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 | |
org.orekit.estimation.measurements |
The measurements package defines everything that is related to orbit
determination measurements.
|
org.orekit.estimation.measurements.generation |
This package provides Orbit Determination measurements generation.
|
org.orekit.files.ccsds |
This package provides a parser for orbit data stored in CCSDS Orbit Data Message format.
|
org.orekit.files.general |
This package provides interfaces for orbit file representations and corresponding
parsers.
|
org.orekit.files.sp3 |
This package provides a parser for orbit data stored in SP3 format.
|
org.orekit.forces |
This package provides the interface for force models that will be used by the
NumericalPropagator , as well as
some classical spacecraft models for surface forces (spherical, box and solar array ...). |
org.orekit.forces.drag |
This package provides all drag-related forces.
|
org.orekit.forces.drag.atmosphere |
This package provides the atmosphere model interface and several implementations.
|
org.orekit.forces.gravity |
This package provides all gravity-related forces.
|
org.orekit.forces.maneuvers |
This package provides models of simple maneuvers.
|
org.orekit.forces.radiation |
This package provides all radiation pressure related forces.
|
org.orekit.frames |
This package provides classes to handle frames and transforms between them.
|
org.orekit.gnss.antenna |
This package provides classes related to receiver and satellites antenna modeling.
|
org.orekit.gnss.attitude |
This package provides classes related to navigation satellites attitude modeling.
|
org.orekit.models.earth |
This package provides models that simulate certain physical phenomena
of Earth and the near-Earth environment.
|
org.orekit.models.earth.displacement |
This package provides models computing reference points
displacements on Earth surface.
|
org.orekit.orbits |
This package provides classes to represent orbits.
|
org.orekit.propagation |
Propagation
|
org.orekit.propagation.analytical |
Top level package for analytical propagators.
|
org.orekit.propagation.analytical.gnss |
This package provides classes to propagate GNSS orbits.
|
org.orekit.propagation.analytical.tle |
This package provides classes to read and extrapolate tle's.
|
org.orekit.propagation.conversion |
This package provides tools to convert a given propagator or a set of
SpacecraftState into another propagator. |
org.orekit.propagation.events |
This package provides interfaces and classes dealing with events occurring during propagation.
|
org.orekit.propagation.integration |
Utilities for integration-based propagators (both numerical and semi-analytical).
|
org.orekit.propagation.numerical |
Top level package for numerical propagators.
|
org.orekit.propagation.semianalytical.dsst |
This package provides an implementation of the Draper Semi-analytical
Satellite Theory (DSST).
|
org.orekit.propagation.semianalytical.dsst.forces |
This package provides force models for Draper Semi-analytical Satellite Theory (DSST).
|
org.orekit.propagation.semianalytical.dsst.utilities |
This package provides utilities for Draper Semi-analytical Satellite Theory (DSST).
|
org.orekit.utils |
This package provides useful objects.
|
Modifier and Type | Method | Description |
---|---|---|
Frame |
GroundPointing.getBodyFrame() |
Get the body frame.
|
Frame |
Attitude.getReferenceFrame() |
Get the reference frame.
|
Frame |
FieldAttitude.getReferenceFrame() |
Get the reference frame.
|
Modifier and Type | Method | Description |
---|---|---|
<T extends org.hipparchus.RealFieldElement<T>> |
AttitudeProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> 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.
|
<T extends org.hipparchus.RealFieldElement<T>> |
AttitudesSequence.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> 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.
|
<T extends org.hipparchus.RealFieldElement<T>> |
CelestialBodyPointed.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame) |
Compute the attitude corresponding to an orbital state.
|
Attitude |
CelestialBodyPointed.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame) |
Compute the attitude corresponding to an orbital state.
|
<T extends org.hipparchus.RealFieldElement<T>> |
FixedRate.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> 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.
|
<T extends org.hipparchus.RealFieldElement<T>> |
GroundPointing.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> 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.RealFieldElement<T>> |
InertialProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame) |
Compute the attitude corresponding to an orbital state.
|
Attitude |
InertialProvider.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame) |
Compute the attitude corresponding to an orbital state.
|
<T extends org.hipparchus.RealFieldElement<T>> |
LofOffset.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> 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.
|
<T extends org.hipparchus.RealFieldElement<T>> |
LofOffsetPointing.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> 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.
|
<T extends org.hipparchus.RealFieldElement<T>> |
SpinStabilized.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> 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.
|
<T extends org.hipparchus.RealFieldElement<T>> |
TabulatedLofOffset.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> 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.
|
<T extends org.hipparchus.RealFieldElement<T>> |
TabulatedProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> 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.
|
<T extends org.hipparchus.RealFieldElement<T>> |
YawCompensation.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame) |
Compute the attitude corresponding to an orbital state.
|
Attitude |
YawCompensation.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame) |
Compute the attitude corresponding to an orbital state.
|
<T extends org.hipparchus.RealFieldElement<T>> |
YawSteering.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> 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.
|
<T extends org.hipparchus.RealFieldElement<T>> |
YawCompensation.getBaseState(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame) |
Compute the base system state at given date, without compensation.
|
Attitude |
YawCompensation.getBaseState(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame) |
Compute the base system state at given date, without compensation.
|
<T extends org.hipparchus.RealFieldElement<T>> |
YawSteering.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.
|
<T extends org.hipparchus.RealFieldElement<T>> |
BodyCenterPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> 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.
|
abstract <T extends org.hipparchus.RealFieldElement<T>> |
GroundPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame) |
Compute the target point position/velocity in specified frame.
|
abstract TimeStampedPVCoordinates |
GroundPointing.getTargetPV(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame) |
Compute the target point position/velocity in specified frame.
|
<T extends org.hipparchus.RealFieldElement<T>> |
LofOffsetPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> 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.
|
<T extends org.hipparchus.RealFieldElement<T>> |
NadirPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> 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.
|
<T extends org.hipparchus.RealFieldElement<T>> |
TargetPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> 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.
