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| Uses of AbsoluteDate in fr.cnes.sirius.patrius.assembly.models |
|---|
| Methods in fr.cnes.sirius.patrius.assembly.models with parameters of type AbsoluteDate | |
|---|---|
double |
SensorModel.celestialBodiesMaskingDistance(AbsoluteDate date)
Computes the minimal euclidian distance to the celestial body shapes. |
double |
RFLinkBudgetModel.computeLinkBudget(AbsoluteDate date)
Computes the link budget at a given date. |
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. |
double |
SensorModel.getInhibitionTargetAngularRadius(AbsoluteDate date,
int inhibitionFieldNumber)
Computes the angular radius from the sensor of the main target at a date. |
double |
SensorModel.getInhibitTargetCenterToFieldAngle(AbsoluteDate date,
int inhibitionFieldNumber)
Computes the angular distance of the CENTER of an inhibition target to the border of the associated inhibition field at a date. |
Vector3D |
MagneticMoment.getMagneticMoment(AbsoluteDate date)
Get the magnetic moment at given date, in the main frame of the spacecraft |
Vector3D |
MagneticMomentProvider.getMagneticMoment(AbsoluteDate date)
Get the magnetic moment at given date, in the main frame of the spacecraft |
double |
SensorModel.getMainTargetAngularRadius(AbsoluteDate date)
Computes the angular radius from the sensor of the main target at a date. |
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. |
Vector3D |
SensorModel.getNormalisedTargetVectorInSensorFrame(AbsoluteDate date)
Computes the target vector at a date in the sensor's frame. |
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 |
double |
SensorModel.getTargetCenterFOVAngle(AbsoluteDate date)
Computes the angular distance of the CENTER of the main target to the border of the main field of view at a date. |
double[] |
SensorModel.getTargetDihedralAngles(AbsoluteDate date)
Computes the dihedral angles of the target at a date in the sensor's frame. |
double |
SensorModel.getTargetRefAxisAngle(AbsoluteDate date,
int axisNumber)
|
double |
SensorModel.getTargetRefAxisElevation(AbsoluteDate date,
int axisNumber)
|
double |
SensorModel.getTargetSightAxisAngle(AbsoluteDate date)
|
double |
SensorModel.getTargetSightAxisElevation(AbsoluteDate date)
|
Vector3D |
SensorModel.getTargetVectorInSensorFrame(AbsoluteDate date)
Computes the target vector at a date in the sensor's frame. |
boolean |
SensorModel.isMainTargetInField(AbsoluteDate date)
Checks if the main target at least partially is in the field of view at a date |
boolean |
SensorModel.noInhibition(AbsoluteDate date)
Checks if at least an inhibition target is at least partially in its associated inhibition field at a date |
double |
SensorModel.spacecraftsMaskingDistance(AbsoluteDate date)
Computes the minimal euclidian distance to the spacecraft's shapes (GEOMERTY properties). |
boolean |
SensorModel.visibilityOk(AbsoluteDate date)
Checks if the main target is in the field of view and no inhibition target in its inhibition field at a given date. |
| Uses of AbsoluteDate in fr.cnes.sirius.patrius.bodies |
|---|
| Methods in fr.cnes.sirius.patrius.bodies with parameters of type AbsoluteDate | |
|---|---|
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. |
| Constructors in fr.cnes.sirius.patrius.bodies with parameters of type AbsoluteDate | |
|---|---|
BasicBoardSun(AbsoluteDate ref,
double alpha1,
double alpha2,
double nu1,
double nu2,
double lon1,
double epsilon)
Constructor with user values. |
|
| Uses of AbsoluteDate in fr.cnes.sirius.patrius.events |
|---|
| Methods in fr.cnes.sirius.patrius.events that return AbsoluteDate | |
|---|---|
AbsoluteDate |
CodedEvent.getDate()
|
AbsoluteDate |
CodedEventsLogger.LoggedCodedEvent.getDate()
|
| Methods in fr.cnes.sirius.patrius.events with parameters of type AbsoluteDate | |
|---|---|
static CodedEvent |
CodedEvent.buildUndefinedEvent(AbsoluteDate date,
boolean isStarting)
Factory method for an undefined event, that still has a valid date. |
Set<CodedEvent> |
CodedEventsList.getEvents(String code,
String comment,
AbsoluteDate date)
Finds one/more events in the list of CodedEvent following some criteria.When a comment and a date are available, the method looks for a specific event in the list, otherwise if only the code is given as input, it looks for a list of events with the same code. |
void |
EarthZoneDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
CombinedPhenomenaDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
GenericCodingEventDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
| Constructors in fr.cnes.sirius.patrius.events with parameters of type AbsoluteDate | |
|---|---|
CodedEvent(String codeIn,
String commentIn,
AbsoluteDate dateIn,
boolean startingEventIn)
Constructor for the coded event. |
|
| Uses of AbsoluteDate in fr.cnes.sirius.patrius.events.multi |
|---|
| Methods in fr.cnes.sirius.patrius.events.multi that return AbsoluteDate | |
|---|---|
AbsoluteDate |
MultiCodedEventsLogger.MultiLoggedCodedEvent.getDate()
|
| Methods in fr.cnes.sirius.patrius.events.multi with parameters of type AbsoluteDate | |
|---|---|
void |
MultiGenericCodingEventDetector.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
|
| Uses of AbsoluteDate in fr.cnes.sirius.patrius.events.sensor |
|---|
| Methods in fr.cnes.sirius.patrius.events.sensor with parameters of type AbsoluteDate | |
|---|---|
void |
SatToSatMutualVisibilityDetector.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
|
void |
SatToSatMutualVisibilityDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
MaskingDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation. |
void |
ExtremaSightAxisDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
SensorVisibilityDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
VisibilityFromStationDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation. |
void |
TargetInFieldOfViewDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
StationToSatMutualVisibilityDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
SensorInhibitionDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
SecondarySpacecraft.updateSpacecraftState(AbsoluteDate date)
Updates the assembly frames at a given date from the orbit and attitude information provided by the propagator. |
| Uses of AbsoluteDate in fr.cnes.sirius.patrius.forces.radiation |
|---|
| Methods in fr.cnes.sirius.patrius.forces.radiation with parameters of type AbsoluteDate | |
|---|---|
static double |
PatriusSolarRadiationPressure.getLightningRatio(PVCoordinatesProvider sun,
GeometricBodyShape earthModel,
Vector3D position,
Frame frame,
AbsoluteDate date)
Get the lightning ratio ([0-1]). |
| Uses of AbsoluteDate in fr.cnes.sirius.patrius.groundstation |
|---|
| Methods in fr.cnes.sirius.patrius.groundstation with parameters of type AbsoluteDate | |
|---|---|
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 AbsoluteDate in fr.cnes.sirius.patrius.guidance |
|---|
| Methods in fr.cnes.sirius.patrius.guidance that return AbsoluteDate | |
|---|---|
AbsoluteDate |
Vector3DPolynomialSegment.getDateZero()
Get the date zero of the polynomial functions. |
| Methods in fr.cnes.sirius.patrius.guidance with parameters of type AbsoluteDate | |
|---|---|
void |
GuidanceProfile.checkDate(AbsoluteDate userDate)
Check date validity |
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. |
Rotation |
QuaternionPolynomialSegment.getOrientation(AbsoluteDate date)
Get the orientation from the quaternion polynomials at a given date. |
Vector3D |
Vector3DPolynomialSegment.getVector3D(AbsoluteDate date)
Get the angular velocity from the vector 3D polynomials at a given date. |
| Constructors in fr.cnes.sirius.patrius.guidance with parameters of type AbsoluteDate | |
|---|---|
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. |
|
QuaternionHarmonicProfile(AbsoluteDate origin,
Frame frame,
FourierSeries q0,
FourierSeries q1,
FourierSeries q2,
FourierSeries q3,
AbsoluteDateInterval timeInterval)
Create a harmonic, quaternion guidance profile. |
|
QuaternionPolynomialSegment(PolynomialFunctionLagrangeForm q0,
PolynomialFunctionLagrangeForm q1,
PolynomialFunctionLagrangeForm q2,
PolynomialFunctionLagrangeForm q3,
AbsoluteDate date0,
AbsoluteDateInterval timeInterval)
Build a quaternion polynomial guidance profile on a segment. The polynomial representing the quaternion components are on lagrange form. |
|
QuaternionPolynomialSegment(PolynomialFunction q0,
PolynomialFunction q1,
PolynomialFunction q2,
PolynomialFunction q3,
AbsoluteDate date0,
AbsoluteDateInterval timeInterval)
Build a quaternion polynomial guidance profile on a segment. The polynomial representing the quaternion components are generic polynomial functions. |
|
Vector3DPolynomialSegment(PolynomialFunctionLagrangeForm x,
PolynomialFunctionLagrangeForm y,
PolynomialFunctionLagrangeForm z,
AbsoluteDate date0,
AbsoluteDateInterval timeInterval)
Build an angular velocity polynomial guidance profile on a segment. The polynomial representing the vector 3D components are on lagrange form. |
|
Vector3DPolynomialSegment(PolynomialFunction x,
PolynomialFunction y,
PolynomialFunction z,
AbsoluteDate date0,
AbsoluteDateInterval timeInterval)
Build an angular velocity polynomial guidance profile on a segment. The polynomial representing the vector 3D components are generic polynomial functions. |
|
| Uses of AbsoluteDate in fr.cnes.sirius.patrius.propagation |
|---|
| Methods in fr.cnes.sirius.patrius.propagation with parameters of type AbsoluteDate | |
|---|---|
double[] |
SimpleAdditionalStateProvider.getAdditionalState(AbsoluteDate date)
Get the additional state. |
Map<String,SpacecraftState> |
MultiPropagator.propagate(AbsoluteDate target)
Propagate towards a target date. |
Map<String,SpacecraftState> |
MultiPropagator.propagate(AbsoluteDate start,
AbsoluteDate target)
Propagate from a start date towards a target date. |
protected Orbit |
PVCoordinatePropagator.propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date. |
| Constructors in fr.cnes.sirius.patrius.propagation with parameters of type AbsoluteDate | |
|---|---|
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. |
|
SimpleAdditionalStateProvider(String name,
AbsoluteDate[] dateTab,
double[][] additionalStatesTab,
ISearchIndex algo)
Creates an instance of SimpleAdditionalStateProvider from a name describing the additional state double table, a table of dates, and a table of additional states associated to these dates. |
|
| Uses of AbsoluteDate in fr.cnes.sirius.patrius.propagation.events.multi |
|---|
| Methods in fr.cnes.sirius.patrius.propagation.events.multi with parameters of type AbsoluteDate | |
|---|---|
void |
OneSatEventDetectorWrapper.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
|
void |
MultiAbstractDetector.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
|
| Constructors in fr.cnes.sirius.patrius.propagation.events.multi with parameters of type AbsoluteDate | |
|---|---|
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. |
|
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 AbsoluteDate in fr.cnes.sirius.patrius.propagation.numerical.multi |
|---|
| Methods in fr.cnes.sirius.patrius.propagation.numerical.multi with parameters of type AbsoluteDate | |
|---|---|
PVCoordinates |
MultiNumericalPropagator.getPVCoordinates(AbsoluteDate date,
Frame frame,
String satId)
Get the PVCoordinates of the body in the selected 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. |
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. |
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 |
Map<String,SpacecraftState> |
MultiNumericalPropagator.propagate(AbsoluteDate target)
|
Map<String,SpacecraftState> |
MultiNumericalPropagator.propagate(AbsoluteDate start,
AbsoluteDate target)
|
void |
MultiEphemerisModeHandler.setReference(AbsoluteDate newReference)
Define new reference date. |
void |
MultiModeHandler.setReference(AbsoluteDate newReference)
Define new reference date. |
| Uses of AbsoluteDate in fr.cnes.sirius.patrius.propagation.precomputed.multi |
|---|
| Methods in fr.cnes.sirius.patrius.propagation.precomputed.multi that return AbsoluteDate | |
|---|---|
AbsoluteDate |
MultiIntegratedEphemeris.getMaxDate()
Get the last date of the range. |
AbsoluteDate |
MultiIntegratedEphemeris.getMinDate()
Get the first date of the range. |
| Methods in fr.cnes.sirius.patrius.propagation.precomputed.multi with parameters of type AbsoluteDate | |
|---|---|
protected SpacecraftState |
MultiIntegratedEphemeris.basicPropagate(AbsoluteDate date)
Propagate an orbit without any fancy features. |
PVCoordinates |
MultiIntegratedEphemeris.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the PVCoordinates of the body in the selected frame. |
protected Orbit |
MultiIntegratedEphemeris.propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date. |
| Constructor parameters in fr.cnes.sirius.patrius.propagation.precomputed.multi with type arguments of type AbsoluteDate | |
|---|---|
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. |
|
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. |
|
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 AbsoluteDate in fr.cnes.sirius.patrius.propagation.sampling.multi |
|---|
| Methods in fr.cnes.sirius.patrius.propagation.sampling.multi that return AbsoluteDate | |
|---|---|
AbsoluteDate |
MultiOrekitStepInterpolator.getCurrentDate()
Get the current grid date. |
AbsoluteDate |
MultiAdaptedStepHandler.getCurrentDate()
Get the current grid date. |
AbsoluteDate |
MultiOrekitStepInterpolator.getInterpolatedDate()
Get the interpolated date. |
AbsoluteDate |
MultiAdaptedStepHandler.getInterpolatedDate()
Get the interpolated date. |
AbsoluteDate |
MultiOrekitStepInterpolator.getPreviousDate()
Get the previous grid date. |
AbsoluteDate |
MultiAdaptedStepHandler.getPreviousDate()
Get the previous grid date. |
| Methods in fr.cnes.sirius.patrius.propagation.sampling.multi with parameters of type AbsoluteDate | |
|---|---|
void |
MultiOrekitStepNormalizer.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
Initialize step handler at the start of a propagation. |
void |
MultiOrekitStepHandler.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
Initialize step handler at the start of a propagation. |
void |
MultiOrekitFixedStepHandler.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
Initialize step handler at the start of a propagation. |
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. |
void |
MultiOrekitStepInterpolator.setInterpolatedDate(AbsoluteDate date)
Set the interpolated date. |
void |
MultiAdaptedStepHandler.setInterpolatedDate(AbsoluteDate date)
Set the interpolated date. |
void |
MultiAdaptedStepHandler.setReference(AbsoluteDate newReference)
Define new reference date. |
| Uses of AbsoluteDate in fr.cnes.sirius.patrius.signalpropagation |
|---|
| Methods in fr.cnes.sirius.patrius.signalpropagation that return AbsoluteDate | |
|---|---|
AbsoluteDate |
SignalPropagation.getEndDate()
