| 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.estimation.iod |
This package provides initial orbit determination methods.
|
| org.orekit.estimation.measurements |
The measurements package defines everything that is related to orbit
determination measurements.
|
| org.orekit.estimation.measurements.generation |
This package provides Orbit Determination measurements generation.
|
| org.orekit.files.ccsds.definitions |
This package contains definitions for CCSDS objects (frames, time systems...).
|
| org.orekit.files.ccsds.ndm.adm |
This package contains class managing CCSDS Attitude Data Message.
|
| org.orekit.files.ccsds.ndm.adm.aem |
This package contains class managing CCSDS Attitude Ephemeris Message.
|
| org.orekit.files.ccsds.ndm.adm.apm |
This package contains class managing CCSDS Attitude Parameter Message.
|
| org.orekit.files.ccsds.ndm.cdm |
This package contains class managing CCSDS Conjunction Data Message.
|
| org.orekit.files.ccsds.ndm.odm |
This package contains class managing CCSDS Orbit Data Message.
|
| org.orekit.files.ccsds.ndm.odm.ocm |
This package contains class managing CCSDS Orbit Comprehensive Message.
|
| org.orekit.files.ccsds.ndm.odm.oem |
This package contains class managing CCSDS Orbit Ephemeris Message.
|
| org.orekit.files.general |
This package provides interfaces for orbit file representations and corresponding
parsers.
|
| org.orekit.files.ilrs |
This package provides parsers for laser ranging data stored in CDR and CPF formats.
|
| org.orekit.files.sp3 |
This package provides a parser for orbit data stored in SP3 format.
|
| org.orekit.forces |
This package provides the interface for force models that will be used by the
NumericalPropagator, as well as
some classical spacecraft models for surface forces (spherical, box and solar array ...). |
| org.orekit.forces.drag |
This package provides all drag-related forces.
|
| org.orekit.forces.gravity |
This package provides all gravity-related forces.
|
| org.orekit.forces.inertia |
This package provides inertial force model.
|
| org.orekit.forces.maneuvers |
This package provides models of simple maneuvers.
|
| org.orekit.forces.maneuvers.propulsion |
This package provides propulsion models intended to be used with class
Maneuver. |
| org.orekit.forces.radiation |
This package provides all radiation pressure related forces.
|
| org.orekit.frames |
This package provides classes to handle frames and transforms between them.
|
| org.orekit.gnss.antenna |
This package provides classes related to receiver and satellites antenna modeling.
|
| org.orekit.gnss.attitude |
This package provides classes related to navigation satellites attitude modeling.
|
| org.orekit.gnss.clock |
This package provides classes related to navigation clock files.
|
| org.orekit.models.earth |
This package provides models that simulate certain physical phenomena
of Earth and the near-Earth environment.
|
| org.orekit.models.earth.atmosphere |
This package provides the atmosphere model interface and several implementations.
|
| org.orekit.models.earth.displacement |
This package provides models computing reference points
displacements on Earth surface.
|
| org.orekit.models.earth.weather |
This package provides models that simulate global weather conditions on Earth.
|
| org.orekit.orbits |
This package provides classes to represent orbits.
|
| org.orekit.propagation |
Propagation
|
| org.orekit.propagation.analytical |
Top level package for analytical propagators.
|
| org.orekit.propagation.analytical.gnss |
This package provides classes to propagate GNSS orbits.
|
| org.orekit.propagation.analytical.tle |
This package provides classes to read and extrapolate tle's.
|
| org.orekit.propagation.conversion |
This package provides tools to convert a given propagator or a set of
SpacecraftState into another propagator. |
| org.orekit.propagation.events |
This package provides interfaces and classes dealing with events occurring during propagation.
|
| org.orekit.propagation.integration |
Utilities for integration-based propagators (both numerical and semi-analytical).
|
| org.orekit.propagation.numerical |
Top level package for numerical propagators.
|
| org.orekit.propagation.semianalytical.dsst |
This package provides an implementation of the Draper Semi-analytical
Satellite Theory (DSST).
|
| org.orekit.propagation.semianalytical.dsst.forces |
This package provides force models for Draper Semi-analytical Satellite Theory (DSST).
|
| org.orekit.propagation.semianalytical.dsst.utilities |
This package provides utilities for Draper Semi-analytical Satellite Theory (DSST).
|
| org.orekit.utils |
This package provides useful objects.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
GroundPointing.getBodyFrame()
Get the body frame.
|
Frame |
FieldAttitude.getReferenceFrame()
Get the reference frame.
|
Frame |
Attitude.getReferenceFrame()
Get the reference frame.
|
| Modifier and Type | Method and Description |
|---|---|
<T extends CalculusFieldElement<T>> |
AttitudeBuilder.build(Frame frame,
FieldPVCoordinatesProvider<T> pvProv,
TimeStampedFieldAngularCoordinates<T> rawAttitude)
Build a filtered attitude.
|
<T extends CalculusFieldElement<T>> |
FixedFrameBuilder.build(Frame frame,
FieldPVCoordinatesProvider<T> pvProv,
TimeStampedFieldAngularCoordinates<T> rawAttitude)
Build a filtered attitude.
|
Attitude |
AttitudeBuilder.build(Frame frame,
PVCoordinatesProvider pvProv,
TimeStampedAngularCoordinates rawAttitude)
Build a filtered attitude.
|
Attitude |
FixedFrameBuilder.build(Frame frame,
PVCoordinatesProvider pvProv,
TimeStampedAngularCoordinates rawAttitude)
Build a filtered attitude.
|
<T extends CalculusFieldElement<T>> |
YawCompensation.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
LofOffset.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
AttitudeProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
InertialProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
FixedRate.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
AttitudesSequence.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
GroundPointing.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
SpinStabilized.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
LofOffsetPointing.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
TabulatedLofOffset.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
YawSteering.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
AggregateBoundedAttitudeProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
TabulatedProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
CelestialBodyPointed.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
YawCompensation.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
LofOffset.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AttitudeProvider.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
InertialProvider.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
FixedRate.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AttitudesSequence.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
GroundPointing.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
SpinStabilized.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
LofOffsetPointing.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
TabulatedLofOffset.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
YawSteering.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AggregateBoundedAttitudeProvider.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
TabulatedProvider.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
CelestialBodyPointed.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
YawCompensation.getBaseState(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the base system state at given date, without compensation.
|
<T extends CalculusFieldElement<T>> |
YawSteering.getBaseState(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the base system state at given date, without compensation.
|
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.
|
<T extends CalculusFieldElement<T>> |
YawCompensation.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
<T extends CalculusFieldElement<T>> |
NadirPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
abstract <T extends CalculusFieldElement<T>> |
GroundPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
<T extends CalculusFieldElement<T>> |
LofOffsetPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
<T extends CalculusFieldElement<T>> |
YawSteering.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
<T extends CalculusFieldElement<T>> |
TargetPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
<T extends CalculusFieldElement<T>> |
BodyCenterPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
TimeStampedPVCoordinates |
YawCompensation.getTargetPV(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
TimeStampedPVCoordinates |
NadirPointing.getTargetPV(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
abstract TimeStampedPVCoordinates |
GroundPointing.getTargetPV(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
TimeStampedPVCoordinates |
LofOffsetPointing.getTargetPV(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
TimeStampedPVCoordinates |
YawSteering.getTargetPV(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
TimeStampedPVCoordinates |
TargetPointing.getTargetPV(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
TimeStampedPVCoordinates |
BodyCenterPointing.getTargetPV(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
<T extends CalculusFieldElement<T>> |
YawCompensation.getYawAngle(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the yaw compensation angle at date.
|
double |
YawCompensation.getYawAngle(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the yaw compensation angle at date.
|
static AttitudeProvider |
InertialProvider.of(Frame satelliteFrame)
Creates an attitude provider aligned with the given frame.
|
FieldAttitude<T> |
FieldAttitude.withReferenceFrame(Frame newReferenceFrame)
Get a similar attitude with a specific reference frame.
|
Attitude |
Attitude.withReferenceFrame(Frame newReferenceFrame)
Get a similar attitude with a specific reference frame.
|
| Constructor and Description |
|---|
Attitude(AbsoluteDate date,
Frame referenceFrame,
AngularCoordinates orientation)
Creates a new instance.
|
Attitude(AbsoluteDate date,
Frame referenceFrame,
Rotation attitude,
Vector3D spin,
Vector3D acceleration)
Creates a new instance.
|
Attitude(Frame referenceFrame,
TimeStampedAngularCoordinates orientation)
Creates a new instance.
|
BodyCenterPointing(Frame inertialFrame,
Ellipsoid shape)
Creates new instance.
|
CelestialBodyPointed(Frame celestialFrame,
PVCoordinatesProvider pointedBody,
Vector3D phasingCel,
Vector3D pointingSat,
Vector3D phasingSat)
Creates new instance.
