| 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.estimation.measurements.modifiers |
This package provides measurement modifier.
|
| 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.acm |
This package contains class managing CCSDS Attitude Comprehensive 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.rinex.clock |
This package provides classes related to navigation clock files.
|
| org.orekit.files.sp3 |
This package provides a parser for orbit data stored in SP3 format.
|
| org.orekit.files.stk |
This package provides a parser for STK ephemeris files.
|
| 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.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.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.gnss.data |
This package provides classes related to navigation data containing in
GNSS almanacs and navigation messages.
|
| org.orekit.propagation.analytical.tle |
This package provides classes to read and extrapolate tle's.
|
| org.orekit.propagation.analytical.tle.generation |
This package provides classes related to TLE generation.
|
| 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.sampling |
This package provides interfaces and classes dealing with step handling during propagation.
|
| org.orekit.propagation.semianalytical.dsst |
This package provides an implementation of the Draper Semi-analytical
Satellite Theory (DSST).
|
| org.orekit.propagation.semianalytical.dsst.forces |
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 |
FieldAttitudeInterpolator.getReferenceFrame()
Get reference frame from which attitude is defined.
|
Frame |
AttitudeInterpolator.getReferenceFrame()
Get reference frame from which attitude is defined.
|
Frame |
FieldAttitude.getReferenceFrame()
Get the reference frame.
|
Frame |
Attitude.getReferenceFrame()
Get the reference frame.
|
| Modifier and Type | Method and Description |
|---|---|
<T extends org.hipparchus.CalculusFieldElement<T>> |
AttitudeBuilder.build(Frame frame,
FieldPVCoordinatesProvider<T> pvProv,
TimeStampedFieldAngularCoordinates<T> rawAttitude)
Build a filtered attitude.
|
<T extends org.hipparchus.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 org.hipparchus.CalculusFieldElement<T>> |
TorqueFree.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
TabulatedLofOffset.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
CelestialBodyPointed.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
YawSteering.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
LofOffset.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
FrameAlignedProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
FixedRate.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
TabulatedProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
AggregateBoundedAttitudeProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
AttitudeProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
AttitudesSequence.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
YawCompensation.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
LofOffsetPointing.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
SpinStabilized.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
GroundPointing.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
TorqueFree.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 |
CelestialBodyPointed.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 |
LofOffset.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
FrameAlignedProvider.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 |
TabulatedProvider.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 |
AttitudeProvider.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 |
YawCompensation.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 |
SpinStabilized.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.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
LofOffset.getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
FrameAlignedProvider.getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
AggregateBoundedAttitudeProvider.getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.
|
default <T extends org.hipparchus.CalculusFieldElement<T>> |
AttitudeProvider.getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
AttitudesSequence.getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame) |
<T extends org.hipparchus.CalculusFieldElement<T>> |
LofOffsetPointing.getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
GroundPointing.getAttitudeRotation(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.
|
org.hipparchus.geometry.euclidean.threed.Rotation |
LofOffset.getAttitudeRotation(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.
|
org.hipparchus.geometry.euclidean.threed.Rotation |
FrameAlignedProvider.getAttitudeRotation(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.
|
org.hipparchus.geometry.euclidean.threed.Rotation |
AggregateBoundedAttitudeProvider.getAttitudeRotation(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.
|
default org.hipparchus.geometry.euclidean.threed.Rotation |
AttitudeProvider.getAttitudeRotation(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.
|
org.hipparchus.geometry.euclidean.threed.Rotation |
AttitudesSequence.getAttitudeRotation(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.
|
org.hipparchus.geometry.euclidean.threed.Rotation |
LofOffsetPointing.getAttitudeRotation(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.
|
org.hipparchus.geometry.euclidean.threed.Rotation |
GroundPointing.getAttitudeRotation(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude-related rotation corresponding to an orbital state.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
YawSteering.getBaseState(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the base system state at given date, without compensation.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
YawCompensation.getBaseState(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> 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.
|
Attitude |
YawCompensation.getBaseState(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the base system state at given date, without compensation.
|
protected <T extends org.hipparchus.CalculusFieldElement<T>> |
GroundPointing.getTargetPosition(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position in specified frame.
|
protected org.hipparchus.geometry.euclidean.threed.Vector3D |
GroundPointing.getTargetPosition(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point position in specified frame.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
YawSteering.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
BodyCenterPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
NadirPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
YawCompensation.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
TargetPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
LofOffsetPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
protected abstract <T extends org.hipparchus.CalculusFieldElement<T>> |
GroundPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> 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 |
BodyCenterPointing.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.
|
TimeStampedPVCoordinates |
YawCompensation.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 |
LofOffsetPointing.getTargetPV(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
protected abstract TimeStampedPVCoordinates |
GroundPointing.getTargetPV(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
<T extends org.hipparchus.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 |
FrameAlignedProvider.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,
org.hipparchus.geometry.euclidean.threed.Rotation attitude,
org.hipparchus.geometry.euclidean.threed.Vector3D spin,
org.hipparchus.geometry.euclidean.threed.Vector3D acceleration)
Creates a new instance.
|
Attitude(Frame referenceFrame,
TimeStampedAngularCoordinates orientation)
Creates a new instance.
|
AttitudeInterpolator(Frame referenceFrame,
TimeInterpolator<TimeStampedAngularCoordinates> interpolator)
Constructor.
|
BodyCenterPointing(Frame inertialFrame,
Ellipsoid shape)
Creates new instance.
|
CelestialBodyPointed(Frame celestialFrame,
PVCoordinatesProvider pointedBody,
org.hipparchus.geometry.euclidean.threed.Vector3D phasingCel,
org.hipparchus.geometry.euclidean.threed.Vector3D pointingSat,
org.hipparchus.geometry.euclidean.threed.Vector3D phasingSat)
Creates new instance.
|
FieldAttitude(FieldAbsoluteDate<T> date,
Frame referenceFrame,
FieldAngularCoordinates<T> orientation)
Creates a new instance.
|
FieldAttitude(FieldAbsoluteDate<T> date,
Frame referenceFrame,
org.hipparchus.geometry.euclidean.threed.FieldRotation<T> attitude,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> spin,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> acceleration)
Creates a new instance.
|
FieldAttitude(FieldAbsoluteDate<T> date,
Frame referenceFrame,
org.hipparchus.geometry.euclidean.threed.Rotation attitude,
org.hipparchus.geometry.euclidean.threed.Vector3D spin,
org.hipparchus.geometry.euclidean.threed.Vector3D acceleration,
org.hipparchus.Field<T> field)
Creates a new instance.
|
FieldAttitude(Frame referenceFrame,
TimeStampedFieldAngularCoordinates<T> orientation)
Creates a new instance.
|
FieldAttitudeInterpolator(Frame referenceFrame,
FieldTimeInterpolator<TimeStampedFieldAngularCoordinates<KK>,KK> interpolator)
Constructor.
|
FixedFrameBuilder(Frame referenceFrame)
Creates new instance.
|
FrameAlignedProvider(Frame frame)
Creates new instance aligned with the given frame.
|
FrameAlignedProvider(org.hipparchus.geometry.euclidean.threed.Rotation rotation,
Frame reference)
Creates new instance with a fixed attitude in the given frame.
|
GroundPointing(Frame inertialFrame,
Frame bodyFrame)
Default constructor.
|
LofOffset(Frame inertialFrame,
LOF lof)
Create a LOF-aligned attitude.
|
LofOffset(Frame inertialFrame,
LOF lof,
org.hipparchus.geometry.euclidean.threed.RotationOrder order,
double alpha1,
double alpha2,
double alpha3)
Creates new instance.
|
LofOffsetPointing(Frame inertialFrame,
BodyShape shape,
AttitudeProvider attLaw,
org.hipparchus.geometry.euclidean.threed.Vector3D satPointingVector)
Creates new instance.
|
NadirPointing(Frame inertialFrame,
BodyShape shape)
Creates new instance.
|
TabulatedLofOffset(Frame inertialFrame,
LOF lof,
List<? extends TimeStampedAngularCoordinates> table,
int n,
AngularDerivativesFilter filter)
Creates new instance.
|
TabulatedLofOffset(Frame inertialFrame,
LOF lof,
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,
org.hipparchus.geometry.euclidean.threed.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,
org.hipparchus.geometry.euclidean.threed.Vector3D phasingAxis)
Creates a new instance.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
OneAxisEllipsoid.getBodyFrame()
Get body frame related to body shape.