|
AbsoluteDate |
SignalPropagation.getStartDate()
|
| Methods in fr.cnes.sirius.patrius.signalpropagation with parameters of type AbsoluteDate | |
|---|---|
SignalPropagation |
SignalPropagationModel.computeSignalPropagation(PVCoordinatesProvider transmitter,
PVCoordinatesProvider receiver,
AbsoluteDate date,
SignalPropagationModel.FixedDate fixedDateType)
Computes the signal propagation object in the void at a particular date |
| Constructors in fr.cnes.sirius.patrius.signalpropagation with parameters of type AbsoluteDate | |
|---|---|
SignalPropagation(Vector3D propagationVector,
AbsoluteDate inEmissionDate,
AbsoluteDate inReceptionDate,
Frame refFrame,
SignalPropagationModel.FixedDate fixedDate)
Constructor with computation of one of the dates |
|
| Uses of AbsoluteDate in fr.cnes.sirius.patrius.signalpropagation.iono |
|---|
| Methods in fr.cnes.sirius.patrius.signalpropagation.iono with parameters of type AbsoluteDate | |
|---|---|
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. |
fr.cnes.sirius.patrius.signalpropagation.iono.USKData |
USKProvider.getData(AbsoluteDate date,
double r12)
Returns the USK data for the Bent model. |
fr.cnes.sirius.patrius.signalpropagation.iono.USKData |
USKLoader.getData(AbsoluteDate date,
double r12)
Returns the USK data for the Bent model. |
double |
R12Provider.getR12(AbsoluteDate date)
Provides the R12 value for the Bent model. |
double |
R12Loader.getR12(AbsoluteDate date)
|
| Uses of AbsoluteDate in fr.cnes.sirius.patrius.stela.bodies |
|---|
| Methods in fr.cnes.sirius.patrius.stela.bodies with parameters of type AbsoluteDate | |
|---|---|
static double |
EarthRotation.getEarthRotationRate(AbsoluteDate date)
Deprecated. |
static double |
EarthRotation.getERA(AbsoluteDate date)
Compute the Earth Rotation Angle (ERA) using Capitaine model (2000). |
static double |
EarthRotation.getERADerivative(AbsoluteDate date)
Compute the Earth Rotation Angle (ERA) derivative. |
double |
GeodPosition.getGeodeticLongitude(Vector3D position,
AbsoluteDate date)
Compute the geodetic longitude at a given date. |
static double |
EarthRotation.getGMST(AbsoluteDate date)
Compute Greenwich Mean Sideral Time. |
static double |
EarthRotation.getGMSTDerivative(AbsoluteDate date)
Compute Greenwich Mean Sideral Time derivative. |
PVCoordinates |
MeeusSunStela.getPVCoordinates(AbsoluteDate date,
Frame frame)
|
PVCoordinates |
MeeusMoonStela.getPVCoordinates(AbsoluteDate date,
Frame frame)
|
double |
GeodPosition.getTloc(Vector3D position,
Vector3D positionSun,
AbsoluteDate date)
Compute the local solar time at a given date. |
static void |
MeeusSunStela.updateTransform(AbsoluteDate date,
Frame frame)
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 AbsoluteDate in fr.cnes.sirius.patrius.stela.forces |
|---|
| Methods in fr.cnes.sirius.patrius.stela.forces that return AbsoluteDate | |
|---|---|
static AbsoluteDate[] |
Squaring.getSquaringJDCNES()
|
| Uses of AbsoluteDate in fr.cnes.sirius.patrius.stela.forces.atmospheres |
|---|
| Methods in fr.cnes.sirius.patrius.stela.forces.atmospheres with parameters of type AbsoluteDate | |
|---|---|
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 AbsoluteDate in fr.cnes.sirius.patrius.stela.forces.noninertial |
|---|
| Methods in fr.cnes.sirius.patrius.stela.forces.noninertial with parameters of type AbsoluteDate | |
|---|---|
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. |
| Uses of AbsoluteDate in fr.cnes.sirius.patrius.stela.orbits |
|---|
| Methods in fr.cnes.sirius.patrius.stela.orbits with parameters of type AbsoluteDate | |
|---|---|
PVCoordinates |
StelaEquinoctialOrbit.getPVCoordinates(AbsoluteDate otherDate,
Frame otherFrame)
|
Orbit |
StelaEquinoctialOrbit.interpolate(AbsoluteDate date,
Collection<Orbit> sample)
Get an interpolated instance. |
| Constructors in fr.cnes.sirius.patrius.stela.orbits with parameters of type AbsoluteDate | |
|---|---|
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 AbsoluteDate in fr.cnes.sirius.patrius.stela.propagation |
|---|
| Fields in fr.cnes.sirius.patrius.stela.propagation declared as AbsoluteDate | |
|---|---|
protected AbsoluteDate |
StelaGTOPropagator.maxDate
Max date after which simulation has to fail if exception mecanism was triggered |
| Methods in fr.cnes.sirius.patrius.stela.propagation that return AbsoluteDate | |
|---|---|
AbsoluteDate |
StelaBasicInterpolator.getCurrentDate()
Get the current grid date. |
AbsoluteDate |
StelaBasicInterpolator.getInterpolatedDate()
Get the interpolated date. |
AbsoluteDate |
StelaBasicInterpolator.getPreviousDate()
Get the previous grid date. |
AbsoluteDate |
StelaGTOPropagator.getReferenceDate()
Get the reference date |
| Methods in fr.cnes.sirius.patrius.stela.propagation with parameters of type AbsoluteDate | |
|---|---|
protected SpacecraftState |
StelaAbstractPropagator.acceptStep(AbsoluteDate target,
double epsilon)
Accept a step, triggering events and step handlers. |
protected SpacecraftState |
StelaAbstractPropagator.basicPropagate(AbsoluteDate date)
Propagate a SpacecraftState without any fancy features. |
protected abstract double |
StelaAbstractPropagator.getMass(AbsoluteDate date)
Get the mass. |
protected double |
StelaGTOPropagator.getMass(AbsoluteDate date)
|
PVCoordinates |
StelaAbstractPropagator.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the PVCoordinates of the body in the selected frame. |
SpacecraftState |
StelaAbstractPropagator.goAhead(double stepSize,
double dt,
AbsoluteDate target)
go one step ahead |
void |
ForcesStepHandler.init(SpacecraftState s0,
AbsoluteDate t)
|
SpacecraftState |
StelaAbstractPropagator.propagate(AbsoluteDate target)
Propagate towards a target date. |
SpacecraftState |
StelaAbstractPropagator.propagate(AbsoluteDate start,
AbsoluteDate target)
Propagate from a start date towards a target date. |
SpacecraftState |
StelaGTOPropagator.propagate(AbsoluteDate start,
AbsoluteDate target)
|
protected abstract SpacecraftState |
StelaAbstractPropagator.propagateSpacecraftState(AbsoluteDate date)
Extrapolate a spacecraftState up to a specific target date. |
protected SpacecraftState |
StelaGTOPropagator.propagateSpacecraftState(AbsoluteDate date)
|
SpacecraftState |
StelaAbstractPropagator.propagationManagement(SpacecraftState state,
double stepSize,
double dt,
AbsoluteDate target)
Manages the current step, method to override when user wants to deal with exceptions during the propagation. |
SpacecraftState |
StelaGTOPropagator.propagationManagement(SpacecraftState state,
double stepSize,
double dt,
AbsoluteDate target)
|
void |
StelaBasicInterpolator.setInterpolatedDate(AbsoluteDate interpolatedDate)
Set the interpolated date. |
protected void |
StelaAbstractPropagator.setStartDate(AbsoluteDate startDateIn)
Set a start date. |
| Uses of AbsoluteDate in fr.cnes.sirius.patrius.tools.ephemerisComparator |
|---|
| Subclasses of AbsoluteDate in fr.cnes.sirius.patrius.tools.ephemerisComparator | |
|---|---|
class |
DateDPFacade
This class is a facade for the use of dates. |
| Uses of AbsoluteDate in fr.cnes.sirius.patrius.tools.force.validation |
|---|
| Methods in fr.cnes.sirius.patrius.tools.force.validation that return types with arguments of type AbsoluteDate | |
|---|---|
List<AbsoluteDate> |
PVEphemerisLoader.getDates()
Give the list of dates which have been read. |
| Methods in fr.cnes.sirius.patrius.tools.force.validation with parameters of type AbsoluteDate | |
|---|---|
PVCoordinates |
BasicPVCoordinatesProvider.getPVCoordinates(AbsoluteDate date,
Frame inFrame)
Get the PVCoordinates of the body in the selected frame. |
| Uses of AbsoluteDate in fr.cnes.sirius.patrius.utils |
|---|
| Methods in fr.cnes.sirius.patrius.utils that return AbsoluteDate | |
|---|---|
AbsoluteDate |
GPSAlmanacParameters.getDate(int weekNumber,
double milliInWeek)
|
abstract AbsoluteDate |
AlmanacParameter.getDate(int weekNumber,
double milliInWeek)
Returns GNSS date given a week number and second in the week. |
AbsoluteDate |
GalileoAlmanacParameters.getDate(int weekNumber,
double milliInWeek)
|
| Methods in fr.cnes.sirius.patrius.utils with parameters of type AbsoluteDate | |
|---|---|
PVCoordinates |
AlmanacPVCoordinates.getPVCoordinates(AbsoluteDate date,
Frame frame)
Geometric computation of the position to a date. |
| Uses of AbsoluteDate in fr.cnes.sirius.validate.mocks.ephemeris |
|---|
| Methods in fr.cnes.sirius.validate.mocks.ephemeris that return types with arguments of type AbsoluteDate | |
|---|---|
Map<AbsoluteDate,PVCoordinates> |
UserEphemeris.getEphemeris()
|
Map<AbsoluteDate,PVCoordinates> |
IUserEphemeris.getEphemeris()
|
| Methods in fr.cnes.sirius.validate.mocks.ephemeris with parameters of type AbsoluteDate | |
|---|---|
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. |
| Uses of AbsoluteDate in org.orekit.attitudes |
|---|
| Methods in org.orekit.attitudes that return AbsoluteDate | |
|---|---|
AbsoluteDate |
Attitude.getDate()
Get the date of attitude parameters. |
| Methods in org.orekit.attitudes with parameters of type AbsoluteDate | |
|---|---|
protected double |
FixedStepAttitudeEphemerisGenerator.computeStep(AbsoluteDate date,
AbsoluteDateInterval ephemerisInterval)
|
protected abstract double |
AbstractAttitudeEphemerisGenerator.computeStep(AbsoluteDate date,
AbsoluteDateInterval ephemerisInterval)
Computes the step used during attitude ephemeris generation. |
protected double |
VariableStepAttitudeEphemerisGenerator.computeStep(AbsoluteDate date,
AbsoluteDateInterval ephemerisInterval)
Computes the step used during the variable step ephemeris generation. |
Attitude |
Slew.getAttitude(AbsoluteDate date,
Frame frame)
Compute the attitude. |
Attitude |
ConstantSpinSlew.getAttitude(AbsoluteDate date,
Frame frame)
|
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 |
InertialProvider.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Deprecated. 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 |
TwoDirectionsAttitude.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state. |
Attitude |
AttitudeLegLaw.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state. |
Attitude |
AttitudeProvider.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state. |
Attitude |
TabulatedAttitude.getAttitude(PVCoordinatesProvider pvProvider,
AbsoluteDate date,
Frame inFrame)
Compute the attitude corresponding to an orbital state. |
Attitude |
CelestialBodyPointed.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state. |
Attitude |
AbstractSlew.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
|
Attitude |
AttitudeLegsSequence.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Gets the attitude from the sequence. The AttitudeLeg matching the date is called to compute the attitude. |
Attitude |
RelativeTabulatedAttitudeLeg.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state. |
Attitude |
LofOffsetPointing.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state. |
Attitude |
SpinStabilized.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state. |
Attitude |
FixedRate.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state. |
Attitude |
GroundPointing.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state. |
Attitude |
AttitudesSequence.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state. |
AttitudeLeg |
AttitudeLegsSequence.getAttitudeLeg(AbsoluteDate date)
Gets the AttitudeLeg corresponding to the date. |
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. |
Transform |
OrientationTransformProvider.getTransform(AbsoluteDate date)
Get the Transform corresponding to specified date. |
Transform |
AttitudeTransformProvider.getTransform(AbsoluteDate date)
Get the Transform corresponding to specified date. |
Transform |
OrientationTransformProvider.getTransform(AbsoluteDate date,
boolean computeSpinDerivatives)
Get the Transform corresponding to specified date. |
Transform |
AttitudeTransformProvider.getTransform(AbsoluteDate date,
boolean computeSpinDerivatives)
Get the Transform corresponding to specified date. |
Transform |
OrientationTransformProvider.getTransform(AbsoluteDate date,
FramesConfiguration config)
Get the Transform corresponding to specified date. |
Transform |
AttitudeTransformProvider.getTransform(AbsoluteDate date,
FramesConfiguration config)
Get the Transform corresponding to specified date. |
Transform |
OrientationTransformProvider.getTransform(AbsoluteDate date,
FramesConfiguration config,
boolean computeSpinDerivatives)
Get the Transform corresponding to specified date. |
Transform |
AttitudeTransformProvider.getTransform(AbsoluteDate date,
FramesConfiguration config,
boolean computeSpinDerivatives)
Get the Transform corresponding to specified date. |
double |
YawCompensation.getYawAngle(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the yaw compensation angle at date. |
Attitude |
Attitude.interpolate(AbsoluteDate interpolationDate,
Collection<Attitude> sample)
Get an interpolated instance. |
Attitude |
Attitude.interpolate(AbsoluteDate interpolationDate,
Collection<Attitude> sample,
boolean computeSpinDerivatives)
Interpolates attitude. |
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. |
| Constructors in org.orekit.attitudes with parameters of type AbsoluteDate | |
|---|---|
AbstractSlew(AttitudeProvider initialLaw,
AttitudeProvider finalLaw,
AbsoluteDate initialDate,
AbsoluteDate finalDate)
Builds a slew when its interval of validity is known. |
|
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. |
|
AttitudeLawLeg(AttitudeLaw attitudeLaw,
AbsoluteDate initialDate,
AbsoluteDate finalDate)
Build an attitude law version "attitude". |
|
ConstantSpinSlew(AttitudeProvider initialLaw,
AttitudeProvider finalLaw,
AbsoluteDate initialDate,
AbsoluteDate finalDate)
Builds a ConstantSpinSlew based on a given interval of dates |
|
ConstantSpinSlew(AttitudeProvider initialLaw,
AttitudeProvider finalLaw,
AbsoluteDate date,
boolean isStartDate,
double constraintValue,
ConstantSpinSlew.Constraint constraintType)
Builds a ConstantSpinSlew from a type of constraint and its value |
|
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. |
|
SpinStabilized(AttitudeLaw pNonRotatingLaw,
AbsoluteDate pStart,
Vector3D pAxis,
double pRate)
Creates a new instance. |
|
TwoSpinBiasSlew(AttitudeProvider initialLaw,
AttitudeProvider targetLaw,
AbsoluteDate initialDate,
double dtSCAOIn,
double thetaMaxIn,
double tauIn,
double epsInRall,
double omegaHigh,
double thetaSwitch,
double epsOutRall,
double omegaLow,
double tStab)
This class extends the AbstractSlew. |
|
| Uses of AbsoluteDate in org.orekit.attitudes.directions |
|---|
| Methods in org.orekit.attitudes.directions with parameters of type AbsoluteDate | |
|---|---|
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 |
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 |
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 |
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. |
| Uses of AbsoluteDate in org.orekit.attitudes.kinematics |
