Uses of Class
org.orekit.errors.OrekitException

Packages that use OrekitException

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.errors	This package provides classes to generate and handle exceptions.
org.orekit.files.ccsds	This package provides a parser for orbit data stored in CCSDS Orbit 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
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.radiation
org.orekit.frames	This package provides classes to handle frames and transforms between them.
org.orekit.models.earth	This package provides models that simulate certain physical phenomena experienced in the atmosphere of the earth.
org.orekit.orbits	This package provides classes to represent orbits.
org.orekit.propagation	This package provides tools to propagate orbital states with different methods.
org.orekit.propagation.analytical
org.orekit.propagation.analytical.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
org.orekit.propagation.numerical
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
org.orekit.propagation.semianalytical.dsst.utilities
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.

Uses of OrekitException in org.orekit.attitudes

Methods in org.orekit.attitudes that throw OrekitException

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

Constructors in org.orekit.attitudes that throw OrekitException

Constructor and Description
LofOffset(Frame inertialFrame, LOFType type) Create a LOF-aligned attitude.
LofOffset(Frame inertialFrame, LOFType type, RotationOrder order, double alpha1, double alpha2, double alpha3) Creates new instance.

Uses of OrekitException in org.orekit.bodies

Methods in org.orekit.bodies that throw OrekitException

Modifier and Type	Method and Description
static void	CelestialBodyFactory.addDefaultCelestialBodyLoader(String supportedNames) Add the default loaders for all predefined celestial bodies.
static void	CelestialBodyFactory.addDefaultCelestialBodyLoader(String name, String supportedNames) Add the default loaders for celestial bodies.
static CelestialBody	CelestialBodyFactory.getBody(String name) Get a celestial body.
Frame	CelestialBody.getBodyOrientedFrame() Get a body oriented, body centered frame.
static CelestialBody	CelestialBodyFactory.getEarth() Get the Earth singleton body.
static CelestialBody	CelestialBodyFactory.getEarthMoonBarycenter() Get the Earth-Moon barycenter singleton bodies pair.
Frame	CelestialBody.getInertiallyOrientedFrame() Get an inertially oriented, body centered frame.
GeodeticPoint	OneAxisEllipsoid.getIntersectionPoint(Line line, Vector3D close, Frame frame, AbsoluteDate date) Get the intersection point of a line with the surface of the body.
GeodeticPoint	BodyShape.getIntersectionPoint(Line line, Vector3D close, Frame frame, AbsoluteDate date) Get the intersection point of a line with the surface of the body.
static CelestialBody	CelestialBodyFactory.getJupiter() Get the Jupiter singleton body.
double	JPLEphemeridesLoader.getLoadedAstronomicalUnit() Get astronomical unit.
double	JPLEphemeridesLoader.getLoadedConstant(String... names) Get a constant defined in the ephemerides headers.
double	JPLEphemeridesLoader.getLoadedEarthMoonMassRatio() Get Earth/Moon mass ratio.
double	JPLEphemeridesLoader.getLoadedGravitationalCoefficient(JPLEphemeridesLoader.EphemerisType body) Get the gravitational coefficient of a body.
static CelestialBody	CelestialBodyFactory.getMars() Get the Mars singleton body.
static CelestialBody	CelestialBodyFactory.getMercury() Get the Mercury singleton body.
static CelestialBody	CelestialBodyFactory.getMoon() Get the Moon singleton body.
static CelestialBody	CelestialBodyFactory.getNeptune() Get the Neptune singleton body.
static CelestialBody	CelestialBodyFactory.getPluto() Get the Pluto singleton body.
PVCoordinates	JPLEphemeridesLoader.RawPVProvider.getRawPV(AbsoluteDate date) Get the position-velocity at date.
static CelestialBody	CelestialBodyFactory.getSaturn() Get the Saturn singleton body.
static CelestialBody	CelestialBodyFactory.getSolarSystemBarycenter() Get the solar system barycenter aggregated body.
static CelestialBody	CelestialBodyFactory.getSun() Get the Sun singleton body.
static CelestialBody	CelestialBodyFactory.getUranus() Get the Uranus singleton body.
static CelestialBody	CelestialBodyFactory.getVenus() Get the Venus singleton body.
CelestialBody	CelestialBodyLoader.loadCelestialBody(String name) Load celestial body.
CelestialBody	JPLEphemeridesLoader.loadCelestialBody(String name) Load celestial body.
TimeStampedPVCoordinates	OneAxisEllipsoid.projectToGround(TimeStampedPVCoordinates pv, Frame frame) Project a moving point to the ground.
TimeStampedPVCoordinates	BodyShape.projectToGround(TimeStampedPVCoordinates pv, Frame frame) Project a moving point to the ground.
Vector3D	OneAxisEllipsoid.projectToGround(Vector3D point, AbsoluteDate date, Frame frame) Project a point to the ground.
Vector3D	BodyShape.projectToGround(Vector3D point, AbsoluteDate date, Frame frame) Project a point to the ground.
GeodeticPoint	OneAxisEllipsoid.transform(Vector3D point, Frame frame, AbsoluteDate date) Transform a cartesian point to a surface-relative point.
GeodeticPoint	BodyShape.transform(Vector3D point, Frame frame, AbsoluteDate date) Transform a cartesian point to a surface-relative point.

Constructors in org.orekit.bodies that throw OrekitException

Constructor and Description
JPLEphemeridesLoader(String supportedNames, JPLEphemeridesLoader.EphemerisType generateType) Create a loader for JPL ephemerides binary files.

Uses of OrekitException in org.orekit.data

Methods in org.orekit.data that throw OrekitException

Modifier and Type	Method and Description
void	DataProvidersManager.addDefaultProviders() Add the default providers configuration.
S	SimpleTimeStampedTableParser.RowConverter.convert(double[] rawFields) Convert a row.
boolean	ZipJarCrawler.feed(Pattern supported, DataLoader visitor) Feed a data file loader by browsing the data collection.
boolean	ClasspathCrawler.feed(Pattern supported, DataLoader visitor) Feed a data file loader by browsing the data collection.
boolean	NetworkCrawler.feed(Pattern supported, DataLoader visitor) Feed a data file loader by browsing the data collection.
boolean	DataProvider.feed(Pattern supported, DataLoader visitor) Feed a data file loader by browsing the data collection.
boolean	DirectoryCrawler.feed(Pattern supported, DataLoader visitor) Feed a data file loader by browsing the data collection.
boolean	DataProvidersManager.feed(String supportedNames, DataLoader loader) Feed a data file loader by browsing all data providers.
void	DataLoader.loadData(InputStream input, String name) Load data from a stream.
List<T>	SimpleTimeStampedTableParser.parse(InputStream stream, String name) Parse a stream.
PoissonSeries<T>	PoissonSeriesParser.parse(InputStream stream, String name) Parse a stream.
PoissonSeriesParser<T>	PoissonSeriesParser.withDoodson(int firstMultiplierColumn, int numberColumn) Set up columns for Doodson multiplers and Doodson number.
PoissonSeriesParser<T>	PoissonSeriesParser.withGamma(int column) Set up column of GMST tide multiplier.

Constructors in org.orekit.data that throw OrekitException

Constructor and Description
ClasspathCrawler(ClassLoader classLoader, String... list) Build a data classpath crawler.
ClasspathCrawler(String... list) Build a data classpath crawler.
DirectoryCrawler(File root) Build a data files crawler.
FundamentalNutationArguments(IERSConventions conventions, TimeScale timeScale, InputStream stream, String name) Build a model of fundamental arguments from an IERS table file.
FundamentalNutationArguments(IERSConventions conventions, TimeScale timeScale, List<double[]> coefficients) Build a model of fundamental arguments from an IERS table file.
ZipJarCrawler(ClassLoader classLoader, String resource) Build a zip crawler for an archive file in classpath.
ZipJarCrawler(String resource) Build a zip crawler for an archive file in classpath.
ZipJarCrawler(URL url) Build a zip crawler for an archive file on network.

