Uses of Class
org.orekit.orbits.KeplerianOrbit

Packages that use KeplerianOrbit

Package	Description
org.orekit.control.relative	Package relative provides classes to compute typical maneuvers of relative proximity operations (RPO).
org.orekit.files.ccsds.ndm.odm	This package contains class managing CCSDS Orbit Data Message.
org.orekit.files.ccsds.ndm.odm.omm	This package contains class managing CCSDS Orbit Mean-Elements Message.
org.orekit.files.ccsds.ndm.odm.opm	This package contains class managing CCSDS Orbit Parameter Message.
org.orekit.orbits	This package provides classes to represent orbits.
org.orekit.propagation.analytical	Top level package for analytical propagators.
org.orekit.propagation.analytical.gnss.data	This package provides classes related to navigation data containing in GNSS almanacs and navigation messages.
org.orekit.propagation.analytical.tle.generation	This package provides classes related to TLE generation.

Uses of KeplerianOrbit in org.orekit.control.relative

Methods in org.orekit.control.relative that return KeplerianOrbit

Modifier and Type	Method	Description
static KeplerianOrbit	CoellipticOrbit.computeChaserOrbit(KeplerianOrbit targetOrbit, double semiMinorAxis, double xPlaneOffset, double vBarOffset, double driftPerOrbit, double xPlaneIVectorPhase)	Computes the chaser orbit to naturally circumnavigate around a target satellite in an elliptic orbit.

Methods in org.orekit.control.relative with parameters of type KeplerianOrbit

Modifier and Type	Method	Description
static KeplerianOrbit	CoellipticOrbit.computeChaserOrbit(KeplerianOrbit targetOrbit, double semiMinorAxis, double xPlaneOffset, double vBarOffset, double driftPerOrbit, double xPlaneIVectorPhase)	Computes the chaser orbit to naturally circumnavigate around a target satellite in an elliptic orbit.

Uses of KeplerianOrbit in org.orekit.files.ccsds.ndm.odm

Methods in org.orekit.files.ccsds.ndm.odm that return KeplerianOrbit

Modifier and Type	Method	Description
KeplerianOrbit	KeplerianElements.generateKeplerianOrbit(Frame frame, double defaultMu)	Generate a keplerian orbit.

Uses of KeplerianOrbit in org.orekit.files.ccsds.ndm.odm.omm

Methods in org.orekit.files.ccsds.ndm.odm.omm that return KeplerianOrbit

Modifier and Type	Method	Description
KeplerianOrbit	Omm.generateKeplerianOrbit()	Generate a keplerian orbit.

Uses of KeplerianOrbit in org.orekit.files.ccsds.ndm.odm.opm

Methods in org.orekit.files.ccsds.ndm.odm.opm that return KeplerianOrbit

Modifier and Type	Method	Description
KeplerianOrbit	Opm.generateKeplerianOrbit()	Generate a keplerian orbit.

Uses of KeplerianOrbit in org.orekit.orbits

Methods in org.orekit.orbits that return KeplerianOrbit

Modifier and Type	Method	Description
KeplerianOrbit	KeplerianOrbitFactory.createFromDrivers()	Create orbital parameters from current drivers values.
KeplerianOrbit	KeplerianOrbit.inFrame(Frame inertialFrame)	Create a new object representing the same physical orbital state, but attached to a different reference frame.
KeplerianOrbit	KeplerianOrbit.shiftedBy(double dt)	Get a time-shifted orbit.
KeplerianOrbit	KeplerianOrbit.shiftedBy(TimeOffset dt)	Get a time-shifted orbit.
KeplerianOrbit	FieldKeplerianOrbit.toOrbit()	Transforms the FieldOrbit instance into an Orbit instance.
KeplerianOrbit	KeplerianOrbit.withCachedPositionAngleType(PositionAngleType positionAngleType)	Creates a new instance with the provided type used for caching.
KeplerianOrbit	KeplerianOrbit.withKeplerianRates()	Creates a new instance such that PositionAngleBased.hasNonKeplerianRates() is false.

