Uses of Class
org.orekit.frames.Frame

Packages that use Frame

fr.cnes.sirius.patrius.assembly
fr.cnes.sirius.patrius.assembly.models
fr.cnes.sirius.patrius.assembly.models.cook
fr.cnes.sirius.patrius.bodies
fr.cnes.sirius.patrius.events
fr.cnes.sirius.patrius.forces
fr.cnes.sirius.patrius.forces.radiation
fr.cnes.sirius.patrius.groundstation
fr.cnes.sirius.patrius.guidance
fr.cnes.sirius.patrius.projections
fr.cnes.sirius.patrius.propagation
fr.cnes.sirius.patrius.propagation.events.multi
fr.cnes.sirius.patrius.propagation.numerical.multi
fr.cnes.sirius.patrius.propagation.precomputed.multi
fr.cnes.sirius.patrius.propagation.sampling.multi
fr.cnes.sirius.patrius.signalpropagation
fr.cnes.sirius.patrius.signalpropagation.iono
fr.cnes.sirius.patrius.stela.bodies
fr.cnes.sirius.patrius.stela.forces.atmospheres
fr.cnes.sirius.patrius.stela.forces.noninertial
fr.cnes.sirius.patrius.stela.orbits
fr.cnes.sirius.patrius.stela.propagation
fr.cnes.sirius.patrius.tools.force.validation
fr.cnes.sirius.patrius.utils
fr.cnes.sirius.patrius.wrenches
fr.cnes.sirius.validate.mocks.ephemeris
org.orekit.attitudes	This package provides classes to represent simple attitudes.
org.orekit.attitudes.directions
org.orekit.bodies	This package provides interface to represent the position and geometry of space objects such as stars, planets or asteroids.
org.orekit.forces.atmospheres
org.orekit.forces.drag
org.orekit.forces.gravity
org.orekit.forces.gravity.tides
org.orekit.forces.gravity.variations
org.orekit.forces.maneuvers	This package provides models of simple maneuvers.
org.orekit.forces.radiation
org.orekit.forces.relativistic
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 experienced in the atmosphere of the earth.
org.orekit.orbits	This package provides classes to represent orbits.
org.orekit.propagation	This package provides tools to propagate orbital states with different methods.
org.orekit.propagation.analytical
org.orekit.propagation.analytical.covariance
org.orekit.propagation.analytical.tle	This package provides classes to read and extrapolate tle's.
org.orekit.propagation.events	This package provides interfaces and classes dealing with events occurring during propagation.
org.orekit.propagation.numerical
org.orekit.propagation.precomputed
org.orekit.propagation.sampling	This package provides interfaces and classes dealing with step handling during propagation.
org.orekit.time	This independent package provides classes to handle epochs, time scales, and to compare instants together.
org.orekit.utils	This package provides useful objects.
org.orekit.wrenches

Uses of Frame in fr.cnes.sirius.patrius.assembly

Methods in fr.cnes.sirius.patrius.assembly that return Frame

Frame	MainPart.getFrame()
Frame	IPart.getFrame()

Uses of Frame in fr.cnes.sirius.patrius.assembly.models

Methods in fr.cnes.sirius.patrius.assembly.models with parameters of type Frame

Wrench	AeroWrenchModel.dragWrench(SpacecraftState state, double density, Vector3D relativeVelocity, Vector3D origin, Frame frame) Compute the torque due to radiation pressire.
Matrix3D	InertiaSimpleModel.getInertiaMatrix(Frame frame, AbsoluteDate date) Getter for the inertia matrix of the spacecraft, expressed with respect to the MASS CENTER in a given frame.
Matrix3D	InertiaComputedModel.getInertiaMatrix(Frame frame, AbsoluteDate date) Getter for the inertia matrix of the spacecraft, expressed with respect to the MASS CENTER in a given frame.
Matrix3D	IInertiaModel.getInertiaMatrix(Frame frame, AbsoluteDate date) Getter for the inertia matrix of the spacecraft, expressed with respect to the MASS CENTER in a given frame.
Matrix3D	InertiaSimpleModel.getInertiaMatrix(Frame frame, AbsoluteDate date, Vector3D inertiaReferencePoint) Getter for the inertia matrix of the spacecraft, once expressed with respect to a point that can be different from the mass center.
Matrix3D	InertiaComputedModel.getInertiaMatrix(Frame frame, AbsoluteDate date, Vector3D inertiaReferencePoint) Getter for the inertia matrix of the spacecraft, once expressed with respect to a point that can be different from the mass center.
Matrix3D	IInertiaModel.getInertiaMatrix(Frame frame, AbsoluteDate date, Vector3D inertiaReferencePoint) Getter for the inertia matrix of the spacecraft, once expressed with respect to a point that can be different from the mass center.
Vector3D	InertiaSimpleModel.getMassCenter(Frame frame, AbsoluteDate date) Getter for the mass center.
Vector3D	InertiaComputedModel.getMassCenter(Frame frame, AbsoluteDate date) Getter for the mass center.
Vector3D	IInertiaModel.getMassCenter(Frame frame, AbsoluteDate date) Getter for the mass center.
PVCoordinates	SensorModel.getPVCoordinates(AbsoluteDate date, Frame frame) Get the PVCoordinates of the sensor part in the selected frame.
Vector3D[]	SensorModel.getRefrenceAxis(Frame frame, AbsoluteDate date) Computes the reference axis of the sensor in a given frame at a date
Vector3D	SensorModel.getSightAxis(Frame frame, AbsoluteDate date) Computes the sight axis of the sensor in a given frame at a date
Wrench	DirectRadiativeWrenchModel.radiationWrench(SpacecraftState state, Vector3D flux, Vector3D origin, Frame frame) Compute the torque due to radiation pressire.

Constructors in fr.cnes.sirius.patrius.assembly.models with parameters of type Frame

InertiaSimpleModel(double mass, Vector3D massCenter, Matrix3D inertiaMatrix, Frame frame, String partName)
Constructor for a simple inertia model.

InertiaSimpleModel(double mass, Vector3D massCenter, Matrix3D inertiaMatrix, Vector3D inertiaReferencePoint, Frame frame, String partName)
Constructor for a simple inertia model; the inertia matrix is expressed with respect to a point that can be different from the mass center.

Uses of Frame in fr.cnes.sirius.patrius.assembly.models.cook

Constructors in fr.cnes.sirius.patrius.assembly.models.cook with parameters of type Frame

CnCookModel(ExtendedAtmosphere atmos, Facet afacet, Frame afacetFrame, double eps, double wallGasTemp)
Constructor with constant wall gas temperature.

CnCookModel(ExtendedAtmosphere atmos, Facet afacet, Frame afacetFrame, double eps, WallGasTemperatureProvider wallGasTemp)
Constructor.

CtCookModel(ExtendedAtmosphere atmos, Facet afacet, Frame afacetFrame, double eps)
Constructor.

Uses of Frame in fr.cnes.sirius.patrius.bodies

Methods in fr.cnes.sirius.patrius.bodies with parameters of type Frame

Line	BasicBoardSun.getLine(PVCoordinatesProvider pvCoord, AbsoluteDate date, Frame frame) Get the line from the position in pvCoord to the Sun.
Vector3D	BasicBoardSun.getVector(PVCoordinatesProvider pvCoord, AbsoluteDate date, Frame frame) Get the direction of the sun.

Uses of Frame in fr.cnes.sirius.patrius.events

Methods in fr.cnes.sirius.patrius.events that return Frame

Frame

EarthZoneDetector.getFrame() Get the frame.

Constructors in fr.cnes.sirius.patrius.events with parameters of type Frame

EarthZoneDetector(List<Vector3D[]> directionsList, Frame bodyFrame)
Constructor for the earth zones entering detector with default maxCheck and convergence threshold.

EarthZoneDetector(List<Vector3D[]> directionsList, Frame bodyFrame, double maxCheck, double threshold)
Constructor for the earth zones entering detector.

EarthZoneDetector(List<Vector3D[]> directionsList, Frame bodyFrame, double maxCheck, double threshold, EventDetector.Action entry, EventDetector.Action exit)
Constructor for the earth zones entering detector.

EarthZoneDetector(List<Vector3D[]> directionsList, Frame bodyFrame, double maxCheck, double threshold, EventDetector.Action entry, EventDetector.Action exit, boolean removeEntry, boolean removeExit)
Constructor.

Uses of Frame in fr.cnes.sirius.patrius.forces

Methods in fr.cnes.sirius.patrius.forces that return Frame

Frame

EmpiricalForce.getLocalFrame()

Methods in fr.cnes.sirius.patrius.forces with parameters of type Frame

Vector3D

EmpiricalForce.computeAcceleration(PVCoordinates pv, LocalOrbitalFrame localFrameValidation, Vector3D vectorS, Frame frame, SpacecraftState state) Method to compute the acceleration.

Constructors in fr.cnes.sirius.patrius.forces with parameters of type Frame

EmpiricalForce(int harmonicFactor, Vector3D vectorS, IParamDiffFunction ax, IParamDiffFunction ay, IParamDiffFunction az, IParamDiffFunction bx, IParamDiffFunction by, IParamDiffFunction bz, IParamDiffFunction cx, IParamDiffFunction cy, IParamDiffFunction cz, Frame coeffsFrame)
Simple constructor for an empiric force using parameterizable functions for A; B and C coef with a given frame.

EmpiricalForce(int harmonicFactor, Vector3D vectorS, Parameter ax, Parameter ay, Parameter az, Parameter bx, Parameter by, Parameter bz, Parameter cx, Parameter cy, Parameter cz, Frame coeffsFrame)
Simple constructor for an empiric force using Parameter for A; B and C coef with a given frame.

EmpiricalForce(int harmonicFactor, Vector3D vectorS, Vector3D a, Vector3D b, Vector3D c, Frame coeffsFrame)
Simple constructor for an empiric force, assigning a generic frame to the A, B, C coefficients frame.

Uses of Frame in fr.cnes.sirius.patrius.forces.radiation

Methods in fr.cnes.sirius.patrius.forces.radiation with parameters of type Frame

static double

PatriusSolarRadiationPressure.getLightningRatio(PVCoordinatesProvider sun, Vector3D satSunVector, GeometricBodyShape earthModel, Vector3D position, Frame frame, AbsoluteDate date) Get the lightning ratio ([0-1]).

Uses of Frame in fr.cnes.sirius.patrius.groundstation

Methods in fr.cnes.sirius.patrius.groundstation that return Frame

Frame

RFStationAntenna.getFrame() Returns ground station topocentric frame.

Methods in fr.cnes.sirius.patrius.groundstation with parameters of type Frame

PVCoordinates	RFStationAntenna.getPVCoordinates(AbsoluteDate date, Frame frame)
PVCoordinates	GeometricStationAntenna.getPVCoordinates(AbsoluteDate date, Frame frame) Get the PVCoordinates of the station antenna in the selected frame.

