Package | Description |
---|---|
org.orekit.attitudes |
This package provides classes to represent simple attitudes.
|
org.orekit.estimation.measurements.modifiers | |
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.maneuvers |
This package provides models of simple maneuvers.
|
org.orekit.gnss.attitude |
This package provides classes related to navigation satellites attitude modeling.
|
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.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.utils |
This package provides useful objects.
|
Modifier and Type | Interface | Description |
---|---|---|
interface |
AttitudeProviderModifier |
This interface represents an attitude provider that modifies/wraps another underlying provider.
|
Modifier and Type | Class | Description |
---|---|---|
class |
AttitudesSequence |
This classes manages a sequence of different attitude providers that are activated
in turn according to switching events.
|
class |
BodyCenterPointing |
This class handles body center pointing attitude provider.
|
class |
CelestialBodyPointed |
This class handles a celestial body pointed attitude provider.
|
class |
FixedRate |
This class handles a simple attitude provider at constant rate around a fixed axis.
|
class |
GroundPointing |
Base class for ground pointing attitude providers.
|
class |
InertialProvider |
This class handles an inertial attitude provider.
|
class |
LofOffset |
Attitude law defined by fixed Roll, Pitch and Yaw angles (in any order)
with respect to a local orbital frame.
|
class |
LofOffsetPointing |
This class provides a default attitude provider.
|
class |
NadirPointing |
This class handles nadir pointing attitude provider.
|
class |
SpinStabilized |
This class handles a spin stabilized attitude provider.
|
class |
TabulatedLofOffset |
This class handles an attitude provider interpolating from a predefined table
containing offsets from a Local Orbital Frame.
|
class |
TabulatedProvider |
This class handles an attitude provider interpolating from a predefined table.
|
class |
TargetPointing |
This class handles target pointing attitude provider.
|
class |
YawCompensation |
This class handles yaw compensation attitude provider.
|
class |
YawSteering |
This class handles yaw steering law.
|
Modifier and Type | Method | Description |
---|---|---|
AttitudeProvider |
AttitudeProviderModifier.getUnderlyingAttitudeProvider() |
Get the underlying attitude provider.
|
AttitudeProvider |
SpinStabilized.getUnderlyingAttitudeProvider() |
Get the underlying attitude provider.
|
AttitudeProvider |
YawCompensation.getUnderlyingAttitudeProvider() |
Get the underlying (ground pointing) attitude provider.
|
AttitudeProvider |
YawSteering.getUnderlyingAttitudeProvider() |
Get the underlying (ground pointing) attitude provider.
|
Modifier and Type | Method | Description |
---|---|---|
<T extends EventDetector> |
AttitudesSequence.addSwitchingCondition(AttitudeProvider past,
AttitudeProvider future,
T switchEvent,
boolean switchOnIncrease,
boolean switchOnDecrease,
double transitionTime,
AngularDerivativesFilter transitionFilter,
AttitudesSequence.SwitchHandler handler) |
Add a switching condition between two attitude providers.
|
void |
AttitudesSequence.resetActiveProvider(AttitudeProvider provider) |
Reset the active provider.
|
void |
AttitudesSequence.SwitchHandler.switchOccurred(AttitudeProvider preceding,
AttitudeProvider following,
SpacecraftState state) |
Method called when attitude is switched from one law to another law.
|
Constructor | Description |
---|---|
LofOffsetPointing(Frame inertialFrame,
BodyShape shape,
AttitudeProvider attLaw,
org.hipparchus.geometry.euclidean.threed.Vector3D satPointingVector) |
Creates new instance.
|
SpinStabilized(AttitudeProvider nonRotatingLaw,
AbsoluteDate start,
org.hipparchus.geometry.euclidean.threed.Vector3D axis,
double rate) |
Creates a new instance.
|
Constructor | Description |
---|---|
TroposphericDSConverter(SpacecraftState state,
int freeStateParameters,
AttitudeProvider provider) |
Simple constructor.
|
Constructor | Description |
---|---|
AbstractParametricAcceleration(org.hipparchus.geometry.euclidean.threed.Vector3D direction,
boolean isInertial,
AttitudeProvider attitudeOverride) |
Simple constructor.
|
HarmonicParametricAcceleration(org.hipparchus.geometry.euclidean.threed.Vector3D direction,
AttitudeProvider attitudeOverride,
String prefix,
AbsoluteDate referenceDate,
double fundamentalPeriod,
int harmonicMultiplier) |
Simple constructor.
|
PolynomialParametricAcceleration(org.hipparchus.geometry.euclidean.threed.Vector3D direction,
AttitudeProvider attitudeOverride,
String prefix,
AbsoluteDate referenceDate,
int degree) |
Simple constructor.
|
Modifier and Type | Method | Description |
---|---|---|
AttitudeProvider |
ConstantThrustManeuver.getAttitudeOverride() |
Get the attitude override used for the maneuver.
|
AttitudeProvider |
ImpulseManeuver.getAttitudeOverride() |
Get the Attitude Provider to use during maneuver.