|---|
| Methods in org.orekit.attitudes.kinematics that return AbsoluteDate | |
|---|---|
AbsoluteDate |
AbstractVector3DFunction.getZeroDate()
Get the date at x = 0. |
AbsoluteDate |
AbstractOrientationFunction.getZeroDate()
Get the date at x = 0. |
| Methods in org.orekit.attitudes.kinematics with parameters of type AbsoluteDate | |
|---|---|
Vector3D |
AbstractOrientationFunction.computeSpin(AbsoluteDate date)
Estimate the spin at a given date from the current OrientationFunction using the quaternions formula:
Ω = 2 * Q' dQ, where Q' is the conjugate of the quaternion and dQ is the derivative of the quaternion at
the given date. |
Vector3D |
AbstractOrientationFunction.estimateRate(AbsoluteDate date,
double dt)
Estimate the spin at a given date from the current OrientationFunction using the
AngularCoordinates.estimateRate(Rotation, Rotation, double) method. |
abstract Rotation |
AbstractOrientationFunction.getOrientation(AbsoluteDate date)
Get the orientation at a given date. |
Rotation |
OrientationFunction.getOrientation(AbsoluteDate date)
Get the orientation at a given date. |
abstract Vector3D |
AbstractVector3DFunction.getVector3D(AbsoluteDate date)
Get the vector at a given date. |
Vector3D |
Vector3DFunction.getVector3D(AbsoluteDate date)
Get the vector at a given date. |
static Rotation |
KinematicsToolkit.integrate(KinematicsToolkit.IntegrationType type,
Rotation initOrientation,
AbsoluteDate initDate,
AbsoluteDate finalDate,
Vector3DFunction spin,
double step)
Integrate a spin function. |
| Constructors in org.orekit.attitudes.kinematics with parameters of type AbsoluteDate | |
|---|---|
AbstractOrientationFunction(AbsoluteDate zeroDate)
Constructor setting a default finite differences differentiator. |
|
AbstractOrientationFunction(AbsoluteDate zeroDate,
UnivariateVectorFunctionDifferentiator inDifferentiator)
|
|
AbstractVector3DFunction(AbsoluteDate zeroDate)
Constructor setting a default finite differences differentiator and a default trapezoid integrator. |
|
AbstractVector3DFunction(AbsoluteDate zeroDate,
UnivariateVectorFunctionDifferentiator inDifferentiator)
Constructor setting a default trapezoid integrator. |
|
AbstractVector3DFunction(AbsoluteDate zeroDate,
UnivariateVectorFunctionDifferentiator inDifferentiator,
UnivariateIntegrator inIntegrator)
Constructor. |
|
| Uses of AbsoluteDate in org.orekit.bodies |
|---|
| Methods in org.orekit.bodies that return AbsoluteDate | |
|---|---|
AbsoluteDate |
PosVelChebyshev.getDate()
Get the date. |
| Methods in org.orekit.bodies with parameters of type AbsoluteDate | |
|---|---|
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.getOccultingRadius(Vector3D position,
Frame frame,
AbsoluteDate date,
PVCoordinatesProvider occultedBody)
Calculate the apparent radius. |
double |
ExtendedOneAxisEllipsoid.getOccultingRadius(Vector3D position,
Frame frame,
AbsoluteDate date,
PVCoordinatesProvider occultedBody)
|
Vector3D |
IAUPole.getPole(AbsoluteDate date)
Get the body North pole direction in EME2000 frame. |
PVCoordinates |
PosVelChebyshev.getPositionVelocity(AbsoluteDate date)
Get the position-velocity at a specified date. |
double |
IAUPole.getPrimeMeridianAngle(AbsoluteDate date)
Get the prime meridian angle. |
PVCoordinates |
MeeusMoon.getPVCoordinates(AbsoluteDate date,
Frame frame)
|
PVCoordinates |
ExtendedOneAxisEllipsoid.getPVCoordinates(AbsoluteDate date,
Frame frame)
|
PVCoordinates |
MeeusSun.getPVCoordinates(AbsoluteDate date,
Frame frame)
|
abstract PVCoordinates |
AbstractCelestialBody.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the PVCoordinates of the body in the selected frame. |
boolean |
PosVelChebyshev.inRange(AbsoluteDate date)
Check if a date is in validity range. |
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. |
| Constructors in org.orekit.bodies with parameters of type AbsoluteDate | |
|---|---|
PosVelChebyshev(AbsoluteDate start,
double duration,
double[] xCoeffs,
double[] yCoeffs,
double[] zCoeffs)
Simple constructor. |
|
| Uses of AbsoluteDate in org.orekit.files.general |
|---|
| Methods in org.orekit.files.general that return AbsoluteDate | |
|---|---|
AbsoluteDate |
SatelliteTimeCoordinate.getDate()
Get the date. |
AbsoluteDate |
SatelliteTimeCoordinate.getEpoch()
Returns the epoch for this coordinate. |
AbsoluteDate |
OrbitFile.getEpoch()
Returns the start epoch of the orbit file. |
| Methods in org.orekit.files.general with parameters of type AbsoluteDate | |
|---|---|
void |
SatelliteTimeCoordinate.setEpoch(AbsoluteDate epoch)
Set the epoch for this coordinate. |
| Constructors in org.orekit.files.general with parameters of type AbsoluteDate | |
|---|---|
SatelliteTimeCoordinate(AbsoluteDate time,
PVCoordinates coord)
Creates a new SatelliteTimeCoordinate instance with
a given epoch and coordinate. |
|
SatelliteTimeCoordinate(AbsoluteDate time,
PVCoordinates coord,
double clockCorr,
double rateChange)
Creates a new SatelliteTimeCoordinate instance with a given
epoch, coordinate and clock value / rate change. |
|
SatelliteTimeCoordinate(AbsoluteDate time,
Vector3D pos,
double clock)
Creates a new SatelliteTimeCoordinate object with a given epoch
and position coordinate. |
|
| Uses of AbsoluteDate in org.orekit.files.sp3 |
|---|
| Methods in org.orekit.files.sp3 that return AbsoluteDate | |
|---|---|
AbsoluteDate |
SP3File.getEpoch()
Returns the start epoch of the orbit file. |
| Methods in org.orekit.files.sp3 with parameters of type AbsoluteDate | |
|---|---|
void |
SP3File.setEpoch(AbsoluteDate time)
Set the epoch of the SP3 file. |
| Uses of AbsoluteDate in org.orekit.forces.atmospheres |
|---|
| Methods in org.orekit.forces.atmospheres that return AbsoluteDate | |
|---|---|
AbsoluteDate |
MSISE2000InputParameters.getMaxDate()
Gets the available data range maximum date. |
AbsoluteDate |
DTM2000InputParameters.getMaxDate()
Gets the available data range maximum date. |
AbsoluteDate |
JB2006InputParameters.getMaxDate()
Gets the available data range maximum date. |
AbsoluteDate |
MSISE2000InputParameters.getMinDate()
Gets the available data range minimum date. |
AbsoluteDate |
DTM2000InputParameters.getMinDate()
Gets the available data range minimum date. |
AbsoluteDate |
JB2006InputParameters.getMinDate()
Gets the available data range minimum date. |
| Methods in org.orekit.forces.atmospheres with parameters of type AbsoluteDate | |
|---|---|
double |
DTM2000InputParameters.get24HoursKp(AbsoluteDate date)
Get the last 24H mean geomagnetic index. |
double |
JB2006InputParameters.getAp(AbsoluteDate date)
Get the Geomagnetic planetary 3-hour index Ap. |
double[] |
MSISE2000InputParameters.getApValues(AbsoluteDate date)
Get the array containing the 7 ap values |
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 |
JB2006InputParameters.getF10(AbsoluteDate date)
Get the value of the instantaneous solar flux index (1e-22*Watt/(m2*Hertz)). |
double |
JB2006InputParameters.getF10B(AbsoluteDate date)
Get the value of the mean solar flux. |
double |
MSISE2000InputParameters.getInstantFlux(AbsoluteDate date)
Get the value of the instantaneous solar flux. |
double |
DTM2000InputParameters.getInstantFlux(AbsoluteDate date)
Get the value of the instantaneous solar flux. |
double |
MSISE2000InputParameters.getMeanFlux(AbsoluteDate date)
Get the 81 day average of F10.7 flux. |
double |
DTM2000InputParameters.getMeanFlux(AbsoluteDate date)
Get the value of the mean solar flux. |
double |
US76.getPress(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local pressure for altitude in interval [0, 1E6] m |
double |
JB2006InputParameters.getS10(AbsoluteDate date)
Get the EUV index (26-34 nm) scaled to F10. |
double |
JB2006InputParameters.getS10B(AbsoluteDate date)
Get the EUV 81-day averaged centered index. |
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 |
double |
DTM2000InputParameters.getThreeHourlyKP(AbsoluteDate date)
Get the value of the 3 hours geomagnetic index. |
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. |
double |
JB2006InputParameters.getXM10(AbsoluteDate date)
Get the MG2 index scaled to F10. |
double |
JB2006InputParameters.getXM10B(AbsoluteDate date)
Get the MG2 81-day average centered index. |
| Uses of AbsoluteDate in org.orekit.forces.atmospheres.solarActivity |
|---|
| Methods in org.orekit.forces.atmospheres.solarActivity that return AbsoluteDate | |
|---|---|
AbsoluteDate |
SolarActivityDataReader.getApKpMaxDate()
Get maximum date of ap / kp values |
AbsoluteDate |
ExtendedSolarActivityWrapper.getApKpMaxDate()
Get maximum date of ap / kp values |
AbsoluteDate |
ConstantSolarActivity.getApKpMaxDate()
Get maximum date of ap / kp values |
AbsoluteDate |
SolarActivityDataProvider.getApKpMaxDate()
Get maximum date of ap / kp values |
AbsoluteDate |
SolarActivityDataReader.getApKpMinDate()
Get minimum date of ap / kp values |
AbsoluteDate |
ExtendedSolarActivityWrapper.getApKpMinDate()
Get minimum date of ap / kp values |
AbsoluteDate |
ConstantSolarActivity.getApKpMinDate()
Get minimum date of ap / kp values |
AbsoluteDate |
SolarActivityDataProvider.getApKpMinDate()
Get minimum date of ap / kp values |
AbsoluteDate |
SolarActivityDataReader.getFluxMaxDate()
Get maximum date of flux values |
AbsoluteDate |
ExtendedSolarActivityWrapper.getFluxMaxDate()
Get maximum date of flux values |
AbsoluteDate |
ConstantSolarActivity.getFluxMaxDate()
Get maximum date of flux values |
AbsoluteDate |
SolarActivityDataProvider.getFluxMaxDate()
Get maximum date of flux values |
AbsoluteDate |
SolarActivityDataReader.getFluxMinDate()
Get minimum date of flux values |
AbsoluteDate |
ExtendedSolarActivityWrapper.getFluxMinDate()
Get minimum date of flux values |
AbsoluteDate |
ConstantSolarActivity.getFluxMinDate()
Get minimum date of flux values |
AbsoluteDate |
SolarActivityDataProvider.getFluxMinDate()
Get minimum date of flux values |
AbsoluteDate |
SolarActivityDataReader.getMaxDate()
Get maximum date at which both flux and ap values are available |
AbsoluteDate |
ExtendedSolarActivityWrapper.getMaxDate()
Get maximum date at which both flux and ap values are available |
AbsoluteDate |
ConstantSolarActivity.getMaxDate()
Get maximum date at which both flux and ap values are available |
AbsoluteDate |
SolarActivityDataProvider.getMaxDate()
Get maximum date at which both flux and ap values are available |
AbsoluteDate |
SolarActivityDataReader.getMinDate()
Get minimum date at which both flux and ap values are available |
AbsoluteDate |
ExtendedSolarActivityWrapper.getMinDate()
Get minimum date at which both flux and ap values are available |
AbsoluteDate |
ConstantSolarActivity.getMinDate()
Get minimum date at which both flux and ap values are available |
AbsoluteDate |
SolarActivityDataProvider.getMinDate()
Get minimum date at which both flux and ap values are available |
| Methods in org.orekit.forces.atmospheres.solarActivity that return types with arguments of type AbsoluteDate | |
|---|---|
SortedMap<AbsoluteDate,Double[]> |
SolarActivityDataReader.getApKpValues(AbsoluteDate date1,
AbsoluteDate date2)
Get ap / kp values between the given dates |
SortedMap<AbsoluteDate,Double[]> |
ExtendedSolarActivityWrapper.getApKpValues(AbsoluteDate date1,
AbsoluteDate date2)
Get ap / kp values between the given dates |
SortedMap<AbsoluteDate,Double[]> |
ConstantSolarActivity.getApKpValues(AbsoluteDate date1,
AbsoluteDate date2)
Get ap / kp values between the given dates |
SortedMap<AbsoluteDate,Double[]> |
SolarActivityDataProvider.getApKpValues(AbsoluteDate date1,
AbsoluteDate date2)
Get ap / kp values between the given dates |
SortedMap<AbsoluteDate,Double> |
SolarActivityDataReader.getInstantFluxValues(AbsoluteDate date1,
AbsoluteDate date2)
Get raw instant flux values between the given dates |
SortedMap<AbsoluteDate,Double> |
ExtendedSolarActivityWrapper.getInstantFluxValues(AbsoluteDate date1,
AbsoluteDate date2)
Get raw instant flux values between the given dates |
SortedMap<AbsoluteDate,Double> |
ConstantSolarActivity.getInstantFluxValues(AbsoluteDate date1,
AbsoluteDate date2)
Get raw instant flux values between the given dates |
SortedMap<AbsoluteDate,Double> |
SolarActivityDataProvider.getInstantFluxValues(AbsoluteDate date1,
AbsoluteDate date2)
Get raw instant flux values between the given dates |
| Methods in org.orekit.forces.atmospheres.solarActivity with parameters of type AbsoluteDate | |
|---|---|
protected void |
SolarActivityDataReader.addApKp(AbsoluteDate date,
Double[][] apkp)
Add a flux value |
protected void |
SolarActivityDataReader.addF107(AbsoluteDate date,
double f107)
Add a flux value |
double |
SolarActivityDataReader.getAp(AbsoluteDate date)
Get Ap value at given user date |
double |
ExtendedSolarActivityWrapper.getAp(AbsoluteDate date)
Get Ap value at given user date |
double |
ConstantSolarActivity.getAp(AbsoluteDate date)
Get Ap value at given user date |
double |
SolarActivityDataProvider.getAp(AbsoluteDate date)
Get Ap value at given user date |
SortedMap<AbsoluteDate,Double[]> |
SolarActivityDataReader.getApKpValues(AbsoluteDate date1,
AbsoluteDate date2)
Get ap / kp values between the given dates |
SortedMap<AbsoluteDate,Double[]> |
ExtendedSolarActivityWrapper.getApKpValues(AbsoluteDate date1,
AbsoluteDate date2)
Get ap / kp values between the given dates |
SortedMap<AbsoluteDate,Double[]> |
ConstantSolarActivity.getApKpValues(AbsoluteDate date1,
AbsoluteDate date2)
Get ap / kp values between the given dates |
SortedMap<AbsoluteDate,Double[]> |
SolarActivityDataProvider.getApKpValues(AbsoluteDate date1,
AbsoluteDate date2)
Get ap / kp values between the given dates |
static double |
SolarActivityToolbox.getAverageFlux(AbsoluteDate date1,
AbsoluteDate date2,
SolarActivityDataProvider data)
Compute mean flux between given dates. |
double |
ConstantSolarActivity.getInstantFlux(AbsoluteDate date)
Get the value of the instantaneous solar flux. |
double |
SolarActivityDataReader.getInstantFluxValue(AbsoluteDate date)
Get instant flux values at the given dates (possibly interpolated) |
double |
ExtendedSolarActivityWrapper.getInstantFluxValue(AbsoluteDate date)
Get instant flux values at the given dates (possibly interpolated) |
double |
ConstantSolarActivity.getInstantFluxValue(AbsoluteDate date)
Get instant flux values at the given dates (possibly interpolated) |
double |
SolarActivityDataProvider.getInstantFluxValue(AbsoluteDate date)
Get instant flux values at the given dates (possibly interpolated) |
SortedMap<AbsoluteDate,Double> |
SolarActivityDataReader.getInstantFluxValues(AbsoluteDate date1,
AbsoluteDate date2)
Get raw instant flux values between the given dates |
SortedMap<AbsoluteDate,Double> |
ExtendedSolarActivityWrapper.getInstantFluxValues(AbsoluteDate date1,
AbsoluteDate date2)
Get raw instant flux values between the given dates |
SortedMap<AbsoluteDate,Double> |
ConstantSolarActivity.getInstantFluxValues(AbsoluteDate date1,
AbsoluteDate date2)
Get raw instant flux values between the given dates |
SortedMap<AbsoluteDate,Double> |