|
FieldAttitude(FieldAbsoluteDate<T> date,
Frame referenceFrame,
FieldAngularCoordinates<T> orientation)
Creates a new instance.
|
FieldAttitude(FieldAbsoluteDate<T> date,
Frame referenceFrame,
FieldRotation<T> attitude,
FieldVector3D<T> spin,
FieldVector3D<T> acceleration)
Creates a new instance.
|
FieldAttitude(FieldAbsoluteDate<T> date,
Frame referenceFrame,
Rotation attitude,
Vector3D spin,
Vector3D acceleration,
Field<T> field)
Creates a new instance.
|
FieldAttitude(Frame referenceFrame,
TimeStampedFieldAngularCoordinates<T> orientation)
Creates a new instance.
|
FixedFrameBuilder(Frame referenceFrame)
Creates new instance.
|
GroundPointing(Frame inertialFrame,
Frame bodyFrame)
Default constructor.
|
InertialProvider(Frame frame)
Creates new instance aligned with the given frame.
|
InertialProvider(Rotation rotation,
Frame reference)
Creates new instance with a fixed attitude in the given frame.
|
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.
|
LofOffsetPointing(Frame inertialFrame,
BodyShape shape,
AttitudeProvider attLaw,
Vector3D satPointingVector)
Creates new instance.
|
NadirPointing(Frame inertialFrame,
BodyShape shape)
Creates new instance.
|
TabulatedLofOffset(Frame inertialFrame,
LOFType type,
List<? extends TimeStampedAngularCoordinates> table,
int n,
AngularDerivativesFilter filter)
Creates new instance.
|
TabulatedLofOffset(Frame inertialFrame,
LOFType type,
List<? extends TimeStampedAngularCoordinates> table,
int n,
AngularDerivativesFilter filter,
AbsoluteDate minDate,
AbsoluteDate maxDate)
Creates new instance.
|
TabulatedProvider(Frame referenceFrame,
List<? extends TimeStampedAngularCoordinates> table,
int n,
AngularDerivativesFilter filter)
Creates new instance.
|
TargetPointing(Frame inertialFrame,
Frame bodyFrame,
Vector3D target)
Creates a new instance from body frame and target expressed in Cartesian coordinates.
|
TargetPointing(Frame inertialFrame,
GeodeticPoint targetGeo,
BodyShape shape)
Creates a new instance from body shape and target expressed in geodetic coordinates.
|
YawCompensation(Frame inertialFrame,
GroundPointing groundPointingLaw)
Creates a new instance.
|
YawSteering(Frame inertialFrame,
GroundPointing groundPointingLaw,
PVCoordinatesProvider sun,
Vector3D phasingAxis)
Creates a new instance.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
BodyShape.getBodyFrame()
Get body frame related to body shape.
|
Frame |
OneAxisEllipsoid.getBodyFrame()
Get body frame related to body shape.
|
Frame |
CelestialBody.getBodyOrientedFrame()
Get a body oriented, body centered frame.
|
Frame |
Ellipsoid.getFrame()
Get the ellipsoid central frame.
|
Frame |
Ellipse.getFrame()
Get the defining frame.
|
Frame |
CelestialBody.getInertiallyOrientedFrame()
Get an inertially oriented, body centered frame.
|
Frame |
CR3BPSystem.getRotatingFrame()
Get the CR3BP Rotating Frame.
|
| Modifier and Type | Method and Description |
|---|---|
<T extends CalculusFieldElement<T>> |
OneAxisEllipsoid.getCartesianIntersectionPoint(FieldLine<T> line,
FieldVector3D<T> close,
Frame frame,
FieldAbsoluteDate<T> date)
Get the intersection point of a line with the surface of the body.
|
Vector3D |
OneAxisEllipsoid.getCartesianIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date)
Get the intersection point of a line with the surface of the body.
|
<T extends CalculusFieldElement<T>> |
BodyShape.getIntersectionPoint(FieldLine<T> line,
FieldVector3D<T> close,
Frame frame,
FieldAbsoluteDate<T> date)
Get the intersection point of a line with the surface of the body.
|
<T extends CalculusFieldElement<T>> |
OneAxisEllipsoid.getIntersectionPoint(FieldLine<T> line,
FieldVector3D<T> close,
Frame frame,
FieldAbsoluteDate<T> date)
Get the intersection point of a line with the surface of the body.
|
GeodeticPoint |
BodyShape.getIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date)
Get the intersection point of a line with the surface of the body.
|
GeodeticPoint |
OneAxisEllipsoid.getIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date)
Get the intersection point of a line with the surface of the body.
|
AbsolutePVCoordinates |
CR3BPSystem.getRealAPV(AbsolutePVCoordinates apv0,
AbsoluteDate initialDate,
Frame outputFrame)
Get the AbsolutePVCoordinates from normalized units to standard units in an output frame.
|
TimeStampedPVCoordinates |
BodyShape.projectToGround(TimeStampedPVCoordinates pv,
Frame frame)
Project a moving point to the ground.
|
TimeStampedPVCoordinates |
OneAxisEllipsoid.projectToGround(TimeStampedPVCoordinates pv,
Frame frame)
Project a moving point to the ground.
|
Vector3D |
BodyShape.projectToGround(Vector3D point,
AbsoluteDate date,
Frame frame)
Project a point to the ground.
|
Vector3D |
OneAxisEllipsoid.projectToGround(Vector3D point,
AbsoluteDate date,
Frame frame)
Project a point to the ground.
|
<T extends CalculusFieldElement<T>> |
BodyShape.transform(FieldVector3D<T> point,
Frame frame,
FieldAbsoluteDate<T> date)
Transform a Cartesian point to a surface-relative point.
|
<T extends CalculusFieldElement<T>> |
OneAxisEllipsoid.transform(FieldVector3D<T> point,
Frame frame,
FieldAbsoluteDate<T> date)
Transform a Cartesian point to a surface-relative point.
|
FieldGeodeticPoint<DerivativeStructure> |
OneAxisEllipsoid.transform(PVCoordinates point,
Frame frame,
AbsoluteDate date)
Transform a Cartesian point to a surface-relative point.
|
GeodeticPoint |
BodyShape.transform(Vector3D point,
Frame frame,
AbsoluteDate date)
Transform a Cartesian point to a surface-relative point.
|
GeodeticPoint |
OneAxisEllipsoid.transform(Vector3D point,
Frame frame,
AbsoluteDate date)
Transform a Cartesian point to a surface-relative point.
|
| Constructor and Description |
|---|
Ellipse(Vector3D center,
Vector3D u,
Vector3D v,
double a,
double b,
Frame frame)
Simple constructor.
|
Ellipsoid(Frame frame,
double a,
double b,
double c)
Simple constructor.
|
JPLEphemeridesLoader(String supportedNames,
JPLEphemeridesLoader.EphemerisType generateType,
DataProvidersManager dataProvidersManager,
TimeScales timeScales,
Frame gcrf)
Create a loader for JPL ephemerides binary files.
|
LazyLoadedCelestialBodies(DataProvidersManager dataProvidersManager,
TimeScales timeScales,
Frame gcrf)
Create a celestial body factory with the given auxiliary data sources.
|
OneAxisEllipsoid(double ae,
double f,
Frame bodyFrame)
Simple constructor.
|
| 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.
|
CartesianOrbit |
IodLaplace.estimate(Frame frame,
PVCoordinates obsPva,
AbsoluteDate obsDate1,
Vector3D los1,
AbsoluteDate obsDate2,
Vector3D los2,
AbsoluteDate obsDate3,
Vector3D los3)
Estimate orbit from three line of sight angles from the same location.
|
CartesianOrbit |
IodLaplace.estimate(Frame frame,
PVCoordinates obsPva,
AngularRaDec raDec1,
AngularRaDec raDec2,
AngularRaDec raDec3)
Estimate the orbit from three angular observations at the same location.
|
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).