|
Constructor | Description |
---|---|
ConstantThrustManeuver(AbsoluteDate date,
double duration,
double thrust,
double isp,
AttitudeProvider attitudeOverride,
org.hipparchus.geometry.euclidean.threed.Vector3D direction) |
Simple constructor for a constant direction and constant thrust.
|
ConstantThrustManeuver(AbsoluteDate date,
double duration,
double thrust,
double isp,
AttitudeProvider attitudeOverride,
org.hipparchus.geometry.euclidean.threed.Vector3D direction,
String name) |
Simple constructor for a constant direction and constant thrust.
|
ImpulseManeuver(T trigger,
AttitudeProvider attitudeOverride,
org.hipparchus.geometry.euclidean.threed.Vector3D deltaVSat,
double isp) |
Build a new instance.
|
Modifier and Type | Interface | Description |
---|---|---|
interface |
GNSSAttitudeProvider |
Attitude providers for navigation satellites.
|
Modifier and Type | Class | Description |
---|---|---|
class |
AbstractGNSSAttitudeProvider |
Base class for attitude providers for navigation satellites.
|
class |
BeidouGeo |
Attitude providers for Beidou geostationary orbit navigation satellites.
|
class |
BeidouIGSO |
Attitude providers for Beidou inclined geosynchronous orbit navigation satellites.
|
class |
BeidouMeo |
Attitude providers for Beidou Medium Earth Orbit navigation satellites.
|
class |
Galileo |
Attitude providers for Galileo navigation satellites.
|
class |
GenericGNSS |
Attitude providers for navigation satellites for which no specialized model is known.
|
class |
Glonass |
Attitude providers for Glonass navigation satellites.
|
class |
GPSBlockIIA |
Attitude providers for GPS block IIR navigation satellites.
|
class |
GPSBlockIIF |
Attitude providers for GPS block IIF navigation satellites.
|
class |
GPSBlockIIR |
Attitude providers for GPS block IIF navigation satellites.
|
Modifier and Type | Field | Description |
---|---|---|
static AttitudeProvider |
FieldPropagator.DEFAULT_LAW |
Default attitude provider.
|
static AttitudeProvider |
Propagator.DEFAULT_LAW |
Default attitude provider.
|
Modifier and Type | Method | Description |
---|---|---|
AttitudeProvider |
AbstractPropagator.getAttitudeProvider() |
Get attitude provider.
|
AttitudeProvider |
FieldAbstractPropagator.getAttitudeProvider() |
Get attitude provider.
|
AttitudeProvider |
FieldPropagator.getAttitudeProvider() |
Get attitude provider.
|
AttitudeProvider |
Propagator.getAttitudeProvider() |
Get attitude provider.
|
Modifier and Type | Method | Description |
---|---|---|
void |
AbstractPropagator.setAttitudeProvider(AttitudeProvider attitudeProvider) |
Set attitude provider.
|
void |
FieldAbstractPropagator.setAttitudeProvider(AttitudeProvider attitudeProvider) |
Set attitude provider.
|
void |
FieldPropagator.setAttitudeProvider(AttitudeProvider attitudeProvider) |
Set attitude provider.
|
void |
Propagator.setAttitudeProvider(AttitudeProvider attitudeProvider) |
Set attitude provider.
|
Constructor | Description |
---|---|
AbstractAnalyticalPropagator(AttitudeProvider attitudeProvider) |
Build a new instance.
|
EcksteinHechlerPropagator(Orbit initialOrbit,
AttitudeProvider attitudeProv,
double referenceRadius,
double mu,
double c20,
double c30,
double c40,
double c50,
double c60) |
Build a propagator from orbit, attitude provider and potential.
|
EcksteinHechlerPropagator(Orbit initialOrbit,
AttitudeProvider attitudeProv,
double mass,
double referenceRadius,
double mu,
double c20,
double c30,
double c40,
double c50,
double c60) |
Build a propagator from orbit, attitude provider, mass and potential.
|
EcksteinHechlerPropagator(Orbit initialOrbit,
AttitudeProvider attitudeProv,
double mass,
UnnormalizedSphericalHarmonicsProvider provider) |
Build a propagator from orbit, attitude provider, mass and potential provider.
|
EcksteinHechlerPropagator(Orbit initialOrbit,
AttitudeProvider attitude,
double mass,
UnnormalizedSphericalHarmonicsProvider provider,
UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics) |
Private helper constructor.
|
EcksteinHechlerPropagator(Orbit initialOrbit,
AttitudeProvider attitudeProv,
UnnormalizedSphericalHarmonicsProvider provider) |
Build a propagator from orbit, attitude provider and potential provider.
|
FieldAbstractAnalyticalPropagator(org.hipparchus.Field<T> field,
AttitudeProvider attitudeProvider) |
Build a new instance.
