| Package | Description |
|---|---|
| org.orekit.attitudes |
This package provides classes to represent simple attitudes.
|
| org.orekit.bodies |
This package provides interface to represent the position and geometry of
space objects such as stars, planets or asteroids.
|
| org.orekit.data |
This package provide base classes for exploring the configured data
directory tree and read external data that can be used by the library.
|
| org.orekit.estimation.iod |
This package provides initial orbit determination methods.
|
| org.orekit.estimation.measurements |
The measurements package defines everything that is related to orbit
determination measurements.
|
| org.orekit.estimation.measurements.generation |
This package provides Orbit Determination measurements generation.
|
| org.orekit.estimation.measurements.gnss |
This package provides methods to handle GNSS measurements.
|
| org.orekit.estimation.sequential |
The sequential package provides an implementation of a
Kalman Filter engine to perform an orbit determination.
|
| org.orekit.files.ccsds |
This package provides a parser for elements data stored in CCSDS Navigation Data Message format.
|
| org.orekit.files.general |
This package provides interfaces for orbit file representations and corresponding
parsers.
|
| org.orekit.files.sp3 |
This package provides a parser for orbit data stored in SP3 format.
|
| org.orekit.forces |
This package provides the interface for force models that will be used by the
NumericalPropagator, as well as
some classical spacecraft models for surface forces (spherical, box and solar array ...). |
| org.orekit.forces.drag |
This package provides all drag-related forces.
|
| org.orekit.forces.gravity |
This package provides all gravity-related forces.
|
| org.orekit.forces.gravity.potential |
This package provides classes to read gravity field files and supports several
different formats.
|
| org.orekit.forces.maneuvers |
This package provides models of simple maneuvers.
|
| org.orekit.forces.maneuvers.propulsion |
This package provides propulsion models intended to be used with class
Maneuver. |
| org.orekit.forces.maneuvers.trigger |
This package provides maneuver triggers' models intended to be used with class
Maneuver. |
| org.orekit.forces.radiation |
This package provides all radiation pressure related forces.
|
| org.orekit.frames |
This package provides classes to handle frames and transforms between them.
|
| org.orekit.gnss |
This package provides classes related to GNSS applications.
|
| org.orekit.gnss.antenna |
This package provides classes related to receiver and satellites antenna modeling.
|
| org.orekit.gnss.attitude |
This package provides classes related to navigation satellites attitude modeling.
|
| org.orekit.models.earth |
This package provides models that simulate certain physical phenomena
of Earth and the near-Earth environment.
|
| org.orekit.models.earth.atmosphere |
This package provides the atmosphere model interface and several implementations.
|
| org.orekit.models.earth.atmosphere.data |
This package provides classes to get atmospheric data,
including solar flux and planetary geomagnetic indices.
|
| org.orekit.models.earth.ionosphere |
This package provides models that simulate the impact of the ionosphere.
|
| org.orekit.models.earth.troposphere |
This package provides models that simulate the impact of the troposphere.
|
| org.orekit.models.earth.weather |
This package provides models that simulate global weather conditions on Earth.
|
| org.orekit.orbits |
This package provides classes to represent orbits.
|
| org.orekit.propagation |
Propagation
|
| org.orekit.propagation.analytical |
Top level package for analytical propagators.
|
| org.orekit.propagation.analytical.gnss |
This package provides classes to propagate GNSS orbits.
|
| org.orekit.propagation.analytical.tle |
This package provides classes to read and extrapolate tle's.
|
| org.orekit.propagation.conversion |
This package provides tools to convert a given propagator or a set of
SpacecraftState into another propagator. |
| org.orekit.propagation.events |
This package provides interfaces and classes dealing with events occurring during propagation.
|
| org.orekit.propagation.events.handlers |
This package provides an interface and classes dealing with events occurrence only.
|
| org.orekit.propagation.integration |
Utilities for integration-based propagators (both numerical and semi-analytical).
|
| org.orekit.propagation.numerical |
Top level package for numerical propagators.
|
| org.orekit.propagation.sampling |
This package provides interfaces and classes dealing with step handling during propagation.
|
| org.orekit.propagation.semianalytical.dsst |
This package provides an implementation of the Draper Semi-analytical
Satellite Theory (DSST).
|
| org.orekit.propagation.semianalytical.dsst.forces |
This package provides force models for Draper Semi-analytical Satellite Theory (DSST).
|
| org.orekit.propagation.semianalytical.dsst.utilities |
This package provides utilities for Draper Semi-analytical Satellite Theory (DSST).
|
| org.orekit.time |
This independent package provides classes to handle epochs, time scales,
and to compare instants together.
|
| org.orekit.utils |
This package provides useful objects.
|
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
Attitude.getDate()
Get the date of attitude parameters.
|
| Modifier and Type | Method and Description |
|---|---|
Attitude |
YawCompensation.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 |
AttitudeProvider.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
InertialProvider.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
FixedRate.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AttitudesSequence.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
GroundPointing.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 |
LofOffsetPointing.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
TabulatedLofOffset.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
YawSteering.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
TabulatedProvider.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
CelestialBodyPointed.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
YawCompensation.getBaseState(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the base system state at given date, without compensation.
|
Attitude |
YawSteering.getBaseState(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the base system state at given date, without compensation.
|
TimeStampedPVCoordinates |
YawCompensation.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)
Compute the target point position/velocity in specified frame.
|
abstract TimeStampedPVCoordinates |
GroundPointing.getTargetPV(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
TimeStampedPVCoordinates |
LofOffsetPointing.getTargetPV(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
TimeStampedPVCoordinates |
YawSteering.getTargetPV(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
TimeStampedPVCoordinates |
TargetPointing.getTargetPV(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
TimeStampedPVCoordinates |
BodyCenterPointing.getTargetPV(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
double |
YawCompensation.getYawAngle(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the yaw compensation angle at date.
|
Attitude |
Attitude.interpolate(AbsoluteDate interpolationDate,
Stream<Attitude> sample)
Get an interpolated instance.
|
| Constructor and Description |
|---|
Attitude(AbsoluteDate date,
Frame referenceFrame,
AngularCoordinates orientation)
Creates a new instance.
|
Attitude(AbsoluteDate date,
Frame referenceFrame,
Rotation attitude,
Vector3D spin,
Vector3D acceleration)
Creates a new instance.
|
SpinStabilized(AttitudeProvider nonRotatingLaw,
AbsoluteDate start,
Vector3D axis,
double rate)
Creates a new instance.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
OneAxisEllipsoid.getCartesianIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date)
Get the intersection point of a line with the surface of the body.
|
GeodeticPoint |
BodyShape.getIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date)
Get the intersection point of a line with the surface of the body.
|
GeodeticPoint |
OneAxisEllipsoid.getIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date)
Get the intersection point of a line with the surface of the body.
|
default Vector3D |
IAUPole.getNode(AbsoluteDate date)
Get the body Q Node direction in ICRF frame.
|
Vector3D |
IAUPole.getPole(AbsoluteDate date)
Get the body North pole direction in ICRF frame.
|
double |
IAUPole.getPrimeMeridianAngle(AbsoluteDate date)
Get the prime meridian angle.
|
PVCoordinates |
JPLEphemeridesLoader.RawPVProvider.getRawPV(AbsoluteDate date)
Get the position-velocity at date.
|
AbsolutePVCoordinates |
CR3BPSystem.getRealAPV(AbsolutePVCoordinates apv0,
AbsoluteDate initialDate,
Frame outputFrame)
Get the AbsolutePVCoordinates from normalized units to standard units in an output frame.
|
Vector3D |
BodyShape.projectToGround(Vector3D point,
AbsoluteDate date,
Frame frame)
Project a point to the ground.
|
Vector3D |
OneAxisEllipsoid.projectToGround(Vector3D point,
AbsoluteDate date,
Frame frame)
Project a point to the ground.
|
FieldGeodeticPoint<DerivativeStructure> |
OneAxisEllipsoid.transform(PVCoordinates point,
Frame frame,
AbsoluteDate date)
Transform a Cartesian point to a surface-relative point.
|
GeodeticPoint |
BodyShape.transform(Vector3D point,
Frame frame,
AbsoluteDate date)
Transform a Cartesian point to a surface-relative point.
|
GeodeticPoint |
OneAxisEllipsoid.transform(Vector3D point,
Frame frame,
AbsoluteDate date)
Transform a Cartesian point to a surface-relative point.
|
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
DelaunayArguments.getDate()
Get the date.
|
| Modifier and Type | Method and Description |
|---|---|
BodiesElements |
FundamentalNutationArguments.evaluateAll(AbsoluteDate date)
Evaluate all fundamental arguments for the current date (Delaunay plus planetary).
|
| Constructor and Description |
|---|
BodiesElements(AbsoluteDate date,
double tc,
double gamma,
double gammaDot,
double l,
double lDot,
double lPrime,
double lPrimeDot,
double f,
double fDot,
double d,
double dDot,
double omega,
double omegaDot,
double lMe,
double lMeDot,
double lVe,
double lVeDot,
double lE,
double lEDot,
double lMa,
double lMaDot,
double lJu,
double lJuDot,
double lSa,
double lSaDot,
double lUr,
double lUrDot,
double lNe,
double lNeDot,
double pa,
double paDot)
Simple constructor.
|
DelaunayArguments(AbsoluteDate date,
double tc,
double gamma,
double gammaDot,
double l,
double lDot,
double lPrime,
double lPrimeDot,
double f,
double fDot,
double d,
double dDot,
double omega,
double omegaDot)
Simple constructor.
|
| Modifier and Type | Method and Description |
|---|---|
KeplerianOrbit |
IodLambert.estimate(Frame frame,
boolean posigrade,
int nRev,
Vector3D p1,
AbsoluteDate t1,
Vector3D p2,
AbsoluteDate t2)
Estimate a Keplerian orbit given two position vectors and a duration.
|
CartesianOrbit |
IodLaplace.estimate(Frame frame,
PVCoordinates obsPva,
AbsoluteDate obsDate1,
Vector3D los1,
AbsoluteDate obsDate2,
Vector3D los2,
AbsoluteDate obsDate3,
Vector3D los3)
Estimate orbit from three line of sight angles from the same location.
|
KeplerianOrbit |
IodGibbs.estimate(Frame frame,
Vector3D r1,
AbsoluteDate date1,
Vector3D r2,
AbsoluteDate date2,
Vector3D r3,
AbsoluteDate date3)
Give an initial orbit estimation, assuming Keplerian motion.
|
KeplerianOrbit |
IodGooding.estimate(Vector3D O1,
Vector3D O2,
Vector3D O3,
Vector3D lineOfSight1,
AbsoluteDate dateObs1,
Vector3D lineOfSight2,
AbsoluteDate dateObs2,
Vector3D lineOfSight3,
AbsoluteDate dateObs3,
double rho1init,
double rho3init)
Orbit got from Observed Three Lines of Sight (angles only).
|
KeplerianOrbit |
IodGooding.estimate(Vector3D O1,
Vector3D O2,
Vector3D O3,
Vector3D lineOfSight1,
AbsoluteDate dateObs1,
Vector3D lineOfSight2,
AbsoluteDate dateObs2,
Vector3D lineOfSight3,
AbsoluteDate dateObs3,
double rho1init,
double rho3init,
int nRev,
boolean direction)
Orbit got from Observed Three Lines of Sight (angles only).
|
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
AbstractMeasurement.getDate()
Get the date.
|
AbsoluteDate |
EstimatedMeasurement.getDate()
Get the date.
|
| Modifier and Type | Method and Description |
|---|---|
GeodeticPoint |
GroundStation.getOffsetGeodeticPoint(AbsoluteDate date)
Get the geodetic point at the center of the offset frame.
|
Transform |
GroundStation.getOffsetToInertial(Frame inertial,
AbsoluteDate clockDate)
Get the transform between offset frame and inertial frame.
|
FieldTransform<DerivativeStructure> |
GroundStation.getOffsetToInertial(Frame inertial,
AbsoluteDate clockDate,
DSFactory factory,
Map<String,Integer> indices)
Deprecated.
as of 10.2, replaced by
GroundStation.getOffsetToInertial(Frame, AbsoluteDate, int, Map) |
FieldTransform<Gradient> |
GroundStation.getOffsetToInertial(Frame inertial,
AbsoluteDate clockDate,
int freeParameters,
Map<String,Integer> indices)
Get the transform between offset frame and inertial frame with derivatives.
|
Transform |
EstimatedEarthFrameProvider.getTransform(AbsoluteDate date)
Get the
Transform corresponding to specified date. |
static double |
AbstractMeasurement.signalTimeOfFlight(TimeStampedPVCoordinates adjustableEmitterPV,
Vector3D receiverPosition,
AbsoluteDate signalArrivalDate)
Compute propagation delay on a link leg (typically downlink or uplink).
|
| Constructor and Description |
|---|
AbstractMeasurement(AbsoluteDate date,
double[] observed,
double[] sigma,
double[] baseWeight,
List<ObservableSatellite> satellites)
Simple constructor, for multi-dimensional measurements.
