| 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.data |
This package provide base classes for exploring the configured data
directory tree and read external data that can be used by the library.
|
| org.orekit.estimation.measurements |
The measurements package defines everything that is related to orbit
determination measurements.
|
| 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.empirical |
This package provides empirical forces.
|
| 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.maneuvers.propulsion |
This package provides propulsion models intended to be used with class
Maneuver. |
| org.orekit.forces.maneuvers.trigger |
This package provides maneuver triggers' models intended to be used with class
Maneuver. |
| org.orekit.forces.radiation |
This package provides all radiation pressure related forces.
|
| org.orekit.frames |
This package provides classes to handle frames and transforms between them.
|
| org.orekit.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.ionosphere |
This package provides models that simulate the impact of the ionosphere.
|
| org.orekit.models.earth.troposphere |
This package provides models that simulate the impact of the troposphere.
|
| 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.tle |
This package provides classes to read and extrapolate tle's.
|
| org.orekit.propagation.events |
This package provides interfaces and classes dealing with events occurring during propagation.
|
| org.orekit.propagation.events.handlers |
This package provides an interface and classes dealing with events occurrence only.
|
| 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.time |
This independent package provides classes to handle epochs, time scales,
and to compare instants together.
|
| org.orekit.utils |
This package provides useful objects.
|
| Modifier and Type | Method and Description |
|---|---|
FieldAbsoluteDate<T> |
FieldAttitude.getDate()
Get the date of attitude parameters.
|
| Modifier and Type | Method and Description |
|---|---|
<T extends CalculusFieldElement<T>> |
YawCompensation.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
LofOffset.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
AttitudeProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
InertialProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
FixedRate.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
AttitudesSequence.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
GroundPointing.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
SpinStabilized.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
LofOffsetPointing.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
TabulatedLofOffset.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
YawSteering.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
AggregateBoundedAttitudeProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
TabulatedProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
CelestialBodyPointed.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends CalculusFieldElement<T>> |
YawCompensation.getBaseState(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the base system state at given date, without compensation.
|
<T extends CalculusFieldElement<T>> |
YawSteering.getBaseState(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the base system state at given date, without compensation.
|
<T extends CalculusFieldElement<T>> |
YawCompensation.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
<T extends CalculusFieldElement<T>> |
NadirPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
abstract <T extends CalculusFieldElement<T>> |
GroundPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
<T extends CalculusFieldElement<T>> |
LofOffsetPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
<T extends CalculusFieldElement<T>> |
YawSteering.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
<T extends CalculusFieldElement<T>> |
TargetPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
<T extends CalculusFieldElement<T>> |
BodyCenterPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
<T extends CalculusFieldElement<T>> |
YawCompensation.getYawAngle(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the yaw compensation angle at date.
|
FieldAttitude<T> |
FieldAttitude.interpolate(FieldAbsoluteDate<T> interpolationDate,
Stream<FieldAttitude<T>> sample)
Get an interpolated instance.
|
| Constructor and Description |
|---|
FieldAttitude(FieldAbsoluteDate<T> date,
Frame referenceFrame,
FieldAngularCoordinates<T> orientation)
Creates a new instance.
|
FieldAttitude(FieldAbsoluteDate<T> date,
Frame referenceFrame,
FieldRotation<T> attitude,
FieldVector3D<T> spin,
FieldVector3D<T> acceleration)
Creates a new instance.
|
FieldAttitude(FieldAbsoluteDate<T> date,
Frame referenceFrame,
Rotation attitude,
Vector3D spin,
Vector3D acceleration,
Field<T> field)
Creates a new instance.
|
| Modifier and Type | Method and Description |
|---|---|
<T extends CalculusFieldElement<T>> |
OneAxisEllipsoid.getCartesianIntersectionPoint(FieldLine<T> line,
FieldVector3D<T> close,
Frame frame,
FieldAbsoluteDate<T> date)
Get the intersection point of a line with the surface of the body.
|
<T extends CalculusFieldElement<T>> |
BodyShape.getIntersectionPoint(FieldLine<T> line,
FieldVector3D<T> close,
Frame frame,
FieldAbsoluteDate<T> date)
Get the intersection point of a line with the surface of the body.
|
<T extends CalculusFieldElement<T>> |
OneAxisEllipsoid.getIntersectionPoint(FieldLine<T> line,
FieldVector3D<T> close,
Frame frame,
FieldAbsoluteDate<T> date)
Get the intersection point of a line with the surface of the body.
|
default <T extends CalculusFieldElement<T>> |
IAUPole.getNode(FieldAbsoluteDate<T> date)
Get the body Q Node direction in ICRF frame.
|
<T extends CalculusFieldElement<T>> |
IAUPole.getPole(FieldAbsoluteDate<T> date)
Get the body North pole direction in ICRF frame.
|
<T extends CalculusFieldElement<T>> |
IAUPole.getPrimeMeridianAngle(FieldAbsoluteDate<T> date)
Get the prime meridian angle.
|
<T extends CalculusFieldElement<T>> |
JPLEphemeridesLoader.RawPVProvider.getRawPV(FieldAbsoluteDate<T> date)
Get the position-velocity at date.
|
<T extends CalculusFieldElement<T>> |
BodyShape.transform(FieldVector3D<T> point,
Frame frame,
FieldAbsoluteDate<T> date)
Transform a Cartesian point to a surface-relative point.
|
<T extends CalculusFieldElement<T>> |
OneAxisEllipsoid.transform(FieldVector3D<T> point,
Frame frame,
FieldAbsoluteDate<T> date)
Transform a Cartesian point to a surface-relative point.
|
| Modifier and Type | Method and Description |
|---|---|
FieldAbsoluteDate<T> |
FieldDelaunayArguments.getDate()
Get the date.
|
| Modifier and Type | Method and Description |
|---|---|
<T extends CalculusFieldElement<T>> |
FundamentalNutationArguments.evaluateAll(FieldAbsoluteDate<T> date)
Evaluate all fundamental arguments for the current date (Delaunay plus planetary).
|
| Constructor and Description |
|---|
FieldBodiesElements(FieldAbsoluteDate<T> date,
T tc,
T gamma,
T gammaDot,
T l,
T lDot,
T lPrime,
T lPrimeDot,
T f,
T fDot,
T d,
T dDot,
T omega,
T omegaDot,
T lMe,
T lMeDot,
T lVe,
T lVeDot,
T lE,
T lEDot,
T lMa,
T lMaDot,
T lJu,
T lJuDot,
T lSa,
T lSaDot,
T lUr,
T lUrDot,
T lNe,
T lNeDot,
T pa,
T paDot)
Simple constructor.
|
FieldDelaunayArguments(FieldAbsoluteDate<T> date,
T tc,
T gamma,
T gammaDot,
T l,
T lDot,
T lPrime,
T lPrimeDot,
T f,
T fDot,
T d,
T dDot,
T omega,
T omegaDot)
Simple constructor.
|
| Modifier and Type | Method and Description |
|---|---|
FieldTransform<Gradient> |
GroundStation.getOffsetToInertial(Frame inertial,
FieldAbsoluteDate<Gradient> offsetCompensatedDate,
int freeParameters,
Map<String,Integer> indices)
Get the transform between offset frame and inertial frame with derivatives.
|
FieldTransform<Gradient> |
EstimatedEarthFrameProvider.getTransform(FieldAbsoluteDate<Gradient> date,
int freeParameters,
Map<String,Integer> indices)
Get the transform with derivatives.
|
<T extends CalculusFieldElement<T>> |
EstimatedEarthFrameProvider.getTransform(FieldAbsoluteDate<T> date)
Get the
FieldTransform corresponding to specified date. |
static <T extends CalculusFieldElement<T>> |
AbstractMeasurement.signalTimeOfFlight(TimeStampedFieldPVCoordinates<T> adjustableEmitterPV,
FieldVector3D<T> receiverPosition,
FieldAbsoluteDate<T> signalArrivalDate)
Compute propagation delay on a link leg (typically downlink or uplink).
|
| Modifier and Type | Method and Description |
|---|---|
<T extends CalculusFieldElement<T>> |
BoxAndSolarArraySpacecraft.dragAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
FieldVector3D<T> position,
FieldRotation<T> rotation,
T mass,
T density,
FieldVector3D<T> relativeVelocity,
T[] parameters)
Compute the acceleration due to drag.