|
Frame |
BodyShape.getBodyFrame()
Get body frame related to body shape.
|
Frame |
CelestialBody.getBodyOrientedFrame()
Get a body oriented, body centered frame.
|
Frame |
Ellipse.getFrame()
Get the defining frame.
|
Frame |
Ellipsoid.getFrame()
Get the ellipsoid central frame.
|
Frame |
FieldEllipse.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 org.hipparchus.CalculusFieldElement<T>> |
OneAxisEllipsoid.getCartesianIntersectionPoint(org.hipparchus.geometry.euclidean.threed.FieldLine<T> line,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> close,
Frame frame,
FieldAbsoluteDate<T> date)
Get the intersection point of a line with the surface of the body.
|
org.hipparchus.geometry.euclidean.threed.Vector3D |
OneAxisEllipsoid.getCartesianIntersectionPoint(org.hipparchus.geometry.euclidean.threed.Line line,
org.hipparchus.geometry.euclidean.threed.Vector3D close,
Frame frame,
AbsoluteDate date)
Get the intersection point of a line with the surface of the body.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
OneAxisEllipsoid.getIntersectionPoint(org.hipparchus.geometry.euclidean.threed.FieldLine<T> line,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> close,
Frame frame,
FieldAbsoluteDate<T> date)
Get the intersection point of a line with the surface of the body.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
BodyShape.getIntersectionPoint(org.hipparchus.geometry.euclidean.threed.FieldLine<T> line,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> close,
Frame frame,
FieldAbsoluteDate<T> date)
Get the intersection point of a line with the surface of the body.
|
GeodeticPoint |
OneAxisEllipsoid.getIntersectionPoint(org.hipparchus.geometry.euclidean.threed.Line line,
org.hipparchus.geometry.euclidean.threed.Vector3D close,
Frame frame,
AbsoluteDate date)
Get the intersection point of a line with the surface of the body.
|
GeodeticPoint |
BodyShape.getIntersectionPoint(org.hipparchus.geometry.euclidean.threed.Line line,
org.hipparchus.geometry.euclidean.threed.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 |
OneAxisEllipsoid.projectToGround(TimeStampedPVCoordinates pv,
Frame frame)
Project a moving point to the ground.
|
TimeStampedPVCoordinates |
BodyShape.projectToGround(TimeStampedPVCoordinates pv,
Frame frame)
Project a moving point to the ground.
|
org.hipparchus.geometry.euclidean.threed.Vector3D |
OneAxisEllipsoid.projectToGround(org.hipparchus.geometry.euclidean.threed.Vector3D point,
AbsoluteDate date,
Frame frame)
Project a point to the ground.
|
org.hipparchus.geometry.euclidean.threed.Vector3D |
BodyShape.projectToGround(org.hipparchus.geometry.euclidean.threed.Vector3D point,
AbsoluteDate date,
Frame frame)
Project a point to the ground.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
OneAxisEllipsoid.transform(org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> point,
Frame frame,
FieldAbsoluteDate<T> date)
Transform a Cartesian point to a surface-relative point.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
BodyShape.transform(org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> point,
Frame frame,
FieldAbsoluteDate<T> date)
Transform a Cartesian point to a surface-relative point.
|
FieldGeodeticPoint<org.hipparchus.analysis.differentiation.DerivativeStructure> |
OneAxisEllipsoid.transform(PVCoordinates point,
Frame frame,
AbsoluteDate date)
Transform a Cartesian point to a surface-relative point.
|
GeodeticPoint |
OneAxisEllipsoid.transform(org.hipparchus.geometry.euclidean.threed.Vector3D point,
Frame frame,
AbsoluteDate date)
Transform a Cartesian point to a surface-relative point.
|
GeodeticPoint |
BodyShape.transform(org.hipparchus.geometry.euclidean.threed.Vector3D point,
Frame frame,
AbsoluteDate date)
Transform a Cartesian point to a surface-relative point.
|
| Constructor and Description |
|---|
Ellipse(org.hipparchus.geometry.euclidean.threed.Vector3D center,
org.hipparchus.geometry.euclidean.threed.Vector3D u,
org.hipparchus.geometry.euclidean.threed.Vector3D v,
double a,
double b,
Frame frame)
Simple constructor.
|
Ellipsoid(Frame frame,
double a,
double b,
double c)
Simple constructor.
|
FieldEllipse(org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> center,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> u,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> v,
T a,
T b,
Frame frame)
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 |
|---|---|
Orbit |
IodGauss.estimate(Frame outputFrame,
AngularAzEl azEl1,
AngularAzEl azEl2,
AngularAzEl azEl3)
Estimate and orbit based on Gauss Intial Orbit Determination method.
|
Orbit |
IodLaplace.estimate(Frame outputFrame,
AngularAzEl azEl1,
AngularAzEl azEl2,
AngularAzEl azEl3)
Estimate the orbit from three angular observations at the same location.
|
Orbit |
IodGooding.estimate(Frame outputFrame,
AngularAzEl azEl1,
AngularAzEl azEl2,
AngularAzEl azEl3,
double rho1init,
double rho3init)
Estimate orbit from three angular observations.
|
Orbit |
IodGooding.estimate(Frame outputFrame,
AngularAzEl azEl1,
AngularAzEl azEl2,
AngularAzEl azEl3,
double rho1init,
double rho3init,
int nRev,
boolean direction)
Estimate orbit from three angular observations.
|
Orbit |
IodGauss.estimate(Frame outputFrame,
AngularRaDec raDec1,
AngularRaDec raDec2,
AngularRaDec raDec3)
Estimate and orbit based on Gauss Intial Orbit Determination method.
|
Orbit |
IodLaplace.estimate(Frame outputFrame,
AngularRaDec raDec1,
AngularRaDec raDec2,
AngularRaDec raDec3)
Estimate the orbit from three angular observations at the same location.
|
Orbit |
IodGooding.estimate(Frame outputFrame,
AngularRaDec raDec1,
AngularRaDec raDec2,
AngularRaDec raDec3,
double rho1init,
double rho3init)
Estimate orbit from three angular observations.
|
Orbit |
IodGooding.estimate(Frame outputFrame,
AngularRaDec raDec1,
AngularRaDec raDec2,
AngularRaDec raDec3,
double rho1init,
double rho3init,
int nRev,
boolean direction)
Estimate orbit from three angular observations.
|
Orbit |
IodLambert.estimate(Frame frame,
boolean posigrade,
int nRev,
Position p1,
Position p2)
Estimate an initial orbit from two position measurements.
|
Orbit |
IodLambert.estimate(Frame frame,
boolean posigrade,
int nRev,
PV pv1,
PV pv2)
Estimate an initial orbit from two PV measurements.
|
Orbit |
IodLambert.estimate(Frame frame,
boolean posigrade,
int nRev,
org.hipparchus.geometry.euclidean.threed.Vector3D p1,
AbsoluteDate t1,
org.hipparchus.geometry.euclidean.threed.Vector3D p2,
AbsoluteDate t2)
Estimate a Keplerian orbit given two position vectors and a duration.
|
Orbit |
IodGibbs.estimate(Frame frame,
Position p1,
Position p2,
Position p3)
Give an initial orbit estimation, assuming Keplerian motion.
|
Orbit |
IodLaplace.estimate(Frame outputFrame,
PVCoordinates obsPva,
AbsoluteDate obsDate1,
org.hipparchus.geometry.euclidean.threed.Vector3D los1,
AbsoluteDate obsDate2,
org.hipparchus.geometry.euclidean.threed.Vector3D los2,
AbsoluteDate obsDate3,
org.hipparchus.geometry.euclidean.threed.Vector3D los3)
Estimate orbit from three line of sight angles at the same location.
|
Orbit |
IodGibbs.estimate(Frame frame,
PV pv1,
PV pv2,
PV pv3)
Give an initial orbit estimation, assuming Keplerian motion.
|
Orbit |
IodGibbs.estimate(Frame frame,
org.hipparchus.geometry.euclidean.threed.Vector3D r1,
AbsoluteDate date1,
org.hipparchus.geometry.euclidean.threed.Vector3D r2,
AbsoluteDate date2,
org.hipparchus.geometry.euclidean.threed.Vector3D r3,
AbsoluteDate date3)
Give an initial orbit estimation, assuming Keplerian motion.