SolarActivityDataProvider.getInstantFluxValues(AbsoluteDate date1,
AbsoluteDate date2)
Get raw instant flux values between the given dates |
double |
SolarActivityDataReader.getKp(AbsoluteDate date)
Get Kp value at given user date |
double |
ExtendedSolarActivityWrapper.getKp(AbsoluteDate date)
Get Kp value at given user date |
double |
ConstantSolarActivity.getKp(AbsoluteDate date)
Get Kp value at given user date |
double |
SolarActivityDataProvider.getKp(AbsoluteDate date)
Get Kp value at given user date |
static double |
SolarActivityToolbox.getMeanAp(AbsoluteDate minDate,
AbsoluteDate maxDate,
SolarActivityDataProvider data)
Compute mean flux between given dates (rectangular rule) |
static double |
SolarActivityToolbox.getMeanFlux(AbsoluteDate date1,
AbsoluteDate date2,
SolarActivityDataProvider data)
Compute mean flux between given dates using trapezoidal rule |
| Uses of AbsoluteDate in org.orekit.forces.atmospheres.solarActivity.specialized |
|---|
| Methods in org.orekit.forces.atmospheres.solarActivity.specialized that return AbsoluteDate | |
|---|---|
AbsoluteDate |
AbstractMSISE2000SolarData.getMaxDate()
Gets the available data range maximum date. |
AbsoluteDate |
DTM2000SolarData.getMaxDate()
Gets the available data range maximum date. |
AbsoluteDate |
MarshallSolarActivityFutureEstimation.getMaxDate()
Gets the available data range maximum date. |
AbsoluteDate |
AbstractMSISE2000SolarData.getMinDate()
Gets the available data range minimum date. |
AbsoluteDate |
DTM2000SolarData.getMinDate()
Gets the available data range minimum date. |
AbsoluteDate |
MarshallSolarActivityFutureEstimation.getMinDate()
Gets the available data range minimum date. |
| Methods in org.orekit.forces.atmospheres.solarActivity.specialized with parameters of type AbsoluteDate | |
|---|---|
double |
DTM2000SolarData.get24HoursKp(AbsoluteDate date)
Get the last 24H mean geomagnetic index. |
double |
MarshallSolarActivityFutureEstimation.get24HoursKp(AbsoluteDate date)
The Kp index is derived from the Ap index. |
abstract double[] |
AbstractMSISE2000SolarData.getApValues(AbsoluteDate date)
Get the array containing the 7 ap values |
double[] |
ContinuousMSISE2000SolarData.getApValues(AbsoluteDate date)
Get the array containing the 7 ap values |
double[] |
ClassicalMSISE2000SolarData.getApValues(AbsoluteDate date)
Get the array containing the 7 ap values |
DateComponents |
MarshallSolarActivityFutureEstimation.getFileDate(AbsoluteDate date)
Get the date of the file from which data at the specified date comes from. |
double |
AbstractMSISE2000SolarData.getInstantFlux(AbsoluteDate date)
Get the value of the instantaneous solar flux. |
double |
DTM2000SolarData.getInstantFlux(AbsoluteDate date)
Get the value of the instantaneous solar flux. |
double |
MarshallSolarActivityFutureEstimation.getInstantFlux(AbsoluteDate date)
Get the value of the instantaneous solar flux. |
double |
ContinuousMSISE2000SolarData.getInstantFlux(AbsoluteDate date)
Get the value of the instantaneous solar flux. |
double |
AbstractMSISE2000SolarData.getMeanFlux(AbsoluteDate date)
Get the 81 day average of F10.7 flux. |
double |
DTM2000SolarData.getMeanFlux(AbsoluteDate date)
Get the value of the mean solar flux. |
double |
MarshallSolarActivityFutureEstimation.getMeanFlux(AbsoluteDate date)
Get the value of the mean solar flux. |
double |
ContinuousMSISE2000SolarData.getMeanFlux(AbsoluteDate date)
Get the 81 day average of F10.7 flux. |
double |
DTM2000SolarData.getThreeHourlyKP(AbsoluteDate date)
Get the value of the 3 hours geomagnetic index. |
double |
MarshallSolarActivityFutureEstimation.getThreeHourlyKP(AbsoluteDate date)
Get the value of the 3 hours geomagnetic index. |
| Uses of AbsoluteDate in org.orekit.forces.drag |
|---|
| Methods in org.orekit.forces.drag with parameters of type AbsoluteDate | |
|---|---|
static Vector3D |
DragForce.computeAcceleration(PVCoordinates pv,
Frame frame,
Atmosphere atm,
AbsoluteDate date,
double kD,
double mass)
Method to compute the acceleration. |
| Uses of AbsoluteDate in org.orekit.forces.gravity |
|---|
| Methods in org.orekit.forces.gravity with parameters of type AbsoluteDate | |
|---|---|
Vector3D |
DrozinerAttractionModel.computeAcceleration(PVCoordinates pv,
AbsoluteDate date)
Method to compute the acceleration. |
Vector3D |
CunninghamAttractionModel.computeAcceleration(PVCoordinates pv,
AbsoluteDate date)
Method to compute the acceleration. |
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 double[][] |
GravityToolbox.computeDAccDPos(PVCoordinates pv,
AbsoluteDate date,
double equatorialRadius,
double mu,
double[][] C,
double[][] S)
Compute the partial derivatives of the acceleration (Cunningham algorithm) with respect to the position. |
| Uses of AbsoluteDate in org.orekit.forces.gravity.tides |
|---|
| Methods in org.orekit.forces.gravity.tides with parameters of type AbsoluteDate | |
|---|---|
Vector3D |
AbstractTides.computeAcceleration(PVCoordinates pv,
Frame frame,
AbsoluteDate date)
Method to compute the acceleration, from Balmino algorithm (see BalminoAttractionModel class). |
static double[][] |
TidesToolbox.computeFundamentalArguments(AbsoluteDate date,
TidesStandards.TidesStandard standard)
Method to compute the Doodson fundamental arguments. |
double[][] |
OceanTides.getDenormalizedCCoefs(AbsoluteDate date)
Get denormalized C coefficients table |
double[][] |
OceanTides.getDenormalizedSCoefs(AbsoluteDate date)
Get denormalized S coefficients table |
double[][] |
OceanTides.getNormalizedCCoefs(AbsoluteDate date)
Get normalized C coefficients table |
double[][] |
OceanTides.getNormalizedSCoefs(AbsoluteDate date)
Get normalized S coefficients table |
abstract void |
AbstractTides.updateCoefficientsCandS(AbsoluteDate date)
Update the C and the S coefficients for acceleration computation. |
void |
PotentialTimeVariations.updateCoefficientsCandS(AbsoluteDate date)
Update the C and the S coefficients for acceleration computation. |
void |
OceanTides.updateCoefficientsCandS(AbsoluteDate date)
Update the C and the S coefficients for acceleration computation. |
void |
TerrestrialTides.updateCoefficientsCandS(AbsoluteDate date)
Update the C and the S coefficients for acceleration computation. |
abstract void |
AbstractTides.updateCoefficientsCandSPD(AbsoluteDate date)
Update the C and the S coefficients for partial derivatives computation. |
void |
PotentialTimeVariations.updateCoefficientsCandSPD(AbsoluteDate date)
Update the C and the S coefficients for partial derivatives computation. |
void |
OceanTides.updateCoefficientsCandSPD(AbsoluteDate date)
Update the C and the S coefficients for partial derivatives computation. |
void |
TerrestrialTides.updateCoefficientsCandSPD(AbsoluteDate date)
Update the C and the S coefficients for partial derivatives computation. |
| Uses of AbsoluteDate in org.orekit.forces.gravity.variations |
|---|
| Methods in org.orekit.forces.gravity.variations with parameters of type AbsoluteDate | |
|---|---|
Vector3D |
VariablePotentialAttractionModel.computeAcceleration(AbsoluteDate date,
PVCoordinates pv)
Compute acceleration in rotating frame |
void |
VariablePotentialAttractionModel.updateCoefficientsCandS(AbsoluteDate date)
Update the C and the S coefficients for acceleration computation. |
void |
VariablePotentialAttractionModel.updateCoefficientsCandSPD(AbsoluteDate date)
Update the C and the S coefficients for partial derivatives computation. |
| Uses of AbsoluteDate in org.orekit.forces.gravity.variations.coefficients |
|---|
| Methods in org.orekit.forces.gravity.variations.coefficients that return AbsoluteDate | |
|---|---|
AbsoluteDate |
VariablePotentialCoefficientsReader.getDate()
|
AbsoluteDate |
VariablePotentialCoefficientsProvider.getDate()
Get the reference date of the file |
| Uses of AbsoluteDate in org.orekit.forces.maneuvers |
|---|
| Methods in org.orekit.forces.maneuvers that return AbsoluteDate | |
|---|---|
AbsoluteDate |
SmallManeuverAnalyticalModel.getDate()
Get the date of the maneuver. |
AbsoluteDate |
ConstantThrustManeuver.getEndDate()
Return the maneuver stop date (if a date or a DateDetector as been provided). |
AbsoluteDate |
ConstantThrustError.getEndDate()
Return the maneuver stop date (if a date or a DateDetector as been provided). |
AbsoluteDate |
VariableThrustManeuver.getEndDate()
Return the maneuver stop date (if a date or a DateDetector as been provided). |
AbsoluteDate |
ConstantThrustManeuver.getStartDate()
Return the maneuver start date (if a date or a DateDetector as been provided). |
AbsoluteDate |
ConstantThrustError.getStartDate()
Return the maneuver start date (if a date or a DateDetector as been provided). |
AbsoluteDate |
VariableThrustManeuver.getStartDate()
Return the maneuver start date (if a date or a DateDetector as been provided). |
| Methods in org.orekit.forces.maneuvers with parameters of type AbsoluteDate | |
|---|---|
void |
ImpulseManeuver.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation. |
| Constructors in org.orekit.forces.maneuvers with parameters of type AbsoluteDate | |
|---|---|
ConstantThrustError(AbsoluteDate date,
double duration,
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,
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,
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(AbsoluteDate date,
double duration,
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,
LOFType lofType,
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,
LOFType lofType,
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,
LOFType lofType,
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,
LOFType lofType,
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,
LOFType lofType,
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(AbsoluteDate date,
double duration,
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,
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 |
|
ConstantThrustManeuver(AbsoluteDate date,
double duration,
double thrust,
double isp,
Vector3D direction,
MassProvider massProvider,
String partName)
Constructor for a constant direction in satellite frame and constant thrust. |
|
ConstantThrustManeuver(AbsoluteDate date,
double duration,
double thrust,
double isp,
Vector3D direction,
MassProvider massProvider,
String partName,
Frame frame)
Constructor for a constant direction in provided frame and constant thrust. |
|
ConstantThrustManeuver(AbsoluteDate date,
double duration,
double thrust,
double isp,
Vector3D direction,
MassProvider massProvider,
String partName,
LOFType lofType)
Constructor for a constant direction in provided local orbital frame and constant thrust. |
|
ConstantThrustManeuver(AbsoluteDate date,
double duration,
Parameter thrust,
Parameter flowRate,
Vector3D direction,
MassProvider massProvider,
String partName)
Constructor for a constant direction in satellite frame and constant thrust using Parameter. |
|
ConstantThrustManeuver(AbsoluteDate date,
double duration,
Parameter thrust,
Parameter flowRate,
Vector3D direction,
MassProvider massProvider,
String partName,
Frame frame)
Constructor for a constant direction in provided frame and constant thrust using Parameter. |
|
ConstantThrustManeuver(AbsoluteDate date,
double duration,
Parameter thrust,
Parameter flowRate,
Vector3D direction,
MassProvider massProvider,
String partName,
LOFType lofType)
Constructor for a constant direction in provided local orbital frame and constant thrust using Parameter with a local orbital frame defined by its type. |
|
VariableThrustManeuver(AbsoluteDate date,
double duration,
IDependentVariable<SpacecraftState> variableThrust,
IDependentVariable<SpacecraftState> variableIsp,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
String partName)
Constructor for a variable direction in spacecraft frame, thrust and ISP. |
|
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,
IDependentVariable<SpacecraftState> variableThrust,
IDependentVariable<SpacecraftState> variableIsp,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
String partName,
LOFType lofTyp)
Constructor for a variable direction in provided local orbital frame, thrust and ISP expressed in a LocalOrbitalFrame. |
|
| Uses of AbsoluteDate in org.orekit.forces.radiation |
|---|
| Fields in org.orekit.forces.radiation declared as AbsoluteDate | |
|---|---|
static AbsoluteDate |
KnockeRiesModel.REFDAY
reference day of Knocke-Ries model. |
| Methods in org.orekit.forces.radiation with parameters of type AbsoluteDate | |
|---|---|
double[] |
KnockeRiesModel.getEmissivity(AbsoluteDate cdate,
double latitude,
double longitude)
Computing of the emissivities of earth (albedo and infrared) based of the Knocke-Reis model (the longitude is not used in this model) |
double[] |
IEmissivityModel.getEmissivity(AbsoluteDate cdate,
double latitude,
double longitude)
Get the albedo and infrared emissivities. |
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 AbsoluteDate | |
|---|---|
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. |
|
| Uses of AbsoluteDate in org.orekit.frames |
|---|
| Methods in org.orekit.frames with parameters of type AbsoluteDate | |
|---|---|
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. |
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. |
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. |
Transform |
LOFType.transformFromInertial(AbsoluteDate date,
PVCoordinates pv)
Get the transform from an inertial frame defining position-velocity and the local orbital frame. |
Transform |
LOFType.transformFromInertial(AbsoluteDate date,
PVCoordinates pv,
boolean computeSpinDerivatives)
Get the transform from an inertial frame defining position-velocity and the local orbital frame. |
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. |
| Uses of AbsoluteDate in org.orekit.frames.configuration |
|---|
| Methods in org.orekit.frames.configuration with parameters of type AbsoluteDate | |
|---|---|
double[] |
PrecessionNutation.getCIPMotion(AbsoluteDate date)
Compute the CIP pole coordinates at given date. |
double[] |
FramesConfigurationImplementation.getCIPMotion(AbsoluteDate date)
Compute the corrected Celestial Intermediate Pole motion (X, Y, S) in the GCRS. |
double[] |
FramesConfiguration.getCIPMotion(AbsoluteDate date)
Compute the corrected Celestial Intermediate Pole motion (X, Y, S) in the GCRS. |
double[] |
PrecessionNutation.getCIPMotionTimeDerivative(AbsoluteDate date)
Compute the CIP pole coordinate derivatives at given date. |
double[] |
FramesConfigurationImplementation.getCIPMotionTimeDerivative(AbsoluteDate date)
Compute the time derivative Celestial Intermediate Pole motion in the GCRS. |
double[] |
FramesConfiguration.getCIPMotionTimeDerivative(AbsoluteDate date)
Compute the time derivative Celestial Intermediate Pole motion in the GCRS. |
double[] |
FramesConfigurationImplementation.getPolarMotion(AbsoluteDate date)
Compute corrected polar motion. |
double[] |
FramesConfiguration.getPolarMotion(AbsoluteDate date)
Compute corrected polar motion. |