|
<T extends CalculusFieldElement<T>> |
BoxAndSolarArraySpacecraft.getNormal(FieldAbsoluteDate<T> date,
Frame frame,
FieldVector3D<T> position,
FieldRotation<T> rotation)
Get solar array normal in spacecraft frame.
|
default <T extends CalculusFieldElement<T>> |
ForceModel.init(FieldSpacecraftState<T> initialState,
FieldAbsoluteDate<T> target)
Initialize the force model at the start of propagation.
|
<T extends CalculusFieldElement<T>> |
BoxAndSolarArraySpacecraft.radiationPressureAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
FieldVector3D<T> position,
FieldRotation<T> rotation,
T mass,
FieldVector3D<T> flux,
T[] parameters)
Compute the acceleration due to radiation pressure.
|
| Modifier and Type | Method and Description |
|---|---|
<T extends CalculusFieldElement<T>> |
IsotropicDrag.dragAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
FieldVector3D<T> position,
FieldRotation<T> rotation,
T mass,
T density,
FieldVector3D<T> relativeVelocity,
T[] parameters)
Compute the acceleration due to drag.
|
<T extends CalculusFieldElement<T>> |
DragSensitive.dragAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
FieldVector3D<T> position,
FieldRotation<T> rotation,
T mass,
T density,
FieldVector3D<T> relativeVelocity,
T[] parameters)
Compute the acceleration due to drag.
|
<T extends CalculusFieldElement<T>> |
TimeSpanDragForce.extractParameters(T[] parameters,
FieldAbsoluteDate<T> date)
Extract the proper parameter drivers' values from the array in input of the
acceleration method. |
| Modifier and Type | Method and Description |
|---|---|
<T extends CalculusFieldElement<T>> |
TimeSpanParametricAcceleration.extractParameters(T[] parameters,
FieldAbsoluteDate<T> date)
Extract the proper parameter drivers' values from the array in input of the
acceleration method. |
| Modifier and Type | Method and Description |
|---|---|
<T extends CalculusFieldElement<T>> |
HolmesFeatherstoneAttractionModel.gradient(FieldAbsoluteDate<T> date,
FieldVector3D<T> position,
T mu)
Compute the gradient of the non-central part of the gravity field.
|
| Modifier and Type | Method and Description |
|---|---|
<T extends CalculusFieldElement<T>> |
Maneuver.init(FieldSpacecraftState<T> initialState,
FieldAbsoluteDate<T> target)
Initialize the force model at the start of propagation.
|
| Modifier and Type | Method and Description |
|---|---|
<T extends CalculusFieldElement<T>> |
ThrustDirectionAndAttitudeProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
default <T extends CalculusFieldElement<T>> |
PropulsionModel.init(FieldSpacecraftState<T> initialState,
FieldAbsoluteDate<T> target)
Initialization method.
|
| Modifier and Type | Method and Description |
|---|---|
default void |
FieldManeuverTriggersResetter.init(FieldSpacecraftState<T> initialState,
FieldAbsoluteDate<T> target)
Initialization method called at propagation start.
|
<T extends CalculusFieldElement<T>> |
AbstractManeuverTriggers.init(FieldSpacecraftState<T> initialState,
FieldAbsoluteDate<T> target)
Initialization method called at propagation start.
|
default <T extends CalculusFieldElement<T>> |
ManeuverTriggers.init(FieldSpacecraftState<T> initialState,
FieldAbsoluteDate<T> target)
Initialization method called at propagation start.
|
protected <T extends CalculusFieldElement<T>> |
AbstractManeuverTriggers.initializeResetters(FieldSpacecraftState<T> initialState,
FieldAbsoluteDate<T> target)
Initialize resetters.
|
<S extends CalculusFieldElement<S>> |
AbstractManeuverTriggers.isFiring(FieldAbsoluteDate<S> date,
S[] parameters)
Find out if the maneuver is firing or not.
|
<T extends CalculusFieldElement<T>> |
EventBasedManeuverTriggers.isFiring(FieldAbsoluteDate<T> date,
T[] parameters)
Find out if the maneuver is firing or not.
|
<T extends CalculusFieldElement<T>> |
ManeuverTriggers.isFiring(FieldAbsoluteDate<T> date,
T[] parameters)
Find out if the maneuver is firing or not.
|
| Modifier and Type | Method and Description |
|---|---|
<T extends CalculusFieldElement<T>> |
SolarRadiationPressure.getLightingRatio(FieldVector3D<T> position,
Frame frame,
FieldAbsoluteDate<T> date)
Get the lighting ratio ([0-1]).
|
<T extends CalculusFieldElement<T>> |
SolarRadiationPressure.getTotalLightingRatio(FieldVector3D<T> position,
Frame frame,
FieldAbsoluteDate<T> date)
Get the total lighting ratio ([0-1]).
|
<T extends CalculusFieldElement<T>> |
RadiationSensitive.radiationPressureAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
FieldVector3D<T> position,
FieldRotation<T> rotation,
T mass,
FieldVector3D<T> flux,
T[] parameters)
Compute the acceleration due to radiation pressure.
|
<T extends CalculusFieldElement<T>> |
IsotropicRadiationSingleCoefficient.radiationPressureAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
FieldVector3D<T> position,
FieldRotation<T> rotation,
T mass,
FieldVector3D<T> flux,
T[] parameters)
Compute the acceleration due to radiation pressure.
|
<T extends CalculusFieldElement<T>> |
IsotropicRadiationCNES95Convention.radiationPressureAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
FieldVector3D<T> position,
FieldRotation<T> rotation,
T mass,
FieldVector3D<T> flux,
T[] parameters)
Compute the acceleration due to radiation pressure.
|
<T extends CalculusFieldElement<T>> |
IsotropicRadiationClassicalConvention.radiationPressureAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
FieldVector3D<T> position,
FieldRotation<T> rotation,
T mass,
FieldVector3D<T> flux,
T[] parameters)
Compute the acceleration due to radiation pressure.
|
| Modifier and Type | Method and Description |
|---|---|
FieldAbsoluteDate<T> |
FieldTransform.getFieldDate()
Get the date.
|
| Modifier and Type | Method and Description |
|---|---|
<T extends CalculusFieldElement<T>> |
TopocentricFrame.getAzimuth(FieldVector3D<T> extPoint,
Frame frame,
FieldAbsoluteDate<T> date)
Get the azimuth of a point with regards to the topocentric frame center point.
|
<T extends CalculusFieldElement<T>> |
TopocentricFrame.getElevation(FieldVector3D<T> extPoint,
Frame frame,
FieldAbsoluteDate<T> date)
Get the elevation of a point with regards to the local point.
|
<T extends CalculusFieldElement<T>> |
EOPHistory.getEquinoxNutationCorrection(FieldAbsoluteDate<T> date)
Get the correction to the nutation parameters for equinox-based paradigm.
|
<T extends CalculusFieldElement<T>> |
EOPHistory.getLOD(FieldAbsoluteDate<T> date)
Get the LoD (Length of Day) value.
|
static <T extends CalculusFieldElement<T>> |
FramesFactory.getNonInterpolatingTransform(Frame from,
Frame to,
FieldAbsoluteDate<T> date)
Get the transform between two frames, suppressing all interpolation.
|
<T extends CalculusFieldElement<T>> |
EOPHistory.getNonRotatinOriginNutationCorrection(FieldAbsoluteDate<T> date)
Get the correction to the nutation parameters for Non-Rotating Origin paradigm.
|
<T extends CalculusFieldElement<T>> |
EOPHistory.getPoleCorrection(FieldAbsoluteDate<T> date)
Get the pole IERS Reference Pole correction.
|
<T extends CalculusFieldElement<T>> |
TopocentricFrame.getRange(FieldVector3D<T> extPoint,
Frame frame,
FieldAbsoluteDate<T> date)
Get the range of a point with regards to the topocentric frame center point.
|
<T extends CalculusFieldElement<T>> |
TopocentricFrame.getRangeRate(FieldPVCoordinates<T> extPV,
Frame frame,
FieldAbsoluteDate<T> date)
Get the range rate of a point with regards to the topocentric frame center point.