Methods in org.orekit.orbits that return types with arguments of type KeplerianOrbit

Modifier and Type	Method	Description
AbstractOrbitFactory<KeplerianOrbit>	KeplerianOrbit.factory(PositionAngleType positionAngleType, double positionScale)	Get a factory for the current orbit type.

Constructors in org.orekit.orbits with parameters of type KeplerianOrbit

Modifier	Constructor	Description
	FieldKeplerianOrbit(Field<T> field, KeplerianOrbit op)	Constructor from Field and KeplerianOrbit.
	KeplerianOrbitFactory(KeplerianOrbit template, double positionScale, PositionAngleType positionAngleType)	Simple constructor.

Uses of KeplerianOrbit in org.orekit.propagation.analytical

Methods in org.orekit.propagation.analytical that return KeplerianOrbit

Modifier and Type	Method	Description
static KeplerianOrbit	BrouwerLyddanePropagator.computeMeanOrbit(Orbit osculating, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double m2Value, double epsilon, int maxIterations)	Conversion from osculating to mean orbit.
static KeplerianOrbit	BrouwerLyddanePropagator.computeMeanOrbit(Orbit osculating, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double m2Value, OsculatingToMeanConverter converter)	Conversion from osculating to mean orbit.
static KeplerianOrbit	BrouwerLyddanePropagator.computeMeanOrbit(Orbit osculating, UnnormalizedSphericalHarmonicsProvider provider, double m2Value, OsculatingToMeanConverter converter)	Conversion from osculating to mean orbit.
static KeplerianOrbit	BrouwerLyddanePropagator.computeMeanOrbit(Orbit osculating, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics, double m2Value)	Conversion from osculating to mean orbit.
static KeplerianOrbit	BrouwerLyddanePropagator.computeMeanOrbit(Orbit osculating, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics, double m2Value, double epsilon, int maxIterations)	Conversion from osculating to mean orbit.
KeplerianOrbit	BrouwerLyddanePropagator.propagateOrbit(AbsoluteDate date)	Extrapolate an orbit up to a specific target date.

Uses of KeplerianOrbit in org.orekit.propagation.analytical.gnss.data

Methods in org.orekit.propagation.analytical.gnss.data that return KeplerianOrbit

Modifier and Type	Method	Description
protected KeplerianOrbit	GNSSOrbitalElementsFactory.createOrbitFromDrivers()	Create orbit from Keplerian elements drivers.
KeplerianOrbit	GNSSOrbitalElements.getOrbit()	Get the underlying Keplerian orbit.

Constructors in org.orekit.propagation.analytical.gnss.data with parameters of type KeplerianOrbit

