEquinoctialOrbit(T a, T ex, T ey, T hx, T hy, T l, T aDot, T exDot, T eyDot, T hxDot, T hyDot, T lDot, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, FieldAbsoluteDate<T> date, T mu)
Creates a new instance.FieldKeplerianOrbit(FieldPVCoordinates<T> FieldPVCoordinates, Frame frame, FieldAbsoluteDate<T> date, T mu)
Constructor from Cartesian parameters.FieldKeplerianOrbit(TimeStampedFieldPVCoordinates<T> pvCoordinates, Frame frame, T mu)
Constructor from Cartesian parameters.FieldKeplerianOrbit(T a, T e, T i, T pa, T raan, T anomaly, PositionAngleType type, Frame frame, FieldAbsoluteDate<T> date, T mu)
Creates a new instance.FieldKeplerianOrbit(T a, T e, T i, T pa, T raan, T anomaly, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, FieldAbsoluteDate<T> date, T mu)
Creates a new instance.FieldKeplerianOrbit(T a, T e, T i, T pa, T raan, T anomaly, T aDot, T eDot, T iDot, T paDot, T raanDot, T anomalyDot, PositionAngleType type, Frame frame, FieldAbsoluteDate<T> date, T mu)
Creates a new instance.FieldKeplerianOrbit(T a, T e, T i, T pa, T raan, T anomaly, T aDot, T eDot, T iDot, T paDot, T raanDot, T anomalyDot, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, FieldAbsoluteDate<T> date, T mu)
Creates a new instance.FieldOrbit(Frame frame, FieldAbsoluteDate<T> date, T mu)
Default constructor.FieldOrbit(TimeStampedFieldPVCoordinates<T> fieldPVCoordinates, Frame frame, T mu)
Set the orbit from Cartesian parameters.FieldOrbitBlender(SmoothStepFactory.FieldSmoothStepFunction<KK> blendingFunction, FieldAbstractAnalyticalPropagator<KK> analyticalPropagator, Frame outputInertialFrame)
Default constructor.FieldOrbitHermiteInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputInertialFrame, CartesianDerivativesFilter pvaFilter)
Constructor.FieldOrbitHermiteInterpolator(int interpolationPoints, Frame outputInertialFrame)
Constructor with : Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC
s) Use of position and two time derivatives during interpolation As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).FieldOrbitHermiteInterpolator(int interpolationPoints, Frame outputInertialFrame, CartesianDerivativesFilter pvaFilter)
Constructor with default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC
s).FieldOrbitHermiteInterpolator(Frame outputInertialFrame)
Constructor with : Default number of interpolation points ofDEFAULT_INTERPOLATION_POINTS
Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC
s) Use of position and two time derivatives during interpolation As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).KeplerianOrbit(double a, double e, double i, double pa, double raan, double anomaly, double aDot, double eDot, double iDot, double paDot, double raanDot, double anomalyDot, PositionAngleType type, Frame frame, AbsoluteDate date, double mu)
Creates a new instance with cached position angle same as value inputted.KeplerianOrbit(double a, double e, double i, double pa, double raan, double anomaly, double aDot, double eDot, double iDot, double paDot, double raanDot, double anomalyDot, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, AbsoluteDate date, double mu)
Creates a new instance.KeplerianOrbit(double a, double e, double i, double pa, double raan, double anomaly, PositionAngleType type, Frame frame, AbsoluteDate date, double mu)
Creates a new instance without derivatives and with cached position angle same as value inputted.KeplerianOrbit(double a, double e, double i, double pa, double raan, double anomaly, PositionAngleType type, PositionAngleType cachedPositionAngleType, Frame frame, AbsoluteDate date, double mu)
Creates a new instance.KeplerianOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu)
Constructor from Cartesian parameters.KeplerianOrbit(TimeStampedPVCoordinates pvCoordinates, Frame frame, double mu)
Constructor from Cartesian parameters.Orbit(Frame frame, AbsoluteDate date, double mu)
Default constructor.Orbit(TimeStampedPVCoordinates pvCoordinates, Frame frame, double mu)
Set the orbit from Cartesian parameters.OrbitBlender(SmoothStepFactory.SmoothStepFunction blendingFunction, Propagator blendingPropagator, Frame outputInertialFrame)
Default constructor.OrbitHermiteInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputInertialFrame, CartesianDerivativesFilter pvaFilter)
Constructor.OrbitHermiteInterpolator(int interpolationPoints, Frame outputInertialFrame)
Constructor with : Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC
s) Use of position and two time derivatives during interpolation As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).OrbitHermiteInterpolator(int interpolationPoints, Frame outputInertialFrame, CartesianDerivativesFilter pvaFilter)
Constructor with default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC
s).OrbitHermiteInterpolator(Frame outputInertialFrame)
Constructor with : Default number of interpolation points ofDEFAULT_INTERPOLATION_POINTS
Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC
s) Use of position and two time derivatives during interpolation As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing). -
