Uses of Class
org.orekit.frames.Frame

Packages that use Frame

Package	Description
org.orekit.attitudes	This package provides classes to represent simple attitudes.
org.orekit.bodies	This package provides interface to represent the position and geometry of space objects such as stars, planets or asteroids.
org.orekit.estimation.iod
org.orekit.files.ccsds	This package provides a parser for orbit data stored in CCSDS Orbit Data Message format.
org.orekit.forces	This package provides the interface for force models that will be used by the NumericalPropagator, as well as some classical spacecraft models for surface forces (spherical, box and solar array ...).
org.orekit.forces.drag	This package provides all drag-related forces.
org.orekit.forces.gravity	This package provides all gravity-related forces.
org.orekit.forces.maneuvers	This package provides models of simple maneuvers.
org.orekit.forces.radiation	This package provides all radiation pressure related forces.
org.orekit.frames	This package provides classes to handle frames and transforms between them.
org.orekit.models.earth	This package provides models that simulate certain physical phenomena of Earth and the near-Earth environment.
org.orekit.orbits	This package provides classes to represent orbits.
org.orekit.propagation	Propagation
org.orekit.propagation.analytical	Top level package for analytical propagators.
org.orekit.propagation.analytical.gnss	This package provides classes to propagate GNSS orbits.
org.orekit.propagation.analytical.tle	This package provides classes to read and extrapolate tle's.
org.orekit.propagation.conversion	This package provides tools to convert a given propagator or a set of SpacecraftState into another propagator.
org.orekit.propagation.events	This package provides interfaces and classes dealing with events occurring during propagation.
org.orekit.propagation.integration	Utilities for integration-based propagators (both numerical and semi-analytical).
org.orekit.propagation.numerical	Top level package for numerical propagators.
org.orekit.propagation.semianalytical.dsst	This package provides an implementation of the Draper Semi-analytical Satellite Theory (DSST).
org.orekit.propagation.semianalytical.dsst.forces	This package provides force models for Draper Semi-analytical Satellite Theory (DSST).
org.orekit.propagation.semianalytical.dsst.utilities	This package provides utilities for Draper Semi-analytical Satellite Theory (DSST).
org.orekit.utils	This package provides useful objects.

Uses of Frame in org.orekit.attitudes

Methods in org.orekit.attitudes that return Frame

Modifier and Type	Method and Description
Frame	GroundPointing.getBodyFrame() Get the body frame.
Frame	Attitude.getReferenceFrame() Get the reference frame.

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

Modifier and Type	Method and Description
Attitude	YawCompensation.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	GroundPointing.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	FixedRate.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	TabulatedLofOffset.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	SpinStabilized.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	TabulatedProvider.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	YawSteering.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	AttitudeProvider.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	LofOffsetPointing.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	LofOffset.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	AttitudesSequence.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	CelestialBodyPointed.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	InertialProvider.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	YawCompensation.getBaseState(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the base system state at given date, without compensation.
Attitude	YawSteering.getBaseState(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the base system state at given date, without compensation.
protected TimeStampedPVCoordinates	YawCompensation.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate 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.
protected TimeStampedPVCoordinates	NadirPointing.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the target point position/velocity in specified frame.
protected TimeStampedPVCoordinates	YawSteering.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the target point position/velocity in specified frame.
protected TimeStampedPVCoordinates	TargetPointing.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the target point position/velocity in specified frame.
protected TimeStampedPVCoordinates	LofOffsetPointing.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the target point position/velocity in specified frame.
protected TimeStampedPVCoordinates	BodyCenterPointing.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the target point position/velocity in specified frame.
double	YawCompensation.getYawAngle(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the yaw compensation angle at date.
Attitude	Attitude.withReferenceFrame(Frame newReferenceFrame) Get a similar attitude with a specific reference frame.