Uses of Frame in fr.cnes.sirius.patrius.guidance

Methods in fr.cnes.sirius.patrius.guidance with parameters of type Frame

static AngularVelocitiesHarmonicProfile	GuidanceProfileBuilder.computeAngularVelocitiesHarmonicProfile(AttitudeLawLeg attitude, PVCoordinatesProvider provider, Frame frame, AbsoluteDate tref, double period, int order, KinematicsToolkit.IntegrationType integType, double integStep) Compute the angular velocities harmonic guidance profile.
Attitude	QuaternionHarmonicProfile.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	QuaternionPolynomialProfile.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	AngularVelocitiesPolynomialProfile.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate userDate, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	AngularVelocitiesHarmonicProfile.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate userDate, Frame frame) Compute the attitude corresponding to an orbital state.

Constructors in fr.cnes.sirius.patrius.guidance with parameters of type Frame

AngularVelocitiesHarmonicProfile(AbsoluteDate origin, Rotation initialRotation, Frame frame, FourierSeries xAngle, FourierSeries yAngle, FourierSeries zAngle, AbsoluteDateInterval timeInterval, KinematicsToolkit.IntegrationType integType, double integStep)
Create a harmonic, angular velocities guidance profile.

AngularVelocitiesPolynomialProfile(Frame frame, AbsoluteDateInterval timeInterval, Rotation initialRotation, List<Vector3DPolynomialSegment> polynomials, KinematicsToolkit.IntegrationType integType, double integStep)
Create a polynomial, angular velocity guidance profile.

QuaternionHarmonicProfile(AbsoluteDate origin, Frame frame, FourierSeries q0, FourierSeries q1, FourierSeries q2, FourierSeries q3, AbsoluteDateInterval timeInterval)
Create a harmonic, quaternion guidance profile.

QuaternionPolynomialProfile(Frame frame, AbsoluteDateInterval timeInterval, List<QuaternionPolynomialSegment> polynomials)
Create a polynomial, quaternion guidance profile.

Uses of Frame in fr.cnes.sirius.patrius.projections

Constructors in fr.cnes.sirius.patrius.projections with parameters of type Frame

ProjectionEllipsoid(double ae, double f, Frame bodyFrame, String name)
Constructor for the body ellipsoid.

Uses of Frame in fr.cnes.sirius.patrius.propagation

Methods in fr.cnes.sirius.patrius.propagation that return Frame

Frame

MultiPropagator.getFrame(String satId) Get the frame in which the orbit is propagated.

Constructors in fr.cnes.sirius.patrius.propagation with parameters of type Frame

PVCoordinatePropagator(PVCoordinatesProvider pvCoordProvider, AbsoluteDate initDate, double mu, Frame frame)
Creates an instance of PVCoordinatePropagator without attitude and additional state providers

PVCoordinatePropagator(PVCoordinatesProvider pvCoordProvider, AbsoluteDate initDate, double mu, Frame frame, AttitudeProvider attProviderForces, AttitudeProvider attProviderEvents, List<AdditionalStateProvider> additionalStateProviders)
Creates an instance of PVCoordinatePropagator with PV, attitude for forces, attitude for events, and additional state providers given by the user.

Uses of Frame in fr.cnes.sirius.patrius.propagation.events.multi

Constructors in fr.cnes.sirius.patrius.propagation.events.multi with parameters of type Frame

AdaptedMonoEventDetector(EventDetector detector, OrbitType orbitType, PositionAngle angleType, AttitudeProvider attProviderForces, AttitudeProvider attProviderEvents, AbsoluteDate referenceDate, double mu, Frame integrationFrame, MultiStateVectorInfo stateVectorInfo, String satId)
Build a wrapped event detector.

Constructor parameters in fr.cnes.sirius.patrius.propagation.events.multi with type arguments of type Frame

AdaptedMultiEventDetector(MultiEventDetector detector, OrbitType orbitType, PositionAngle angleType, Map<String,AttitudeProvider> attProvidersForces, Map<String,AttitudeProvider> attProvidersEvents, AbsoluteDate referenceDate, Map<String,Double> muMap, Map<String,Frame> framesMap, MultiStateVectorInfo stateVectorInfo)
Build a wrapped multi-sat event detector.

Uses of Frame in fr.cnes.sirius.patrius.propagation.numerical.multi

Methods in fr.cnes.sirius.patrius.propagation.numerical.multi that return Frame

Frame

MultiNumericalPropagator.getFrame(String satId)

Methods in fr.cnes.sirius.patrius.propagation.numerical.multi with parameters of type Frame

PVCoordinates	MultiNumericalPropagator.getPVCoordinates(AbsoluteDate date, Frame frame, String satId) Get the PVCoordinates of the body in the selected frame.
SpacecraftState	MultiStateVectorInfo.mapArrayToState(double[] y, AbsoluteDate currentDate, OrbitType orbitType, PositionAngle angleType, AttitudeProvider attProviderForces, AttitudeProvider attProviderEvents, double mu, Frame integrationFrame, String satId) Extract a given SpacecraftState from the state vector.
void	MultiNumericalPropagator.setOrbitFrame(String satId, Frame frame) Set a frame for propagation The initial state must have first been added using the MultiNumericalPropagator.addInitialState(SpacecraftState, String) method before defining the associated integration frame.

Method parameters in fr.cnes.sirius.patrius.propagation.numerical.multi with type arguments of type Frame

void	MultiEphemerisModeHandler.initialize(OrbitType orbit, PositionAngle angle, Map<String,AttitudeProvider> attitudeProvidersForces, Map<String,AttitudeProvider> attitudeProvidersEvents, MultiStateVectorInfo stateVectorInfo, boolean activateHandlers, AbsoluteDate reference, Map<String,Frame> frame, Map<String,Double> mu) Initialize the mode handler.
void	MultiModeHandler.initialize(OrbitType orbit, PositionAngle angle, Map<String,AttitudeProvider> attitudeProvidersForces, Map<String,AttitudeProvider> attitudeProvidersEvents, MultiStateVectorInfo stateVectorInfo, boolean activateHandlers, AbsoluteDate reference, Map<String,Frame> frame, Map<String,Double> mu) Initialize the mode handler.
Map<String,SpacecraftState>	MultiStateVectorInfo.mapArrayToStates(double[] y, AbsoluteDate currentDate, OrbitType orbitType, PositionAngle angleType, Map<String,AttitudeProvider> attProvidersForces, Map<String,AttitudeProvider> attProvidersEvents, Map<String,Double> mu, Map<String,Frame> integrationFrame) Convert state vector into a Map of SpacecraftState

Uses of Frame in fr.cnes.sirius.patrius.propagation.precomputed.multi

Methods in fr.cnes.sirius.patrius.propagation.precomputed.multi with parameters of type Frame

PVCoordinates

MultiIntegratedEphemeris.getPVCoordinates(AbsoluteDate date, Frame frame) Get the PVCoordinates of the body in the selected frame.

Constructors in fr.cnes.sirius.patrius.propagation.precomputed.multi with parameters of type Frame

MultiIntegratedEphemeris(List<AbsoluteDate> startDatesIn, List<AbsoluteDate> minDatesIn, List<AbsoluteDate> maxDatesIn, OrbitType orbitTypeIn, PositionAngle angleTypeIn, AttitudeProvider attitudeProviderForces, AttitudeProvider attitudeProviderEvents, MultiStateVectorInfo stateInfos, List<ContinuousOutputModel> modelsIn, Frame referenceFrameIn, double muIn, String satIdIn)
Creates a new instance of IntegratedEphemeris.

Uses of Frame in fr.cnes.sirius.patrius.propagation.sampling.multi

Method parameters in fr.cnes.sirius.patrius.propagation.sampling.multi with type arguments of type Frame

void

MultiAdaptedStepHandler.initialize(OrbitType orbit, PositionAngle angle, Map<String,AttitudeProvider> attProvidersForces, Map<String,AttitudeProvider> attProvidersEvents, MultiStateVectorInfo stateVectorInfo, boolean activateHandlers, AbsoluteDate reference, Map<String,Frame> frameMap, Map<String,Double> muMap) Initialize the mode handler.

Uses of Frame in fr.cnes.sirius.patrius.signalpropagation

Methods in fr.cnes.sirius.patrius.signalpropagation with parameters of type Frame

Vector3D

SignalPropagation.getVector(Frame expressionFrame)

Constructors in fr.cnes.sirius.patrius.signalpropagation with parameters of type Frame

SignalPropagation(Vector3D propagationVector, AbsoluteDate inEmissionDate, AbsoluteDate inReceptionDate, Frame refFrame, SignalPropagationModel.FixedDate fixedDate)
Constructor with computation of one of the dates

SignalPropagationModel(Frame frame, double threshold)
Constructor of the signal propagation model.

Uses of Frame in fr.cnes.sirius.patrius.signalpropagation.iono

Methods in fr.cnes.sirius.patrius.signalpropagation.iono with parameters of type Frame

double	BentModel.computeElectronicCont(AbsoluteDate date, Vector3D satellite, Frame frameSat) Computation of the electric content between the station and the satellite at a date.
double	BentModel.computeSignalDelay(AbsoluteDate date, Vector3D satellite, Frame frameSat)
double	IonosphericCorrection.computeSignalDelay(AbsoluteDate date, Vector3D satellite, Frame satFrame) Calculates the ionospheric signal delay for the signal path from the position of the transmitter and the receiver and the current date.

Constructors in fr.cnes.sirius.patrius.signalpropagation.iono with parameters of type Frame

BentModel(R12Provider r12Provider, SolarActivityDataProvider solarActivity, USKProvider uskProvider, BodyShape earth, Vector3D inStation, Frame inFrameSta, double freq)
Constructor for the Bent ionospheric correction model.

Uses of Frame in fr.cnes.sirius.patrius.stela.bodies

Methods in fr.cnes.sirius.patrius.stela.bodies with parameters of type Frame

PVCoordinates	MeeusSunStela.getPVCoordinates(AbsoluteDate date, Frame frame) Deprecated.
PVCoordinates	MeeusMoonStela.getPVCoordinates(AbsoluteDate date, Frame frame)
static void	MeeusSunStela.updateTransform(AbsoluteDate date, Frame frame) Deprecated. Update cached transform from FramesFactory.getMOD(boolean) to provided frame.
static void	MeeusMoonStela.updateTransform(AbsoluteDate date, Frame frame) Update cached transform from FramesFactory.getMOD(boolean) to provided frame.