|
Orbit |
IodGauss.estimate(Frame outputFrame,
org.hipparchus.geometry.euclidean.threed.Vector3D obsP1,
AbsoluteDate obsDate1,
org.hipparchus.geometry.euclidean.threed.Vector3D los1,
org.hipparchus.geometry.euclidean.threed.Vector3D obsP2,
AbsoluteDate obsDate2,
org.hipparchus.geometry.euclidean.threed.Vector3D los2,
org.hipparchus.geometry.euclidean.threed.Vector3D obsP3,
AbsoluteDate obsDate3,
org.hipparchus.geometry.euclidean.threed.Vector3D los3)
Estimate and orbit based on Gauss Intial Orbit Determination method.
|
Orbit |
IodGooding.estimate(Frame outputFrame,
org.hipparchus.geometry.euclidean.threed.Vector3D O1,
org.hipparchus.geometry.euclidean.threed.Vector3D O2,
org.hipparchus.geometry.euclidean.threed.Vector3D O3,
org.hipparchus.geometry.euclidean.threed.Vector3D lineOfSight1,
AbsoluteDate dateObs1,
org.hipparchus.geometry.euclidean.threed.Vector3D lineOfSight2,
AbsoluteDate dateObs2,
org.hipparchus.geometry.euclidean.threed.Vector3D lineOfSight3,
AbsoluteDate dateObs3,
double rho1init,
double rho3init)
Estimate orbit from three line of sight.
|
Orbit |
IodGooding.estimate(Frame outputFrame,
org.hipparchus.geometry.euclidean.threed.Vector3D O1,
org.hipparchus.geometry.euclidean.threed.Vector3D O2,
org.hipparchus.geometry.euclidean.threed.Vector3D O3,
org.hipparchus.geometry.euclidean.threed.Vector3D lineOfSight1,
AbsoluteDate dateObs1,
org.hipparchus.geometry.euclidean.threed.Vector3D lineOfSight2,
AbsoluteDate dateObs2,
org.hipparchus.geometry.euclidean.threed.Vector3D lineOfSight3,
AbsoluteDate dateObs3,
double rho1init,
double rho3init,
int nRev,
boolean direction)
Estimate orbit from three line of sight.
|
| 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 |
|---|---|
PVCoordinates |
GroundReceiverMeasurement.getGroundStationCoordinates(Frame frame)
Get the station coordinates for a given frame.
|
org.hipparchus.geometry.euclidean.threed.Vector3D |
GroundReceiverMeasurement.getGroundStationPosition(Frame frame)
Get the station position for a given frame.
|
org.hipparchus.geometry.euclidean.threed.Vector3D |
AngularAzEl.getObservedLineOfSight(Frame outputFrame)
Calculate the Line Of Sight of the given measurement.
|
org.hipparchus.geometry.euclidean.threed.Vector3D |
AngularRaDec.getObservedLineOfSight(Frame outputFrame)
Calculate the Line Of Sight of the given measurement.
|
Transform |
GroundStation.getOffsetToInertial(Frame inertial,
AbsoluteDate date,
boolean clockOffsetAlreadyApplied)
Get the transform between offset frame and inertial frame.
|
FieldTransform<org.hipparchus.analysis.differentiation.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<org.hipparchus.analysis.differentiation.Gradient> |
GroundStation.getOffsetToInertial(Frame inertial,
FieldAbsoluteDate<org.hipparchus.analysis.differentiation.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(org.hipparchus.random.CorrelatedRandomVectorGenerator noiseSource,
GroundStation station,
Frame referenceFrame,
double[] sigma,
double[] baseWeight,
ObservableSatellite satellite)
Simple constructor.
|
| Modifier and Type | Method and Description |
|---|---|
static org.hipparchus.analysis.differentiation.Gradient[] |
AberrationModifier.fieldNaturalToProper(org.hipparchus.analysis.differentiation.Gradient[] naturalRaDec,
FieldTransform<org.hipparchus.analysis.differentiation.Gradient> stationToInertial,
Frame frame)
Natural to proper correction for aberration of light.
|
static org.hipparchus.analysis.differentiation.Gradient[] |
AberrationModifier.fieldNaturalToProper(org.hipparchus.analysis.differentiation.Gradient[] naturalRaDec,
FieldTransform<org.hipparchus.analysis.differentiation.Gradient> stationToInertial,
Frame frame,
DataContext context)
Natural to proper correction for aberration of light.
|
static org.hipparchus.analysis.differentiation.Gradient[] |
AberrationModifier.fieldProperToNatural(org.hipparchus.analysis.differentiation.Gradient[] properRaDec,
FieldTransform<org.hipparchus.analysis.differentiation.Gradient> stationToInertial,
Frame frame)
Proper to natural correction for aberration of light.
|
static org.hipparchus.analysis.differentiation.Gradient[] |
AberrationModifier.fieldProperToNatural(org.hipparchus.analysis.differentiation.Gradient[] properRaDec,
FieldTransform<org.hipparchus.analysis.differentiation.Gradient> stationToInertial,
Frame frame,
DataContext context)
Proper to natural correction for aberration of light.
|
static double[] |
AberrationModifier.naturalToProper(double[] naturalRaDec,
GroundStation station,
AbsoluteDate date,
Frame frame)
Natural to proper correction for aberration of light.
|
static double[] |
AberrationModifier.naturalToProper(double[] naturalRaDec,
GroundStation station,
AbsoluteDate date,
Frame frame,
DataContext context)
Natural to proper correction for aberration of light.
|
static double[] |
AberrationModifier.properToNatural(double[] properRaDec,
GroundStation station,
AbsoluteDate date,
Frame frame)
Proper to natural correction for aberration of light.
|
static double[] |
AberrationModifier.properToNatural(double[] properRaDec,
GroundStation station,
AbsoluteDate date,
Frame frame,
DataContext context)
Proper to natural correction for aberration of light.
|
| 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 Transform |
FrameFacade.getTransform(FrameFacade frameIn,
FrameFacade frameOut,
Frame inertialPivotFrame,
AbsoluteDate date,
PVCoordinatesProvider pv)
Get the transform between
CCSDS frames. |
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 FrameFacade |
FrameFacade.map(Frame frame)
Map an Orekit frame to a CCSDS frame facade.
|
static CelestialBodyFrame |
CelestialBodyFrame.map(Frame frame)
Map an Orekit frame to a CCSDS frame.
|
| 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 org.hipparchus.CalculusFieldElement<T>> |
AttitudeEndpoints.build(Frame frame,
FieldPVCoordinatesProvider<T> pvProv,
TimeStampedFieldAngularCoordinates<T> rawAttitude)
Build a filtered attitude.
|
Attitude |
AttitudeEndpoints.build(Frame frame,
PVCoordinatesProvider pvProv,
TimeStampedAngularCoordinates rawAttitude)
Build a filtered attitude.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
AttitudeStateHistory.getReferenceFrame()
Get the reference frame from which attitude is defined.
|
| 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 |
Apm.getAttitude(Frame frame,
PVCoordinatesProvider pvProvider)
Get the attitude.
|
Attitude |
ApmData.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 |
OdmCommonMetadata.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 |
|---|---|
double[] |
OrbitElementsType.toRawElements(TimeStampedPVCoordinates pv,
Frame frame,
OneAxisEllipsoid body,
double mu)
Convert to raw elements array.
|
| 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 |
OrekitEphemerisFile.OrekitEphemerisSegment.getFrame()
Get the reference frame for this ephemeris segment.
|
Frame |
EphemerisFile.EphemerisSegment.getFrame()
Get the reference frame for this ephemeris segment.
|
Frame |
OrekitEphemerisFile.OrekitEphemerisSegment.getInertialFrame()
Get the inertial reference frame for this ephemeris segment.
|
default Frame |
EphemerisFile.EphemerisSegment.getInertialFrame()
Get the inertial reference frame for this ephemeris segment.
|
Frame |
OrekitAttitudeEphemerisFile.OrekitAttitudeEphemerisSegment.getReferenceFrame()
Get the reference frame from which attitude is defined.
|
Frame |
AttitudeEphemerisFile.AttitudeEphemerisSegment.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 |
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 |
SP3Ephemeris.getFrame()
Get the reference frame.