Uses of Frame in org.orekit.propagation
Methods in org.orekit.propagation that return Frame Modifier and Type Method Description Frame
AbstractPropagator. getFrame()
Get the frame in which the orbit is propagated.Frame
FieldAbstractPropagator. getFrame()
Get the frame in which the orbit is propagated.Frame
FieldPropagator. getFrame()
Get the frame in which the orbit is propagated.Frame
FieldSpacecraftState. getFrame()
Get the defining frame.Frame
FieldStateCovariance. getFrame()
Get the covariance frame.Frame
Propagator. getFrame()
Get the frame in which the orbit is propagated.Frame
SpacecraftState. getFrame()
Get the defining frame.Frame
StateCovariance. getFrame()
Get the covariance frame.Frame
AbstractStateCovarianceInterpolator. getOutFrame()
Get output frame.Frame
FieldSpacecraftStateInterpolator. getOutputFrame()
Get output frame.Frame
SpacecraftStateInterpolator. getOutputFrame()
Get output frame.Methods in org.orekit.propagation with parameters of type Frame Modifier and Type Method Description FieldStateCovariance<T>
FieldStateCovariance. changeCovarianceFrame(FieldOrbit<T> orbit, Frame frameOut)
Get the covariance in the output frame.StateCovariance
StateCovariance. changeCovarianceFrame(Orbit orbit, Frame frameOut)
Get the covariance in the output frame.static void
StateCovariance. checkFrameAndOrbitTypeConsistency(Frame covarianceFrame, OrbitType inputType)
Check constructor's inputs consistency.default FieldVector3D<T>
FieldPropagator. getPosition(FieldAbsoluteDate<T> date, Frame frame)
Get the position of the body in the selected frame.FieldVector3D<T>
FieldSpacecraftState. getPosition(Frame outputFrame)
Get the position in given output frame.default Vector3D
Propagator. getPosition(AbsoluteDate date, Frame frame)
Get the position of the body in the selected frame.Vector3D
SpacecraftState. getPosition(Frame outputFrame)
Get the position in given output frame.default TimeStampedFieldPVCoordinates<T>
FieldPropagator. getPVCoordinates(FieldAbsoluteDate<T> date, Frame frame)
Get theFieldPVCoordinates
of the body in the selected frame.TimeStampedFieldPVCoordinates<T>
FieldSpacecraftState. getPVCoordinates(Frame outputFrame)
Get theTimeStampedFieldPVCoordinates
in given output frame.default TimeStampedPVCoordinates
Propagator. getPVCoordinates(AbsoluteDate date, Frame frame)
Get thePVCoordinates
of the body in the selected frame.TimeStampedPVCoordinates
SpacecraftState. getPVCoordinates(Frame outputFrame)
Get theTimeStampedPVCoordinates
in given output frame.StateCovariance
StateCovarianceMatrixProvider. getStateCovariance(SpacecraftState state, Frame frame)
Get the state covariance expressed in a given frame.Constructors in org.orekit.propagation with parameters of type Frame Constructor Description AbstractStateCovarianceInterpolator(int interpolationPoints, double extrapolationThreshold, TimeInterpolator<Orbit> orbitInterpolator, Frame outFrame, OrbitType outOrbitType, PositionAngleType outPositionAngleType)
Constructor.FieldSpacecraftStateInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputFrame)
Constructor to create a customizable Hermite interpolator for every spacecraft state field.FieldSpacecraftStateInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputFrame, Frame attitudeReferenceFrame)
Constructor to create a customizable Hermite interpolator for every spacecraft state field.FieldSpacecraftStateInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputFrame, Frame attitudeReferenceFrame, CartesianDerivativesFilter pvaFilter, AngularDerivativesFilter angularFilter)
Constructor.FieldSpacecraftStateInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputFrame, FieldTimeInterpolator<FieldOrbit<KK>,KK> orbitInterpolator, FieldTimeInterpolator<FieldAbsolutePVCoordinates<KK>,KK> absPVAInterpolator, FieldTimeInterpolator<TimeStampedField<KK>,KK> massInterpolator, FieldTimeInterpolator<FieldAttitude<KK>,KK> attitudeInterpolator, FieldTimeInterpolator<TimeStampedField<KK>,KK> additionalStateInterpolator)
Constructor.FieldSpacecraftStateInterpolator(int interpolationPoints, Frame outputFrame)
Constructor to create a customizable Hermite interpolator for every spacecraft state field.FieldSpacecraftStateInterpolator(int interpolationPoints, Frame outputFrame, Frame attitudeReferenceFrame)
Constructor to create a customizable Hermite interpolator for every spacecraft state field.FieldSpacecraftStateInterpolator(Frame outputFrame)
Simplest constructor to create a default Hermite interpolator for every spacecraft state field.FieldSpacecraftStateInterpolator(Frame outputFrame, FieldTimeInterpolator<FieldOrbit<KK>,KK> orbitInterpolator, FieldTimeInterpolator<FieldAbsolutePVCoordinates<KK>,KK> absPVAInterpolator, FieldTimeInterpolator<TimeStampedField<KK>,KK> massInterpolator, FieldTimeInterpolator<FieldAttitude<KK>,KK> attitudeInterpolator, FieldTimeInterpolator<TimeStampedField<KK>,KK> additionalStateInterpolator)
Deprecated.using this constructor may throw an exception if any given interpolator does not useAbstractFieldTimeInterpolator.DEFAULT_INTERPOLATION_POINTS
