Package | Description |
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org.orekit.estimation.leastsquares |
The leastsquares package provides an implementation of a batch least
squares estimator engine to perform an orbit determination.
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org.orekit.estimation.sequential |
The sequential package provides an implementation of a
Kalman Filter engine to perform an orbit determination.
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org.orekit.propagation |
Propagation
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org.orekit.propagation.analytical |
Top level package for analytical propagators.
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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).
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org.orekit.propagation.semianalytical.dsst |
This package provides an implementation of the Draper Semi-analytical
Satellite Theory (DSST).
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org.orekit.propagation.semianalytical.dsst.forces |
This package provides force models for Draper Semi-analytical Satellite Theory (DSST).
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Constructor and Description |
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DSSTBatchLSModel(OrbitDeterminationPropagatorBuilder[] propagatorBuilders,
List<ObservedMeasurement<?>> measurements,
ParameterDriversList estimatedMeasurementsParameters,
ModelObserver observer,
PropagationType propagationType,
PropagationType stateType)
Simple constructor.
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Modifier and Type | Method and Description |
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protected abstract void |
AbstractKalmanModel.updateReferenceTrajectories(Propagator[] propagators,
PropagationType pType,
PropagationType sType)
Update the reference trajectories using the propagators as input.
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protected void |
TLEKalmanModel.updateReferenceTrajectories(Propagator[] propagators,
PropagationType pType,
PropagationType sType)
Update the reference trajectories using the propagators as input.
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protected void |
DSSTKalmanModel.updateReferenceTrajectories(Propagator[] propagators,
PropagationType pType,
PropagationType sType)
Update the reference trajectories using the propagators as input.
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protected void |
KalmanModel.updateReferenceTrajectories(Propagator[] propagators,
PropagationType pType,
PropagationType sType)
Update the reference trajectories using the propagators as input.
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Constructor and Description |
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AbstractKalmanModel(List<OrbitDeterminationPropagatorBuilder> propagatorBuilders,
List<CovarianceMatrixProvider> covarianceMatricesProviders,
ParameterDriversList estimatedMeasurementParameters,
CovarianceMatrixProvider measurementProcessNoiseMatrix,
AbstractJacobiansMapper[] mappers,
PropagationType propagationType,
PropagationType stateType)
Kalman process model constructor (package private).
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DSSTKalmanModel(List<OrbitDeterminationPropagatorBuilder> propagatorBuilders,
List<CovarianceMatrixProvider> covarianceMatricesProviders,
ParameterDriversList estimatedMeasurementParameters,
CovarianceMatrixProvider measurementProcessNoiseMatrix,
PropagationType propagationType,
PropagationType stateType)
Kalman process model constructor.
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Modifier and Type | Method and Description |
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static PropagationType |
PropagationType.valueOf(String name)
Returns the enum constant of this type with the specified name.
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static PropagationType[] |
PropagationType.values()
Returns an array containing the constants of this enum type, in
the order they are declared.
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Modifier and Type | Method and Description |
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void |
FieldEcksteinHechlerPropagator.resetInitialState(FieldSpacecraftState<T> state,
PropagationType stateType)
Reset the propagator initial state.
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void |
EcksteinHechlerPropagator.resetInitialState(SpacecraftState state,
PropagationType stateType)
Reset the propagator initial state.
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Constructor and Description |
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EcksteinHechlerPropagator(Orbit initialOrbit,
AttitudeProvider attitudeProv,
double mass,
double referenceRadius,
double mu,
double c20,
double c30,
double c40,
double c50,
double c60,
PropagationType initialType)
Build a propagator from orbit, attitude provider, mass and potential.
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EcksteinHechlerPropagator(Orbit initialOrbit,
AttitudeProvider attitudeProv,
double mass,
UnnormalizedSphericalHarmonicsProvider provider,
PropagationType initialType)
Build a propagator from orbit, attitude provider, mass and potential provider.
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EcksteinHechlerPropagator(Orbit initialOrbit,
AttitudeProvider attitude,
double mass,
UnnormalizedSphericalHarmonicsProvider provider,
UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics,
PropagationType initialType)
Private helper constructor.
