Package | Description |
---|---|
org.orekit.attitudes |
This package provides classes to represent simple attitudes.
|
org.orekit.forces.maneuvers.propulsion |
This package provides propulsion models intended to be used with class
Maneuver . |
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.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.utils |
This package provides useful objects.
|
Modifier and Type | Method and Description |
---|---|
<T extends RealFieldElement<T>> |
YawCompensation.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends RealFieldElement<T>> |
LofOffset.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends RealFieldElement<T>> |
AttitudeProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends RealFieldElement<T>> |
InertialProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends RealFieldElement<T>> |
FixedRate.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends RealFieldElement<T>> |
AttitudesSequence.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends RealFieldElement<T>> |
GroundPointing.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends RealFieldElement<T>> |
SpinStabilized.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends RealFieldElement<T>> |
LofOffsetPointing.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends RealFieldElement<T>> |
TabulatedLofOffset.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends RealFieldElement<T>> |
YawSteering.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends RealFieldElement<T>> |
TabulatedProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends RealFieldElement<T>> |
CelestialBodyPointed.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
<T extends RealFieldElement<T>> |
YawCompensation.getBaseState(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the base system state at given date, without compensation.
|
<T extends RealFieldElement<T>> |
YawSteering.getBaseState(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the base system state at given date, without compensation.
|
<T extends RealFieldElement<T>> |
YawCompensation.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
<T extends RealFieldElement<T>> |
NadirPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
abstract <T extends RealFieldElement<T>> |
GroundPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
<T extends RealFieldElement<T>> |
LofOffsetPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
<T extends RealFieldElement<T>> |
YawSteering.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
<T extends RealFieldElement<T>> |
TargetPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
<T extends RealFieldElement<T>> |
BodyCenterPointing.getTargetPV(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
<T extends RealFieldElement<T>> |
YawCompensation.getYawAngle(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the yaw compensation angle at date.
|
Modifier and Type | Method and Description |
---|---|
<T extends RealFieldElement<T>> |
ThrustDirectionAndAttitudeProvider.getAttitude(FieldPVCoordinatesProvider<T> pvProv,
FieldAbsoluteDate<T> date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Modifier and Type | Class and Description |
---|---|
class |
FieldCartesianOrbit<T extends RealFieldElement<T>>
This class holds Cartesian orbital parameters.
|
class |
FieldCircularOrbit<T extends RealFieldElement<T>>
This class handles circular orbital parameters.
|
class |
FieldEquinoctialOrbit<T extends RealFieldElement<T>>
This class handles equinoctial orbital parameters, which can support both
circular and equatorial orbits.
|
class |
FieldKeplerianOrbit<T extends RealFieldElement<T>>
This class handles traditional Keplerian orbital parameters.
|
class |
FieldOrbit<T extends RealFieldElement<T>>
This class handles orbital parameters.
|
Modifier and Type | Interface and Description |
---|---|
interface |
FieldBoundedPropagator<T extends RealFieldElement<T>>
This interface is intended for ephemerides valid only during a time range.
|
interface |
FieldPropagator<T extends RealFieldElement<T>>
This interface provides a way to propagate an orbit at any time.
|
Modifier and Type | Class and Description |
---|---|
class |
FieldAbstractPropagator<T extends RealFieldElement<T>>
Common handling of
Propagator methods for analytical propagators. |
Modifier and Type | Class and Description |
---|---|
class |
FieldAbstractAnalyticalPropagator<T extends RealFieldElement<T>>
Common handling of
FieldPropagator methods for analytical propagators. |
class |
FieldEcksteinHechlerPropagator<T extends RealFieldElement<T>>
This class propagates a
FieldSpacecraftState
using the analytical Eckstein-Hechler model. |
class |
FieldKeplerianPropagator<T extends RealFieldElement<T>>
Simple Keplerian orbit propagator.
|
Modifier and Type | Method and Description |
---|---|
FieldPVCoordinatesProvider<T> |
FieldAbstractAnalyticalPropagator.getPvProvider()
Get PV coordinates provider.
|
Modifier and Type | Class and Description |
---|---|
class |
FieldAbstractIntegratedPropagator<T extends RealFieldElement<T>>
Common handling of
FieldPropagator
methods for both numerical and semi-analytical propagators. |
class |
FieldIntegratedEphemeris<T extends RealFieldElement<T>>
This class stores sequentially generated orbital parameters for
later retrieval.
|
Modifier and Type | Class and Description |
---|---|
class |
FieldNumericalPropagator<T extends RealFieldElement<T>>
This class propagates
orbits using
numerical integration. |
Modifier and Type | Class and Description |
---|---|
class |
FieldDSSTPropagator<T extends RealFieldElement<T>>
This class propagates
orbits using the DSST theory. |
Modifier and Type | Class and Description |
---|---|
class |
FieldAbsolutePVCoordinates<T extends RealFieldElement<T>>
Field implementation of AbsolutePVCoordinates.
|
Modifier and Type | Method and Description |
---|---|
default <T extends RealFieldElement<T>> |
ExtendedPVCoordinatesProvider.toFieldPVCoordinatesProvider(Field<T> field)
Convert to a
FieldPVCoordinatesProvider with a specific type. |
FieldPVCoordinatesProvider<T> |
FieldAbsolutePVCoordinates.toTaylorProvider()
Create a local provider using simply Taylor expansion through
FieldAbsolutePVCoordinates.shiftedBy(double) . |
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