Uses of Frame in fr.cnes.sirius.patrius.stela.forces.atmospheres

Methods in fr.cnes.sirius.patrius.stela.forces.atmospheres with parameters of type Frame

AtmosphereData	MSIS00Adapter.getData(AbsoluteDate date, Vector3D position, Frame frame) Get detailed atmospheric data.
double	MSIS00Adapter.getDensity(AbsoluteDate date, Vector3D position, Frame frame) Get the local density.
double	MSIS00Adapter.getSpeedOfSound(AbsoluteDate date, Vector3D position, Frame frame) Get the local speed of sound.
Vector3D	MSIS00Adapter.getVelocity(AbsoluteDate date, Vector3D position, Frame frame)

Uses of Frame in fr.cnes.sirius.patrius.stela.forces.noninertial

Methods in fr.cnes.sirius.patrius.stela.forces.noninertial with parameters of type Frame

Vector3D	NonInertialContribution.computeOmega(AbsoluteDate date, Frame frame1, Frame frame2) Compute rotation vector of frame2 with respect to frame1 expressed in frame2, which is the rotation vector from frame1 to frame2.
Vector3D	NonInertialContribution.computeOmegaDerivative(AbsoluteDate date, Frame frame1, Frame frame2, double dt) Compute rotation vector derivative from frame1 to frame2 using finite differences.

Constructors in fr.cnes.sirius.patrius.stela.forces.noninertial with parameters of type Frame

NonInertialContribution(int quadPointsIn, Frame referenceSystemIn)
Constructor.

Uses of Frame in fr.cnes.sirius.patrius.stela.orbits

Methods in fr.cnes.sirius.patrius.stela.orbits with parameters of type Frame

PVCoordinates

StelaEquinoctialOrbit.getPVCoordinates(AbsoluteDate otherDate, Frame otherFrame)

Constructors in fr.cnes.sirius.patrius.stela.orbits with parameters of type Frame

StelaEquinoctialOrbit(double aIn, double exIn, double eyIn, double ixIn, double iyIn, double lMIn, Frame frame, AbsoluteDate date, double mu)
Creates a new instance.

StelaEquinoctialOrbit(double aIn, double exIn, double eyIn, double ixIn, double iyIn, double lMIn, Frame frame, AbsoluteDate date, double mu, boolean isCorrectedIn)
Creates a new instance.

StelaEquinoctialOrbit(IOrbitalParameters params, Frame frame, AbsoluteDate date)
Creates a new instance.

StelaEquinoctialOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu)
Constructor from cartesian parameters.

Uses of Frame in fr.cnes.sirius.patrius.stela.propagation

Methods in fr.cnes.sirius.patrius.stela.propagation that return Frame

Frame

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

Methods in fr.cnes.sirius.patrius.stela.propagation with parameters of type Frame

PVCoordinates	StelaAbstractPropagator.getPVCoordinates(AbsoluteDate date, Frame frame) Get the PVCoordinates of the body in the selected frame.
void	StelaAbstractPropagator.setOrbitFrame(Frame frame) Set propagation frame.

Uses of Frame in fr.cnes.sirius.patrius.tools.force.validation

Methods in fr.cnes.sirius.patrius.tools.force.validation with parameters of type Frame

PVCoordinates

BasicPVCoordinatesProvider.getPVCoordinates(AbsoluteDate date, Frame inFrame) Get the PVCoordinates of the body in the selected frame.

Constructors in fr.cnes.sirius.patrius.tools.force.validation with parameters of type Frame

BasicPVCoordinatesProvider(PVCoordinates inCoordinates, Frame inFrame)
Build a direction from an origin and a target described by their PVCoordinatesProvider

Uses of Frame in fr.cnes.sirius.patrius.utils

Methods in fr.cnes.sirius.patrius.utils with parameters of type Frame

PVCoordinates

AlmanacPVCoordinates.getPVCoordinates(AbsoluteDate date, Frame frame) Geometric computation of the position to a date.

Uses of Frame in fr.cnes.sirius.patrius.wrenches

Methods in fr.cnes.sirius.patrius.wrenches with parameters of type Frame

Vector3D	SolarRadiationWrench.computeTorque(SpacecraftState s, Vector3D origin, Frame frame) Compute the resulting wrench.
Vector3D	GravitationalAttractionWrench.computeTorque(SpacecraftState s, Vector3D origin, Frame frame) Compute the resulting wrench.
Vector3D	DragWrench.computeTorque(SpacecraftState s, Vector3D origin, Frame frame) Compute the resulting wrench.
Vector3D	GenericWrenchModel.computeTorque(SpacecraftState s, Vector3D origin, Frame frame) Compute the resulting wrench.
Vector3D	MagneticWrench.computeTorque(SpacecraftState s, Vector3D origin, Frame frame) Compute the resulting wrench.
Wrench	SolarRadiationWrench.computeWrench(SpacecraftState s, Vector3D origin, Frame frame) Compute the resulting wrench.
Wrench	GravitationalAttractionWrench.computeWrench(SpacecraftState s, Vector3D origin, Frame frame) Compute the resulting wrench.
Wrench	DragWrench.computeWrench(SpacecraftState s, Vector3D origin, Frame frame) Compute the resulting wrench.
Wrench	GenericWrenchModel.computeWrench(SpacecraftState s, Vector3D origin, Frame frame) Compute the resulting wrench.
Wrench	MagneticWrench.computeWrench(SpacecraftState s, Vector3D origin, Frame frame) Compute the resulting wrench.
Wrench	DragWrenchSensitive.dragWrench(SpacecraftState state, double density, Vector3D relativeVelocity, Vector3D origin, Frame frame) Compute the torque due to radiation pressire.
Wrench	RadiationWrenchSensitive.radiationWrench(SpacecraftState state, Vector3D flux, Vector3D origin, Frame frame) Compute the torque due to radiation pressire.

Uses of Frame in fr.cnes.sirius.validate.mocks.ephemeris

Methods in fr.cnes.sirius.validate.mocks.ephemeris that return Frame

Frame	UserEphemeris.getReferenceFrame()
Frame	IUserEphemeris.getReferenceFrame()

Methods in fr.cnes.sirius.validate.mocks.ephemeris with parameters of type Frame

PVCoordinates	UserCelestialBody.getPVCoordinates(AbsoluteDate date, Frame frame) Computes the PV coordinates at a date using linear interpolator.
PVCoordinates	UserCelestialBody.getPVCoordinatesLagrange4(AbsoluteDate date, Frame frame) Computes the PV coordinates at a date using Lagrange 4 interpolator.

Constructors in fr.cnes.sirius.validate.mocks.ephemeris with parameters of type Frame

UserEphemeris(String ephemerisFile, DateComponents referenceEpoch, TimeScale timeScale, Frame frame)
Constructor.

Uses of Frame in org.orekit.attitudes

Subclasses of Frame in org.orekit.attitudes

class	AttitudeFrame This class is a special implementation of the Frame class; it represents a dynamic spacecraft frame, i.e.
class	OrientationFrame This class is a special implementation of the Frame class; it represents a dynamic orientation frame, i.e.

Fields in org.orekit.attitudes declared as Frame

protected Frame

AbstractIsisSpinBiasSlew.refFrame Reference frame.

Methods in org.orekit.attitudes that return Frame

Frame	GroundPointing.getBodyFrame() Get the body frame.
Frame	Attitude.getReferenceFrame() Get the reference frame.

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

SortedSet<Attitude>	AbstractAttitudeEphemerisGenerator.generateEphemeris(AbsoluteDateInterval ephemerisInterval, Frame frame) Computes attitude ephemeris using a fixed or variable time step and choosing the interval of validity.
SortedSet<Attitude>	AbstractAttitudeEphemerisGenerator.generateEphemeris(Frame frame) Computes attitude ephemeris using a fixed or variable time step.
Attitude	Slew.getAttitude(AbsoluteDate date, Frame frame) Compute the attitude.
Attitude	ConstantSpinSlew.getAttitude(AbsoluteDate date, Frame frame)
Attitude	AbstractIsisSpinBiasSlew.getAttitude(AbsoluteDate date, Frame frame) Compute the attitude.
Attitude	TwoSpinBiasSlew.getAttitude(AbsoluteDate date, Frame frame)
Attitude	ComposedAttitudeLaw.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Attitude	BodyCenterPointing.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	TargetPointing.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	ConstantAttitudeLaw.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	AttitudeLawLeg.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Attitude	YawCompensation.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	YawSteering.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	LofOffset.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	RelativeTabulatedAttitudeLaw.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	IsisSunPointing.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	TwoDirectionsAttitude.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	AttitudeLegLaw.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	TabulatedAttitude.getAttitude(PVCoordinatesProvider pvProvider, AbsoluteDate date, Frame inFrame) 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	AbstractSlew.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
Attitude	AttitudeLegsSequence.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Gets the attitude from the sequence. The AttitudeLeg matching the date is called to compute the attitude.
Attitude	RelativeTabulatedAttitudeLeg.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	LofOffsetPointing.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	SpinStabilized.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	FixedRate.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	AttitudesSequence.getAttitude(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the attitude corresponding to an orbital state.
Attitude	GroundPointingWrapper.getBaseState(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the base system state at given date, without compensation.
abstract TimeStampedAngularCoordinates	GroundPointingWrapper.getCompensation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame, Attitude base) Compute the TimeStampedAngularCoordinates at a given time.
TimeStampedAngularCoordinates	YawCompensation.getCompensation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame orbitFrame, Attitude base) Compute the TimeStampedAngularCoordinates at a given time.
TimeStampedAngularCoordinates	YawSteering.getCompensation(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame orbitFrame, Attitude base) Compute the TimeStampedAngularCoordinates at a given time.
Attitude	AttitudeLegsSequence.getOldAttitudeOnTransition(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Returns the attitude at a transition date for the old attitude law (the law previous to the valid transition law).
Rotation	DirectionTrackingOrientation.getOrientation(AbsoluteDate date, Frame frame)
Rotation	IOrientationLaw.getOrientation(AbsoluteDate date, Frame frame) Gets the rotation defining the orientation with respect to a given frame at a given date.
Vector3D	TwoSpinBiasSlew.getSpinDerivatives(AbsoluteDate date, Frame frame) get the spin derivatives (default implementation : finite differences differentiator).
Vector3DFunction	TwoSpinBiasSlew.getSpinFunction(Frame frame, AbsoluteDate zeroAbscissa)
protected Vector3D	GroundPointingWrapper.getTargetPoint(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the target point in specified frame.
protected Vector3D	TargetGroundPointing.getTargetPoint(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the target point in specified frame.
protected Vector3D	BodyCenterGroundPointing.getTargetPoint(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
protected Vector3D	LofOffsetPointing.getTargetPoint(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the target point in specified frame.
protected Vector3D	NadirPointing.getTargetPoint(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the target point in specified frame.
protected abstract Vector3D	GroundPointing.getTargetPoint(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the target point in specified frame.
protected TimeStampedPVCoordinates	GroundPointingWrapper.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame) Compute the target point position/velocity in specified frame.
TimeStampedPVCoordinates	NadirPointing.getTargetPV(PVCoordinatesProvider pvProv, AbsoluteDate date, Frame frame)
protected TimeStampedPVCoordinates	GroundPointing.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.
static Attitude	Attitude.slerp(AbsoluteDate date, Attitude attitude1, Attitude attitude2, Frame frame, boolean computeSpinDerivative) The slerp interpolation method is efficient but is less accurate than the interpolate method.
Attitude	Attitude.withReferenceFrame(Frame newReferenceFrame) Get a similar attitude with a specific reference frame.
Attitude	Attitude.withReferenceFrame(Frame newReferenceFrame, boolean spinDerivativesComputation) Get a similar attitude with a specific reference frame.