|
<T extends CalculusFieldElement<T>> |
InterpolatingTransformProvider.getTransform(FieldAbsoluteDate<T> date)
Get the
FieldTransform corresponding to specified date. |
<T extends CalculusFieldElement<T>> |
FixedTransformProvider.getTransform(FieldAbsoluteDate<T> date)
Get the
FieldTransform corresponding to specified date. |
<T extends CalculusFieldElement<T>> |
L1TransformProvider.getTransform(FieldAbsoluteDate<T> date)
Get the
FieldTransform corresponding to specified date. |
<T extends CalculusFieldElement<T>> |
GTODProvider.getTransform(FieldAbsoluteDate<T> date)
Get the
FieldTransform corresponding to specified date. |
<T extends CalculusFieldElement<T>> |
TransformProvider.getTransform(FieldAbsoluteDate<T> date)
Get the
FieldTransform corresponding to specified date. |
<T extends CalculusFieldElement<T>> |
ShiftingTransformProvider.getTransform(FieldAbsoluteDate<T> date)
Get the
FieldTransform corresponding to specified date. |
<T extends CalculusFieldElement<T>> |
EclipticProvider.getTransform(FieldAbsoluteDate<T> date) |
<T extends CalculusFieldElement<T>> |
ITRFVersion.Converter.getTransform(FieldAbsoluteDate<T> date)
Get the
FieldTransform corresponding to specified date. |
<T extends CalculusFieldElement<T>> |
HelmertTransformation.getTransform(FieldAbsoluteDate<T> date)
Get the
FieldTransform corresponding to specified date. |
<T extends CalculusFieldElement<T>> |
Frame.getTransformTo(Frame destination,
FieldAbsoluteDate<T> date)
Get the transform from the instance to another frame.
|
<T extends CalculusFieldElement<T>> |
EOPHistory.getUT1MinusUTC(FieldAbsoluteDate<T> date)
Get the UT1-UTC value.
|
static <T extends CalculusFieldElement<T>> |
FieldTransform.interpolate(FieldAbsoluteDate<T> date,
CartesianDerivativesFilter cFilter,
AngularDerivativesFilter aFilter,
Collection<FieldTransform<T>> sample)
Interpolate a transform from a sample set of existing transforms.
|
static <T extends CalculusFieldElement<T>> |
FieldTransform.interpolate(FieldAbsoluteDate<T> date,
CartesianDerivativesFilter cFilter,
AngularDerivativesFilter aFilter,
Stream<FieldTransform<T>> sample)
Interpolate a transform from a sample set of existing transforms.
|
static <T extends CalculusFieldElement<T>> |
FieldTransform.interpolate(FieldAbsoluteDate<T> interpolationDate,
Collection<FieldTransform<T>> sample)
Interpolate a transform from a sample set of existing transforms.
|
<T extends CalculusFieldElement<T>> |
LOFType.transformFromInertial(FieldAbsoluteDate<T> date,
FieldPVCoordinates<T> pv)
Get the transform from an inertial frame defining position-velocity and the local orbital frame.
|
| Constructor and Description |
|---|
FieldTransform(FieldAbsoluteDate<T> date,
FieldAngularCoordinates<T> angular)
Build a rotation transform.
|
FieldTransform(FieldAbsoluteDate<T> date,
FieldPVCoordinates<T> cartesian)
Build a translation transform, with its first time derivative.
|
FieldTransform(FieldAbsoluteDate<T> date,
FieldRotation<T> rotation)
Build a rotation transform.
|
FieldTransform(FieldAbsoluteDate<T> date,
FieldRotation<T> rotation,
FieldVector3D<T> rotationRate)
Build a rotation transform.
|
FieldTransform(FieldAbsoluteDate<T> date,
FieldRotation<T> rotation,
FieldVector3D<T> rotationRate,
FieldVector3D<T> rotationAcceleration)
Build a rotation transform.
|
FieldTransform(FieldAbsoluteDate<T> date,
FieldTransform<T> first,
FieldTransform<T> second)
Build a transform by combining two existing ones.
|
FieldTransform(FieldAbsoluteDate<T> date,
FieldVector3D<T> translation)
Build a translation transform.
|
FieldTransform(FieldAbsoluteDate<T> date,
FieldVector3D<T> translation,
FieldVector3D<T> velocity)
Build a translation transform, with its first time derivative.
|
FieldTransform(FieldAbsoluteDate<T> date,
FieldVector3D<T> translation,
FieldVector3D<T> velocity,
FieldVector3D<T> acceleration)
Build a translation transform, with its first and second time derivatives.
|
| Modifier and Type | Method and Description |
|---|---|
<T extends CalculusFieldElement<T>> |
Geoid.getIntersectionPoint(FieldLine<T> lineInFrame,
FieldVector3D<T> closeInFrame,
Frame frame,
FieldAbsoluteDate<T> date)
Get the intersection point of a line with the surface of the body.
|
<T extends CalculusFieldElement<T>> |
Geoid.transform(FieldVector3D<T> point,
Frame frame,
FieldAbsoluteDate<T> date)
Transform a Cartesian point to a surface-relative point.
|
| Modifier and Type | Method and Description |
|---|---|
<T extends CalculusFieldElement<T>> |
DTM2000.getDensity(FieldAbsoluteDate<T> date,
FieldVector3D<T> position,
Frame frame)
Get the local density.
|
<T extends CalculusFieldElement<T>> |
NRLMSISE00.getDensity(FieldAbsoluteDate<T> date,
FieldVector3D<T> position,
Frame frame)
Get the local density.
|
<T extends CalculusFieldElement<T>> |
Atmosphere.getDensity(FieldAbsoluteDate<T> date,
FieldVector3D<T> position,
Frame frame)
Get the local density.
|
<T extends CalculusFieldElement<T>> |
HarrisPriester.getDensity(FieldAbsoluteDate<T> date,
FieldVector3D<T> position,
Frame frame)
Get the local density at some position.
|
<T extends CalculusFieldElement<T>> |
SimpleExponentialAtmosphere.getDensity(FieldAbsoluteDate<T> date,
FieldVector3D<T> position,
Frame frame) |
<T extends CalculusFieldElement<T>> |
JB2008.getDensity(FieldAbsoluteDate<T> date,
FieldVector3D<T> position,
Frame frame)
Get the local density.
|
default <T extends CalculusFieldElement<T>> |
Atmosphere.getVelocity(FieldAbsoluteDate<T> date,
FieldVector3D<T> position,
Frame frame)
Get the inertial velocity of atmosphere molecules.
|
| Modifier and Type | Method and Description |
|---|---|
<T extends CalculusFieldElement<T>> |
GlobalIonosphereMapModel.getTEC(FieldAbsoluteDate<T> date,
GeodeticPoint recPoint)
Computes the Total Electron Content (TEC) at a given date by performing a
temporal interpolation with the two closest date in the IONEX file.
|
<T extends CalculusFieldElement<T>> |
KlobucharIonoModel.pathDelay(FieldAbsoluteDate<T> date,
FieldGeodeticPoint<T> geo,
T elevation,
T azimuth,
double frequency,
T[] parameters)
Calculates the ionospheric path delay for the signal path from a ground
station to a satellite.
|
<T extends CalculusFieldElement<T>> |
GlobalIonosphereMapModel.pathDelay(FieldAbsoluteDate<T> date,
GeodeticPoint geo,
T elevation,
double frequency)
Calculates the ionospheric path delay for the signal path from a ground
station to a satellite.
|
<T extends CalculusFieldElement<T>> |
NeQuickModel.stec(FieldAbsoluteDate<T> date,
FieldGeodeticPoint<T> recP,
FieldGeodeticPoint<T> satP)
This method allows the computation of the Stant Total Electron Content (STEC).
|
| Modifier and Type | Method and Description |
|---|---|
<T extends CalculusFieldElement<T>> |
ViennaOneModel.computeZenithDelay(FieldGeodeticPoint<T> point,
T[] parameters,
FieldAbsoluteDate<T> date)
This method allows the computation of the zenith hydrostatic and
zenith wet delay.
|
<T extends CalculusFieldElement<T>> |
MendesPavlisModel.computeZenithDelay(FieldGeodeticPoint<T> point,
T[] parameters,
FieldAbsoluteDate<T> date)
This method allows the computation of the zenith hydrostatic and
zenith wet delay.