PoleCorrection |
PolarMotion.getPoleCorrection(AbsoluteDate date)
Compute pole correction. |
double |
PolarMotion.getSP(AbsoluteDate date)
Compute S'. |
double |
FramesConfigurationImplementation.getSprime(AbsoluteDate date)
Compute S' value. |
double |
FramesConfiguration.getSprime(AbsoluteDate date)
Compute S' value. |
double |
FramesConfigurationImplementation.getUT1Correction(AbsoluteDate date)
Compute correction dut1. |
double |
FramesConfiguration.getUT1Correction(AbsoluteDate date)
Compute correction dut1. |
double |
DiurnalRotation.getUT1Correction(AbsoluteDate date)
Compute ut1-tai correction. |
double |
FramesConfigurationImplementation.getUT1MinusTAI(AbsoluteDate date)
Compute corrected ut1-tai. |
double |
FramesConfiguration.getUT1MinusTAI(AbsoluteDate date)
Compute corrected ut1-tai. |
| Uses of AbsoluteDate in org.orekit.frames.configuration.eop |
|---|
| Methods in org.orekit.frames.configuration.eop that return AbsoluteDate | |
|---|---|
AbsoluteDate |
EOPEntry.getDate()
Get the date. |
AbsoluteDate |
AbstractEOPHistory.getEndDate()
Get the date of the last available Earth Orientation Parameters. |
AbsoluteDate |
EOP2000HistoryConstantOutsideInterval.getEndDate()
|
AbsoluteDate |
EOPHistory.getEndDate()
Get the date of the last available Earth Orientation Parameters. |
AbsoluteDate |
NoEOP2000History.getEndDate()
getEndDate. |
AbsoluteDate |
AbstractEOPHistory.getStartDate()
Get the date of the first available Earth Orientation Parameters. |
AbsoluteDate |
EOP2000HistoryConstantOutsideInterval.getStartDate()
|
AbsoluteDate |
EOPHistory.getStartDate()
Get the date of the first available Earth Orientation Parameters. |
AbsoluteDate |
NoEOP2000History.getStartDate()
getStartDate. |
| Methods in org.orekit.frames.configuration.eop with parameters of type AbsoluteDate | |
|---|---|
double |
AbstractEOPHistory.getLOD(AbsoluteDate date)
Get the LoD (Length of Day) value. |
double |
EOP2000HistoryConstantOutsideInterval.getLOD(AbsoluteDate date)
Get the LoD (Length of Day) value. |
double |
EOPHistory.getLOD(AbsoluteDate date)
Get the LoD (Length of Day) value. |
double |
NoEOP2000History.getLOD(AbsoluteDate date)
getLOD. |
protected EOPEntry[] |
AbstractEOPHistory.getNeighbors(AbsoluteDate central)
Get the entries surrounding a central date. |
NutationCorrection |
AbstractEOPHistory.getNutationCorrection(AbsoluteDate date)
Get the correction to the nutation parameters. |
NutationCorrection |
EOP2000HistoryConstantOutsideInterval.getNutationCorrection(AbsoluteDate date)
Get the correction to the nutation parameters. |
NutationCorrection |
NoEOP2000History.getNutationCorrection(AbsoluteDate date)
|
PoleCorrection |
AbstractEOPHistory.getPoleCorrection(AbsoluteDate date)
Get the pole IERS Reference Pole correction. |
PoleCorrection |
EOP2000HistoryConstantOutsideInterval.getPoleCorrection(AbsoluteDate date)
Get the pole IERS Reference Pole correction. |
PoleCorrection |
NoEOP2000History.getPoleCorrection(AbsoluteDate date)
|
double |
AbstractEOPHistory.getUT1MinusTAI(AbsoluteDate date)
Get the UT1-TAI value. |
double |
EOP2000HistoryConstantOutsideInterval.getUT1MinusTAI(AbsoluteDate date)
Get the UT1-TAI value. |
double |
EOPHistory.getUT1MinusTAI(AbsoluteDate date)
Get the UT1-TAI value. |
double |
NoEOP2000History.getUT1MinusTAI(AbsoluteDate date)
getUT1MinusTAI. |
double |
AbstractEOPHistory.getUT1MinusUTC(AbsoluteDate date)
Get the UT1-UTC value. |
double |
EOP2000HistoryConstantOutsideInterval.getUT1MinusUTC(AbsoluteDate date)
Get the UT1-UTC value. |
double |
EOPHistory.getUT1MinusUTC(AbsoluteDate date)
Get the UT1-UTC value. |
| Constructors in org.orekit.frames.configuration.eop with parameters of type AbsoluteDate | |
|---|---|
EOP1980Entry(AbsoluteDate adate,
double dt,
double lod,
double x,
double y,
double ddPsi,
double ddEps)
Constructor with an AbsoluteDate parameter. |
|
EOP1980Entry(AbsoluteDate adate,
double dt,
double lod,
double x,
double y,
double ddPsi,
double ddEps,
EOPEntry.DtType type)
Constructor with an AbsoluteDate parameter. |
|
EOP2000Entry(AbsoluteDate adate,
double dt,
double lod,
double x,
double y,
double dx,
double dy)
Constructor with an AbsoluteDate parameter. |
|
EOP2000Entry(AbsoluteDate adate,
double dt,
double lod,
double x,
double y,
double dx,
double dy,
EOPEntry.DtType type)
Constructor with an AbsoluteDate parameter. |
|
EOPEntry(AbsoluteDate adate,
double dt,
double lod,
double x,
double y,
double dx,
double dy)
Constructor with an AbsoluteDate parameter. |
|
EOPEntry(AbsoluteDate adate,
double dt,
double lod,
double x,
double y,
double dx,
double dy,
EOPEntry.DtType type)
Constructor with an AbsoluteDate parameter. |
|
| Uses of AbsoluteDate in org.orekit.frames.configuration.libration |
|---|
| Methods in org.orekit.frames.configuration.libration with parameters of type AbsoluteDate | |
|---|---|
PoleCorrection |
LibrationCorrectionModel.getPoleCorrection(AbsoluteDate t)
Compute the pole corrections at a given date. |
PoleCorrection |
NoLibrationCorrection.getPoleCorrection(AbsoluteDate t)
Compute the pole corrections at a given date. |
PoleCorrection |
IERS2010LibrationCorrection.getPoleCorrection(AbsoluteDate date)
This method provides the diurnal lunisolar effect on polar motion in time domain. |
double |
LibrationCorrectionModel.getUT1Correction(AbsoluteDate t)
Compute the UT1-TAI corrections at a given date. |
double |
NoLibrationCorrection.getUT1Correction(AbsoluteDate t)
Compute the UT1-TAI corrections at a given date. |
double |
IERS2010LibrationCorrection.getUT1Correction(AbsoluteDate date)
Get the dUT1 value. |
| Uses of AbsoluteDate in org.orekit.frames.configuration.precessionnutation |
|---|
| Methods in org.orekit.frames.configuration.precessionnutation that return AbsoluteDate | |
|---|---|
AbsoluteDate |
CIPCoordinates.getDate()
Get the date. |
| Methods in org.orekit.frames.configuration.precessionnutation with parameters of type AbsoluteDate | |
|---|---|
List<CIPCoordinates> |
CIPCoordinatesGenerator.generate(CIPCoordinates existingData,
AbsoluteDate date)
Generate a chronologically sorted list of entries to be cached. |
double[] |
PrecessionNutationModel.getCIPMotion(AbsoluteDate t)
Compute the Celestial Intermediate pole motion in the GCRS. |
double[] |
NoPrecessionNutation.getCIPMotion(AbsoluteDate t)
Compute the Celestial Intermediate pole motion in the GCRS. |
double[] |
StelaPrecessionNutationModel.getCIPMotion(AbsoluteDate date)
Compute the Celestial Intermediate pole motion in the GCRS. |
double[] |
IERS20032010PrecessionNutation.getCIPMotion(AbsoluteDate date)
Compute the Celestial Intermediate pole motion in the GCRS. |
double[] |
PrecessionNutationCache.getCIPMotion(AbsoluteDate date)
Compute the Celestial Intermediate pole motion in the GCRS. |
double[] |
PrecessionNutationModel.getCIPMotionTimeDerivative(AbsoluteDate t)
Compute the Celestial Intermediate pole motion in the GCRS. |
double[] |
NoPrecessionNutation.getCIPMotionTimeDerivative(AbsoluteDate t)
Compute the Celestial Intermediate pole motion in the GCRS. |
double[] |
StelaPrecessionNutationModel.getCIPMotionTimeDerivative(AbsoluteDate date)
Compute the Celestial Intermediate pole motion in the GCRS. |
double[] |
IERS20032010PrecessionNutation.getCIPMotionTimeDerivative(AbsoluteDate date)
Compute the Celestial Intermediate pole motion in the GCRS. |
double[] |
PrecessionNutationCache.getCIPMotionTimeDerivative(AbsoluteDate date)
Compute the Celestial Intermediate pole motion in the GCRS. |
| Constructors in org.orekit.frames.configuration.precessionnutation with parameters of type AbsoluteDate | |
|---|---|
CIPCoordinates(AbsoluteDate date,
double[] cip,
double[] cipDV)
|
|
CIPCoordinates(AbsoluteDate date,
double x,
double xP,
double y,
double yP,
double s,
double sP)
|
|
| Uses of AbsoluteDate in org.orekit.frames.configuration.sp |
|---|
| Methods in org.orekit.frames.configuration.sp with parameters of type AbsoluteDate | |
|---|---|
double |
NoSpCorrection.getSP(AbsoluteDate t)
Compute the correction S' at a given date. |
double |
IERS2010SPCorrection.getSP(AbsoluteDate date)
Compute the correction S' at a given date. |
double |
SPrimeModel.getSP(AbsoluteDate t)
Compute the correction S' at a given date. |
| Uses of AbsoluteDate in org.orekit.frames.configuration.tides |
|---|
| Methods in org.orekit.frames.configuration.tides that return AbsoluteDate | |
|---|---|
AbsoluteDate |
TidalCorrection.getDate()
|
| Methods in org.orekit.frames.configuration.tides with parameters of type AbsoluteDate | |
|---|---|
protected TidalCorrection |
IERS2003TidalCorrection.computeCorrections(AbsoluteDate date)
Compute the partials of the tidal variations to the orthoweights. |
List<TidalCorrection> |
TidalCorrectionGenerator.generate(TidalCorrection existingData,
AbsoluteDate date)
Generate a chronologically sorted list of entries to be cached. |
double |
IERS2010TidalCorrection.getLODCorrection(AbsoluteDate date)
Get length of day correction. |
double |
IERS2003TidalCorrection.getLODCorrection(AbsoluteDate t)
Get length of day correction. |
double |
TidalCorrectionModel.getLODCorrection(AbsoluteDate date)
Get length of day correction. |
double |
NoTidalCorrection.getLODCorrection(AbsoluteDate t)
Get length of day correction. |
PoleCorrection |
IERS2010TidalCorrection.getPoleCorrection(AbsoluteDate date)
Compute the pole corrections at a given date. |
PoleCorrection |
IERS2003TidalCorrection.getPoleCorrection(AbsoluteDate date)
Compute the pole corrections at a given date. |
PoleCorrection |
TidalCorrectionModel.getPoleCorrection(AbsoluteDate date)
Compute the pole corrections at a given date. |
PoleCorrection |
NoTidalCorrection.getPoleCorrection(AbsoluteDate t)
Compute the pole corrections at a given date. |
double |
IERS2010TidalCorrection.getUT1Correction(AbsoluteDate date)
Compute the UT1-TAI corrections at a given date. |
double |
IERS2003TidalCorrection.getUT1Correction(AbsoluteDate date)
Compute the UT1-TAI corrections at a given date. |
double |
TidalCorrectionModel.getUT1Correction(AbsoluteDate date)
Compute the UT1-TAI corrections at a given date. |
double |
NoTidalCorrection.getUT1Correction(AbsoluteDate t)
Compute the UT1-TAI corrections at a given date. |
| Constructors in org.orekit.frames.configuration.tides with parameters of type AbsoluteDate | |
|---|---|
TidalCorrection(AbsoluteDate date,
PoleCorrection pole,
double ut1Corr,
double lodCor)
|
|
| Uses of AbsoluteDate in org.orekit.frames.transformations |
|---|
| Methods in org.orekit.frames.transformations that return AbsoluteDate | |
|---|---|
AbsoluteDate |
Transform.getDate()
Get the date. |
AbsoluteDate |
HelmertTransformation.getEpoch()
Get the reference epoch of the transform. |
| Methods in org.orekit.frames.transformations with parameters of type AbsoluteDate | |
|---|---|
static double |
TIRFProvider.getEarthRotationAngle(AbsoluteDate date)
Get the Earth Rotation Angle at the current date. |
static double |
TODProvider.getEquationOfEquinoxes(AbsoluteDate date)
Get the Equation of the Equinoxes at the current date. |
double[] |
MODProvider.getEulerAngles(AbsoluteDate date)
Compute Euler angles (3, 2, 3) of MOD => EME2000 transformation and their derivatives with respect to time. |
double |
GTODProvider.getGAST(AbsoluteDate date)
Get the Greenwich apparent sidereal time, in radians. |
static double |
GTODProvider.getGMST(AbsoluteDate date)
Get the Greenwich mean sidereal time, in radians. |
PoleCorrection |
TODProvider.getPoleCorrection(AbsoluteDate date)
Get the pole IERS Reference Pole correction. |
static double |
GTODProvider.getRotationRate(AbsoluteDate date)
Get the rotation rate of the Earth. |
Transform |
VEISProvider.getTransform(AbsoluteDate date)
Get the transform from GTOD at specified date. |
Transform |
MODProvider.getTransform(AbsoluteDate date)
Get the transfrom from parent frame. |
Transform |
CIRFProvider.getTransform(AbsoluteDate date)
Get the transform from GCRF to CIRF2000 at the specified date. |
Transform |
TEMEProvider.getTransform(AbsoluteDate date)
Get the transform from True Of Date date. |
Transform |
ITRFProvider.getTransform(AbsoluteDate date)
Get the transform from TIRF 2000 at specified date. |
Transform |
TIRFProvider.getTransform(AbsoluteDate date)
Get the transform from CIRF 2000 at specified date. |
Transform |
EODProvider.getTransform(AbsoluteDate date)
Get the Transform corresponding to specified date. |
Transform |
FixedTransformProvider.getTransform(AbsoluteDate date)
Get the Transform corresponding to specified date. |
Transform |
ITRFEquinoxProvider.getTransform(AbsoluteDate date)
Get the transform from GTOD at specified date. |
Transform |
GTODProvider.getTransform(AbsoluteDate date)
Get the transform from TOD at specified date. |
Transform |
TransformProvider.getTransform(AbsoluteDate date)
Get the Transform corresponding to specified date. |
Transform |
HelmertTransformation.getTransform(AbsoluteDate date)
Compute the transform at some date. |
Transform |
TODProvider.getTransform(AbsoluteDate date)
Get the transform from Mean Of Date at specified date. |
Transform |
InterpolatingTransformProvider.getTransform(AbsoluteDate date)
Get the Transform corresponding to specified date. |
Transform |
VEISProvider.getTransform(AbsoluteDate date,
boolean computeSpinDerivatives)
Get the transform from GTOD at specified date. |
Transform |
MODProvider.getTransform(AbsoluteDate date,
boolean computeSpinDerivatives)
Get the transfrom from parent frame. |
Transform |
CIRFProvider.getTransform(AbsoluteDate date,
boolean computeSpinDerivatives)
Get the transform from GCRF to CIRF2000 at the specified date. |
Transform |
TEMEProvider.getTransform(AbsoluteDate date,
boolean computeSpinDerivatives)
Get the transform from True Of Date date. |
Transform |
ITRFProvider.getTransform(AbsoluteDate date,
boolean computeSpinDerivatives)
Get the transform from TIRF 2000 at specified date. |
Transform |
TIRFProvider.getTransform(AbsoluteDate date,
boolean computeSpinDerivatives)
Get the transform from CIRF 2000 at specified date. |
Transform |
EODProvider.getTransform(AbsoluteDate date,
boolean computeSpinDerivatives)
Get the Transform corresponding to specified date. |
Transform |
FixedTransformProvider.getTransform(AbsoluteDate date,
boolean computeSpinDerivatives)
Get the Transform corresponding to specified date. |
Transform |
ITRFEquinoxProvider.getTransform(AbsoluteDate date,
boolean computeSpinDerivatives)
Get the transform from GTOD at specified date. |
Transform |
GTODProvider.getTransform(AbsoluteDate date,
boolean computeSpinDerivatives)
Get the transform from TOD at specified date. |
Transform |
TransformProvider.getTransform(AbsoluteDate date,
boolean computeSpinDerivatives)
Get the Transform corresponding to specified date. |
Transform |
HelmertTransformation.getTransform(AbsoluteDate date,
boolean computeSpinDerivatives)
Compute the transform at some date. |
Transform |
TODProvider.getTransform(AbsoluteDate date,
boolean computeSpinDerivatives)