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

Attitude(AbsoluteDate date, Frame referenceFrame, AngularCoordinates orientation)
Creates a new instance.

Attitude(AbsoluteDate date, Frame referenceFrame, Rotation attitude, Vector3D spin)
Creates a new instance.

Attitude(AbsoluteDate date, Frame referenceFrame, Rotation attitude, Vector3D spin, Vector3D acceleration)
Creates a new instance.

Attitude(double[] y, AbsoluteDate date, Frame referenceFrame)
Creates a new instance from an array containing a quaternion and a spin vector.

Attitude(Frame referenceFrame, TimeStampedAngularCoordinates orientation)
Creates a new instance.

AttitudeFrame(PVCoordinatesProvider pvProvider, AttitudeLaw attitudeLaw, Frame referenceFrame)
Constructor of the dynamic spacecraft frame.

AttitudeTransformProvider(AttitudeLaw law, PVCoordinatesProvider pv, Frame frame)
Protected constructor.

BodyCenterPointing(Frame bodyFrame)
Creates new instance.

CelestialBodyPointed(Frame pCelestialFrame, PVCoordinatesProvider pPointedBody, Vector3D pPhasingCel, Vector3D pPointingSat, Vector3D pPhasingSat)
Creates new instance.

ConstantAttitudeLaw(Frame referenceFrame, Rotation rotation)
Creates new instance.

LofOffset(Frame inertialFrame, LOFType type)
Create a LOF-aligned attitude.

LofOffset(Frame pInertialFrame, LOFType type, RotationOrder order, double alpha1, double alpha2, double alpha3)
Creates new instance.

OrientationTransformProvider(IOrientationLaw law, Frame frame)
Protected constructor.

RelativeTabulatedAttitudeLaw(AbsoluteDate refDate, List<Pair<Double,AngularCoordinates>> angularCoordinates, Frame frame, RelativeTabulatedAttitudeLaw.AroundAttitudeType lawBefore, RelativeTabulatedAttitudeLaw.AroundAttitudeType lawAfter)
Create a RelativeTabulatedAttitudeLaw object with list of Angular Coordinates (during the interval of validity), a law before the interval and a law after the interval.

RelativeTabulatedAttitudeLaw(Frame frame, AbsoluteDate refDate, List<Pair<Double,Rotation>> orientations, RelativeTabulatedAttitudeLaw.AroundAttitudeType lawBefore, RelativeTabulatedAttitudeLaw.AroundAttitudeType lawAfter)
Create a RelativeTabulatedAttitudeLaw object with list of rotations (during the interval of validity), a law before the interval and a law after the interval.

RelativeTabulatedAttitudeLeg(AbsoluteDate referenceDate, Frame frame, List<Pair<Double,AngularCoordinates>> angularCoordinates)
Build a RelativeTabulatedAttitudeLeg with a reference date, a list of angular coordinates associated with a double representing the time elapsed since the reference date.

RelativeTabulatedAttitudeLeg(AbsoluteDate referenceDate, List<Pair<Double,AngularCoordinates>> angularCoordinates, int nbInterpolationPoints, Frame frame)
Build a RelativeTabulatedAttitudeLeg with a reference date, a list of angular coordinates associated with a double representing the time elapsed since the reference date and a number of points used for interpolation.

RelativeTabulatedAttitudeLeg(AbsoluteDate referenceDate, List<Pair<Double,Rotation>> orientations, Frame frame)
Build a RelativeTabulatedAttitudeLeg with a reference date, a list of Rotations associated with a double representing the time elapsed since the reference date.

RelativeTabulatedAttitudeLeg(AbsoluteDate referenceDate, List<Pair<Double,Rotation>> orientations, Frame frame, int nbInterpolationPoints)
Build a RelativeTabulatedAttitudeLeg with a reference date, a list of Rotations associated with a double representing the time elapsed since the reference date and a number of points used for interpolation.

TargetPointing(Frame bodyFrame, Vector3D target)
Creates a new instance from body frame and target expressed in cartesian coordinates.

Uses of Frame in org.orekit.attitudes.directions

Methods in org.orekit.attitudes.directions that return Frame

Frame

ConstantVectorDirection.getFrame()

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

Line	IDirection.getLine(PVCoordinatesProvider pvCoord, AbsoluteDate date, Frame frame) Provides the line containing the origin (given PV coordinates) and directed by the direction vector.
Line	NadirDirection.getLine(PVCoordinatesProvider pvCoord, AbsoluteDate date, Frame frame)
Line	MomentumDirection.getLine(PVCoordinatesProvider origin, AbsoluteDate date, Frame frame) Provides the line containing the origin (given PV coordinates) and directed by the direction vector.
Line	GlintApproximatePointingDirection.getLine(PVCoordinatesProvider origin, AbsoluteDate date, Frame frame) Provides the line containing the origin (given PV coordinates) and directed by the direction vector.
Line	EarthToCelestialBodyCenterDirection.getLine(PVCoordinatesProvider pvCoord, AbsoluteDate date, Frame frame) Provides the line containing the origin (given PV coordinates) and directed by the direction vector.
Line	GenericTargetDirection.getLine(PVCoordinatesProvider origin, AbsoluteDate date, Frame frame) Provides the line containing the origin (given PV coordinates) and directed by the direction vector.
Line	ConstantVectorDirection.getLine(PVCoordinatesProvider pvCoord, AbsoluteDate date, Frame frame) Provides the line containing the given origin point and directed by the direction vector
Line	EarthCenterDirection.getLine(PVCoordinatesProvider pvCoord, AbsoluteDate date, Frame frame) Provides the line containing the origin (given PV coordinates) and directed by the direction vector.
Line	CrossProductDirection.getLine(PVCoordinatesProvider pvCoord, AbsoluteDate date, Frame frame) Provides the line containing the origin (given PV coordinates) and directed by the cross product of directions.
Line	GroundVelocityDirection.getLine(PVCoordinatesProvider pvCoord, AbsoluteDate date, Frame frame)
Line	CelestialBodyPolesAxisDirection.getLine(PVCoordinatesProvider pvCoord, AbsoluteDate date, Frame frame) Provides the line containing the origin (given PV coordinates) and directed by the direction vector.
Line	VelocityDirection.getLine(PVCoordinatesProvider origin, AbsoluteDate date, Frame frame) Provides the line containing the origin (given PV coordinates) and directed by the direction vector.
Line	ToCelestialBodyCenterDirection.getLine(PVCoordinatesProvider origin, AbsoluteDate date, Frame frame) Provides the line containing the origin (given PV coordinates) and directed by the direction vector.
PVCoordinates	ITargetDirection.getTargetPVCoordinates(AbsoluteDate date, Frame frame) Provides the target point at a given date in a given frame, represented by the associated PVCoordinates object
PVCoordinates	EarthToCelestialBodyCenterDirection.getTargetPVCoordinates(AbsoluteDate date, Frame frame) Provides the target point at a given date in a given frame, represented by the associated PVCoordinates object
PVCoordinates	GenericTargetDirection.getTargetPVCoordinates(AbsoluteDate date, Frame frame) Provides the target point at a given date in a given frame, represented by the associated PVCoordinates object
PVCoordinates	EarthCenterDirection.getTargetPVCoordinates(AbsoluteDate date, Frame frame) Provides the target point at a given date in a given frame, represented by the associated PVCoordinates object
PVCoordinates	ToCelestialBodyCenterDirection.getTargetPVCoordinates(AbsoluteDate date, Frame frame) Provides the target point at a given date in a given frame, represented by the associated PVCoordinates object
Vector3D	IDirection.getVector(PVCoordinatesProvider pvCoord, AbsoluteDate date, Frame frame) Provides the direction vector at a given date in a given frame.
Vector3D	NadirDirection.getVector(PVCoordinatesProvider pvCoord, AbsoluteDate date, Frame frame)
Vector3D	MomentumDirection.getVector(PVCoordinatesProvider origin, AbsoluteDate date, Frame frame) Provides the direction vector at a given date in a given frame.
Vector3D	GlintApproximatePointingDirection.getVector(PVCoordinatesProvider origin, AbsoluteDate date, Frame frame) Provides the direction vector at a given date in a given frame.
Vector3D	EarthToCelestialBodyCenterDirection.getVector(PVCoordinatesProvider pvCoord, AbsoluteDate date, Frame frame) Provides the direction vector at a given date in a given frame.
Vector3D	GenericTargetDirection.getVector(PVCoordinatesProvider origin, AbsoluteDate date, Frame frame) Provides the direction vector at a given date in a given frame.
Vector3D	ConstantVectorDirection.getVector(PVCoordinatesProvider pvCoord, AbsoluteDate date, Frame frame) Provides the direction vector at a given date in a given frame.
Vector3D	EarthCenterDirection.getVector(PVCoordinatesProvider pvCoord, AbsoluteDate date, Frame frame) Provides the direction vector at a given date in a given frame.
Vector3D	CrossProductDirection.getVector(PVCoordinatesProvider pvCoord, AbsoluteDate date, Frame frame) Provides the cross product of direction1 vector and dirction2 vector.
Vector3D	GroundVelocityDirection.getVector(PVCoordinatesProvider pvCoord, AbsoluteDate date, Frame frame)
Vector3D	CelestialBodyPolesAxisDirection.getVector(PVCoordinatesProvider pvCoord, AbsoluteDate date, Frame frame) Provides the direction vector at a given date in a given frame.
Vector3D	VelocityDirection.getVector(PVCoordinatesProvider origin, AbsoluteDate date, Frame frame) Provides the direction vector at a given date in a given frame.
Vector3D	ToCelestialBodyCenterDirection.getVector(PVCoordinatesProvider origin, AbsoluteDate date, Frame frame) Provides the direction vector at a given date in a given frame.

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

ConstantVectorDirection(Vector3D inVector, Frame inFrame)
Build a direction from a frame and a vector constant in this frame

VelocityDirection(Frame referenceFrame)
Build a Direction defined for any PVCoordinatesProvider origin by its velocity vector with respect to a reference frame.

Uses of Frame in org.orekit.bodies

Fields in org.orekit.bodies declared as Frame

protected Frame

MeeusSun.MODEL.inertialSunFrame Sun inertially oriented frame.