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EcksteinHechlerPropagator(Orbit initialOrbit,
UnnormalizedSphericalHarmonicsProvider provider,
PropagationType initialType)
Build a propagator from orbit and potential provider.
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FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
AttitudeProvider attitudeProv,
T mass,
double referenceRadius,
T mu,
double c20,
double c30,
double c40,
double c50,
double c60,
PropagationType initialType)
Build a propagator from FieldOrbit, attitude provider, mass and potential.
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FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
AttitudeProvider attitudeProv,
T mass,
UnnormalizedSphericalHarmonicsProvider provider,
PropagationType initialType)
Build a propagator from orbit, attitude provider, mass and potential provider.
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FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
AttitudeProvider attitude,
T mass,
UnnormalizedSphericalHarmonicsProvider provider,
UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics,
PropagationType initialType)
Private helper constructor.
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FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
UnnormalizedSphericalHarmonicsProvider provider,
PropagationType initialType)
Build a propagator from orbit and potential provider.
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Constructor and Description |
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DSSTPropagatorBuilder(Orbit referenceOrbit,
ODEIntegratorBuilder builder,
double positionScale,
PropagationType propagationType,
PropagationType stateType)
Build a new instance.
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DSSTPropagatorBuilder(Orbit referenceOrbit,
ODEIntegratorBuilder builder,
double positionScale,
PropagationType propagationType,
PropagationType stateType,
AttitudeProvider attitudeProvider)
Build a new instance.
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Modifier and Type | Method and Description |
---|---|
protected PropagationType |
AbstractIntegratedPropagator.isMeanOrbit()
Check if only the mean elements should be used in a semianalitical propagation.
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protected PropagationType |
FieldAbstractIntegratedPropagator.isMeanOrbit()
Check if only the mean elements should be used in a semianalitical propagation.
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Modifier and Type | Method and Description |
---|---|
abstract SpacecraftState |
StateMapper.mapArrayToState(AbsoluteDate date,
double[] y,
double[] yDot,
PropagationType type)
Map the raw double components to a spacecraft state.
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SpacecraftState |
StateMapper.mapArrayToState(double t,
double[] y,
double[] yDot,
PropagationType type)
Map the raw double components to a spacecraft state.
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abstract FieldSpacecraftState<T> |
FieldStateMapper.mapArrayToState(FieldAbsoluteDate<T> date,
T[] y,
T[] yDot,
PropagationType type)
Map the raw double components to a spacecraft state.
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FieldSpacecraftState<T> |
FieldStateMapper.mapArrayToState(T t,
T[] y,
T[] yDot,
PropagationType type)
Map the raw double components to a spacecraft state.
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Constructor and Description |
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AbstractIntegratedPropagator(ODEIntegrator integrator,
PropagationType propagationType)
Build a new instance.
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FieldAbstractIntegratedPropagator(Field<T> field,
FieldODEIntegrator<T> integrator,
PropagationType propagationType)
Build a new instance.
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FieldIntegratedEphemeris(FieldAbsoluteDate<T> startDate,
FieldAbsoluteDate<T> minDate,
FieldAbsoluteDate<T> maxDate,
FieldStateMapper<T> mapper,
PropagationType type,
FieldDenseOutputModel<T> model,
Map<String,T[]> unmanaged,
List<FieldAdditionalStateProvider<T>> providers,
String[] equations)
Creates a new instance of IntegratedEphemeris.
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IntegratedEphemeris(AbsoluteDate startDate,
AbsoluteDate minDate,
AbsoluteDate maxDate,
StateMapper mapper,
PropagationType type,
DenseOutputModel model,
Map<String,double[]> unmanaged,
List<AdditionalStateProvider> providers,
String[] equations)
Creates a new instance of IntegratedEphemeris.
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Modifier and Type | Method and Description |
---|---|
void |
FieldDSSTPropagator.setInitialState(FieldSpacecraftState<T> initialState,
PropagationType stateType)
Set the initial state.
|
void |
DSSTPropagator.setInitialState(SpacecraftState initialState,
PropagationType stateType)
Set the initial state.