|
<T extends org.hipparchus.RealFieldElement<T>> |
YawCompensation.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame) |
Compute the target point position/velocity in specified frame.
|
TimeStampedPVCoordinates |
YawCompensation.getTargetPV(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame) |
Compute the target point position/velocity in specified frame.
|
<T extends org.hipparchus.RealFieldElement<T>> |
YawSteering.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.
|
<T extends org.hipparchus.RealFieldElement<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.
|
Attitude |
Attitude.withReferenceFrame(Frame newReferenceFrame) |
Get a similar attitude with a specific reference frame.
|
FieldAttitude<T> |
FieldAttitude.withReferenceFrame(Frame newReferenceFrame) |
Get a similar attitude with a specific reference frame.
|
Constructor | Description |
---|---|
Attitude(Frame referenceFrame,
TimeStampedAngularCoordinates 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(AbsoluteDate date,
Frame referenceFrame,
AngularCoordinates orientation) |
Creates a new instance.
|
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(Frame referenceFrame,
TimeStampedFieldAngularCoordinates<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(FieldAbsoluteDate<T> date,
Frame referenceFrame,
FieldAngularCoordinates<T> orientation) |
Creates a new instance.
|
GroundPointing(Frame inertialFrame,
Frame bodyFrame) |
Default constructor.
|
LofOffset(Frame inertialFrame,
LOFType type) |
Create a LOF-aligned attitude.
|
LofOffset(Frame inertialFrame,
LOFType type,
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,
LOFType type,
List<TimeStampedAngularCoordinates> table,
int n,
AngularDerivativesFilter filter) |
Creates new instance.
|
TabulatedProvider(Frame referenceFrame,
List<TimeStampedAngularCoordinates> table,
int n,
AngularDerivativesFilter filter) |
Creates new instance.
|
TargetPointing(Frame inertialFrame,
GeodeticPoint targetGeo,
BodyShape shape) |
Creates a new instance from body shape and target expressed in geodetic coordinates.
|
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.
|
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 | Description |
---|---|---|
Frame |
BodyShape.getBodyFrame() |
Get body frame related to body shape.
|
Frame |
OneAxisEllipsoid.getBodyFrame() |
Get body frame related to body shape.
|
Frame |
CelestialBody.getBodyOrientedFrame() |
Get a body oriented, body centered frame.
|
Frame |
Ellipse.getFrame() |
Get the defining frame.
|
Frame |
Ellipsoid.getFrame() |
Get the ellipsoid central frame.
|
Frame |
CelestialBody.getInertiallyOrientedFrame() |
Get an inertially oriented, body centered frame.
|
Modifier and Type | Method | Description |
---|---|---|
<T extends org.hipparchus.RealFieldElement<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.RealFieldElement<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 |
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.
|
<T extends org.hipparchus.RealFieldElement<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.
|
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.
|
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.
|
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.
|
TimeStampedPVCoordinates |
OneAxisEllipsoid.projectToGround(TimeStampedPVCoordinates pv,
Frame frame) |
Project a moving point to the ground.
|
<T extends org.hipparchus.RealFieldElement<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.
|
GeodeticPoint |
BodyShape.transform(org.hipparchus.geometry.euclidean.threed.Vector3D point,
Frame frame,
AbsoluteDate date) |
Transform a Cartesian point to a surface-relative point.
|
<T extends org.hipparchus.RealFieldElement<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.
|
GeodeticPoint |
OneAxisEllipsoid.transform(org.hipparchus.geometry.euclidean.threed.Vector3D point,
Frame frame,
AbsoluteDate 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.
|
Constructor | 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.
|
OneAxisEllipsoid(double ae,
double f,
Frame bodyFrame) |
Simple constructor.
|
Modifier and Type | Method | Description |
---|---|---|
KeplerianOrbit |
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.
|
KeplerianOrbit |
IodGibbs.estimate(Frame frame,
PV pv1,
PV pv2,
PV pv3) |
Give an initial orbit estimation, assuming Keplerian motion.
|
KeplerianOrbit |
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.
|
Constructor | Description |
---|---|
IodGooding(Frame frame,
double mu) |
Creator.
|
Modifier and Type | Method | 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 | Description |
---|---|---|
Transform |
GroundStation.getOffsetToInertial(Frame inertial,
AbsoluteDate clockDate) |
Get the transform between offset frame and inertial frame.
|
FieldTransform<org.hipparchus.analysis.differentiation.DerivativeStructure> |
GroundStation.getOffsetToInertial(Frame inertial,
AbsoluteDate clockDate,
org.hipparchus.analysis.differentiation.DSFactory factory,
Map<String,Integer> indices) |
Get the transform between offset frame and inertial frame with derivatives.
|
FieldTransform<org.hipparchus.analysis.differentiation.DerivativeStructure> |
GroundStation.getOffsetToInertial(Frame inertial,
FieldAbsoluteDate<org.hipparchus.analysis.differentiation.DerivativeStructure> offsetCompensatedDate,
org.hipparchus.analysis.differentiation.DSFactory factory,
Map<String,Integer> indices) |
Get the transform between offset frame and inertial frame with derivatives.
|
Constructor | Description |
---|---|
AngularRaDec(GroundStation station,
Frame referenceFrame,
AbsoluteDate date,
double[] angular,
double[] sigma,
double[] baseWeight) |
Deprecated.
|
AngularRaDec(GroundStation station,
Frame referenceFrame,
AbsoluteDate date,
double[] angular,
double[] sigma,
double[] baseWeight,
int propagatorIndex) |
Deprecated.
|
AngularRaDec(GroundStation station,
Frame referenceFrame,
AbsoluteDate date,
double[] angular,
double[] sigma,
double[] baseWeight,
ObservableSatellite satellite) |
Simple constructor.
|
Constructor | Description |
---|---|
AngularRaDecBuilder(org.hipparchus.random.CorrelatedRandomVectorGenerator noiseSource,
GroundStation station,
Frame referenceFrame,
double[] sigma,
double[] baseWeight,
ObservableSatellite satellite) |
Simple constructor.