Uses of OrekitException in org.orekit.errors

Subclasses of OrekitException in org.orekit.errors

Modifier and Type	Class and Description
class	FrameAncestorException This class is the base class for exception thrown by the UpdatableFrame.updateTransform method.
class	PropagationException This class is the base class for all specific exceptions thrown by during the propagation computation.
class	TimeStampedCacheException This class is the base class for all specific exceptions thrown by during the GenericTimeStampedCache.

Methods in org.orekit.errors that return OrekitException

Modifier and Type	Method and Description
OrekitException	OrekitExceptionWrapper.getException() Get the wrapped exception.

Methods in org.orekit.errors with parameters of type OrekitException

Modifier and Type	Method and Description
static TimeStampedCacheException	TimeStampedCacheException.unwrap(OrekitException oe) Recover a PropagationException, possibly embedded in a OrekitException.
static PropagationException	PropagationException.unwrap(OrekitException oe) Recover a PropagationException, possibly embedded in a OrekitException.

Constructors in org.orekit.errors with parameters of type OrekitException

Constructor and Description
OrekitException(OrekitException exception) Copy constructor.
OrekitExceptionWrapper(OrekitException wrappedException) Simple constructor.
PropagationException(OrekitException exception) Simple constructor.
TimeStampedCacheException(OrekitException exception) Simple constructor.

Uses of OrekitException in org.orekit.files.ccsds

Methods in org.orekit.files.ccsds that throw OrekitException

Modifier and Type	Method and Description
CartesianOrbit	OMMFile.generateCartesianOrbit() Generate a CartesianOrbit from the KeplerianOrbit.
CartesianOrbit	OPMFile.generateCartesianOrbit() Generate a CartesianOrbit from the OPM state vector data.
KeplerianOrbit	OMMFile.generateKeplerianOrbit() Generate a KeplerianOrbit based on the OMM mean keplerian elements.
KeplerianOrbit	OPMFile.generateKeplerianOrbit() Generate a KeplerianOrbit from the OPM keplerian elements if hasKeplerianElements is true, or from the state vector data otherwise.
SpacecraftState	OMMFile.generateSpacecraftState() Generate spacecraft state from the KeplerianOrbit generated by generateKeplerianOrbit.
SpacecraftState	OPMFile.generateSpacecraftState() Generate spacecraft state from the CartesianOrbit generated by generateCartesianOrbit.
abstract CelestialBody	CenterName.getCelestialBody() Get the celestial body corresponding to the CCSDS constant.
IERSConventions	ODMFile.getConventions() Get IERS conventions.
Frame	CCSDSFrame.getFrame(IERSConventions conventions, boolean simpleEOP) Get the frame corresponding to the CCSDS constant.
double	OGMFile.getMass() Get the spacecraft mass.
ODMFile	ODMParser.parse(InputStream stream) Parse a CCSDS Orbit Data Message.
OMMFile	OMMParser.parse(InputStream stream, String fileName) Parse a CCSDS Orbit Data Message.
OPMFile	OPMParser.parse(InputStream stream, String fileName) Parse a CCSDS Orbit Data Message.
abstract ODMFile	ODMParser.parse(InputStream stream, String fileName) Parse a CCSDS Orbit Data Message.
OEMFile	OEMParser.parse(InputStream stream, String fileName) Parse a CCSDS Orbit Data Message.
OMMFile	OMMParser.parse(String fileName) Parse a CCSDS Orbit Data Message.
OPMFile	OPMParser.parse(String fileName) Parse a CCSDS Orbit Data Message.
ODMFile	ODMParser.parse(String fileName) Parse a CCSDS Orbit Data Message.
OEMFile	OEMParser.parse(String fileName) Parse a CCSDS Orbit Data Message.
protected AbsoluteDate	ODMParser.parseDate(String date, OrbitFile.TimeSystem timeSystem) Parse a date.
protected boolean	ODMParser.parseGeneralStateDataEntry(org.orekit.files.ccsds.KeyValue keyValue, OGMFile general, List<String> comment) Parse a general state data key = value entry.
protected boolean	ODMParser.parseHeaderEntry(org.orekit.files.ccsds.KeyValue keyValue, ODMFile odmFile, List<String> comment) Parse an entry from the header.
protected boolean	ODMParser.parseMetaDataEntry(org.orekit.files.ccsds.KeyValue keyValue, ODMMetaData metaData, List<String> comment) Parse a meta-data key = value entry.
protected void	ODMFile.setMuUsed() Set the gravitational coefficient created from the knowledge of the central body.

Uses of OrekitException in org.orekit.files.general

Methods in org.orekit.files.general that throw OrekitException

Modifier and Type	Method and Description
OrbitFile	OrbitFileParser.parse(InputStream stream) Reads an orbit file from the given stream and returns a parsed OrbitFile.
OrbitFile	OrbitFileParser.parse(String fileName) Reads the orbit file and returns a parsed OrbitFile.

Uses of OrekitException in org.orekit.files.sp3

Methods in org.orekit.files.sp3 that throw OrekitException

Modifier and Type	Method and Description
SP3File	SP3Parser.parse(InputStream stream) Reads an orbit file from the given stream and returns a parsed OrbitFile.
SP3File	SP3Parser.parse(String fileName) Reads the orbit file and returns a parsed OrbitFile.

Uses of OrekitException in org.orekit.forces

Methods in org.orekit.forces that throw OrekitException

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

Uses of OrekitException in org.orekit.forces.drag

Methods in org.orekit.forces.drag that throw OrekitException

Modifier and Type	Method and Description
FieldVector3D<DerivativeStructure>	DragForce.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
FieldVector3D<DerivativeStructure>	DragForce.accelerationDerivatives(SpacecraftState s, String paramName) Compute acceleration derivatives with respect to additional parameters.
void	DragForce.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the drag to the perturbing acceleration.
FieldVector3D<DerivativeStructure>	DragSensitive.dragAcceleration(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass, double density, FieldVector3D<DerivativeStructure> relativeVelocity) Compute the acceleration due to drag, with state derivatives.
Vector3D	DragSensitive.dragAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, double density, Vector3D relativeVelocity) Compute the acceleration due to drag.
FieldVector3D<DerivativeStructure>	DragSensitive.dragAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, double density, Vector3D relativeVelocity, String paramName) Compute acceleration due to drag, with parameters derivatives.
double	MarshallSolarActivityFutureEstimation.get24HoursKp(AbsoluteDate date) The Kp index is derived from the Ap index.
double	DTM2000InputParameters.get24HoursKp(AbsoluteDate date) Get the last 24H mean geomagnetic index.
double	JB2006InputParameters.getAp(AbsoluteDate date) Get the Geomagnetic planetary 3-hour index Ap.
double	DTM2000.getDensity(AbsoluteDate date, Vector3D position, Frame frame) Get the local density.
double	Atmosphere.getDensity(AbsoluteDate date, Vector3D position, Frame frame) Get the local density.
double	HarrisPriester.getDensity(AbsoluteDate date, Vector3D position, Frame frame) Get the local density at some position.
double	JB2006.getDensity(AbsoluteDate date, Vector3D position, Frame frame) Get the local density.
double	SimpleExponentialAtmosphere.getDensity(AbsoluteDate date, Vector3D position, Frame frame) Get the local density.
double	DTM2000.getDensity(int day, double alti, double lon, double lat, double hl, double f, double fbar, double akp3, double akp24) Get the local density with initial entries.
double	HarrisPriester.getDensity(Vector3D sunInEarth, Vector3D posInEarth) Get the local density.
double	JB2006InputParameters.getF10(AbsoluteDate date) Get the value of the instantaneous solar flux index (1e-22*Watt/(m²*Hertz)).
double	JB2006InputParameters.getF10B(AbsoluteDate date) Get the value of the mean solar flux.
DateComponents	MarshallSolarActivityFutureEstimation.getFileDate(AbsoluteDate date) Get the date of the file from which data at the specified date comes from.
double	MarshallSolarActivityFutureEstimation.getInstantFlux(AbsoluteDate date) Get the value of the instantaneous solar flux.
double	DTM2000InputParameters.getInstantFlux(AbsoluteDate date) Get the value of the instantaneous solar flux.
double	MarshallSolarActivityFutureEstimation.getMeanFlux(AbsoluteDate date) Get the value of the mean solar flux.
double	DTM2000InputParameters.getMeanFlux(AbsoluteDate date) Get the value of the mean solar flux.
double	JB2006InputParameters.getS10(AbsoluteDate date) Get the EUV index (26-34 nm) scaled to F10.
double	JB2006InputParameters.getS10B(AbsoluteDate date) Get the EUV 81-day averaged centered index.
double	MarshallSolarActivityFutureEstimation.getThreeHourlyKP(AbsoluteDate date) Get the value of the 3 hours geomagnetic index.
double	DTM2000InputParameters.getThreeHourlyKP(AbsoluteDate date) Get the value of the 3 hours geomagnetic index.
Vector3D	DTM2000.getVelocity(AbsoluteDate date, Vector3D position, Frame frame) Get the inertial velocity of atmosphere molecules.
Vector3D	Atmosphere.getVelocity(AbsoluteDate date, Vector3D position, Frame frame) Get the inertial velocity of atmosphere molecules.
Vector3D	HarrisPriester.getVelocity(AbsoluteDate date, Vector3D position, Frame frame) Get the inertial velocity of atmosphere molecules.
Vector3D	JB2006.getVelocity(AbsoluteDate date, Vector3D position, Frame frame) Get the inertial velocity of atmosphere molecules.
Vector3D	SimpleExponentialAtmosphere.getVelocity(AbsoluteDate date, Vector3D position, Frame frame) Get the inertial velocity of atmosphere molecules.
double	JB2006InputParameters.getXM10(AbsoluteDate date) Get the MG2 index scaled to F10.
double	JB2006InputParameters.getXM10B(AbsoluteDate date) Get the MG2 81-day average centered index.
void	MarshallSolarActivityFutureEstimation.loadData(InputStream input, String name) Load data from a stream.