andAbstractFieldTimeInterpolator.DEFAULT_EXTRAPOLATION_THRESHOLD_SEC
.FieldStateCovariance(FieldMatrix<T> orbitalCovariance, FieldAbsoluteDate<T> epoch, Frame covarianceFrame, OrbitType orbitType, PositionAngleType angleType)
Constructor.SpacecraftStateInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputFrame)
Constructor to create a customizable Hermite interpolator for every spacecraft state field.SpacecraftStateInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputFrame, Frame attitudeReferenceFrame)
Constructor to create a customizable Hermite interpolator for every spacecraft state field.SpacecraftStateInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputFrame, Frame attitudeReferenceFrame, CartesianDerivativesFilter pvaFilter, AngularDerivativesFilter angularFilter)
Constructor to create a customizable Hermite interpolator for every spacecraft state field.SpacecraftStateInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputFrame, TimeInterpolator<Orbit> orbitInterpolator, TimeInterpolator<AbsolutePVCoordinates> absPVAInterpolator, TimeInterpolator<TimeStampedDouble> massInterpolator, TimeInterpolator<Attitude> attitudeInterpolator, TimeInterpolator<TimeStampedDouble> additionalStateInterpolator)
Constructor.SpacecraftStateInterpolator(int interpolationPoints, Frame outputFrame)
Constructor to create a customizable Hermite interpolator for every spacecraft state field.SpacecraftStateInterpolator(int interpolationPoints, Frame outputFrame, Frame attitudeReferenceFrame)
Constructor to create a customizable Hermite interpolator for every spacecraft state field.SpacecraftStateInterpolator(Frame outputFrame)
Simplest constructor to create a default Hermite interpolator for every spacecraft state field.SpacecraftStateInterpolator(Frame outputFrame, TimeInterpolator<Orbit> orbitInterpolator, TimeInterpolator<AbsolutePVCoordinates> absPVAInterpolator, TimeInterpolator<TimeStampedDouble> massInterpolator, TimeInterpolator<Attitude> attitudeInterpolator, TimeInterpolator<TimeStampedDouble> additionalStateInterpolator)
Deprecated.using this constructor may throw an exception if any given interpolator does not useAbstractTimeInterpolator.DEFAULT_INTERPOLATION_POINTS
andAbstractTimeInterpolator.DEFAULT_EXTRAPOLATION_THRESHOLD_SEC
.StateCovariance(RealMatrix orbitalCovariance, AbsoluteDate epoch, Frame covarianceFrame, OrbitType orbitType, PositionAngleType angleType)
Constructor.StateCovarianceBlender(SmoothStepFactory.SmoothStepFunction blendingFunction, TimeInterpolator<Orbit> orbitInterpolator, Frame outFrame, OrbitType outOrbitType, PositionAngleType outPositionAngleType)
Constructor.StateCovarianceKeplerianHermiteInterpolator(int interpolationPoints, double extrapolationThreshold, TimeInterpolator<Orbit> orbitInterpolator, CartesianDerivativesFilter filter, Frame outFrame, OrbitType outOrbitType, PositionAngleType outPositionAngleType)
Constructor using an output frame.StateCovarianceKeplerianHermiteInterpolator(int interpolationPoints, TimeInterpolator<Orbit> orbitInterpolator, Frame outFrame, OrbitType outOrbitType, PositionAngleType outPositionAngleType)
Constructor using an output frame and : Default number of interpolation points ofDEFAULT_INTERPOLATION_POINTS
Use of position and two time derivatives during interpolation As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).StateCovarianceKeplerianHermiteInterpolator(int interpolationPoints, TimeInterpolator<Orbit> orbitInterpolator, CartesianDerivativesFilter filter, Frame outFrame, OrbitType outOrbitType, PositionAngleType outPositionAngleType)
Constructor using an output frame and : Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC
s) As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).StateCovarianceKeplerianHermiteInterpolator(TimeInterpolator<Orbit> orbitInterpolator, Frame outFrame, OrbitType outOrbitType, PositionAngleType outPositionAngleType)
Constructor using an output frame and : Default number of interpolation points ofDEFAULT_INTERPOLATION_POINTS
Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC
s) Use of position and two time derivatives during interpolation As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing). -
Uses of Frame in org.orekit.propagation.analytical
Methods in org.orekit.propagation.analytical that return Frame Modifier and Type Method Description Frame
Ephemeris. getFrame()
Get the frame in which the orbit is propagated.Methods in org.orekit.propagation.analytical with parameters of type Frame Modifier and Type Method Description Vector3D
AggregateBoundedPropagator. getPosition(AbsoluteDate date, Frame frame)
TimeStampedPVCoordinates
AggregateBoundedPropagator. getPVCoordinates(AbsoluteDate date, Frame frame)
-
Uses of Frame in org.orekit.propagation.analytical.gnss
Methods in org.orekit.propagation.analytical.gnss that return Frame Modifier and Type Method Description Frame
GLONASSAnalyticalPropagator. getECEF()
Gets the Earth Centered Earth Fixed frame used to propagate GLONASS orbits.Frame
GNSSPropagator. getECEF()