|
Modifier and Type | Class | Description |
---|---|---|
class |
CcsdsModifiedFrame |
A reference frame created from the
REF_FRAME and CENTER_NAME is a CCSDS
OPM, OMM, or OEM file. |
Modifier and Type | Method | Description |
---|---|---|
Frame |
OGMFile.getCovRefFrame() |
Get coordinate system for covariance matrix, for absolute frames.
|
Frame |
CCSDSFrame.getFrame(IERSConventions conventions,
boolean simpleEOP) |
Get the frame corresponding to the CCSDS constant.
|
Frame |
ODMMetaData.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).
|
Frame |
OEMFile.CovarianceMatrix.getFrame() |
Get coordinate system for covariance matrix, for absolute frames.
|
Frame |
OEMFile.EphemeridesBlock.getFrame() |
|
Frame |
TDMFile.TDMMetaData.getReferenceFrame() |
Get the the value of
REFERENCE_FRAME as an Orekit Frame . |
Frame |
ODMMetaData.getRefFrame() |
Get the the value of
REF_FRAME as an Orekit Frame . |
Frame |
OPMFile.Maneuver.getRefFrame() |
Get Coordinate system for velocity increment vector, for absolute frames.
|
Modifier and Type | Method | Description |
---|---|---|
StreamingOemWriter.Segment |
StreamingOemWriter.newSegment(Frame frame,
Map<Keyword,String> segmentMetadata) |
Create a writer for a new OEM ephemeris segment.
|
void |
TDMFile.TDMMetaData.setReferenceFrame(Frame refFrame) |
Set the reference frame in which data are given: used for RADEC tracking data.
|
void |
OPMFile.Maneuver.setRefFrame(Frame refFrame) |
Set Coordinate system for velocity increment vector, for absolute frames.
|
Modifier and Type | Method | Description |
---|---|---|
Frame |
EphemerisFile.EphemerisSegment.getFrame() |
Get the reference frame for this ephemeris segment.
|
Frame |
OrekitEphemerisFile.OrekitEphemerisSegment.getFrame() |
Constructor | Description |
---|---|
OrekitEphemerisSegment(List<TimeStampedPVCoordinates> coordinates,
Frame frame,
String frameCenterString,
double mu,
TimeScale timeScale,
int samples) |
constructor for OrekitEphemerisSegment.
|
Modifier and Type | Method | Description |
---|---|---|
Frame |
SP3File.SP3Ephemeris.getFrame() |
Constructor | 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. |
Modifier and Type | Method | Description |
---|---|---|
org.hipparchus.geometry.euclidean.threed.Vector3D |
BoxAndSolarArraySpacecraft.dragAcceleration(AbsoluteDate date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
org.hipparchus.geometry.euclidean.threed.Rotation rotation,
double mass,
double density,
org.hipparchus.geometry.euclidean.threed.Vector3D relativeVelocity,
double[] parameters) |
Compute the acceleration due to drag.
|
org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure> |
BoxAndSolarArraySpacecraft.dragAcceleration(AbsoluteDate date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
org.hipparchus.geometry.euclidean.threed.Rotation rotation,
double mass,
double density,
org.hipparchus.geometry.euclidean.threed.Vector3D relativeVelocity,
double[] parameters,
String paramName) |
Compute acceleration due to drag, with parameters derivatives.
|
<T extends org.hipparchus.RealFieldElement<T>> |
BoxAndSolarArraySpacecraft.dragAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position,
org.hipparchus.geometry.euclidean.threed.FieldRotation<T> rotation,
T mass,
T density,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> relativeVelocity,
T[] parameters) |
Compute the acceleration due to drag.
|
org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure> |
BoxAndSolarArraySpacecraft.getNormal(AbsoluteDate date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure> position,
org.hipparchus.geometry.euclidean.threed.FieldRotation<org.hipparchus.analysis.differentiation.DerivativeStructure> rotation) |
Get solar array normal in spacecraft frame.
|
org.hipparchus.geometry.euclidean.threed.Vector3D |
BoxAndSolarArraySpacecraft.getNormal(AbsoluteDate date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
org.hipparchus.geometry.euclidean.threed.Rotation rotation) |
Get solar array normal in spacecraft frame.
|
<T extends org.hipparchus.RealFieldElement<T>> |
BoxAndSolarArraySpacecraft.getNormal(FieldAbsoluteDate<T> date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position,
org.hipparchus.geometry.euclidean.threed.FieldRotation<T> rotation) |
Get solar array normal in spacecraft frame.
|
org.hipparchus.geometry.euclidean.threed.Vector3D |
BoxAndSolarArraySpacecraft.radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
org.hipparchus.geometry.euclidean.threed.Rotation rotation,
double mass,
org.hipparchus.geometry.euclidean.threed.Vector3D flux,
double[] parameters) |
Compute the acceleration due to radiation pressure.
|
org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure> |
BoxAndSolarArraySpacecraft.radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
org.hipparchus.geometry.euclidean.threed.Rotation rotation,
double mass,
org.hipparchus.geometry.euclidean.threed.Vector3D flux,
double[] parameters,
String paramName) |
Compute the acceleration due to radiation pressure, with parameters derivatives.
|
<T extends org.hipparchus.RealFieldElement<T>> |
BoxAndSolarArraySpacecraft.radiationPressureAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position,
org.hipparchus.geometry.euclidean.threed.FieldRotation<T> rotation,
T mass,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> flux,
T[] parameters) |
Compute the acceleration due to radiation pressure.
|
Modifier and Type | Method | Description |
---|---|---|
org.hipparchus.geometry.euclidean.threed.Vector3D |
DragSensitive.dragAcceleration(AbsoluteDate date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
org.hipparchus.geometry.euclidean.threed.Rotation rotation,
double mass,
double density,
org.hipparchus.geometry.euclidean.threed.Vector3D relativeVelocity,
double[] parameters) |
Compute the acceleration due to drag.