|
AbstractMeasurement(AbsoluteDate date,
double observed,
double sigma,
double baseWeight,
List<ObservableSatellite> satellites)
Simple constructor for mono-dimensional measurements.
|
AngularAzEl(GroundStation station,
AbsoluteDate date,
double[] angular,
double[] sigma,
double[] baseWeight,
ObservableSatellite satellite)
Simple constructor.
|
AngularRaDec(GroundStation station,
Frame referenceFrame,
AbsoluteDate date,
double[] angular,
double[] sigma,
double[] baseWeight,
ObservableSatellite satellite)
Simple constructor.
|
InterSatellitesRange(ObservableSatellite local,
ObservableSatellite remote,
boolean twoWay,
AbsoluteDate date,
double range,
double sigma,
double baseWeight)
Simple constructor.
|
Position(AbsoluteDate date,
Vector3D position,
double[][] covarianceMatrix,
double baseWeight,
ObservableSatellite satellite)
Constructor with full covariance matrix and all inputs.
|
Position(AbsoluteDate date,
Vector3D position,
double[] sigmaPosition,
double baseWeight,
ObservableSatellite satellite)
Constructor with one vector for the standard deviation.
|
Position(AbsoluteDate date,
Vector3D position,
double sigmaPosition,
double baseWeight,
ObservableSatellite satellite)
Constructor with one double for the standard deviation.
|
PV(AbsoluteDate date,
Vector3D position,
Vector3D velocity,
double[][] positionCovarianceMatrix,
double[][] velocityCovarianceMatrix,
double baseWeight,
ObservableSatellite satellite)
Constructor with 2 smaller covariance matrices.
|
PV(AbsoluteDate date,
Vector3D position,
Vector3D velocity,
double[][] covarianceMatrix,
double baseWeight,
ObservableSatellite satellite)
Constructor with full covariance matrix and all inputs.
|
PV(AbsoluteDate date,
Vector3D position,
Vector3D velocity,
double[] sigmaPosition,
double[] sigmaVelocity,
double baseWeight,
ObservableSatellite satellite)
Constructor with two vectors for the standard deviations.
|
PV(AbsoluteDate date,
Vector3D position,
Vector3D velocity,
double[] sigmaPV,
double baseWeight,
ObservableSatellite satellite)
Constructor with one vector for the standard deviations.
|
PV(AbsoluteDate date,
Vector3D position,
Vector3D velocity,
double sigmaPosition,
double sigmaVelocity,
double baseWeight,
ObservableSatellite satellite)
Constructor with two double for the standard deviations.
|
Range(GroundStation station,
boolean twoWay,
AbsoluteDate date,
double range,
double sigma,
double baseWeight,
ObservableSatellite satellite)
Simple constructor.
|
RangeRate(GroundStation station,
AbsoluteDate date,
double rangeRate,
double sigma,
double baseWeight,
boolean twoway,
ObservableSatellite satellite)
Simple constructor.
|
TurnAroundRange(GroundStation masterStation,
GroundStation slaveStation,
AbsoluteDate date,
double turnAroundRange,
double sigma,
double baseWeight,
ObservableSatellite satellite)
Simple constructor.
|
| Modifier and Type | Method and Description |
|---|---|
protected AbsoluteDate |
AbstractMeasurementBuilder.getEnd()
Get the end of the measurements time span.
|
protected AbsoluteDate |
AbstractMeasurementBuilder.getStart()
Get the start of the measurements time span.
|
| Modifier and Type | Method and Description |
|---|---|
SortedSet<ObservedMeasurement<?>> |
Generator.generate(AbsoluteDate start,
AbsoluteDate end)
Generate measurements.
|
void |
MeasurementBuilder.init(AbsoluteDate start,
AbsoluteDate end)
Initialize builder at the start of a measurements generation.
|
void |
AbstractMeasurementBuilder.init(AbsoluteDate start,
AbsoluteDate end)
Initialize builder at the start of a measurements generation.
|
void |
Scheduler.init(AbsoluteDate start,
AbsoluteDate end)
Initialize scheduler at the start of a measurements generation.
|
void |
AbstractScheduler.init(AbsoluteDate start,
AbsoluteDate end)
Initialize scheduler at the start of a measurements generation.
|
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
CycleSlipDetectorResults.getBeginDate(Frequency f)
Return the date of validity beginning of the detector.
|
AbsoluteDate |
CycleSlipDetectorResults.getEndDate(Frequency f)
Return the end date at the given frequency.
|
| Modifier and Type | Method and Description |
|---|---|
Map<Frequency,List<AbsoluteDate>> |
CycleSlipDetectorResults.getCycleSlipMap()
Get the cycle slip Map with contains the results.
|
| Modifier and Type | Method and Description |
|---|---|
protected void |
AbstractCycleSlipDetector.cycleSlipDataSet(String nameSat,
AbsoluteDate date,
double value,
Frequency freq)
Set the data: collect data at the current Date, at the current frequency, for a given satellite, add it within the attributes data and stuff.
|
| Constructor and Description |
|---|
Phase(GroundStation station,
AbsoluteDate date,
double phase,
double wavelength,
double sigma,
double baseWeight,
ObservableSatellite satellite)
Simple constructor.
|
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
KalmanEstimation.getCurrentDate()
Get the current date.
|
AbsoluteDate |
KalmanEstimator.getCurrentDate()
Get the current date.
|
AbsoluteDate |
DSSTKalmanModel.getCurrentDate()
Get the current date.
|
AbsoluteDate |
KalmanModel.getCurrentDate()
Get the current date.
|
| Constructor and Description |
|---|
MeasurementDecorator(ObservedMeasurement<?> observedMeasurement,
RealMatrix covariance,
AbsoluteDate reference)
Simple constructor.
|
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
NDMFile.getCreationDate()
Get the file creation date and time in UTC.
|
AbsoluteDate |
TDMFile.Observation.getEpoch()
Getter for the epoch.
|
AbsoluteDate |
OGMFile.getEpoch()
Get epoch of state vector, Keplerian elements and covariance matrix data.
|
AbsoluteDate |
OEMFile.CovarianceMatrix.getEpoch()
Get the epoch relative to the covariance matrix.
|
AbsoluteDate |
APMFile.getEpoch()
Get the epoch of the data.
|
AbsoluteDate |
OPMFile.Maneuver.getEpochIgnition()
Get epoch ignition.
|
AbsoluteDate |
APMFile.APMManeuver.getEpochStart()
Get epoch start.
|
AbsoluteDate |
ODMMetaData.getFrameEpoch()
Get epoch of reference frame, if not intrinsic to the definition of the
reference frame.
|
AbsoluteDate |
NDMFile.getMissionReferenceDate()
Get reference date for Mission Elapsed Time and Mission Relative Time time systems.
|
AbsoluteDate |
ODMParser.getMissionReferenceDate()
Get initial date.
|
AbsoluteDate |
TDMParser.getMissionReferenceDate()
Get initial date.
|
AbsoluteDate |
ADMParser.getMissionReferenceDate()
Get initial date.
|
AbsoluteDate |
OEMFile.EphemeridesBlock.getStart() |
AbsoluteDate |
OEMFile.OemSatelliteEphemeris.getStart() |
AbsoluteDate |
AEMFile.AttitudeEphemeridesBlock.getStart()
Get the start date of this attitude data segment.
|
AbsoluteDate |
AEMFile.AemSatelliteEphemeris.getStart()
Get the start date of the attitude ephemeris.
|
AbsoluteDate |
TDMFile.TDMMetaData.getStartTime()
Getter for the startTime.
|
AbsoluteDate |
OEMFile.EphemeridesBlock.getStartTime()
Get start of total time span covered by ephemerides data and
covariance data.
|
AbsoluteDate |
AEMFile.AttitudeEphemeridesBlock.getStartTime()
Get start of total time span covered by attitude data.
|
AbsoluteDate |
OEMFile.EphemeridesBlock.getStop() |
AbsoluteDate |
OEMFile.OemSatelliteEphemeris.getStop() |
AbsoluteDate |
AEMFile.AttitudeEphemeridesBlock.getStop()
Get the end date of this attitude data segment.
|
AbsoluteDate |
AEMFile.AemSatelliteEphemeris.getStop()
Get the end date of the attitude ephemeris.
|
AbsoluteDate |
TDMFile.TDMMetaData.getStopTime()
Getter for the stopTime.
|
AbsoluteDate |
OEMFile.EphemeridesBlock.getStopTime()
Get end of total time span covered by ephemerides data and covariance
data.
|
AbsoluteDate |
AEMFile.AttitudeEphemeridesBlock.getStopTime()
Get end of total time span covered by attitude data.
|
AbsoluteDate |
OEMFile.EphemeridesBlock.getUseableStartTime()
Get start of useable time span covered by ephemerides data, it may be
necessary to allow for proper interpolation.
|
AbsoluteDate |
AEMFile.AttitudeEphemeridesBlock.getUseableStartTime()
Get start of useable time span covered by attitude data.
|
AbsoluteDate |
OEMFile.EphemeridesBlock.getUseableStopTime()
Get end of useable time span covered by ephemerides data, it may be
necessary to allow for proper interpolation.
|
AbsoluteDate |
AEMFile.AttitudeEphemeridesBlock.getUseableStopTime()
Get end of useable time span covered by ephemerides data.
|
protected AbsoluteDate |
ODMParser.parseDate(String date,
CcsdsTimeScale timeSystem)
Parse a date.
|
protected AbsoluteDate |
ADMParser.parseDate(String date,
CcsdsTimeScale timeSystem)
Parse a date.
|
AbsoluteDate |
CcsdsTimeScale.parseDate(String date,
IERSConventions conventions,
AbsoluteDate missionReferenceDate)
Parse a date in this time scale.
|
AbsoluteDate |
CcsdsTimeScale.parseDate(String date,
IERSConventions conventions,
AbsoluteDate missionReferenceDate,
TimeScales timeScales)
Parse a date in this time scale.
|
| Modifier and Type | Method and Description |
|---|---|
void |
TDMFile.ObservationsBlock.addObservation(String keyword,
AbsoluteDate epoch,
double measurement)
Adds an observation data line.
|
abstract TimeStampedAngularCoordinates |
AEMAttitudeType.getAngularCoordinates(AbsoluteDate date,
double[] attitudeData,
boolean isFirst,
RotationOrder order)
Get the angular coordinates corresponding to the attitude data.
|
void |
StreamingAemWriter.AEMSegment.init(SpacecraftState s0,
AbsoluteDate t,
double step)
Initialize step handler at the start of a propagation.
|
void |
StreamingOemWriter.Segment.init(SpacecraftState s0,
AbsoluteDate t,
double step)
Initialize step handler at the start of a propagation.
|
AbsoluteDate |
CcsdsTimeScale.parseDate(String date,
IERSConventions conventions,
AbsoluteDate missionReferenceDate)
Parse a date in this time scale.
|
AbsoluteDate |
CcsdsTimeScale.parseDate(String date,
IERSConventions conventions,
AbsoluteDate missionReferenceDate,
TimeScales timeScales)
Parse a date in this time scale.
|
void |
NDMFile.setCreationDate(AbsoluteDate creationDate)
Set the file creation date and time in UTC.
|
void |
TDMFile.Observation.setEpoch(AbsoluteDate epoch)
Setter for the epoch.
|
void |
APMFile.setEpoch(AbsoluteDate epoch)
Set the epoch of the data.
|
void |
APMFile.APMManeuver.setEpochStart(AbsoluteDate epochStart)
Set epoch start.
|
void |
ODMMetaData.setFrameEpoch(AbsoluteDate frameEpoch)
Set epoch of reference frame, if not intrinsic to the definition of the
reference frame.
|
void |
NDMFile.setMissionReferenceDate(AbsoluteDate missionReferenceDate)
Set reference date for Mission Elapsed Time and Mission Relative Time time systems.
|
void |
TDMFile.TDMMetaData.setStartTime(AbsoluteDate startTime)
Setter for the startTime.
|
void |
OEMFile.EphemeridesBlock.setStartTime(AbsoluteDate startTime)
Set start of total time span covered by ephemerides data and
covariance data.
|
void |
AEMFile.AttitudeEphemeridesBlock.setStartTime(AbsoluteDate startTime)
Set start of total time span covered by attitude data.
|
void |
TDMFile.TDMMetaData.setStopTime(AbsoluteDate stopTime)
Setter for the stopTime.
|
void |
OEMFile.EphemeridesBlock.setStopTime(AbsoluteDate stopTime)
Set end of total time span covered by ephemerides data and covariance
data.
|
void |
AEMFile.AttitudeEphemeridesBlock.setStopTime(AbsoluteDate stopTime)
Set end of total time span covered by attitude data.
|
void |
OEMFile.EphemeridesBlock.setUseableStartTime(AbsoluteDate useableStartTime)
Set start of useable time span covered by ephemerides data, it may be
necessary to allow for proper interpolation.