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Constructor and Description |
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DSSTPartialDerivativesEquations(String name,
DSSTPropagator propagator,
PropagationType propagationType)
Simple constructor.
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DSSTPropagator(ODEIntegrator integrator,
PropagationType propagationType)
Create a new instance of DSSTPropagator.
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DSSTPropagator(ODEIntegrator integrator,
PropagationType propagationType,
AttitudeProvider attitudeProvider)
Create a new instance of DSSTPropagator.
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FieldDSSTPropagator(Field<T> field,
FieldODEIntegrator<T> integrator,
PropagationType propagationType)
Create a new instance of DSSTPropagator.
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FieldDSSTPropagator(Field<T> field,
FieldODEIntegrator<T> integrator,
PropagationType propagationType,
AttitudeProvider attitudeProvider)
Create a new instance of DSSTPropagator.
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Modifier and Type | Method and Description |
---|---|
List<ShortPeriodTerms> |
DSSTZonal.initializeShortPeriodTerms(AuxiliaryElements auxiliaryElements,
PropagationType type,
double[] parameters)
Performs initialization prior to propagation for the current force model.
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List<ShortPeriodTerms> |
AbstractGaussianContribution.initializeShortPeriodTerms(AuxiliaryElements auxiliaryElements,
PropagationType type,
double[] parameters)
Performs initialization prior to propagation for the current force model.
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List<ShortPeriodTerms> |
DSSTNewtonianAttraction.initializeShortPeriodTerms(AuxiliaryElements auxiliaryElements,
PropagationType type,
double[] parameters)
Performs initialization prior to propagation for the current force model.
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List<ShortPeriodTerms> |
DSSTForceModel.initializeShortPeriodTerms(AuxiliaryElements auxiliaryElements,
PropagationType type,
double[] parameters)
Performs initialization prior to propagation for the current force model.
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List<ShortPeriodTerms> |
DSSTTesseral.initializeShortPeriodTerms(AuxiliaryElements auxiliaryElements,
PropagationType type,
double[] parameters)
Performs initialization prior to propagation for the current force model.
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List<ShortPeriodTerms> |
DSSTThirdBody.initializeShortPeriodTerms(AuxiliaryElements auxiliaryElements,
PropagationType type,
double[] parameters)
Computes the highest power of the eccentricity and the highest power
of a/R3 to appear in the truncated analytical power series expansion.
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<T extends CalculusFieldElement<T>> |
DSSTZonal.initializeShortPeriodTerms(FieldAuxiliaryElements<T> auxiliaryElements,
PropagationType type,
T[] parameters)
Performs initialization prior to propagation for the current force model.
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<T extends CalculusFieldElement<T>> |
AbstractGaussianContribution.initializeShortPeriodTerms(FieldAuxiliaryElements<T> auxiliaryElements,
PropagationType type,
T[] parameters)
Performs initialization prior to propagation for the current force model.
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<T extends CalculusFieldElement<T>> |
DSSTNewtonianAttraction.initializeShortPeriodTerms(FieldAuxiliaryElements<T> auxiliaryElements,
PropagationType type,
T[] parameters)
Performs initialization prior to propagation for the current force model.
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<T extends CalculusFieldElement<T>> |
DSSTForceModel.initializeShortPeriodTerms(FieldAuxiliaryElements<T> auxiliaryElements,
PropagationType type,
T[] parameters)
Performs initialization prior to propagation for the current force model.
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<T extends CalculusFieldElement<T>> |
DSSTTesseral.initializeShortPeriodTerms(FieldAuxiliaryElements<T> auxiliaryElements,
PropagationType type,
T[] parameters)
Performs initialization prior to propagation for the current force model.
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<T extends CalculusFieldElement<T>> |
DSSTThirdBody.initializeShortPeriodTerms(FieldAuxiliaryElements<T> auxiliaryElements,
PropagationType type,
T[] parameters)
Performs initialization prior to propagation for the current force model.
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