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

Constructor and Description
Attitude(AbsoluteDate date, Frame referenceFrame, AngularCoordinates orientation) Creates a new instance.
Attitude(AbsoluteDate date, Frame referenceFrame, Rotation attitude, Vector3D spin, Vector3D acceleration) Creates a new instance.
Attitude(Frame referenceFrame, TimeStampedAngularCoordinates orientation) Creates a new instance.
BodyCenterPointing(Frame inertialFrame, Ellipsoid shape) Creates new instance.
CelestialBodyPointed(Frame celestialFrame, PVCoordinatesProvider pointedBody, Vector3D phasingCel, Vector3D pointingSat, Vector3D phasingSat) Creates new instance.
GroundPointing(Frame inertialFrame, Frame bodyFrame) Default constructor.
LofOffset(Frame inertialFrame, LOFType type) Create a LOF-aligned attitude.
LofOffset(Frame inertialFrame, LOFType type, RotationOrder order, double alpha1, double alpha2, double alpha3) Creates new instance.
LofOffsetPointing(Frame inertialFrame, BodyShape shape, AttitudeProvider attLaw, Vector3D satPointingVector) Creates new instance.
NadirPointing(Frame inertialFrame, BodyShape shape) Creates new instance.
TabulatedLofOffset(Frame inertialFrame, LOFType type, List<TimeStampedAngularCoordinates> table, int n, AngularDerivativesFilter filter) Creates new instance.
TabulatedProvider(Frame referenceFrame, List<TimeStampedAngularCoordinates> table, int n, AngularDerivativesFilter filter) Creates new instance.
TargetPointing(Frame inertialFrame, Frame bodyFrame, Vector3D target) Creates a new instance from body frame and target expressed in cartesian coordinates.
TargetPointing(Frame inertialFrame, GeodeticPoint targetGeo, BodyShape shape) Creates a new instance from body shape and target expressed in geodetic coordinates.
YawCompensation(Frame inertialFrame, GroundPointing groundPointingLaw) Creates a new instance.
YawSteering(Frame inertialFrame, GroundPointing groundPointingLaw, PVCoordinatesProvider sun, Vector3D phasingAxis) Creates a new instance.

Uses of Frame in org.orekit.bodies

Methods in org.orekit.bodies that return Frame

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

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

Modifier and Type	Method and Description
GeodeticPoint	OneAxisEllipsoid.getIntersectionPoint(Line line, Vector3D close, Frame frame, AbsoluteDate date) Get the intersection point of a line with the surface of the body.
GeodeticPoint	BodyShape.getIntersectionPoint(Line line, Vector3D close, Frame frame, AbsoluteDate date) Get the intersection point of a line with the surface of the body.
TimeStampedPVCoordinates	OneAxisEllipsoid.projectToGround(TimeStampedPVCoordinates pv, Frame frame) Project a moving point to the ground.
TimeStampedPVCoordinates	BodyShape.projectToGround(TimeStampedPVCoordinates pv, Frame frame) Project a moving point to the ground.
Vector3D	OneAxisEllipsoid.projectToGround(Vector3D point, AbsoluteDate date, Frame frame) Project a point to the ground.
Vector3D	BodyShape.projectToGround(Vector3D point, AbsoluteDate date, Frame frame) Project a point to the ground.
FieldGeodeticPoint<DerivativeStructure>	OneAxisEllipsoid.transform(PVCoordinates point, Frame frame, AbsoluteDate date) Transform a Cartesian point to a surface-relative point.
GeodeticPoint	OneAxisEllipsoid.transform(Vector3D point, Frame frame, AbsoluteDate date) Transform a cartesian point to a surface-relative point.
GeodeticPoint	BodyShape.transform(Vector3D point, Frame frame, AbsoluteDate date) Transform a cartesian point to a surface-relative point.

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

Constructor and Description
Ellipse(Vector3D center, Vector3D u, Vector3D v, double a, double b, Frame frame) Simple constructor.
Ellipsoid(Frame frame, double a, double b, double c) Simple constructor.
OneAxisEllipsoid(double ae, double f, Frame bodyFrame) Simple constructor.

Uses of Frame in org.orekit.estimation.iod

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

Modifier and Type	Method and Description
KeplerianOrbit	IodLambert.estimate(Frame frame, boolean posigrade, int nRev, Vector3D P1, AbsoluteDate T1, Vector3D P2, AbsoluteDate T2) Estimate an keplerian orbit given two position vector and a duration.
KeplerianOrbit	IodGibbs.estimate(Frame frame, PV pv1, PV pv2, PV pv3) Give an initial orbit estimation, assuming Keplerian motion.
KeplerianOrbit	IodGibbs.estimate(Frame frame, Vector3D r1, AbsoluteDate date1, Vector3D r2, AbsoluteDate date2, Vector3D r3, AbsoluteDate date3) Give an initial orbit estimation, assuming Keplerian motion.