|
void |
AEMFile.AttitudeEphemeridesBlock.setUseableStartTime(AbsoluteDate useableStartTime)
Set start of useable time span covered by attitude data.
|
void |
OEMFile.EphemeridesBlock.setUseableStopTime(AbsoluteDate useableStopTime)
Set end of useable time span covered by ephemerides data, it may be
necessary to allow for proper interpolation.
|
void |
AEMFile.AttitudeEphemeridesBlock.setUseableStopTime(AbsoluteDate useableStopTime)
Set end of useable time span covered by ephemerides data.
|
OPMParser |
OPMParser.withMissionReferenceDate(AbsoluteDate newMissionReferenceDate)
Set initial date.
|
abstract ODMParser |
ODMParser.withMissionReferenceDate(AbsoluteDate newMissionReferenceDate)
Set initial date.
|
OMMParser |
OMMParser.withMissionReferenceDate(AbsoluteDate newMissionReferenceDate)
Set initial date.
|
TDMParser |
TDMParser.withMissionReferenceDate(AbsoluteDate newMissionReferenceDate)
Set initial date.
|
OEMParser |
OEMParser.withMissionReferenceDate(AbsoluteDate newMissionReferenceDate)
Set initial date.
|
abstract ADMParser |
ADMParser.withMissionReferenceDate(AbsoluteDate newMissionReferenceDate)
Set initial date.
|
APMParser |
APMParser.withMissionReferenceDate(AbsoluteDate newMissionReferenceDate)
Set initial date.
|
AEMParser |
AEMParser.withMissionReferenceDate(AbsoluteDate newMissionReferenceDate)
Set initial date.
|
| Constructor and Description |
|---|
ADMParser(AbsoluteDate missionReferenceDate,
double mu,
IERSConventions conventions,
boolean simpleEOP,
int launchYear,
int launchNumber,
String launchPiece,
DataContext dataContext)
Complete constructor.
|
CovarianceMatrix(AbsoluteDate epoch,
LOFType lofType,
Frame frame,
RealMatrix lastMatrix)
Covariance Matrix constructor.
|
ODMParser(AbsoluteDate missionReferenceDate,
double mu,
IERSConventions conventions,
boolean simpleEOP,
int launchYear,
int launchNumber,
String launchPiece)
Deprecated.
|
ODMParser(AbsoluteDate missionReferenceDate,
double mu,
IERSConventions conventions,
boolean simpleEOP,
int launchYear,
int launchNumber,
String launchPiece,
DataContext dataContext)
Complete constructor.
|
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
EphemerisFile.SatelliteEphemeris.getStart()
Get the start date of the ephemeris.
|
AbsoluteDate |
EphemerisFile.EphemerisSegment.getStart()
Get the start date of this ephemeris segment.
|
AbsoluteDate |
OrekitEphemerisFile.OrekitSatelliteEphemeris.getStart() |
AbsoluteDate |
OrekitEphemerisFile.OrekitEphemerisSegment.getStart() |
AbsoluteDate |
EphemerisFile.SatelliteEphemeris.getStop()
Get the end date of the ephemeris.
|
AbsoluteDate |
EphemerisFile.EphemerisSegment.getStop()
Get the end date of this ephemeris segment.
|
AbsoluteDate |
OrekitEphemerisFile.OrekitSatelliteEphemeris.getStop() |
AbsoluteDate |
OrekitEphemerisFile.OrekitEphemerisSegment.getStop() |
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
SP3File.getEpoch()
Returns the start epoch of the orbit file.
|
AbsoluteDate |
SP3File.SP3Ephemeris.getStart() |
AbsoluteDate |
SP3File.SP3Ephemeris.getStop() |
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
BoxAndSolarArraySpacecraft.dragAcceleration(AbsoluteDate date,
Frame frame,
Vector3D position,
Rotation rotation,
double mass,
double density,
Vector3D relativeVelocity,
double[] parameters)
Compute the acceleration due to drag.
|
FieldVector3D<DerivativeStructure> |
BoxAndSolarArraySpacecraft.getNormal(AbsoluteDate date,
Frame frame,
FieldVector3D<DerivativeStructure> position,
FieldRotation<DerivativeStructure> rotation)
Deprecated.
Method not used anymore, should have been deleted in 9.0 but was left over. To be deleted in the next major version.
|
Vector3D |
BoxAndSolarArraySpacecraft.getNormal(AbsoluteDate date,
Frame frame,
Vector3D position,
Rotation rotation)
Get solar array normal in spacecraft frame.
|
default void |
ForceModel.init(SpacecraftState initialState,
AbsoluteDate target)
Initialize the force model at the start of propagation.
|
void |
HarmonicParametricAcceleration.init(SpacecraftState initialState,
AbsoluteDate target)
Initialize the force model at the start of propagation.
|
void |
PolynomialParametricAcceleration.init(SpacecraftState initialState,
AbsoluteDate target)
Initialize the force model at the start of propagation.
|
Vector3D |
BoxAndSolarArraySpacecraft.radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
Vector3D position,
Rotation rotation,
double mass,
Vector3D flux,
double[] parameters)
Compute the acceleration due to radiation pressure.
|
| Constructor and Description |
|---|
BoxAndSolarArraySpacecraft(BoxAndSolarArraySpacecraft.Facet[] facets,
PVCoordinatesProvider sun,
double solarArrayArea,
Vector3D solarArrayAxis,
AbsoluteDate referenceDate,
Vector3D referenceNormal,
double rotationRate,
double dragCoeff,
double absorptionCoeff,
double reflectionCoeff)
Build a spacecraft model with linear rotation of solar array.
|
BoxAndSolarArraySpacecraft(BoxAndSolarArraySpacecraft.Facet[] facets,
PVCoordinatesProvider sun,
double solarArrayArea,
Vector3D solarArrayAxis,
AbsoluteDate referenceDate,
Vector3D referenceNormal,
double rotationRate,
double dragCoeff,
double liftRatio,
double absorptionCoeff,
double reflectionCoeff)
Build a spacecraft model with linear rotation of solar array.
|
BoxAndSolarArraySpacecraft(double xLength,
double yLength,
double zLength,
PVCoordinatesProvider sun,
double solarArrayArea,
Vector3D solarArrayAxis,
AbsoluteDate referenceDate,
Vector3D referenceNormal,
double rotationRate,
double dragCoeff,
double absorptionCoeff,
double reflectionCoeff)
Build a spacecraft model with linear rotation of solar array.
|
BoxAndSolarArraySpacecraft(double xLength,
double yLength,
double zLength,
PVCoordinatesProvider sun,
double solarArrayArea,
Vector3D solarArrayAxis,
AbsoluteDate referenceDate,
Vector3D referenceNormal,
double rotationRate,
double dragCoeff,
double liftRatio,
double absorptionCoeff,
double reflectionCoeff)
Build a spacecraft model with linear rotation of solar array.
|
HarmonicParametricAcceleration(Vector3D direction,
AttitudeProvider attitudeOverride,
String prefix,
AbsoluteDate referenceDate,
double fundamentalPeriod,
int harmonicMultiplier)
Simple constructor.
|
HarmonicParametricAcceleration(Vector3D direction,
boolean isInertial,
String prefix,
AbsoluteDate referenceDate,
double fundamentalPeriod,
int harmonicMultiplier)
Simple constructor.
|
PolynomialParametricAcceleration(Vector3D direction,
AttitudeProvider attitudeOverride,
String prefix,
AbsoluteDate referenceDate,
int degree)
Simple constructor.
|
PolynomialParametricAcceleration(Vector3D direction,
boolean isInertial,
String prefix,
AbsoluteDate referenceDate,
int degree)
Simple constructor.
|
| Modifier and Type | Method and Description |
|---|---|
void |
TimeSpanDragForce.addDragSensitiveValidAfter(DragSensitive dragSensitive,
AbsoluteDate earliestValidityDate)
Add a DragSensitive entry valid after a limit date.
Using addDragSensitiveValidAfter(entry, t) will make entry
valid in [t, +∞[ (note the closed bracket). |
void |
TimeSpanDragForce.addDragSensitiveValidBefore(DragSensitive dragSensitive,
AbsoluteDate latestValidityDate)
Add a DragSensitive entry valid before a limit date.
Using addDragSensitiveValidBefore(entry, t) will make entry
valid in ]-∞, t[ (note the open bracket). |
Vector3D |
IsotropicDrag.dragAcceleration(AbsoluteDate date,
Frame frame,
Vector3D position,
Rotation rotation,
double mass,
double density,
Vector3D relativeVelocity,
double[] parameters)
Compute the acceleration due to drag.
|
Vector3D |
DragSensitive.dragAcceleration(AbsoluteDate date,
Frame frame,
Vector3D position,
Rotation rotation,
double mass,
double density,
Vector3D relativeVelocity,
double[] parameters)
Compute the acceleration due to drag.
|
TimeSpanMap<DragSensitive> |
TimeSpanDragForce.extractDragSensitiveRange(AbsoluteDate start,
AbsoluteDate end)
Extract a range of the
DragSensitive map. |
double[] |
TimeSpanDragForce.extractParameters(double[] parameters,
AbsoluteDate date)
Extract the proper parameter drivers' values from the array in input of the
acceleration method. |
DragSensitive |
TimeSpanDragForce.getDragSensitive(AbsoluteDate date)
Get the
DragSensitive model valid at a date. |
TimeSpanMap.Span<DragSensitive> |
TimeSpanDragForce.getDragSensitiveSpan(AbsoluteDate date)
Get the
DragSensitive TimeSpanMap.Span containing a specified date. |
protected DerivativeStructure |
AbstractDragForceModel.getDSDensityWrtStateUsingFiniteDifferences(AbsoluteDate date,
Frame frame,
FieldVector3D<DerivativeStructure> position)
Compute density and its derivatives.
|
protected Gradient |
AbstractDragForceModel.getGradientDensityWrtStateUsingFiniteDifferences(AbsoluteDate date,
Frame frame,
FieldVector3D<Gradient> position)
Compute density and its derivatives.
|
| Modifier and Type | Method and Description |
|---|---|
double[] |
HolmesFeatherstoneAttractionModel.gradient(AbsoluteDate date,
Vector3D position,
double mu)
Compute the gradient of the non-central part of the gravity field.
|
double |
HolmesFeatherstoneAttractionModel.nonCentralPart(AbsoluteDate date,
Vector3D position,
double mu)
Compute the non-central part of the gravity field.
|
double |
HolmesFeatherstoneAttractionModel.value(AbsoluteDate date,
Vector3D position,
double mu)
Compute the value of the gravity field.
|
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
CachedNormalizedSphericalHarmonicsProvider.getReferenceDate()
Get the reference date for the harmonics.
|
AbsoluteDate |
SphericalHarmonicsProvider.getReferenceDate()
Get the reference date for the harmonics.
|
protected AbsoluteDate |
PotentialCoefficientsReader.toDate(DateComponents components)
Create a date from components.
|
| Modifier and Type | Method and Description |
|---|---|
double |
CachedNormalizedSphericalHarmonicsProvider.getOffset(AbsoluteDate date)
Get the offset from
reference date for the harmonics. |
double |
SphericalHarmonicsProvider.getOffset(AbsoluteDate date)
Get the offset from
reference date for the harmonics. |
NormalizedSphericalHarmonicsProvider.NormalizedSphericalHarmonics |
CachedNormalizedSphericalHarmonicsProvider.onDate(AbsoluteDate date)
Get the normalized spherical harmonic coefficients at a specific instance in time.
|
NormalizedSphericalHarmonicsProvider.NormalizedSphericalHarmonics |
NormalizedSphericalHarmonicsProvider.onDate(AbsoluteDate date)
Get the normalized spherical harmonic coefficients at a specific instance in time.
|
UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics |
UnnormalizedSphericalHarmonicsProvider.onDate(AbsoluteDate date)
Get the un-normalized spherical harmonic coefficients at a specific instance in time.
|
RawSphericalHarmonicsProvider.RawSphericalHarmonics |
RawSphericalHarmonicsProvider.onDate(AbsoluteDate date)
Get the raw spherical harmonic coefficients on a specific date.
|
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
SmallManeuverAnalyticalModel.getDate()
Get the date of the maneuver.
|
AbsoluteDate |
ConstantThrustManeuver.getEndDate()
Get the end date.
|
AbsoluteDate |
ConstantThrustManeuver.getStartDate()
Get the start date.
|
| Modifier and Type | Method and Description |
|---|---|
void |
Maneuver.init(SpacecraftState initialState,
AbsoluteDate target)
Initialize the force model at the start of propagation.
|
void |
ImpulseManeuver.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
boolean |
ConstantThrustManeuver.isFiring(AbsoluteDate date)
Check if maneuvering is on.