|
Frame |
SP3Segment.getFrame()
Get the reference frame for this ephemeris segment.
|
| Constructor and Description |
|---|
SP3(double mu,
int interpolationSamples,
Frame frame)
Create a new SP3 file object.
|
SP3Ephemeris(String id,
double mu,
Frame frame,
int interpolationSamples,
CartesianDerivativesFilter filter)
Create an ephemeris for a single satellite.
|
SP3Segment(double mu,
Frame frame,
int interpolationSamples,
CartesianDerivativesFilter filter)
Simple constructor.
|
| Constructor and Description |
|---|
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 |
|---|---|
Frame |
STKEphemerisFile.STKEphemerisSegment.getFrame() |
| Constructor and Description |
|---|
STKEphemerisSegment(double mu,
Frame frame,
int interpolationSamples,
CartesianDerivativesFilter cartesianDerivativesFilter,
List<TimeStampedPVCoordinates> timeStampedPVCoordinates)
Constructs a
STKEphemerisFile.STKEphemerisSegment instance. |
| Constructor and Description |
|---|
STKEphemerisFileParser(String satelliteId,
double mu,
UTCScale utc,
Map<STKEphemerisFile.STKCoordinateSystem,Frame> frameMapping)
Constructs a
STKEphemerisFileParser instance. |
| Modifier and Type | Method and Description |
|---|---|
protected org.hipparchus.analysis.differentiation.DerivativeStructure |
AbstractDragForceModel.getDSDensityWrtStateUsingFiniteDifferences(AbsoluteDate date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure> position)
Compute density and its derivatives.
|
protected org.hipparchus.analysis.differentiation.Gradient |
AbstractDragForceModel.getGradientDensityWrtStateUsingFiniteDifferences(AbsoluteDate date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.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,
org.hipparchus.geometry.euclidean.threed.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,
org.hipparchus.geometry.euclidean.threed.Vector3D thrusterAxisInSatelliteFrame)
Build a ThrustDirectionAndAttitudeProvider by a variable direction in a
custom frame.
|
org.hipparchus.geometry.euclidean.threed.Vector3D |
ConstantThrustDirectionProvider.computeThrustDirection(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame) |
org.hipparchus.geometry.euclidean.threed.Vector3D |
ThrustDirectionProvider.computeThrustDirection(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the thrust direction corresponding to an orbital state.
|
<T extends org.hipparchus.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 | 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 |
|---|---|
static Frame |
FramesFactory.buildUncachedITRF(EOPHistory eopHistory,
UTCScale utc)
Build an uncached International Terrestrial Reference Frame with specific
EOP history. |
Frame |
AbstractFrames.buildUncachedITRF(UT1Scale ut1) |
Frame |
Frames.buildUncachedITRF(UT1Scale ut1)
Build an uncached International Terrestrial Reference Frame with specific
EOP history. |
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 |
AbstractFrames.getEcliptic(IERSConventions conventions) |
Frame |
Frames.getEcliptic(IERSConventions conventions)
Get the ecliptic frame.
|
static Frame |
FramesFactory.getEcliptic(IERSConventions conventions)
Get the ecliptic frame.
|
Frame |
OrphanFrame.getFrame()
Get the associated
frame. |
Frame |
AbstractFrames.getFrame(Predefined factoryKey) |
Frame |
Frames.getFrame(Predefined factoryKey)
Get one of the predefined frames.
|
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 |
AbstractFrames.getGCRF() |
Frame |
Frames.getGCRF()
Get the unique GCRF frame.
|
static Frame |
FramesFactory.getGCRF()
Get the unique GCRF frame.
|
Frame |
AbstractFrames.getICRF() |
Frame |
Frames.getICRF()
Get the unique ICRF frame.
|
static Frame |
FramesFactory.getICRF()
Get the unique ICRF frame.
|
Frame |
LocalMagneticFieldFrame.getInertialFrame()
Get interlai 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 org.hipparchus.CalculusFieldElement<T>> |
TopocentricFrame.getAzimuth(org.hipparchus.geometry.euclidean.threed.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(org.hipparchus.geometry.euclidean.threed.Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Get the azimuth of a point with regards to the topocentric frame center point.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
TopocentricFrame.getElevation(org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> extPoint,
Frame frame,
FieldAbsoluteDate<T> date)
Get the elevation of a point with regards to the local point.
|
double |
TopocentricFrame.getElevation(org.hipparchus.geometry.euclidean.threed.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 org.hipparchus.CalculusFieldElement<T>> |
FramesFactory.getNonInterpolatingTransform(Frame from,
Frame to,
FieldAbsoluteDate<T> date)
Get the transform between two frames, suppressing all interpolation.
|
org.hipparchus.geometry.euclidean.threed.Vector3D |
TopocentricFrame.getPosition(AbsoluteDate date,
Frame frame)
Get the position of the body in the selected frame.
|
TimeStampedPVCoordinates |
TopocentricFrame.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the topocentric frame origin in the selected frame. |
<T extends org.hipparchus.CalculusFieldElement<T>> |
TopocentricFrame.getRange(org.hipparchus.geometry.euclidean.threed.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(org.hipparchus.geometry.euclidean.threed.Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Get the range of a point with regards to the topocentric frame center point.
|
<T extends org.hipparchus.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.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
Frame.getStaticTransformTo(Frame destination,
FieldAbsoluteDate<T> date)
Get the static portion of the transform from the instance to another
frame.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
TopocentricFrame.getTrackingCoordinates(org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> extPoint,
Frame frame,
FieldAbsoluteDate<T> date)
Get the tracking coordinates of a point with regards to the local point.
|
TrackingCoordinates |
TopocentricFrame.getTrackingCoordinates(org.hipparchus.geometry.euclidean.threed.Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Get the tracking coordinates of a point with regards to the local point.
|
Transform |
Frame.getTransformTo(Frame destination,
AbsoluteDate date)
Get the transform from the instance to another frame.
|
<T extends org.hipparchus.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.
|
LocalMagneticFieldFrame(Frame inertialFrame,
GeoMagneticField magneticField,
Frame bodyFrame)
Constructor with default definition of the local orbital frame:
x: Magnetic field
y: Completes orthonormal frame
z: Cross product of the magnetic field with the orbital momentum
.
|
LocalMagneticFieldFrame(Frame inertialFrame,
GeoMagneticField magneticField,
LocalMagneticFieldFrame.LOFBuilderVector lofBuilderVector,
Frame bodyFrame)
Constructor with custom definition of the local orbital frame:
x: Magnetic field
y: Completes orthonormal frame
z: Cross product of the magnetic field with chosen
vector
For near-polar orbits, it is suggested to use the orbital momentum to define the local
orbital frame. |
LocalOrbitalFrame(Frame parent,
LOF lof,
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 |
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 org.hipparchus.CalculusFieldElement<T>> |
Geoid.getIntersectionPoint(org.hipparchus.geometry.euclidean.threed.FieldLine<T> lineInFrame,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> closeInFrame,
Frame frame,
FieldAbsoluteDate<T> date)
Get the intersection point of a line with the surface of the body.
|
GeodeticPoint |
Geoid.getIntersectionPoint(org.hipparchus.geometry.euclidean.threed.Line lineInFrame,
org.hipparchus.geometry.euclidean.threed.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) |
org.hipparchus.geometry.euclidean.threed.Vector3D |
Geoid.projectToGround(org.hipparchus.geometry.euclidean.threed.Vector3D point,
AbsoluteDate date,
Frame frame) |
<T extends org.hipparchus.CalculusFieldElement<T>> |
Geoid.transform(org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> point,
Frame frame,
FieldAbsoluteDate<T> date)
Transform a Cartesian point to a surface-relative point.
|
GeodeticPoint |
Geoid.transform(org.hipparchus.geometry.euclidean.threed.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 |
HarrisPriester.getFrame()
Get the frame of the central body.
|
Frame |
JB2008.getFrame()
Get the frame of the central body.
|
Frame |
DTM2000.getFrame()
Get the frame of the central body.
|
Frame |
Atmosphere.getFrame()
Get the frame of the central body.
|
Frame |
SimpleExponentialAtmosphere.getFrame()
Get the frame of the central body.
|
Frame |
NRLMSISE00.getFrame()
Get the frame of the central body.