Get the transform from Mean Of Date at specified date. |
Transform |
InterpolatingTransformProvider.getTransform(AbsoluteDate date,
boolean computeSpinDerivatives)
Get the Transform corresponding to specified date. |
Transform |
VEISProvider.getTransform(AbsoluteDate date,
FramesConfiguration config)
Get the Transform corresponding to specified date. |
Transform |
MODProvider.getTransform(AbsoluteDate date,
FramesConfiguration config)
Get the transfrom from parent frame. |
Transform |
CIRFProvider.getTransform(AbsoluteDate date,
FramesConfiguration config)
Get the transform from GCRF to CIRF2000 at the specified date. |
Transform |
TEMEProvider.getTransform(AbsoluteDate date,
FramesConfiguration config)
Get the transform from True Of Date date. |
Transform |
ITRFProvider.getTransform(AbsoluteDate date,
FramesConfiguration config)
Get the transform from TIRF 2000 at specified date. |
Transform |
TIRFProvider.getTransform(AbsoluteDate date,
FramesConfiguration config)
Get the transform from CIRF 2000 at specified date. |
Transform |
EODProvider.getTransform(AbsoluteDate date,
FramesConfiguration config)
Get the Transform corresponding to specified date. |
Transform |
FixedTransformProvider.getTransform(AbsoluteDate date,
FramesConfiguration config)
Get the Transform corresponding to specified date. |
Transform |
ITRFEquinoxProvider.getTransform(AbsoluteDate date,
FramesConfiguration config)
Get the transform from GTOD at specified date. |
Transform |
GTODProvider.getTransform(AbsoluteDate date,
FramesConfiguration config)
Get the transform from TOD at specified date. |
Transform |
TransformProvider.getTransform(AbsoluteDate date,
FramesConfiguration config)
Get the Transform corresponding to specified date. |
Transform |
HelmertTransformation.getTransform(AbsoluteDate date,
FramesConfiguration config)
Compute the transform at some date. |
Transform |
TODProvider.getTransform(AbsoluteDate date,
FramesConfiguration config)
Get the transform from Mean Of Date at specified date. |
Transform |
InterpolatingTransformProvider.getTransform(AbsoluteDate date,
FramesConfiguration config)
Get the Transform corresponding to specified date. |
Transform |
VEISProvider.getTransform(AbsoluteDate date,
FramesConfiguration config,
boolean computeSpinDerivatives)
Get the Transform corresponding to specified date. |
Transform |
MODProvider.getTransform(AbsoluteDate date,
FramesConfiguration config,
boolean computeSpinDerivatives)
Get the transfrom from parent frame. |
Transform |
CIRFProvider.getTransform(AbsoluteDate date,
FramesConfiguration config,
boolean computeSpinDerivatives)
Get the transform from GCRF to CIRF2000 at the specified date. |
Transform |
TEMEProvider.getTransform(AbsoluteDate date,
FramesConfiguration config,
boolean computeSpinDerivatives)
Get the transform from True Of Date date. |
Transform |
ITRFProvider.getTransform(AbsoluteDate date,
FramesConfiguration config,
boolean computeSpinDerivatives)
Get the transform from TIRF 2000 at specified date. |
Transform |
TIRFProvider.getTransform(AbsoluteDate date,
FramesConfiguration config,
boolean computeSpinDerivatives)
Get the transform from CIRF 2000 at specified date. |
Transform |
EODProvider.getTransform(AbsoluteDate date,
FramesConfiguration config,
boolean computeSpinDerivatives)
Get the Transform corresponding to specified date. |
Transform |
FixedTransformProvider.getTransform(AbsoluteDate date,
FramesConfiguration config,
boolean computeSpinDerivatives)
Get the Transform corresponding to specified date. |
Transform |
ITRFEquinoxProvider.getTransform(AbsoluteDate date,
FramesConfiguration config,
boolean computeSpinDerivatives)
Get the transform from GTOD at specified date. |
Transform |
GTODProvider.getTransform(AbsoluteDate date,
FramesConfiguration config,
boolean computeSpinDerivatives)
Get the transform from TOD at specified date. |
Transform |
TransformProvider.getTransform(AbsoluteDate date,
FramesConfiguration config,
boolean computeSpinDerivatives)
Get the Transform corresponding to specified date. |
Transform |
HelmertTransformation.getTransform(AbsoluteDate date,
FramesConfiguration config,
boolean computeSpinDerivatives)
Compute the transform at some date. |
Transform |
TODProvider.getTransform(AbsoluteDate date,
FramesConfiguration config,
boolean computeSpinDerivatives)
Get the transform from Mean Of Date at specified date. |
Transform |
InterpolatingTransformProvider.getTransform(AbsoluteDate date,
FramesConfiguration config,
boolean computeSpinDerivatives)
Get the Transform corresponding to specified date. |
static Transform |
Transform.interpolate(AbsoluteDate date,
boolean useVelocities,
boolean useRotationRates,
Collection<Transform> sample)
Interpolate a transform from a sample set of existing transforms. |
static Transform |
Transform.interpolate(AbsoluteDate date,
boolean useVelocities,
boolean useRotationRates,
Collection<Transform> sample,
boolean computeSpinDerivative)
Interpolate a transform from a sample set of existing transforms. |
Transform |
Transform.interpolate(AbsoluteDate interpolationDate,
Collection<Transform> sample)
Get an interpolated instance. |
Transform |
Transform.interpolate(AbsoluteDate interpolationDate,
Collection<Transform> sample,
boolean computeSpinDerivative)
Get an interpolated instance. |
| Constructors in org.orekit.frames.transformations with parameters of type AbsoluteDate | |
|---|---|
H0MinusNProvider(AbsoluteDate h0MinusN,
double longitude)
Simple constructor. |
|
HelmertTransformation(AbsoluteDate epoch,
double t1,
double t2,
double t3,
double r1,
double r2,
double r3,
double t1Dot,
double t2Dot,
double t3Dot,
double r1Dot,
double r2Dot,
double r3Dot)
Build a transform from its primitive operations. |
|
InterpolatingTransformProvider(TransformProvider rawProvider,
boolean useVelocities,
boolean useRotationRates,
AbsoluteDate earliest,
AbsoluteDate latest,
int gridPoints,
double step,
int maxSlots,
double maxSpan,
double newSlotInterval)
Simple constructor. |
|
InterpolatingTransformProvider(TransformProvider rawProvider,
boolean useVelocities,
boolean useRotationRates,
AbsoluteDate earliest,
AbsoluteDate latest,
int gridPoints,
double step,
int maxSlots,
double maxSpan,
double newSlotInterval,
boolean computeSpinDerivatives)
Simple constructor. |
|
Transform(AbsoluteDate date,
AngularCoordinates angular)
Build a rotation transform. |
|
Transform(AbsoluteDate date,
PVCoordinates cartesian)
Build a translation transform, with its first time derivative. |
|
Transform(AbsoluteDate date,
PVCoordinates cartesian,
AngularCoordinates angular)
Build a transform from its primitive operations. |
|
Transform(AbsoluteDate date,
Rotation rotation)
Build a rotation transform. |
|
Transform(AbsoluteDate date,
Rotation rotation,
Vector3D rotationRate)
Build a rotation transform. |
|
Transform(AbsoluteDate date,
Rotation rotation,
Vector3D rotationRate,
Vector3D rotationAcceleration)
Build a rotation transform. |
|
Transform(AbsoluteDate date,
Transform first,
Transform second)
Build a transform by combining two existing ones without computing spin derivatives. |
|
Transform(AbsoluteDate date,
Transform first,
Transform second,
boolean computeSpinDerivatives)
Build a transform by combining two existing ones. |
|
Transform(AbsoluteDate date,
Vector3D translation)
Build a translation transform. |
|
Transform(AbsoluteDate date,
Vector3D translation,
Vector3D velocity)
Build a translation transform, with its first time derivative. |
|
Transform(AbsoluteDate date,
Vector3D translation,
Vector3D velocity,
Vector3D acceleration)
Build a translation transform, with its first and second time derivatives. |
|
| Uses of AbsoluteDate in org.orekit.models.earth |
|---|
| Methods in org.orekit.models.earth with parameters of type AbsoluteDate | |
|---|---|
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. |
static double |
GeoMagneticField.getDecimalYear(AbsoluteDate date)
Utility function to get a decimal year for a given AbsoluteDate. |
static GeoMagneticField |
GeoMagneticFieldFactory.getField(GeoMagneticFieldFactory.FieldModel type,
AbsoluteDate year)
Get the GeoMagneticField for the given model type and year. |
static GeoMagneticField |
GeoMagneticFieldFactory.getIGRF(AbsoluteDate year)
Get the IGRF model for the given year. |
static GeoMagneticField |
GeoMagneticFieldFactory.getWMM(AbsoluteDate year)
Get the WMM model for the given year. |
| Uses of AbsoluteDate in org.orekit.orbits |
|---|
| Methods in org.orekit.orbits that return AbsoluteDate | |
|---|---|
AbsoluteDate |
Orbit.getDate()
Get the date of orbital parameters. |
| Methods in org.orekit.orbits with parameters of type AbsoluteDate | |
|---|---|
PVCoordinates |
Orbit.getPVCoordinates(AbsoluteDate otherDate,
Frame otherFrame)
Get the PVCoordinates of the body in the selected frame. |
CircularOrbit |
CircularOrbit.interpolate(AbsoluteDate date,
Collection<Orbit> sample)
Get an interpolated instance. |
KeplerianOrbit |
KeplerianOrbit.interpolate(AbsoluteDate date,
Collection<Orbit> sample)
Get an interpolated instance. |
EquatorialOrbit |
EquatorialOrbit.interpolate(AbsoluteDate date,
Collection<Orbit> sample)
Get an interpolated instance. |
EquinoctialOrbit |
EquinoctialOrbit.interpolate(AbsoluteDate date,
Collection<Orbit> sample)
Get an interpolated instance. |
ApsisOrbit |
ApsisOrbit.interpolate(AbsoluteDate date,
Collection<Orbit> sample)
Get an interpolated instance. |
CartesianOrbit |
CartesianOrbit.interpolate(AbsoluteDate date,
Collection<Orbit> sample)
Get an interpolated instance. |
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 AbsoluteDate | |
|---|---|
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 AbsoluteDate in org.orekit.parameter |
|---|
| Constructors in org.orekit.parameter with parameters of type AbsoluteDate | |
|---|---|
LinearFunction(AbsoluteDate t0,
double slope,
double zeroValue)
Simple constructor of a linear function a * (t - t0) + b using input constant a, b and initial date. |
|
LinearFunction(AbsoluteDate t0,
Parameter slope,
Parameter zeroValue)
Simple constructor of a linear function a * (t - t0) + b
using input Parameter and initial date. |
|
| Constructor parameters in org.orekit.parameter with type arguments of type AbsoluteDate | |
|---|---|
PiecewiseFunction(ArrayList<IParamDiffFunction> flist,
ArrayList<AbsoluteDate> xlist)
Simple constructor with 2 lists (IParamDiffFunction and AbsoluteDate) where dates list represent the connection points between functions. |
|
| Uses of AbsoluteDate in org.orekit.propagation |
|---|
| Methods in org.orekit.propagation that return AbsoluteDate | |
|---|---|
AbsoluteDate |
SpacecraftState.getDate()
Get the date. |
AbsoluteDate |
AnalyticalIntegratedEphemeris.getMaxDate()
Get the last date of the range. |
AbsoluteDate |
BoundedPropagator.getMaxDate()
Get the last date of the range. |
AbsoluteDate |
AnalyticalIntegratedEphemeris.getMinDate()
Get the first date of the range. |
AbsoluteDate |
BoundedPropagator.getMinDate()
Get the first date of the range. |
| Methods in org.orekit.propagation with parameters of type AbsoluteDate | |
|---|---|
protected SpacecraftState |
AbstractPropagator.acceptStep(AbsoluteDate target,
double epsilon)
Accept a step, triggering events and step handlers. |
protected SpacecraftState |
AbstractPropagator.basicPropagate(AbsoluteDate date)
Propagate an orbit without any fancy features. |
double[] |
AdditionalStateProvider.getAdditionalState(AbsoluteDate date)
Get the additional state. |
PVCoordinates |
AbstractPropagator.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the PVCoordinates of the body in the selected frame. |
SpacecraftState |
SpacecraftState.interpolate(AbsoluteDate date,
Collection<SpacecraftState> sample)
Get an interpolated instance. |
SpacecraftState |
AnalyticalIntegratedEphemeris.propagate(AbsoluteDate target)
Propagate towards a target date. |
SpacecraftState |
Propagator.propagate(AbsoluteDate target)
Propagate towards a target date. |
SpacecraftState |
AbstractPropagator.propagate(AbsoluteDate target)
Propagate towards a target date. |
SpacecraftState |
AnalyticalIntegratedEphemeris.propagate(AbsoluteDate start,
AbsoluteDate target)
Propagate from a start date towards a target date. |
SpacecraftState |
Propagator.propagate(AbsoluteDate start,
AbsoluteDate target)
Propagate from a start date towards a target date. |
SpacecraftState |
AbstractPropagator.propagate(AbsoluteDate start,
AbsoluteDate target)
Propagate from a start date towards a target date. |
Orbit |
MeanOsculatingElementsProvider.propagateMeanOrbit(AbsoluteDate date)
Propagate mean orbit until provided date. |
protected Orbit |
AnalyticalIntegratedEphemeris.propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date. |
protected abstract Orbit |
AbstractPropagator.propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date. |
protected void |
AbstractPropagator.setStartDate(AbsoluteDate startDate)
Set a start date. |
| Constructors in org.orekit.propagation with parameters of type AbsoluteDate | |
|---|---|
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. |
|
| Constructor parameters in org.orekit.propagation with type arguments of type AbsoluteDate | |
|---|---|
AnalyticalIntegratedEphemeris(List<AbsoluteDate> initialDates,
List<AbsoluteDate> finalDates,
List<SpacecraftState> initialStates,
AbstractPropagator propagator,
AttitudeProvider attForcesProvider,
AttitudeProvider attEventsProvider,
boolean isForward)
Constructor. |
|
AnalyticalIntegratedEphemeris(List<AbsoluteDate> initialDates,
List<AbsoluteDate> finalDates,
List<SpacecraftState> initialStates,
AbstractPropagator propagator,
AttitudeProvider attForcesProvider,
AttitudeProvider attEventsProvider,
boolean isForward)
Constructor. |
|
| Uses of AbsoluteDate in org.orekit.propagation.analytical |
|---|
| Methods in org.orekit.propagation.analytical with parameters of type AbsoluteDate | |
|---|---|
protected SpacecraftState |
AdapterPropagator.basicPropagate(AbsoluteDate date)
Propagate an orbit without any fancy features. |
void |
AnalyticalEphemerisModeHandler.init(SpacecraftState s0,
AbsoluteDate t)
Initialize step handler at the start of a propagation. |
Orbit |
EcksteinHechlerPropagator.propagateMeanOrbit(AbsoluteDate date)
Propagate mean orbit until provided date. |
Orbit |
AbstractLyddanePropagator.propagateMeanOrbit(AbsoluteDate date)
Propagate mean orbit until provided date. |
Orbit |
LyddaneSecularPropagator.propagateMeanOrbit(AbsoluteDate date)
Propagate mean orbit until provided date. |
protected Orbit |
AdapterPropagator.propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date. |
Orbit |
EcksteinHechlerPropagator.propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date. |
Orbit |
AbstractLyddanePropagator.propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date. |
protected Orbit |
KeplerianPropagator.propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date. |
Orbit |
J2SecularPropagator.propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date. |