|
| Constructor and Description |
|---|
ConstantThrustManeuver(AbsoluteDate date,
double duration,
AttitudeProvider attitudeOverride,
AbstractConstantThrustPropulsionModel constantThrustPropulsionModel)
Simple constructor for a constant direction and constant thrust.
|
ConstantThrustManeuver(AbsoluteDate date,
double duration,
double thrust,
double isp,
AttitudeProvider attitudeOverride,
Vector3D direction)
Simple constructor for a constant direction and constant thrust.
|
ConstantThrustManeuver(AbsoluteDate date,
double duration,
double thrust,
double isp,
AttitudeProvider attitudeOverride,
Vector3D direction,
String name)
Simple constructor for a constant direction and constant thrust.
|
ConstantThrustManeuver(AbsoluteDate date,
double duration,
double thrust,
double isp,
Vector3D direction)
Simple constructor for a constant direction and constant thrust.
|
ConstantThrustManeuver(AbsoluteDate date,
double duration,
double thrust,
double isp,
Vector3D direction,
String name)
Simple constructor for a constant direction and constant thrust.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
ThrustDirectionProvider.computeThrustDirection(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the thrust direction corresponding to an orbital state.
|
Vector3D |
ConstantThrustDirectionProvider.computeThrustDirection(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame) |
Attitude |
ThrustDirectionAndAttitudeProvider.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
protected Attitude |
ThrustDirectionAndAttitudeProvider.getAttitudeFromFrame(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude for DIRECTION_IN_FRAME or DIRECTION_IN_LOF types.
|
default void |
PropulsionModel.init(SpacecraftState initialState,
AbsoluteDate target)
Initialization method.
|
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
DateBasedManeuverTriggers.getEndDate()
Get the end date.
|
AbsoluteDate |
DateBasedManeuverTriggers.getStartDate()
Get the start date.
|
AbsoluteDate |
EventBasedManeuverTriggers.getTriggeredEnd()
Getter for the triggered date of engine stop.
|
AbsoluteDate |
EventBasedManeuverTriggers.getTriggeredStart()
Getter triggered date of engine start.
|
| Modifier and Type | Method and Description |
|---|---|
void |
DateBasedManeuverTriggers.init(SpacecraftState initialState,
AbsoluteDate target)
Initialization method.
|
void |
EventBasedManeuverTriggers.init(SpacecraftState initialState,
AbsoluteDate target)
Initialization method.
|
default void |
ManeuverTriggers.init(SpacecraftState initialState,
AbsoluteDate target)
Initialization method.
|
boolean |
DateBasedManeuverTriggers.isFiring(AbsoluteDate date)
Check if maneuvering is on.
|
boolean |
EventBasedManeuverTriggers.isFiring(AbsoluteDate date)
Check if maneuvering is on.
|
boolean |
DateBasedManeuverTriggers.isFiring(AbsoluteDate date,
double[] parameters)
Find out if the maneuver is firing or not.
|
boolean |
EventBasedManeuverTriggers.isFiring(AbsoluteDate date,
double[] parameters)
Find out if the maneuver is firing or not.
|
boolean |
ManeuverTriggers.isFiring(AbsoluteDate date,
double[] parameters)
Find out if the maneuver is firing or not.
|
void |
EventBasedManeuverTriggers.setFiring(boolean firing,
AbsoluteDate date)
Set the firing start or end date depending on the firing flag.
|
| Constructor and Description |
|---|
DateBasedManeuverTriggers(AbsoluteDate date,
double duration) |
| Modifier and Type | Method and Description |
|---|---|
double |
SolarRadiationPressure.getLightingRatio(Vector3D position,
Frame frame,
AbsoluteDate date)
Get the lighting ratio ([0-1]).
|
Vector3D |
RadiationSensitive.radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
Vector3D position,
Rotation rotation,
double mass,
Vector3D flux,
double[] parameters)
Compute the acceleration due to radiation pressure.
|
Vector3D |
IsotropicRadiationSingleCoefficient.radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
Vector3D position,
Rotation rotation,
double mass,
Vector3D flux,
double[] parameters)
Compute the acceleration due to radiation pressure.
|
Vector3D |
IsotropicRadiationCNES95Convention.radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
Vector3D position,
Rotation rotation,
double mass,
Vector3D flux,
double[] parameters)
Compute the acceleration due to radiation pressure.
|
Vector3D |
IsotropicRadiationClassicalConvention.radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
Vector3D position,
Rotation rotation,
double mass,
Vector3D flux,
double[] parameters)
Compute the acceleration due to radiation pressure.
|
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
EOPEntry.getDate()
Get the date.
|
AbsoluteDate |
FieldTransform.getDate()
Get the date.
|
AbsoluteDate |
Transform.getDate()
Get the date.
|
AbsoluteDate |
EOPHistory.getEndDate()
Get the date of the last available Earth Orientation Parameters.
|
AbsoluteDate |
HelmertTransformation.getEpoch()
Get the reference epoch of the transform.
|
AbsoluteDate |
EOPHistory.getStartDate()
Get the date of the first available Earth Orientation Parameters.
|
| Modifier and Type | Method and Description |
|---|---|
List<Transform> |
TransformGenerator.generate(AbsoluteDate existingDate,
AbsoluteDate date)
Generate a chronologically sorted list of entries to be cached.
|
List<FieldTransform<T>> |
FieldTransformGenerator.generate(AbsoluteDate existingDate,
AbsoluteDate date)
Generate a chronologically sorted list of entries to be cached.
|
double |
TopocentricFrame.getAzimuth(Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Get the azimuth of a point with regards to the topocentric frame center point.
|
double |
TopocentricFrame.getElevation(Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Get the elevation of a point with regards to the local point.
|
double[] |
EOPHistory.getEquinoxNutationCorrection(AbsoluteDate date)
Get the correction to the nutation parameters for equinox-based paradigm.
|
Frame |
Frame.getFrozenFrame(Frame reference,
AbsoluteDate freezingDate,
String frozenName)
Get a new version of the instance, frozen with respect to a reference frame.
|
ITRFVersion |
EOPHistory.getITRFVersion(AbsoluteDate date)
Get the ITRF version.
|
double |
EOPHistory.getLOD(AbsoluteDate date)
Get the LoD (Length of Day) value.
|
protected Stream<EOPEntry> |
EOPHistory.getNeighbors(AbsoluteDate central)
Get the entries surrounding a central date.
|
static Transform |
FramesFactory.getNonInterpolatingTransform(Frame from,
Frame to,
AbsoluteDate date)
Get the transform between two frames, suppressing all interpolation.
|
double[] |
EOPHistory.getNonRotatinOriginNutationCorrection(AbsoluteDate date)
Get the correction to the nutation parameters for Non-Rotating Origin paradigm.
|
PoleCorrection |
EOPHistory.getPoleCorrection(AbsoluteDate date)
Get the pole IERS Reference Pole correction.
|
TimeStampedPVCoordinates |
TopocentricFrame.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the topocentric frame origin in the selected frame. |
double |
TopocentricFrame.getRange(Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Get the range of a point with regards to the topocentric frame center point.
|
double |
TopocentricFrame.getRangeRate(PVCoordinates extPV,
Frame frame,
AbsoluteDate date)
Get the range rate of a point with regards to the topocentric frame center point.
|
Transform |
InterpolatingTransformProvider.getTransform(AbsoluteDate date)
Get the
Transform corresponding to specified date. |
Transform |
FixedTransformProvider.getTransform(AbsoluteDate date)
Get the
Transform corresponding to specified date. |
Transform |
L1TransformProvider.getTransform(AbsoluteDate date)
Get the
Transform corresponding to specified date. |
Transform |
GTODProvider.getTransform(AbsoluteDate date)
Get the
Transform corresponding to specified date. |
Transform |
TransformProvider.getTransform(AbsoluteDate date)
Get the
Transform corresponding to specified date. |
Transform |
ShiftingTransformProvider.getTransform(AbsoluteDate date)
Get the
Transform corresponding to specified date. |
Transform |
EclipticProvider.getTransform(AbsoluteDate date) |
Transform |
ITRFVersion.Converter.getTransform(AbsoluteDate date)
Get the
Transform corresponding to specified date. |
Transform |
HelmertTransformation.getTransform(AbsoluteDate date)
Get the
Transform corresponding to specified date. |
Transform |
Frame.getTransformTo(Frame destination,
AbsoluteDate date)
Get the transform from the instance to another frame.
|
double |
EOPHistory.getUT1MinusUTC(AbsoluteDate date)
Get the UT1-UTC value.
|
protected boolean |
EOPHistory.hasDataFor(AbsoluteDate date)
Check if the cache has data for the given date using
EOPHistory.getStartDate() and EOPHistory.getEndDate(). |
static Transform |
Transform.interpolate(AbsoluteDate date,
CartesianDerivativesFilter cFilter,
AngularDerivativesFilter aFilter,
Collection<Transform> sample)
Interpolate a transform from a sample set of existing transforms.
|
Transform |
Transform.interpolate(AbsoluteDate interpolationDate,
Stream<Transform> sample)
Get an interpolated instance.
|
Transform |
LOFType.transformFromInertial(AbsoluteDate date,
PVCoordinates pv)
Get the transform from an inertial frame defining position-velocity and the local orbital frame.
|
void |
UpdatableFrame.updateTransform(Frame f1,
Frame f2,
Transform f1Tof2,
AbsoluteDate date)
Update the transform from parent frame implicitly according to two other
frames.
|
| Constructor and Description |
|---|
EOPEntry(int mjd,
double dt,
double lod,
double x,
double y,
double ddPsi,
double ddEps,
double dx,
double dy,
ITRFVersion itrfType,
AbsoluteDate date)
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.
|
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,
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.
|
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.
|
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
GLONASSEphemeris.getDate() |
AbsoluteDate |
IRNSSAlmanac.getDate() |
AbsoluteDate |
DOP.getDate()
Gets the calculation date of the DOP.
|
AbsoluteDate |
QZSSAlmanac.getDate() |
AbsoluteDate |
GalileoAlmanac.getDate() |
AbsoluteDate |
ObservationDataSet.getDate()
Get the date.
|
AbsoluteDate |
GPSAlmanac.getDate() |
AbsoluteDate |
CombinedObservationDataSet.getDate()
Get the date.
|
AbsoluteDate |
BeidouAlmanac.getDate() |
AbsoluteDate |
GLONASSAlmanac.getDate() |
AbsoluteDate |
RinexHeader.getTFirstObs()
Get the time of First observation record.
|
AbsoluteDate |
RinexHeader.getTLastObs()
Get the time of last observation record.
|
| Modifier and Type | Method and Description |
|---|---|
DOP |
DOPComputer.compute(AbsoluteDate date,
List<Propagator> gnss)
Compute the
DOP at a given date for a set of GNSS spacecrafts. |
| Constructor and Description |
|---|
BeidouAlmanac(int prn,
int week,
double toa,
double sqa,
double ecc,
double inc0,
double dinc,
double om0,
double dom,
double aop,
double anom,
double af0,
double af1,
int health,
AbsoluteDate date)
Build a new almanac.
|
CombinedObservationDataSet(RinexHeader header,
SatelliteSystem satelliteSystem,
int prnNumber,
AbsoluteDate tObs,
double rcvrClkOffset,
List<CombinedObservationData> observationData)
Simple constructor.
|
DOP(GeodeticPoint location,
AbsoluteDate date,
int gnssNb,
double gdop,
double pdop,
double hdop,
double vdop,
double tdop)
Constructor.
|
GalileoAlmanac(int prn,
int week,
double toa,
double dsqa,
double ecc,
double dinc,
int iod,
double om0,
double dom,
double aop,
double anom,
double af0,
double af1,
int healthE5a,
int healthE5b,
int healthE1,
AbsoluteDate date)
Build a new almanac.
|
GLONASSEphemeris(int n4,
int nt,
double tb,
double x,
double xDot,
double xDotDot,
double y,
double yDot,
double yDotDot,
double z,
double zDot,
double zDotDot,
AbsoluteDate date)
Build a new instance.
|
GPSAlmanac(String source,
int prn,
int svn,
int week,
double toa,
double sqa,
double ecc,
double inc,
double om0,
double dom,
double aop,
double anom,
double af0,
double af1,
int health,
int ura,
int config,
AbsoluteDate date)
Constructor.
|
IRNSSAlmanac(int prn,
int week,
double toa,
double sqa,
double ecc,
double inc,
double om0,
double dom,
double aop,
double anom,
double af0,
double af1,
AbsoluteDate date)
Constructor.
|
ObservationDataSet(RinexHeader header,
SatelliteSystem satelliteSystem,
int prnNumber,
AbsoluteDate tObs,
double rcvrClkOffset,
List<ObservationData> observationData)
Simple constructor.
|
QZSSAlmanac(String source,
int prn,
int week,
double toa,
double sqa,
double ecc,
double inc,
double om0,
double dom,
double aop,
double anom,
double af0,
double af1,
int health,
AbsoluteDate date)
Constructor.