|
| Modifier and Type | Method and Description |
|---|---|
double |
HarrisPriester.getDensity(AbsoluteDate date,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
Frame frame)
Get the local density at some position.
|
double |
JB2008.getDensity(AbsoluteDate date,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
Frame frame)
Get the local density.
|
double |
DTM2000.getDensity(AbsoluteDate date,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
Frame frame)
Get the local density.
|
double |
Atmosphere.getDensity(AbsoluteDate date,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
Frame frame)
Get the local density.
|
double |
SimpleExponentialAtmosphere.getDensity(AbsoluteDate date,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
Frame frame)
Get the local density.
|
double |
NRLMSISE00.getDensity(AbsoluteDate date,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
Frame frame)
Get the local density.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
HarrisPriester.getDensity(FieldAbsoluteDate<T> date,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position,
Frame frame)
Get the local density at some position.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
JB2008.getDensity(FieldAbsoluteDate<T> date,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position,
Frame frame)
Get the local density.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
DTM2000.getDensity(FieldAbsoluteDate<T> date,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position,
Frame frame)
Get the local density.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
Atmosphere.getDensity(FieldAbsoluteDate<T> date,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position,
Frame frame)
Get the local density.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
SimpleExponentialAtmosphere.getDensity(FieldAbsoluteDate<T> date,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position,
Frame frame) |
<T extends org.hipparchus.CalculusFieldElement<T>> |
NRLMSISE00.getDensity(FieldAbsoluteDate<T> date,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position,
Frame frame)
Get the local density.
|
default org.hipparchus.geometry.euclidean.threed.Vector3D |
Atmosphere.getVelocity(AbsoluteDate date,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
Frame frame)
Get the inertial velocity of atmosphere molecules.
|
default <T extends org.hipparchus.CalculusFieldElement<T>> |
Atmosphere.getVelocity(FieldAbsoluteDate<T> date,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position,
Frame frame)
Get the inertial velocity of atmosphere molecules.
|
| Modifier and Type | Method and Description |
|---|---|
org.hipparchus.geometry.euclidean.threed.Vector3D |
TidalDisplacement.displacement(BodiesElements elements,
Frame earthFrame,
org.hipparchus.geometry.euclidean.threed.Vector3D referencePoint)
Compute displacement of a ground reference point.
|
org.hipparchus.geometry.euclidean.threed.Vector3D |
StationDisplacement.displacement(BodiesElements elements,
Frame earthFrame,
org.hipparchus.geometry.euclidean.threed.Vector3D referencePoint)
Compute displacement of a ground reference point.
|
org.hipparchus.geometry.euclidean.threed.Vector3D |
TectonicsDisplacement.displacement(BodiesElements elements,
Frame earthFrame,
org.hipparchus.geometry.euclidean.threed.Vector3D referencePoint)
Compute displacement of a ground reference point.
|
org.hipparchus.geometry.euclidean.threed.Vector3D |
OceanLoading.displacement(BodiesElements elements,
Frame earthFrame,
org.hipparchus.geometry.euclidean.threed.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 |
FieldOrbit.getFrame()
Get the frame in which the orbital parameters are defined.
|
Frame |
Orbit.getFrame()
Get the frame in which the orbital parameters are defined.
|
Frame |
AbstractOrbitInterpolator.getOutputInertialFrame()
Get output inertial frame.
|
Frame |
AbstractFieldOrbitInterpolator.getOutputInertialFrame()
Get output inertial frame.
|
| Modifier and Type | Method and Description |
|---|---|
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> |
FieldOrbit.getPosition(Frame outputFrame)
Get the position in a specified frame.
|
org.hipparchus.geometry.euclidean.threed.Vector3D |
Orbit.getPosition(Frame outputFrame)
Get the position in a specified frame.
|
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. |
TimeStampedFieldPVCoordinates<T> |
FieldOrbit.getPVCoordinates(Frame outputFrame)
Get the
TimeStampedPVCoordinates in a specified frame. |
TimeStampedPVCoordinates |
Orbit.getPVCoordinates(Frame outputFrame)
Get the
TimeStampedPVCoordinates in a specified frame. |
abstract Orbit |
OrbitType.mapArrayToOrbit(double[] array,
double[] arrayDot,
PositionAngleType type,
AbsoluteDate date,
double mu,
Frame frame)
Convert state array to orbital parameters.
|
abstract <T extends org.hipparchus.CalculusFieldElement<T>> |
OrbitType.mapArrayToOrbit(T[] array,
T[] arrayDot,
PositionAngleType type,
FieldAbsoluteDate<T> date,
T mu,
Frame frame)
Convert state array to orbital parameters.
|
| Constructor and Description |
|---|
AbstractFieldOrbitInterpolator(int interpolationPoints,
double extrapolationThreshold,
Frame outputInertialFrame)
Constructor.
|
AbstractOrbitInterpolator(int interpolationPoints,
double extrapolationThreshold,
Frame outputInertialFrame)
Constructor.
|
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,
PositionAngleType type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance.
|
CircularOrbit(double a,
double ex,
double ey,
double i,
double raan,
double alpha,
PositionAngleType 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,
PositionAngleType type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance.
|
EquinoctialOrbit(double a,
double ex,
double ey,
double hx,
double hy,
double l,
PositionAngleType 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,
PositionAngleType 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,
PositionAngleType 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,
PositionAngleType 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,
PositionAngleType 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,
PositionAngleType 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,
PositionAngleType 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.
|
FieldOrbitBlender(org.hipparchus.analysis.polynomials.SmoothStepFactory.FieldSmoothStepFunction<KK> blendingFunction,
FieldAbstractAnalyticalPropagator<KK> analyticalPropagator,
Frame outputInertialFrame)
Default constructor.
|
FieldOrbitHermiteInterpolator(Frame outputInertialFrame)
Constructor with :
Default number of interpolation points of
DEFAULT_INTERPOLATION_POINTS
Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s)
Use of position and two time derivatives during interpolation
As this implementation of interpolation is polynomial, it should be used only with small number of interpolation
points (about 10-20 points) in order to avoid Runge's
phenomenon and numerical problems (including NaN appearing). |
FieldOrbitHermiteInterpolator(int interpolationPoints,
double extrapolationThreshold,
Frame outputInertialFrame,
CartesianDerivativesFilter pvaFilter)
Constructor.
|
FieldOrbitHermiteInterpolator(int interpolationPoints,
Frame outputInertialFrame)
Constructor with :
Default extrapolation threshold value (
DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s)
Use of position and two time derivatives during interpolation
As this implementation of interpolation is polynomial, it should be used only with small number of interpolation
points (about 10-20 points) in order to avoid Runge's
phenomenon and numerical problems (including NaN appearing). |
FieldOrbitHermiteInterpolator(int interpolationPoints,
Frame outputInertialFrame,
CartesianDerivativesFilter pvaFilter)
Constructor with default extrapolation threshold value (
DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s). |
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,
PositionAngleType type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance.
|
KeplerianOrbit(double a,
double e,
double i,
double pa,
double raan,
double anomaly,
PositionAngleType 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.
|
OrbitBlender(org.hipparchus.analysis.polynomials.SmoothStepFactory.SmoothStepFunction blendingFunction,
Propagator blendingPropagator,
Frame outputInertialFrame)
Default constructor.
|
OrbitHermiteInterpolator(Frame outputInertialFrame)
Constructor with :
Default number of interpolation points of
DEFAULT_INTERPOLATION_POINTS
Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s)
Use of position and two time derivatives during interpolation
As this implementation of interpolation is polynomial, it should be used only with small number of interpolation
points (about 10-20 points) in order to avoid Runge's
phenomenon and numerical problems (including NaN appearing). |
OrbitHermiteInterpolator(int interpolationPoints,
double extrapolationThreshold,
Frame outputInertialFrame,
CartesianDerivativesFilter pvaFilter)
Constructor.
|
OrbitHermiteInterpolator(int interpolationPoints,
Frame outputInertialFrame)
Constructor with :
Default extrapolation threshold value (
DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s)
Use of position and two time derivatives during interpolation
As this implementation of interpolation is polynomial, it should be used only with small number of interpolation
points (about 10-20 points) in order to avoid Runge's
phenomenon and numerical problems (including NaN appearing). |
OrbitHermiteInterpolator(int interpolationPoints,
Frame outputInertialFrame,
CartesianDerivativesFilter pvaFilter)
Constructor with default extrapolation threshold value (
DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s). |
| Modifier and Type | Method and Description |
|---|---|
Frame |
Propagator.getFrame()
Get the frame in which the orbit is propagated.