Gets the Earth Centered Earth Fixed frame used to propagate GNSS orbits according to the Interface Control Document.Frame
SBASPropagator. getECEF()
Gets the Earth Centered Earth Fixed frame used to propagate GNSS orbits.Frame
GLONASSAnalyticalPropagator. getECI()
Gets the Earth Centered Inertial frame used to propagate the orbit.Frame
GNSSPropagator. getECI()
Gets the Earth Centered Inertial frame used to propagate the orbit.Frame
SBASPropagator. getECI()
Gets the Earth Centered Inertial frame used to propagate the orbit.Frame
GLONASSAnalyticalPropagator. getFrame()
Get the frame in which the orbit is propagated.Frame
GNSSPropagator. getFrame()
Get the frame in which the orbit is propagated.Frame
SBASPropagator. getFrame()
Get the frame in which the orbit is propagated.Methods in org.orekit.propagation.analytical.gnss with parameters of type Frame Modifier and Type Method Description GLONASSAnalyticalPropagatorBuilder
GLONASSAnalyticalPropagatorBuilder. ecef(Frame bodyFixed)
Sets the Earth Centered Earth Fixed frame assimilated to the WGS84 ECEF.GNSSPropagatorBuilder
GNSSPropagatorBuilder. ecef(Frame bodyFixed)
Sets the Earth Centered Earth Fixed frame assimilated to the WGS84 ECEF.SBASPropagatorBuilder
SBASPropagatorBuilder. ecef(Frame bodyFixed)
Sets the Earth Centered Earth Fixed frame assimilated to the WGS84 ECEF.GLONASSAnalyticalPropagatorBuilder
GLONASSAnalyticalPropagatorBuilder. eci(Frame inertial)
Sets the Earth Centered Inertial frame used for propagation.GNSSPropagatorBuilder
GNSSPropagatorBuilder. eci(Frame inertial)
Sets the Earth Centered Inertial frame used for propagation.SBASPropagatorBuilder
SBASPropagatorBuilder. eci(Frame inertial)
Sets the Earth Centered Inertial frame used for propagation. -
Uses of Frame in org.orekit.propagation.analytical.gnss.data
Methods in org.orekit.propagation.analytical.gnss.data with parameters of type Frame Modifier and Type Method Description GLONASSAnalyticalPropagator
GLONASSAlmanac. getPropagator(DataContext context, AttitudeProvider provider, Frame inertial, Frame bodyFixed, double mass)
Get the propagator corresponding to the navigation message.GLONASSNumericalPropagator
GLONASSNavigationMessage. getPropagator(double step, DataContext context, AttitudeProvider provider, Frame inertial, double mass)
Get the propagator corresponding to the navigation message.default GNSSPropagator
GNSSOrbitalElements. getPropagator(Frames frames, AttitudeProvider provider, Frame inertial, Frame bodyFixed, double mass)
Get the propagator corresponding to the navigation message.SBASPropagator
SBASNavigationMessage. getPropagator(Frames frames, AttitudeProvider provider, Frame inertial, Frame bodyFixed, double mass, double mu)
Get the propagator corresponding to the navigation message. -
Uses of Frame in org.orekit.propagation.analytical.intelsat
Methods in org.orekit.propagation.analytical.intelsat that return Frame Modifier and Type Method Description Frame
FieldIntelsatElevenElementsPropagator. getFrame()
Get the frame in which the orbit is propagated.Frame
IntelsatElevenElementsPropagator. getFrame()
Get the frame in which the orbit is propagated.Constructors in org.orekit.propagation.analytical.intelsat with parameters of type Frame Constructor Description FieldIntelsatElevenElementsPropagator(FieldIntelsatElevenElements<T> elements, Frame inertialFrame, Frame ecefFrame)
Constructor.FieldIntelsatElevenElementsPropagator(FieldIntelsatElevenElements<T> elements, Frame inertialFrame, Frame ecefFrame, AttitudeProvider attitudeProvider, T mass)
Constructor.IntelsatElevenElementsPropagator(IntelsatElevenElements elements, Frame inertialFrame, Frame ecefFrame)
Constructor.IntelsatElevenElementsPropagator(IntelsatElevenElements elements, Frame inertialFrame, Frame ecefFrame, AttitudeProvider attitudeProvider, double mass)
Constructor. -
Uses of Frame in org.orekit.propagation.analytical.tle
Methods in org.orekit.propagation.analytical.tle that return Frame Modifier and Type Method Description Frame
FieldTLEPropagator. getFrame()
Get the frame in which the orbit is propagated.Frame
TLEPropagator. getFrame()
Get the frame in which the orbit is propagated.Methods in org.orekit.propagation.analytical.tle with parameters of type Frame Modifier and Type Method Description static TleGenerationAlgorithm
TLEPropagator. getDefaultTleGenerationAlgorithm(TimeScale utc, Frame teme)
Get the default TLE generation algorithm.static <T extends CalculusFieldElement<T>>
FieldTLEPropagator<T>FieldTLEPropagator. selectExtrapolator(FieldTLE<T> tle, AttitudeProvider attitudeProvider, T mass, Frame teme, T[] parameters)
Selects the extrapolator to use with the selected TLE.static <T extends CalculusFieldElement<T>>
FieldTLEPropagator<T>FieldTLEPropagator. selectExtrapolator(FieldTLE<T> tle, Frame teme, T[] parameters)
Selects the extrapolator to use with the selected TLE.static TLEPropagator
TLEPropagator. selectExtrapolator(TLE tle, AttitudeProvider attitudeProvider, double mass, Frame teme)
Selects the extrapolator to use with the selected TLE.static TLEPropagator