Constructors in org.orekit.forces.drag that throw OrekitException

Constructor and Description
DTM2000(DTM2000InputParameters parameters, PVCoordinatesProvider sun, BodyShape earth) Simple constructor for independent computation.

Uses of OrekitException in org.orekit.forces.gravity

Methods in org.orekit.forces.gravity that throw OrekitException

Modifier and Type	Method and Description
FieldVector3D<DerivativeStructure>	SolidTides.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
FieldVector3D<DerivativeStructure>	CunninghamAttractionModel.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
FieldVector3D<DerivativeStructure>	ThirdBodyAttraction.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
FieldVector3D<DerivativeStructure>	OceanTides.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
FieldVector3D<DerivativeStructure>	DrozinerAttractionModel.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
FieldVector3D<DerivativeStructure>	HolmesFeatherstoneAttractionModel.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
FieldVector3D<DerivativeStructure>	NewtonianAttraction.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
FieldVector3D<DerivativeStructure>	SolidTides.accelerationDerivatives(SpacecraftState s, String paramName) Compute acceleration derivatives with respect to additional parameters.
FieldVector3D<DerivativeStructure>	CunninghamAttractionModel.accelerationDerivatives(SpacecraftState s, String paramName) Compute acceleration derivatives with respect to additional parameters.
FieldVector3D<DerivativeStructure>	Relativity.accelerationDerivatives(SpacecraftState s, String paramName)
FieldVector3D<DerivativeStructure>	ThirdBodyAttraction.accelerationDerivatives(SpacecraftState s, String paramName) Compute acceleration derivatives with respect to additional parameters.
FieldVector3D<DerivativeStructure>	OceanTides.accelerationDerivatives(SpacecraftState s, String paramName) Compute acceleration derivatives with respect to additional parameters.
FieldVector3D<DerivativeStructure>	DrozinerAttractionModel.accelerationDerivatives(SpacecraftState s, String paramName) Compute acceleration derivatives with respect to additional parameters.
FieldVector3D<DerivativeStructure>	HolmesFeatherstoneAttractionModel.accelerationDerivatives(SpacecraftState s, String paramName) Compute acceleration derivatives with respect to additional parameters.
FieldVector3D<DerivativeStructure>	NewtonianAttraction.accelerationDerivatives(SpacecraftState s, String paramName) Compute acceleration derivatives with respect to additional parameters.
void	SolidTides.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	CunninghamAttractionModel.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	Relativity.addContribution(SpacecraftState s, TimeDerivativesEquations adder)
void	ThirdBodyAttraction.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	OceanTides.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	DrozinerAttractionModel.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	HolmesFeatherstoneAttractionModel.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
void	NewtonianAttraction.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
double[]	HolmesFeatherstoneAttractionModel.gradient(AbsoluteDate date, Vector3D position) Compute the gradient of the non-central part of the gravity field.
HolmesFeatherstoneAttractionModel.GradientHessian	HolmesFeatherstoneAttractionModel.gradientHessian(AbsoluteDate date, Vector3D position) Compute both the gradient and the hessian of the non-central part of the gravity field.
double	HolmesFeatherstoneAttractionModel.nonCentralPart(AbsoluteDate date, Vector3D position) Compute the non-central part of the gravity field.
double	HolmesFeatherstoneAttractionModel.value(AbsoluteDate date, Vector3D position) Compute the value of the gravity field.

Constructors in org.orekit.forces.gravity that throw OrekitException

Constructor and Description
OceanTides(Frame centralBodyFrame, double ae, double mu, boolean poleTide, double step, int nbPoints, int degree, int order, IERSConventions conventions, UT1Scale ut1) Simple constructor.
OceanTides(Frame centralBodyFrame, double ae, double mu, int degree, int order, IERSConventions conventions, UT1Scale ut1) Simple constructor.
SolidTides(Frame centralBodyFrame, double ae, double mu, TideSystem centralTideSystem, boolean poleTide, double step, int nbPoints, IERSConventions conventions, UT1Scale ut1, CelestialBody... bodies) Simple constructor.
SolidTides(Frame centralBodyFrame, double ae, double mu, TideSystem centralTideSystem, IERSConventions conventions, UT1Scale ut1, CelestialBody... bodies) Simple constructor.