|
<T extends CalculusFieldElement<T>> |
ViennaThreeModel.computeZenithDelay(FieldGeodeticPoint<T> point,
T[] parameters,
FieldAbsoluteDate<T> date)
This method allows the computation of the zenith hydrostatic and
zenith wet delay.
|
<T extends CalculusFieldElement<T>> |
TimeSpanEstimatedTroposphericModel.extractParameters(T[] parameters,
FieldAbsoluteDate<T> date)
Extract the proper parameter drivers' values from the array in input of the
pathDelay method. |
<T extends CalculusFieldElement<T>> |
ViennaOneModel.mappingFactors(T elevation,
FieldGeodeticPoint<T> point,
FieldAbsoluteDate<T> date)
This method allows the computation of the hydrostatic and
wet mapping functions.
|
<T extends CalculusFieldElement<T>> |
GlobalMappingFunctionModel.mappingFactors(T elevation,
FieldGeodeticPoint<T> point,
FieldAbsoluteDate<T> date)
This method allows the computation of the hydrostatic and
wet mapping functions.
|
<T extends CalculusFieldElement<T>> |
NiellMappingFunctionModel.mappingFactors(T elevation,
FieldGeodeticPoint<T> point,
FieldAbsoluteDate<T> date)
This method allows the computation of the hydrostatic and
wet mapping functions.
|
<T extends CalculusFieldElement<T>> |
MappingFunction.mappingFactors(T elevation,
FieldGeodeticPoint<T> point,
FieldAbsoluteDate<T> date)
This method allows the computation of the hydrostatic and
wet mapping functions.
|
<T extends CalculusFieldElement<T>> |
MendesPavlisModel.mappingFactors(T elevation,
FieldGeodeticPoint<T> point,
FieldAbsoluteDate<T> date)
With the Mendes Pavlis tropospheric model, the mapping
function is not split into hydrostatic and wet component.
|
<T extends CalculusFieldElement<T>> |
ViennaThreeModel.mappingFactors(T elevation,
FieldGeodeticPoint<T> point,
FieldAbsoluteDate<T> date)
This method allows the computation of the hydrostatic and
wet mapping functions.
|
<T extends CalculusFieldElement<T>> |
ViennaOneModel.pathDelay(T elevation,
FieldGeodeticPoint<T> point,
T[] parameters,
FieldAbsoluteDate<T> date)
Calculates the tropospheric path delay for the signal path from a ground
station to a satellite.
|
<T extends CalculusFieldElement<T>> |
DiscreteTroposphericModel.pathDelay(T elevation,
FieldGeodeticPoint<T> point,
T[] parameters,
FieldAbsoluteDate<T> date)
Calculates the tropospheric path delay for the signal path from a ground
station to a satellite.
|
<T extends CalculusFieldElement<T>> |
FixedTroposphericDelay.pathDelay(T elevation,
FieldGeodeticPoint<T> point,
T[] parameters,
FieldAbsoluteDate<T> date)
Calculates the tropospheric path delay for the signal path from a ground
station to a satellite.
|
<T extends CalculusFieldElement<T>> |
MendesPavlisModel.pathDelay(T elevation,
FieldGeodeticPoint<T> point,
T[] parameters,
FieldAbsoluteDate<T> date)
Calculates the tropospheric path delay for the signal path from a ground
station to a satellite.
|
<T extends CalculusFieldElement<T>> |
MariniMurrayModel.pathDelay(T elevation,
FieldGeodeticPoint<T> point,
T[] parameters,
FieldAbsoluteDate<T> date)
Calculates the tropospheric path delay for the signal path from a ground
station to a satellite.
|
<T extends CalculusFieldElement<T>> |
SaastamoinenModel.pathDelay(T elevation,
FieldGeodeticPoint<T> point,
T[] parameters,
FieldAbsoluteDate<T> date)
Calculates the tropospheric path delay for the signal path from a ground
station to a satellite.
|
<T extends CalculusFieldElement<T>> |
ViennaThreeModel.pathDelay(T elevation,
FieldGeodeticPoint<T> point,
T[] parameters,
FieldAbsoluteDate<T> date)
Calculates the tropospheric path delay for the signal path from a ground
station to a satellite.
|
<T extends CalculusFieldElement<T>> |
EstimatedTroposphericModel.pathDelay(T elevation,
FieldGeodeticPoint<T> point,
T[] parameters,
FieldAbsoluteDate<T> date)
Calculates the tropospheric path delay for the signal path from a ground
station to a satellite.
|
<T extends CalculusFieldElement<T>> |
TimeSpanEstimatedTroposphericModel.pathDelay(T elevation,
FieldGeodeticPoint<T> point,
T[] parameters,
FieldAbsoluteDate<T> date)
Calculates the tropospheric path delay for the signal path from a ground
station to a satellite.
|
| Modifier and Type | Method and Description |
|---|---|
FieldAbsoluteDate<T> |
FieldOrbit.getDate()
Get the date of orbital parameters.
|
| Modifier and Type | Method and Description |
|---|---|
TimeStampedFieldPVCoordinates<T> |
FieldOrbit.getPVCoordinates(FieldAbsoluteDate<T> otherDate,
Frame otherFrame)
Get the
FieldPVCoordinates of the body in the selected frame. |
FieldKeplerianOrbit<T> |
FieldKeplerianOrbit.interpolate(FieldAbsoluteDate<T> date,
Stream<FieldOrbit<T>> sample)
Get an interpolated instance.
|
FieldCircularOrbit<T> |
FieldCircularOrbit.interpolate(FieldAbsoluteDate<T> date,
Stream<FieldOrbit<T>> sample)
Get an interpolated instance.
|
FieldEquinoctialOrbit<T> |
FieldEquinoctialOrbit.interpolate(FieldAbsoluteDate<T> date,
Stream<FieldOrbit<T>> sample)
Get an interpolated instance.
|
FieldCartesianOrbit<T> |
FieldCartesianOrbit.interpolate(FieldAbsoluteDate<T> date,
Stream<FieldOrbit<T>> sample)
Get an interpolated instance.
|
abstract <T extends CalculusFieldElement<T>> |
OrbitType.mapArrayToOrbit(T[] array,
T[] arrayDot,
PositionAngle type,
FieldAbsoluteDate<T> date,
T mu,
Frame frame)
Convert state array to orbital parameters.
|
| Constructor and Description |
|---|
FieldCartesianOrbit(FieldPVCoordinates<T> pvaCoordinates,
Frame frame,
FieldAbsoluteDate<T> date,
T mu)
Constructor from Cartesian parameters.
|
FieldCircularOrbit(FieldPVCoordinates<T> PVCoordinates,
Frame frame,
FieldAbsoluteDate<T> date,
T mu)
Constructor from Cartesian parameters.
|
FieldCircularOrbit(T a,
T ex,
T ey,
T i,
T raan,
T alpha,
PositionAngle type,
Frame frame,
FieldAbsoluteDate<T> date,
T mu)
Creates a new instance.
|
FieldCircularOrbit(T a,
T ex,
T ey,
T i,
T raan,
T alpha,
T aDot,
T exDot,
T eyDot,
T iDot,
T raanDot,
T alphaDot,
PositionAngle type,
Frame frame,
FieldAbsoluteDate<T> date,
T mu)
Creates a new instance.
|
FieldEquinoctialOrbit(FieldPVCoordinates<T> pvCoordinates,
Frame frame,
FieldAbsoluteDate<T> date,
T mu)
Constructor from Cartesian parameters.
|
FieldEquinoctialOrbit(T a,
T ex,
T ey,
T hx,
T hy,
T l,
PositionAngle type,
Frame frame,
FieldAbsoluteDate<T> date,
T mu)
Creates a new instance.
|
FieldEquinoctialOrbit(T a,
T ex,
T ey,
T hx,
T hy,
T l,
T aDot,
T exDot,
T eyDot,
T hxDot,
T hyDot,
T lDot,
PositionAngle type,
Frame frame,
FieldAbsoluteDate<T> date,
T mu)
Creates a new instance.
|
FieldKeplerianOrbit(FieldPVCoordinates<T> FieldPVCoordinates,
Frame frame,
FieldAbsoluteDate<T> date,
T mu)
Constructor from Cartesian parameters.