TLEPropagator. selectExtrapolator(TLE tle, Frame teme)
Selects the extrapolator to use with the selected TLE.Constructors in org.orekit.propagation.analytical.tle with parameters of type Frame Constructor Description DeepSDP4(TLE initialTLE, AttitudeProvider attitudeProvider, double mass, Frame teme)
Constructor for a unique initial TLE.FieldDeepSDP4(FieldTLE<T> initialTLE, AttitudeProvider attitudeProvider, T mass, Frame teme, T[] parameters)
Constructor for a unique initial TLE.FieldSGP4(FieldTLE<T> initialTLE, AttitudeProvider attitudeProvider, T mass, Frame teme, T[] parameters)
Constructor for a unique initial TLE.FieldTLEPropagator(FieldTLE<T> initialTLE, AttitudeProvider attitudeProvider, T mass, Frame teme, T[] parameters)
Protected constructor for derived classes.SGP4(TLE initialTLE, AttitudeProvider attitudeProvider, double mass, Frame teme)
Constructor for a unique initial TLE.TLEPropagator(TLE initialTLE, AttitudeProvider attitudeProvider, double mass, Frame teme)
Protected constructor for derived classes. -
Uses of Frame in org.orekit.propagation.analytical.tle.generation
Constructors in org.orekit.propagation.analytical.tle.generation with parameters of type Frame Constructor Description FixedPointTleGenerationAlgorithm(double epsilon, int maxIterations, double scale, TimeScale utc, Frame teme)
Constructor.LeastSquaresTleGenerationAlgorithm(int maxIterations, TimeScale utc, Frame teme)
Constructor. -
Uses of Frame in org.orekit.propagation.conversion
Methods in org.orekit.propagation.conversion that return Frame Modifier and Type Method Description Frame
AbstractPropagatorBuilder. getFrame()
Get the frame in which the orbit is propagated.protected Frame
AbstractPropagatorConverter. getFrame()
Get the frame of the initial state.Frame
PropagatorBuilder. getFrame()
Get the frame in which the orbit is propagated. -
Uses of Frame in org.orekit.propagation.conversion.averaging
Methods in org.orekit.propagation.conversion.averaging that return Frame Modifier and Type Method Description Frame
AbstractAveragedOrbitalState. getFrame()
Getter for the reference frame.Frame
AveragedOrbitalState. getFrame()
Getter for the reference frame.Methods in org.orekit.propagation.conversion.averaging with parameters of type Frame Modifier and Type Method Description static SGP4OrbitalState
SGP4OrbitalState. of(TLE tle, Frame teme)
Static constructor.Constructors in org.orekit.propagation.conversion.averaging with parameters of type Frame Constructor Description AbstractAveragedOrbitalState(AbsoluteDate date, Frame frame)
Protected constructor.BrouwerLyddaneOrbitalState(AbsoluteDate date, AveragedKeplerianWithMeanAngle elements, Frame frame, UnnormalizedSphericalHarmonicsProvider harmonicsProvider)
Constructor.DSST6X0OrbitalState(AbsoluteDate date, AveragedEquinoctialWithMeanAngle elements, Frame frame, UnnormalizedSphericalHarmonicsProvider harmonicsProvider)
Constructor.EcksteinHechlerOrbitalState(AbsoluteDate date, AveragedCircularWithMeanAngle elements, Frame frame, UnnormalizedSphericalHarmonicsProvider harmonicsProvider)
Constructor. -
Uses of Frame in org.orekit.propagation.events
Methods in org.orekit.propagation.events that return Frame Modifier and Type Method Description Frame
FieldNodeDetector. getFrame()
Get the frame in which the equator is defined.Frame
GroundFieldOfViewDetector. getFrame()
Get the sensor reference frame.Frame
NodeDetector. getFrame()
Get the frame in which the equator is defined.Frame
BetaAngleDetector. getInertialFrame()
The inertial frame in which beta angle is computed.Frame
FieldBetaAngleDetector. getInertialFrame()
The inertial frame in which beta angle is computed.Methods in org.orekit.propagation.events with parameters of type Frame Modifier and Type Method Description static double
BetaAngleDetector. calculateBetaAngle(SpacecraftState state, PVCoordinatesProvider celestialBodyProvider, Frame frame)
Calculate the beta angle between the orbit plane and the celestial body.static <T extends CalculusFieldElement<T>>
TFieldBetaAngleDetector. calculateBetaAngle(FieldSpacecraftState<T> state, FieldPVCoordinatesProvider<T> celestialBodyProvider, Frame frame)
Calculate the beta angle between the orbit plane and the celestial body.BetaAngleDetector
BetaAngleDetector. withInertialFrame(Frame newFrame)
Create a new instance with the provided inertial frame.FieldBetaAngleDetector<T>
FieldBetaAngleDetector. withInertialFrame(Frame newFrame)
Create a new instance with the provided inertial frame.Constructors in org.orekit.propagation.events with parameters of type Frame Constructor Description BetaAngleDetector(double betaAngleThreshold, PVCoordinatesProvider celestialBodyProvider, Frame inertialFrame)
Class constructor.BetaAngleDetector(AdaptableInterval maxCheck, double threshold, int maxIter, EventHandler handler, double betaAngleThreshold, PVCoordinatesProvider celestialBodyProvider, Frame inertialFrame)
Protected constructor with full parameters.FieldBetaAngleDetector(Field<T> field, T betaAngleThreshold, FieldPVCoordinatesProvider<T> celestialBodyProvider, Frame inertialFrame)