|
org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure> |
DragSensitive.dragAcceleration(AbsoluteDate date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
org.hipparchus.geometry.euclidean.threed.Rotation rotation,
double mass,
double density,
org.hipparchus.geometry.euclidean.threed.Vector3D relativeVelocity,
double[] parameters,
String paramName) |
Compute acceleration due to drag, with parameters derivatives.
|
<T extends org.hipparchus.RealFieldElement<T>> |
DragSensitive.dragAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position,
org.hipparchus.geometry.euclidean.threed.FieldRotation<T> rotation,
T mass,
T density,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> relativeVelocity,
T[] parameters) |
Compute the acceleration due to drag.
|
org.hipparchus.geometry.euclidean.threed.Vector3D |
IsotropicDrag.dragAcceleration(AbsoluteDate date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
org.hipparchus.geometry.euclidean.threed.Rotation rotation,
double mass,
double density,
org.hipparchus.geometry.euclidean.threed.Vector3D relativeVelocity,
double[] parameters) |
Compute the acceleration due to drag.
|
org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure> |
IsotropicDrag.dragAcceleration(AbsoluteDate date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
org.hipparchus.geometry.euclidean.threed.Rotation rotation,
double mass,
double density,
org.hipparchus.geometry.euclidean.threed.Vector3D relativeVelocity,
double[] parameters,
String paramName) |
Compute acceleration due to drag, with parameters derivatives.
|
<T extends org.hipparchus.RealFieldElement<T>> |
IsotropicDrag.dragAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position,
org.hipparchus.geometry.euclidean.threed.FieldRotation<T> rotation,
T mass,
T density,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> relativeVelocity,
T[] parameters) |
Compute the acceleration due to drag.
|
Modifier and Type | Method | Description |
---|---|---|
Frame |
Atmosphere.getFrame() |
Get the frame of the central body.
|
Frame |
DTM2000.getFrame() |
Get the frame of the central body.
|
Frame |
HarrisPriester.getFrame() |
Get the frame of the central body.
|
Frame |
JB2008.getFrame() |
Get the frame of the central body.
|
Frame |
NRLMSISE00.getFrame() |
Get the frame of the central body.
|
Frame |
SimpleExponentialAtmosphere.getFrame() |
Get the frame of the central body.
|
Modifier and Type | Method | Description |
---|---|---|
double |
Atmosphere.getDensity(AbsoluteDate date,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
Frame frame) |
Get the local density.
|
<T extends org.hipparchus.RealFieldElement<T>> |
Atmosphere.getDensity(FieldAbsoluteDate<T> date,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> 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.
|
<T extends org.hipparchus.RealFieldElement<T>> |
DTM2000.getDensity(FieldAbsoluteDate<T> date,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position,
Frame frame) |
Get the local density.
|
double |
HarrisPriester.getDensity(AbsoluteDate date,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
Frame frame) |
Get the local density at some position.
|
<T extends org.hipparchus.RealFieldElement<T>> |
HarrisPriester.getDensity(FieldAbsoluteDate<T> date,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> 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.
|
<T extends org.hipparchus.RealFieldElement<T>> |
JB2008.getDensity(FieldAbsoluteDate<T> date,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> 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.RealFieldElement<T>> |
NRLMSISE00.getDensity(FieldAbsoluteDate<T> date,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> 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.
|
<T extends org.hipparchus.RealFieldElement<T>> |
SimpleExponentialAtmosphere.getDensity(FieldAbsoluteDate<T> date,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position,
Frame frame) |
|
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.RealFieldElement<T>> |
Atmosphere.getVelocity(FieldAbsoluteDate<T> date,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position,
Frame frame) |
Get the inertial velocity of atmosphere molecules.
|
Constructor | Description |
---|---|
HolmesFeatherstoneAttractionModel(Frame centralBodyFrame,
NormalizedSphericalHarmonicsProvider provider) |
Creates a new instance.
|
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,
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.
|
Modifier and Type | Method | Description |
---|---|---|
Frame |
SmallManeuverAnalyticalModel.getInertialFrame() |
Get the inertial frame in which the velocity increment is defined.
|
Constructor | 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 | Description |
---|---|---|
<T extends org.hipparchus.RealFieldElement<T>> |
SolarRadiationPressure.getLightingRatio(org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position,
Frame frame,
FieldAbsoluteDate<T> date) |
Get the lighting ratio ([0-1]).
|
double |
SolarRadiationPressure.getLightingRatio(org.hipparchus.geometry.euclidean.threed.Vector3D position,
Frame frame,
AbsoluteDate date) |
Get the lighting ratio ([0-1]).
|
org.hipparchus.geometry.euclidean.threed.Vector3D |
IsotropicRadiationClassicalConvention.radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
org.hipparchus.geometry.euclidean.threed.Rotation rotation,
double mass,
org.hipparchus.geometry.euclidean.threed.Vector3D flux,
double[] parameters) |
Compute the acceleration due to radiation pressure.
|
org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure> |
IsotropicRadiationClassicalConvention.radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
org.hipparchus.geometry.euclidean.threed.Rotation rotation,
double mass,
org.hipparchus.geometry.euclidean.threed.Vector3D flux,
double[] parameters,
String paramName) |
Compute the acceleration due to radiation pressure, with parameters derivatives.
|
<T extends org.hipparchus.RealFieldElement<T>> |
IsotropicRadiationClassicalConvention.radiationPressureAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position,
org.hipparchus.geometry.euclidean.threed.FieldRotation<T> rotation,
T mass,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> flux,
T[] parameters) |
Compute the acceleration due to radiation pressure.
|
org.hipparchus.geometry.euclidean.threed.Vector3D |
IsotropicRadiationCNES95Convention.radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
org.hipparchus.geometry.euclidean.threed.Rotation rotation,
double mass,
org.hipparchus.geometry.euclidean.threed.Vector3D flux,
double[] parameters) |
Compute the acceleration due to radiation pressure.