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

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

Uses of Frame in org.orekit.files.ccsds

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

Modifier and Type	Method and Description
Frame	OGMFile.getCovRefFrame() Get coordinate system for covariance matrix, for absolute frames.
Frame	OEMFile.CovarianceMatrix.getFrame() Get coordinate system for covariance matrix, for absolute frames.
Frame	ODMMetaData.getFrame() Get the reference frame in which data are given: used for state vector and Keplerian elements data (and for the covariance reference frame if none is given).
Frame	CCSDSFrame.getFrame(IERSConventions conventions, boolean simpleEOP) Get the frame corresponding to the CCSDS constant.
Frame	OPMFile.Maneuver.getRefFrame() Get Coordinate system for velocity increment vector, for absolute frames.

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

Modifier and Type	Method and Description
void	OPMFile.Maneuver.setRefFrame(Frame refFrame) Set Coordinate system for velocity increment vector, for absolute frames.

Uses of Frame in org.orekit.forces

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

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

Uses of Frame in org.orekit.forces.drag

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

Modifier and Type	Method and Description
Frame	DTM2000.getFrame() Get the frame of the central body.
Frame	Atmosphere.getFrame() Get the frame of the central body.
Frame	HarrisPriester.getFrame() Get the frame of the central body.
Frame	JB2006.getFrame() Get the frame of the central body.
Frame	SimpleExponentialAtmosphere.getFrame() Get the frame of the central body.

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

Modifier and Type	Method and Description
FieldVector3D<DerivativeStructure>	DragForce.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
FieldVector3D<DerivativeStructure>	DragSensitive.dragAcceleration(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass, DerivativeStructure density, FieldVector3D<DerivativeStructure> relativeVelocity) Compute the acceleration due to drag, with state derivatives.
FieldVector3D<DerivativeStructure>	IsotropicDrag.dragAcceleration(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass, DerivativeStructure density, FieldVector3D<DerivativeStructure> relativeVelocity) Compute the acceleration due to drag, with state derivatives.
Vector3D	DragSensitive.dragAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, double density, Vector3D relativeVelocity) Compute the acceleration due to drag.
Vector3D	IsotropicDrag.dragAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, double density, Vector3D relativeVelocity) Compute the acceleration due to drag.
FieldVector3D<DerivativeStructure>	DragSensitive.dragAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, double density, Vector3D relativeVelocity, String paramName) Compute acceleration due to drag, with parameters derivatives.
FieldVector3D<DerivativeStructure>	IsotropicDrag.dragAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, double density, Vector3D relativeVelocity, String paramName) Compute acceleration due to drag, with parameters derivatives.
double	DTM2000.getDensity(AbsoluteDate date, Vector3D position, Frame frame) Get the local density.
double	Atmosphere.getDensity(AbsoluteDate date, Vector3D position, Frame frame) Get the local density.
double	HarrisPriester.getDensity(AbsoluteDate date, Vector3D position, Frame frame) Get the local density at some position.
double	JB2006.getDensity(AbsoluteDate date, Vector3D position, Frame frame) Get the local density.
double	SimpleExponentialAtmosphere.getDensity(AbsoluteDate date, Vector3D position, Frame frame) Get the local density.
Vector3D	DTM2000.getVelocity(AbsoluteDate date, Vector3D position, Frame frame) Get the inertial velocity of atmosphere molecules.
Vector3D	Atmosphere.getVelocity(AbsoluteDate date, Vector3D position, Frame frame) Get the inertial velocity of atmosphere molecules.
Vector3D	HarrisPriester.getVelocity(AbsoluteDate date, Vector3D position, Frame frame) Get the inertial velocity of atmosphere molecules.
Vector3D	JB2006.getVelocity(AbsoluteDate date, Vector3D position, Frame frame) Get the inertial velocity of atmosphere molecules.
Vector3D	SimpleExponentialAtmosphere.getVelocity(AbsoluteDate date, Vector3D position, Frame frame) Get the inertial velocity of atmosphere molecules.

Uses of Frame in org.orekit.forces.gravity

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

Modifier and Type	Method and Description
FieldVector3D<DerivativeStructure>	SolidTides.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
FieldVector3D<DerivativeStructure>	CunninghamAttractionModel.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
FieldVector3D<DerivativeStructure>	Relativity.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass)
FieldVector3D<DerivativeStructure>	ThirdBodyAttraction.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
FieldVector3D<DerivativeStructure>	OceanTides.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
FieldVector3D<DerivativeStructure>	DrozinerAttractionModel.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
FieldVector3D<DerivativeStructure>	HolmesFeatherstoneAttractionModel.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
FieldVector3D<DerivativeStructure>	NewtonianAttraction.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.