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
GroundStation.getEstimatedEarthFrame()
Get the estimated Earth frame, including the estimated linear models for pole and prime meridian.
|
Frame |
AngularRaDec.getReferenceFrame()
Get the reference frame in which the right ascension - declination angles are given.
|
| Modifier and Type | Method and Description |
|---|---|
Transform |
GroundStation.getOffsetToInertial(Frame inertial,
AbsoluteDate clockDate)
Get the transform between offset frame and inertial frame.
|
FieldTransform<Gradient> |
GroundStation.getOffsetToInertial(Frame inertial,
AbsoluteDate clockDate,
int freeParameters,
Map<String,Integer> indices)
Get the transform between offset frame and inertial frame with derivatives.
|
FieldTransform<Gradient> |
GroundStation.getOffsetToInertial(Frame inertial,
FieldAbsoluteDate<Gradient> offsetCompensatedDate,
int freeParameters,
Map<String,Integer> indices)
Get the transform between offset frame and inertial frame with derivatives.
|
| Constructor and Description |
|---|
AngularRaDec(GroundStation station,
Frame referenceFrame,
AbsoluteDate date,
double[] angular,
double[] sigma,
double[] baseWeight,
ObservableSatellite satellite)
Simple constructor.
|
| Constructor and Description |
|---|
AngularRaDecBuilder(CorrelatedRandomVectorGenerator noiseSource,
GroundStation station,
Frame referenceFrame,
double[] sigma,
double[] baseWeight,
ObservableSatellite satellite)
Simple constructor.
|
| Modifier and Type | Class and Description |
|---|---|
class |
ModifiedFrame
A reference frame created from the
REF_FRAME and CENTER_NAME is a CCSDS
OPM, OMM, or OEM file. |
| Modifier and Type | Method and Description |
|---|---|
Frame |
FrameFacade.asFrame()
Get the associated frame tree node.
|
abstract Frame |
CelestialBodyFrame.getFrame(IERSConventions conventions,
boolean simpleEOP,
DataContext dataContext)
Get the frame corresponding to the CCSDS constant.
|
| Modifier and Type | Method and Description |
|---|---|
static String |
CenterName.guessCenter(Frame frame)
Guess the name of the center of the reference frame.
|
static String |
CelestialBodyFrame.guessFrame(Frame frame)
Guesses names from ODM Table 5-3 and Annex A.
|
static CenterName |
CenterName.map(Frame frame)
Map an Orekit frame to a CCSDS center.
|
static CelestialBodyFrame |
CelestialBodyFrame.map(Frame frame)
Map an Orekit frame to a CCSDS frame.
|
static FrameFacade |
FrameFacade.map(Frame frame)
Map an Orekit frame to a CCSDS frame facade.
|
| Constructor and Description |
|---|
FrameFacade(Frame frame,
CelestialBodyFrame celestialBodyFrame,
OrbitRelativeFrame orbitRelativeFrame,
SpacecraftBodyFrame spacecraftBodyFrame,
String name)
Simple constructor.
|
ModifiedFrame(Frame frame,
CelestialBodyFrame refFrame,
CelestialBody body,
String centerName)
Create a CCSDS reference frame by changing the origin of an existing frame.
|
| Modifier and Type | Method and Description |
|---|---|
<T extends CalculusFieldElement<T>> |
AttitudeEndoints.build(Frame frame,
FieldPVCoordinatesProvider<T> pvProv,
TimeStampedFieldAngularCoordinates<T> rawAttitude)
Build a filtered attitude.
|
Attitude |
AttitudeEndoints.build(Frame frame,
PVCoordinatesProvider pvProv,
TimeStampedAngularCoordinates rawAttitude)
Build a filtered attitude.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
AemSegment.getReferenceFrame()
Get the reference frame from which attitude is defined.
|
| Modifier and Type | Method and Description |
|---|---|
Attitude |
ApmQuaternion.getAttitude(Frame frame,
PVCoordinatesProvider pvProvider)
Get the attitude.
|
Attitude |
Apm.getAttitude(Frame frame,
PVCoordinatesProvider pvProvider)
Get the attitude.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
CdmMetadata.getFrame()
Get the reference frame in which data are given: used for state vector and
Keplerian elements data (and for the covariance reference frame if none is given).
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
CommonMetadata.getFrame()
Get the reference frame in which data are given: used for state vector and
Keplerian elements data (and for the covariance reference frame if none is given).
|
| Modifier and Type | Method and Description |
|---|---|
KeplerianOrbit |
KeplerianElements.generateKeplerianOrbit(Frame frame)
Generate a keplerian orbit.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
TrajectoryStateHistory.getFrame()
Get the reference frame for this ephemeris segment.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
OemSegment.getFrame()
Get the reference frame for this ephemeris segment.
|
Frame |
OemSegment.getInertialFrame()
Get the inertial reference frame for this ephemeris segment.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
EphemerisFile.EphemerisSegment.getFrame()
Get the reference frame for this ephemeris segment.
|
Frame |
OrekitEphemerisFile.OrekitEphemerisSegment.getFrame()
Get the reference frame for this ephemeris segment.
|
default Frame |
EphemerisFile.EphemerisSegment.getInertialFrame()
Get the inertial reference frame for this ephemeris segment.
|
Frame |
OrekitEphemerisFile.OrekitEphemerisSegment.getInertialFrame()
Get the inertial reference frame for this ephemeris segment.
|
Frame |
AttitudeEphemerisFile.AttitudeEphemerisSegment.getReferenceFrame()
Get the reference frame from which attitude is defined.
|
Frame |
OrekitAttitudeEphemerisFile.OrekitAttitudeEphemerisSegment.getReferenceFrame()
Get the reference frame from which attitude is defined.
|
| Constructor and Description |
|---|
OrekitAttitudeEphemerisSegment(List<TimeStampedAngularCoordinates> attitudeDataLines,
String interpolationMethod,
int interpolationSamples,
Frame referenceFrame,
AngularDerivativesFilter availableDerivatives)
Constructor for OrekitAttitudeEphemerisSegment.
|
OrekitEphemerisSegment(List<TimeStampedPVCoordinates> coordinates,
Frame frame,
double mu,
int interpolationSamples)
constructor for OrekitEphemerisSegment.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
CPF.CPFEphemeris.getFrame()
Get the reference frame for this ephemeris segment.
|
Frame |
CPFHeader.getRefFrame()
Get the reference frame.
|
| Modifier and Type | Method and Description |
|---|---|
StreamingCpfWriter.Segment |
StreamingCpfWriter.newSegment(Frame frame)
Create a writer for a new CPF ephemeris segment.
|
void |
CPFHeader.setRefFrame(Frame refFrame)
Set the reference frame.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
SP3.SP3Ephemeris.getFrame() |
| Constructor and Description |
|---|
SP3(double mu,
int interpolationSamples,
Function<? super String,? extends Frame> frameBuilder)
Create a new SP3 file object.
|
SP3Parser(double mu,
int interpolationSamples,
Function<? super String,? extends Frame> frameBuilder)
Create an SP3 parser and specify the extra information needed to create a
Propagator from the ephemeris data. |
SP3Parser(double mu,
int interpolationSamples,
Function<? super String,? extends Frame> frameBuilder,
TimeScales timeScales)
Create an SP3 parser and specify the extra information needed to create a
Propagator from the ephemeris data. |
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
BoxAndSolarArraySpacecraft.dragAcceleration(AbsoluteDate date,
Frame frame,
Vector3D position,
Rotation rotation,
double mass,
double density,
Vector3D relativeVelocity,
double[] parameters)
Compute the acceleration due to drag.
|
<T extends CalculusFieldElement<T>> |
BoxAndSolarArraySpacecraft.dragAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
FieldVector3D<T> position,
FieldRotation<T> rotation,
T mass,
T density,
FieldVector3D<T> relativeVelocity,
T[] parameters)
Compute the acceleration due to drag.
|
Vector3D |
BoxAndSolarArraySpacecraft.getNormal(AbsoluteDate date,
Frame frame,
Vector3D position,
Rotation rotation)
Get solar array normal in spacecraft frame.
|
<T extends CalculusFieldElement<T>> |
BoxAndSolarArraySpacecraft.getNormal(FieldAbsoluteDate<T> date,
Frame frame,
FieldVector3D<T> position,
FieldRotation<T> rotation)
Get solar array normal in spacecraft frame.
|
Vector3D |
BoxAndSolarArraySpacecraft.radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
Vector3D position,
Rotation rotation,
double mass,
Vector3D flux,
double[] parameters)
Compute the acceleration due to radiation pressure.
|
<T extends CalculusFieldElement<T>> |
BoxAndSolarArraySpacecraft.radiationPressureAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
FieldVector3D<T> position,
FieldRotation<T> rotation,
T mass,
FieldVector3D<T> flux,
T[] parameters)
Compute the acceleration due to radiation pressure.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
IsotropicDrag.dragAcceleration(AbsoluteDate date,
Frame frame,
Vector3D position,
Rotation rotation,
double mass,
double density,
Vector3D relativeVelocity,
double[] parameters)
Compute the acceleration due to drag.
|
Vector3D |
DragSensitive.dragAcceleration(AbsoluteDate date,
Frame frame,
Vector3D position,
Rotation rotation,
double mass,
double density,
Vector3D relativeVelocity,
double[] parameters)
Compute the acceleration due to drag.
|
<T extends CalculusFieldElement<T>> |
IsotropicDrag.dragAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
FieldVector3D<T> position,
FieldRotation<T> rotation,
T mass,
T density,
FieldVector3D<T> relativeVelocity,
T[] parameters)
Compute the acceleration due to drag.
|
<T extends CalculusFieldElement<T>> |
DragSensitive.dragAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
FieldVector3D<T> position,
FieldRotation<T> rotation,
T mass,
T density,
FieldVector3D<T> relativeVelocity,
T[] parameters)
Compute the acceleration due to drag.