|
org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure> |
IsotropicRadiationCNES95Convention.radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
org.hipparchus.geometry.euclidean.threed.Rotation rotation,
double mass,
org.hipparchus.geometry.euclidean.threed.Vector3D flux,
double[] parameters,
String paramName) |
Compute the acceleration due to radiation pressure, with parameters derivatives.
|
<T extends org.hipparchus.RealFieldElement<T>> |
IsotropicRadiationCNES95Convention.radiationPressureAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position,
org.hipparchus.geometry.euclidean.threed.FieldRotation<T> rotation,
T mass,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> flux,
T[] parameters) |
Compute the acceleration due to radiation pressure.
|
org.hipparchus.geometry.euclidean.threed.Vector3D |
IsotropicRadiationSingleCoefficient.radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
org.hipparchus.geometry.euclidean.threed.Rotation rotation,
double mass,
org.hipparchus.geometry.euclidean.threed.Vector3D flux,
double[] parameters) |
Compute the acceleration due to radiation pressure.
|
org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure> |
IsotropicRadiationSingleCoefficient.radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
org.hipparchus.geometry.euclidean.threed.Rotation rotation,
double mass,
org.hipparchus.geometry.euclidean.threed.Vector3D flux,
double[] parameters,
String paramName) |
Compute the acceleration due to radiation pressure, with parameters derivatives.
|
<T extends org.hipparchus.RealFieldElement<T>> |
IsotropicRadiationSingleCoefficient.radiationPressureAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position,
org.hipparchus.geometry.euclidean.threed.FieldRotation<T> rotation,
T mass,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> flux,
T[] parameters) |
Compute the acceleration due to radiation pressure.
|
org.hipparchus.geometry.euclidean.threed.Vector3D |
RadiationSensitive.radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
org.hipparchus.geometry.euclidean.threed.Rotation rotation,
double mass,
org.hipparchus.geometry.euclidean.threed.Vector3D flux,
double[] parameters) |
Compute the acceleration due to radiation pressure.
|
org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure> |
RadiationSensitive.radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
org.hipparchus.geometry.euclidean.threed.Rotation rotation,
double mass,
org.hipparchus.geometry.euclidean.threed.Vector3D flux,
double[] parameters,
String paramName) |
Compute the acceleration due to radiation pressure, with parameters derivatives.
|
<T extends org.hipparchus.RealFieldElement<T>> |
RadiationSensitive.radiationPressureAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position,
org.hipparchus.geometry.euclidean.threed.FieldRotation<T> rotation,
T mass,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> flux,
T[] parameters) |
Compute the acceleration due to radiation pressure.
|
Modifier and Type | Class | Description |
---|---|---|
class |
FactoryManagedFrame |
Base class for the predefined frames that are managed by
FramesFactory . |
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 |
UpdatableFrame |
Frame whose transform from its parent can be updated.
|
class |
VersionedITRF |
Specific version of International Terrestrial Reference Frame.
|
Modifier and Type | Method | Description |
---|---|---|
Frame |
HelmertTransformation.Predefined.createTransformedITRF(Frame parent,
String name) |
Create an ITRF frame by transforming another ITRF frame.
|
Frame |
Frame.getAncestor(int n) |
Get the nth ancestor of the frame.
|
static Frame |
FramesFactory.getEcliptic(IERSConventions conventions) |
Get the ecliptic frame.
|
static Frame |
FramesFactory.getFrame(Predefined factoryKey) |
Get one of the predefined frames.
|
Frame |
OrphanFrame.getFrame() |
Get the associated
frame . |
Frame |
Frame.getFrozenFrame(Frame reference,
AbsoluteDate freezingDate,
String frozenName) |
Get a new version of the instance, frozen with respect to a reference frame.
|
static Frame |
FramesFactory.getGCRF() |
Get the unique GCRF frame.
|
static Frame |
FramesFactory.getICRF() |
Get the unique ICRF frame.
|
Frame |
Frame.getParent() |
Get the parent frame.
|
protected static Frame |
Frame.getRoot() |
Get the unique root frame.
|
Modifier and Type | Method | 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.
|
static EOPHistory |
FramesFactory.findEOP(Frame start) |
Retrieve EOP from a frame hierarchy.
|
<T extends org.hipparchus.RealFieldElement<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.RealFieldElement<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.RealFieldElement<T>> |
FramesFactory.getNonInterpolatingTransform(Frame from,
Frame to,
FieldAbsoluteDate<T> date) |
Get the transform between two frames, suppressing all interpolation.
|
TimeStampedPVCoordinates |
TopocentricFrame.getPVCoordinates(AbsoluteDate date,
Frame frame) |
Get the
PVCoordinates of the topocentric frame origin in the selected frame. |
<T extends org.hipparchus.RealFieldElement<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.RealFieldElement<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.
|
Transform |
Frame.getTransformTo(Frame destination,
AbsoluteDate date) |
Get the transform from the instance to another frame.
|
<T extends org.hipparchus.RealFieldElement<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.
|
Constructor | Description |
---|---|
FactoryManagedFrame(Frame parent,
TransformProvider transformProvider,
boolean pseudoInertial,
Predefined factoryKey) |
Simple constructor.
|
Frame(Frame parent,
TransformProvider transformProvider,
String name) |
Build a non-inertial frame from its transform with respect to its parent.
|
Frame(Frame parent,
TransformProvider transformProvider,
String name,
boolean pseudoInertial) |
Build a frame from its transform with respect to its parent.
|
Frame(Frame parent,
Transform transform,
String name) |
Build a non-inertial frame from its transform with respect to its parent.
|
Frame(Frame parent,
Transform transform,
String name,
boolean pseudoInertial) |
Build a frame from its transform with respect to its parent.
|
LocalOrbitalFrame(Frame parent,
LOFType type,
PVCoordinatesProvider provider,
String name) |
Build a new instance.
|
UpdatableFrame(Frame parent,
Transform transform,
String name) |
Build a non-inertial frame from its transform with respect to its parent.
|
UpdatableFrame(Frame parent,
Transform transform,
String name,
boolean pseudoInertial) |
Build a frame from its transform with respect to its parent.