Modifier	Constructor	Description
protected	AbstractNavigationMessage(double angularVelocity, int weeksInCycle, TimeScales timeScales, String type, int prn, GNSSDate toe, KeplerianOrbit orbit, double aDot, double deltaN0, double deltaN0Dot, double iDot, double omegaDot, double cuc, double cus, double crc, double crs, double cic, double cis, double af0, double af1, double af2, double tgd, GNSSDate toc, GNSSDate transmissionTime)	Constructor.
	BeidouAlmanac(TimeScales timeScales, int prn, GNSSDate toe, KeplerianOrbit orbit, double aDot, double deltaN0, double deltaN0Dot, double iDot, double omegaDot, double cuc, double cus, double crc, double crs, double cic, double cis, double af0, double af1, double af2, double tgd, GNSSDate toc, int health)	Build a new almanac.
	BeidouCivilianNavigationMessage(BeidouCivilianType beidouType, TimeScales timeScales, int prn, GNSSDate toe, KeplerianOrbit orbit, double aDot, double deltaN0, double deltaN0Dot, double iDot, double omegaDot, double cuc, double cus, double crc, double crs, double cic, double cis, double af0, double af1, double af2, double tgd, GNSSDate toc, GNSSDate transmissionTime, int iode, int iodc, double iscB1CD, double iscB1CP, double iscB2AD, int sisaiOe, int sisaiOcb, int sisaiOc1, int sisaiOc2, int sismai, int health, int integrityFlags, double tgdB1Cp, double tgdB2ap, double tgdB2bI, BeidouSatelliteType satelliteType)	Constructor.
	BeidouLegacyNavigationMessage(boolean d2, TimeScales timeScales, String type, int prn, GNSSDate toe, KeplerianOrbit orbit, double aDot, double deltaN0, double deltaN0Dot, double iDot, double omegaDot, double cuc, double cus, double crc, double crs, double cic, double cis, double af0, double af1, double af2, double tgd, GNSSDate toc, GNSSDate transmissionTime, int aode, int aodc, int satH1, double tgd1, double tgd2, double svAccuracy)	Constructor.
protected	CivilianNavigationMessage(boolean cnv2, double angularVelocity, int weeksInCycle, TimeScales timeScales, String type, int prn, GNSSDate toe, KeplerianOrbit orbit, double aDot, double deltaN0, double deltaN0Dot, double iDot, double omegaDot, double cuc, double cus, double crc, double crs, double cic, double cis, double af0, double af1, double af2, double tgd, GNSSDate toc, GNSSDate transmissionTime, double svAccuracy, int svHealth, double iscL1CA, double iscL1CD, double iscL1CP, double iscL2C, double iscL5I5, double iscL5Q5, int uraiEd, int uraiNed0, int uraiNed1, int uraiNed2, int flags)	Constructor.
	GalileoAlmanac(TimeScales timeScales, int prn, GNSSDate toe, KeplerianOrbit orbit, double aDot, double deltaN0, double deltaN0Dot, double iDot, double omegaDot, double cuc, double cus, double crc, double crs, double cic, double cis, double af0, double af1, double af2, double tgd, GNSSDate toc, int healthE5a, int healthE5b, int healthE1, int iod)	Build a new almanac.
	GalileoNavigationMessage(TimeScales timeScales, String type, int prn, GNSSDate toe, KeplerianOrbit orbit, double aDot, double deltaN0, double deltaN0Dot, double iDot, double omegaDot, double cuc, double cus, double crc, double crs, double cic, double cis, double af0, double af1, double af2, double tgd, GNSSDate toc, GNSSDate transmissionTime, int iodNav, int dataSource, double bgdE1E5a, double bgdE5bE1, double sisa, double svHealth)	Constructor.
protected	GNSSOrbitalElements(double angularVelocity, int weeksInCycle, TimeScales timeScales, String type, int prn, GNSSDate toe, KeplerianOrbit orbit, double aDot, double deltaN0, double deltaN0Dot, double iDot, double omegaDot, double cuc, double cus, double crc, double crs, double cic, double cis, double af0, double af1, double af2, double tgd, GNSSDate toc)	Creates a new instance.
	GPSAlmanac(TimeScales timeScales, int prn, GNSSDate toe, KeplerianOrbit orbit, double aDot, double deltaN0, double deltaN0Dot, double iDot, double omegaDot, double cuc, double cus, double crc, double crs, double cic, double cis, double af0, double af1, double af2, double tgd, GNSSDate toc, String source, int svn, int health, int ura, int satConfiguration)	Constructor.