Class constructor.FieldBetaAngleDetector(FieldAdaptableInterval<T> maxCheck, T threshold, int maxIter, FieldEventHandler<T> handler, T betaAngleThreshold, FieldPVCoordinatesProvider<T> celestialBodyProvider, Frame inertialFrame)
Protected constructor with full parameters.FieldNodeDetector(FieldOrbit<T> orbit, Frame frame)
Build a new instance.FieldNodeDetector(FieldAdaptableInterval<T> maxCheck, T threshold, int maxIter, FieldEventHandler<T> handler, Frame frame)
Protected constructor with full parameters.FieldNodeDetector(T threshold, FieldOrbit<T> orbit, Frame frame)
Build a new instance.GroundFieldOfViewDetector(Frame frame, FieldOfView fov)
Build a new instance.GroundFieldOfViewDetector(AdaptableInterval maxCheck, double threshold, int maxIter, EventHandler handler, Frame frame, FieldOfView fov)
Protected constructor with full parameters.NodeDetector(double threshold, Orbit orbit, Frame frame)
Build a new instance.NodeDetector(Frame frame)
Build a new instance.NodeDetector(Orbit orbit, Frame frame)
Build a new instance.NodeDetector(AdaptableInterval maxCheck, double threshold, int maxIter, EventHandler handler, Frame frame)
Protected constructor with full parameters. -
Uses of Frame in org.orekit.propagation.integration
Methods in org.orekit.propagation.integration that return Frame Modifier and Type Method Description Frame
FieldIntegratedEphemeris. getFrame()
Frame
FieldStateMapper. getFrame()
Get the inertial frame.Frame
IntegratedEphemeris. getFrame()
Frame
StateMapper. getFrame()
Get the inertial frame.Methods in org.orekit.propagation.integration with parameters of type Frame Modifier and Type Method Description protected abstract StateMapper
AbstractIntegratedPropagator. createMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngleType positionAngleType, AttitudeProvider attitudeProvider, Frame frame)
Create a mapper between raw double components and spacecraft state.protected abstract FieldStateMapper<T>
FieldAbstractIntegratedPropagator. createMapper(FieldAbsoluteDate<T> referenceDate, T mu, OrbitType orbitType, PositionAngleType positionAngleType, AttitudeProvider attitudeProvider, Frame frame)
Create a mapper between raw double components and spacecraft state.Constructors in org.orekit.propagation.integration with parameters of type Frame Constructor Description FieldStateMapper(FieldAbsoluteDate<T> referenceDate, T mu, OrbitType orbitType, PositionAngleType positionAngleType, AttitudeProvider attitudeProvider, Frame frame)
Simple constructor.StateMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngleType positionAngleType, AttitudeProvider attitudeProvider, Frame frame)
Simple constructor. -
Uses of Frame in org.orekit.propagation.numerical
Methods in org.orekit.propagation.numerical with parameters of type Frame Modifier and Type Method Description protected FieldStateMapper<T>
FieldNumericalPropagator. createMapper(FieldAbsoluteDate<T> referenceDate, T mu, OrbitType orbitType, PositionAngleType positionAngleType, AttitudeProvider attitudeProvider, Frame frame)
Create a mapper between raw double components and spacecraft state.protected StateMapper
GLONASSNumericalPropagator. createMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngleType positionAngleType, AttitudeProvider attitudeProvider, Frame frame)
protected StateMapper
NumericalPropagator. createMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngleType positionAngleType, AttitudeProvider attitudeProvider, Frame frame)
Create a mapper between raw double components and spacecraft state.GLONASSNumericalPropagatorBuilder
GLONASSNumericalPropagatorBuilder. eci(Frame inertial)
Sets the Earth Centered Inertial frame used for propagation.Constructors in org.orekit.propagation.numerical with parameters of type Frame Constructor Description GLONASSNumericalPropagator(ClassicalRungeKuttaIntegrator integrator, GLONASSOrbitalElements glonassOrbit, Frame eci, AttitudeProvider provider, double mass, DataContext context, boolean isAccAvailable)
Private constructor. -
Uses of Frame in org.orekit.propagation.sampling
Methods in org.orekit.propagation.sampling with parameters of type Frame Modifier and Type Method Description default TimeStampedFieldPVCoordinates<T>
FieldOrekitStepInterpolator. getPVCoordinates(FieldAbsoluteDate<T> date, Frame frame)
Get theFieldPVCoordinates
of the body in the selected frame.default TimeStampedPVCoordinates
OrekitStepInterpolator. getPVCoordinates(AbsoluteDate date, Frame frame)
Get thePVCoordinates
of the body in the selected frame. -
Uses of Frame in org.orekit.propagation.semianalytical.dsst
Methods in org.orekit.propagation.semianalytical.dsst with parameters of type Frame Modifier and Type Method Description protected StateMapper
DSSTPropagator. createMapper(AbsoluteDate referenceDate, double mu, OrbitType ignoredOrbitType, PositionAngleType ignoredPositionAngleType, AttitudeProvider attitudeProvider, Frame frame)
Create a mapper between raw double components and spacecraft state.protected FieldStateMapper<T>