|
Frame |
FieldSpacecraftState.getFrame()
Get the defining frame.
|
Frame |
FieldAbstractPropagator.getFrame()
Get the frame in which the orbit is propagated.
|
Frame |
FieldPropagator.getFrame()
Get the frame in which the orbit is propagated.
|
Frame |
StateCovariance.getFrame()
Get the covariance frame.
|
Frame |
FieldStateCovariance.getFrame()
Get the covariance frame.
|
Frame |
SpacecraftState.getFrame()
Get the defining frame.
|
Frame |
AbstractPropagator.getFrame()
Get the frame in which the orbit is propagated.
|
Frame |
AbstractStateCovarianceInterpolator.getOutFrame()
Get output frame.
|
Frame |
SpacecraftStateInterpolator.getOutputFrame()
Get output frame.
|
Frame |
FieldSpacecraftStateInterpolator.getOutputFrame()
Get output frame.
|
| Modifier and Type | Method and Description |
|---|---|
FieldStateCovariance<T> |
FieldStateCovariance.changeCovarianceFrame(FieldOrbit<T> orbit,
Frame frameOut)
Get the covariance in the output frame.
|
StateCovariance |
StateCovariance.changeCovarianceFrame(Orbit orbit,
Frame frameOut)
Get the covariance in the output frame.
|
static void |
StateCovariance.checkFrameAndOrbitTypeConsistency(Frame covarianceFrame,
OrbitType inputType)
Check constructor's inputs consistency.
|
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> |
FieldSpacecraftState.getPosition(Frame outputFrame)
Get the position in given output frame.
|
org.hipparchus.geometry.euclidean.threed.Vector3D |
SpacecraftState.getPosition(Frame outputFrame)
Get the position in given output frame.
|
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. |
StateCovariance |
StateCovarianceMatrixProvider.getStateCovariance(SpacecraftState state,
Frame frame)
Get the state covariance expressed in a given frame.
|
| Constructor and Description |
|---|
AbstractStateCovarianceInterpolator(int interpolationPoints,
double extrapolationThreshold,
TimeInterpolator<Orbit> orbitInterpolator,
Frame outFrame,
OrbitType outOrbitType,
PositionAngleType outPositionAngleType)
Constructor.
|
FieldSpacecraftStateInterpolator(Frame outputFrame)
Simplest constructor to create a default Hermite interpolator for every spacecraft state field.
|
FieldSpacecraftStateInterpolator(Frame outputFrame,
FieldTimeInterpolator<FieldOrbit<KK>,KK> orbitInterpolator,
FieldTimeInterpolator<FieldAbsolutePVCoordinates<KK>,KK> absPVAInterpolator,
FieldTimeInterpolator<TimeStampedField<KK>,KK> massInterpolator,
FieldTimeInterpolator<FieldAttitude<KK>,KK> attitudeInterpolator,
FieldTimeInterpolator<TimeStampedField<KK>,KK> additionalStateInterpolator)
Constructor.
|
FieldSpacecraftStateInterpolator(int interpolationPoints,
double extrapolationThreshold,
Frame outputFrame,
Frame attitudeReferenceFrame)
Constructor to create a customizable Hermite interpolator for every spacecraft state field.
|
FieldSpacecraftStateInterpolator(int interpolationPoints,
double extrapolationThreshold,
Frame outputFrame,
Frame attitudeReferenceFrame,
CartesianDerivativesFilter pvaFilter,
AngularDerivativesFilter angularFilter)
Constructor.
|
FieldSpacecraftStateInterpolator(int interpolationPoints,
Frame outputFrame)
Constructor to create a customizable Hermite interpolator for every spacecraft state field.
|
FieldSpacecraftStateInterpolator(int interpolationPoints,
Frame outputFrame,
Frame attitudeReferenceFrame)
Constructor to create a customizable Hermite interpolator for every spacecraft state field.
|
FieldStateCovariance(org.hipparchus.linear.FieldMatrix<T> orbitalCovariance,
FieldAbsoluteDate<T> epoch,
Frame covarianceFrame,
OrbitType orbitType,
PositionAngleType angleType)
Constructor.
|
SpacecraftStateInterpolator(Frame outputFrame)
Simplest constructor to create a default Hermite interpolator for every spacecraft state field.
|
SpacecraftStateInterpolator(Frame outputFrame,
TimeInterpolator<Orbit> orbitInterpolator,
TimeInterpolator<AbsolutePVCoordinates> absPVAInterpolator,
TimeInterpolator<TimeStampedDouble> massInterpolator,
TimeInterpolator<Attitude> attitudeInterpolator,
TimeInterpolator<TimeStampedDouble> additionalStateInterpolator)
Constructor with:
Default number of interpolation points of
DEFAULT_INTERPOLATION_POINTS
Default extrapolation threshold of DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s
|
SpacecraftStateInterpolator(int interpolationPoints,
double extrapolationThreshold,
Frame outputFrame,
Frame attitudeReferenceFrame)
Constructor to create a customizable Hermite interpolator for every spacecraft state field.
|
SpacecraftStateInterpolator(int interpolationPoints,
double extrapolationThreshold,
Frame outputFrame,
Frame attitudeReferenceFrame,
CartesianDerivativesFilter pvaFilter,
AngularDerivativesFilter angularFilter)
Constructor to create a customizable Hermite interpolator for every spacecraft state field.
|
SpacecraftStateInterpolator(int interpolationPoints,
double extrapolationThreshold,
Frame outputFrame,
TimeInterpolator<Orbit> orbitInterpolator,
TimeInterpolator<AbsolutePVCoordinates> absPVAInterpolator,
TimeInterpolator<TimeStampedDouble> massInterpolator,
TimeInterpolator<Attitude> attitudeInterpolator,
TimeInterpolator<TimeStampedDouble> additionalStateInterpolator)
Constructor.
|
SpacecraftStateInterpolator(int interpolationPoints,
Frame outputFrame)
Constructor to create a customizable Hermite interpolator for every spacecraft state field.
|
SpacecraftStateInterpolator(int interpolationPoints,
Frame outputFrame,
Frame attitudeReferenceFrame)
Constructor to create a customizable Hermite interpolator for every spacecraft state field.
|
StateCovariance(org.hipparchus.linear.RealMatrix orbitalCovariance,
AbsoluteDate epoch,
Frame covarianceFrame,
OrbitType orbitType,
PositionAngleType angleType)
Constructor.
|
StateCovarianceBlender(org.hipparchus.analysis.polynomials.SmoothStepFactory.SmoothStepFunction blendingFunction,
TimeInterpolator<Orbit> orbitInterpolator,
Frame outFrame,
OrbitType outOrbitType,
PositionAngleType outPositionAngleType)
Constructor.
|
StateCovarianceKeplerianHermiteInterpolator(int interpolationPoints,
double extrapolationThreshold,
TimeInterpolator<Orbit> orbitInterpolator,
CartesianDerivativesFilter filter,
Frame outFrame,
OrbitType outOrbitType,
PositionAngleType outPositionAngleType)
Constructor using an output frame.
|
StateCovarianceKeplerianHermiteInterpolator(int interpolationPoints,
TimeInterpolator<Orbit> orbitInterpolator,
CartesianDerivativesFilter filter,
Frame outFrame,
OrbitType outOrbitType,
PositionAngleType outPositionAngleType)
Constructor using an output frame and :
Default extrapolation threshold value (
DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s)
As this implementation of interpolation is polynomial, it should be used only with small number of interpolation
points (about 10-20 points) in order to avoid Runge's
phenomenon and numerical problems (including NaN appearing). |
StateCovarianceKeplerianHermiteInterpolator(int interpolationPoints,
TimeInterpolator<Orbit> orbitInterpolator,
Frame outFrame,
OrbitType outOrbitType,
PositionAngleType outPositionAngleType)
Constructor using an output frame and :
Default number of interpolation points of
DEFAULT_INTERPOLATION_POINTS
Use of position and two time derivatives during interpolation
As this implementation of interpolation is polynomial, it should be used only with small number of interpolation
points (about 10-20 points) in order to avoid Runge's
phenomenon and numerical problems (including NaN appearing). |
StateCovarianceKeplerianHermiteInterpolator(TimeInterpolator<Orbit> orbitInterpolator,
Frame outFrame,
OrbitType outOrbitType,
PositionAngleType outPositionAngleType)
Constructor using an output frame and :
Default number of interpolation points of
DEFAULT_INTERPOLATION_POINTS
Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s)
Use of position and two time derivatives during interpolation
As this implementation of interpolation is polynomial, it should be used only with small number of interpolation
points (about 10-20 points) in order to avoid Runge's
phenomenon and numerical problems (including NaN appearing). |
| Modifier and Type | Method and Description |
|---|---|
Frame |
Ephemeris.getFrame()
Get the frame in which the orbit is propagated.