Methods in org.orekit.bodies that return Frame

Frame	BodyShape.getBodyFrame() Get body frame related to body shape.
Frame	ExtendedOneAxisEllipsoid.getBodyFrame()
Frame	OneAxisEllipsoid.getBodyFrame() Get the body frame related to body shape.
Frame	CelestialBody.getBodyOrientedFrame() Get a body oriented, body centered frame.
Frame	AbstractCelestialBody.getBodyOrientedFrame() Get a body oriented, body centered frame.
Frame	CelestialBody.getFrame() Deprecated. as of 6.0 replaced by CelestialBody.getInertiallyOrientedFrame()
Frame	AbstractCelestialBody.getFrame() Deprecated.
Frame	CelestialBody.getInertiallyOrientedFrame() Get an inertially oriented, body centered frame.
Frame	AbstractCelestialBody.getInertiallyOrientedFrame() Get an inertially oriented, body centered frame.

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

double	GeometricBodyShape.distanceTo(Line line, Frame frame, AbsoluteDate date) Computes the distance to a line.
double	ExtendedOneAxisEllipsoid.distanceTo(Line line, Frame frame, AbsoluteDate date)
GeodeticPoint	BodyShape.getIntersectionPoint(Line line, Vector3D close, Frame frame, AbsoluteDate date) Get the intersection point of a line with the surface of the body.
GeodeticPoint	ExtendedOneAxisEllipsoid.getIntersectionPoint(Line line, Vector3D close, Frame frame, AbsoluteDate date)
GeodeticPoint	OneAxisEllipsoid.getIntersectionPoint(Line line, Vector3D close, Frame frame, AbsoluteDate date) Get the intersection point of a line with the surface of the body.
Vector3D[]	GeometricBodyShape.getIntersectionPoints(Line line, Frame frame, AbsoluteDate date) Compute the intersection points with a line.
Vector3D[]	ExtendedOneAxisEllipsoid.getIntersectionPoints(Line line, Frame frame, AbsoluteDate date)
double	GeometricBodyShape.getLocalRadius(Vector3D position, Frame frame, AbsoluteDate date, PVCoordinatesProvider occultedBody) Calculate the apparent radius.
double	ExtendedOneAxisEllipsoid.getLocalRadius(Vector3D position, Frame frame, AbsoluteDate date, PVCoordinatesProvider occultedBody)
PVCoordinates	MeeusMoon.getPVCoordinates(AbsoluteDate date, Frame frame)
PVCoordinates	ExtendedOneAxisEllipsoid.getPVCoordinates(AbsoluteDate date, Frame frame)
PVCoordinates	MeeusSun.getPVCoordinates(AbsoluteDate date, Frame frame)
abstract PVCoordinates	AbstractCelestialBody.getPVCoordinates(AbsoluteDate date, Frame frame) Get the PVCoordinates of the body in the selected frame.
GeodeticPoint	BodyShape.transform(Vector3D point, Frame frame, AbsoluteDate date) Transform a cartesian point to a surface-relative point.
GeodeticPoint	ExtendedOneAxisEllipsoid.transform(Vector3D point, Frame frame, AbsoluteDate date)
GeodeticPoint	OneAxisEllipsoid.transform(Vector3D point, Frame frame, AbsoluteDate date) Transform a cartesian point to a surface-relative point.
GeodeticPoint	OneAxisEllipsoid.transformAndComputeJacobian(Vector3D point, Frame frame, AbsoluteDate date, double[][] jacobian) Transform a cartesian point to a surface-relative point and compute the jacobian of the transformation.
static void	MeeusSun.updateTransform(AbsoluteDate date, Frame frame) Update cached transform from FramesFactory.getMOD(boolean) to provided frame.

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

AbstractCelestialBody(String name, double gm, IAUPole iauPole, Frame definingFrame, String inertialFrameName, String bodyFrameName)
Build an instance and the underlying frame.

ExtendedOneAxisEllipsoid(double ae, double f, Frame bodyFrame, String name)
Constructor for the body spheroid.

OneAxisEllipsoid(double ae, double f, Frame bodyFrame)
Simple constructor.

Uses of Frame in org.orekit.forces.atmospheres

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

AtmosphereData	DTM2000.getData(AbsoluteDate date, Vector3D position, Frame frame) Get detailed atmospheric data.
AtmosphereData	ExtendedAtmosphere.getData(AbsoluteDate date, Vector3D position, Frame frame) Get detailed atmospheric data.
AtmosphereData	MSISE2000.getData(AbsoluteDate date, Vector3D position, Frame frame) Get detailed atmospheric data.
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.
double	SimpleExponentialAtmosphere.getDensity(AbsoluteDate date, Vector3D position, Frame frame) Get the local density.
double	MSISE2000.getDensity(AbsoluteDate date, Vector3D position, Frame frame) Get the local density.
double	US76.getDensity(AbsoluteDate date, Vector3D position, Frame frame) Get the local density for altitude in interval [0, 1E6] m
double	JB2006.getDensity(AbsoluteDate date, Vector3D position, Frame frame) Get the local density.
double	US76.getPress(AbsoluteDate date, Vector3D position, Frame frame) Get the local pressure for altitude in interval [0, 1E6] m
double	DTM2000.getSpeedOfSound(AbsoluteDate date, Vector3D position, Frame frame) Get the local speed of sound.
double	Atmosphere.getSpeedOfSound(AbsoluteDate date, Vector3D position, Frame frame) Get the local speed of sound.
double	HarrisPriester.getSpeedOfSound(AbsoluteDate date, Vector3D position, Frame frame) Get the local speed of sound.
double	SimpleExponentialAtmosphere.getSpeedOfSound(AbsoluteDate date, Vector3D position, Frame frame) Get the local speed of sound.
double	MSISE2000.getSpeedOfSound(AbsoluteDate date, Vector3D position, Frame frame) Get the local speed of sound.
double	US76.getSpeedOfSound(AbsoluteDate date, Vector3D position, Frame frame) Get the local speed of sound.
double	JB2006.getSpeedOfSound(AbsoluteDate date, Vector3D position, Frame frame) Get the local speed of sound.
double	US76.getTemp(AbsoluteDate date, Vector3D position, Frame frame) Get the local temperature for altitude in interval [0, 1E6] m
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 spacecraft velocity relative to the atmosphere.
Vector3D	HarrisPriester.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 spacecraft velocity relative to the atmosphere.
Vector3D	MSISE2000.getVelocity(AbsoluteDate date, Vector3D position, Frame frame) Get the spacecraft velocity relative to the atmosphere.
Vector3D	US76.getVelocity(AbsoluteDate date, Vector3D position, Frame frame) Get the spacecraft velocity relative to the atmosphere.
Vector3D	JB2006.getVelocity(AbsoluteDate date, Vector3D position, Frame frame) Get the inertial velocity of atmosphere molecules.

Uses of Frame in org.orekit.forces.drag

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

static Vector3D

DragForce.computeAcceleration(PVCoordinates pv, Frame frame, Atmosphere atm, AbsoluteDate date, double kD, double mass) Method to compute the acceleration.

Uses of Frame in org.orekit.forces.gravity

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

Vector3D	ThirdBodyAttraction.computeAcceleration(PVCoordinates pv, Frame frame, AbsoluteDate date) Method to compute the acceleration.
Vector3D	NewtonianAttraction.computeAcceleration(PVCoordinates pv, Frame frame, AbsoluteDate date) Method to compute the acceleration.
static Vector3D	GravityToolbox.computeDrozinerAcceleration(PVCoordinates pv, Frame frame, double[][] coefficientsC, double[][] coefficientsS, double muc, double eqRadius, double threshold, int degree, int order) Method to compute the acceleration, from Droziner algorithm (see DrozinerAttractionModel).

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

BalminoAttractionModel(Frame frame, double ae, double mu, double[][] Ccoefs, double[][] Scoefs)
Create an instance of a normalized gravity computation model using normalized coefficients.

BalminoAttractionModel(Frame frame, double ae, double mu, double[][] Ccoefs, double[][] Scoefs, int degreePD, int orderPD)
Create an instance of a normalized gravity computation model using normalized coefficients.

BalminoAttractionModel(Frame frame, Parameter ae, Parameter mu, double[][] Ccoefs, double[][] Scoefs)
Create an instance of a normalized gravity computation model using normalized coefficients.

BalminoAttractionModel(Frame frame, Parameter ae, Parameter mu, double[][] Ccoefs, double[][] Scoefs, int degreePD, int orderPD)
Create an instance of a normalized gravity computation model using normalized coefficients.

CunninghamAttractionModel(Frame centralBodyFrame, double equatorialRadius, double mu, double[][] C, double[][] S)
Creates a new instance.

CunninghamAttractionModel(Frame centralBodyFrame, double equatorialRadius, double mu, double[][] C, double[][] S, int degreePD, int orderPD)
Creates a new instance.

CunninghamAttractionModel(Frame centralBodyFrame, Parameter equatorialRadius, Parameter mu, double[][] C, double[][] S)
Creates a new instance using Parameter.

CunninghamAttractionModel(Frame centralBodyFrame, Parameter equatorialRadius, Parameter mu, double[][] C, double[][] S, int degreePD, int orderPD)
Creates a new instance using Parameter.

DrozinerAttractionModel(Frame centralBodyFrame, double equatorialRadius, double mu, double[][] C, double[][] S)
Creates a new instance.

DrozinerAttractionModel(Frame centralBodyFrame, double equatorialRadius, double mu, double[][] C, double[][] S, boolean computePDPos, boolean computePDVel)
Creates a new instance.

DrozinerAttractionModel(Frame centralBodyFrame, Parameter equatorialRadius, Parameter mu, double[][] C, double[][] S)
Creates a new instance using Parameter.

DrozinerAttractionModel(Frame centralBodyFrame, Parameter equatorialRadius, Parameter mu, double[][] C, double[][] S, boolean computePDPos, boolean computePDVel)
Creates a new instance using Parameter.

Uses of Frame in org.orekit.forces.gravity.tides

Fields in org.orekit.forces.gravity.tides declared as Frame

protected Frame

AbstractTides.bodyFrame Frame for the central body.

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

Vector3D

AbstractTides.computeAcceleration(PVCoordinates pv, Frame frame, AbsoluteDate date) Method to compute the acceleration, from Balmino algorithm (see BalminoAttractionModel class).

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

AbstractTides(Frame centralBodyFrame, double equatorialRadius, double mu, int degree, int order)
Build a new instance.

AbstractTides(Frame centralBodyFrame, double equatorialRadius, double mu, int degree, int order, int degreePD, int orderPD)
Build a new instance.

AbstractTides(Frame centralBodyFrame, Parameter equatorialRadius, Parameter mu, int degree, int order)
Build a new instance using Parameter.

AbstractTides(Frame centralBodyFrame, Parameter equatorialRadius, Parameter mu, int degree, int order, int degreePD, int orderPD)
Build a new instance using Parameter.

OceanTides(Frame centralBodyFrame, double equatorialRadius, double mu, double density, int degree, int order, boolean withAdmittance, IOceanTidesDataProvider tidesData)
Constructor.

