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 Description 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
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
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).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, Vector3D p1, AbsoluteDate t1, Vector3D p2, AbsoluteDate t2)
Estimate a Keplerian orbit given two position vectors and a duration.KeplerianOrbit
IodLambert. estimate(Frame frame, boolean posigrade, int nRev, Position p1, Position p2)
Estimate an initial orbit from two position measurements. -
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)
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
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 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.
-