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

Constructor and Description
CunninghamAttractionModel(Frame centralBodyFrame, UnnormalizedSphericalHarmonicsProvider provider, double hPosition) Creates a new instance.
DrozinerAttractionModel(Frame centralBodyFrame, UnnormalizedSphericalHarmonicsProvider provider, double hPosition) Creates a new instance.
HolmesFeatherstoneAttractionModel(Frame centralBodyFrame, NormalizedSphericalHarmonicsProvider provider) Creates a new instance.
OceanTides(Frame centralBodyFrame, double ae, double mu, boolean poleTide, double step, int nbPoints, int degree, int order, IERSConventions conventions, UT1Scale ut1) Simple constructor.
OceanTides(Frame centralBodyFrame, double ae, double mu, int degree, int order, IERSConventions conventions, UT1Scale ut1) Simple constructor.
SolidTides(Frame centralBodyFrame, double ae, double mu, TideSystem centralTideSystem, boolean poleTide, double step, int nbPoints, IERSConventions conventions, UT1Scale ut1, CelestialBody... bodies) Simple constructor.
SolidTides(Frame centralBodyFrame, double ae, double mu, TideSystem centralTideSystem, IERSConventions conventions, UT1Scale ut1, CelestialBody... bodies) Simple constructor.

Uses of Frame in org.orekit.forces.maneuvers

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

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

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

Modifier and Type	Method and Description
FieldVector3D<DerivativeStructure>	ConstantThrustManeuver.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.

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

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

Uses of Frame in org.orekit.forces.radiation

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

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

Uses of Frame in org.orekit.frames

Subclasses of Frame in org.orekit.frames

Modifier and Type	Class and Description
class	FactoryManagedFrame Base class for the predefined frames that are managed by FramesFactory.
class	LocalOrbitalFrame Class for frames moving with an orbiting satellite.
class	TopocentricFrame Topocentric frame.
class	UpdatableFrame Frame whose transform from its parent can be updated.

Methods in org.orekit.frames that return Frame

Modifier and Type	Method and Description
Frame	HelmertTransformation.Predefined.createTransformedITRF(Frame parent, String name) Create an ITRF frame by transforming another ITRF frame.
Frame	Frame.getAncestor(int n) Get the nth ancestor of the frame.
static Frame	FramesFactory.getEcliptic(IERSConventions conventions) Get the ecliptic frame.
Frame	OrphanFrame.getFrame() Get the associated frame.
static Frame	FramesFactory.getFrame(Predefined factoryKey) Get one of the predefined frames.
Frame	Frame.getFrozenFrame(Frame reference, AbsoluteDate freezingDate, String frozenName) Get a new version of the instance, frozen with respect to a reference frame.
static Frame	FramesFactory.getGCRF() Get the unique GCRF frame.
static Frame	FramesFactory.getICRF() Get the unique ICRF frame.
Frame	Frame.getParent() Get the parent frame.
protected static Frame	Frame.getRoot() Get the unique root frame.

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

Modifier and Type	Method and Description
void	OrphanFrame.attachTo(Frame parent, Transform transform, boolean isPseudoInertial) Attach the instance (and all its children down to leafs) to the main tree.
void	OrphanFrame.attachTo(Frame parent, TransformProvider transformProvider, boolean isPseudoInertial) Attach the instance (and all its children down to leafs) to the main tree.
Frame	HelmertTransformation.Predefined.createTransformedITRF(Frame parent, String name) Create an ITRF frame by transforming another ITRF frame.
double	TopocentricFrame.getAzimuth(Vector3D extPoint, Frame frame, AbsoluteDate date) Get the azimuth of a point with regards to the topocentric frame center point.
double	TopocentricFrame.getElevation(Vector3D extPoint, Frame frame, AbsoluteDate date) Get the elevation of a point with regards to the local point.
Frame	Frame.getFrozenFrame(Frame reference, AbsoluteDate freezingDate, String frozenName) Get a new version of the instance, frozen with respect to a reference frame.
static Transform	FramesFactory.getNonInterpolatingTransform(Frame from, Frame to, AbsoluteDate date) Get the transform between two frames, suppressing all interpolation.
TimeStampedPVCoordinates	TopocentricFrame.getPVCoordinates(AbsoluteDate date, Frame frame) Get the PVCoordinates of the topocentric frame origin in the selected frame.
double	TopocentricFrame.getRange(Vector3D extPoint, Frame frame, AbsoluteDate date) Get the range of a point with regards to the topocentric frame center point.
double	TopocentricFrame.getRangeRate(PVCoordinates extPV, Frame frame, AbsoluteDate date) Get the range rate of a point with regards to the topocentric frame center point.
Transform	Frame.getTransformTo(Frame destination, AbsoluteDate date) Get the transform from the instance to another frame.
boolean	Frame.isChildOf(Frame potentialAncestor) Determine if a Frame is a child of another one.
void	UpdatableFrame.updateTransform(Frame f1, Frame f2, Transform f1Tof2, AbsoluteDate date) Update the transform from parent frame implicitly according to two other frames.

