Uses of Class
org.orekit.orbits.KeplerianOrbit

Packages that use KeplerianOrbit

Package	Description
org.orekit.estimation.iod	This package provides initial orbit determination methods.
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.

Uses of KeplerianOrbit in org.orekit.estimation.iod

Methods in org.orekit.estimation.iod that return KeplerianOrbit

Modifier and Type	Method and Description
KeplerianOrbit	IodGooding.estimate(Frame frame, AngularRaDec raDec1, AngularRaDec raDec2, AngularRaDec raDec3, double rho1init, double rho3init) Orbit got from three angular observations.
KeplerianOrbit	IodGooding.estimate(Frame frame, AngularRaDec raDec1, AngularRaDec raDec2, AngularRaDec raDec3, double rho1init, double rho3init, int nRev, boolean direction) Orbit got from three angular observations.
KeplerianOrbit	IodLambert.estimate(Frame frame, boolean posigrade, int nRev, Position p1, Position p2) Estimate an initial orbit from two position measurements.
KeplerianOrbit	IodLambert.estimate(Frame frame, boolean posigrade, int nRev, Vector3D p1, AbsoluteDate t1, Vector3D p2, AbsoluteDate t2) Estimate a Keplerian orbit given two position vectors and a duration.
KeplerianOrbit	IodGibbs.estimate(Frame frame, Position p1, Position p2, Position p3) Give an initial orbit estimation, assuming Keplerian motion.
KeplerianOrbit	IodGibbs.estimate(Frame frame, PV pv1, PV pv2, PV pv3) Give an initial orbit estimation, assuming Keplerian motion.
KeplerianOrbit	IodGibbs.estimate(Frame frame, Vector3D r1, AbsoluteDate date1, Vector3D r2, AbsoluteDate date2, Vector3D r3, AbsoluteDate date3) Give an initial orbit estimation, assuming Keplerian motion.
KeplerianOrbit	IodGooding.estimate(Frame frame, Vector3D O1, Vector3D O2, Vector3D O3, Vector3D lineOfSight1, AbsoluteDate dateObs1, Vector3D lineOfSight2, AbsoluteDate dateObs2, Vector3D lineOfSight3, AbsoluteDate dateObs3, double rho1init, double rho3init) Orbit got from Observed Three Lines of Sight (angles only).
KeplerianOrbit	IodGooding.estimate(Frame frame, Vector3D O1, Vector3D O2, Vector3D O3, Vector3D lineOfSight1, AbsoluteDate dateObs1, Vector3D lineOfSight2, AbsoluteDate dateObs2, Vector3D lineOfSight3, AbsoluteDate dateObs3, double rho1init, double rho3init, int nRev, boolean direction) Orbit got from Observed Three Lines of Sight (angles only).

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 and Description
KeplerianOrbit	KeplerianElements.generateKeplerianOrbit(Frame frame) 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 and 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 and 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 and Description
KeplerianOrbit	KeplerianOrbit.interpolate(AbsoluteDate date, Stream<Orbit> sample) Get an interpolated instance.
KeplerianOrbit	KeplerianOrbit.shiftedBy(double dt) Get a time-shifted orbit.
KeplerianOrbit	FieldKeplerianOrbit.toOrbit() Transforms the FieldOrbit instance into an Orbit instance.

Uses of KeplerianOrbit in org.orekit.propagation.analytical

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

Modifier and Type	Method and 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, 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.