OceanTides(Frame centralBodyFrame, double equatorialRadius, double mu, double density, int degree, int order, int degreePD, int orderPD, boolean withAdmittance, IOceanTidesDataProvider tidesData)
Constructor.

OceanTides(Frame centralBodyFrame, Parameter equatorialRadius, Parameter mu, Parameter density, int degree, int order, boolean withAdmittance, IOceanTidesDataProvider tidesData)
Constructor using Parameter.

OceanTides(Frame centralBodyFrame, Parameter equatorialRadius, Parameter mu, Parameter density, int degree, int order, int degreePD, int orderPD, boolean withAdmittance, IOceanTidesDataProvider tidesData)
Constructor using Parameter.

TerrestrialTides(Frame centralBodyFrame, double equatorialRadius, double mu)
Creates a new instance.

TerrestrialTides(Frame centralBodyFrame, double equatorialRadius, double mu, boolean computePD)
Creates a new instance.

TerrestrialTides(Frame centralBodyFrame, double equatorialRadius, double mu, List<CelestialBody> bodies, boolean thirdBodyAttDegree3, boolean frequencyCorr, boolean ellipticityCorr, ITerrestrialTidesDataProvider terrestrialData)
Creates a new instance.

TerrestrialTides(Frame centralBodyFrame, double equatorialRadius, double mu, List<CelestialBody> bodies, boolean thirdBodyAttDegree3, boolean frequencyCorr, boolean ellipticityCorr, ITerrestrialTidesDataProvider terrestrialData, boolean computePD)
Creates a new instance.

TerrestrialTides(Frame centralBodyFrame, Parameter equatorialRadius, Parameter mu)
Creates a new instance.

TerrestrialTides(Frame centralBodyFrame, Parameter equatorialRadius, Parameter mu, boolean computePD)
Creates a new instance.

TerrestrialTides(Frame centralBodyFrame, Parameter equatorialRadius, Parameter mu, List<CelestialBody> bodies, boolean thirdBodyAttDegree3, boolean frequencyCorr, boolean ellipticityCorr, ITerrestrialTidesDataProvider terrestrialData)
Creates a new instance using Parameter.

TerrestrialTides(Frame centralBodyFrame, Parameter equatorialRadius, Parameter mu, List<CelestialBody> bodies, boolean thirdBodyAttDegree3, boolean frequencyCorr, boolean ellipticityCorr, ITerrestrialTidesDataProvider terrestrialData, boolean computePD)
Creates a new instance using Parameter.

Uses of Frame in org.orekit.forces.gravity.variations

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

VariablePotentialAttractionModel(Frame centralBodyFrame, VariablePotentialCoefficientsProvider provider, int degree, int order)
Variable gravity field force model constructor (static part only).

VariablePotentialAttractionModel(Frame centralBodyFrame, VariablePotentialCoefficientsProvider provider, int degree, int order, int degreePD, int orderPD)
Variable gravity field force model constructor (static part only).

VariablePotentialAttractionModel(Frame centralBodyFrame, VariablePotentialCoefficientsProvider provider, int degree, int order, int degreeOptional, int orderOptional, boolean computeOptionalOnce)
Variable gravity field force model constructor.

VariablePotentialAttractionModel(Frame centralBodyFrame, VariablePotentialCoefficientsProvider provider, int degree, int order, int degreePD, int orderPD, int degreeOptional, int orderOptional, int degreeOptionalPD, int orderOptionalPD, boolean computeOptionalOnce)
Variable gravity field force model constructor.

Uses of Frame in org.orekit.forces.maneuvers

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

Frame	ImpulseManeuver.getFrame() Get the frame of the velocity increment.
Frame	ConstantThrustManeuver.getFrame() Get the frame of the acceleration direction.
Frame	VariableThrustManeuver.getFrame() Get the frame of the acceleration direction.
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

ConstantThrustError(AbsoluteDate date, double duration, Frame frame, double cx, double cy, double cz)
Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx
fy = cy
fz = cz

ConstantThrustError(AbsoluteDate date, double duration, Frame frame, double ax, double bx, double ay, double by, double az, double bz, AbsoluteDate date0)
Create a constant thrust error model whose x, y and z components are linear functions:
fx = ax*t + bx
fy = ay*t + by
fz = az*t + bz

ConstantThrustError(AbsoluteDate date, double duration, Frame frame, IParamDiffFunction fx, IParamDiffFunction fy, IParamDiffFunction fz)
Create a constant thrust error model whose x, y and z components are parameterizable and differentiable function.

ConstantThrustError(AbsoluteDate date, double duration, Frame frame, Parameter cx, Parameter cy, Parameter cz)
Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx
fy = cy
fz = cz

ConstantThrustError(AbsoluteDate date, double duration, Frame frame, Parameter ax, Parameter bx, Parameter ay, Parameter by, Parameter az, Parameter bz, AbsoluteDate date0)
Create a constant thrust error model whose x, y and z components are linear functions:
fx = ax*t + bx
fy = ay*t + by
fz = az*t + bz

ConstantThrustError(EventDetector startEventDetector, EventDetector stopEventDetector, Frame frame, IParamDiffFunction fx, IParamDiffFunction fy, IParamDiffFunction fz)
Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx
fy = cy
fz = cz

ConstantThrustError(EventDetector startEventDetector, EventDetector stopEventDetector, Frame frame, Parameter cx, Parameter cy, Parameter cz)
Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx
fy = cy
fz = cz

ConstantThrustManeuver(AbsoluteDate date, double duration, double thrust, double isp, Vector3D direction, MassProvider massProvider, String partName, Frame frame)
Constructor for a constant direction in provided frame and constant thrust.

ConstantThrustManeuver(AbsoluteDate date, double duration, Parameter thrust, Parameter flowRate, Vector3D direction, MassProvider massProvider, String partName, Frame frame)
Constructor for a constant direction in provided frame and constant thrust using Parameter.

ConstantThrustManeuver(EventDetector startEventDetector, EventDetector stopEventDetector, double thrust, double isp, Vector3D direction, MassProvider massProvider, String partName, Frame frame)
Constructor for a constant direction in provided frame and constant thrust.

ImpulseManeuver(EventDetector trigger, Vector3D deltaVSat, Frame frame, double isp, MassProvider massModel, String part)
Build a new instance.

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

VariableThrustManeuver(AbsoluteDate date, double duration, IDependentVariable<SpacecraftState> variableThrust, IDependentVariable<SpacecraftState> variableIsp, IDependentVectorVariable<SpacecraftState> variableDirection, MassProvider massModel, String partName, Frame refFrame)
Constructor for a variable direction in provided frame, thrust and ISP.

VariableThrustManeuver(EventDetector startEventDetector, EventDetector stopEventDetector, IDependentVariable<SpacecraftState> variableThrust, IDependentVariable<SpacecraftState> variableIsp, IDependentVectorVariable<SpacecraftState> variableDirection, MassProvider massModel, String partName, Frame refFrame)
Constructor for a variable direction in provided frame, thrust and ISP.

Uses of Frame in org.orekit.forces.radiation

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

double

SolarRadiationPressure.getLightningRatio(Vector3D position, Frame frame, AbsoluteDate date) Get the lightning ratio ([0-1]).

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

RediffusedFlux(int nCorona, int nMeridian, Frame bodyFrame, CelestialBody sunProvider, PVCoordinatesProvider satProvider, AbsoluteDate d, IEmissivityModel model)
Default constructor of rediffused flux.

RediffusedFlux(int nCorona, int nMeridian, Frame bodyFrame, CelestialBody sun, PVCoordinatesProvider satProvider, AbsoluteDate dDate, IEmissivityModel model, boolean inIr, boolean inAlbedo)
Generic constructor of rediffused flux.

RediffusedRadiationPressure(CelestialBody inSun, Frame inBodyFrame, int inCorona, int inMeridian, IEmissivityModel inEmissivityModel, RediffusedRadiationSensitive inModel)
Constructor.

RediffusedRadiationPressure(CelestialBody inSun, Frame inBodyFrame, int inCorona, int inMeridian, IEmissivityModel inEmissivityModel, RediffusedRadiationSensitive inModel, boolean computePD)
Constructor.

Uses of Frame in org.orekit.forces.relativistic

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

LenseThirringRelativisticEffect(double mu, Frame frame)
Constructor and with partial derivative computation by default.

LenseThirringRelativisticEffect(double mu, Frame frame, boolean computePartialDerivativesPos, boolean computePartialDerivativesVel)
Constructor.

Uses of Frame in org.orekit.frames

Subclasses of Frame in org.orekit.frames

class	FactoryManagedFrame Base class for the predefined frames that are managed by FramesFactory.
class	LocalOrbitalFrame Class for frames moving with an orbiting satellite.
class	SpacecraftFrame Deprecated. as of 6.0 replaced by SpacecraftState.toTransform()
class	TopocentricFrame Topocentric frame.
class	UpdatableFrame Frame whose transform from its parent can be updated.

Methods in org.orekit.frames that return Frame

protected Frame	Frame.getAncestor(int n) Get the nth ancestor of the 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.getH0MinusN(String name, AbsoluteDate h0MinusN, double longitude) Get the "H0 - n" reference frame.
static Frame	FramesFactory.getH0MinusN(String name, AbsoluteDate h0, double n, double longitude) Get the "H0 - n" reference frame.
static Frame	FramesFactory.getICRF() Get the unique ICRF frame.
static Frame	OrphanFrame.getNewOrphanFrame(String name) This method creates an Orphan 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