|
protected DerivativeStructure |
AbstractDragForceModel.getDSDensityWrtStateUsingFiniteDifferences(AbsoluteDate date,
Frame frame,
FieldVector3D<DerivativeStructure> position)
Compute density and its derivatives.
|
protected Gradient |
AbstractDragForceModel.getGradientDensityWrtStateUsingFiniteDifferences(AbsoluteDate date,
Frame frame,
FieldVector3D<Gradient> position)
Compute density and its derivatives.
|
| Constructor and Description |
|---|
HolmesFeatherstoneAttractionModel(Frame centralBodyFrame,
NormalizedSphericalHarmonicsProvider provider)
Creates a new instance.
|
LenseThirringRelativity(double gm,
Frame bodyFrame)
Constructor.
|
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,
boolean poleTide,
double step,
int nbPoints,
int degree,
int order,
IERSConventions conventions,
UT1Scale ut1,
GravityFields gravityFields)
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.
|
| Constructor and Description |
|---|
InertialForces(Frame referenceInertialFrame)
Simple constructor.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
SmallManeuverAnalyticalModel.getInertialFrame()
Get the inertial frame in which the velocity increment is defined.
|
| Constructor and Description |
|---|
SmallManeuverAnalyticalModel(SpacecraftState state0,
Frame frame,
Vector3D dV,
double isp)
Build a maneuver defined in user-specified frame.
|
| Modifier and Type | Method and Description |
|---|---|
static ThrustDirectionAndAttitudeProvider |
ThrustDirectionAndAttitudeProvider.buildFromDirectionInFrame(Frame thrustDirectionFrame,
ThrustDirectionProvider variableDirectionInFrame,
Vector3D thrusterAxisInSatelliteFrame)
Build a ThrustDirectionAndAttitudeProvider by a variable direction in a
custom frame.
|
Vector3D |
ThrustDirectionProvider.computeThrustDirection(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the thrust direction corresponding to an orbital state.
|
Vector3D |
ConstantThrustDirectionProvider.computeThrustDirection(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame) |
<T extends CalculusFieldElement<T>> |
ThrustDirectionAndAttitudeProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
ThrustDirectionAndAttitudeProvider.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
protected Attitude |
ThrustDirectionAndAttitudeProvider.getAttitudeFromFrame(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude for DIRECTION_IN_FRAME or DIRECTION_IN_LOF types.
|
| Modifier and Type | Method and Description |
|---|---|
<T extends CalculusFieldElement<T>> |
SolarRadiationPressure.getLightingRatio(FieldVector3D<T> position,
Frame frame,
FieldAbsoluteDate<T> date)
Get the lighting ratio ([0-1]).
|
double |
SolarRadiationPressure.getLightingRatio(Vector3D position,
Frame frame,
AbsoluteDate date)
Get the lighting ratio ([0-1]).
|
<T extends CalculusFieldElement<T>> |
SolarRadiationPressure.getTotalLightingRatio(FieldVector3D<T> position,
Frame frame,
FieldAbsoluteDate<T> date)
Get the total lighting ratio ([0-1]).
|
double |
SolarRadiationPressure.getTotalLightingRatio(Vector3D position,
Frame frame,
AbsoluteDate date)
Get the total lighting ratio ([0-1]).
|
Vector3D |
RadiationSensitive.radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
Vector3D position,
Rotation rotation,
double mass,
Vector3D flux,
double[] parameters)
Compute the acceleration due to radiation pressure.
|
Vector3D |
IsotropicRadiationSingleCoefficient.radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
Vector3D position,
Rotation rotation,
double mass,
Vector3D flux,
double[] parameters)
Compute the acceleration due to radiation pressure.
|
Vector3D |
IsotropicRadiationCNES95Convention.radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
Vector3D position,
Rotation rotation,
double mass,
Vector3D flux,
double[] parameters)
Compute the acceleration due to radiation pressure.
|
Vector3D |
IsotropicRadiationClassicalConvention.radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
Vector3D position,
Rotation rotation,
double mass,
Vector3D flux,
double[] parameters)
Compute the acceleration due to radiation pressure.
|
<T extends CalculusFieldElement<T>> |
RadiationSensitive.radiationPressureAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
FieldVector3D<T> position,
FieldRotation<T> rotation,
T mass,
FieldVector3D<T> flux,
T[] parameters)
Compute the acceleration due to radiation pressure.
|
<T extends CalculusFieldElement<T>> |
IsotropicRadiationSingleCoefficient.radiationPressureAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
FieldVector3D<T> position,
FieldRotation<T> rotation,
T mass,
FieldVector3D<T> flux,
T[] parameters)
Compute the acceleration due to radiation pressure.
|
<T extends CalculusFieldElement<T>> |
IsotropicRadiationCNES95Convention.radiationPressureAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
FieldVector3D<T> position,
FieldRotation<T> rotation,
T mass,
FieldVector3D<T> flux,
T[] parameters)
Compute the acceleration due to radiation pressure.
|
<T extends CalculusFieldElement<T>> |
IsotropicRadiationClassicalConvention.radiationPressureAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
FieldVector3D<T> position,
FieldRotation<T> rotation,
T mass,
FieldVector3D<T> flux,
T[] parameters)
Compute the acceleration due to radiation pressure.
|
| Modifier and Type | Class and Description |
|---|---|
class |
CR3BPRotatingFrame
Class creating the rotating frame centered on the barycenter of the CR3BP System.
|
class |
FactoryManagedFrame
Base class for the predefined frames that are managed by
Frames. |
class |
L1Frame
Class to create a L1 centered frame with
L1TransformProvider. |
class |
L2Frame
Class to create a L2 centered frame with
L2TransformProvider. |
class |
LocalOrbitalFrame
Class for frames moving with an orbiting satellite.
|
class |
TopocentricFrame
Topocentric frame.
|
class |
TwoBodiesBaryFrame
Class creating the inertial barycenter frame from two bodies.
|
class |
UpdatableFrame
Frame whose transform from its parent can be updated.
|
class |
VersionedITRF
Specific version of International Terrestrial Reference Frame.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
HelmertTransformation.Predefined.createTransformedITRF(Frame parent,
String name)
Create an ITRF frame by transforming another ITRF frame.
|
Frame |
HelmertTransformation.Predefined.createTransformedITRF(Frame parent,
String name,
TimeScale tt)
Create an ITRF frame by transforming another ITRF frame.
|
Frame |
Frame.getAncestor(int n)
Get the nth ancestor of the frame.
|
Frame |
Frames.getEcliptic(IERSConventions conventions)
Get the ecliptic frame.
|
Frame |
AbstractFrames.getEcliptic(IERSConventions conventions) |
static Frame |
FramesFactory.getEcliptic(IERSConventions conventions)
Get the ecliptic frame.
|
Frame |
OrphanFrame.getFrame()
Get the associated
frame. |
Frame |
Frames.getFrame(Predefined factoryKey)
Get one of the predefined frames.
|
Frame |
AbstractFrames.getFrame(Predefined factoryKey) |
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.
|
Frame |
Frames.getGCRF()
Get the unique GCRF frame.
|
Frame |
AbstractFrames.getGCRF() |
static Frame |
FramesFactory.getGCRF()
Get the unique GCRF frame.
|
Frame |
Frames.getICRF()
Get the unique ICRF frame.
|
Frame |
AbstractFrames.getICRF() |
static Frame |
FramesFactory.getICRF()
Get the unique ICRF frame.
|
Frame |
Frame.getParent()
Get the parent frame.
|
static Frame |
Frame.getRoot()
Get the unique root frame.
|
| Modifier and Type | Method and Description |
|---|---|
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.
|
Frame |
HelmertTransformation.Predefined.createTransformedITRF(Frame parent,
String name)
Create an ITRF frame by transforming another ITRF frame.
|
Frame |
HelmertTransformation.Predefined.createTransformedITRF(Frame parent,
String name,
TimeScale tt)
Create an ITRF frame by transforming another ITRF frame.
|
static EOPHistory |
FramesFactory.findEOP(Frame start)
Retrieve EOP from a frame hierarchy.
|
<T extends CalculusFieldElement<T>> |
TopocentricFrame.getAzimuth(FieldVector3D<T> extPoint,
Frame frame,
FieldAbsoluteDate<T> date)
Get the azimuth of a point with regards to the topocentric frame center point.
|
double |
TopocentricFrame.getAzimuth(Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Get the azimuth of a point with regards to the topocentric frame center point.
|
<T extends CalculusFieldElement<T>> |
TopocentricFrame.getElevation(FieldVector3D<T> extPoint,
Frame frame,
FieldAbsoluteDate<T> date)
Get the elevation of a point with regards to the local point.
|
double |
TopocentricFrame.getElevation(Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Get the elevation of a point with regards to the local point.
|
Frame |
Frame.getFrozenFrame(Frame reference,
AbsoluteDate freezingDate,
String frozenName)
Get a new version of the instance, frozen with respect to a reference frame.