Uses of OrekitException in org.orekit.forces.gravity.potential

Methods in org.orekit.forces.gravity.potential that throw OrekitException

Modifier and Type	Method and Description
static void	GravityFieldFactory.addDefaultOceanTidesReaders() Add the default READERS for ocean tides.
protected void	OceanTidesReader.addWaveCoefficients(int doodson, int n, int m, double cPlus, double sPlus, double cMinus, double sMinus, int lineNumber, String line) Add parsed coefficients.
protected void	OceanTidesReader.endParse() End parsing.
abstract double[]	OceanLoadDeformationCoefficients.getCoefficients() Get the load deformation coefficients for ocean tides.
static NormalizedSphericalHarmonicsProvider	GravityFieldFactory.getConstantNormalizedProvider(int degree, int order) Get the constant gravity field coefficients provider from the first supported file.
protected org.orekit.forces.gravity.potential.ConstantSphericalHarmonics	PotentialCoefficientsReader.getConstantProvider(boolean wantNormalized, int degree, int order) Get a time-independent provider for read spherical harmonics coefficients.
static UnnormalizedSphericalHarmonicsProvider	GravityFieldFactory.getConstantUnnormalizedProvider(int degree, int order) Get the constant gravity field coefficients provider from the first supported file.
double	NormalizedSphericalHarmonicsProvider.NormalizedSphericalHarmonics.getNormalizedCnm(int n, int m) Get a spherical harmonic cosine coefficient.
static NormalizedSphericalHarmonicsProvider	GravityFieldFactory.getNormalizedProvider(int degree, int order) Get the gravity field coefficients provider from the first supported file.
static NormalizedSphericalHarmonicsProvider	GravityFieldFactory.getNormalizedProvider(UnnormalizedSphericalHarmonicsProvider unnormalized) Create a NormalizedSphericalHarmonicsProvider from an UnnormalizedSphericalHarmonicsProvider.
double	NormalizedSphericalHarmonicsProvider.NormalizedSphericalHarmonics.getNormalizedSnm(int n, int m) Get a spherical harmonic sine coefficient.
static List<OceanTidesWave>	GravityFieldFactory.getOceanTidesWaves(int degree, int order) Get the ocean tides waves from the first supported file.
RawSphericalHarmonicsProvider	SHMFormatReader.getProvider(boolean wantNormalized, int degree, int order) Get a provider for read spherical harmonics coefficients.
RawSphericalHarmonicsProvider	EGMFormatReader.getProvider(boolean wantNormalized, int degree, int order) Get a provider for read spherical harmonics coefficients.
abstract RawSphericalHarmonicsProvider	PotentialCoefficientsReader.getProvider(boolean wantNormalized, int degree, int order) Get a provider for read spherical harmonics coefficients.
RawSphericalHarmonicsProvider	ICGEMFormatReader.getProvider(boolean wantNormalized, int degree, int order) Get a provider for read spherical harmonics coefficients.
RawSphericalHarmonicsProvider	GRGSFormatReader.getProvider(boolean wantNormalized, int degree, int order) Get a provider for read spherical harmonics coefficients.
double	RawSphericalHarmonicsProvider.RawSphericalHarmonics.getRawCnm(int n, int m) Get a spherical harmonic cosine coefficient.
double	RawSphericalHarmonicsProvider.RawSphericalHarmonics.getRawSnm(int n, int m) Get a spherical harmonic sine coefficient.
static double[][]	GravityFieldFactory.getUnnormalizationFactors(int degree, int order) Get a un-normalization factors array.
double	UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics.getUnnormalizedCnm(int n, int m) Get a spherical harmonic cosine coefficient.
static UnnormalizedSphericalHarmonicsProvider	GravityFieldFactory.getUnnormalizedProvider(int degree, int order) Get the gravity field coefficients provider from the first supported file.
static UnnormalizedSphericalHarmonicsProvider	GravityFieldFactory.getUnnormalizedProvider(NormalizedSphericalHarmonicsProvider normalized) Create an UnnormalizedSphericalHarmonicsProvider from a NormalizedSphericalHarmonicsProvider.
double	UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics.getUnnormalizedSnm(int n, int m) Get a spherical harmonic sine coefficient.
void	AstronomicalAmplitudeReader.loadData(InputStream input, String name) Load data from a stream.
void	FESCnmSnmReader.loadData(InputStream input, String name) Load data from a stream.
void	SHMFormatReader.loadData(InputStream input, String name) Load data from a stream.
void	EGMFormatReader.loadData(InputStream input, String name) Load data from a stream.
abstract void	PotentialCoefficientsReader.loadData(InputStream input, String name) Load data from a stream.
void	ICGEMFormatReader.loadData(InputStream input, String name) Load data from a stream.
void	GRGSFormatReader.loadData(InputStream input, String name) Load data from a stream.
void	FESCHatEpsilonReader.loadData(InputStream input, String name) Load data from a stream.
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.
NormalizedSphericalHarmonicsProvider.NormalizedSphericalHarmonics	NormalizedSphericalHarmonicsProvider.onDate(AbsoluteDate date) Get the normalized spherical harmonic coefficients at a specific instance in time.
protected void	PotentialCoefficientsReader.parseCoefficient(String field, double[][] array, int i, int j, String cName, String name) Parse a coefficient.
protected void	PotentialCoefficientsReader.parseCoefficient(String field, List<List<Double>> list, int i, int j, String cName, String name) Parse a coefficient.
static PotentialCoefficientsReader	GravityFieldFactory.readGravityField(int maxParseDegree, int maxParseOrder) Read a gravity field coefficients provider from the first supported file.
protected static void	PotentialCoefficientsReader.rescale(double scale, boolean normalizedOrigin, double[][] originC, double[][] originS, boolean wantNormalized, double[][] rescaledC, double[][] rescaledS) Rescale coefficients arrays.
protected void	PotentialCoefficientsReader.setRawCoefficients(boolean rawNormalized, double[][] c, double[][] s, String name) Set the tesseral-sectorial coefficients matrix.

Uses of OrekitException in org.orekit.forces.maneuvers

Methods in org.orekit.forces.maneuvers that throw OrekitException

Modifier and Type	Method and Description
FieldVector3D<DerivativeStructure>	ConstantThrustManeuver.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
FieldVector3D<DerivativeStructure>	ConstantThrustManeuver.accelerationDerivatives(SpacecraftState s, String paramName) Compute acceleration derivatives with respect to additional parameters.
void	ConstantThrustManeuver.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
double	ImpulseManeuver.g(SpacecraftState s) Compute the value of the switching function.
void	SmallManeuverAnalyticalModel.getJacobian(Orbit orbit1, PositionAngle positionAngle, double[][] jacobian) Compute the Jacobian of the orbit with respect to maneuver parameters.

Constructors in org.orekit.forces.maneuvers that throw OrekitException

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

Uses of OrekitException in org.orekit.forces.radiation

Methods in org.orekit.forces.radiation that throw OrekitException

Modifier and Type	Method and Description
FieldVector3D<DerivativeStructure>	SolarRadiationPressure.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration derivatives with respect to state parameters.
FieldVector3D<DerivativeStructure>	SolarRadiationPressure.accelerationDerivatives(SpacecraftState s, String paramName) Compute acceleration derivatives with respect to additional parameters.
void	SolarRadiationPressure.addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
double	SolarRadiationPressure.getLightningRatio(Vector3D position, Frame frame, AbsoluteDate date) Get the lightning ratio ([0-1]).
FieldVector3D<DerivativeStructure>	RadiationSensitive.radiationPressureAcceleration(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass, FieldVector3D<DerivativeStructure> flux) Compute the acceleration due to radiation pressure, with state derivatives.
Vector3D	RadiationSensitive.radiationPressureAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, Vector3D flux) Compute the acceleration due to radiation pressure.
FieldVector3D<DerivativeStructure>	RadiationSensitive.radiationPressureAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, Vector3D flux, String paramName) Compute the acceleration due to radiation pressure, with parameters derivatives.