|
RinexHeader(double rinexVersion,
SatelliteSystem satelliteSystem,
String markerName,
String markerNumber,
String markerType,
String observerName,
String agencyName,
String receiverNumber,
String receiverType,
String receiverVersion,
String antennaNumber,
String antennaType,
Vector3D approxPos,
double antHeight,
Vector2D eccentricities,
Vector3D antRefPoint,
String obsCode,
Vector3D antPhaseCenter,
Vector3D antBSight,
double antAzi,
Vector3D antZeroDir,
Vector3D centerMass,
String sigStrengthUnit,
double interval,
AbsoluteDate tFirstObs,
AbsoluteDate tLastObs,
int clkOffset,
List<RinexLoader.Parser.AppliedDCBS> listAppliedDCBS,
List<RinexLoader.Parser.AppliedPCVS> listAppliedPCVS,
List<RinexLoader.Parser.PhaseShiftCorrection> phaseShiftCorrections,
int leapSeconds,
int leapSecondsFuture,
int leapSecondsWeekNum,
int leapSecondsDayNum)
Simple constructor, for Rinex 3 Header.
|
RinexHeader(double rinexVersion,
SatelliteSystem satelliteSystem,
String markerName,
String markerNumber,
String markerType,
String observerName,
String agencyName,
String receiverNumber,
String receiverType,
String receiverVersion,
String antennaNumber,
String antennaType,
Vector3D approxPos,
double antHeight,
Vector2D eccentricities,
Vector3D antRefPoint,
Vector3D antBSight,
Vector3D centerMass,
double interval,
AbsoluteDate tFirstObs,
AbsoluteDate tLastObs,
int clkOffset,
int leapSeconds)
Simple constructor, for Rinex 2 Header.
|
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
SatelliteAntenna.getValidFrom()
Get start of validity.
|
AbsoluteDate |
SatelliteAntenna.getValidUntil()
Get end of validity.
|
| Modifier and Type | Method and Description |
|---|---|
abstract GNSSAttitudeProvider |
SatelliteType.buildAttitudeProvider(AbsoluteDate validityStart,
AbsoluteDate validityEnd,
ExtendedPVCoordinatesProvider sun,
Frame inertialFrame,
int prnNumber)
Build an attitude provider suitable for this satellite type.
|
| Constructor and Description |
|---|
SatelliteAntenna(String type,
String sinexCode,
Map<Frequency,FrequencyPattern> patterns,
SatelliteSystem satelliteSystem,
int prnNumber,
SatelliteType satelliteType,
int satelliteCode,
String cosparID,
AbsoluteDate validFrom,
AbsoluteDate validUntil)
Simple constructor.
|
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
GNSSAttitudeProvider.validityEnd()
Get end of validity for this provider.
|
AbsoluteDate |
GNSSAttitudeProvider.validityStart()
Get start of validity for this provider.
|
| Constructor and Description |
|---|
BeidouGeo(AbsoluteDate validityStart,
AbsoluteDate validityEnd,
ExtendedPVCoordinatesProvider sun,
Frame inertialFrame)
Simple constructor.
|
BeidouIGSO(AbsoluteDate validityStart,
AbsoluteDate validityEnd,
ExtendedPVCoordinatesProvider sun,
Frame inertialFrame)
Simple constructor.
|
BeidouMeo(AbsoluteDate validityStart,
AbsoluteDate validityEnd,
ExtendedPVCoordinatesProvider sun,
Frame inertialFrame)
Simple constructor.
|
Galileo(double yawRate,
AbsoluteDate validityStart,
AbsoluteDate validityEnd,
ExtendedPVCoordinatesProvider sun,
Frame inertialFrame)
Simple constructor.
|
GenericGNSS(AbsoluteDate validityStart,
AbsoluteDate validityEnd,
ExtendedPVCoordinatesProvider sun,
Frame inertialFrame)
Simple constructor.
|
Glonass(double yawRate,
AbsoluteDate validityStart,
AbsoluteDate validityEnd,
ExtendedPVCoordinatesProvider sun,
Frame inertialFrame)
Simple constructor.
|
GPSBlockIIA(double yawRate,
double yawBias,
AbsoluteDate validityStart,
AbsoluteDate validityEnd,
ExtendedPVCoordinatesProvider sun,
Frame inertialFrame)
Simple constructor.
|
GPSBlockIIF(double yawRate,
double yawBias,
AbsoluteDate validityStart,
AbsoluteDate validityEnd,
ExtendedPVCoordinatesProvider sun,
Frame inertialFrame)
Simple constructor.
|
GPSBlockIIR(double yawRate,
AbsoluteDate validityStart,
AbsoluteDate validityEnd,
ExtendedPVCoordinatesProvider sun,
Frame inertialFrame)
Simple constructor.
|
| Modifier and Type | Method and Description |
|---|---|
GeodeticPoint |
Geoid.getIntersectionPoint(Line lineInFrame,
Vector3D closeInFrame,
Frame frame,
AbsoluteDate date)
Get the intersection point of a line with the surface of the body.
|
double |
Geoid.getUndulation(double geodeticLatitude,
double longitude,
AbsoluteDate date)
Gets the Undulation of the Geoid, N at the given position.
|
Vector3D |
Geoid.projectToGround(Vector3D point,
AbsoluteDate date,
Frame frame) |
GeodeticPoint |
Geoid.transform(Vector3D point,
Frame frame,
AbsoluteDate date)
Transform a Cartesian point to a surface-relative point.
|
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
NRLMSISE00InputParameters.getMaxDate()
Gets the available data range maximum date.
|
AbsoluteDate |
JB2008InputParameters.getMaxDate()
Gets the available data range maximum date.
|
AbsoluteDate |
DTM2000InputParameters.getMaxDate()
Gets the available data range maximum date.
|
AbsoluteDate |
NRLMSISE00InputParameters.getMinDate()
Gets the available data range minimum date.
|
AbsoluteDate |
JB2008InputParameters.getMinDate()
Gets the available data range minimum date.
|
AbsoluteDate |
DTM2000InputParameters.getMinDate()
Gets the available data range minimum date.
|
| Modifier and Type | Method and Description |
|---|---|
double |
DTM2000InputParameters.get24HoursKp(AbsoluteDate date)
Get the last 24H mean geomagnetic index.
|
double[] |
NRLMSISE00InputParameters.getAp(AbsoluteDate date)
Get the Ap geomagnetic indices.
|
double |
NRLMSISE00InputParameters.getAverageFlux(AbsoluteDate date)
Get the value of the 81 day average of F10.7 solar flux centered on current day.
|
double |
NRLMSISE00InputParameters.getDailyFlux(AbsoluteDate date)
Get the value of the daily F10.7 solar flux for previous day.
|
double |
DTM2000.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local density.
|
double |
NRLMSISE00.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local density.
|
double |
Atmosphere.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local density.
|
double |
HarrisPriester.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local density at some position.
|
double |
SimpleExponentialAtmosphere.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local density.
|
double |
JB2008.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local density.
|
double |
JB2008InputParameters.getDSTDTC(AbsoluteDate date)
Get the temperature change computed from Dst index.
|
double |
JB2008InputParameters.getF10(AbsoluteDate date)
Get the value of the instantaneous solar flux index
(1e-22*Watt/(m²*Hertz)).
|
double |
JB2008InputParameters.getF10B(AbsoluteDate date)
Get the value of the mean solar flux.
|
double |
DTM2000InputParameters.getInstantFlux(AbsoluteDate date)
Get the value of the instantaneous solar flux.
|
double |
DTM2000InputParameters.getMeanFlux(AbsoluteDate date)
Get the value of the mean solar flux.
|
double |
JB2008InputParameters.getS10(AbsoluteDate date)
Get the EUV index (26-34 nm) scaled to F10.
|
double |
JB2008InputParameters.getS10B(AbsoluteDate date)
Get the EUV 81-day averaged centered index.
|
double |
DTM2000InputParameters.getThreeHourlyKP(AbsoluteDate date)
Get the value of the 3 hours geomagnetic index.
|
default Vector3D |
Atmosphere.getVelocity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the inertial velocity of atmosphere molecules.
|
double |
JB2008InputParameters.getXM10(AbsoluteDate date)
Get the MG2 index scaled to F10.
|
double |
JB2008InputParameters.getXM10B(AbsoluteDate date)
Get the MG2 81-day average centered index.
|
double |
JB2008InputParameters.getY10(AbsoluteDate date)
Get the Solar X-Ray & Lya index scaled to F10.
|
double |
JB2008InputParameters.getY10B(AbsoluteDate date)
Get the Solar X-Ray & Lya 81-day ave.
|
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
CssiSpaceWeatherDataLoader.LineParameters.getDate() |
AbsoluteDate |
CssiSpaceWeatherDataLoader.getLastDailyPredictedDate()
Gets the day (at data start) of the last daily data entry.
|
AbsoluteDate |
CssiSpaceWeatherDataLoader.getLastObservedDate()
Gets the day (at data start) of the last observed data entry.
|
AbsoluteDate |
CssiSpaceWeatherDataLoader.getMaxDate()
Gets the available data range maximum date.
|
AbsoluteDate |
CssiSpaceWeatherData.getMaxDate()
Gets the available data range maximum date.
|
AbsoluteDate |
MarshallSolarActivityFutureEstimation.getMaxDate()
Gets the available data range maximum date.
|
AbsoluteDate |
CssiSpaceWeatherDataLoader.getMinDate()
Gets the available data range minimum date.
|
AbsoluteDate |
CssiSpaceWeatherData.getMinDate()
Gets the available data range minimum date.
|
AbsoluteDate |
MarshallSolarActivityFutureEstimation.getMinDate()
Gets the available data range minimum date.
|
| Modifier and Type | Method and Description |
|---|---|
double |
CssiSpaceWeatherData.get24HoursKp(AbsoluteDate date)
Get the last 24H mean geomagnetic index.
|
double |
MarshallSolarActivityFutureEstimation.get24HoursKp(AbsoluteDate date)
The Kp index is derived from the Ap index.
|
double[] |
CssiSpaceWeatherData.getAp(AbsoluteDate date)
Get the Ap geomagnetic indices.
|
double[] |
MarshallSolarActivityFutureEstimation.getAp(AbsoluteDate date)
Get the Ap geomagnetic indices.
|
double |
CssiSpaceWeatherData.getAverageFlux(AbsoluteDate date)
Get the value of the 81 day average of F10.7 solar flux centered on current day.
|
double |
MarshallSolarActivityFutureEstimation.getAverageFlux(AbsoluteDate date)
Get the value of the 81 day average of F10.7 solar flux centered on current day.
|
double |
CssiSpaceWeatherData.getDailyFlux(AbsoluteDate date)
Get the value of the daily F10.7 solar flux for previous day.
|
double |
MarshallSolarActivityFutureEstimation.getDailyFlux(AbsoluteDate date)
Get the value of the daily F10.7 solar flux for previous day.
|
DateComponents |
MarshallSolarActivityFutureEstimation.getFileDate(AbsoluteDate date)
Get the date of the file from which data at the specified date comes from.
|
double |
CssiSpaceWeatherData.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 |
CssiSpaceWeatherData.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 |
CssiSpaceWeatherData.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.
|
| Constructor and Description |
|---|
LineParameters(AbsoluteDate date,
double[] threeHourlyKp,
double kpSum,
double[] threeHourlyAp,
double apAvg,
double f107Adj,
int fluxQualifier,
double ctr81Adj,
double lst81Adj,
double f107Obs,
double ctr81Obs,
double lst81Obs)
Constructor.
|
| Modifier and Type | Method and Description |
|---|---|
double |
GlobalIonosphereMapModel.getTEC(AbsoluteDate date,
GeodeticPoint recPoint)
Computes the Total Electron Content (TEC) at a given date by performing a
temporal interpolation with the two closest date in the IONEX file.
|
double |
GlobalIonosphereMapModel.pathDelay(AbsoluteDate date,
GeodeticPoint geo,
double elevation,
double frequency)
Calculates the ionospheric path delay for the signal path from a ground
station to a satellite.
|
double |
KlobucharIonoModel.pathDelay(AbsoluteDate date,
GeodeticPoint geo,
double elevation,
double azimuth,
double frequency,
double[] parameters)
Calculates the ionospheric path delay for the signal path from a ground
station to a satellite.
|
double |
NeQuickModel.stec(AbsoluteDate date,
GeodeticPoint recP,
GeodeticPoint satP)
This method allows the computation of the Stant Total Electron Content (STEC).
|
| Modifier and Type | Method and Description |
|---|---|
void |
TimeSpanEstimatedTroposphericModel.addTroposphericModelValidAfter(EstimatedTroposphericModel model,
AbsoluteDate earliestValidityDate)
Add a EstimatedTroposphericModel entry valid after a limit date.
Using addTroposphericModelValidAfter(entry, t) will make entry
valid in [t, +∞[ (note the closed bracket). |
void |
TimeSpanEstimatedTroposphericModel.addTroposphericModelValidBefore(EstimatedTroposphericModel model,
AbsoluteDate latestValidityDate)
Add an EstimatedTroposphericModel entry valid before a limit date.