|
static Transform |
FramesFactory.getNonInterpolatingTransform(Frame from,
Frame to,
AbsoluteDate date)
Get the transform between two frames, suppressing all interpolation.
|
static <T extends CalculusFieldElement<T>> |
FramesFactory.getNonInterpolatingTransform(Frame from,
Frame to,
FieldAbsoluteDate<T> 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. |
<T extends CalculusFieldElement<T>> |
TopocentricFrame.getRange(FieldVector3D<T> extPoint,
Frame frame,
FieldAbsoluteDate<T> date)
Get the range of a point with regards to the topocentric frame center point.
|
double |
TopocentricFrame.getRange(Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Get the range of a point with regards to the topocentric frame center point.
|
<T extends CalculusFieldElement<T>> |
TopocentricFrame.getRangeRate(FieldPVCoordinates<T> extPV,
Frame frame,
FieldAbsoluteDate<T> date)
Get the range rate 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.
|
StaticTransform |
Frame.getStaticTransformTo(Frame destination,
AbsoluteDate date)
Get the static portion of the transform from the instance to another
frame.
|
Transform |
Frame.getTransformTo(Frame destination,
AbsoluteDate date)
Get the transform from the instance to another frame.
|
<T extends CalculusFieldElement<T>> |
Frame.getTransformTo(Frame destination,
FieldAbsoluteDate<T> date)
Get the transform from the instance to another frame.
|
boolean |
Frame.isChildOf(Frame potentialAncestor)
Determine if a Frame is a child of another one.
|
void |
UpdatableFrame.updateTransform(Frame f1,
Frame f2,
Transform f1Tof2,
AbsoluteDate date)
Update the transform from parent frame implicitly according to two other
frames.
|
| Modifier and Type | Method and Description |
|---|---|
static Frames |
Frames.of(TimeScales timeScales,
Supplier<Frame> icrfSupplier)
Create a set of frames from the given data.
|
| Constructor and Description |
|---|
FactoryManagedFrame(Frame parent,
TransformProvider transformProvider,
boolean pseudoInertial,
Predefined factoryKey)
Simple constructor.
|
Frame(Frame parent,
TransformProvider transformProvider,
String name)
Build a non-inertial frame from its transform with respect to its parent.
|
Frame(Frame parent,
TransformProvider transformProvider,
String name,
boolean pseudoInertial)
Build a frame from its transform with respect to its parent.
|
Frame(Frame parent,
Transform transform,
String name)
Build a non-inertial frame from its transform with respect to its parent.
|
Frame(Frame parent,
Transform transform,
String name,
boolean pseudoInertial)
Build a frame from its transform with respect to its parent.
|
LocalOrbitalFrame(Frame parent,
LOFType type,
PVCoordinatesProvider provider,
String name)
Build a new instance.
|
UpdatableFrame(Frame parent,
Transform transform,
String name)
Build a non-inertial frame from its transform with respect to its parent.
|
UpdatableFrame(Frame parent,
Transform transform,
String name,
boolean pseudoInertial)
Build a frame from its transform with respect to its parent.
|
| Constructor and Description |
|---|
AbstractFrames(TimeScales timeScales,
Supplier<Frame> icrfSupplier)
Simple constructor.
|
| Modifier and Type | Method and Description |
|---|---|
abstract GNSSAttitudeProvider |
SatelliteType.buildAttitudeProvider(AbsoluteDate validityStart,
AbsoluteDate validityEnd,
ExtendedPVCoordinatesProvider sun,
Frame inertialFrame,
int prnNumber)
Build an attitude provider suitable for this satellite type.
|
| Constructor and Description |
|---|
BeidouGeo(AbsoluteDate validityStart,
AbsoluteDate validityEnd,
ExtendedPVCoordinatesProvider sun,
Frame inertialFrame)
Simple constructor.
|
BeidouIGSO(AbsoluteDate validityStart,
AbsoluteDate validityEnd,
ExtendedPVCoordinatesProvider sun,
Frame inertialFrame)
Simple constructor.
|
BeidouMeo(AbsoluteDate validityStart,
AbsoluteDate validityEnd,
ExtendedPVCoordinatesProvider sun,
Frame inertialFrame)
Simple constructor.
|
Galileo(double yawRate,
AbsoluteDate validityStart,
AbsoluteDate validityEnd,
ExtendedPVCoordinatesProvider sun,
Frame inertialFrame)
Simple constructor.
|
GenericGNSS(AbsoluteDate validityStart,
AbsoluteDate validityEnd,
ExtendedPVCoordinatesProvider sun,
Frame inertialFrame)
Simple constructor.
|
Glonass(double yawRate,
AbsoluteDate validityStart,
AbsoluteDate validityEnd,
ExtendedPVCoordinatesProvider sun,
Frame inertialFrame)
Simple constructor.
|
GPSBlockIIA(double yawRate,
double yawBias,
AbsoluteDate validityStart,
AbsoluteDate validityEnd,
ExtendedPVCoordinatesProvider sun,
Frame inertialFrame)
Simple constructor.
|
GPSBlockIIF(double yawRate,
double yawBias,
AbsoluteDate validityStart,
AbsoluteDate validityEnd,
ExtendedPVCoordinatesProvider sun,
Frame inertialFrame)
Simple constructor.
|
GPSBlockIIR(double yawRate,
AbsoluteDate validityStart,
AbsoluteDate validityEnd,
ExtendedPVCoordinatesProvider sun,
Frame inertialFrame)
Simple constructor.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
RinexClock.getFrame()
Get the reference frame for the station positions.
|
| Constructor and Description |
|---|
RinexClock(Function<? super String,? extends Frame> frameBuilder)
Constructor.
|
RinexClockParser(Function<? super String,? extends Frame> frameBuilder)
Create a clock file parser and specify the frame builder.
|
RinexClockParser(Function<? super String,? extends Frame> frameBuilder,
TimeScales timeScales)
Constructor, build the IGS clock file parser.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
Geoid.getBodyFrame() |
| Modifier and Type | Method and Description |
|---|---|
static ReferenceEllipsoid |
ReferenceEllipsoid.getGrs80(Frame bodyFrame)
Get the GRS80 ellipsoid, attached to the given body frame.
|
static ReferenceEllipsoid |
ReferenceEllipsoid.getIers2003(Frame bodyFrame)
Get the IERS2003 ellipsoid, attached to the given body frame.
|
static ReferenceEllipsoid |
ReferenceEllipsoid.getIers2010(Frame bodyFrame)
Get the IERS2010 ellipsoid, attached to the given body frame.
|
static ReferenceEllipsoid |
ReferenceEllipsoid.getIers96(Frame bodyFrame)
Get the IERS96 ellipsoid, attached to the given body frame.
|
<T extends CalculusFieldElement<T>> |
Geoid.getIntersectionPoint(FieldLine<T> lineInFrame,
FieldVector3D<T> closeInFrame,
Frame frame,
FieldAbsoluteDate<T> date)
Get the intersection point of a line with the surface of the body.
|
GeodeticPoint |
Geoid.getIntersectionPoint(Line lineInFrame,
Vector3D closeInFrame,
Frame frame,
AbsoluteDate date)
Get the intersection point of a line with the surface of the body.
|
static ReferenceEllipsoid |
ReferenceEllipsoid.getWgs84(Frame bodyFrame)
Get the WGS84 ellipsoid, attached to the given body frame.
|
TimeStampedPVCoordinates |
Geoid.projectToGround(TimeStampedPVCoordinates pv,
Frame frame) |
Vector3D |
Geoid.projectToGround(Vector3D point,
AbsoluteDate date,
Frame frame) |
<T extends CalculusFieldElement<T>> |
Geoid.transform(FieldVector3D<T> point,
Frame frame,
FieldAbsoluteDate<T> date)
Transform a Cartesian point to a surface-relative point.
|
GeodeticPoint |
Geoid.transform(Vector3D point,
Frame frame,
AbsoluteDate date)
Transform a Cartesian point to a surface-relative point.
|
| Constructor and Description |
|---|
ReferenceEllipsoid(double ae,
double f,
Frame bodyFrame,
double GM,
double spin)
Creates a new geodetic Reference Ellipsoid from four defining
parameters.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
DTM2000.getFrame()
Get the frame of the central body.
|
Frame |
NRLMSISE00.getFrame()
Get the frame of the central body.
|
Frame |
Atmosphere.getFrame()
Get the frame of the central body.
|
Frame |
HarrisPriester.getFrame()
Get the frame of the central body.
|
Frame |
SimpleExponentialAtmosphere.getFrame()
Get the frame of the central body.
|
Frame |
JB2008.getFrame()
Get the frame of the central body.
|
| Modifier and Type | Method and Description |
|---|---|
double |
DTM2000.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local density.
|
double |
NRLMSISE00.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local density.