|
Modifier and Type | Method | Description |
---|---|---|
abstract GNSSAttitudeProvider |
SatelliteType.buildAttitudeProvider(AbsoluteDate validityStart,
AbsoluteDate validityEnd,
ExtendedPVCoordinatesProvider sun,
Frame inertialFrame,
int prnNumber) |
Build an attitude provider suitable for this satellite type.
|
Modifier and Type | Method | Description |
---|---|---|
<T extends org.hipparchus.RealFieldElement<T>> |
AbstractGNSSAttitudeProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame) |
Compute the attitude corresponding to an orbital state.
|
Attitude |
AbstractGNSSAttitudeProvider.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame) |
Compute the attitude corresponding to an orbital state.
|
Constructor | Description |
---|---|
AbstractGNSSAttitudeProvider(AbsoluteDate validityStart,
AbsoluteDate validityEnd,
ExtendedPVCoordinatesProvider sun,
Frame inertialFrame) |
Simple constructor.
|
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.
|
GPSBlockIIA(double yawRate,
double yawBias,
AbsoluteDate validityStart,
AbsoluteDate validityEnd,
ExtendedPVCoordinatesProvider sun,
Frame inertialFrame,
int prnNumber) |
Deprecated.
|
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 | Description |
---|---|---|
Frame |
Geoid.getBodyFrame() |
Modifier and Type | Method | Description |
---|---|---|
static ReferenceEllipsoid |
ReferenceEllipsoid.getGrs80(Frame bodyFrame) |
Get the GRS80 ellipsoid, attached to the given body frame.
|
<T extends org.hipparchus.RealFieldElement<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.
|
org.hipparchus.geometry.euclidean.threed.Vector3D |
Geoid.projectToGround(org.hipparchus.geometry.euclidean.threed.Vector3D point,
AbsoluteDate date,
Frame frame) |
|
TimeStampedPVCoordinates |
Geoid.projectToGround(TimeStampedPVCoordinates pv,
Frame frame) |
|
<T extends org.hipparchus.RealFieldElement<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 | Description |
---|---|
GlobalPressureTemperatureModel(double latitude,
double longitude,
Frame bodyFrame) |
Build a new instance.
|
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 | Description |
---|---|---|
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.
|
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 |
TidalDisplacement.displacement(BodiesElements elements,
Frame earthFrame,
org.hipparchus.geometry.euclidean.threed.Vector3D referencePoint) |
Compute displacement of a ground reference point.
|
Modifier and Type | Method | 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.
|
Modifier and Type | Method | Description |
---|---|---|
TimeStampedFieldPVCoordinates<T> |
FieldOrbit.getPVCoordinates(Frame outputFrame) |
Get the
TimeStampedPVCoordinates in a specified frame. |
TimeStampedFieldPVCoordinates<T> |
FieldOrbit.getPVCoordinates(FieldAbsoluteDate<T> otherDate,
Frame otherFrame) |
Get the
FieldPVCoordinates of the body in the selected frame. |
TimeStampedPVCoordinates |
Orbit.getPVCoordinates(Frame outputFrame) |
Get the
TimeStampedPVCoordinates in a specified frame. |
TimeStampedPVCoordinates |
Orbit.getPVCoordinates(AbsoluteDate otherDate,
Frame otherFrame) |
Get the
PVCoordinates of the body in the selected frame. |
abstract Orbit |
OrbitType.mapArrayToOrbit(double[] array,
double[] arrayDot,
PositionAngle type,
AbsoluteDate date,
double mu,
Frame frame) |
Convert state array to orbital parameters.
|
abstract <T extends org.hipparchus.RealFieldElement<T>> |
OrbitType.mapArrayToOrbit(T[] array,
T[] arrayDot,
PositionAngle type,
FieldAbsoluteDate<T> date,
double mu,
Frame frame) |
Convert state array to orbital parameters.
|
Constructor | Description |
---|---|
CartesianOrbit(PVCoordinates pvaCoordinates,
Frame frame,
AbsoluteDate date,
double mu) |
Constructor from Cartesian parameters.
|
CartesianOrbit(TimeStampedPVCoordinates pvaCoordinates,
Frame frame,
double mu) |
Constructor from Cartesian parameters.
|
CircularOrbit(double a,
double ex,
double ey,
double i,
double raan,
double alpha,
double aDot,
double exDot,
double eyDot,
double iDot,
double raanDot,
double alphaDot,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu) |
Creates a new instance.
|
CircularOrbit(double a,
double ex,
double ey,
double i,
double raan,
double alpha,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu) |
Creates a new instance.
|
CircularOrbit(PVCoordinates pvCoordinates,
Frame frame,
AbsoluteDate date,
double mu) |
Constructor from Cartesian parameters.
|
CircularOrbit(TimeStampedPVCoordinates pvCoordinates,
Frame frame,
double mu) |
Constructor from Cartesian parameters.
|
EquinoctialOrbit(double a,
double ex,
double ey,
double hx,
double hy,
double l,
double aDot,
double exDot,
double eyDot,
double hxDot,
double hyDot,
double lDot,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu) |
Creates a new instance.
|
EquinoctialOrbit(double a,
double ex,
double ey,
double hx,
double hy,
double l,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu) |
Creates a new instance.
|
EquinoctialOrbit(PVCoordinates pvCoordinates,
Frame frame,
AbsoluteDate date,
double mu) |
Constructor from Cartesian parameters.
|
EquinoctialOrbit(TimeStampedPVCoordinates pvCoordinates,
Frame frame,
double mu) |
Constructor from Cartesian parameters.
|
FieldCartesianOrbit(FieldPVCoordinates<T> pvaCoordinates,
Frame frame,
FieldAbsoluteDate<T> date,
double mu) |
Constructor from Cartesian parameters.
|
FieldCartesianOrbit(TimeStampedFieldPVCoordinates<T> pvaCoordinates,
Frame frame,
double mu) |
Constructor from Cartesian parameters.