|
| Modifier and Type | Method and Description |
|---|---|
TimeStampedPVCoordinates |
AggregateBoundedPropagator.getPVCoordinates(AbsoluteDate date,
Frame frame) |
| Modifier and Type | Method and Description |
|---|---|
Frame |
GNSSPropagator.getECEF()
Gets the Earth Centered Earth Fixed frame used to propagate GNSS orbits according to the
Interface Control Document.
|
Frame |
GLONASSAnalyticalPropagator.getECEF()
Gets the Earth Centered Earth Fixed frame used to propagate GLONASS orbits.
|
Frame |
SBASPropagator.getECEF()
Gets the Earth Centered Earth Fixed frame used to propagate GNSS orbits.
|
Frame |
GNSSPropagator.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 |
SBASPropagator.getECI()
Gets the Earth Centered Inertial frame used to propagate the orbit.
|
Frame |
GNSSPropagator.getFrame()
Get the frame in which the orbit is propagated.
|
Frame |
GLONASSAnalyticalPropagator.getFrame()
Get the frame in which the orbit is propagated.
|
Frame |
SBASPropagator.getFrame()
Get the frame in which the orbit is propagated.
|
| Modifier and Type | Method and Description |
|---|---|
SBASPropagatorBuilder |
SBASPropagatorBuilder.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.
|
GNSSPropagatorBuilder |
GNSSPropagatorBuilder.ecef(Frame bodyFixed)
Sets the Earth Centered Earth Fixed frame assimilated to the WGS84 ECEF.
|
SBASPropagatorBuilder |
SBASPropagatorBuilder.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.
|
GNSSPropagatorBuilder |
GNSSPropagatorBuilder.eci(Frame inertial)
Sets the Earth Centered Inertial frame used for propagation.
|
| Modifier and Type | Method and Description |
|---|---|
GLONASSAnalyticalPropagator |
GLONASSAlmanac.getPropagator(DataContext context,
AttitudeProvider provider,
Frame inertial,
Frame bodyFixed,
double mass)
Get the propagator corresponding to the navigation message.
|
GLONASSNumericalPropagator |
GLONASSNavigationMessage.getPropagator(double step,
DataContext context,
AttitudeProvider provider,
Frame inertial,
double mass)
Get the propagator corresponding to the navigation message.
|
default GNSSPropagator |
GNSSOrbitalElements.getPropagator(Frames frames,
AttitudeProvider provider,
Frame inertial,
Frame bodyFixed,
double mass)
Get the propagator corresponding to the navigation message.
|
SBASPropagator |
SBASNavigationMessage.getPropagator(Frames frames,
AttitudeProvider provider,
Frame inertial,
Frame bodyFixed,
double mass,
double mu)
Get the propagator corresponding to the navigation message.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
FieldTLEPropagator.getFrame()
Get the frame in which the orbit is propagated.
|
Frame |
TLEPropagator.getFrame()
Get the frame in which the orbit is propagated.
|
| Modifier and Type | Method and Description |
|---|---|
static TleGenerationAlgorithm |
TLEPropagator.getDefaultTleGenerationAlgorithm(TimeScale utc,
Frame teme)
Get the default TLE generation algorithm.
|
static <T extends org.hipparchus.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 <T extends org.hipparchus.CalculusFieldElement<T>> |
FieldTLEPropagator.selectExtrapolator(FieldTLE<T> tle,
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 TLEPropagator |
TLEPropagator.selectExtrapolator(TLE tle,
Frame teme)
Selects the extrapolator to use with the selected 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.
|
| Constructor and Description |
|---|
FixedPointTleGenerationAlgorithm(double epsilon,
int maxIterations,
double scale,
TimeScale utc,
Frame teme)
Constructor.
|
LeastSquaresTleGenerationAlgorithm(int maxIterations,
TimeScale utc,
Frame teme)
Constructor.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
AbstractPropagatorBuilder.getFrame()
Get the frame in which the orbit is propagated.
|
Frame |
PropagatorBuilder.getFrame()
Get the frame in which the orbit is propagated.
|
protected Frame |
AbstractPropagatorConverter.getFrame()
Get the frame of the initial state.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
GroundFieldOfViewDetector.getFrame()
Get the sensor reference frame.
|
Frame |
NodeDetector.getFrame()
Get the frame in which the equator is defined.
|
Frame |
FieldNodeDetector.getFrame()
Get the frame in which the equator is defined.
|
| Constructor and Description |
|---|
FieldNodeDetector(FieldAdaptableInterval<T> maxCheck,
T threshold,
int maxIter,
FieldEventHandler<T> handler,
Frame frame)
Protected constructor with full parameters.
|
FieldNodeDetector(FieldOrbit<T> orbit,
Frame frame)
Build a new instance.
|
FieldNodeDetector(T threshold,
FieldOrbit<T> orbit,
Frame frame)
Build a new instance.
|
GroundFieldOfViewDetector(AdaptableInterval maxCheck,
double threshold,
int maxIter,
EventHandler handler,
Frame frame,
FieldOfView fov)
Protected constructor with full parameters.
|
GroundFieldOfViewDetector(Frame frame,
FieldOfView fov)
Build a new instance.
|
NodeDetector(AdaptableInterval maxCheck,
double threshold,
int maxIter,
EventHandler handler,
Frame frame)
Protected constructor with full parameters.
|
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 |
FieldStateMapper.getFrame()
Get the inertial frame.
|
Frame |
FieldIntegratedEphemeris.getFrame() |
Frame |
StateMapper.getFrame()
Get the inertial frame.
|
| Modifier and Type | Method and Description |
|---|---|
protected abstract StateMapper |
AbstractIntegratedPropagator.createMapper(AbsoluteDate referenceDate,
double mu,
OrbitType orbitType,
PositionAngleType 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,
PositionAngleType 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,
PositionAngleType positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame)
Simple constructor.
|
StateMapper(AbsoluteDate referenceDate,
double mu,
OrbitType orbitType,
PositionAngleType positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame)
Simple constructor.
|
| Modifier and Type | Method and Description |
|---|---|
protected StateMapper |
GLONASSNumericalPropagator.createMapper(AbsoluteDate referenceDate,
double mu,
OrbitType orbitType,
PositionAngleType positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame) |
protected StateMapper |
NumericalPropagator.createMapper(AbsoluteDate referenceDate,
double mu,
OrbitType orbitType,
PositionAngleType positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame)
Create a mapper between raw double components and spacecraft state.
|
protected FieldStateMapper<T> |
FieldNumericalPropagator.createMapper(FieldAbsoluteDate<T> referenceDate,
T mu,
OrbitType orbitType,
PositionAngleType 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(org.hipparchus.ode.nonstiff.ClassicalRungeKuttaIntegrator integrator,
GLONASSOrbitalElements glonassOrbit,
Frame eci,
AttitudeProvider provider,
double mass,
DataContext context,
boolean isAccAvailable)
Private constructor.
|
| Modifier and Type | Method and Description |
|---|---|
default TimeStampedPVCoordinates |
OrekitStepInterpolator.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
default TimeStampedFieldPVCoordinates<T> |
FieldOrekitStepInterpolator.getPVCoordinates(FieldAbsoluteDate<T> date,
Frame frame)
Get the
FieldPVCoordinates of the body in the selected frame. |
| Modifier and Type | Method and Description |
|---|---|
protected StateMapper |
DSSTPropagator.createMapper(AbsoluteDate referenceDate,
double mu,
OrbitType ignoredOrbitType,
PositionAngleType 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,
PositionAngleType 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 |
AuxiliaryElements.getFrame()
Get the definition frame of the orbit.