|
double |
Atmosphere.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local density.
|
double |
HarrisPriester.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local density at some position.
|
double |
SimpleExponentialAtmosphere.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local density.
|
double |
JB2008.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local density.
|
<T extends CalculusFieldElement<T>> |
DTM2000.getDensity(FieldAbsoluteDate<T> date,
FieldVector3D<T> position,
Frame frame)
Get the local density.
|
<T extends CalculusFieldElement<T>> |
NRLMSISE00.getDensity(FieldAbsoluteDate<T> date,
FieldVector3D<T> position,
Frame frame)
Get the local density.
|
<T extends CalculusFieldElement<T>> |
Atmosphere.getDensity(FieldAbsoluteDate<T> date,
FieldVector3D<T> position,
Frame frame)
Get the local density.
|
<T extends CalculusFieldElement<T>> |
HarrisPriester.getDensity(FieldAbsoluteDate<T> date,
FieldVector3D<T> position,
Frame frame)
Get the local density at some position.
|
<T extends CalculusFieldElement<T>> |
SimpleExponentialAtmosphere.getDensity(FieldAbsoluteDate<T> date,
FieldVector3D<T> position,
Frame frame) |
<T extends CalculusFieldElement<T>> |
JB2008.getDensity(FieldAbsoluteDate<T> date,
FieldVector3D<T> position,
Frame frame)
Get the local density.
|
default Vector3D |
Atmosphere.getVelocity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the inertial velocity of atmosphere molecules.
|
default <T extends CalculusFieldElement<T>> |
Atmosphere.getVelocity(FieldAbsoluteDate<T> date,
FieldVector3D<T> position,
Frame frame)
Get the inertial velocity of atmosphere molecules.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
StationDisplacement.displacement(BodiesElements elements,
Frame earthFrame,
Vector3D referencePoint)
Compute displacement of a ground reference point.
|
Vector3D |
OceanLoading.displacement(BodiesElements elements,
Frame earthFrame,
Vector3D referencePoint)
Compute displacement of a ground reference point.
|
Vector3D |
TidalDisplacement.displacement(BodiesElements elements,
Frame earthFrame,
Vector3D referencePoint)
Compute displacement of a ground reference point.
|
| Constructor and Description |
|---|
GlobalPressureTemperatureModel(double latitude,
double longitude,
Frame bodyFrame)
Build a new instance.
|
GlobalPressureTemperatureModel(double latitude,
double longitude,
Frame bodyFrame,
DataContext dataContext)
Build a new instance.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
Orbit.getFrame()
Get the frame in which the orbital parameters are defined.
|
Frame |
FieldOrbit.getFrame()
Get the frame in which the orbital parameters are defined.
|
| Modifier and Type | Method and Description |
|---|---|
TimeStampedPVCoordinates |
Orbit.getPVCoordinates(AbsoluteDate otherDate,
Frame otherFrame)
Get the
PVCoordinates of the body in the selected frame. |
TimeStampedFieldPVCoordinates<T> |
FieldOrbit.getPVCoordinates(FieldAbsoluteDate<T> otherDate,
Frame otherFrame)
Get the
FieldPVCoordinates of the body in the selected frame. |
TimeStampedPVCoordinates |
Orbit.getPVCoordinates(Frame outputFrame)
Get the
TimeStampedPVCoordinates in a specified frame. |
TimeStampedFieldPVCoordinates<T> |
FieldOrbit.getPVCoordinates(Frame outputFrame)
Get the
TimeStampedPVCoordinates in a specified frame. |
abstract Orbit |
OrbitType.mapArrayToOrbit(double[] array,
double[] arrayDot,
PositionAngle type,
AbsoluteDate date,
double mu,
Frame frame)
Convert state array to orbital parameters.
|
abstract <T extends CalculusFieldElement<T>> |
OrbitType.mapArrayToOrbit(T[] array,
T[] arrayDot,
PositionAngle type,
FieldAbsoluteDate<T> date,
T mu,
Frame frame)
Convert state array to orbital parameters.
|
| Constructor and Description |
|---|
CartesianOrbit(PVCoordinates pvaCoordinates,
Frame frame,
AbsoluteDate date,
double mu)
Constructor from Cartesian parameters.
|
CartesianOrbit(TimeStampedPVCoordinates pvaCoordinates,
Frame frame,
double mu)
Constructor from Cartesian parameters.
|
CircularOrbit(double a,
double ex,
double ey,
double i,
double raan,
double alpha,
double aDot,
double exDot,
double eyDot,
double iDot,
double raanDot,
double alphaDot,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance.
|
CircularOrbit(double a,
double ex,
double ey,
double i,
double raan,
double alpha,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance.
|
CircularOrbit(PVCoordinates pvCoordinates,
Frame frame,
AbsoluteDate date,
double mu)
Constructor from Cartesian parameters.
|
CircularOrbit(TimeStampedPVCoordinates pvCoordinates,
Frame frame,
double mu)
Constructor from Cartesian parameters.
|
EquinoctialOrbit(double a,
double ex,
double ey,
double hx,
double hy,
double l,
double aDot,
double exDot,
double eyDot,
double hxDot,
double hyDot,
double lDot,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance.
|
EquinoctialOrbit(double a,
double ex,
double ey,
double hx,
double hy,
double l,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance.
|
EquinoctialOrbit(PVCoordinates pvCoordinates,
Frame frame,
AbsoluteDate date,
double mu)
Constructor from Cartesian parameters.
|
EquinoctialOrbit(TimeStampedPVCoordinates pvCoordinates,
Frame frame,
double mu)
Constructor from Cartesian parameters.
|
FieldCartesianOrbit(FieldPVCoordinates<T> pvaCoordinates,
Frame frame,
FieldAbsoluteDate<T> date,
T mu)
Constructor from Cartesian parameters.
|
FieldCartesianOrbit(TimeStampedFieldPVCoordinates<T> pvaCoordinates,
Frame frame,
T mu)
Constructor from Cartesian parameters.
|
FieldCircularOrbit(FieldPVCoordinates<T> PVCoordinates,
Frame frame,
FieldAbsoluteDate<T> date,
T mu)
Constructor from Cartesian parameters.
|
FieldCircularOrbit(TimeStampedFieldPVCoordinates<T> pvCoordinates,
Frame frame,
T mu)
Constructor from Cartesian parameters.
|
FieldCircularOrbit(T a,
T ex,
T ey,
T i,
T raan,
T alpha,
PositionAngle type,
Frame frame,
FieldAbsoluteDate<T> date,
T mu)
Creates a new instance.
|
FieldCircularOrbit(T a,
T ex,
T ey,
T i,
T raan,
T alpha,
T aDot,
T exDot,
T eyDot,
T iDot,
T raanDot,
T alphaDot,
PositionAngle type,
Frame frame,
FieldAbsoluteDate<T> date,
T mu)
Creates a new instance.
|
FieldEquinoctialOrbit(FieldPVCoordinates<T> pvCoordinates,
Frame frame,
FieldAbsoluteDate<T> date,
T mu)
Constructor from Cartesian parameters.
|
FieldEquinoctialOrbit(TimeStampedFieldPVCoordinates<T> pvCoordinates,
Frame frame,
T mu)
Constructor from Cartesian parameters.
|
FieldEquinoctialOrbit(T a,
T ex,
T ey,
T hx,
T hy,
T l,
PositionAngle type,
Frame frame,
FieldAbsoluteDate<T> date,
T mu)
Creates a new instance.
|
FieldEquinoctialOrbit(T a,
T ex,
T ey,
T hx,
T hy,
T l,
T aDot,
T exDot,
T eyDot,
T hxDot,
T hyDot,
T lDot,
PositionAngle type,
Frame frame,
FieldAbsoluteDate<T> date,
T mu)
Creates a new instance.
|
FieldKeplerianOrbit(FieldPVCoordinates<T> FieldPVCoordinates,
Frame frame,
FieldAbsoluteDate<T> date,
T mu)
Constructor from Cartesian parameters.
|
FieldKeplerianOrbit(TimeStampedFieldPVCoordinates<T> pvCoordinates,
Frame frame,
T mu)
Constructor from Cartesian parameters.
|
FieldKeplerianOrbit(T a,
T e,
T i,
T pa,
T raan,
T anomaly,
PositionAngle type,
Frame frame,
FieldAbsoluteDate<T> date,
T mu)
Creates a new instance.
|
FieldKeplerianOrbit(T a,
T e,
T i,
T pa,
T raan,
T anomaly,
T aDot,
T eDot,
T iDot,
T paDot,
T raanDot,
T anomalyDot,
PositionAngle type,
Frame frame,
FieldAbsoluteDate<T> date,
T mu)
Creates a new instance.
|
FieldOrbit(Frame frame,
FieldAbsoluteDate<T> date,
T mu)
Default constructor.