protected Orbit |
AbstractLyddanePropagator.propagateOrbit(AbsoluteDate date,
Orbit secularOrbit,
Frame outputFrame,
AbstractLyddanePropagator.LyddaneParametersType returnType)
Propagate orbit to provided date. |
| Uses of AbsoluteDate in org.orekit.propagation.analytical.covariance |
|---|
| Methods in org.orekit.propagation.analytical.covariance that return AbsoluteDate | |
|---|---|
AbsoluteDate |
OrbitCovariance.getDate()
Get the date. |
AbsoluteDate |
CovarianceInterpolation.getT1()
|
AbsoluteDate |
CovarianceInterpolation.getT2()
|
| Methods in org.orekit.propagation.analytical.covariance with parameters of type AbsoluteDate | |
|---|---|
RealMatrix |
CovarianceInterpolation.interpolate(AbsoluteDate t)
Computes the interpolation of a covariance matrix based on its two surrounding covariance matrices which define the interpolation interval allowed. |
double[][] |
CovarianceInterpolation.interpolateArray(AbsoluteDate t)
Computes the interpolation of a covariance matrix based on its two surrounding covariance matrices which define the interpolation interval allowed. |
OrbitCovariance |
OrbitCovariance.propagate(Orbit refOrbit,
AbsoluteDate target)
Propagate covariance. |
void |
CovarianceInterpolation.setFirstCovarianceMatrix(RealMatrix covMatrix,
AbsoluteDate t)
Allows to change the CovarianceMatrix standing for the lower bound of the interpolation interval, associated with t1. |
void |
CovarianceInterpolation.setSecondCovarianceMatrix(RealMatrix covMatrix,
AbsoluteDate t)
Allows to change the CovarianceMatrix standing for the upper bound of the interpolation interval, associated with t2. |
| Constructors in org.orekit.propagation.analytical.covariance with parameters of type AbsoluteDate | |
|---|---|
CovarianceInterpolation(AbsoluteDate t1In,
double[][] matrix1,
AbsoluteDate t2In,
double[][] matrix2,
int order,
Orbit orbitSatellite,
double muValue)
Constructor of the class CovarianceInterpolation |
|
CovarianceInterpolation(AbsoluteDate t1In,
RealMatrix matrix1,
AbsoluteDate t2In,
RealMatrix matrix2,
int order,
Orbit orbitSatellite,
double muValue)
Constructor of the class CovarianceInterpolation |
|
OrbitCovariance(AbsoluteDate covDate,
Frame refFrame,
OrbitType coordType,
RealMatrix covMat)
Simple constructor |
|
| Uses of AbsoluteDate in org.orekit.propagation.analytical.tle |
|---|
| Methods in org.orekit.propagation.analytical.tle that return AbsoluteDate | |
|---|---|
AbsoluteDate |
TLE.getDate()
Get the TLE current date. |
AbsoluteDate |
TLESeries.getFirstDate()
Get the start date of the series. |
AbsoluteDate |
TLESeries.getLastDate()
Get the last date of the series. |
| Methods in org.orekit.propagation.analytical.tle with parameters of type AbsoluteDate | |
|---|---|
TLE |
TLESeries.getClosestTLE(AbsoluteDate date)
Get the closest TLE to the selected date. |
PVCoordinates |
TLEPropagator.getPVCoordinates(AbsoluteDate date)
Get the extrapolated position and velocity from an initial TLE. |
PVCoordinates |
TLESeries.getPVCoordinates(AbsoluteDate date)
Get the extrapolated position and velocity from an initial date. |
protected Orbit |
TLEPropagator.propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date. |
| Constructors in org.orekit.propagation.analytical.tle with parameters of type AbsoluteDate | |
|---|---|
TLE(int satelliteNumber,
char classification,
int launchYear,
int launchNumber,
String launchPiece,
int ephemerisType,
int elementNumber,
AbsoluteDate epoch,
double meanMotion,
double meanMotionFirstDerivative,
double meanMotionSecondDerivative,
double e,
double i,
double pa,
double raan,
double meanAnomaly,
int revolutionNumberAtEpoch,
double bStar)
Simple constructor from already parsed elements. |
|
| Uses of AbsoluteDate in org.orekit.propagation.analytical.twod |
|---|
| Methods in org.orekit.propagation.analytical.twod that return AbsoluteDate | |
|---|---|
AbsoluteDate[] |
AbstractDateIntervalFunction.getDateIntervals()
Returns a copy of date intervals. |
AbsoluteDate |
DatePolynomialFunction.getT0()
Returns the model origin date. |
| Methods in org.orekit.propagation.analytical.twod with parameters of type AbsoluteDate | |
|---|---|
double |
Analytical2DParameterModel.getCenteredValue(AbsoluteDate date)
Get the centered value of the model. |
protected int |
AbstractDateIntervalFunction.getIndexInterval(AbsoluteDate date)
Returns index such as dateIntervals[k] <= date <= dateIntervals[k+1]. |
double |
Analytical2DParameterModel.getValue(AbsoluteDate date,
double pso,
double lna)
Get the value of the model at provided date. |
double |
Analytical2DParameterModel.getValue(AbsoluteDate date,
double pso,
double lna,
int order)
Get the value of the model at provided date. |
double[] |
Analytical2DOrbitModel.propagateModel(AbsoluteDate date)
Propagate each parameter model to specified date and return an array of 6 values. |
double[] |
Analytical2DOrbitModel.propagateModel(AbsoluteDate date,
int[] orders)
Propagate each parameter model to specified date and return an array of 6 values. |
protected Orbit |
Analytical2DPropagator.propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date. |
double |
DateIntervalLinearFunction.value(AbsoluteDate t)
Returns value of function at provided date. |
double |
DateIntervalParabolicFunction.value(AbsoluteDate t)
Returns value of function at provided date. |
double |
DatePolynomialFunction.value(AbsoluteDate date)
Returns value of function at provided date. |
double |
UnivariateDateFunction.value(AbsoluteDate date)
Returns value of function at provided date. |
| Constructors in org.orekit.propagation.analytical.twod with parameters of type AbsoluteDate | |
|---|---|
AbstractDateIntervalFunction(AbsoluteDate[] timeIntervals)
Constructor. |
|
Analytical2DPropagator(Analytical2DOrbitModel model,
AbsoluteDate initialDate)
Create an instance of a 2D propagator with default EME2000 aligned attitude. |
|
Analytical2DPropagator(Analytical2DOrbitModel model,
AbsoluteDate initialDate,
int[] orders)
Create an instance of a 2D propagator with default EME2000 aligned attitude. |
|
Analytical2DPropagator(AttitudeProvider attitudeProvider,
Analytical2DOrbitModel model,
AbsoluteDate initialDate)
Create an instance of a 2D propagator. |
|
Analytical2DPropagator(AttitudeProvider attitudeProvider,
Analytical2DOrbitModel model,
AbsoluteDate initialDate,
int[] orders)
Create an instance of a 2D propagator. |
|
DateIntervalLinearFunction(double ax0,
AbsoluteDate[] timeIntervals,
double[] axDotIntervals)
Constructor. |
|
DateIntervalParabolicFunction(double ax0,
double axDot0,
AbsoluteDate[] timeIntervals,
double[] axDotDotIntervals)
Constructor. |
|
DatePolynomialFunction(AbsoluteDate origin,
double[] polynomialCoefs)
Constructor. |
|
| Uses of AbsoluteDate in org.orekit.propagation.events |
|---|
| Methods in org.orekit.propagation.events that return AbsoluteDate | |
|---|---|
AbsoluteDate |
DateDetector.getDate()
Get the current event date according to the propagator. |
AbsoluteDate |
EventState.getEventTime()
Get the occurrence time of the event triggered in the current step. |
| Methods in org.orekit.propagation.events with parameters of type AbsoluteDate | |
|---|---|
void |
DateDetector.addEventDate(AbsoluteDate target)
Add an event date. |
void |
ThreeBodiesAngleDetector.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
|
void |
ExtremaThreeBodiesAngleDetector.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
|
void |
ThreeBodiesAngleDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
ExtremaDistanceDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
AbstractDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation. |
void |
EventDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation. |
void |
NthOccurrenceDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation. |
void |
LatitudeDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
DistanceDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
EventShifter.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation. |
void |
ExtremaThreeBodiesAngleDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
BetaAngleDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
LocalTimeDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
NadirSolarIncidenceDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
ExtremaLatitudeDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
AOLDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
ExtremaElevationDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
SolarTimeDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
ExtremaLongitudeDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
LongitudeDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
AnomalyDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
| Constructors in org.orekit.propagation.events with parameters of type AbsoluteDate | |
|---|---|
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. |
|
DateDetector(AbsoluteDate target)
Build a new instance. |
|
DateDetector(AbsoluteDate target,
double maxCheck,
double threshold)
Build a new instance. |
|
DateDetector(AbsoluteDate target,
double maxCheck,
double threshold,
EventDetector.Action action)
Build a new instance. |
|
DateDetector(AbsoluteDate target,
double maxCheck,
double threshold,
EventDetector.Action action,
boolean remove)
Build a new instance. |
|
| Uses of AbsoluteDate in org.orekit.propagation.events.multi |
|---|
| Methods in org.orekit.propagation.events.multi with parameters of type AbsoluteDate | |
|---|---|
void |
MultiEventDetector.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation. |
| Uses of AbsoluteDate in org.orekit.propagation.numerical |
|---|
| Methods in org.orekit.propagation.numerical with parameters of type AbsoluteDate | |
|---|---|
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. |
SpacecraftState |
NumericalPropagator.propagate(AbsoluteDate target)
Propagate towards a target date. |
SpacecraftState |
NumericalPropagator.propagate(AbsoluteDate tStart,
AbsoluteDate tEnd)
Propagate from a start date towards a target date. |
void |
ModeHandler.setReference(AbsoluteDate newReference)
Define new reference date. |
| Uses of AbsoluteDate in org.orekit.propagation.precomputed |
|---|
| Fields in org.orekit.propagation.precomputed declared as AbsoluteDate | |
|---|---|
protected AbsoluteDate |
AbstractEphemeris.maxDate
Last date in range. |
protected AbsoluteDate |
AbstractEphemeris.minDate
First date in range. |
| Methods in org.orekit.propagation.precomputed that return AbsoluteDate | |
|---|---|
AbsoluteDate |
IntegratedEphemeris.getMaxDate()
Get the last date of the range. |
AbsoluteDate |
Ephemeris.getMaxDate()
Get the last date of the range. |
AbsoluteDate |
AbstractEphemeris.getMaxDate()
Get the last date of the range. |
AbsoluteDate |
IntegratedEphemeris.getMinDate()
Get the first date of the range. |
AbsoluteDate |
Ephemeris.getMinDate()
Get the first date of the range. |
AbsoluteDate |
AbstractEphemeris.getMinDate()
Get the first date of the range. |
| Methods in org.orekit.propagation.precomputed with parameters of type AbsoluteDate | |
|---|---|
protected Attitude[] |
AbstractEphemeris.attitudesInterpolation(SpacecraftState[] tab,
int order,
int i0,
AbsoluteDate date)
This method is called only if attitudes are supported. |
protected SpacecraftState |
IntegratedEphemeris.basicPropagate(AbsoluteDate date)
Propagate an orbit without any fancy features. |
SpacecraftState |
Ephemeris.basicPropagate(AbsoluteDate date)
|
protected SpacecraftState |
AbstractEphemeris.basicPropagate(AbsoluteDate date)
|
protected SpacecraftState |
LagrangeEphemeris.getInterpolatedSpacecraftState(AbsoluteDate date)
Deprecated. Get the interpolated spacecraft state. |
protected SpacecraftState |
HermiteEphemeris.getInterpolatedSpacecraftState(AbsoluteDate date)
Deprecated. Get the interpolated spacecraft state. |
protected abstract SpacecraftState |
AbstractEphemeris.getInterpolatedSpacecraftState(AbsoluteDate date)
Get the interpolated spacecraft state. |
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. |
protected Orbit |
IntegratedEphemeris.propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date. |
protected Orbit |
Ephemeris.propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date. |
protected Orbit |
AbstractEphemeris.propagateOrbit(AbsoluteDate date)
|
| Constructor parameters in org.orekit.propagation.precomputed with type arguments of type AbsoluteDate | |
|---|---|
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. |
|
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. |
|
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. |
|
| Uses of AbsoluteDate in org.orekit.propagation.sampling |
|---|
| Methods in org.orekit.propagation.sampling that return AbsoluteDate | |
|---|---|
AbsoluteDate |
BasicStepInterpolator.getCurrentDate()
Get the current grid date. |
AbsoluteDate |
OrekitStepInterpolator.getCurrentDate()
Get the current grid date. |
AbsoluteDate |
AdaptedStepHandler.getCurrentDate()
Get the current grid date. |
AbsoluteDate |
BasicStepInterpolator.getInterpolatedDate()
Get the interpolated date. |
AbsoluteDate |
OrekitStepInterpolator.getInterpolatedDate()
Get the interpolated date. |
AbsoluteDate |
AdaptedStepHandler.getInterpolatedDate()
Get the interpolated date. |
AbsoluteDate |
BasicStepInterpolator.getPreviousDate()
Get the previous grid date. |
AbsoluteDate |
OrekitStepInterpolator.getPreviousDate()
Get the previous grid date. |
AbsoluteDate |
AdaptedStepHandler.getPreviousDate()
Get the previous grid date. |
| Methods in org.orekit.propagation.sampling with parameters of type AbsoluteDate | |
|---|---|
void |
OrekitFixedStepHandler.init(SpacecraftState s0,
AbsoluteDate t)
Initialize step handler at the start of a propagation. |
void |
OrekitStepHandler.init(SpacecraftState s0,
AbsoluteDate t)
Initialize step handler at the start of a propagation. |
void |
OrekitStepNormalizer.init(SpacecraftState s0,
AbsoluteDate t)
Initialize step handler at the start of a propagation. |
void |
OrekitStepHandlerMultiplexer.init(SpacecraftState s0,
AbsoluteDate t)
Initialize step handler at the start of a propagation. |
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. |
void |
BasicStepInterpolator.setInterpolatedDate(AbsoluteDate date)
Set the interpolated date. |
void |
OrekitStepInterpolator.setInterpolatedDate(AbsoluteDate date)
Set the interpolated date. |
void |
AdaptedStepHandler.setInterpolatedDate(AbsoluteDate date)
Set the interpolated date. |
void |
AdaptedStepHandler.setReference(AbsoluteDate newReference)
Define new reference date. |
void |
BasicStepInterpolator.storeDate(AbsoluteDate date)
Store the current step date. |
| Uses of AbsoluteDate in org.orekit.time |
|---|
| Fields in org.orekit.time declared as AbsoluteDate | |
|---|---|
static AbsoluteDate |
AbsoluteDate.CCSDS_EPOCH
Reference epoch for CCSDS Time Code Format (CCSDS 301.0-B-4): 1958-01-01T00:00:00 International Atomic Time (not UTC). |
