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| 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()
|
| Methods in fr.cnes.sirius.patrius.assembly with parameters of type Frame | |
|---|---|
Assembly |
Vehicle.createAssembly(Frame frame)
Create an Assembly. |
Assembly |
Vehicle.createAssembly(Frame frame,
double cMass,
double cDrag,
double cSRP)
Create an Assembly with multiplicative coefficients to take into
account the change in surface for drag or SRP during a propagation of the
change of dry mass. |
| 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. |
protected static Vector3D |
AeroModel.forceOnSphere(SpacecraftState state,
IPart part,
double density,
Vector3D relativeVelocity,
Frame mainPartFrame)
Method to compute the force for the part model (cylinder, parallelepiped, sphere). |
protected static Vector3D |
DirectRadiativeModel.forceOnSphere(SpacecraftState state,
IPart part,
Vector3D flux,
Frame mainPartFrame)
Method to compute the force for a spherical model. |
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.assembly.properties |
|---|
| Methods in fr.cnes.sirius.patrius.assembly.properties with parameters of type Frame | |
|---|---|
double |
AeroSphereProperty.getCrossSection(SpacecraftState state,
Vector3D relativeVelocity,
Frame mainPartFrame,
Frame partFrame)
|
double |
RadiativeSphereProperty.getCrossSection(SpacecraftState state,
Vector3D flux,
Frame mainPartFrame,
Frame partFrame)
|
double |
RadiativeCrossSectionProperty.getCrossSection(SpacecraftState state,
Vector3D flux,
Frame mainPartFrame,
Frame partFrame)
Compute the cross section of main shape using the relative velocity in the part (having the aero property) frame as the direction to provider to the CrossSectionProvider.getCrossSection(Vector3D). |
double |
AeroCrossSectionProperty.getCrossSection(SpacecraftState state,
Vector3D relativeVelocity,
Frame mainPartFrame,
Frame partFrame)
Compute the cross section of main shape using the relative velocity in the part (having the aero property) frame as the direction to provider to the CrossSectionProvider.getCrossSection(Vector3D). |
| 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 |
ConstantThrustManeuver.getFrame()
Get the frame of the acceleration inDirection. |
Frame |
VariableThrustManeuver.getFrame()
Get the frame of the acceleration direction. |
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 | |
|---|---|
ConstantThrustManeuver(AbsoluteDate date,
double duration,
double thrust,
double isp,
Vector3D inDirection,
MassProvider massProvider,
String partNameIn,
Frame frameIn)
Constructor for a constant direction in provided frame and constant thrust. |
|
ConstantThrustManeuver(AbsoluteDate date,
double duration,
Parameter thrust,
Parameter flowRate,
Vector3D inDirection,
MassProvider massProvider,
String partNameIn,
Frame frameIn)
Constructor for a constant dDirection in provided frame and constant thrust using Parameter. |
|
ConstantThrustManeuver(AbsoluteDate date,
double duration,
PropulsiveProperty engine,
Parameter flowRate,
Vector3D inDirection,
MassProvider massProvider,
TankProperty tank,
Frame frameIn)
Constructor for a constant direction in satellite frame and constant thrust using Parameter,
PropulsiveProperty and TankProperty. |
|
ConstantThrustManeuver(AbsoluteDate date,
double duration,
PropulsiveProperty engine,
Vector3D inDirection,
MassProvider massProvider,
TankProperty tank,
Frame frameIn)
Constructor for a constant direction in provided frame and constant thrust, using PropulsiveProperty and TankProperty. |
|
ConstantThrustManeuver(EventDetector startEventDetector,
EventDetector stopEventDetector,
double thrust,
double isp,
Vector3D inDirection,
MassProvider massProvider,
String partNameIn,
Frame frameIn)
Constructor for a constant direction in provided frame and constant thrust. |
|
ConstantThrustManeuver(EventDetector startEventDetector,
EventDetector stopEventDetector,
PropulsiveProperty engine,
Vector3D inDirection,
MassProvider massProvider,
TankProperty tank,
Frame frameIn)
Constructor for a constant direction in provided frame and constant thrust with PropulsiveProperty and TankProperty properties. |
|
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. |
|
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(AbsoluteDate date,
double duration,
PropulsiveProperty engine,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
TankProperty tank,
Frame refFrame)
Constructor for a variable direction in provided frame, thrust and ISP, using PropulsiveProperty and TankProperty. |
|
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. |
|
VariableThrustManeuver(EventDetector startEventDetector,
EventDetector stopEventDetector,
PropulsiveProperty engine,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
TankProperty tank,
Frame refFrame)
Constructor for a variable direction in spacecraft frame, thrust and ISP, using PropulsiveProperty
and TankProperty. |
|
| 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 |
AeroAttitudeLaw.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state. |
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)
Calculate the apparent radius. |
PVCoordinates |
MeeusMoon.getPVCoordinates(AbsoluteDate date,
Frame frame)
|
PVCoordinates |
UserCelestialBody.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the PVCoordinates of the body in the selected 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 |
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 |
|
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. |
|
| 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 |
H0MinusNFrame
"H0 - n" reference frame. |
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 |
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. |
|
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 |
LocalTimeAngle.computeMeanLocalTimeAngle(AbsoluteDate date,
Vector3D pos,
Frame frame)
Compute mean local time angle in TIRF frame in the range [-Π, Π[. |
double |
LocalTimeAngle.computeTrueLocalTimeAngle(AbsoluteDate date,
Vector3D pos,
Frame frame)
Compute true local time angle in TIRF frame in the range [-Π, Π[. |
| 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,
int order,
Frame frame,
AbsoluteDate[] tabDate,
ISearchIndex algo)
Instantiation of AbstractBoundedPVProvider attributes. |
|
EphemerisPvHermite(PVCoordinates[] tabPV,
int order,
Vector3D[] tabAcc,
Frame frame,
AbsoluteDate[] tabDate,
ISearchIndex algo)
Creates an instance of EphemerisPvHermite. |
|
EphemerisPvHermite(PVCoordinates[] tabPV,
Vector3D[] tabAcc,
Frame frame,
AbsoluteDate[] tabDate,
ISearchIndex algo)
Creates an instance of EphemerisPvHermite with default interpolation order = 2. |
|
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. |
|
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