|
FieldOrbit(TimeStampedFieldPVCoordinates<T> FieldPVCoordinates,
Frame frame,
T mu)
Set the orbit from Cartesian parameters.
|
KeplerianOrbit(double a,
double e,
double i,
double pa,
double raan,
double anomaly,
double aDot,
double eDot,
double iDot,
double paDot,
double raanDot,
double anomalyDot,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance.
|
KeplerianOrbit(double a,
double e,
double i,
double pa,
double raan,
double anomaly,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance.
|
KeplerianOrbit(PVCoordinates pvCoordinates,
Frame frame,
AbsoluteDate date,
double mu)
Constructor from Cartesian parameters.
|
KeplerianOrbit(TimeStampedPVCoordinates pvCoordinates,
Frame frame,
double mu)
Constructor from Cartesian parameters.
|
Orbit(Frame frame,
AbsoluteDate date,
double mu)
Default constructor.
|
Orbit(TimeStampedPVCoordinates pvCoordinates,
Frame frame,
double mu)
Set the orbit from Cartesian parameters.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
Propagator.getFrame()
Get the frame in which the orbit is propagated.
|
Frame |
FieldPropagator.getFrame()
Get the frame in which the orbit is propagated.
|
Frame |
FieldSpacecraftState.getFrame()
Get the defining frame.
|
Frame |
SpacecraftState.getFrame()
Get the defining frame.
|
Frame |
AbstractPropagator.getFrame()
Get the frame in which the orbit is propagated.
|
Frame |
FieldAbstractPropagator.getFrame()
Get the frame in which the orbit is propagated.
|
| Modifier and Type | Method and Description |
|---|---|
TimeStampedPVCoordinates |
AbstractPropagator.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
TimeStampedFieldPVCoordinates<T> |
FieldAbstractPropagator.getPVCoordinates(FieldAbsoluteDate<T> date,
Frame frame)
Get the
FieldPVCoordinates of the body in the selected frame. |
TimeStampedFieldPVCoordinates<T> |
FieldSpacecraftState.getPVCoordinates(Frame outputFrame)
Get the
TimeStampedFieldPVCoordinates in given output frame. |
TimeStampedPVCoordinates |
SpacecraftState.getPVCoordinates(Frame outputFrame)
Get the
TimeStampedPVCoordinates in given output frame. |
| Modifier and Type | Method and Description |
|---|---|
Frame |
Ephemeris.getFrame() |
| Modifier and Type | Method and Description |
|---|---|
TimeStampedPVCoordinates |
AggregateBoundedPropagator.getPVCoordinates(AbsoluteDate date,
Frame frame) |
TimeStampedPVCoordinates |
Ephemeris.getPVCoordinates(AbsoluteDate date,
Frame f)
Get the
PVCoordinates of the body in the selected frame. |
| Modifier and Type | Method and Description |
|---|---|
Frame |
SBASPropagator.getECEF()
Gets the Earth Centered Earth Fixed frame used to propagate GNSS orbits.
|
Frame |
GLONASSAnalyticalPropagator.getECEF()
Gets the Earth Centered Earth Fixed frame used to propagate GLONASS orbits.
|
Frame |
GNSSPropagator.getECEF()
Gets the Earth Centered Earth Fixed frame used to propagate GNSS orbits according to the
Interface Control Document.
|
Frame |
SBASPropagator.getECI()
Gets the Earth Centered Inertial frame used to propagate the orbit.
|
Frame |
GLONASSAnalyticalPropagator.getECI()
Gets the Earth Centered Inertial frame used to propagate the orbit.
|
Frame |
GNSSPropagator.getECI()
Gets the Earth Centered Inertial frame used to propagate the orbit.
|
Frame |
SBASPropagator.getFrame()
Get the frame in which the orbit is propagated.
|
Frame |
GLONASSAnalyticalPropagator.getFrame()
Get the frame in which the orbit is propagated.
|
Frame |
GNSSPropagator.getFrame()
Get the frame in which the orbit is propagated.
|
| Modifier and Type | Method and Description |
|---|---|
GNSSPropagatorBuilder |
GNSSPropagatorBuilder.ecef(Frame bodyFixed)
Sets the Earth Centered Earth Fixed frame assimilated to the WGS84 ECEF.
|
GLONASSAnalyticalPropagatorBuilder |
GLONASSAnalyticalPropagatorBuilder.ecef(Frame bodyFixed)
Sets the Earth Centered Earth Fixed frame assimilated to the WGS84 ECEF.
|
SBASPropagatorBuilder |
SBASPropagatorBuilder.ecef(Frame bodyFixed)
Sets the Earth Centered Earth Fixed frame assimilated to the WGS84 ECEF.
|
GNSSPropagatorBuilder |
GNSSPropagatorBuilder.eci(Frame inertial)
Sets the Earth Centered Inertial frame used for propagation.
|
GLONASSAnalyticalPropagatorBuilder |
GLONASSAnalyticalPropagatorBuilder.eci(Frame inertial)
Sets the Earth Centered Inertial frame used for propagation.
|
SBASPropagatorBuilder |
SBASPropagatorBuilder.eci(Frame inertial)
Sets the Earth Centered Inertial frame used for propagation.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
TLEPropagator.getFrame()
Get the frame in which the orbit is propagated.
|
Frame |
FieldTLEPropagator.getFrame()
Get the frame in which the orbit is propagated.
|
| Modifier and Type | Method and Description |
|---|---|
static <T extends CalculusFieldElement<T>> |
FieldTLEPropagator.selectExtrapolator(FieldTLE<T> tle,
AttitudeProvider attitudeProvider,
T mass,
Frame teme,
T[] parameters)
Selects the extrapolator to use with the selected TLE.
|
static TLEPropagator |
TLEPropagator.selectExtrapolator(TLE tle,
AttitudeProvider attitudeProvider,
double mass,
Frame teme)
Selects the extrapolator to use with the selected TLE.
|
static <T extends CalculusFieldElement<T>> |
FieldTLE.stateToTLE(FieldSpacecraftState<T> state,
FieldTLE<T> templateTLE,
TimeScale utc,
Frame teme)
Convert Spacecraft State into TLE.
|
static <T extends CalculusFieldElement<T>> |
FieldTLE.stateToTLE(FieldSpacecraftState<T> state,
FieldTLE<T> templateTLE,
TimeScale utc,
Frame teme,
double epsilon,
int maxIterations)
Convert Spacecraft State into TLE.
|
static TLE |
TLE.stateToTLE(SpacecraftState state,
TLE templateTLE,
TimeScale utc,
Frame teme)
Convert Spacecraft State into TLE.
|
static TLE |
TLE.stateToTLE(SpacecraftState state,
TLE templateTLE,
TimeScale utc,
Frame teme,
double epsilon,
int maxIterations)
Convert Spacecraft State into TLE.
|
| Constructor and Description |
|---|
DeepSDP4(TLE initialTLE,
AttitudeProvider attitudeProvider,
double mass,
Frame teme)
Constructor for a unique initial TLE.
|
FieldDeepSDP4(FieldTLE<T> initialTLE,
AttitudeProvider attitudeProvider,
T mass,
Frame teme,
T[] parameters)
Constructor for a unique initial TLE.
|
FieldSGP4(FieldTLE<T> initialTLE,
AttitudeProvider attitudeProvider,
T mass,
Frame teme,
T[] parameters)
Constructor for a unique initial TLE.
|
FieldTLEPropagator(FieldTLE<T> initialTLE,
AttitudeProvider attitudeProvider,
T mass,
Frame teme,
T[] parameters)
Protected constructor for derived classes.
|
SGP4(TLE initialTLE,
AttitudeProvider attitudeProvider,
double mass,
Frame teme)
Constructor for a unique initial TLE.
|
TLEPropagator(TLE initialTLE,
AttitudeProvider attitudeProvider,
double mass,
Frame teme)
Protected constructor for derived classes.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
AbstractPropagatorBuilder.getFrame()
Get the frame in which the orbit is propagated.
|
protected Frame |
AbstractPropagatorConverter.getFrame()
Get the frame of the initial state.
|
Frame |
PropagatorBuilder.getFrame()
Get the frame in which the orbit is propagated.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
FieldNodeDetector.getFrame()
Get the frame in which the equator is defined.
|
Frame |
NodeDetector.getFrame()
Get the frame in which the equator is defined.
|
Frame |
GroundFieldOfViewDetector.getFrame()
Get the sensor reference frame.
|
| Constructor and Description |
|---|
FieldNodeDetector(FieldOrbit<T> orbit,
Frame frame)
Build a new instance.
|
FieldNodeDetector(T threshold,
FieldOrbit<T> orbit,
Frame frame)
Build a new instance.
|
GroundFieldOfViewDetector(Frame frame,
FieldOfView fov)
Build a new instance.
|
NodeDetector(double threshold,
Orbit orbit,
Frame frame)
Build a new instance.
|
NodeDetector(Frame frame)
Build a new instance.