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.getAzimuthRate(PVCoordinates extPV, Frame frame, AbsoluteDate date) Get the azimuth rate of a point.
double	TopocentricFrame.getElevation(Vector3D extPoint, Frame frame, AbsoluteDate date) Get the elevation of a point with regards to the local point.
double	TopocentricFrame.getElevationRate(PVCoordinates extPV, Frame frame, AbsoluteDate date) Get the elevation rate of a point.
Frame	Frame.getFrozenFrame(Frame reference, AbsoluteDate freezingDate, String frozenName) Get a new version of the instance, frozen with respect to a reference frame.
PVCoordinates	SpacecraftFrame.getPVCoordinates(AbsoluteDate date, Frame frame) Deprecated. Get the PVCoordinates of the spacecraft frame origin in the selected frame.
PVCoordinates	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.
RealMatrix	Frame.getTransformJacobian(Frame to, AbsoluteDate date) Compute the Jacobian from current frame to target frame at provided date.
Transform	Frame.getTransformTo(Frame destination, AbsoluteDate date) Get the transform from the instance to another frame.
Transform	Frame.getTransformTo(Frame destination, AbsoluteDate date, boolean computeSpinDerivatives) Get the transform from the instance to another frame.
Transform	Frame.getTransformTo(Frame destination, AbsoluteDate date, FramesConfiguration config) Get the transform from the instance to another frame.
Transform	Frame.getTransformTo(Frame destination, AbsoluteDate date, FramesConfiguration config, boolean computeSpinDerivatives) Get the transform from the instance to another frame.
double	TopocentricFrame.getXangleCardan(Vector3D extPoint, Frame frame, AbsoluteDate date) Get the Cardan x angle of a point.
double	TopocentricFrame.getXangleCardanRate(PVCoordinates extPV, Frame frame, AbsoluteDate date) Get the Cardan x angle rate.
double	TopocentricFrame.getYangleCardan(Vector3D extPoint, Frame frame, AbsoluteDate date) Get the Cardan y angle of a point with regards to the projection point on the plane defined by the zenith and the west axis.
double	TopocentricFrame.getYangleCardanRate(PVCoordinates extPV, Frame frame, AbsoluteDate date) Get the Cardan y angle rate.
boolean	Frame.isChildOf(Frame potentialAncestor) Determine if a Frame is a child of another one.
CardanMountPosition	TopocentricFrame.transformFromPositionToCardan(Vector3D extPoint, Frame frame, AbsoluteDate date) Transform a Cartesian position coordinates into Cardan mounting in this local topocentric frame.
TopocentricPosition	TopocentricFrame.transformFromPositionToTopocentric(Vector3D extPoint, Frame frame, AbsoluteDate date) Transform a Cartesian position coordinates into topocentric coordinates in this local topocentric frame.
CardanMountPV	TopocentricFrame.transformFromPVToCardan(PVCoordinates extPV, Frame frame, AbsoluteDate date) Transform a Cartesian position coordinates into Cardan mounting in this local topocentric frame.
TopocentricPV	TopocentricFrame.transformFromPVToTopocentric(PVCoordinates extPV, Frame frame, AbsoluteDate date) Transform a Cartesian position and velocity coordinates into topocentric coordinates in this local topocentric frame.
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

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 with parameters of type Frame

GeoMagneticElements

GeoMagneticField.calculateField(Vector3D point, Frame frame, AbsoluteDate date) Calculate the magnetic field at the specified point identified by the coordinates of the point and the reference point.

Uses of Frame in org.orekit.orbits

Methods in org.orekit.orbits that return Frame

Frame

Orbit.getFrame() Get the frame in which the orbital parameters are defined.

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

abstract Orbit	OrbitType.convertOrbit(Orbit initOrbit, Frame frame) Convert an orbit from a given orbit type to an other in a wished frame.
PVCoordinates	Orbit.getPVCoordinates(AbsoluteDate otherDate, Frame otherFrame) Get the PVCoordinates of the body in the selected frame.
PVCoordinates	Orbit.getPVCoordinates(Frame outputFrame) Get the PVCoordinates 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

ApsisOrbit(double peri, double apo, double i, double pa, double raan, double anomaly, PositionAngle type, Frame frame, AbsoluteDate date, double mu)
Creates a new instance.

ApsisOrbit(IOrbitalParameters parameters, Frame frame, AbsoluteDate date)
Creates a new instance.

ApsisOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu)
Constructor from cartesian parameters.

CartesianOrbit(IOrbitalParameters parameters, Frame frame, AbsoluteDate date)
Creates a new instance.

CartesianOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu)
Constructor from cartesian parameters.

CircularOrbit(double a, double ex, double ey, double i, double raan, double alpha, int type, Frame frame, AbsoluteDate date, double mu)
Deprecated. as of 6.0 replaced by CircularOrbit.CircularOrbit(double, double, double, double, double, double, PositionAngle, Frame, AbsoluteDate, double)

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(IOrbitalParameters parameters, Frame frame, AbsoluteDate date)
Creates a new instance.

CircularOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu)
Constructor from cartesian parameters.

EquatorialOrbit(double a, double e, double pomega, double ix, double iy, double anomaly, PositionAngle type, Frame frame, AbsoluteDate date, double mu)
Creates a new instance.

EquatorialOrbit(IOrbitalParameters parameters, Frame frame, AbsoluteDate date)
Creates a new instance.

EquatorialOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu)
Constructor from cartesian parameters.

EquinoctialOrbit(double a, double ex, double ey, double hx, double hy, double l, int type, Frame frame, AbsoluteDate date, double mu)
Deprecated. as of 6.0 replaced by EquinoctialOrbit.EquinoctialOrbit(double, double, double, double, double, double, PositionAngle, Frame, AbsoluteDate, double)

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(IOrbitalParameters parameters, Frame frame, AbsoluteDate date)
Creates a new instance.

EquinoctialOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu)
Constructor from cartesian parameters.

KeplerianOrbit(double a, double e, double i, double pa, double raan, double anomaly, int type, Frame frame, AbsoluteDate date, double mu)
Deprecated. as of 6.0 replaced by KeplerianOrbit.KeplerianOrbit(double, double, double, double, double, double, PositionAngle, Frame, AbsoluteDate, double)

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(IOrbitalParameters parameters, Frame frame, AbsoluteDate date)
Creates a new instance.

KeplerianOrbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu)
Constructor from cartesian parameters.

Orbit(Frame frame, AbsoluteDate date, double mu)
Default constructor.

Orbit(PVCoordinates pvCoordinates, Frame frame, AbsoluteDate date, double mu)
Set the orbit from Cartesian parameters.

Uses of Frame in org.orekit.propagation

Methods in org.orekit.propagation that return Frame

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

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

Attitude	SpacecraftState.getAttitude(Frame outputFrame) Get the default attitude : the attitude for forces computation in given output frame.
Attitude	SpacecraftState.getAttitudeEvents(Frame outputFrame) Get the attitude for events computation in given output frame.
Attitude	SpacecraftState.getAttitudeForces(Frame outputFrame) Get the attitude for forces computation in given output frame.
PVCoordinates	AbstractPropagator.getPVCoordinates(AbsoluteDate date, Frame frame) Get the PVCoordinates of the body in the selected frame.
PVCoordinates	SpacecraftState.getPVCoordinates(Frame outputFrame) Get the PVCoordinates in given output frame.
void	Propagator.setOrbitFrame(Frame frame) Set propagation frame.
void	AbstractPropagator.setOrbitFrame(Frame frame) Set propagation frame.
Transform	SpacecraftState.toTransform(Frame frame) Compute the transform from specified frame to spacecraft frame.
Transform	SpacecraftState.toTransform(Frame frame, LOFType lofType) Compute the transform from specified frame to local orbital frame.
Transform	SpacecraftState.toTransformEvents(Frame frame) Compute the transform from specified reference frame to spacecraft frame.
Transform	SpacecraftState.toTransformForces(Frame frame) Compute the transform from specified frame to spacecraft frame.

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

SpacecraftState(double[] y, OrbitType orbitType, PositionAngle angleType, AbsoluteDate date, double mu, Frame frame, Map<String,AdditionalStateInfo> addStatesInfo, AttitudeProvider attProviderForces, AttitudeProvider attProviderEvents)
Build a spacecraft from an array (a state vector) and an additional states informations map.

Uses of Frame in org.orekit.propagation.analytical

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

protected Orbit	AbstractLyddanePropagator.convertFrame(Orbit orbit, Frame outputFrame) Convert provided orbit in output frame.
protected Orbit	AbstractLyddanePropagator.propagateOrbit(AbsoluteDate date, Orbit secularOrbit, Frame outputFrame, AbstractLyddanePropagator.LyddaneParametersType returnType) Propagate orbit to provided date.

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

AbstractLyddanePropagator(Orbit secularOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents, MassProvider massProvider)
Generic constructor.

EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents, double referenceRadius, double mu, Frame frame, double c20, double c30, double c40, double c50, double c60, MassProvider massProvider, ParametersType paramsType)
Build a propagator from orbit, attitude provider, mass and potential.

EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents, double referenceRadius, double mu, Frame frame, double c20, double c30, double c40, double c50, double c60, ParametersType paramsType)
Build a propagator from orbit, attitude provider for forces and events computation and potential.

EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double referenceRadius, double mu, Frame frame, double c20, double c30, double c40, double c50, double c60, MassProvider massProvider, ParametersType paramsType)
Build a propagator from orbit, attitude provider, mass and potential.

EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double referenceRadius, double mu, Frame frame, double c20, double c30, double c40, double c50, double c60, ParametersType paramsType)
Build a propagator from orbit, attitude provider and potential.

EcksteinHechlerPropagator(Orbit initialOrbit, double referenceRadius, double mu, Frame frame, double c20, double c30, double c40, double c50, double c60, MassProvider massProvider, ParametersType paramsType)
Build a propagator from orbit, mass and potential.

EcksteinHechlerPropagator(Orbit initialOrbit, double referenceRadius, double mu, Frame frame, double c20, double c30, double c40, double c50, double c60, ParametersType paramsType)
Build a propagator from orbit and potential.

J2SecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, Frame frameIn)
Constructor without attitude provider and mass provider.

J2SecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, Frame frameIn, AttitudeProvider attitudeProvider)
Constructor without mass provider.

J2SecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, Frame frameIn, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents)
Constructor without mass provider.

J2SecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, Frame frameIn, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents, MassProvider massProvider)
Generic constructor.

J2SecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, Frame frameIn, AttitudeProvider attitudeProvider, MassProvider massProvider)
Generic constructor.

J2SecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, Frame frameIn, MassProvider massProvider)
Constructor without attitude provider.

LyddaneLongPeriodPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn)
Constructor without attitude provider and mass provider.

LyddaneLongPeriodPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, AttitudeProvider attitudeProvider)
Constructor without mass provider.

LyddaneLongPeriodPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents)
Constructor without mass provider.

LyddaneLongPeriodPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents, MassProvider massProvider)
Generic constructor.

LyddaneLongPeriodPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, AttitudeProvider attitudeProvider, MassProvider massProvider)
Generic constructor.

LyddaneLongPeriodPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, MassProvider massProvider)
Constructor without attitude provider.

LyddaneSecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn)
Constructor without attitude provider and mass provider.

LyddaneSecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, AttitudeProvider attitudeProvider)
Constructor without mass provider.

LyddaneSecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents)
Constructor without mass provider.

LyddaneSecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents, MassProvider massProvider)
Generic constructor.

LyddaneSecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, AttitudeProvider attitudeProvider, MassProvider massProvider)
Generic constructor.

LyddaneSecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, MassProvider massProvider)
Constructor without attitude provider.

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

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

SymmetricMatrix

OrbitCovariance.getCovarianceMatrix(Orbit refOrbit, OrbitType outCovType, Frame outFrame) Covariance matrix getter.

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

OrbitCovariance(AbsoluteDate covDate, Frame refFrame, OrbitType coordType, RealMatrix covMat)
Simple constructor

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

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

Frame

TLEPropagator.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

Frame	AOLDetector.getAOLFrame() Get the reference frame.
Frame	LocalTimeDetector.getBodyFrame() Get frame of the body.
Frame	ExtremaLatitudeDetector.getBodyFrame() Returns the body frame.
Frame	ExtremaLongitudeDetector.getBodyFrame() Returns the body frame.
Frame	LongitudeDetector.getBodyFrame() Returns central body frame.
Frame	NodeDetector.getFrame() Get the frame in which the equator is defined.