|
FieldKeplerianOrbit(T a,
T e,
T i,
T pa,
T raan,
T anomaly,
PositionAngle type,
Frame frame,
FieldAbsoluteDate<T> date,
T mu)
Creates a new instance.
|
FieldKeplerianOrbit(T a,
T e,
T i,
T pa,
T raan,
T anomaly,
T aDot,
T eDot,
T iDot,
T paDot,
T raanDot,
T anomalyDot,
PositionAngle type,
Frame frame,
FieldAbsoluteDate<T> date,
T mu)
Creates a new instance.
|
FieldOrbit(Frame frame,
FieldAbsoluteDate<T> date,
T mu)
Default constructor.
|
| Modifier and Type | Method and Description |
|---|---|
FieldAbsoluteDate<T> |
FieldSpacecraftState.getDate()
Get the date.
|
FieldAbsoluteDate<T> |
FieldBoundedPropagator.getMaxDate()
Get the last date of the range.
|
FieldAbsoluteDate<T> |
FieldBoundedPropagator.getMinDate()
Get the first date of the range.
|
protected FieldAbsoluteDate<T> |
FieldAbstractPropagator.getStartDate()
Get the start date.
|
| Modifier and Type | Method and Description |
|---|---|
TimeStampedFieldPVCoordinates<T> |
FieldAbstractPropagator.getPVCoordinates(FieldAbsoluteDate<T> date,
Frame frame)
Get the
FieldPVCoordinates of the body in the selected frame. |
FieldSpacecraftState<T> |
FieldSpacecraftState.interpolate(FieldAbsoluteDate<T> date,
Stream<FieldSpacecraftState<T>> sample)
Get an interpolated instance.
|
FieldSpacecraftState<T> |
FieldPropagator.propagate(FieldAbsoluteDate<T> target)
Propagate towards a target date.
|
FieldSpacecraftState<T> |
FieldAbstractPropagator.propagate(FieldAbsoluteDate<T> target)
Propagate towards a target date.
|
FieldSpacecraftState<T> |
FieldPropagator.propagate(FieldAbsoluteDate<T> start,
FieldAbsoluteDate<T> target)
Propagate from a start date towards a target date.
|
FieldSpacecraftState<T> |
FieldPropagator.propagate(FieldAbsoluteDate<T> start,
FieldAbsoluteDate<T> target)
Propagate from a start date towards a target date.
|
protected void |
FieldAbstractPropagator.setStartDate(FieldAbsoluteDate<T> startDate)
Set a start date.
|
| Modifier and Type | Method and Description |
|---|---|
protected FieldSpacecraftState<T> |
FieldAbstractAnalyticalPropagator.acceptStep(org.orekit.propagation.analytical.FieldAbstractAnalyticalPropagator.FieldBasicStepInterpolator interpolator,
FieldAbsoluteDate<T> target)
Accept a step, triggering events and step handlers.
|
protected FieldSpacecraftState<T> |
FieldAbstractAnalyticalPropagator.basicPropagate(FieldAbsoluteDate<T> date)
Propagate an orbit without any fancy features.
|
protected T |
FieldKeplerianPropagator.getMass(FieldAbsoluteDate<T> date)
Get the mass.
|
protected abstract T |
FieldAbstractAnalyticalPropagator.getMass(FieldAbsoluteDate<T> date)
Get the mass.
|
protected T |
FieldEcksteinHechlerPropagator.getMass(FieldAbsoluteDate<T> date)
Get the mass.
|
protected T |
FieldBrouwerLyddanePropagator.getMass(FieldAbsoluteDate<T> date)
Get the mass.
|
FieldSpacecraftState<T> |
FieldAbstractAnalyticalPropagator.propagate(FieldAbsoluteDate<T> start,
FieldAbsoluteDate<T> target)
Propagate from a start date towards a target date.
|
FieldSpacecraftState<T> |
FieldAbstractAnalyticalPropagator.propagate(FieldAbsoluteDate<T> start,
FieldAbsoluteDate<T> target)
Propagate from a start date towards a target date.
|
protected FieldOrbit<T> |
FieldKeplerianPropagator.propagateOrbit(FieldAbsoluteDate<T> date,
T[] parameters)
Extrapolate an orbit up to a specific target date.
|
protected abstract FieldOrbit<T> |
FieldAbstractAnalyticalPropagator.propagateOrbit(FieldAbsoluteDate<T> date,
T[] parameters)
Extrapolate an orbit up to a specific target date.
|
FieldCartesianOrbit<T> |
FieldEcksteinHechlerPropagator.propagateOrbit(FieldAbsoluteDate<T> date,
T[] parameters)
Extrapolate an orbit up to a specific target date.
|
FieldKeplerianOrbit<T> |
FieldBrouwerLyddanePropagator.propagateOrbit(FieldAbsoluteDate<T> date,
T[] parameters)
Extrapolate an orbit up to a specific target date.
|
| Modifier and Type | Method and Description |
|---|---|
FieldAbsoluteDate<T> |
FieldTLE.getDate()
Get the TLE current date.
|
| Modifier and Type | Method and Description |
|---|---|
protected T |
FieldTLEPropagator.getMass(FieldAbsoluteDate<T> date)
Get the mass.
|
FieldPVCoordinates<T> |
FieldTLEPropagator.getPVCoordinates(FieldAbsoluteDate<T> date,
T[] parameters)
Get the extrapolated position and velocity from an initial TLE.
|
FieldOrbit<T> |
FieldTLEPropagator.propagateOrbit(FieldAbsoluteDate<T> date,
T[] parameters)
Extrapolate an orbit up to a specific target date.
|
| Constructor and Description |
|---|
FieldTLE(int satelliteNumber,
char classification,
int launchYear,
int launchNumber,
String launchPiece,
int ephemerisType,
int elementNumber,
FieldAbsoluteDate<T> epoch,
T meanMotion,
T meanMotionFirstDerivative,
T meanMotionSecondDerivative,
T e,
T i,
T pa,
T raan,
T meanAnomaly,
int revolutionNumberAtEpoch,
double bStar)
Simple constructor from already parsed elements.
|
FieldTLE(int satelliteNumber,
char classification,
int launchYear,
int launchNumber,
String launchPiece,
int ephemerisType,
int elementNumber,
FieldAbsoluteDate<T> epoch,
T meanMotion,
T meanMotionFirstDerivative,
T meanMotionSecondDerivative,
T e,
T i,
T pa,
T raan,
T meanAnomaly,
int revolutionNumberAtEpoch,
double bStar,
TimeScale utc)
Simple constructor from already parsed elements using the given time scale as
UTC.
|
| Modifier and Type | Method and Description |
|---|---|
FieldAbsoluteDate<T> |
FieldDateDetector.getDate()
Get the current event date according to the propagator.
|
FieldAbsoluteDate<T> |
FieldEventState.getEventDate()
Get the occurrence time of the event triggered in the current
step.
|
FieldAbsoluteDate<T> |
FieldEventState.EventOccurrence.getStopDate()
Get the new time for a stop action.
|
| Modifier and Type | Method and Description |
|---|---|
void |
FieldDateDetector.addEventDate(FieldAbsoluteDate<T> target)
Add an event date.
|
void |
FieldEventState.init(FieldSpacecraftState<T> s0,
FieldAbsoluteDate<T> t)
Initialize event handler at the start of a propagation.
|
void |
FieldAbstractDetector.init(FieldSpacecraftState<T> s0,
FieldAbsoluteDate<T> t)
Initialize event handler at the start of a propagation.
|
default void |
FieldEventDetector.init(FieldSpacecraftState<T> s0,
FieldAbsoluteDate<T> t)
Initialize event handler at the start of a propagation.
|
| Constructor and Description |
|---|
FieldDateDetector(FieldAbsoluteDate<T> target)
Build a new instance.
|
| Modifier and Type | Method and Description |
|---|---|
default void |
FieldEventHandler.init(FieldSpacecraftState<T> initialState,
FieldAbsoluteDate<T> target)
Deprecated.
as of 11.1, replaced by
FieldEventHandler.init(FieldSpacecraftState, FieldAbsoluteDate, FieldEventDetector) |
default void |
FieldEventHandler.init(FieldSpacecraftState<T> initialState,
FieldAbsoluteDate<T> target,
KK detector)
Initialize event handler at the start of a propagation.