|
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
AttitudeProvider attitudeProv,
double referenceRadius,
double mu,
double c20,
double c30,
double c40,
double c50,
double c60) |
Build a propagator from FieldOrbit
|
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
AttitudeProvider attitudeProv,
UnnormalizedSphericalHarmonicsProvider provider) |
Build a propagator from FieldOrbit
|
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
AttitudeProvider attitudeProv,
T mass,
double referenceRadius,
double mu,
double c20,
double c30,
double c40,
double c50,
double c60) |
Build a propagator from FieldOrbit
|
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
AttitudeProvider attitudeProv,
T mass,
UnnormalizedSphericalHarmonicsProvider provider) |
Build a propagator from FieldOrbit
|
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
AttitudeProvider attitude,
T mass,
UnnormalizedSphericalHarmonicsProvider provider,
UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics) |
Private helper constructor.
|
FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit,
AttitudeProvider attitudeProv) |
Build a propagator from orbit and attitude provider.
|
FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit,
AttitudeProvider attitudeProv,
double mu) |
Build a propagator from orbit, attitude provider and central attraction
coefficient μ.
|
FieldKeplerianPropagator(FieldOrbit<T> initialOrbit,
AttitudeProvider attitudeProv,
double mu,
T mass) |
Build propagator from orbit, attitude provider, central attraction
coefficient μ and mass.
|
KeplerianPropagator(Orbit initialOrbit,
AttitudeProvider attitudeProv) |
Build a propagator from orbit and attitude provider.
|
KeplerianPropagator(Orbit initialOrbit,
AttitudeProvider attitudeProv,
double mu) |
Build a propagator from orbit, attitude provider and central attraction
coefficient μ.
|
KeplerianPropagator(Orbit initialOrbit,
AttitudeProvider attitudeProv,
double mu,
double mass) |
Build propagator from orbit, attitude provider, central attraction
coefficient μ and mass.
|
Modifier and Type | Method | Description |
---|---|---|
GPSPropagator.Builder |
GPSPropagator.Builder.attitudeProvider(AttitudeProvider userProvider) |
Sets the attitude provider.
|
Modifier and Type | Method | Description |
---|---|---|
static TLEPropagator |
TLEPropagator.selectExtrapolator(TLE tle,
AttitudeProvider attitudeProvider,
double mass) |
Selects the extrapolator to use with the selected TLE.
|
Constructor | Description |
---|---|
DeepSDP4(TLE initialTLE,
AttitudeProvider attitudeProvider,
double mass) |
Constructor for a unique initial TLE.
|
SGP4(TLE initialTLE,
AttitudeProvider attitudeProvider,
double mass) |
Constructor for a unique initial TLE.
|
TLEPropagator(TLE initialTLE,
AttitudeProvider attitudeProvider,
double mass) |
Protected constructor for derived classes.
|
Modifier and Type | Method | Description |
---|---|---|
AttitudeProvider |
NumericalPropagatorBuilder.getAttitudeProvider() |
Get the attitudeProvider.
|
Modifier and Type | Method | Description |
---|---|---|
void |
NumericalPropagatorBuilder.setAttitudeProvider(AttitudeProvider attitudeProvider) |
Set the attitude provider.
|
Modifier and Type | Method | Description |
---|---|---|
AttitudeProvider |
FieldStateMapper.getAttitudeProvider() |
Get the attitude provider.
|
AttitudeProvider |
StateMapper.getAttitudeProvider() |
Get the attitude provider.
|
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.
|
void |
AbstractIntegratedPropagator.setAttitudeProvider(AttitudeProvider attitudeProvider) |
Set attitude provider.
|
void |
FieldAbstractIntegratedPropagator.setAttitudeProvider(AttitudeProvider attitudeProvider) |
Set attitude provider.
|
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.
|
Modifier and Type | Method | Description |
---|---|---|
static SpacecraftState |
DSSTPropagator.computeMeanState(SpacecraftState osculating,
AttitudeProvider attitudeProvider,
Collection<DSSTForceModel> forceModels) |
Conversion from osculating to mean orbit.
|
static SpacecraftState |
DSSTPropagator.computeOsculatingState(SpacecraftState mean,
AttitudeProvider attitudeProvider,
Collection<DSSTForceModel> forces) |
Conversion from mean to osculating orbit.
|
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.
|
void |
DSSTPropagator.setAttitudeProvider(AttitudeProvider attitudeProvider) |
Set attitude provider.
|
Modifier and Type | Method | Description |
---|---|---|
void |
AbstractGaussianContribution.registerAttitudeProvider(AttitudeProvider provider) |
Register an attitude provider.
|
void |
DSSTForceModel.registerAttitudeProvider(AttitudeProvider provider) |
Register an attitude provider.
|
void |
DSSTTesseral.registerAttitudeProvider(AttitudeProvider attitudeProvider) |
Register an attitude provider.
|
void |
DSSTThirdBody.registerAttitudeProvider(AttitudeProvider provider) |
Register an attitude provider.
|
void |
DSSTZonal.registerAttitudeProvider(AttitudeProvider attitudeProvider) |
Register an attitude provider.
|
Modifier and Type | Method | Description |
---|---|---|
static StateJacobian |
Differentiation.differentiate(StateFunction function,
int dimension,
AttitudeProvider provider,
OrbitType orbitType,
PositionAngle positionAngle,
double dP,
int nbPoints) |
Differentiate a vector function using finite differences.
|
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