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

double	ConstantRadiusProvider.getLocalRadius(Vector3D position, Frame frame, AbsoluteDate date, PVCoordinatesProvider occultedBodyIn) Calculate the apparent radius.
double	VariableRadiusProvider.getLocalRadius(Vector3D position, Frame frame, AbsoluteDate date, PVCoordinatesProvider occultedBodyIn) Calculate the apparent radius.
double	LocalRadiusProvider.getLocalRadius(Vector3D position, Frame frame, AbsoluteDate date, PVCoordinatesProvider occultedBodyIn) Calculate the apparent radius.

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

AdaptedEventDetector(EventDetector detector, Map<String,AdditionalStateInfo> info, OrbitType orbitType, PositionAngle angleType, AttitudeProvider attProviderForces, AttitudeProvider attProviderEvents, AbsoluteDate referenceDate, double mu, Frame integrationFrame)
Build a wrapped event detector.

AOLDetector(double angle, PositionAngle type, Frame equator)
Constructor for an AOLDetector instance.

AOLDetector(double angle, PositionAngle type, Frame equator, double maxCheck, double threshold)
Constructor for an AOLDetector instance with complementary parameters.

AOLDetector(double angle, PositionAngle type, Frame equator, double maxCheck, double threshold, EventDetector.Action action)
Constructor for an AOLDetector instance with complementary parameters.

AOLDetector(double angle, PositionAngle type, Frame equator, double maxCheck, double threshold, EventDetector.Action action, boolean remove)
Constructor for an AOLDetector instance with complementary parameters.

ExtremaLatitudeDetector(int extremumType, Frame bodyFrame)
Constructor for a ExtremaLatitudeDetector instance.

ExtremaLatitudeDetector(int extremumType, Frame bodyFrame, double maxCheck, double threshold)
Constructor for a ExtremaLatitudeDetector instance.

ExtremaLatitudeDetector(int extremumType, Frame bodyFrame, double maxCheck, double threshold, EventDetector.Action action)
Constructor for a ExtremaLatitudeDetector instance.

ExtremaLatitudeDetector(int extremumType, Frame bodyFrame, double maxCheck, double threshold, EventDetector.Action action, boolean remove)
Constructor for a ExtremaLatitudeDetector instance.

ExtremaLongitudeDetector(int extremumType, Frame bodyFrame)
Constructor for a ExtremaLongitudeDetector instance.

ExtremaLongitudeDetector(int extremumType, Frame bodyFrame, double maxCheck, double threshold)
Constructor for a ExtremaLongitudeDetector instance.

ExtremaLongitudeDetector(int extremumType, Frame bodyFrame, double maxCheck, double threshold, EventDetector.Action action)
Constructor for a ExtremaLongitudeDetector instance.

ExtremaLongitudeDetector(int extremumType, Frame bodyFrame, double maxCheck, double threshold, EventDetector.Action action, boolean remove)
Constructor for a ExtremaLongitudeDetector instance.

LocalTimeDetector(double localTime, Frame bodyFrame)
Constructor for a LocalTimeDetector instance.

LocalTimeDetector(double localTime, Frame bodyFrame, double maxCheck, double threshold)
Constructor for a LocalTimeDetector instance with complimentary parameters.

LocalTimeDetector(double localTime, Frame bodyFrame, double maxCheck, double threshold, EventDetector.Action action)
Constructor for a LocalTimeDetector instance with complimentary parameters.

LocalTimeDetector(double localTime, Frame bodyFrame, double maxCheck, double threshold, EventDetector.Action action, boolean remove)
Constructor for a LocalTimeDetector instance with complimentary parameters.

LongitudeDetector(double longitudeToDetect, Frame bodyFrame)
Constructor for the longitude detector.

LongitudeDetector(double longitudeToDetect, Frame bodyFrame, double maxCheck, double threshold)
Constructor for the longitude detector.

LongitudeDetector(double longitudeToDetect, Frame bodyFrame, double maxCheck, double threshold, EventDetector.Action action)
Constructor for the longitude detector.

LongitudeDetector(double longitudeToDetect, Frame bodyFrame, double maxCheck, double threshold, EventDetector.Action action, boolean remove)
Constructor for the longitude detector.

NodeDetector(Frame frame, double maxCheck, double threshold, EventDetector.Action ascendingNode, EventDetector.Action descendingNode)
Build a new instance for both ascending and descending node detection.

NodeDetector(Frame frame, double maxCheck, double threshold, EventDetector.Action ascendingNode, EventDetector.Action descendingNode, boolean removeAscendingNode, boolean removeDescendingNode)
Build a new instance for both ascending and descending node detection.

NodeDetector(Frame frame, int slopeSelection, double maxCheck, double threshold)
Build a new instance.

NodeDetector(Frame frame, int slopeSelection, double maxCheck, double threshold, EventDetector.Action action)
Build a new instance.

NodeDetector(Frame frame, int slopeSelection, double maxCheck, double threshold, EventDetector.Action action, boolean removeCrossingNode)
Build a new instance.

NodeDetector(Orbit orbit, Frame frame, int slopeSelection)
Build a new instance.

NodeDetector(Orbit orbit, Frame frame, int slopeSelection, double threshold)
Build a new instance.

Uses of Frame in org.orekit.propagation.numerical

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

Frame

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

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

void	TimeDerivativesEquations.addAcceleration(Vector3D gamma, Frame frame) Add the contribution of an acceleration expressed in some inertial frame.
PVCoordinates	NumericalPropagator.getPVCoordinates(AbsoluteDate date, Frame frame) Get the PVCoordinates of the body in the selected frame.
void	ModeHandler.initialize(OrbitType orbit, PositionAngle angle, AttitudeProvider attitudeProviderForces, AttitudeProvider attitudeProviderEvents, Map<String,AdditionalStateInfo> additionalStateInfos, boolean activateHandlers, AbsoluteDate reference, Frame frame, double mu) Initialize the mode handler.
void	NumericalPropagator.setOrbitFrame(Frame frame) Set propagation frame.

Uses of Frame in org.orekit.propagation.precomputed

Fields in org.orekit.propagation.precomputed declared as Frame

protected Frame

AbstractEphemeris.frame Reference frame.

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

static SpacecraftState[]	AbstractEphemeris.generateSpacecraftState(PVCoordinatesProvider pvProv, AttitudeProvider attProvForces, AttitudeProvider attProvEvents, double step, AbsoluteDateInterval ptsInterval, Frame frame, double mu) Creates a spacecraft array with constant step size.
PVCoordinates	IntegratedEphemeris.getPVCoordinates(AbsoluteDate date, Frame frame) Get the PVCoordinates of the body in the selected frame.
PVCoordinates	Ephemeris.getPVCoordinates(AbsoluteDate date, Frame frame) Get the PVCoordinates of the body in the selected frame.

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

HermiteEphemeris(PVCoordinatesProvider pvProv, AttitudeProvider attProvForces, AttitudeProvider attProvEvents, double step, AbsoluteDateInterval intervalOfPoints, Frame frame2, double mu2)
Deprecated. Constructor n°1 using a PV coordinates provider and an AttitudeProvider to build the interpolation points.

IntegratedEphemeris(List<AbsoluteDate> startDates, List<AbsoluteDate> minDates, List<AbsoluteDate> maxDates, OrbitType orbitType, PositionAngle angleType, AttitudeProvider attitudeForcesProvider, AttitudeProvider attitudeEventsProvider, Map<String,AdditionalStateInfo> additionalStateInfos, List<ContinuousOutputModel> models, Frame referenceFrame, double mu)
Creates a new instance of IntegratedEphemeris.

LagrangeEphemeris(PVCoordinatesProvider pvProv, AttitudeProvider attProvForces, AttitudeProvider attProvEvents, double step, AbsoluteDateInterval intervalOfPoints, Frame frame, double mu)
Deprecated. Constructor using a PV coordinates provider and an AttitudeProvider to build the interpolation points, defaulting to 8th order for the Lagrange interpolator.

LagrangeEphemeris(PVCoordinatesProvider pvProv, AttitudeProvider attProvForces, AttitudeProvider attProvEvents, double step, AbsoluteDateInterval intervalOfPoints, Frame frame, double mu, int order)
Deprecated. Constructor using a PV coordinates provider and an AttitudeProvider to build the interpolation points.

Uses of Frame in org.orekit.propagation.sampling

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

void

AdaptedStepHandler.initialize(OrbitType orbit, PositionAngle angle, AttitudeProvider attitudeProviderForces, AttitudeProvider attitudeProviderEvents, Map<String,AdditionalStateInfo> additionalStateInfos, boolean activateHandlers, AbsoluteDate reference, Frame frame, double mu) Initialize the mode handler.

Uses of Frame in org.orekit.time

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

double	LocalTime.computeMeanLocalTime(AbsoluteDate date, Vector3D pos, Frame frame) Compute mean local time in TIRF frame in s.
double	LocalTime.computeTrueLocalTime(AbsoluteDate date, Vector3D pos, Frame frame) Compute true local time in TIRF frame in the range [0s; 86400s[.

Uses of Frame in org.orekit.utils

Methods in org.orekit.utils that return Frame

Frame

AbstractBoundedPVProvider.getFrame() Get the reference frame

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

PVCoordinates	PVCoordinatesProvider.getPVCoordinates(AbsoluteDate date, Frame frame) Get the PVCoordinates of the body in the selected frame.
PVCoordinates	EphemerisPvLagrange.getPVCoordinates(AbsoluteDate date, Frame frame) Frame can be null : by default the frame of expression is the frame used at instantiation (which is the frame of the first spacecraft state when instantiation is done from a table of spacecraft states).
PVCoordinates	EphemerisPvHermite.getPVCoordinates(AbsoluteDate date, Frame frame) Get the PVCoordinates of the body in the selected frame.

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

AbstractBoundedPVProvider(PVCoordinates[] tabPV, Frame frame, AbsoluteDate[] tabDate, ISearchIndex algo)
Instantiation of AbstractBoundedPVProvider attributes.

EphemerisPvHermite(PVCoordinates[] tabPV, Vector3D[] tabAcc, Frame frame, AbsoluteDate[] tabDate, ISearchIndex algo)
Creates an instance of EphemerisPvHermite.

EphemerisPvLagrange(PVCoordinates[] tabPV, int order, Frame frame, AbsoluteDate[] tabDate, ISearchIndex algo)
Creates an instance of EphemerisPvLagrange

Uses of Frame in org.orekit.wrenches

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

Vector3D	WrenchModel.computeTorque(SpacecraftState s, Vector3D origin, Frame frame) Compute the resulting wrench.
Wrench	WrenchModel.computeWrench(SpacecraftState s, Vector3D origin, Frame frame) Compute the resulting wrench.