	GPSCivilianNavigationMessage(boolean cnv2, TimeScales timeScales, String type, int prn, GNSSDate toe, KeplerianOrbit orbit, double aDot, double deltaN0, double deltaN0Dot, double iDot, double omegaDot, double cuc, double cus, double crc, double crs, double cic, double cis, double af0, double af1, double af2, double tgd, GNSSDate toc, GNSSDate transmissionTime, double svAccuracy, int svHealth, double iscL1CA, double iscL1CD, double iscL1CP, double iscL2C, double iscL5I5, double iscL5Q5, int uraiEd, int uraiNed0, int uraiNed1, int uraiNed2, int flags)	Constructor.
	GPSLegacyNavigationMessage(TimeScales timeScales, String type, int prn, GNSSDate toe, KeplerianOrbit orbit, double aDot, double deltaN0, double deltaN0Dot, double iDot, double omegaDot, double cuc, double cus, double crc, double crs, double cic, double cis, double af0, double af1, double af2, double tgd, GNSSDate toc, GNSSDate transmissionTime, int iode, int iodc, double svAccuracy, int svHealth, int fitInterval, int l2Codes, int l2PFlags)	Constructor.
protected	LegacyNavigationMessage(double angularVelocity, int weeksInCycle, TimeScales timeScales, String type, int prn, GNSSDate toe, KeplerianOrbit orbit, double aDot, double deltaN0, double deltaN0Dot, double iDot, double omegaDot, double cuc, double cus, double crc, double crs, double cic, double cis, double af0, double af1, double af2, double tgd, GNSSDate toc, GNSSDate transmissionTime, int iode, int iodc, double svAccuracy, int svHealth, int fitInterval, int l2Codes, int l2PFlags)	Constructor.
	NavICAlmanac(TimeScales timeScales, int prn, GNSSDate toe, KeplerianOrbit orbit, double aDot, double deltaN0, double deltaN0Dot, double iDot, double omegaDot, double cuc, double cus, double crc, double crs, double cic, double cis, double af0, double af1, double af2, double tgd, GNSSDate toc)	Constructor.
	NavICL1NvNavigationMessage(TimeScales timeScales, String type, int prn, GNSSDate toe, KeplerianOrbit orbit, double aDot, double deltaN0, double deltaN0Dot, double iDot, double omegaDot, double cuc, double cus, double crc, double crs, double cic, double cis, double af0, double af1, double af2, double tgd, GNSSDate toc, GNSSDate transmissionTime, int referenceSignalFlag, int urai, int l1SpsHealth, double tgdSL5, double iscSL1P, double iscL1DL1P, double iscL1PS, double iscL1DS)	Constructor.
	NavICLegacyNavigationMessage(TimeScales timeScales, String type, int prn, GNSSDate toe, KeplerianOrbit orbit, double aDot, double deltaN0, double deltaN0Dot, double iDot, double omegaDot, double cuc, double cus, double crc, double crs, double cic, double cis, double af0, double af1, double af2, double tgd, GNSSDate toc, GNSSDate transmissionTime, int iode, int iodc, double svAccuracy, int svHealth, int fitInterval, int l2Codes, int l2PFlags)	Constructor.
	QZSSAlmanac(TimeScales timeScales, int prn, GNSSDate toe, KeplerianOrbit orbit, double aDot, double deltaN0, double deltaN0Dot, double iDot, double omegaDot, double cuc, double cus, double crc, double crs, double cic, double cis, double af0, double af1, double af2, double tgd, GNSSDate toc, String source, int health)	Constructor.
	QZSSCivilianNavigationMessage(boolean cnv2, TimeScales timeScales, String type, int prn, GNSSDate toe, KeplerianOrbit orbit, double aDot, double deltaN0, double deltaN0Dot, double iDot, double omegaDot, double cuc, double cus, double crc, double crs, double cic, double cis, double af0, double af1, double af2, double tgd, GNSSDate toc, GNSSDate transmissionTime, double svAccuracy, int svHealth, double iscL1CA, double iscL1CD, double iscL1CP, double iscL2C, double iscL5I5, double iscL5Q5, int uraiEd, int uraiNed0, int uraiNed1, int uraiNed2, int flags)	Constructor.
	QZSSLegacyNavigationMessage(TimeScales timeScales, String type, int prn, GNSSDate toe, KeplerianOrbit orbit, double aDot, double deltaN0, double deltaN0Dot, double iDot, double omegaDot, double cuc, double cus, double crc, double crs, double cic, double cis, double af0, double af1, double af2, double tgd, GNSSDate toc, GNSSDate transmissionTime, int iode, int iodc, double svAccuracy, int svHealth, int fitInterval, int l2Codes, int l2PFlags)	Constructor.

Uses of KeplerianOrbit in org.orekit.propagation.analytical.tle.generation

Methods in org.orekit.propagation.analytical.tle.generation with parameters of type KeplerianOrbit

Modifier and Type	Method	Description
static TLE	TleGenerationUtil.newTLE(KeplerianOrbit keplerianOrbit, TLE templateTLE)	Builds a new TLE from Keplerian parameters and a template for TLE data.