Uses of OrekitException in org.orekit.frames

Methods in org.orekit.frames that throw OrekitException

Modifier and Type	Method and Description
void	OrphanFrame.addChild(OrphanFrame child, Transform transform, boolean isPseudoInertial) Add a child.
void	OrphanFrame.addChild(OrphanFrame child, TransformProvider transformProvider, boolean isPseudoInertial) Add a child.
void	OrphanFrame.attachTo(Frame parent, Transform transform, boolean isPseudoInertial) Attach the instance (and all its children down to leafs) to the main tree.
void	OrphanFrame.attachTo(Frame parent, TransformProvider transformProvider, boolean isPseudoInertial) Attach the instance (and all its children down to leafs) to the main tree.
void	EOPHistory.checkEOPContinuity(double maxGap) Check Earth orientation parameters continuity.
GeodeticPoint	TopocentricFrame.computeLimitVisibilityPoint(double radius, double azimuth, double elevation) Compute the limit visibility point for a satellite in a given direction.
void	EOPHistoryLoader.fillHistory(IERSConventions.NutationCorrectionConverter converter, SortedSet<EOPEntry> history) Load celestial body.
double	TopocentricFrame.getAzimuth(Vector3D extPoint, Frame frame, AbsoluteDate date) Get the azimuth of a point with regards to the topocentric frame center point.
static FactoryManagedFrame	FramesFactory.getCIRF(IERSConventions conventions, boolean simpleEOP) Get the CIRF2000 reference frame.
static Frame	FramesFactory.getEcliptic(IERSConventions conventions) Get the ecliptic frame.
double	TopocentricFrame.getElevation(Vector3D extPoint, Frame frame, AbsoluteDate date) Get the elevation of a point with regards to the local point.
static EOPHistory	FramesFactory.getEOPHistory(IERSConventions conventions, boolean simpleEOP) Get Earth Orientation Parameters history.
Frame	OrphanFrame.getFrame() Get the associated frame.
static Frame	FramesFactory.getFrame(Predefined factoryKey) Get one of the predefined frames.
Frame	Frame.getFrozenFrame(Frame reference, AbsoluteDate freezingDate, String frozenName) Get a new version of the instance, frozen with respect to a reference frame.
static FactoryManagedFrame	FramesFactory.getGTOD(boolean applyEOPCorr) Get the GTOD reference frame.
static FactoryManagedFrame	FramesFactory.getGTOD(IERSConventions conventions, boolean simpleEOP) Get the GTOD reference frame.
static Frame	FramesFactory.getICRF() Get the unique ICRF frame.
static FactoryManagedFrame	FramesFactory.getITRF(IERSConventions conventions, boolean simpleEOP) Get the ITRF2008 reference frame, using IERS 2010 conventions.
static FactoryManagedFrame	FramesFactory.getITRFEquinox(IERSConventions conventions, boolean simpleEOP) Get the equinox-based ITRF reference frame.
static FactoryManagedFrame	FramesFactory.getMOD(boolean applyEOPCorr) Get the MOD reference frame.
static FactoryManagedFrame	FramesFactory.getMOD(IERSConventions conventions) Get the MOD reference frame.
static Transform	FramesFactory.getNonInterpolatingTransform(Frame from, Frame to, AbsoluteDate date) Get the transform between two frames, suppressing all interpolation.
TimeStampedPVCoordinates	TopocentricFrame.getPVCoordinates(AbsoluteDate date, Frame frame) Get the PVCoordinates of the topocentric frame origin in the selected frame.
double	TopocentricFrame.getRange(Vector3D extPoint, Frame frame, AbsoluteDate date) Get the range of a point with regards to the topocentric frame center point.
double	TopocentricFrame.getRangeRate(PVCoordinates extPV, Frame frame, AbsoluteDate date) Get the range rate of a point with regards to the topocentric frame center point.
static FactoryManagedFrame	FramesFactory.getTEME() Get the TEME reference frame.
static FactoryManagedFrame	FramesFactory.getTIRF(IERSConventions conventions) Get the TIRF reference frame, ignoring tidal effects.
static FactoryManagedFrame	FramesFactory.getTIRF(IERSConventions conventions, boolean simpleEOP) Get the TIRF reference frame.
static FactoryManagedFrame	FramesFactory.getTOD(boolean applyEOPCorr) Get the TOD reference frame.
static FactoryManagedFrame	FramesFactory.getTOD(IERSConventions conventions, boolean simpleEOP) Get the TOD reference frame.
Transform	InterpolatingTransformProvider.getTransform(AbsoluteDate date) Get the Transform corresponding to specified date.
Transform	EclipticProvider.getTransform(AbsoluteDate date)
Transform	GTODProvider.getTransform(AbsoluteDate date) Get the transform from TOD at specified date.
Transform	TransformProvider.getTransform(AbsoluteDate date) Get the Transform corresponding to specified date.
Transform	Frame.getTransformTo(Frame destination, AbsoluteDate date) Get the transform from the instance to another frame.
static FactoryManagedFrame	FramesFactory.getVeis1950() Get the VEIS 1950 reference frame.
static Transform	Transform.interpolate(AbsoluteDate date, boolean useVelocities, boolean useRotationRates, Collection<Transform> sample) Deprecated. as of 7.0, replaced with Transform.interpolate(AbsoluteDate, CartesianDerivativesFilter, AngularDerivativesFilter, Collection)
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, Collection<Transform> sample) Get an interpolated instance.
GeodeticPoint	TopocentricFrame.pointAtDistance(double azimuth, double elevation, double distance) Compute the point observed from the station at some specified distance.
void	UpdatableFrame.updateTransform(Frame f1, Frame f2, Transform f1Tof2, AbsoluteDate date) Update the transform from parent frame implicitly according to two other frames.

Constructors in org.orekit.frames that throw OrekitException

Constructor and Description
EclipticProvider(IERSConventions conventions) Create a transform provider from MOD to an ecliptically aligned frame.
EOPEntry(int mjd, double dt, double lod, double x, double y, double ddPsi, double ddEps, double dx, double dy) Simple constructor.
EOPHistory(IERSConventions conventions, Collection<EOPEntry> data, boolean simpleEOP) Simple constructor.
GTODProvider(IERSConventions conventions, EOPHistory eopHistory) Simple constructor.

Uses of OrekitException in org.orekit.models.earth

Methods in org.orekit.models.earth that throw OrekitException

Modifier and Type	Method and Description
static FixedTroposphericDelay	FixedTroposphericDelay.getDefaultModel() Returns the default model, loading delay values from the file "tropospheric-delay.txt".
static GeoMagneticField	GeoMagneticFieldFactory.getField(GeoMagneticFieldFactory.FieldModel type, double year) Get the GeoMagneticField for the given model type and year.
static GeoMagneticField	GeoMagneticFieldFactory.getIGRF(double year) Get the IGRF model for the given year.
static GeoMagneticField	GeoMagneticFieldFactory.getWMM(double year) Get the WMM model for the given year.
GeoMagneticField	GeoMagneticField.transformModel(double year) Time transform the model coefficients from the base year of the model using secular variation coefficients.
GeoMagneticField	GeoMagneticField.transformModel(GeoMagneticField otherModel, double year) Time transform the model coefficients from the base year of the model using a linear interpolation with a second model.

Constructors in org.orekit.models.earth that throw OrekitException

Constructor and Description
FixedTroposphericDelay(String supportedName) Creates a new FixedTroposphericDelay instance, and loads the delay values from the given resource via the DataProvidersManager.

Uses of OrekitException in org.orekit.orbits

Methods in org.orekit.orbits that throw OrekitException

Modifier and Type	Method and Description
TimeStampedPVCoordinates	Orbit.getPVCoordinates(AbsoluteDate otherDate, Frame otherFrame) Get the PVCoordinates of the body in the selected frame.
TimeStampedPVCoordinates	Orbit.getPVCoordinates(Frame outputFrame) Get the TimeStampedPVCoordinates in a specified frame.

Uses of OrekitException in org.orekit.propagation

Methods in org.orekit.propagation that throw OrekitException

Modifier and Type	Method and Description
void	Propagator.addAdditionalStateProvider(AdditionalStateProvider additionalStateProvider) Add a set of user-specified state parameters to be computed along with the orbit propagation.
void	AbstractPropagator.addAdditionalStateProvider(AdditionalStateProvider additionalStateProvider) Add a set of user-specified state parameters to be computed along with the orbit propagation.
void	SpacecraftState.ensureCompatibleAdditionalStates(SpacecraftState state) Check if two instances have the same set of additional states available.
double[]	SpacecraftState.getAdditionalState(String name) Get an additional state.
TimeStampedPVCoordinates	AbstractPropagator.getPVCoordinates(AbsoluteDate date, Frame frame) Get the PVCoordinates of the body in the selected frame.
TimeStampedPVCoordinates	SpacecraftState.getPVCoordinates(Frame outputFrame) Get the TimeStampedPVCoordinates in given output frame.
SpacecraftState	SpacecraftState.interpolate(AbsoluteDate date, Collection<SpacecraftState> sample) Get an interpolated instance.

Constructors in org.orekit.propagation that throw OrekitException

Constructor and Description
SpacecraftState(Orbit orbit) Build a spacecraft state from orbit only.
SpacecraftState(Orbit orbit, double mass) Create a new instance from orbit and mass.
SpacecraftState(Orbit orbit, double mass, Map<String,double[]> additional) Create a new instance from orbit and mass.
SpacecraftState(Orbit orbit, Map<String,double[]> additional) Build a spacecraft state from orbit only.

Uses of OrekitException in org.orekit.propagation.analytical

Methods in org.orekit.propagation.analytical that throw OrekitException

Modifier and Type	Method and Description
protected SpacecraftState	AbstractAnalyticalPropagator.acceptStep(AbsoluteDate target, double epsilon) Accept a step, triggering events and step handlers.
SpacecraftState	AdapterPropagator.DifferentialEffect.apply(SpacecraftState original) Apply the effect to a spacecraft state.
TimeStampedPVCoordinates	Ephemeris.getPVCoordinates(AbsoluteDate date, Frame f) Get the PVCoordinates of the body in the selected frame.