|
FieldCircularOrbit(FieldPVCoordinates<T> PVCoordinates,
Frame frame,
FieldAbsoluteDate<T> date,
double mu) |
Constructor from Cartesian parameters.
|
FieldCircularOrbit(TimeStampedFieldPVCoordinates<T> pvCoordinates,
Frame frame,
double mu) |
Constructor from Cartesian parameters.
|
FieldCircularOrbit(T a,
T ex,
T ey,
T i,
T raan,
T alpha,
PositionAngle type,
Frame frame,
FieldAbsoluteDate<T> date,
double mu) |
Creates a new instance.
|
FieldCircularOrbit(T a,
T ex,
T ey,
T i,
T raan,
T alpha,
T aDot,
T exDot,
T eyDot,
T iDot,
T raanDot,
T alphaDot,
PositionAngle type,
Frame frame,
FieldAbsoluteDate<T> date,
double mu) |
Creates a new instance.
|
FieldEquinoctialOrbit(FieldPVCoordinates<T> pvCoordinates,
Frame frame,
FieldAbsoluteDate<T> date,
double mu) |
Constructor from Cartesian parameters.
|
FieldEquinoctialOrbit(TimeStampedFieldPVCoordinates<T> pvCoordinates,
Frame frame,
double mu) |
Constructor from Cartesian parameters.
|
FieldEquinoctialOrbit(T a,
T ex,
T ey,
T hx,
T hy,
T l,
PositionAngle type,
Frame frame,
FieldAbsoluteDate<T> date,
double mu) |
Creates a new instance.
|
FieldEquinoctialOrbit(T a,
T ex,
T ey,
T hx,
T hy,
T l,
T aDot,
T exDot,
T eyDot,
T hxDot,
T hyDot,
T lDot,
PositionAngle type,
Frame frame,
FieldAbsoluteDate<T> date,
double mu) |
Creates a new instance.
|
FieldKeplerianOrbit(FieldPVCoordinates<T> FieldPVCoordinates,
Frame frame,
FieldAbsoluteDate<T> date,
double mu) |
Constructor from Cartesian parameters.
|
FieldKeplerianOrbit(TimeStampedFieldPVCoordinates<T> pvCoordinates,
Frame frame,
double mu) |
Constructor from Cartesian parameters.
|
FieldKeplerianOrbit(T a,
T e,
T i,
T pa,
T raan,
T anomaly,
PositionAngle type,
Frame frame,
FieldAbsoluteDate<T> date,
double mu) |
Creates a new instance.
|
FieldKeplerianOrbit(T a,
T e,
T i,
T pa,
T raan,
T anomaly,
T aDot,
T eDot,
T iDot,
T paDot,
T raanDot,
T anomalyDot,
PositionAngle type,
Frame frame,
FieldAbsoluteDate<T> date,
double mu) |
Creates a new instance.
|
FieldOrbit(Frame frame,
FieldAbsoluteDate<T> date,
double mu) |
Default constructor.
|
FieldOrbit(TimeStampedFieldPVCoordinates<T> FieldPVCoordinates,
Frame frame,
double mu) |
Set the orbit from Cartesian parameters.
|
KeplerianOrbit(double a,
double e,
double i,
double pa,
double raan,
double anomaly,
double aDot,
double eDot,
double iDot,
double paDot,
double raanDot,
double anomalyDot,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu) |
Creates a new instance.
|
KeplerianOrbit(double a,
double e,
double i,
double pa,
double raan,
double anomaly,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu) |
Creates a new instance.
|
KeplerianOrbit(PVCoordinates pvCoordinates,
Frame frame,
AbsoluteDate date,
double mu) |
Constructor from Cartesian parameters.
|
KeplerianOrbit(TimeStampedPVCoordinates pvCoordinates,
Frame frame,
double mu) |
Constructor from Cartesian parameters.
|
Orbit(Frame frame,
AbsoluteDate date,
double mu) |
Default constructor.
|
Orbit(TimeStampedPVCoordinates pvCoordinates,
Frame frame,
double mu) |
Set the orbit from Cartesian parameters.
|
Modifier and Type | Method | Description |
---|---|---|
Frame |
AbstractPropagator.getFrame() |
Get the frame in which the orbit is propagated.
|
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 |
FieldSpacecraftState.getFrame() |
Get the inertial frame.
|
Frame |
Propagator.getFrame() |
Get the frame in which the orbit is propagated.
|
Frame |
SpacecraftState.getFrame() |
Get the inertial frame.
|
Modifier and Type | Method | Description |
---|---|---|
TimeStampedPVCoordinates |
AbstractPropagator.getPVCoordinates(AbsoluteDate date,
Frame frame) |
Get the
PVCoordinates of the body in the selected frame. |
TimeStampedFieldPVCoordinates<T> |
FieldAbstractPropagator.getPVCoordinates(FieldAbsoluteDate<T> date,
Frame frame) |
Get the
FieldPVCoordinates of the body in the selected frame. |
TimeStampedFieldPVCoordinates<T> |
FieldSpacecraftState.getPVCoordinates(Frame outputFrame) |
Get the
TimeStampedFieldPVCoordinates in given output frame. |
TimeStampedPVCoordinates |
SpacecraftState.getPVCoordinates(Frame outputFrame) |
Get the
TimeStampedPVCoordinates in given output frame. |
Modifier and Type | Method | Description |
---|---|---|
Frame |
Ephemeris.getFrame() |
Modifier and Type | Method | Description |
---|---|---|
TimeStampedPVCoordinates |
AggregateBoundedPropagator.getPVCoordinates(AbsoluteDate date,
Frame frame) |
|
TimeStampedPVCoordinates |
Ephemeris.getPVCoordinates(AbsoluteDate date,
Frame f) |
Get the
PVCoordinates of the body in the selected frame. |
Modifier and Type | Method | Description |
---|---|---|
Frame |
GPSPropagator.getECEF() |
Gets the Earth Centered Earth Fixed frame used to propagate GPS orbits according to the
GPS Interface Specification.