FieldDSSTPropagator. createMapper(FieldAbsoluteDate<T> referenceDate, T mu, OrbitType ignoredOrbitType, PositionAngleType ignoredPositionAngleType, AttitudeProvider attitudeProvider, Frame frame)
Create a mapper between raw double components and spacecraft state. -
Uses of Frame in org.orekit.propagation.semianalytical.dsst.forces
Constructors in org.orekit.propagation.semianalytical.dsst.forces with parameters of type Frame Constructor Description DSSTTesseral(Frame centralBodyFrame, double centralBodyRotationRate, UnnormalizedSphericalHarmonicsProvider provider)
Simple constructor with default reference values.DSSTTesseral(Frame centralBodyFrame, double centralBodyRotationRate, UnnormalizedSphericalHarmonicsProvider provider, int maxDegreeTesseralSP, int maxOrderTesseralSP, int maxEccPowTesseralSP, int maxFrequencyShortPeriodics, int maxDegreeMdailyTesseralSP, int maxOrderMdailyTesseralSP, int maxEccPowMdailyTesseralSP)
Simple constructor. -
Uses of Frame in org.orekit.propagation.semianalytical.dsst.utilities
Methods in org.orekit.propagation.semianalytical.dsst.utilities that return Frame Modifier and Type Method Description Frame
AuxiliaryElements. getFrame()
Get the definition frame of the orbit.Frame
FieldAuxiliaryElements. getFrame()
Get the definition frame of the orbit. -
Uses of Frame in org.orekit.utils
Subclasses of Frame in org.orekit.utils Modifier and Type Class Description class
ExtendedPVCoordinatesProviderAdapter
Adapter fromExtendedPVCoordinatesProvider
toTransformProvider
.Methods in org.orekit.utils that return Frame Modifier and Type Method Description Frame
AbsolutePVCoordinates. getFrame()
Get the frame in which the coordinates are defined.Frame
FieldAbsolutePVCoordinates. getFrame()
Get the frame in which the coordinates are defined.Frame
AbsolutePVCoordinatesHermiteInterpolator. getOutputFrame()
Get output frame for the interpolated instance.Frame
FieldAbsolutePVCoordinatesHermiteInterpolator. getOutputFrame()
Get output frame for the interpolated instance.Methods in org.orekit.utils with parameters of type Frame Modifier and Type Method Description Vector3D
AbsolutePVCoordinates. getPosition(Frame outputFrame)
Get the position in a specified frame.Vector3D
AggregatedPVCoordinatesProvider. getPosition(AbsoluteDate date, Frame frame)
Vector3D
ConstantPVCoordinatesProvider. getPosition(AbsoluteDate date, Frame frame)
<T extends CalculusFieldElement<T>>
FieldVector3D<T>ExtendedPositionProvider. getPosition(FieldAbsoluteDate<T> date, Frame frame)
Get the position in the selected frame.default <T extends CalculusFieldElement<T>>
FieldVector3D<T>ExtendedPVCoordinatesProvider. getPosition(FieldAbsoluteDate<T> date, Frame frame)
Get the position of the body in the selected frame.FieldVector3D<T>
FieldAbsolutePVCoordinates. getPosition(Frame outputFrame)
Get the position in a specified frame.default FieldVector3D<T>
FieldPVCoordinatesProvider. getPosition(FieldAbsoluteDate<T> date, Frame frame)
Get the position of the body in the selected frame.default Vector3D
PVCoordinatesProvider. getPosition(AbsoluteDate date, Frame frame)
Get the position of the body in the selected frame.TimeStampedPVCoordinates
AbsolutePVCoordinates. getPVCoordinates(Frame outputFrame)
Get the TimeStampedPVCoordinates in a specified frame.TimeStampedPVCoordinates
AbsolutePVCoordinates. getPVCoordinates(AbsoluteDate otherDate, Frame outputFrame)
TimeStampedPVCoordinates
AggregatedPVCoordinatesProvider. getPVCoordinates(AbsoluteDate date, Frame frame)
TimeStampedPVCoordinates
AggregatedPVCoordinatesProvider.InvalidPVProvider. getPVCoordinates(AbsoluteDate date, Frame frame)
TimeStampedPVCoordinates
ConstantPVCoordinatesProvider. getPVCoordinates(AbsoluteDate date, Frame frame)
default TimeStampedPVCoordinates
ExtendedPositionProvider. getPVCoordinates(AbsoluteDate date, Frame frame)
Get thePVCoordinates
of the body in the selected frame.default <T extends CalculusFieldElement<T>>
TimeStampedFieldPVCoordinates<T>ExtendedPositionProvider. getPVCoordinates(FieldAbsoluteDate<T> date, Frame frame)
Get the position-velocity-acceleration in the selected frame.<T extends CalculusFieldElement<T>>
TimeStampedFieldPVCoordinates<T>ExtendedPVCoordinatesProvider. getPVCoordinates(FieldAbsoluteDate<T> date, Frame frame)
Get theFieldPVCoordinates
of the body in the selected frame.TimeStampedFieldPVCoordinates<T>
FieldAbsolutePVCoordinates. getPVCoordinates(Frame outputFrame)
Get the TimeStampedFieldPVCoordinates in a specified frame.TimeStampedFieldPVCoordinates<T>
FieldAbsolutePVCoordinates. getPVCoordinates(FieldAbsoluteDate<T> otherDate, Frame outputFrame)
TimeStampedFieldPVCoordinates<T>
FieldPVCoordinatesProvider. getPVCoordinates(FieldAbsoluteDate<T> date, Frame frame)
Get theFieldPVCoordinates
of the body in the selected frame.TimeStampedFieldPVCoordinates<T>
FieldShiftingPVCoordinatesProvider. getPVCoordinates(FieldAbsoluteDate<T> date, Frame frame)
Get theFieldPVCoordinates
of the body in the selected frame.TimeStampedPVCoordinates
FrameAdapter. getPVCoordinates(AbsoluteDate date, Frame frame)
Get thePVCoordinates