Constructors in org.orekit.propagation.analytical that throw OrekitException

Constructor and Description
EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mass, UnnormalizedSphericalHarmonicsProvider provider) Build a propagator from orbit, attitude provider, mass and potential provider.
EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitude, double mass, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics) Private helper constructor.
EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, UnnormalizedSphericalHarmonicsProvider provider) Build a propagator from orbit, attitude provider and potential provider.
EcksteinHechlerPropagator(Orbit initialOrbit, double mass, UnnormalizedSphericalHarmonicsProvider provider) Build a propagator from orbit, mass and potential provider.
EcksteinHechlerPropagator(Orbit initialOrbit, UnnormalizedSphericalHarmonicsProvider provider) Build a propagator from orbit and potential provider.
Ephemeris(List<SpacecraftState> states, int interpolationPoints) Constructor with tabulated states.
J2DifferentialEffect(Orbit orbit0, Orbit orbit1, boolean applyBefore, UnnormalizedSphericalHarmonicsProvider gravityField) Simple constructor.
J2DifferentialEffect(SpacecraftState original, AdapterPropagator.DifferentialEffect directEffect, boolean applyBefore, double referenceRadius, double mu, double j2) Simple constructor.
J2DifferentialEffect(SpacecraftState original, AdapterPropagator.DifferentialEffect directEffect, boolean applyBefore, UnnormalizedSphericalHarmonicsProvider gravityField) Simple constructor.

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

Methods in org.orekit.propagation.analytical.tle that throw OrekitException

Modifier and Type	Method and Description
Set<Integer>	TLESeries.getAvailableSatelliteNumbers() Get the available satellite numbers.
String	TLE.getLine1() Get the first line.
PVCoordinates	TLESeries.getPVCoordinates(AbsoluteDate date) Get the extrapolated position and velocity from an initial date.
PVCoordinates	TLEPropagator.getPVCoordinates(AbsoluteDate date) Get the extrapolated position and velocity from an initial TLE.
static boolean	TLE.isFormatOK(String line1, String line2) Check the lines format validity.
void	TLESeries.loadData(InputStream input, String name) Load data from a stream.
void	TLESeries.loadTLEData() Load TLE data for a specified object.
void	TLESeries.loadTLEData(int satelliteNumber) Load TLE data for a specified object.
void	TLESeries.loadTLEData(int launchYear, int launchNumber, String launchPiece) Load TLE data for a specified object.
static TLEPropagator	TLEPropagator.selectExtrapolator(TLE tle) Selects the extrapolator to use with the selected TLE.
static TLEPropagator	TLEPropagator.selectExtrapolator(TLE tle, AttitudeProvider attitudeProvider, double mass) Selects the extrapolator to use with the selected TLE.
protected abstract void	TLEPropagator.sxpInitialize() Initialization proper to each propagator (SGP or SDP).
protected abstract void	TLEPropagator.sxpPropagate(double t) Propagation proper to each propagator (SGP or SDP).

Constructors in org.orekit.propagation.analytical.tle that throw OrekitException

Constructor and Description
TLE(String line1, String line2) Simple constructor from unparsed two lines.
TLEPropagator(TLE initialTLE, AttitudeProvider attitudeProvider, double mass) Protected constructor for derived classes.

Uses of OrekitException in org.orekit.propagation.conversion

Methods in org.orekit.propagation.conversion that throw OrekitException

Modifier and Type	Method and Description
Propagator	PropagatorBuilder.buildPropagator(AbsoluteDate date, double[] parameters) Build a propagator.
NumericalPropagator	NumericalPropagatorBuilder.buildPropagator(AbsoluteDate date, double[] parameters) Build a propagator.
Propagator	TLEPropagatorBuilder.buildPropagator(AbsoluteDate date, double[] parameters) Build a propagator.
Propagator	KeplerianPropagatorBuilder.buildPropagator(AbsoluteDate date, double[] parameters) Build a propagator.
Propagator	EcksteinHechlerPropagatorBuilder.buildPropagator(AbsoluteDate date, double[] parameters) Build a propagator.
SpacecraftState	OsculatingToMeanElementsConverter.convert() Convert an osculating orbit into a mean orbit, in DSST sense.
Propagator	AbstractPropagatorConverter.convert(List<SpacecraftState> states, boolean positionOnly, Collection<String> freeParameters) Find the propagator that minimize the mean square error for a sample of states.
Propagator	PropagatorConverter.convert(List<SpacecraftState> states, boolean positionOnly, Collection<String> freeParameters) Find the propagator that minimize the mean square error for a sample of states.
Propagator	AbstractPropagatorConverter.convert(List<SpacecraftState> states, boolean positionOnly, String... freeParameters) Find the propagator that minimize the mean square error for a sample of states.
Propagator	PropagatorConverter.convert(List<SpacecraftState> states, boolean positionOnly, String... freeParameters) Find the propagator that minimize the mean square error for a sample of states.
Propagator	AbstractPropagatorConverter.convert(Propagator source, double timeSpan, int nbPoints, Collection<String> freeParameters) Convert a propagator to another.
Propagator	PropagatorConverter.convert(Propagator source, double timeSpan, int nbPoints, Collection<String> freeParameters) Convert a propagator into another one.
Propagator	AbstractPropagatorConverter.convert(Propagator source, double timeSpan, int nbPoints, String... freeParameters) Convert a propagator to another.
Propagator	PropagatorConverter.convert(Propagator source, double timeSpan, int nbPoints, String... freeParameters) Convert a propagator into another one.

Constructors in org.orekit.propagation.conversion that throw OrekitException

Constructor and Description
TLEPropagatorBuilder(int satelliteNumber, char classification, int launchYear, int launchNumber, String launchPiece, int elementNumber, int revolutionNumberAtEpoch) Build a new instance.

Uses of OrekitException in org.orekit.propagation.events

Methods in org.orekit.propagation.events that throw OrekitException

Modifier and Type	Method and Description
boolean	EventState.evaluateStep(OrekitStepInterpolator interpolator) Evaluate the impact of the proposed step on the event detector.
EventHandler.Action	AbstractDetector.eventOccurred(SpacecraftState s, boolean increasing) Handle the event.
EventHandler.Action	EventDetector.eventOccurred(SpacecraftState s, boolean increasing) Handle the event.
double	GeographicZoneDetector.g(SpacecraftState s) Compute the value of the detection function.
double	DateDetector.g(SpacecraftState s) Compute the value of the switching function.
double	ApsideDetector.g(SpacecraftState s) Compute the value of the switching function.
double	NodeDetector.g(SpacecraftState s) Compute the value of the switching function.
double	EventFilter.g(SpacecraftState s) Compute the value of the switching function.
double	EclipseDetector.g(SpacecraftState s) Compute the value of the switching function.
double	AlignmentDetector.g(SpacecraftState s) Compute the value of the switching function.
double	DihedralFieldOfViewDetector.g(SpacecraftState s) Compute the value of the switching function.
double	AltitudeDetector.g(SpacecraftState s) Compute the value of the switching function.
double	CircularFieldOfViewDetector.g(SpacecraftState s) Compute the value of the switching function.
abstract double	AbstractDetector.g(SpacecraftState s) Compute the value of the switching function.
double	ElevationDetector.g(SpacecraftState s) Compute the value of the switching function.
double	EventShifter.g(SpacecraftState s) Compute the value of the switching function.
double	EventDetector.g(SpacecraftState s) Compute the value of the switching function.
void	EventState.reinitializeBegin(SpacecraftState state0, boolean isForward) Reinitialize the beginning of the step.
SpacecraftState	EventState.reset(SpacecraftState oldState) Let the event detector reset the state if it wants.
SpacecraftState	AbstractDetector.resetState(SpacecraftState oldState) Reset the state prior to continue propagation.
SpacecraftState	EventDetector.resetState(SpacecraftState oldState) Reset the state prior to continue propagation.
void	EventState.stepAccepted(SpacecraftState state) Acknowledge the fact the step has been accepted by the propagator.