|
Frame |
FieldAuxiliaryElements.getFrame()
Get the definition frame of the orbit.
|
| Modifier and Type | Class and Description |
|---|---|
class |
ExtendedPVCoordinatesProviderAdapter
Adapter from
ExtendedPVCoordinatesProvider to TransformProvider. |
| Modifier and Type | Method and Description |
|---|---|
Frame |
AbsolutePVCoordinates.getFrame()
Get the frame in which the coordinates are defined.
|
Frame |
FieldAbsolutePVCoordinates.getFrame()
Get the frame in which the coordinates are defined.
|
Frame |
FieldAbsolutePVCoordinatesHermiteInterpolator.getOutputFrame()
Get output frame for the interpolated instance.
|
Frame |
AbsolutePVCoordinatesHermiteInterpolator.getOutputFrame()
Get output frame for the interpolated instance.
|
| Modifier and Type | Method and Description |
|---|---|
org.hipparchus.geometry.euclidean.threed.Vector3D |
AggregatedPVCoordinatesProvider.getPosition(AbsoluteDate date,
Frame frame) |
org.hipparchus.geometry.euclidean.threed.Vector3D |
ConstantPVCoordinatesProvider.getPosition(AbsoluteDate date,
Frame frame) |
default org.hipparchus.geometry.euclidean.threed.Vector3D |
PVCoordinatesProvider.getPosition(AbsoluteDate date,
Frame frame)
Get the position of the body in the selected frame.
|
default org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> |
FieldPVCoordinatesProvider.getPosition(FieldAbsoluteDate<T> date,
Frame frame)
Get the position of the body in the selected frame.
|
default <T extends org.hipparchus.CalculusFieldElement<T>> |
ExtendedPVCoordinatesProvider.getPosition(FieldAbsoluteDate<T> date,
Frame frame)
Get the position of the body in the selected frame.
|
org.hipparchus.geometry.euclidean.threed.Vector3D |
AbsolutePVCoordinates.getPosition(Frame outputFrame)
Get the position in a specified frame.
|
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> |
FieldAbsolutePVCoordinates.getPosition(Frame outputFrame)
Get the position in a specified frame.
|
TimeStampedPVCoordinates |
AggregatedPVCoordinatesProvider.getPVCoordinates(AbsoluteDate date,
Frame frame) |
TimeStampedPVCoordinates |
AggregatedPVCoordinatesProvider.InvalidPVProvider.getPVCoordinates(AbsoluteDate date,
Frame frame) |
TimeStampedPVCoordinates |
AbsolutePVCoordinates.getPVCoordinates(AbsoluteDate otherDate,
Frame outputFrame) |
TimeStampedPVCoordinates |
FrameAdapter.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
TimeStampedPVCoordinates |
ConstantPVCoordinatesProvider.getPVCoordinates(AbsoluteDate date,
Frame frame) |
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 org.hipparchus.CalculusFieldElement<T>> |
FrameAdapter.getPVCoordinates(FieldAbsoluteDate<T> date,
Frame frame)
Get the
FieldPVCoordinates of the body in the selected frame. |
<T extends org.hipparchus.CalculusFieldElement<T>> |
ExtendedPVCoordinatesProvider.getPVCoordinates(FieldAbsoluteDate<T> date,
Frame frame)
Get the
FieldPVCoordinates of the body in the selected frame. |
TimeStampedPVCoordinates |
AbsolutePVCoordinates.getPVCoordinates(Frame outputFrame)
Get the TimeStampedPVCoordinates in a specified frame.
|
TimeStampedFieldPVCoordinates<T> |
FieldAbsolutePVCoordinates.getPVCoordinates(Frame outputFrame)
Get the TimeStampedFieldPVCoordinates in a specified frame.
|
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,
org.hipparchus.geometry.euclidean.threed.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,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
org.hipparchus.geometry.euclidean.threed.Vector3D velocity)
Build from position and velocity.
|
AbsolutePVCoordinates(Frame frame,
AbsoluteDate date,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
org.hipparchus.geometry.euclidean.threed.Vector3D velocity,
org.hipparchus.geometry.euclidean.threed.Vector3D acceleration)
Build from position, velocity, acceleration.
|
AbsolutePVCoordinates(Frame frame,
TimeStampedPVCoordinates pva)
Build from frame and TimeStampedPVCoordinates.
|
AbsolutePVCoordinatesHermiteInterpolator(Frame outputFrame)
Constructor with :
Default number of interpolation points of
DEFAULT_INTERPOLATION_POINTS
Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s)
Use of position and two time derivatives during interpolation
As this implementation of interpolation is polynomial, it should be used only with small number of interpolation
points (about 10-20 points) in order to avoid Runge's
phenomenon and numerical problems (including NaN appearing). |
AbsolutePVCoordinatesHermiteInterpolator(int interpolationPoints,
double extrapolationThreshold,
Frame outputFrame,
CartesianDerivativesFilter filter)
Constructor.
|
AbsolutePVCoordinatesHermiteInterpolator(int interpolationPoints,
Frame outputFrame)
Constructor with :
Default extrapolation threshold value (
DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s)
Use of position and two time derivatives during interpolation
As this implementation of interpolation is polynomial, it should be used only with small number of interpolation
points (about 10-20 points) in order to avoid Runge's
phenomenon and numerical problems (including NaN appearing). |
AbsolutePVCoordinatesHermiteInterpolator(int interpolationPoints,
Frame outputFrame,
CartesianDerivativesFilter filter)
Constructor with default extrapolation threshold value (
DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s). |
ConstantPVCoordinatesProvider(PVCoordinates pva,
Frame frame)
Create the PVCoordinatesProvider from a fixed point in a frame.
|
ConstantPVCoordinatesProvider(org.hipparchus.geometry.euclidean.threed.Vector3D pos,
Frame frame)
Create the PVCoordinatesProvider from a fixed point in a frame.
|
ExtendedPVCoordinatesProviderAdapter(Frame parent,
ExtendedPVCoordinatesProvider provider,
String name)
Simple constructor.
|
FieldAbsolutePVCoordinates(Frame frame,
FieldAbsoluteDate<T> date,
FieldPVCoordinates<T> pva)
Build from frame, date and FieldPVA coordinates.
|
FieldAbsolutePVCoordinates(Frame frame,
FieldAbsoluteDate<T> date,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> velocity)
Build from position and velocity.
|
FieldAbsolutePVCoordinates(Frame frame,
FieldAbsoluteDate<T> date,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> velocity,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> acceleration)
Build from position, velocity, acceleration.
|
FieldAbsolutePVCoordinates(Frame frame,
FieldAbsoluteDate<T> date,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<U> p)
Builds a FieldAbsolutePVCoordinates triplet from a
FieldVector3D<DerivativeStructure>. |
FieldAbsolutePVCoordinates(Frame frame,
TimeStampedFieldPVCoordinates<T> pva)
Build from frame and TimeStampedFieldPVCoordinates.
|
FieldAbsolutePVCoordinatesHermiteInterpolator(Frame outputFrame)
Constructor with :
Default number of interpolation points of
DEFAULT_INTERPOLATION_POINTS
Default extrapolation threshold value (DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s)
Use of position and two time derivatives during interpolation
As this implementation of interpolation is polynomial, it should be used only with small number of interpolation
points (about 10-20 points) in order to avoid Runge's
phenomenon and numerical problems (including NaN appearing). |
FieldAbsolutePVCoordinatesHermiteInterpolator(int interpolationPoints,
double extrapolationThreshold,
Frame outputFrame,
CartesianDerivativesFilter filter)
Constructor.
|
FieldAbsolutePVCoordinatesHermiteInterpolator(int interpolationPoints,
Frame outputFrame)
Constructor with :
Default extrapolation threshold value (
DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s)
Use of position and two time derivatives during interpolation
As this implementation of interpolation is polynomial, it should be used only with small number of interpolation
points (about 10-20 points) in order to avoid Runge's
phenomenon and numerical problems (including NaN appearing). |
FieldAbsolutePVCoordinatesHermiteInterpolator(int interpolationPoints,
Frame outputFrame,
CartesianDerivativesFilter filter)
Constructor with default extrapolation threshold value (
DEFAULT_EXTRAPOLATION_THRESHOLD_SEC s). |
FrameAdapter(Frame originFrame)
Simple constructor.
|
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