Using addTroposphericValidBefore(entry, t) will make entry
valid in ]-∞, t[ (note the open bracket). |
double[] |
ViennaOneModel.computeZenithDelay(double height,
double[] parameters,
AbsoluteDate date)
This method allows the computation of the zenith hydrostatic and
zenith wet delay.
|
double[] |
DiscreteTroposphericModel.computeZenithDelay(double height,
double[] parameters,
AbsoluteDate date)
This method allows the computation of the zenith hydrostatic and
zenith wet delay.
|
double[] |
FixedTroposphericDelay.computeZenithDelay(double height,
double[] parameters,
AbsoluteDate date) |
double[] |
MendesPavlisModel.computeZenithDelay(double height,
double[] parameters,
AbsoluteDate date)
This method allows the computation of the zenith hydrostatic and
zenith wet delay.
|
double[] |
MariniMurrayModel.computeZenithDelay(double height,
double[] parameters,
AbsoluteDate date) |
double[] |
SaastamoinenModel.computeZenithDelay(double height,
double[] parameters,
AbsoluteDate date) |
double[] |
ViennaThreeModel.computeZenithDelay(double height,
double[] parameters,
AbsoluteDate date)
This method allows the computation of the zenith hydrostatic and
zenith wet delay.
|
double[] |
EstimatedTroposphericModel.computeZenithDelay(double height,
double[] parameters,
AbsoluteDate date)
This method allows the computation of the zenith hydrostatic and zenith total delays.
|
double[] |
TimeSpanEstimatedTroposphericModel.computeZenithDelay(double height,
double[] parameters,
AbsoluteDate date)
This method allows the computation of the zenith hydrostatic and
zenith wet delay.
|
double[] |
TimeSpanEstimatedTroposphericModel.extractParameters(double[] parameters,
AbsoluteDate date)
Extract the proper parameter drivers' values from the array in input of the
pathDelay method. |
EstimatedTroposphericModel |
TimeSpanEstimatedTroposphericModel.getTroposphericModel(AbsoluteDate date)
Get the
EstimatedTroposphericModel model valid at a date. |
double[] |
ViennaOneModel.mappingFactors(double elevation,
double height,
double[] parameters,
AbsoluteDate date)
This method allows the computation of the hydrostatic and
wet mapping functions.
|
double[] |
GlobalMappingFunctionModel.mappingFactors(double elevation,
double height,
double[] parameters,
AbsoluteDate date)
This method allows the computation of the hydrostatic and
wet mapping functions.
|
double[] |
NiellMappingFunctionModel.mappingFactors(double elevation,
double height,
double[] parameters,
AbsoluteDate date) |
double[] |
MappingFunction.mappingFactors(double elevation,
double height,
double[] parameters,
AbsoluteDate date)
This method allows the computation of the hydrostatic and
wet mapping functions.
|
double[] |
FixedTroposphericDelay.mappingFactors(double elevation,
double height,
double[] parameters,
AbsoluteDate date) |
double[] |
MendesPavlisModel.mappingFactors(double elevation,
double height,
double[] parameters,
AbsoluteDate date)
With the Mendes Pavlis tropospheric model, the mapping
function is not split into hydrostatic and wet component.
|
double[] |
MariniMurrayModel.mappingFactors(double elevation,
double height,
double[] parameters,
AbsoluteDate date) |
double[] |
SaastamoinenModel.mappingFactors(double elevation,
double height,
double[] parameters,
AbsoluteDate date) |
double[] |
ViennaThreeModel.mappingFactors(double elevation,
double height,
double[] parameters,
AbsoluteDate date)
This method allows the computation of the hydrostatic and
wet mapping functions.
|
double[] |
EstimatedTroposphericModel.mappingFactors(double elevation,
double height,
double[] parameters,
AbsoluteDate date) |
double[] |
TimeSpanEstimatedTroposphericModel.mappingFactors(double elevation,
double height,
double[] parameters,
AbsoluteDate date)
This method allows the computation of the hydrostatic and
wet mapping functions.
|
double |
ViennaOneModel.pathDelay(double elevation,
double height,
double[] parameters,
AbsoluteDate date)
Calculates the tropospheric path delay for the signal path from a ground
station to a satellite.
|
double |
DiscreteTroposphericModel.pathDelay(double elevation,
double height,
double[] parameters,
AbsoluteDate date)
Calculates the tropospheric path delay for the signal path from a ground
station to a satellite.
|
double |
FixedTroposphericDelay.pathDelay(double elevation,
double height,
double[] parameters,
AbsoluteDate date)
Calculates the tropospheric path delay for the signal path from a ground
station to a satellite.
|
double |
MendesPavlisModel.pathDelay(double elevation,
double height,
double[] parameters,
AbsoluteDate date)
Calculates the tropospheric path delay for the signal path from a ground
station to a satellite.
|
double |
MariniMurrayModel.pathDelay(double elevation,
double height,
double[] parameters,
AbsoluteDate date) |
double |
SaastamoinenModel.pathDelay(double elevation,
double height,
double[] parameters,
AbsoluteDate date)
Calculates the tropospheric path delay for the signal path from a ground
station to a satellite.
|
double |
ViennaThreeModel.pathDelay(double elevation,
double height,
double[] parameters,
AbsoluteDate date)
Calculates the tropospheric path delay for the signal path from a ground
station to a satellite.
|
double |
EstimatedTroposphericModel.pathDelay(double elevation,
double height,
double[] parameters,
AbsoluteDate date) |
double |
TimeSpanEstimatedTroposphericModel.pathDelay(double elevation,
double height,
double[] parameters,
AbsoluteDate date)
Calculates the tropospheric path delay for the signal path from a ground
station to a satellite.
|
| Modifier and Type | Method and Description |
|---|---|
void |
GlobalPressureTemperatureModel.weatherParameters(double height,
AbsoluteDate date) |
void |
WeatherModel.weatherParameters(double stationHeight,
AbsoluteDate currentDate)
Calculates the weather parameters of the model.
|
void |
GlobalPressureTemperature2Model.weatherParameters(double stationHeight,
AbsoluteDate currentDate) |
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
Orbit.getDate()
Get the date of orbital parameters.
|
| Modifier and Type | Method and Description |
|---|---|
TimeStampedPVCoordinates |
Orbit.getPVCoordinates(AbsoluteDate otherDate,
Frame otherFrame)
Get the
PVCoordinates of the body in the selected frame. |
EquinoctialOrbit |
EquinoctialOrbit.interpolate(AbsoluteDate date,
Stream<Orbit> sample)
Get an interpolated instance.
|
KeplerianOrbit |
KeplerianOrbit.interpolate(AbsoluteDate date,
Stream<Orbit> sample)
Get an interpolated instance.
|
CircularOrbit |
CircularOrbit.interpolate(AbsoluteDate date,
Stream<Orbit> sample)
Get an interpolated instance.
|
CartesianOrbit |
CartesianOrbit.interpolate(AbsoluteDate date,
Stream<Orbit> sample)
Get an interpolated instance.
|
abstract Orbit |
OrbitType.mapArrayToOrbit(double[] array,
double[] arrayDot,
PositionAngle type,
AbsoluteDate date,
double mu,
Frame frame)
Convert state array to orbital parameters.
|
| Constructor and Description |
|---|
CartesianOrbit(PVCoordinates pvaCoordinates,
Frame frame,
AbsoluteDate date,
double mu)
Constructor from Cartesian parameters.
|
CircularOrbit(double a,
double ex,
double ey,
double i,
double raan,
double alpha,
double aDot,
double exDot,
double eyDot,
double iDot,
double raanDot,
double alphaDot,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance.
|
CircularOrbit(double a,
double ex,
double ey,
double i,
double raan,
double alpha,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance.
|
CircularOrbit(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,
double aDot,
double exDot,
double eyDot,
double hxDot,
double hyDot,
double lDot,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance.
|
EquinoctialOrbit(double a,
double ex,
double ey,
double hx,
double hy,
double l,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance.
|
EquinoctialOrbit(PVCoordinates pvCoordinates,
Frame frame,
AbsoluteDate date,
double mu)
Constructor from Cartesian parameters.
|
KeplerianOrbit(double a,
double e,
double i,
double pa,
double raan,
double anomaly,
double aDot,
double eDot,
double iDot,
double paDot,
double raanDot,
double anomalyDot,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance.
|
KeplerianOrbit(double a,
double e,
double i,
double pa,
double raan,
double anomaly,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance.
|
KeplerianOrbit(PVCoordinates pvCoordinates,
Frame frame,
AbsoluteDate date,
double mu)
Constructor from Cartesian parameters.
|
Orbit(Frame frame,
AbsoluteDate date,
double mu)
Default constructor.
|
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
SpacecraftState.getDate()
Get the date.
|
AbsoluteDate |
BoundedPropagator.getMaxDate()
Get the last date of the range.
|
AbsoluteDate |
BoundedPropagator.getMinDate()
Get the first date of the range.
|
protected AbsoluteDate |
AbstractPropagator.getStartDate()
Get the start date.
|
| Modifier and Type | Method and Description |
|---|---|
TimeStampedPVCoordinates |
AbstractPropagator.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
SpacecraftState |
SpacecraftState.interpolate(AbsoluteDate date,
Stream<SpacecraftState> sample)
Get an interpolated instance.
|
SpacecraftState |
Propagator.propagate(AbsoluteDate target)
Propagate towards a target date.
|
SpacecraftState |
AbstractPropagator.propagate(AbsoluteDate target)
Propagate towards a target date.
|
SpacecraftState |
Propagator.propagate(AbsoluteDate start,
AbsoluteDate target)
Propagate from a start date towards a target date.
|
List<SpacecraftState> |
PropagatorsParallelizer.propagate(AbsoluteDate start,
AbsoluteDate target)
Propagate from a start date towards a target date.
|
protected void |
AbstractPropagator.setStartDate(AbsoluteDate startDate)
Set a start date.
|
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
AggregateBoundedPropagator.getMaxDate() |
AbsoluteDate |
Ephemeris.getMaxDate()
Get the last date of the range.
|
AbsoluteDate |
AggregateBoundedPropagator.getMinDate() |
AbsoluteDate |
Ephemeris.getMinDate()
Get the first date of the range.
|
| Modifier and Type | Method and Description |
|---|---|
protected SpacecraftState |
AbstractAnalyticalPropagator.acceptStep(OrekitStepInterpolator interpolator,
AbsoluteDate target,
double epsilon)
Accept a step, triggering events and step handlers.
|
protected SpacecraftState |
AggregateBoundedPropagator.basicPropagate(AbsoluteDate date) |
SpacecraftState |
Ephemeris.basicPropagate(AbsoluteDate date) |
protected SpacecraftState |
AbstractAnalyticalPropagator.basicPropagate(AbsoluteDate date)
Propagate an orbit without any fancy features.
|
protected SpacecraftState |
AdapterPropagator.basicPropagate(AbsoluteDate date)
Propagate an orbit without any fancy features.
|
protected double |
KeplerianPropagator.getMass(AbsoluteDate date)
Get the mass.
|
protected double |
AggregateBoundedPropagator.getMass(AbsoluteDate date) |
protected double |
EcksteinHechlerPropagator.getMass(AbsoluteDate date)
Get the mass.
|
protected double |
Ephemeris.getMass(AbsoluteDate date)
Get the mass.
|
protected abstract double |
AbstractAnalyticalPropagator.getMass(AbsoluteDate date)
Get the mass.
|
protected double |
AdapterPropagator.getMass(AbsoluteDate date)
Get the mass.
|
TimeStampedPVCoordinates |
AggregateBoundedPropagator.getPVCoordinates(AbsoluteDate date,
Frame frame) |
TimeStampedPVCoordinates |
Ephemeris.getPVCoordinates(AbsoluteDate date,
Frame f)
Get the
PVCoordinates of the body in the selected frame. |
SpacecraftState |
AbstractAnalyticalPropagator.propagate(AbsoluteDate start,
AbsoluteDate target)
Propagate from a start date towards a target date.
|
protected Orbit |
KeplerianPropagator.propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date.
|
protected Orbit |
AggregateBoundedPropagator.propagateOrbit(AbsoluteDate date) |
CartesianOrbit |
EcksteinHechlerPropagator.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 abstract Orbit |
AbstractAnalyticalPropagator.propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date.
|
protected Orbit |
AdapterPropagator.propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date.
|
| Modifier and Type | Method and Description |
|---|---|
protected double |
SBASPropagator.getMass(AbsoluteDate date)
Get the mass.
|
protected double |
GLONASSAnalyticalPropagator.getMass(AbsoluteDate date)
Get the mass.
|
protected double |
AbstractGNSSPropagator.getMass(AbsoluteDate date)
Get the mass.