Uses of OrekitException in org.orekit.propagation.events.handlers

Methods in org.orekit.propagation.events.handlers that throw OrekitException

Modifier and Type	Method and Description
EventHandler.Action	StopOnIncreasing.eventOccurred(SpacecraftState s, T detector, boolean increasing) Handle a detection event and choose what to do next.
EventHandler.Action	ContinueOnEvent.eventOccurred(SpacecraftState s, T detector, boolean increasing) Specific implementation of the eventOccurred interface.
EventHandler.Action	EventHandler.eventOccurred(SpacecraftState s, T detector, boolean increasing) eventOccurred method mirrors the same interface method as in EventDetector and its subclasses, but with an additional parameter that allows the calling method to pass in an object from the detector which would have potential additional data to allow the implementing class to determine the correct return state.
EventHandler.Action	StopOnDecreasing.eventOccurred(SpacecraftState s, T detector, boolean increasing) Handle a detection event and choose what to do next.
EventHandler.Action	StopOnEvent.eventOccurred(SpacecraftState s, T detector, boolean increasing) Specific implementation of the eventOccurred interface.
SpacecraftState	StopOnIncreasing.resetState(T detector, SpacecraftState oldState) Reset the state prior to continue propagation.
SpacecraftState	ContinueOnEvent.resetState(T detector, SpacecraftState oldState) Reset the state prior to continue propagation.
SpacecraftState	EventHandler.resetState(T detector, SpacecraftState oldState) Reset the state prior to continue propagation.
SpacecraftState	StopOnDecreasing.resetState(T detector, SpacecraftState oldState) Reset the state prior to continue propagation.
SpacecraftState	StopOnEvent.resetState(T detector, SpacecraftState oldState) Reset the state prior to continue propagation.

Uses of OrekitException in org.orekit.propagation.integration

Methods in org.orekit.propagation.integration that throw OrekitException

Modifier and Type	Method and Description
void	AbstractIntegratedPropagator.addAdditionalEquations(AdditionalEquations additional) Add a set of user-specified equations to be integrated along with the orbit propagation.
protected void	AbstractIntegratedPropagator.afterIntegration() Method called just after integration.
protected void	AbstractIntegratedPropagator.beforeIntegration(SpacecraftState initialState, AbsoluteDate tEnd) Method called just before integration.
double[]	AbstractIntegratedPropagator.MainStateEquations.computeDerivatives(SpacecraftState state) Compute differential equations for main state.
double[]	AdditionalEquations.computeDerivatives(SpacecraftState s, double[] pDot) Compute the derivatives related to the additional state parameters.
TimeStampedPVCoordinates	IntegratedEphemeris.getPVCoordinates(AbsoluteDate date, Frame frame) Get the PVCoordinates of the body in the selected frame.
abstract SpacecraftState	StateMapper.mapArrayToState(double t, double[] y, boolean meanOnly) Map the raw double components to a spacecraft state.
abstract void	StateMapper.mapStateToArray(SpacecraftState state, double[] y) Map a spacecraft state to raw double components.

Constructors in org.orekit.propagation.integration that throw OrekitException

Constructor and Description
IntegratedEphemeris(AbsoluteDate startDate, AbsoluteDate minDate, AbsoluteDate maxDate, StateMapper mapper, boolean meanOrbit, ContinuousOutputModel model, Map<String,double[]> unmanaged, List<AdditionalStateProvider> providers, String[] equations) Creates a new instance of IntegratedEphemeris.

Uses of OrekitException in org.orekit.propagation.numerical

Methods in org.orekit.propagation.numerical that throw OrekitException

Modifier and Type	Method and Description
FieldVector3D<DerivativeStructure>	Jacobianizer.accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) Compute acceleration and derivatives with respect to state.
FieldVector3D<DerivativeStructure>	Jacobianizer.accelerationDerivatives(SpacecraftState s, String paramName) Compute acceleration and derivatives with respect to parameter.
void	TimeDerivativesEquations.addAcceleration(Vector3D gamma, Frame frame) Add the contribution of an acceleration expressed in some inertial frame.
double[]	PartialDerivativesEquations.computeDerivatives(SpacecraftState s, double[] pDot) Compute the derivatives related to the additional state parameters.
JacobiansMapper	PartialDerivativesEquations.getMapper() Get a mapper between two-dimensional Jacobians and one-dimensional additional state.
void	JacobiansMapper.getParametersJacobian(SpacecraftState state, double[][] dYdP) Get theJacobian with respect to parameters from a one-dimensional additional state array.
TimeStampedPVCoordinates	NumericalPropagator.getPVCoordinates(AbsoluteDate date, Frame frame) Get the PVCoordinates of the body in the selected frame.
void	JacobiansMapper.getStateJacobian(SpacecraftState state, double[][] dYdY0) Get the Jacobian with respect to state from a one-dimensional additional state array.
SpacecraftState	PartialDerivativesEquations.setInitialJacobians(SpacecraftState s1, double[][] dY1dY0, double[][] dY1dP) Set the initial value of the Jacobian with respect to state and parameter.
SpacecraftState	PartialDerivativesEquations.setInitialJacobians(SpacecraftState s0, int stateDimension, int paramDimension) Set the initial value of the Jacobian with respect to state and parameter.

Constructors in org.orekit.propagation.numerical that throw OrekitException

Constructor and Description
PartialDerivativesEquations(String name, NumericalPropagator propagator) Simple constructor.

Uses of OrekitException in org.orekit.propagation.sampling

Methods in org.orekit.propagation.sampling that throw OrekitException

Modifier and Type	Method and Description
SpacecraftState	OrekitStepInterpolator.getInterpolatedState() Get the interpolated state.

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

Methods in org.orekit.propagation.semianalytical.dsst that throw OrekitException

Modifier and Type	Method and Description
protected void	DSSTPropagator.afterIntegration() Method called just after integration.
protected void	DSSTPropagator.beforeIntegration(SpacecraftState initialState, AbsoluteDate tEnd) Method called just before integration.
static SpacecraftState	DSSTPropagator.computeMeanState(SpacecraftState osculating, Collection<DSSTForceModel> forces) Conversion from osculating to mean, orbit.
static SpacecraftState	DSSTPropagator.computeOsculatingState(SpacecraftState mean, Collection<DSSTForceModel> forces) Conversion from mean to osculating orbit.

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

Methods in org.orekit.propagation.semianalytical.dsst.forces that throw OrekitException

Modifier and Type	Method and Description
void	AbstractGaussianContribution.computeShortPeriodicsCoefficients(SpacecraftState state) Compute the coefficients used for short periodic variations.
void	DSSTThirdBody.computeShortPeriodicsCoefficients(SpacecraftState state) Compute the coefficients used for short periodic variations.
void	DSSTCentralBody.computeShortPeriodicsCoefficients(SpacecraftState state) Compute the coefficients used for short periodic variations.
void	DSSTForceModel.computeShortPeriodicsCoefficients(SpacecraftState state) Compute the coefficients used for short periodic variations.
protected Vector3D	AbstractGaussianContribution.getAcceleration(SpacecraftState state) Compute the acceleration due to the non conservative perturbing force.
protected abstract double[]	AbstractGaussianContribution.getLLimits(SpacecraftState state) Compute the limits in L, the true longitude, for integration.
protected double[]	DSSTSolarRadiationPressure.getLLimits(SpacecraftState state) Compute the limits in L, the true longitude, for integration.
protected double[]	DSSTAtmosphericDrag.getLLimits(SpacecraftState state) Compute the limits in L, the true longitude, for integration.
double[]	AbstractGaussianContribution.getMeanElementRate(SpacecraftState state) Computes the mean equinoctial elements rates dai / dt.
double[]	DSSTThirdBody.getMeanElementRate(SpacecraftState currentState) Computes the mean equinoctial elements rates dai / dt.
double[]	DSSTCentralBody.getMeanElementRate(SpacecraftState spacecraftState) Computes the mean equinoctial elements rates dai / dt.
double[]	DSSTForceModel.getMeanElementRate(SpacecraftState state) Computes the mean equinoctial elements rates dai / dt.
double[]	AbstractGaussianContribution.getShortPeriodicVariations(AbsoluteDate date, double[] meanElements) Computes the short periodic variations.
double[]	DSSTThirdBody.getShortPeriodicVariations(AbsoluteDate date, double[] meanElements) Computes the short periodic variations.
double[]	DSSTCentralBody.getShortPeriodicVariations(AbsoluteDate date, double[] meanElements) Computes the short periodic variations.
double[]	DSSTForceModel.getShortPeriodicVariations(AbsoluteDate date, double[] meanElements) Computes the short periodic variations.
void	AbstractGaussianContribution.initialize(AuxiliaryElements aux, boolean meanOnly) Performs initialization prior to propagation for the current force model.
void	DSSTThirdBody.initialize(AuxiliaryElements aux, boolean meanOnly) Computes the highest power of the eccentricity and the highest power of a/R3 to appear in the truncated analytical power series expansion.
void	DSSTCentralBody.initialize(AuxiliaryElements aux, boolean meanOnly) Performs initialization prior to propagation for the current force model.
void	DSSTForceModel.initialize(AuxiliaryElements aux, boolean meanOnly) Performs initialization prior to propagation for the current force model.
void	AbstractGaussianContribution.initializeStep(AuxiliaryElements aux) Performs initialization at each integration step for the current force model.
void	DSSTThirdBody.initializeStep(AuxiliaryElements aux) Performs initialization at each integration step for the current force model.
void	DSSTCentralBody.initializeStep(AuxiliaryElements aux) Performs initialization at each integration step for the current force model.
void	DSSTForceModel.initializeStep(AuxiliaryElements aux) Performs initialization at each integration step for the current force model.