|
Frame |
GPSPropagator.getECI() |
Gets the Earth Centered Inertial frame used to propagate the orbit.
|
Frame |
GPSPropagator.getFrame() |
Get the frame in which the orbit is propagated.
|
Modifier and Type | Method | Description |
---|---|---|
GPSPropagator.Builder |
GPSPropagator.Builder.ecef(Frame bodyFixed) |
Sets the Earth Centered Earth Fixed frame assimilated to the WGS84 ECEF.
|
GPSPropagator.Builder |
GPSPropagator.Builder.eci(Frame inertial) |
Sets the Earth Centered Inertial frame used for propagation.
|
Modifier and Type | Method | Description |
---|---|---|
Frame |
TLEPropagator.getFrame() |
Get the frame in which the orbit is propagated.
|
Modifier and Type | Method | Description |
---|---|---|
Frame |
AbstractPropagatorBuilder.getFrame() |
Get the frame in which the orbit is propagated.
|
protected Frame |
AbstractPropagatorConverter.getFrame() |
Get the frame of the initial state.
|
Frame |
PropagatorBuilder.getFrame() |
Get the frame in which the orbit is propagated.
|
Modifier and Type | Method | Description |
---|---|---|
Frame |
FieldNodeDetector.getFrame() |
Get the frame in which the equator is defined.
|
Frame |
GroundFieldOfViewDetector.getFrame() |
Get the sensor reference frame.
|
Frame |
NodeDetector.getFrame() |
Get the frame in which the equator is defined.
|
Constructor | Description |
---|---|
FieldNodeDetector(FieldOrbit<T> orbit,
Frame frame) |
Build a new instance.
|
FieldNodeDetector(T threshold,
FieldOrbit<T> orbit,
Frame frame) |
Build a new instance.
|
GroundFieldOfViewDetector(Frame frame,
FieldOfView fov) |
Build a new instance.
|
NodeDetector(double threshold,
Orbit orbit,
Frame frame) |
Build a new instance.
|
NodeDetector(Orbit orbit,
Frame frame) |
Build a new instance.
|
Modifier and Type | Method | Description |
---|---|---|
Frame |
FieldIntegratedEphemeris.getFrame() |
|
Frame |
FieldStateMapper.getFrame() |
Get the inertial frame.
|
Frame |
IntegratedEphemeris.getFrame() |
|
Frame |
StateMapper.getFrame() |
Get the inertial frame.
|
Modifier and Type | Method | Description |
---|---|---|
protected abstract StateMapper |
AbstractIntegratedPropagator.createMapper(AbsoluteDate referenceDate,
double mu,
OrbitType orbitType,
PositionAngle positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame) |
Create a mapper between raw double components and spacecraft state.
|
protected abstract FieldStateMapper<T> |
FieldAbstractIntegratedPropagator.createMapper(FieldAbsoluteDate<T> referenceDate,
double mu,
OrbitType orbitType,
PositionAngle positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame) |
Create a mapper between raw double components and spacecraft state.
|
TimeStampedFieldPVCoordinates<T> |
FieldIntegratedEphemeris.getPVCoordinates(FieldAbsoluteDate<T> date,
Frame frame) |
Get the
FieldPVCoordinates of the body in the selected frame. |
TimeStampedPVCoordinates |
IntegratedEphemeris.getPVCoordinates(AbsoluteDate date,
Frame frame) |
Get the
PVCoordinates of the body in the selected frame. |
Constructor | Description |
---|---|
FieldStateMapper(FieldAbsoluteDate<T> referenceDate,
double mu,
OrbitType orbitType,
PositionAngle positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame) |
Simple constructor.
|
StateMapper(AbsoluteDate referenceDate,
double mu,
OrbitType orbitType,
PositionAngle positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame) |
Simple constructor.
|
Modifier and Type | Method | Description |
---|---|---|
protected FieldStateMapper<T> |
FieldNumericalPropagator.createMapper(FieldAbsoluteDate<T> referenceDate,
double mu,
OrbitType orbitType,
PositionAngle positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame) |
Create a mapper between raw double components and spacecraft state.
|
protected StateMapper |
NumericalPropagator.createMapper(AbsoluteDate referenceDate,
double mu,
OrbitType orbitType,
PositionAngle positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame) |
Create a mapper between raw double components and spacecraft state.
|
TimeStampedFieldPVCoordinates<T> |
FieldNumericalPropagator.getPVCoordinates(FieldAbsoluteDate<T> date,
Frame frame) |
Get the
FieldPVCoordinates of the body in the selected frame. |
TimeStampedPVCoordinates |
NumericalPropagator.getPVCoordinates(AbsoluteDate date,
Frame frame) |
Get the
PVCoordinates of the body in the selected frame. |
Modifier and Type | Method | Description |
---|---|---|
protected StateMapper |
DSSTPropagator.createMapper(AbsoluteDate referenceDate,
double mu,
OrbitType ignoredOrbitType,
PositionAngle ignoredPositionAngleType,
AttitudeProvider attitudeProvider,
Frame frame) |
Create a mapper between raw double components and spacecraft state.
|
Constructor | Description |
---|---|
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 | Description |
---|---|---|
Frame |
AuxiliaryElements.getFrame() |
Get the definition frame of the orbit.
|
Modifier and Type | Method | Description |
---|---|---|
<T extends org.hipparchus.RealFieldElement<T>> |
ExtendedPVCoordinatesProvider.getPVCoordinates(FieldAbsoluteDate<T> date,
Frame frame) |
Get the
FieldPVCoordinates 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. |
TimeStampedPVCoordinates |
PVCoordinatesProvider.getPVCoordinates(AbsoluteDate date,
Frame frame) |
Get the
PVCoordinates of the body in the selected frame. |
PVCoordinatesProvider |
TimeStampedPVCoordinates.toTaylorProvider(Frame instanceFrame) |
Create a local provider using simply Taylor expansion through
TimeStampedPVCoordinates.shiftedBy(double) . |
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