|
PVCoordinates |
SBASPropagator.propagateInEcef(AbsoluteDate date)
Gets the PVCoordinates of the GNSS SV in
ECEF frame. |
PVCoordinates |
GLONASSAnalyticalPropagator.propagateInEcef(AbsoluteDate date)
Gets the PVCoordinates of the GLONASS SV in
ECEF frame. |
PVCoordinates |
AbstractGNSSPropagator.propagateInEcef(AbsoluteDate date)
Gets the PVCoordinates of the GNSS SV in
ECEF frame. |
protected Orbit |
SBASPropagator.propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date.
|
protected Orbit |
GLONASSAnalyticalPropagator.propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date.
|
protected Orbit |
AbstractGNSSPropagator.propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date.
|
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
TLE.getDate()
Get the TLE current date.
|
| Modifier and Type | Method and Description |
|---|---|
protected double |
TLEPropagator.getMass(AbsoluteDate date)
Get the mass.
|
PVCoordinates |
TLEPropagator.getPVCoordinates(AbsoluteDate date)
Get the extrapolated position and velocity from an initial TLE.
|
protected Orbit |
TLEPropagator.propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date.
|
| Constructor and Description |
|---|
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.
|
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,
TimeScale utc)
Simple constructor from already parsed elements using the given time scale as
UTC.
|
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
AbstractPropagatorBuilder.getInitialOrbitDate()
Get the date of the initial orbit.
|
AbsoluteDate |
PropagatorBuilder.getInitialOrbitDate()
Get the date of the initial orbit.
|
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
DateDetector.getDate()
Get the current event date according to the propagator.
|
AbsoluteDate |
EventState.getEventDate()
Get the occurrence time of the event triggered in the current
step.
|
AbsoluteDate |
EventState.EventOccurrence.getStopDate()
Get the new time for a stop action.
|
| Modifier and Type | Method and Description |
|---|---|
void |
DateDetector.addEventDate(AbsoluteDate target)
Add an event date.
|
void |
NegateDetector.init(SpacecraftState s0,
AbsoluteDate t) |
void |
AdapterDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
EventEnablingPredicateFilter.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
EventState.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
BooleanDetector.init(SpacecraftState s0,
AbsoluteDate t) |
void |
MagneticFieldDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
EventShifter.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
AbstractDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
EventSlopeFilter.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
PositionAngleDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
default void |
EventDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
| Constructor and Description |
|---|
DateDetector(AbsoluteDate target)
Build a new instance.
|
| Modifier and Type | Method and Description |
|---|---|
default void |
EventHandler.init(SpacecraftState initialState,
AbsoluteDate target)
Initialize event handler at the start of a propagation.
|
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
IntegratedEphemeris.getMaxDate()
Get the last date of the range.
|
AbsoluteDate |
IntegratedEphemeris.getMinDate()
Get the first date of the range.
|
AbsoluteDate |
StateMapper.getReferenceDate()
Get reference date.
|
AbsoluteDate |
StateMapper.mapDoubleToDate(double t)
Map the raw double time offset to a date.
|
AbsoluteDate |
StateMapper.mapDoubleToDate(double t,
AbsoluteDate date)
Map the raw double time offset to a date.
|
| Modifier and Type | Method and Description |
|---|---|
protected SpacecraftState |
IntegratedEphemeris.basicPropagate(AbsoluteDate date)
Propagate an orbit without any fancy features.
|
protected void |
AbstractIntegratedPropagator.beforeIntegration(SpacecraftState initialState,
AbsoluteDate tEnd)
Method called just before integration.
|
protected abstract StateMapper |
AbstractIntegratedPropagator.createMapper(AbsoluteDate referenceDate,
double mu,
OrbitType orbitType,
PositionAngle positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame)
Create a mapper between raw double components and spacecraft state.
|
protected double |
IntegratedEphemeris.getMass(AbsoluteDate date)
Get the mass.
|
TimeStampedPVCoordinates |
IntegratedEphemeris.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
default void |
AbstractIntegratedPropagator.MainStateEquations.init(SpacecraftState initialState,
AbsoluteDate target)
Initialize the equations at the start of propagation.
|
default void |
AdditionalEquations.init(SpacecraftState initialState,
AbsoluteDate target)
Initialize the equations at the start of propagation.
|
void |
ModeHandler.initialize(boolean activateHandlers,
AbsoluteDate targetDate)
Initialize the mode handler.
|
abstract SpacecraftState |
StateMapper.mapArrayToState(AbsoluteDate date,
double[] y,
double[] yDot,
PropagationType type)
Map the raw double components to a spacecraft state.
|
double |
StateMapper.mapDateToDouble(AbsoluteDate date)
Map a date to a raw double time offset.
|
AbsoluteDate |
StateMapper.mapDoubleToDate(double t,
AbsoluteDate date)
Map the raw double time offset to a date.
|
SpacecraftState |
AbstractIntegratedPropagator.propagate(AbsoluteDate target)
Propagate towards a target date.
|
SpacecraftState |
AbstractIntegratedPropagator.propagate(AbsoluteDate tStart,
AbsoluteDate tEnd)
Propagate from a start date towards a target date.
|
protected SpacecraftState |
AbstractIntegratedPropagator.propagate(AbsoluteDate tEnd,
boolean activateHandlers)
Propagation with or without event detection.
|
protected Orbit |
IntegratedEphemeris.propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date.
|
| Constructor and Description |
|---|
IntegratedEphemeris(AbsoluteDate startDate,
AbsoluteDate minDate,
AbsoluteDate maxDate,
StateMapper mapper,
PropagationType type,
DenseOutputModel model,
Map<String,double[]> unmanaged,
List<AdditionalStateProvider> providers,
String[] equations)
Creates a new instance of IntegratedEphemeris.
|
StateMapper(AbsoluteDate referenceDate,
double mu,
OrbitType orbitType,
PositionAngle positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame)
Simple constructor.
|
| Modifier and Type | Method and Description |
|---|---|
protected void |
NumericalPropagator.beforeIntegration(SpacecraftState initialState,
AbsoluteDate tEnd)
Method called just before integration.
|
protected StateMapper |
NumericalPropagator.createMapper(AbsoluteDate referenceDate,
double mu,
OrbitType orbitType,
PositionAngle positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame)
Create a mapper between raw double components and spacecraft state.
|
protected StateMapper |
GLONASSNumericalPropagator.createMapper(AbsoluteDate referenceDate,
double mu,
OrbitType orbitType,
PositionAngle positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame) |
TimeStampedPVCoordinates |
NumericalPropagator.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
SpacecraftState |
GLONASSNumericalPropagator.propagate(AbsoluteDate date)
Propagate towards a target date.
|
| Modifier and Type | Method and Description |
|---|---|
SpacecraftState |
OrekitStepInterpolator.getInterpolatedState(AbsoluteDate date)
Get the state at interpolated date.
|
default void |
MultiSatStepHandler.init(List<SpacecraftState> states0,
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.
|
default void |
OrekitStepHandler.init(SpacecraftState s0,
AbsoluteDate t)
Initialize step handler at the start of a propagation.
|
void |
OrekitFixedStepHandlerMultiplexer.init(SpacecraftState s0,
AbsoluteDate t,
double step)
Initialize step handler at the start of a propagation.
|
default void |
OrekitFixedStepHandler.init(SpacecraftState s0,
AbsoluteDate t,
double step)
Initialize step handler at the start of a propagation.
|
| Modifier and Type | Method and Description |
|---|---|
protected void |
DSSTPropagator.beforeIntegration(SpacecraftState initialState,
AbsoluteDate tEnd)
Method called just before integration.
|
protected StateMapper |
DSSTPropagator.createMapper(AbsoluteDate referenceDate,
double mu,
OrbitType ignoredOrbitType,
PositionAngle ignoredPositionAngleType,
AttitudeProvider attitudeProvider,
Frame frame)
Create a mapper between raw double components and spacecraft state.
|
| Modifier and Type | Method and Description |
|---|---|
Map<String,double[]> |
ShortPeriodTerms.getCoefficients(AbsoluteDate date,
Set<String> selected)
Computes the coefficients involved in the contributions.
|
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
AuxiliaryElements.getDate()
Get the date of the orbit.
|
| Modifier and Type | Method and Description |
|---|---|
void |
ShortPeriodicsInterpolatedCoefficient.addGridPoint(AbsoluteDate date,
double[] value)
Add a point to the interpolation grid.
|
double[] |
ShortPeriodicsInterpolatedCoefficient.value(AbsoluteDate date)
Compute the value of the coefficient.
|
| Modifier and Type | Field and Description |
|---|---|
static AbsoluteDate |
AbsoluteDate.ARBITRARY_EPOCH
An arbitrary finite date.
|
static AbsoluteDate |
AbsoluteDate.BEIDOU_EPOCH
Reference epoch for BeiDou weeks: 2006-01-01T00:00:00 UTC.
|
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
Reference epoch for 1950 dates: 1950-01-01T00:00:00 Terrestrial Time.
|
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 GST.
|
static AbsoluteDate |
AbsoluteDate.GLONASS_EPOCH
Reference epoch for GLONASS four-year interval number: 1996-01-01T00:00:00 GLONASS time.
|
static AbsoluteDate |
AbsoluteDate.GPS_EPOCH
Reference epoch for GPS weeks: 1980-01-06T00:00:00 GPS time.
|
static AbsoluteDate |
AbsoluteDate.IRNSS_EPOCH
Reference epoch for IRNSS weeks: 1999-08-22T00:00:00 IRNSS 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.
|
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.
|
static AbsoluteDate |
AbsoluteDate.QZSS_EPOCH
Reference epoch for QZSS weeks: 1980-01-06T00:00:00 QZSS time.
|
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
TimeScales.createBesselianEpoch(double besselianEpoch)
Build an instance corresponding to a Besselian Epoch (BE).
|
static AbsoluteDate |
AbsoluteDate.createBesselianEpoch(double besselianEpoch)
Build an instance corresponding to a Besselian Epoch (BE).
|
AbsoluteDate |
AbstractTimeScales.createBesselianEpoch(double besselianEpoch) |
static AbsoluteDate |
AbsoluteDate.createJDDate(int jd,
double secondsSinceNoon,
TimeScale timeScale)
Build an instance corresponding to a Julian Day date.
|
AbsoluteDate |
TimeScales.createJulianEpoch(double julianEpoch)
Build an instance corresponding to a Julian Epoch (JE).
|
static AbsoluteDate |
AbsoluteDate.createJulianEpoch(double julianEpoch)
Build an instance corresponding to a Julian Epoch (JE).
|
AbsoluteDate |
AbstractTimeScales.createJulianEpoch(double julianEpoch) |
static AbsoluteDate |
AbsoluteDate.createMJDDate(int mjd,
double secondsInDay,
TimeScale timeScale)
Build an instance corresponding to a Modified Julian Day date.
|
AbsoluteDate |
TimeScales.getBeidouEpoch()
Reference epoch for BeiDou weeks: 2006-01-01T00:00:00 UTC.
|
AbsoluteDate |
AbstractTimeScales.getBeidouEpoch() |
AbsoluteDate |
TimeScales.getCcsdsEpoch()
Reference epoch for CCSDS Time Code Format (CCSDS 301.0-B-4): 1958-01-01T00:00:00
International Atomic Time (not UTC).
|
AbsoluteDate |
AbstractTimeScales.getCcsdsEpoch() |
AbsoluteDate |
GLONASSDate.getDate() |
AbsoluteDate |
TimeStamped.getDate()
Get the date.
|
AbsoluteDate |
GNSSDate.getDate()
Get the date.
|
AbsoluteDate |
AbsoluteDate.getDate()
Get the date.
|
AbsoluteDate |
TimeScales.getFiftiesEpoch()
Reference epoch for 1950 dates: 1950-01-01T00:00:00 Terrestrial Time.
|
AbsoluteDate |
AbstractTimeScales.getFiftiesEpoch() |
AbsoluteDate |
UTCScale.getFirstKnownLeapSecond()
Get the date of the first known leap second.
|
AbsoluteDate |
TimeScales.getFutureInfinity()
Dummy date at infinity in the future direction.
|
AbsoluteDate |
AbstractTimeScales.getFutureInfinity() |
AbsoluteDate |
TimeScales.getGalileoEpoch()
Reference epoch for Galileo System Time: 1999-08-22T00:00:00 GST.
|
AbsoluteDate |
AbstractTimeScales.getGalileoEpoch() |
AbsoluteDate |
TimeScales.getGlonassEpoch()
Reference epoch for GLONASS four-year interval number: 1996-01-01T00:00:00 GLONASS
time.
|
AbsoluteDate |
AbstractTimeScales.getGlonassEpoch() |
AbsoluteDate |
TimeScales.getGpsEpoch()
Reference epoch for GPS weeks: 1980-01-06T00:00:00 GPS time.