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

Methods in org.orekit.propagation.semianalytical.dsst.utilities that throw OrekitException

Modifier and Type	Method and Description
static double	CoefficientsFactory.getVmns(int m, int n, int s, double fns, double fnm) Get the Vn,sm coefficient from Vn,s.

Uses of OrekitException in org.orekit.time

Methods in org.orekit.time that throw OrekitException

Modifier and Type	Method and Description
static GMSTScale	TimeScalesFactory.getGMST(IERSConventions conventions, boolean simpleEOP) Get the Greenwich Mean Sidereal Time scale.
static UT1Scale	TimeScalesFactory.getUT1(EOPHistory history) Get the Universal Time 1 scale.
static UT1Scale	TimeScalesFactory.getUT1(IERSConventions conventions, boolean simpleEOP) Get the Universal Time 1 scale.
static UTCScale	TimeScalesFactory.getUTC() Get the Universal Time Coordinate scale.
T	TimeInterpolable.interpolate(AbsoluteDate date, Collection<T> sample) Get an interpolated instance.
static AbsoluteDate	AbsoluteDate.parseCCSDSCalendarSegmentedTimeCode(byte preambleField, byte[] timeField) Build an instance from a CCSDS Calendar Segmented Time Code (CCS).
static AbsoluteDate	AbsoluteDate.parseCCSDSDaySegmentedTimeCode(byte preambleField, byte[] timeField, DateComponents agencyDefinedEpoch) Build an instance from a CCSDS Day Segmented Time Code (CDS).
static AbsoluteDate	AbsoluteDate.parseCCSDSUnsegmentedTimeCode(byte preambleField1, byte preambleField2, byte[] timeField, AbsoluteDate agencyDefinedEpoch) Build an instance from a CCSDS Unsegmented Time Code (CUC).

Uses of OrekitException in org.orekit.utils

Methods in org.orekit.utils that throw OrekitException

Modifier and Type	Method and Description
abstract TimeFunction<double[]>	IERSConventions.getEOPTidalCorrection() Get the function computing tidal corrections for Earth Orientation Parameters.
abstract TimeFunction<DerivativeStructure>	IERSConventions.getGASTFunction(TimeScale ut1, EOPHistory eopHistory) Get the function computing Greenwich apparent sidereal time, in radians.
abstract TimeFunction<DerivativeStructure>	IERSConventions.getGMSTFunction(TimeScale ut1) Get the function computing Greenwich mean sidereal time, in radians.
abstract LoveNumbers	IERSConventions.getLoveNumbers() Get the Love numbers.
abstract TimeFunction<Double>	IERSConventions.getMeanObliquityFunction() Get the function computing mean obliquity of the ecliptic.
abstract FundamentalNutationArguments	IERSConventions.getNutationArguments(TimeScale timeScale) Get the fundamental nutation arguments.
IERSConventions.NutationCorrectionConverter	IERSConventions.getNutationCorrectionConverter() Create a function converting nutation corrections between δX/δY and δΔψ/δΔε.
abstract TimeFunction<double[]>	IERSConventions.getNutationFunction() Get the function computing the nutation angles.
abstract TimeFunction<double[]>	IERSConventions.getOceanPoleTide(EOPHistory eopHistory) Get the function computing ocean pole tide (ΔC₂₁, ΔS₂₁).
abstract double	IERSConventions.getPermanentTide() Get the permanent tide to be removed from ΔC₂₀ when zero-tide potentials are used.
abstract TimeFunction<double[]>	IERSConventions.getPrecessionFunction() Get the function computing the precession angles.
TimeStampedPVCoordinates	PVCoordinatesProvider.getPVCoordinates(AbsoluteDate date, Frame frame) Get the PVCoordinates of the body in the selected frame.
abstract TimeFunction<double[]>	IERSConventions.getSolidPoleTide(EOPHistory eopHistory) Get the function computing solid pole tide (ΔC₂₁, ΔS₂₁).
abstract TimeFunction<double[]>	IERSConventions.getTideFrequencyDependenceFunction(TimeScale ut1) Get the function computing frequency dependent terms (ΔC₂₀, ΔC₂₁, ΔS₂₁, ΔC₂₂, ΔS₂₂).
abstract TimeFunction<double[]>	IERSConventions.getXYSpXY2Function() Get the function computing the Celestial Intermediate Pole and Celestial Intermediate Origin components.
static TimeStampedAngularCoordinates	TimeStampedAngularCoordinates.interpolate(AbsoluteDate date, AngularDerivativesFilter filter, Collection<TimeStampedAngularCoordinates> sample) Interpolate angular coordinates.
static <T extends RealFieldElement<T>> TimeStampedFieldAngularCoordinates<T>	TimeStampedFieldAngularCoordinates.interpolate(AbsoluteDate date, AngularDerivativesFilter filter, Collection<TimeStampedFieldAngularCoordinates<T>> sample) Interpolate angular coordinates.
static AngularCoordinates	AngularCoordinates.interpolate(AbsoluteDate date, boolean useRotationRates, Collection<Pair<AbsoluteDate,AngularCoordinates>> sample) Deprecated. since 7.0 replaced with TimeStampedAngularCoordinates.interpolate(AbsoluteDate, AngularDerivativesFilter, Collection)
static <T extends RealFieldElement<T>> FieldAngularCoordinates<T>	FieldAngularCoordinates.interpolate(AbsoluteDate date, boolean useRotationRates, Collection<Pair<AbsoluteDate,FieldAngularCoordinates<T>>> sample) Deprecated. since 7.0 replaced with TimeStampedFieldAngularCoordinates.interpolate(AbsoluteDate, AngularDerivativesFilter, Collection)
void	InterpolationTableLoader.loadData(InputStream input, String name) Loads an bi-variate interpolation table from the given InputStream.
protected LoveNumbers	IERSConventions.loadLoveNumbers(String nameLove) Load the Love numbers.
FieldRotation<DerivativeStructure>	AngularCoordinates.toDerivativeStructureRotation(int order) Transform the instance to a FieldRotation<DerivativeStructure>.
FieldVector3D<DerivativeStructure>	PVCoordinates.toDerivativeStructureVector(int order) Transform the instance to a FieldVector3D<DerivativeStructure>.
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.

Constructors in org.orekit.utils that throw OrekitException

Constructor and Description
AngularCoordinates(PVCoordinates u, PVCoordinates v) Build one of the rotations that transform one pv coordinates into another one.
AngularCoordinates(PVCoordinates u1, PVCoordinates u2, PVCoordinates v1, PVCoordinates v2, double tolerance) Build the rotation that transforms a pair of pv coordinates into another one.
TimeStampedAngularCoordinates(AbsoluteDate date, PVCoordinates u, PVCoordinates v) Build one of the rotations that transform one pv coordinates into another one.
TimeStampedAngularCoordinates(AbsoluteDate date, PVCoordinates u1, PVCoordinates u2, PVCoordinates v1, PVCoordinates v2, double tolerance) Build the rotation that transforms a pair of pv coordinates into another pair.