|
| Modifier and Type | Method and Description |
|---|---|
FieldAbsoluteDate<T> |
FieldIntegratedEphemeris.getMaxDate()
Get the last date of the range.
|
FieldAbsoluteDate<T> |
FieldIntegratedEphemeris.getMinDate()
Get the first date of the range.
|
FieldAbsoluteDate<T> |
FieldStateMapper.getReferenceDate()
Get reference date.
|
FieldAbsoluteDate<T> |
FieldStateMapper.mapDoubleToDate(T t)
Map the raw double time offset to a date.
|
FieldAbsoluteDate<T> |
FieldStateMapper.mapDoubleToDate(T t,
FieldAbsoluteDate<T> date)
Map the raw double time offset to a date.
|
| Modifier and Type | Method and Description |
|---|---|
protected FieldSpacecraftState<T> |
FieldIntegratedEphemeris.basicPropagate(FieldAbsoluteDate<T> date)
Propagate an orbit without any fancy features.
|
protected void |
FieldAbstractIntegratedPropagator.beforeIntegration(FieldSpacecraftState<T> initialState,
FieldAbsoluteDate<T> tEnd)
Method called just before integration.
|
protected abstract FieldStateMapper<T> |
FieldAbstractIntegratedPropagator.createMapper(FieldAbsoluteDate<T> referenceDate,
T mu,
OrbitType orbitType,
PositionAngle positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame)
Create a mapper between raw double components and spacecraft state.
|
protected T |
FieldIntegratedEphemeris.getMass(FieldAbsoluteDate<T> date)
Get the mass.
|
TimeStampedFieldPVCoordinates<T> |
FieldIntegratedEphemeris.getPVCoordinates(FieldAbsoluteDate<T> date,
Frame frame)
Get the
FieldPVCoordinates of the body in the selected frame. |
void |
FieldAdditionalEquationsAdapter.init(FieldSpacecraftState<T> initialState,
FieldAbsoluteDate<T> target)
Deprecated.
Initialize the generator at the start of propagation.
|
void |
FieldAbstractIntegratedPropagator.MainStateEquations.init(FieldSpacecraftState<T> initialState,
FieldAbsoluteDate<T> target)
Initialize the equations at the start of propagation.
|
default void |
FieldAdditionalDerivativesProvider.init(FieldSpacecraftState<T> initialState,
FieldAbsoluteDate<T> target)
Initialize the generator at the start of propagation.
|
default void |
FieldAdditionalEquations.init(FieldSpacecraftState<T> initialState,
FieldAbsoluteDate<T> target)
Deprecated.
Initialize the equations at the start of propagation.
|
abstract FieldSpacecraftState<T> |
FieldStateMapper.mapArrayToState(FieldAbsoluteDate<T> date,
T[] y,
T[] yDot,
PropagationType type)
Map the raw double components to a spacecraft state.
|
T |
FieldStateMapper.mapDateToDouble(FieldAbsoluteDate<T> date)
Map a date to a raw double time offset.
|
FieldAbsoluteDate<T> |
FieldStateMapper.mapDoubleToDate(T t,
FieldAbsoluteDate<T> date)
Map the raw double time offset to a date.
|
FieldSpacecraftState<T> |
FieldAbstractIntegratedPropagator.propagate(FieldAbsoluteDate<T> target)
Propagate towards a target date.
|
FieldSpacecraftState<T> |
FieldAbstractIntegratedPropagator.propagate(FieldAbsoluteDate<T> tStart,
FieldAbsoluteDate<T> tEnd)
Propagate from a start date towards a target date.
|
FieldSpacecraftState<T> |
FieldAbstractIntegratedPropagator.propagate(FieldAbsoluteDate<T> tStart,
FieldAbsoluteDate<T> tEnd)
Propagate from a start date towards a target date.
|
protected FieldOrbit<T> |
FieldIntegratedEphemeris.propagateOrbit(FieldAbsoluteDate<T> date,
T[] parameters)
Extrapolate an orbit up to a specific target date.
|
| Modifier and Type | Method and Description |
|---|---|
protected FieldStateMapper<T> |
FieldNumericalPropagator.createMapper(FieldAbsoluteDate<T> referenceDate,
T mu,
OrbitType orbitType,
PositionAngle positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame)
Create a mapper between raw double components and spacecraft state.
|
TimeStampedFieldPVCoordinates<T> |
FieldNumericalPropagator.getPVCoordinates(FieldAbsoluteDate<T> date,
Frame frame)
Get the
FieldPVCoordinates of the body in the selected frame. |
| Modifier and Type | Method and Description |
|---|---|
FieldSpacecraftState<T> |
FieldOrekitStepInterpolator.getInterpolatedState(FieldAbsoluteDate<T> date)
Get the state at interpolated date.
|
void |
FieldStepHandlerMultiplexer.init(FieldSpacecraftState<T> s0,
FieldAbsoluteDate<T> t)
Initialize step handler at the start of a propagation.
|
default void |
FieldOrekitStepHandler.init(FieldSpacecraftState<T> s0,
FieldAbsoluteDate<T> t)
Initialize step handler at the start of a propagation.
|
void |
FieldOrekitStepNormalizer.init(FieldSpacecraftState<T> s0,
FieldAbsoluteDate<T> t)
Initialize step handler at the start of a propagation.
|
default void |
FieldOrekitFixedStepHandler.init(FieldSpacecraftState<T> s0,
FieldAbsoluteDate<T> t,
T step)
Initialize step handler at the start of a propagation.
|
| Modifier and Type | Method and Description |
|---|---|
protected void |
FieldDSSTPropagator.beforeIntegration(FieldSpacecraftState<T> initialState,
FieldAbsoluteDate<T> tEnd)
Method called just before integration.
|
protected FieldStateMapper<T> |
FieldDSSTPropagator.createMapper(FieldAbsoluteDate<T> referenceDate,
T mu,
OrbitType ignoredOrbitType,
PositionAngle ignoredPositionAngleType,
AttitudeProvider attitudeProvider,
Frame frame)
Create a mapper between raw double components and spacecraft state.
|
| Modifier and Type | Method and Description |
|---|---|
Map<String,T[]> |
AbstractGaussianContribution.FieldGaussianShortPeriodicCoefficients.getCoefficients(FieldAbsoluteDate<T> date,
Set<String> selected)
Computes the coefficients involved in the contributions.
|
Map<String,T[]> |
FieldShortPeriodTerms.getCoefficients(FieldAbsoluteDate<T> date,
Set<String> selected)
Computes the coefficients involved in the contributions.
|
<T extends CalculusFieldElement<T>> |
AbstractGaussianContribution.init(FieldSpacecraftState<T> initialState,
FieldAbsoluteDate<T> target)
Initialize the force model at the start of propagation.
|
default <T extends CalculusFieldElement<T>> |
DSSTForceModel.init(FieldSpacecraftState<T> initialState,
FieldAbsoluteDate<T> target)
Initialize the force model at the start of propagation.
|
| Modifier and Type | Method and Description |
|---|---|
FieldAbsoluteDate<T> |
FieldAuxiliaryElements.getDate()
Get the date of the orbit.
|
| Modifier and Type | Method and Description |
|---|---|
void |
FieldShortPeriodicsInterpolatedCoefficient.addGridPoint(FieldAbsoluteDate<T> date,
T[] value)
Add a point to the interpolation grid.
|
T[] |
FieldShortPeriodicsInterpolatedCoefficient.value(FieldAbsoluteDate<T> date)
Compute the value of the coefficient.
|
| Modifier and Type | Method and Description |
|---|---|
static <T extends CalculusFieldElement<T>> |
FieldAbsoluteDate.createBesselianEpoch(T besselianEpoch)
Build an instance corresponding to a Besselian Epoch (BE).
|
static <T extends CalculusFieldElement<T>> |
FieldAbsoluteDate.createBesselianEpoch(T besselianEpoch,
TimeScales timeScales)
Build an instance corresponding to a Besselian Epoch (BE).
|
static <T extends CalculusFieldElement<T>> |
FieldAbsoluteDate.createGPSDate(int weekNumber,
T milliInWeek)
Build an instance corresponding to a GPS date.
|
static <T extends CalculusFieldElement<T>> |
FieldAbsoluteDate.createGPSDate(int weekNumber,
T milliInWeek,
TimeScale gps)
Build an instance corresponding to a GPS date.
|
static <T extends CalculusFieldElement<T>> |
FieldAbsoluteDate.createJDDate(int jd,
T secondsSinceNoon,
TimeScale timeScale)
Build an instance corresponding to a Julian Day date.
|
static <T extends CalculusFieldElement<T>> |
FieldAbsoluteDate.createJulianEpoch(T julianEpoch)
Build an instance corresponding to a Julian Epoch (JE).
|
static <T extends CalculusFieldElement<T>> |
FieldAbsoluteDate.createJulianEpoch(T julianEpoch,
TimeScales timeScales)
Build an instance corresponding to a Julian Epoch (JE).
|
static <T extends CalculusFieldElement<T>> |
FieldAbsoluteDate.createMJDDate(int mjd,
T secondsInDay,
TimeScale timeScale)
Build an instance corresponding to a Modified Julian Day date.