|
AbsoluteDate |
AbstractTimeScales.getGpsEpoch() |
AbsoluteDate |
TimeScales.getIrnssEpoch()
Reference epoch for IRNSS weeks: 1999-08-22T00:00:00 IRNSS time.
|
AbsoluteDate |
AbstractTimeScales.getIrnssEpoch() |
AbsoluteDate |
TimeScales.getJ2000Epoch()
J2000.0 Reference epoch: 2000-01-01T12:00:00 Terrestrial Time (not UTC).
|
AbsoluteDate |
AbstractTimeScales.getJ2000Epoch() |
AbsoluteDate |
TimeScales.getJavaEpoch()
Java Reference epoch: 1970-01-01T00:00:00 Universal Time Coordinate.
|
AbsoluteDate |
AbstractTimeScales.getJavaEpoch() |
AbsoluteDate |
TimeScales.getJulianEpoch()
Reference epoch for julian dates: -4712-01-01T12:00:00 Terrestrial Time.
|
AbsoluteDate |
AbstractTimeScales.getJulianEpoch() |
AbsoluteDate |
UTCScale.getLastKnownLeapSecond()
Get the date of the last known leap second.
|
AbsoluteDate |
TimeScales.getModifiedJulianEpoch()
Reference epoch for modified julian dates: 1858-11-17T00:00:00 Terrestrial Time.
|
AbsoluteDate |
AbstractTimeScales.getModifiedJulianEpoch() |
AbsoluteDate |
TimeScales.getPastInfinity()
Dummy date at infinity in the past direction.
|
AbsoluteDate |
AbstractTimeScales.getPastInfinity() |
AbsoluteDate |
TimeScales.getQzssEpoch()
Reference epoch for QZSS weeks: 1980-01-06T00:00:00 QZSS time.
|
AbsoluteDate |
AbstractTimeScales.getQzssEpoch() |
static AbsoluteDate |
AbsoluteDate.parseCCSDSCalendarSegmentedTimeCode(byte preambleField,
byte[] timeField)
Build an instance from a CCSDS Calendar Segmented Time Code (CCS).
|
static AbsoluteDate |
AbsoluteDate.parseCCSDSCalendarSegmentedTimeCode(byte preambleField,
byte[] timeField,
TimeScale utc)
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.parseCCSDSDaySegmentedTimeCode(byte preambleField,
byte[] timeField,
DateComponents agencyDefinedEpoch,
TimeScale utc)
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).
|
static AbsoluteDate |
AbsoluteDate.parseCCSDSUnsegmentedTimeCode(byte preambleField1,
byte preambleField2,
byte[] timeField,
AbsoluteDate agencyDefinedEpoch,
AbsoluteDate ccsdsEpoch)
Build an instance from a CCSDS Unsegmented Time Code (CUC).
|
AbsoluteDate |
AbsoluteDate.shiftedBy(double dt)
Get a time-shifted date.
|
AbsoluteDate |
FieldAbsoluteDate.toAbsoluteDate()
Transform the FieldAbsoluteDate in an AbsoluteDate.
|
| Modifier and Type | Method and Description |
|---|---|
List<AbsoluteDate> |
BurstSelector.selectDates(AbsoluteDate start,
AbsoluteDate end)
Select dates within an interval.
|
List<AbsoluteDate> |
FixedStepSelector.selectDates(AbsoluteDate start,
AbsoluteDate end)
Select dates within an interval.
|
List<AbsoluteDate> |
DatesSelector.selectDates(AbsoluteDate start,
AbsoluteDate end)
Select dates within an interval.
|
| Modifier and Type | Method and Description |
|---|---|
int |
AbsoluteDate.compareTo(AbsoluteDate date)
Compare the instance with another date.
|
T |
FieldAbsoluteDate.durationFrom(AbsoluteDate instant)
Compute the physically elapsed duration between two instants.
|
double |
AbsoluteDate.durationFrom(AbsoluteDate instant)
Compute the physically elapsed duration between two instants.
|
double |
GLONASSScale.getLeap(AbsoluteDate date)
Get the value of the previous leap.
|
default double |
TimeScale.getLeap(AbsoluteDate date)
Get the value of the previous leap.
|
double |
UTCScale.getLeap(AbsoluteDate date)
Get the value of the previous leap.
|
boolean |
GLONASSScale.insideLeap(AbsoluteDate date)
Check if date is within a leap second introduction in this time scale.
|
default boolean |
TimeScale.insideLeap(AbsoluteDate date)
Check if date is within a leap second introduction in this time scale.
|
boolean |
UTCScale.insideLeap(AbsoluteDate date)
Check if date is within a leap second introduction in this time scale.
|
default T |
TimeInterpolable.interpolate(AbsoluteDate date,
Collection<T> sample)
Get an interpolated instance.
|
T |
TimeInterpolable.interpolate(AbsoluteDate date,
Stream<T> sample)
Get an interpolated instance.
|
int |
GLONASSScale.minuteDuration(AbsoluteDate date)
Check length of the current minute in this time scale.
|
default int |
TimeScale.minuteDuration(AbsoluteDate date)
Check length of the current minute in this time scale.
|
int |
UTCScale.minuteDuration(AbsoluteDate date)
Check length of the current minute in this time scale.
|
double |
AbsoluteDate.offsetFrom(AbsoluteDate instant,
TimeScale timeScale)
Compute the apparent clock offset between two instant in the
perspective of a specific
time scale. |
double |
GLONASSScale.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. |
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 |
GalileoScale.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 |
QZSSScale.offsetFromTAI(AbsoluteDate date)
Get the offset to convert locations from
TAIScale to instance. |
double |
IRNSSScale.offsetFromTAI(AbsoluteDate date)
Get the offset to convert locations from
TAIScale to instance. |
double |
UTCScale.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 |
TTScale.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 |
TCBScale.offsetFromTAI(AbsoluteDate date)
Get the offset to convert locations from
TAIScale to instance. |
double |
BDTScale.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. |
static AbsoluteDate |
AbsoluteDate.parseCCSDSUnsegmentedTimeCode(byte preambleField1,
byte preambleField2,
byte[] timeField,
AbsoluteDate agencyDefinedEpoch)
Build an instance from a CCSDS Unsegmented Time Code (CUC).
|
static AbsoluteDate |
AbsoluteDate.parseCCSDSUnsegmentedTimeCode(byte preambleField1,
byte preambleField2,
byte[] timeField,
AbsoluteDate agencyDefinedEpoch,
AbsoluteDate ccsdsEpoch)
Build an instance from a CCSDS Unsegmented Time Code (CUC).
|
List<AbsoluteDate> |
BurstSelector.selectDates(AbsoluteDate start,
AbsoluteDate end)
Select dates within an interval.
|
List<AbsoluteDate> |
FixedStepSelector.selectDates(AbsoluteDate start,
AbsoluteDate end)
Select dates within an interval.
|
List<AbsoluteDate> |
DatesSelector.selectDates(AbsoluteDate start,
AbsoluteDate end)
Select dates within an interval.
|
double |
TimeScalarFunction.value(AbsoluteDate date)
Compute a function of time.
|
double[] |
TimeVectorFunction.value(AbsoluteDate date)
Compute a function of time.
|
| Constructor and Description |
|---|
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. |
FieldAbsoluteDate(AbsoluteDate since,
T elapsedDuration)
Build an instance from an elapsed duration since to another instant.
|
FieldAbsoluteDate(Field<T> field,
AbsoluteDate date)
Build an instance from an AbsoluteDate.
|
GLONASSDate(AbsoluteDate date)
Build an instance from an absolute date.
|
GLONASSDate(AbsoluteDate date,
TimeScale glonass)
Build an instance from an absolute date.
|
GNSSDate(AbsoluteDate date,
SatelliteSystem system)
Build an instance from an absolute date.
|
GNSSDate(AbsoluteDate date,
SatelliteSystem system,
TimeScales timeScales)
Build an instance from an absolute date.
|
| Modifier and Type | Method and Description |
|---|---|
AbsoluteDate |
FieldTimeSpanMap.Transition.getDate()
Get the transition absolute date.
|
AbsoluteDate |
TimeStampedAngularCoordinates.getDate()
Get the date.
|
AbsoluteDate |
TimeSpanMap.Transition.getDate()
Get the transition date.
|
AbsoluteDate |
TimeStampedPVCoordinates.getDate()
Get the date.
|
AbsoluteDate |
TimeSpanMap.Span.getEnd()
Get the end of this time span.
|
AbsoluteDate |
IERSConventions.getNutationReferenceEpoch()
Get the reference epoch for fundamental nutation arguments.
|
AbsoluteDate |
IERSConventions.getNutationReferenceEpoch(TimeScales timeScales)
Get the reference epoch for fundamental nutation arguments.
|
AbsoluteDate |
ParameterDriver.getReferenceDate()
Get current reference date.
|
AbsoluteDate |
SecularAndHarmonic.getReferenceDate()
Get the reference date.
|
AbsoluteDate |
TimeSpanMap.Span.getStart()
Get the start of this time span.
|
| Modifier and Type | Method and Description |
|---|---|
void |
SecularAndHarmonic.addPoint(AbsoluteDate date,
double osculatingValue)
Add a fitting point.
|
void |
TimeSpanMap.addValidAfter(T entry,
AbsoluteDate earliestValidityDate)
Add an entry valid after a limit date.
|
void |
TimeSpanMap.addValidBefore(T entry,
AbsoluteDate latestValidityDate)
Add an entry valid before a limit date.
|
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.
|
double |
IERSConventions.evaluateTC(AbsoluteDate date)
Evaluate the date offset between the current date and the
reference date. |
double |
IERSConventions.evaluateTC(AbsoluteDate date,
TimeScales timeScales)
Evaluate the date offset between the current date and the
reference date. |
TimeSpanMap<T> |
TimeSpanMap.extractRange(AbsoluteDate start,
AbsoluteDate end)
Extract a range of the map.
|
List<T> |
TimeStampedGenerator.generate(AbsoluteDate existingDate,
AbsoluteDate date)
Generate a chronologically sorted list of entries to be cached.
|
T |
TimeSpanMap.get(AbsoluteDate date)
Get the entry valid at a specified date.
|
Stream<T> |
TimeStampedCache.getNeighbors(AbsoluteDate central)
Get the entries surrounding a central date.
|
Stream<T> |
ImmutableTimeStampedCache.getNeighbors(AbsoluteDate central)
Get the entries surrounding a central date.
|
Stream<T> |
GenericTimeStampedCache.getNeighbors(AbsoluteDate central)
Get the entries surrounding a central date.
|
TimeStampedPVCoordinates |
AbsolutePVCoordinates.getPVCoordinates(AbsoluteDate otherDate,
Frame outputFrame) |
TimeStampedPVCoordinates |
PVCoordinatesProvider.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
TimeSpanMap.Span<T> |
TimeSpanMap.getSpan(AbsoluteDate date)
Get the time span containing a specified date.
|
static TimeStampedAngularCoordinates |
TimeStampedAngularCoordinates.interpolate(AbsoluteDate date,
AngularDerivativesFilter filter,
Collection<TimeStampedAngularCoordinates> sample)
Interpolate angular coordinates.
|
static <T extends RealFieldElement<T>> |
TimeStampedFieldAngularCoordinates.interpolate(AbsoluteDate date,
AngularDerivativesFilter filter,
Collection<TimeStampedFieldAngularCoordinates<T>> sample)
Interpolate angular coordinates.
|
static TimeStampedPVCoordinates |
TimeStampedPVCoordinates.interpolate(AbsoluteDate date,
CartesianDerivativesFilter filter,
Collection<TimeStampedPVCoordinates> sample)
Interpolate position-velocity.
|
static TimeStampedPVCoordinates |
TimeStampedPVCoordinates.interpolate(AbsoluteDate date,
CartesianDerivativesFilter filter,
Stream<TimeStampedPVCoordinates> sample)
Interpolate position-velocity.
|
AbsolutePVCoordinates |
AbsolutePVCoordinates.interpolate(AbsoluteDate date,
Stream<AbsolutePVCoordinates> sample) |
static AbsolutePVCoordinates |
AbsolutePVCoordinates.interpolate(Frame frame,
AbsoluteDate date,
CartesianDerivativesFilter filter,
Stream<AbsolutePVCoordinates> 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.
|
default void |
ParameterObserver.referenceDateChanged(AbsoluteDate previousReferenceDate,
ParameterDriver driver)
Notify that a parameter reference date has been changed.
|
void |
SecularAndHarmonic.resetFitting(AbsoluteDate date,
double... initialGuess)
Reset fitting.
|
void |
ParameterDriver.setReferenceDate(AbsoluteDate newReferenceDate)
Set reference date.
|
double[] |
IERSConventions.NutationCorrectionConverter.toEquinox(AbsoluteDate date,
double dX,
double dY)
Convert nutation corrections.
|
double[] |
IERSConventions.NutationCorrectionConverter.toNonRotating(AbsoluteDate date,
double ddPsi,
double ddEpsilon)
Convert nutation corrections.
|
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