static AbsoluteDate |
AbsoluteDate.FIFTIES_EPOCH_TAI
Reference epoch for 1950 dates: 1950-01-01T00:00:00 TAI. |
static AbsoluteDate |
AbsoluteDate.FIFTIES_EPOCH_TT
Reference epoch for 1950 dates: 1950-01-01T00:00:00 Terrestrial Time. |
static AbsoluteDate |
AbsoluteDate.FIFTIES_EPOCH_UTC
Reference epoch for 1950 dates: 1950-01-01T00:00:00 UTC. |
static AbsoluteDate |
AbsoluteDate.FUTURE_INFINITY
Dummy date at infinity in the future direction. |
static AbsoluteDate |
AbsoluteDate.GALILEO_EPOCH
Reference epoch for Galileo System Time: 1999-08-22T00:00:00 UTC. |
static AbsoluteDate |
AbsoluteDate.GPS_EPOCH
Reference epoch for GPS weeks: 1980-01-06T00:00:00 GPS time. |
static AbsoluteDate |
AbsoluteDate.J2000_EPOCH
J2000.0 Reference epoch: 2000-01-01T12:00:00 Terrestrial Time (not UTC). |
static AbsoluteDate |
AbsoluteDate.JAVA_EPOCH
Java Reference epoch: 1970-01-01T00:00:00 Universal Time Coordinate is equivalent to Java Reference epoch: 1970-01-01T00:00:08 TAI. |
static AbsoluteDate |
AbsoluteDate.JULIAN_EPOCH
Reference epoch for julian dates: -4712-01-01T12:00:00 Terrestrial Time. |
static AbsoluteDate |
AbsoluteDate.MODIFIED_JULIAN_EPOCH
Reference epoch for modified julian dates: 1858-11-17T00:00:00 Terrestrial Time. |
static AbsoluteDate |
AbsoluteDate.PAST_INFINITY
Dummy date at infinity in the past direction. |
| Methods in org.orekit.time that return AbsoluteDate | |
|---|---|
static AbsoluteDate |
AbsoluteDate.createGPSDate(int weekNumber,
double milliInWeek)
Build an instance corresponding to a GPS date. |
AbsoluteDate |
AbsoluteDate.getDate()
Get the date. |
AbsoluteDate |
TimeStamped.getDate()
Get the date. |
AbsoluteDate |
UTCScale.getFirstKnownLeapSecond()
Get the date of the first known leap second. |
AbsoluteDate |
UTCScale.getLastKnownLeapSecond()
Get the date of the last known leap second. |
static AbsoluteDate |
AbsoluteDate.parseCCSDSCalendarSegmentedTimeCode(byte preambleField,
byte[] timeField)
Build an instance from a CCSDS Calendar Segmented Time Code (CCS). |
static AbsoluteDate |
AbsoluteDate.parseCCSDSDaySegmentedTimeCode(byte preambleField,
byte[] timeField,
DateComponents agencyDefinedEpoch)
Build an instance from a CCSDS Day Segmented Time Code (CDS). |
static AbsoluteDate |
AbsoluteDate.parseCCSDSUnsegmentedTimeCode(byte preambleField1,
byte preambleField2,
byte[] timeField,
AbsoluteDate agencyDefinedEpoch)
Build an instance from a CCSDS Unsegmented Time Code (CUC). |
AbsoluteDate |
AbsoluteDate.shiftedBy(double dt)
Get a time-shifted date. |
| Methods in org.orekit.time with parameters of type AbsoluteDate | |
|---|---|
int |
AbsoluteDate.compareTo(AbsoluteDate date)
Compare the instance with another date. |
double |
LocalTime.computeMeanLocalTime(AbsoluteDate date,
Vector3D pos)
Compute mean local time in TIRF frame. |
double |
LocalTime.computeMeanLocalTime(AbsoluteDate date,
Vector3D pos,
Frame frame,
double sideralTime)
Compute mean local time in provided frame. |
double |
LocalTime.computeTrueLocalTime(AbsoluteDate date,
Vector3D pos)
Compute true local time in TIRF frame. |
double |
LocalTime.computeTrueLocalTime(AbsoluteDate date,
Vector3D pos,
Frame frame)
Compute true local time in provided frame in the range ] -43200s; 43200s ]. |
double |
AbsoluteDate.durationFrom(AbsoluteDate instant)
Compute the physically elapsed duration between two instants. |
double |
UTCScale.getLeap(AbsoluteDate date)
Get the value of the previous leap. |
boolean |
UTCScale.insideLeap(AbsoluteDate date)
Check if date is within a leap second introduction. |
T |
TimeInterpolable.interpolate(AbsoluteDate date,
Collection<T> sample)
Get an interpolated instance. |
double |
AbsoluteDate.offsetFrom(AbsoluteDate instant,
TimeScale timeScale)
Compute the apparent clock offset between two instant in the perspective of a specific time scale. |
double |
UTCScale.offsetFromTAI(AbsoluteDate date)
Get the offset to convert locations from TAIScale to instance. |
double |
TTScale.offsetFromTAI(AbsoluteDate date)
Get the offset to convert locations from TAIScale to instance. |
double |
UT1Scale.offsetFromTAI(AbsoluteDate date)
Get the offset to convert locations from TAIScale to instance. |
double |
GMSTScale.offsetFromTAI(AbsoluteDate date)
Get the offset to convert locations from TAIScale to instance. |
double |
TCBScale.offsetFromTAI(AbsoluteDate date)
Get the offset to convert locations from TAIScale to instance. |
double |
GalileoScale.offsetFromTAI(AbsoluteDate date)
Get the offset to convert locations from TAIScale to instance. |
double |
TCGScale.offsetFromTAI(AbsoluteDate date)
Get the offset to convert locations from TAIScale to instance. |
double |
TAIScale.offsetFromTAI(AbsoluteDate taiTime)
Get the offset to convert locations from TAIScale to instance. |
double |
TimeScale.offsetFromTAI(AbsoluteDate date)
Get the offset to convert locations from TAIScale to instance. |
double |
TDBScale.offsetFromTAI(AbsoluteDate date)
Get the offset to convert locations from TAIScale to instance. |
double |
GPSScale.offsetFromTAI(AbsoluteDate date)
Get the offset to convert locations from TAIScale to instance. |
static AbsoluteDate |
AbsoluteDate.parseCCSDSUnsegmentedTimeCode(byte preambleField1,
byte preambleField2,
byte[] timeField,
AbsoluteDate agencyDefinedEpoch)
Build an instance from a CCSDS Unsegmented Time Code (CUC). |
| Constructors in org.orekit.time with parameters of type AbsoluteDate | |
|---|---|
AbsoluteDate(AbsoluteDate since,
double elapsedDuration)
Build an instance from an elapsed duration since to another instant. |
|
AbsoluteDate(AbsoluteDate reference,
double apparentOffset,
TimeScale timeScale)
Build an instance from an apparent clock offset with respect to another instant in the perspective of a specific time scale. |
|
| Uses of AbsoluteDate in org.orekit.utils |
|---|
| Fields in org.orekit.utils declared as AbsoluteDate | |
|---|---|
protected AbsoluteDate[] |
AbstractBoundedPVProvider.tDate
Dates table |
| Methods in org.orekit.utils that return AbsoluteDate | |
|---|---|
AbsoluteDate |
TimeStampedPVCoordinates.getDate()
Get the date. |
AbsoluteDate |
TimeStampedAngularCoordinates.getDate()
Get the date. |
AbsoluteDate |
AbstractBoundedPVProvider.getDateRef()
Get the reference date |
abstract AbsoluteDate |
AbstractBoundedPVProvider.getMaxDate()
Get the last date of the range. |
AbsoluteDate |
EphemerisPvLagrange.getMaxDate()
Return the higher date authorized to call getPVCoordinates. |
AbsoluteDate |
EphemerisPvHermite.getMaxDate()
For hermite interpolation, the last date is the date of the step before the last ephemeris point |
abstract AbsoluteDate |
AbstractBoundedPVProvider.getMinDate()
Get the first date of the range. |
AbsoluteDate |
EphemerisPvLagrange.getMinDate()
Return the lower date authorized to call getPVCoordinates. |
AbsoluteDate |
EphemerisPvHermite.getMinDate()
For hermite interpolation, the min date is the first ephemeris date which is also the reference date |
AbsoluteDate |
SecularAndHarmonic.getReferenceDate()
Get the reference date. |
| Methods in org.orekit.utils with parameters of type AbsoluteDate | |
|---|---|
void |
SecularAndHarmonic.addPoint(AbsoluteDate date,
double osculatingValue)
Add a fitting point. |
double[] |
SecularAndHarmonic.approximateAsPolynomialOnly(int combinedDegree,
AbsoluteDate combinedReference,
int meanDegree,
int meanHarmonics,
AbsoluteDate start,
AbsoluteDate end,
double step)
Approximate an already fitted model to polynomial only terms. |
List<T> |
TimeStampedGenerator.generate(T existing,
AbsoluteDate date)
Generate a chronologically sorted list of entries to be cached. |
AbsoluteDateIntervalsList |
AbsoluteDateIntervalsList.getIntervalsContainingDate(AbsoluteDate date)
Gets the AbsoluteDateIntervalsList containing the specified date. |
T[] |
TimeStampedCache.getNeighbors(AbsoluteDate central)
Get the entries surrounding a central date. |
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. |
static TimeStampedAngularCoordinates |
TimeStampedAngularCoordinates.interpolate(AbsoluteDate date,
AngularDerivativesFilter filter,
Collection<TimeStampedAngularCoordinates> sample)
Interpolate angular coordinates. |
static TimeStampedAngularCoordinates |
TimeStampedAngularCoordinates.interpolate(AbsoluteDate date,
AngularDerivativesFilter filter,
Collection<TimeStampedAngularCoordinates> sample,
boolean computeSpinDerivatives)
Interpolate angular coordinates. |
static AngularCoordinates |
AngularCoordinates.interpolate(AbsoluteDate date,
boolean useRotationRates,
Collection<Pair<AbsoluteDate,AngularCoordinates>> sample)
Deprecated. since 3.1 replaced with TimeStampedAngularCoordinates.interpolate(AbsoluteDate, AngularDerivativesFilter, Collection) |
static AngularCoordinates |
AngularCoordinates.interpolate(AbsoluteDate date,
boolean useRotationRates,
Collection<Pair<AbsoluteDate,AngularCoordinates>> sample,
boolean computeSpinDerivative)
Deprecated. since 3.1 replaced with TimeStampedAngularCoordinates.interpolate(AbsoluteDate, AngularDerivativesFilter, Collection, boolean) |
static PVCoordinates |
PVCoordinates.interpolate(AbsoluteDate date,
boolean useVelocities,
Collection<Pair<AbsoluteDate,PVCoordinates>> sample)
Deprecated. since 3.1 replaced with TimeStampedPVCoordinates.interpolate(AbsoluteDate, CartesianDerivativesFilter, Collection) |
static TimeStampedPVCoordinates |
TimeStampedPVCoordinates.interpolate(AbsoluteDate date,
CartesianDerivativesFilter filter,
Collection<TimeStampedPVCoordinates> sample)
Interpolate position-velocity. |
double |
SecularAndHarmonic.meanDerivative(AbsoluteDate date,
int degree,
int harmonics)
Get mean derivative, truncated to first components. |
double |
SecularAndHarmonic.meanSecondDerivative(AbsoluteDate date,
int degree,
int harmonics)
Get mean second derivative, truncated to first components. |
double |
SecularAndHarmonic.meanValue(AbsoluteDate date,
int degree,
int harmonics)
Get mean value, truncated to first components. |
double |
SecularAndHarmonic.osculatingDerivative(AbsoluteDate date)
Get fitted osculating derivative. |
double |
SecularAndHarmonic.osculatingSecondDerivative(AbsoluteDate date)
Get fitted osculating second derivative. |
double |
SecularAndHarmonic.osculatingValue(AbsoluteDate date)
Get fitted osculating value. |
void |
SecularAndHarmonic.resetFitting(AbsoluteDate date,
double... initialGuess)
Reset fitting. |
static Vector3D |
ReferencePointsDisplacement.solidEarthTidesCorrections(AbsoluteDate date,
Vector3D point,
Vector3D sun,
Vector3D moon)
Computes the displacement of reference points due to the effect of the solid Earth tides. |
| Method parameters in org.orekit.utils with type arguments of type AbsoluteDate | |
|---|---|
static AngularCoordinates |
AngularCoordinates.interpolate(AbsoluteDate date,
boolean useRotationRates,
Collection<Pair<AbsoluteDate,AngularCoordinates>> sample)
Deprecated. since 3.1 replaced with TimeStampedAngularCoordinates.interpolate(AbsoluteDate, AngularDerivativesFilter, Collection) |
static AngularCoordinates |
AngularCoordinates.interpolate(AbsoluteDate date,
boolean useRotationRates,
Collection<Pair<AbsoluteDate,AngularCoordinates>> sample,
boolean computeSpinDerivative)
Deprecated. since 3.1 replaced with TimeStampedAngularCoordinates.interpolate(AbsoluteDate, AngularDerivativesFilter, Collection, boolean) |
static PVCoordinates |
PVCoordinates.interpolate(AbsoluteDate date,
boolean useVelocities,
Collection<Pair<AbsoluteDate,PVCoordinates>> sample)
Deprecated. since 3.1 replaced with TimeStampedPVCoordinates.interpolate(AbsoluteDate, CartesianDerivativesFilter, Collection) |
| Constructors in org.orekit.utils with parameters of type AbsoluteDate | |
|---|---|
AbsoluteDateInterval(IntervalEndpointType lowerEndpointIn,
AbsoluteDate lowerDataIn,
AbsoluteDate upperDataIn,
IntervalEndpointType upperEndpointIn)
Constructor for an AbsoluteDate interval. |
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AbstractBoundedPVProvider(PVCoordinates[] tabPV,
Frame frame,
AbsoluteDate[] tabDate,
ISearchIndex algo)
Instantiation of AbstractBoundedPVProvider attributes. |
|
EphemerisPvHermite(PVCoordinates[] tabPV,
Vector3D[] tabAcc,
Frame frame,
AbsoluteDate[] tabDate,
ISearchIndex algo)
Creates an instance of EphemerisPvHermite. |
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EphemerisPvLagrange(PVCoordinates[] tabPV,
int order,
Frame frame,
AbsoluteDate[] tabDate,
ISearchIndex algo)
Creates an instance of EphemerisPvLagrange |
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TimeStampedAngularCoordinates(AbsoluteDate date,
PVCoordinates u1,
PVCoordinates u2,
PVCoordinates v1,
PVCoordinates v2,
double tolerance)
Build the rotation that transforms a pair of pv coordinates into another pair. |
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TimeStampedAngularCoordinates(AbsoluteDate date,
PVCoordinates u1,
PVCoordinates u2,
PVCoordinates v1,
PVCoordinates v2,
double tolerance,
boolean spinDerivativesComputation)
Build the rotation that transforms a pair of pv coordinates into another pair. |
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TimeStampedAngularCoordinates(AbsoluteDate date,
Rotation rotation,
Vector3D rotationRate,
Vector3D rotationAcceleration)
Builds a rotation/rotation rate pair. |
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TimeStampedPVCoordinates(AbsoluteDate date,
double a,
PVCoordinates pv)
Multiplicative constructor |
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TimeStampedPVCoordinates(AbsoluteDate date,
double a1,
PVCoordinates pv1,
double a2,
PVCoordinates pv2)
Linear constructor |
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TimeStampedPVCoordinates(AbsoluteDate date,
double a1,
PVCoordinates pv1,
double a2,
PVCoordinates pv2,
double a3,
PVCoordinates pv3)
Linear constructor |
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TimeStampedPVCoordinates(AbsoluteDate date,
double a1,
PVCoordinates pv1,
double a2,
PVCoordinates pv2,
double a3,
PVCoordinates pv3,
double a4,
PVCoordinates pv4)
Linear constructor |
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TimeStampedPVCoordinates(AbsoluteDate date,
FieldVector3D<DerivativeStructure> p)
Builds a TimeStampedPVCoordinates triplet from a FieldVector3D<DerivativeStructure>. |
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TimeStampedPVCoordinates(AbsoluteDate date,
PVCoordinates pv)
Build from position velocity acceleration coordinates. |
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TimeStampedPVCoordinates(AbsoluteDate date,
PVCoordinates start,
PVCoordinates end)
Subtractive constructor |
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TimeStampedPVCoordinates(AbsoluteDate date,
Vector3D position,
Vector3D velocity)
Build from position and velocity. |
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TimeStampedPVCoordinates(AbsoluteDate date,
Vector3D position,
Vector3D velocity,
Vector3D acceleration)
Builds a TimeStampedPVCoordinates triplet. |
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