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static <T extends CalculusFieldElement<T>> |
FieldAbsoluteDate.getArbitraryEpoch(Field<T> field)
Get an arbitrary date.
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static <T extends CalculusFieldElement<T>> |
FieldAbsoluteDate.getCCSDSEpoch(Field<T> field)
Reference epoch for CCSDS Time Code Format (CCSDS 301.0-B-4):
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FieldAbsoluteDate<T> |
FieldAbsoluteDate.getDate()
Get the date.
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FieldAbsoluteDate<T> |
FieldTimeStamped.getDate()
Get the date.
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static <T extends CalculusFieldElement<T>> |
FieldAbsoluteDate.getFiftiesEpoch(Field<T> field)
Reference epoch for 1950 dates: 1950-01-01T00:00:00 Terrestrial Time.
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static <T extends CalculusFieldElement<T>> |
FieldAbsoluteDate.getFutureInfinity(Field<T> field)
Dummy date at infinity in the future direction.
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static <T extends CalculusFieldElement<T>> |
FieldAbsoluteDate.getGalileoEpoch(Field<T> field)
Reference epoch for Galileo System Time: 1999-08-22T00:00:00 UTC.
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static <T extends CalculusFieldElement<T>> |
FieldAbsoluteDate.getGPSEpoch(Field<T> field)
Reference epoch for GPS weeks: 1980-01-06T00:00:00 GPS time.
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static <T extends CalculusFieldElement<T>> |
FieldAbsoluteDate.getJ2000Epoch(Field<T> field)
J2000.0 Reference epoch: 2000-01-01T12:00:00 Terrestrial Time (not UTC).
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static <T extends CalculusFieldElement<T>> |
FieldAbsoluteDate.getJavaEpoch(Field<T> field)
Java Reference epoch: 1970-01-01T00:00:00 Universal Time Coordinate.
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static <T extends CalculusFieldElement<T>> |
FieldAbsoluteDate.getJulianEpoch(Field<T> field)
Reference epoch for julian dates: -4712-01-01T12:00:00 Terrestrial Time.
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static <T extends CalculusFieldElement<T>> |
FieldAbsoluteDate.getModifiedJulianEpoch(Field<T> field)
Reference epoch for modified julian dates: 1858-11-17T00:00:00 Terrestrial Time.
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static <T extends CalculusFieldElement<T>> |
FieldAbsoluteDate.getPastInfinity(Field<T> field)
Dummy date at infinity in the past direction.
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FieldAbsoluteDate<T> |
FieldAbsoluteDate.parseCCSDSCalendarSegmentedTimeCode(byte preambleField,
byte[] timeField)
Build an instance from a CCSDS Calendar Segmented Time Code (CCS).
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FieldAbsoluteDate<T> |
FieldAbsoluteDate.parseCCSDSCalendarSegmentedTimeCode(byte preambleField,
byte[] timeField,
TimeScale utc)
Build an instance from a CCSDS Calendar Segmented Time Code (CCS).
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static <T extends CalculusFieldElement<T>> |
FieldAbsoluteDate.parseCCSDSDaySegmentedTimeCode(Field<T> field,
byte preambleField,
byte[] timeField,
DateComponents agencyDefinedEpoch)
Build an instance from a CCSDS Day Segmented Time Code (CDS).
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static <T extends CalculusFieldElement<T>> |
FieldAbsoluteDate.parseCCSDSDaySegmentedTimeCode(Field<T> field,
byte preambleField,
byte[] timeField,
DateComponents agencyDefinedEpoch,
TimeScale utc)
Build an instance from a CCSDS Day Segmented Time Code (CDS).
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static <T extends CalculusFieldElement<T>> |
FieldAbsoluteDate.parseCCSDSUnsegmentedTimeCode(Field<T> field,
byte preambleField1,
byte preambleField2,
byte[] timeField,
FieldAbsoluteDate<T> agencyDefinedEpoch)
Build an instance from a CCSDS Unsegmented Time Code (CUC).
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static <T extends CalculusFieldElement<T>> |
FieldAbsoluteDate.parseCCSDSUnsegmentedTimeCode(Field<T> field,
byte preambleField1,
byte preambleField2,
byte[] timeField,
FieldAbsoluteDate<T> agencyDefinedEpoch,
FieldAbsoluteDate<T> ccsdsEpoch)
Build an instance from a CCSDS Unsegmented Time Code (CUC).
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FieldAbsoluteDate<T> |
FieldAbsoluteDate.shiftedBy(double dt)
Get a time-shifted date.
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FieldAbsoluteDate<T> |
FieldAbsoluteDate.shiftedBy(T dt)
Get a time-shifted date.
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| Modifier and Type | Method and Description |
|---|---|
int |
FieldAbsoluteDate.compareTo(FieldAbsoluteDate<T> date)
Compare the instance with another date.
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T |
FieldAbsoluteDate.durationFrom(FieldAbsoluteDate<T> instant)
Compute the physically elapsed duration between two instants.
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<T extends CalculusFieldElement<T>> |
GLONASSScale.getLeap(FieldAbsoluteDate<T> date)
Get the value of the previous leap.
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default <T extends CalculusFieldElement<T>> |
TimeScale.getLeap(FieldAbsoluteDate<T> date)
Get the value of the previous leap.
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<T extends CalculusFieldElement<T>> |
UTCScale.getLeap(FieldAbsoluteDate<T> date)
Get the value of the previous leap.
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<T extends CalculusFieldElement<T>> |
UTCTAIOffset.getOffset(FieldAbsoluteDate<T> date)
Get the TAI - UTC offset in seconds.
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<T extends CalculusFieldElement<T>> |
GLONASSScale.insideLeap(FieldAbsoluteDate<T> date)
Check if date is within a leap second introduction in this time scale.
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default <T extends CalculusFieldElement<T>> |
TimeScale.insideLeap(FieldAbsoluteDate<T> date)
Check if date is within a leap second introduction in this time scale.
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<T extends CalculusFieldElement<T>> |
UTCScale.insideLeap(FieldAbsoluteDate<T> date)
Check if date is within a leap second introduction in this time scale.
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default T |
FieldTimeInterpolable.interpolate(FieldAbsoluteDate<KK> date,
Collection<T> sample)
Get an interpolated instance.
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T |
FieldTimeInterpolable.interpolate(FieldAbsoluteDate<KK> date,
Stream<T> sample)
Get an interpolated instance.
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<T extends CalculusFieldElement<T>> |
GLONASSScale.minuteDuration(FieldAbsoluteDate<T> date)
Check length of the current minute in this time scale.
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default <T extends CalculusFieldElement<T>> |
TimeScale.minuteDuration(FieldAbsoluteDate<T> date)
Check length of the current minute in this time scale.
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<T extends CalculusFieldElement<T>> |
UTCScale.minuteDuration(FieldAbsoluteDate<T> date)
Check length of the current minute in this time scale.