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

Constructor and Description
FactoryManagedFrame(Frame parent, TransformProvider transformProvider, boolean pseudoInertial, Predefined factoryKey) Simple constructor.
Frame(Frame parent, TransformProvider transformProvider, String name) Build a non-inertial frame from its transform with respect to its parent.
Frame(Frame parent, TransformProvider transformProvider, String name, boolean pseudoInertial) Build a frame from its transform with respect to its parent.
Frame(Frame parent, Transform transform, String name) Build a non-inertial frame from its transform with respect to its parent.
Frame(Frame parent, Transform transform, String name, boolean pseudoInertial) Build a frame from its transform with respect to its parent.
LocalOrbitalFrame(Frame parent, LOFType type, PVCoordinatesProvider provider, String name) Build a new instance.
UpdatableFrame(Frame parent, Transform transform, String name) Build a non-inertial frame from its transform with respect to its parent.
UpdatableFrame(Frame parent, Transform transform, String name, boolean pseudoInertial) Build a frame from its transform with respect to its parent.

Uses of Frame in org.orekit.models.earth

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

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

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

Modifier and Type	Method and Description
static ReferenceEllipsoid	ReferenceEllipsoid.getGrs80(Frame bodyFrame) Get the GRS80 ellipsoid, attached to the given body frame.
GeodeticPoint	Geoid.getIntersectionPoint(Line lineInFrame, Vector3D closeInFrame, Frame frame, AbsoluteDate date) Get the intersection point of a line with the surface of the body.
static ReferenceEllipsoid	ReferenceEllipsoid.getWgs84(Frame bodyFrame) Get the WGS84 ellipsoid, attached to the given body frame.
TimeStampedPVCoordinates	Geoid.projectToGround(TimeStampedPVCoordinates pv, Frame frame)
Vector3D	Geoid.projectToGround(Vector3D point, AbsoluteDate date, Frame frame)
GeodeticPoint	Geoid.transform(Vector3D point, Frame frame, AbsoluteDate date) Transform a cartesian point to a surface-relative point.

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

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

Uses of Frame in org.orekit.orbits

Methods in org.orekit.orbits that return Frame

Modifier and Type	Method and Description
Frame	Orbit.getFrame() Get the frame in which the orbital parameters are defined.

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

Modifier and Type	Method and Description
TimeStampedPVCoordinates	Orbit.getPVCoordinates(AbsoluteDate otherDate, Frame otherFrame) Get the PVCoordinates of the body in the selected frame.
TimeStampedPVCoordinates	Orbit.getPVCoordinates(Frame outputFrame) Get the TimeStampedPVCoordinates in a specified frame.
abstract Orbit	OrbitType.mapArrayToOrbit(double[] array, PositionAngle type, AbsoluteDate date, double mu, Frame frame) Convert state array to orbital parameters.

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

Constructor and Description
CartesianOrbit(PVCoordinates pvaCoordinates, Frame frame, AbsoluteDate date, double mu) Constructor from Cartesian parameters.
CartesianOrbit(TimeStampedPVCoordinates pvaCoordinates, Frame frame, double mu) Constructor from Cartesian parameters.
CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, PositionAngle type, Frame frame, AbsoluteDate date, double mu) Creates a new instance.
CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, PositionAngle type, TimeStampedPVCoordinates pvCoordinates, Frame frame, 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, PositionAngle type, Frame frame, AbsoluteDate date, double mu) Creates a new instance.
EquinoctialOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu) Constructor from cartesian parameters.
EquinoctialOrbit(TimeStampedPVCoordinates pvCoordinates, Frame frame, double mu) Constructor from cartesian parameters.
KeplerianOrbit(double a, double e, double i, double pa, double raan, double anomaly, PositionAngle type, Frame frame, AbsoluteDate date, double mu) Creates a new instance.
KeplerianOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu) Constructor from cartesian parameters.
KeplerianOrbit(TimeStampedPVCoordinates pvCoordinates, Frame frame, double mu) Constructor from cartesian parameters.
Orbit(Frame frame, AbsoluteDate date, double mu) Default constructor.
Orbit(TimeStampedPVCoordinates pvCoordinates, Frame frame, double mu) Set the orbit from Cartesian parameters.