of the body in the selected frame.<T extends CalculusFieldElement<T>>
TimeStampedFieldPVCoordinates<T>FrameAdapter. getPVCoordinates(FieldAbsoluteDate<T> date, Frame frame)
Get theFieldPVCoordinates
of the body in the selected frame.TimeStampedPVCoordinates
PVCoordinatesProvider. getPVCoordinates(AbsoluteDate date, Frame frame)
Get thePVCoordinates
of the body in the selected frame.TimeStampedPVCoordinates
ShiftingPVCoordinatesProvider. getPVCoordinates(AbsoluteDate date, Frame frame)
Get thePVCoordinates
of the body in the selected frame.PVCoordinatesProvider
TimeStampedPVCoordinates. toTaylorProvider(Frame instanceFrame)
Create a local provider using simply Taylor expansion throughTimeStampedPVCoordinates.shiftedBy(double)
.Constructors in org.orekit.utils with parameters of type Frame Constructor Description AbsolutePVCoordinates(Frame frame, AbsoluteDate date, FieldVector3D<U> p)
Builds a AbsolutePVCoordinates triplet from aFieldVector3D
<Derivative
>.AbsolutePVCoordinates(Frame frame, AbsoluteDate date, Vector3D position, Vector3D velocity)
Build from position and velocity.AbsolutePVCoordinates(Frame frame, AbsoluteDate date, Vector3D position, Vector3D velocity, Vector3D acceleration)
Build from position, velocity, acceleration.AbsolutePVCoordinates(Frame frame, AbsoluteDate date, PVCoordinates pva)
Build from frame, date and PVA coordinates.AbsolutePVCoordinates(Frame frame, TimeStampedPVCoordinates pva)
Build from frame and TimeStampedPVCoordinates.AbsolutePVCoordinatesHermiteInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputFrame, CartesianDerivativesFilter filter)
Constructor.AbsolutePVCoordinatesHermiteInterpolator(int interpolationPoints, Frame outputFrame)
Constructor with : Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC
s) Use of position and two time derivatives during interpolation As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).AbsolutePVCoordinatesHermiteInterpolator(int interpolationPoints, Frame outputFrame, CartesianDerivativesFilter filter)
Constructor with default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC
s).AbsolutePVCoordinatesHermiteInterpolator(Frame outputFrame)
Constructor with : Default number of interpolation points ofDEFAULT_INTERPOLATION_POINTS
Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC
s) Use of position and two time derivatives during interpolation As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).ConstantPVCoordinatesProvider(Vector3D pos, Frame frame)
Create the PVCoordinatesProvider from a fixed point in a frame.ConstantPVCoordinatesProvider(PVCoordinates pva, Frame frame)
Create the PVCoordinatesProvider from a fixed point in a frame.ExtendedPVCoordinatesProviderAdapter(Frame parent, ExtendedPVCoordinatesProvider provider, String name)
Simple constructor.FieldAbsolutePVCoordinates(Frame frame, FieldAbsoluteDate<T> date, FieldVector3D<T> position, FieldVector3D<T> velocity)
Build from position and velocity.FieldAbsolutePVCoordinates(Frame frame, FieldAbsoluteDate<T> date, FieldVector3D<T> position, FieldVector3D<T> velocity, FieldVector3D<T> acceleration)
Build from position, velocity, acceleration.FieldAbsolutePVCoordinates(Frame frame, FieldAbsoluteDate<T> date, FieldVector3D<U> p)
Builds a FieldAbsolutePVCoordinates triplet from aFieldVector3D
<DerivativeStructure
>.FieldAbsolutePVCoordinates(Frame frame, FieldAbsoluteDate<T> date, FieldPVCoordinates<T> pva)
Build from frame, date and FieldPVA coordinates.FieldAbsolutePVCoordinates(Frame frame, TimeStampedFieldPVCoordinates<T> pva)
Build from frame and TimeStampedFieldPVCoordinates.FieldAbsolutePVCoordinatesHermiteInterpolator(int interpolationPoints, double extrapolationThreshold, Frame outputFrame, CartesianDerivativesFilter filter)
Constructor.FieldAbsolutePVCoordinatesHermiteInterpolator(int interpolationPoints, Frame outputFrame)
Constructor with : Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC
s) Use of position and two time derivatives during interpolation As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).FieldAbsolutePVCoordinatesHermiteInterpolator(int interpolationPoints, Frame outputFrame, CartesianDerivativesFilter filter)
Constructor with default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC
s).FieldAbsolutePVCoordinatesHermiteInterpolator(Frame outputFrame)
Constructor with : Default number of interpolation points ofDEFAULT_INTERPOLATION_POINTS
Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC
s) Use of position and two time derivatives during interpolation As this implementation of interpolation is polynomial, it should be used only with small number of interpolation points (about 10-20 points) in order to avoid Runge's phenomenon and numerical problems (including NaN appearing).FieldShiftingPVCoordinatesProvider(TimeStampedFieldPVCoordinates<T> referencePV, Frame referenceFrame)
Simple constructor.FrameAdapter(Frame originFrame)
Simple constructor.ShiftingPVCoordinatesProvider(TimeStampedPVCoordinates referencePV, Frame referenceFrame)
Simple constructor.
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