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T |
FieldAbsoluteDate.offsetFrom(FieldAbsoluteDate<T> instant,
TimeScale timeScale)
Compute the apparent clock offset between two instant in the
perspective of a specific
time scale. |
<T extends CalculusFieldElement<T>> |
GLONASSScale.offsetFromTAI(FieldAbsoluteDate<T> date)
Get the offset to convert locations from
TAIScale to instance. |
<T extends CalculusFieldElement<T>> |
GPSScale.offsetFromTAI(FieldAbsoluteDate<T> date)
Get the offset to convert locations from
TAIScale to instance. |
<T extends CalculusFieldElement<T>> |
TimeScale.offsetFromTAI(FieldAbsoluteDate<T> date)
Get the offset to convert locations from
TAIScale to instance. |
<T extends CalculusFieldElement<T>> |
TDBScale.offsetFromTAI(FieldAbsoluteDate<T> date)
Get the offset to convert locations from
TAIScale to instance. |
<T extends CalculusFieldElement<T>> |
GalileoScale.offsetFromTAI(FieldAbsoluteDate<T> date)
Get the offset to convert locations from
TAIScale to instance. |
<T extends CalculusFieldElement<T>> |
GMSTScale.offsetFromTAI(FieldAbsoluteDate<T> date)
Get the offset to convert locations from
TAIScale to instance. |
<T extends CalculusFieldElement<T>> |
QZSSScale.offsetFromTAI(FieldAbsoluteDate<T> date)
Get the offset to convert locations from
TAIScale to instance. |
<T extends CalculusFieldElement<T>> |
IRNSSScale.offsetFromTAI(FieldAbsoluteDate<T> date)
Get the offset to convert locations from
TAIScale to instance. |
<T extends CalculusFieldElement<T>> |
UTCScale.offsetFromTAI(FieldAbsoluteDate<T> date)
Get the offset to convert locations from
TAIScale to instance. |
<T extends CalculusFieldElement<T>> |
SatelliteClockScale.offsetFromTAI(FieldAbsoluteDate<T> date)
Get the offset to convert locations from
TAIScale to instance. |
<T extends CalculusFieldElement<T>> |
UT1Scale.offsetFromTAI(FieldAbsoluteDate<T> date)
Get the offset to convert locations from
TAIScale to instance. |
<T extends CalculusFieldElement<T>> |
TTScale.offsetFromTAI(FieldAbsoluteDate<T> date)
Get the offset to convert locations from
TAIScale to instance. |
<T extends CalculusFieldElement<T>> |
TCGScale.offsetFromTAI(FieldAbsoluteDate<T> date)
Get the offset to convert locations from
TAIScale to instance. |
<T extends CalculusFieldElement<T>> |
TCBScale.offsetFromTAI(FieldAbsoluteDate<T> date)
Get the offset to convert locations from
TAIScale to instance. |
<T extends CalculusFieldElement<T>> |
BDTScale.offsetFromTAI(FieldAbsoluteDate<T> date)
Get the offset to convert locations from
TAIScale to instance. |
<T extends CalculusFieldElement<T>> |
TAIScale.offsetFromTAI(FieldAbsoluteDate<T> date)
Get the offset to convert locations from
TAIScale to instance. |
static <T extends CalculusFieldElement<T>> |
FieldAbsoluteDate.parseCCSDSUnsegmentedTimeCode(Field<T> field,
byte preambleField1,
byte preambleField2,
byte[] timeField,
FieldAbsoluteDate<T> agencyDefinedEpoch)
Build an instance from a CCSDS Unsegmented Time Code (CUC).
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static <T extends CalculusFieldElement<T>> |
FieldAbsoluteDate.parseCCSDSUnsegmentedTimeCode(Field<T> field,
byte preambleField1,
byte preambleField2,
byte[] timeField,
FieldAbsoluteDate<T> agencyDefinedEpoch,
FieldAbsoluteDate<T> ccsdsEpoch)
Build an instance from a CCSDS Unsegmented Time Code (CUC).
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static <T extends CalculusFieldElement<T>> |
FieldAbsoluteDate.parseCCSDSUnsegmentedTimeCode(Field<T> field,
byte preambleField1,
byte preambleField2,
byte[] timeField,
FieldAbsoluteDate<T> agencyDefinedEpoch,
FieldAbsoluteDate<T> ccsdsEpoch)
Build an instance from a CCSDS Unsegmented Time Code (CUC).
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<T extends CalculusFieldElement<T>> |
TimeScalarFunction.value(FieldAbsoluteDate<T> date)
Compute a function of time.
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<T extends CalculusFieldElement<T>> |
TimeVectorFunction.value(FieldAbsoluteDate<T> date)
Compute a function of time.
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| Constructor and Description |
|---|
FieldAbsoluteDate(FieldAbsoluteDate<T> since,
double elapsedDuration)
Build an instance from an elapsed duration since to another instant.
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FieldAbsoluteDate(FieldAbsoluteDate<T> reference,
double apparentOffset,
TimeScale timeScale)
Build an instance from an apparent clock offset with respect to another
instant in the perspective of a specific
time scale. |
FieldAbsoluteDate(FieldAbsoluteDate<T> since,
T elapsedDuration)
Build an instance from an elapsed duration since to another instant.
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| Modifier and Type | Method and Description |
|---|---|
FieldAbsoluteDate<D> |
FieldTimeSpanMap.Transition.getAbsoluteDate()
Get the transition field absolute date.
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FieldAbsoluteDate<T> |
TimeStampedFieldPVCoordinates.getDate()
Get the date.
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FieldAbsoluteDate<T> |
TimeStampedFieldAngularCoordinates.getDate()
Get the date.
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| Modifier and Type | Method and Description |
|---|---|
void |
FieldTimeSpanMap.addValidAfter(T entry,
FieldAbsoluteDate<D> earliestValidityDate)
Add an entry valid after a limit date.
|
void |
FieldTimeSpanMap.addValidBefore(T entry,
FieldAbsoluteDate<D> latestValidityDate)
Add an entry valid before a limit date.
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<T extends CalculusFieldElement<T>> |
IERSConventions.evaluateTC(FieldAbsoluteDate<T> date)
Evaluate the date offset between the current date and the
reference date. |
<T extends CalculusFieldElement<T>> |
IERSConventions.evaluateTC(FieldAbsoluteDate<T> date,
TimeScales timeScales)
Evaluate the date offset between the current date and the
reference date. |
T |
FieldTimeSpanMap.get(FieldAbsoluteDate<D> date)
Get the entry valid at a specified date.
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TimeStampedFieldPVCoordinates<T> |
FieldPVCoordinatesProvider.getPVCoordinates(FieldAbsoluteDate<T> date,
Frame frame)
Get the
FieldPVCoordinates of the body in the selected frame. |
TimeStampedFieldPVCoordinates<T> |
FieldAbsolutePVCoordinates.getPVCoordinates(FieldAbsoluteDate<T> otherDate,
Frame outputFrame) |
<T extends CalculusFieldElement<T>> |
ExtendedPVCoordinatesProvider.getPVCoordinates(FieldAbsoluteDate<T> date,
Frame frame)
Get the
FieldPVCoordinates of the body in the selected frame. |
static <T extends CalculusFieldElement<T>> |
TimeStampedFieldAngularCoordinates.interpolate(FieldAbsoluteDate<T> date,
AngularDerivativesFilter filter,
Collection<TimeStampedFieldAngularCoordinates<T>> sample)
Interpolate angular coordinates.
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static <T extends CalculusFieldElement<T>> |
TimeStampedFieldPVCoordinates.interpolate(FieldAbsoluteDate<T> date,
CartesianDerivativesFilter filter,
Collection<TimeStampedFieldPVCoordinates<T>> sample)
Interpolate position-velocity.
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static <T extends CalculusFieldElement<T>> |
TimeStampedFieldPVCoordinates.interpolate(FieldAbsoluteDate<T> date,
CartesianDerivativesFilter filter,
Stream<TimeStampedFieldPVCoordinates<T>> sample)
Interpolate position-velocity.
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FieldAbsolutePVCoordinates<T> |
FieldAbsolutePVCoordinates.interpolate(FieldAbsoluteDate<T> date,
Stream<FieldAbsolutePVCoordinates<T>> sample) |
static <T extends CalculusFieldElement<T>> |
FieldAbsolutePVCoordinates.interpolate(Frame frame,
FieldAbsoluteDate<T> date,
CartesianDerivativesFilter filter,
Stream<FieldAbsolutePVCoordinates<T>> sample)
Interpolate position-velocity.
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