Uses of Frame in org.orekit.propagation

Methods in org.orekit.propagation that return Frame

Modifier and Type	Method and Description
Frame	Propagator.getFrame() Get the frame in which the orbit is propagated.
Frame	AbstractPropagator.getFrame() Get the frame in which the orbit is propagated.
Frame	SpacecraftState.getFrame() Get the inertial frame.

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

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

Uses of Frame in org.orekit.propagation.analytical

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

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

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

Modifier and Type	Method and Description
TimeStampedPVCoordinates	Ephemeris.getPVCoordinates(AbsoluteDate date, Frame f) Get the PVCoordinates of the body in the selected frame.

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

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

Modifier and Type	Method and Description
Frame	GPSPropagator.getECEF() Gets the Earth Centered Earth Fixed frame used to propagate GPS orbits according to the GPS Interface Specification.
Frame	GPSPropagator.getECI() Gets the Earth Centered Inertial frame used to propagate the orbit.
Frame	GPSPropagator.getFrame() Get the frame in which the orbit is propagated.

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

Modifier and Type	Method and Description
GPSPropagator.Builder	GPSPropagator.Builder.ecef(Frame bodyFixed) Sets the Earth Centered Earth Fixed frame assimilated to the WGS84 ECEF.
GPSPropagator.Builder	GPSPropagator.Builder.eci(Frame inertial) Sets the Earth Centered Inertial frame used for propagation.

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

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

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

Uses of Frame in org.orekit.propagation.conversion

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

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

Uses of Frame in org.orekit.propagation.events

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

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

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

Constructor and Description
GroundFieldOfViewDetector(Frame frame, FieldOfView fov) Build a new instance.
NodeDetector(double threshold, Orbit orbit, Frame frame) Build a new instance.
NodeDetector(Orbit orbit, Frame frame) Build a new instance.

Uses of Frame in org.orekit.propagation.integration

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

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

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

Modifier and Type	Method and Description
protected abstract StateMapper	AbstractIntegratedPropagator.createMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame) Create a mapper between raw double components and spacecraft state.
TimeStampedPVCoordinates	IntegratedEphemeris.getPVCoordinates(AbsoluteDate date, Frame frame) Get the PVCoordinates of the body in the selected frame.

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

Constructor and Description
StateMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame) Simple constructor.

Uses of Frame in org.orekit.propagation.numerical

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

Modifier and Type	Method and Description
FieldVector3D<DerivativeStructure>	Jacobianizer.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration and derivatives with respect to state.
void	TimeDerivativesEquations.addAcceleration(Vector3D gamma, Frame frame) Add the contribution of an acceleration expressed in some inertial frame.
protected StateMapper	NumericalPropagator.createMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngle positionAngleType, AttitudeProvider attitudeProvider, Frame frame) Create a mapper between raw double components and spacecraft state.
TimeStampedPVCoordinates	NumericalPropagator.getPVCoordinates(AbsoluteDate date, Frame frame) Get the PVCoordinates of the body in the selected frame.

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

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

Modifier and Type	Method and Description
protected StateMapper	DSSTPropagator.createMapper(AbsoluteDate referenceDate, double mu, OrbitType ignoredOrbitType, PositionAngle ignoredPositionAngleType, AttitudeProvider attitudeProvider, Frame frame) Create a mapper between raw double components and spacecraft state.

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

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

Constructor and Description
DSSTTesseral(Frame centralBodyFrame, double centralBodyRotationRate, UnnormalizedSphericalHarmonicsProvider provider, int maxDegreeTesseralSP, int maxOrderTesseralSP, int maxEccPowTesseralSP, int maxFrequencyShortPeriodics, int maxDegreeMdailyTesseralSP, int maxOrderMdailyTesseralSP, int maxEccPowMdailyTesseralSP) Simple constructor.

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

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

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

Uses of Frame in org.orekit.utils

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

Modifier and Type	Method and Description
TimeStampedPVCoordinates	PVCoordinatesProvider.getPVCoordinates(AbsoluteDate date, Frame frame) Get the PVCoordinates of the body in the selected frame.
PVCoordinatesProvider	TimeStampedPVCoordinates.toTaylorProvider(Frame instanceFrame) Create a local provider using simply Taylor expansion through TimeStampedPVCoordinates.shiftedBy(double).