|
NodeDetector(Orbit orbit,
Frame frame)
Build a new instance.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
IntegratedEphemeris.getFrame() |
Frame |
StateMapper.getFrame()
Get the inertial frame.
|
Frame |
FieldStateMapper.getFrame()
Get the inertial frame.
|
Frame |
FieldIntegratedEphemeris.getFrame() |
| Modifier and Type | Method and Description |
|---|---|
protected abstract StateMapper |
AbstractIntegratedPropagator.createMapper(AbsoluteDate referenceDate,
double mu,
OrbitType orbitType,
PositionAngle positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame)
Create a mapper between raw double components and spacecraft state.
|
protected abstract FieldStateMapper<T> |
FieldAbstractIntegratedPropagator.createMapper(FieldAbsoluteDate<T> referenceDate,
T mu,
OrbitType orbitType,
PositionAngle positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame)
Create a mapper between raw double components and spacecraft state.
|
TimeStampedPVCoordinates |
IntegratedEphemeris.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
TimeStampedFieldPVCoordinates<T> |
FieldIntegratedEphemeris.getPVCoordinates(FieldAbsoluteDate<T> date,
Frame frame)
Get the
FieldPVCoordinates of the body in the selected frame. |
| Constructor and Description |
|---|
FieldStateMapper(FieldAbsoluteDate<T> referenceDate,
T mu,
OrbitType orbitType,
PositionAngle positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame)
Simple constructor.
|
StateMapper(AbsoluteDate referenceDate,
double mu,
OrbitType orbitType,
PositionAngle positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame)
Simple constructor.
|
| Modifier and Type | Method and Description |
|---|---|
protected StateMapper |
NumericalPropagator.createMapper(AbsoluteDate referenceDate,
double mu,
OrbitType orbitType,
PositionAngle positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame)
Create a mapper between raw double components and spacecraft state.
|
protected StateMapper |
GLONASSNumericalPropagator.createMapper(AbsoluteDate referenceDate,
double mu,
OrbitType orbitType,
PositionAngle positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame) |
protected FieldStateMapper<T> |
FieldNumericalPropagator.createMapper(FieldAbsoluteDate<T> referenceDate,
T mu,
OrbitType orbitType,
PositionAngle positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame)
Create a mapper between raw double components and spacecraft state.
|
GLONASSNumericalPropagatorBuilder |
GLONASSNumericalPropagatorBuilder.eci(Frame inertial)
Sets the Earth Centered Inertial frame used for propagation.
|
TimeStampedPVCoordinates |
NumericalPropagator.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
TimeStampedFieldPVCoordinates<T> |
FieldNumericalPropagator.getPVCoordinates(FieldAbsoluteDate<T> date,
Frame frame)
Get the
FieldPVCoordinates of the body in the selected frame. |
| Constructor and Description |
|---|
GLONASSNumericalPropagator(ClassicalRungeKuttaIntegrator integrator,
GLONASSOrbitalElements glonassOrbit,
Frame eci,
AttitudeProvider provider,
double mass,
DataContext context,
boolean isAccAvailable)
Private constructor.
|
| Modifier and Type | Method and Description |
|---|---|
protected StateMapper |
DSSTPropagator.createMapper(AbsoluteDate referenceDate,
double mu,
OrbitType ignoredOrbitType,
PositionAngle ignoredPositionAngleType,
AttitudeProvider attitudeProvider,
Frame frame)
Create a mapper between raw double components and spacecraft state.
|
protected FieldStateMapper<T> |
FieldDSSTPropagator.createMapper(FieldAbsoluteDate<T> referenceDate,
T mu,
OrbitType ignoredOrbitType,
PositionAngle ignoredPositionAngleType,
AttitudeProvider attitudeProvider,
Frame frame)
Create a mapper between raw double components and spacecraft state.
|
| Constructor and Description |
|---|
DSSTTesseral(Frame centralBodyFrame,
double centralBodyRotationRate,
UnnormalizedSphericalHarmonicsProvider provider)
Simple constructor with default reference values.
|
DSSTTesseral(Frame centralBodyFrame,
double centralBodyRotationRate,
UnnormalizedSphericalHarmonicsProvider provider,
int maxDegreeTesseralSP,
int maxOrderTesseralSP,
int maxEccPowTesseralSP,
int maxFrequencyShortPeriodics,
int maxDegreeMdailyTesseralSP,
int maxOrderMdailyTesseralSP,
int maxEccPowMdailyTesseralSP)
Simple constructor.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
FieldAuxiliaryElements.getFrame()
Get the definition frame of the orbit.
|
Frame |
AuxiliaryElements.getFrame()
Get the definition frame of the orbit.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
FieldAbsolutePVCoordinates.getFrame()
Get the frame in which the coordinates are defined.
|
Frame |
AbsolutePVCoordinates.getFrame()
Get the frame in which the coordinates are defined.
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| Modifier and Type | Method and Description |
|---|---|
TimeStampedPVCoordinates |
AbsolutePVCoordinates.getPVCoordinates(AbsoluteDate otherDate,
Frame outputFrame) |
TimeStampedPVCoordinates |
PVCoordinatesProvider.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
TimeStampedFieldPVCoordinates<T> |
FieldPVCoordinatesProvider.getPVCoordinates(FieldAbsoluteDate<T> date,
Frame frame)
Get the
FieldPVCoordinates of the body in the selected frame. |
TimeStampedFieldPVCoordinates<T> |
FieldAbsolutePVCoordinates.getPVCoordinates(FieldAbsoluteDate<T> otherDate,
Frame outputFrame) |
<T extends CalculusFieldElement<T>> |
ExtendedPVCoordinatesProvider.getPVCoordinates(FieldAbsoluteDate<T> date,
Frame frame)
Get the
FieldPVCoordinates of the body in the selected frame. |
TimeStampedFieldPVCoordinates<T> |
FieldAbsolutePVCoordinates.getPVCoordinates(Frame outputFrame)
Get the TimeStampedFieldPVCoordinates in a specified frame.
|
TimeStampedPVCoordinates |
AbsolutePVCoordinates.getPVCoordinates(Frame outputFrame)
Get the TimeStampedPVCoordinates in a specified frame.
|
static AbsolutePVCoordinates |
AbsolutePVCoordinates.interpolate(Frame frame,
AbsoluteDate date,
CartesianDerivativesFilter filter,
Stream<AbsolutePVCoordinates> sample)
Interpolate position-velocity.
|
static <T extends CalculusFieldElement<T>> |
FieldAbsolutePVCoordinates.interpolate(Frame frame,
FieldAbsoluteDate<T> date,
CartesianDerivativesFilter filter,
Stream<FieldAbsolutePVCoordinates<T>> sample)
Interpolate position-velocity.
|
PVCoordinatesProvider |
TimeStampedPVCoordinates.toTaylorProvider(Frame instanceFrame)
Create a local provider using simply Taylor expansion through
TimeStampedPVCoordinates.shiftedBy(double). |
| Constructor and Description |
|---|
AbsolutePVCoordinates(Frame frame,
AbsoluteDate date,
FieldVector3D<U> p)
Builds a AbsolutePVCoordinates triplet from a
FieldVector3D<Derivative>. |
AbsolutePVCoordinates(Frame frame,
AbsoluteDate date,
PVCoordinates pva)
Build from frame, date and PVA coordinates.
|
AbsolutePVCoordinates(Frame frame,
AbsoluteDate date,
Vector3D position,
Vector3D velocity)
Build from position and velocity.
|
AbsolutePVCoordinates(Frame frame,
AbsoluteDate date,
Vector3D position,
Vector3D velocity,
Vector3D acceleration)
Build from position, velocity, acceleration.
|
AbsolutePVCoordinates(Frame frame,
TimeStampedPVCoordinates pva)
Build from frame and TimeStampedPVCoordinates.
|
FieldAbsolutePVCoordinates(Frame frame,
FieldAbsoluteDate<T> date,
FieldPVCoordinates<T> pva)
Build from frame, date and FieldPVA coordinates.
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FieldAbsolutePVCoordinates(Frame frame,
FieldAbsoluteDate<T> date,
FieldVector3D<T> position,
FieldVector3D<T> velocity)
Build from position and velocity.
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FieldAbsolutePVCoordinates(Frame frame,
FieldAbsoluteDate<T> date,
FieldVector3D<T> position,
FieldVector3D<T> velocity,
FieldVector3D<T> acceleration)
Build from position, velocity, acceleration.
|
FieldAbsolutePVCoordinates(Frame frame,
FieldAbsoluteDate<T> date,
FieldVector3D<U> p)
Builds a FieldAbsolutePVCoordinates triplet from a
FieldVector3D<DerivativeStructure>. |
FieldAbsolutePVCoordinates(Frame frame,
TimeStampedFieldPVCoordinates<T> pva)
Build from frame and TimeStampedFieldPVCoordinates.
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