java.lang.Object
- org.orekit.propagation.FieldAbstractPropagator<T>
- - org.orekit.propagation.analytical.FieldAbstractAnalyticalPropagator<T>
  - - org.orekit.propagation.analytical.FieldEcksteinHechlerPropagator<T>

Type Parameters:

T - type of the field elements

All Implemented Interfaces:

FieldPropagator<T>, FieldPVCoordinatesProvider<T>, ParameterDriversProvider
```
public class FieldEcksteinHechlerPropagator<T extends CalculusFieldElement<T>>
extends FieldAbstractAnalyticalPropagator<T>
```
This class propagates a FieldSpacecraftState using the analytical Eckstein-Hechler model.
The Eckstein-Hechler model is suited for near circular orbits (e < 0.1, with poor accuracy between 0.005 and 0.1) and inclination neither equatorial (direct or retrograde) nor critical (direct or retrograde).

Author:

Guylaine Prat

See Also:

FieldOrbit

Field Summary
- Fields inherited from interface org.orekit.propagation.FieldPropagator
  DEFAULT_MASS

Constructor Summary

Constructors
Constructor	Description
`FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, double referenceRadius, T mu, double c20, double c30, double c40, double c50, double c60)`	Build a propagator from FieldOrbit and potential.
`FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, double referenceRadius, T mu, double c20, double c30, double c40, double c50, double c60)`	Build a propagator from FieldOrbit, attitude provider and potential.
`FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, UnnormalizedSphericalHarmonicsProvider provider)`	Build a propagator from FieldOrbit, attitude provider and potential provider.
`FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, T mass, double referenceRadius, T mu, double c20, double c30, double c40, double c50, double c60)`	Build a propagator from FieldOrbit, attitude provider, mass and potential.
`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.
`FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, T mass, double referenceRadius, T mu, double c20, double c30, double c40, double c50, double c60, PropagationType initialType, double epsilon, int maxIterations)`	Build a propagator from FieldOrbit, attitude provider, mass and potential.
`FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, T mass, double referenceRadius, T mu, double c20, double c30, double c40, double c50, double c60, PropagationType initialType, OsculatingToMeanConverter converter)`	Build a propagator from FieldOrbit, attitude provider, mass and potential.
`FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, T mass, UnnormalizedSphericalHarmonicsProvider provider)`	Build a propagator from FieldOrbit, attitude provider, mass and potential provider.
`FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitude, T mass, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics)`	Private helper constructor.
`FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitude, T mass, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics, PropagationType initialType)`	Private helper constructor.
`FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, AttitudeProvider attitudeProv, T mass, UnnormalizedSphericalHarmonicsProvider provider, PropagationType initialType)`	Build a propagator from orbit, attitude provider, mass and potential provider.
`FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, UnnormalizedSphericalHarmonicsProvider provider)`	Build a propagator from FieldOrbit and potential provider.
`FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, UnnormalizedSphericalHarmonicsProvider provider, PropagationType initialType)`	Build a propagator from orbit and potential provider.
`FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, T mass, double referenceRadius, T mu, double c20, double c30, double c40, double c50, double c60)`	Build a propagator from FieldOrbit, mass and potential.
`FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit, T mass, UnnormalizedSphericalHarmonicsProvider provider)`	Build a propagator from FieldOrbit, mass and potential provider.

Method Summary

All Methods Static Methods Instance Methods Concrete Methods
Modifier and Type	Method	Description
`static <T extends CalculusFieldElement<T>> FieldCircularOrbit<T>`	`computeMeanOrbit(FieldOrbit<T> osculating, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double c60, double epsilon, int maxIterations)`	Conversion from osculating to mean orbit.
`static <T extends CalculusFieldElement<T>> FieldCircularOrbit<T>`	`computeMeanOrbit(FieldOrbit<T> osculating, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double c60, OsculatingToMeanConverter converter)`	Conversion from osculating to mean orbit.
`static <T extends CalculusFieldElement<T>> FieldCircularOrbit<T>`	`computeMeanOrbit(FieldOrbit<T> osculating, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics)`	Conversion from osculating to mean orbit.
`static <T extends CalculusFieldElement<T>> FieldCircularOrbit<T>`	`computeMeanOrbit(FieldOrbit<T> osculating, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics, double epsilon, int maxIterations)`	Conversion from osculating to mean orbit.
`protected T`	`getMass(FieldAbsoluteDate<T> date)`	Get the mass.
`FieldCircularOrbit<T>`	`getOsculatingCircularOrbit(FieldAbsoluteDate<T> date)`	Get the osculating circular orbit from the EH model.
`List<ParameterDriver>`	`getParametersDrivers()`	Get the drivers for parameters.
`FieldCartesianOrbit<T>`	`propagateOrbit(FieldAbsoluteDate<T> date, T[] parameters)`	Propagate an orbit up to a specific target date.
`void`	`resetInitialState(FieldSpacecraftState<T> state)`	Reset the propagator initial state.
`void`	`resetInitialState(FieldSpacecraftState<T> state, PropagationType stateType)`	Reset the propagator initial state.
`void`	`resetInitialState(FieldSpacecraftState<T> state, PropagationType stateType, double epsilon, int maxIterations)`	Reset the propagator initial state.
`void`	`resetInitialState(FieldSpacecraftState<T> state, PropagationType stateType, OsculatingToMeanConverter converter)`	Reset the propagator initial state.
`protected void`	`resetIntermediateState(FieldSpacecraftState<T> state, boolean forward)`	Reset an intermediate state.
`protected void`	`resetIntermediateState(FieldSpacecraftState<T> state, boolean forward, double epsilon, int maxIterations)`	Reset an intermediate state.
`protected void`	`resetIntermediateState(FieldSpacecraftState<T> state, boolean forward, OsculatingToMeanConverter converter)`	Reset an intermediate state.

Methods inherited from class org.orekit.propagation.analytical.FieldAbstractAnalyticalPropagator
acceptStep, addEventDetector, basicPropagate, clearEventsDetectors, getEphemerisGenerator, getEventDetectors, propagate

Methods inherited from class org.orekit.propagation.FieldAbstractPropagator
addAdditionalDataProvider, getAdditionalDataProviders, getAttitudeProvider, getField, getFrame, getInitialState, getManagedAdditionalData, getMultiplexer, getStartDate, initializeAdditionalData, initializePropagation, isAdditionalDataManaged, propagate, setAttitudeProvider, setStartDate, stateChanged, updateAdditionalData, updateUnmanagedData

Methods inherited from class java.lang.Object
clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait

Methods inherited from interface org.orekit.propagation.FieldPropagator
clearStepHandlers, getPosition, getPVCoordinates, setStepHandler, setStepHandler

Methods inherited from interface org.orekit.utils.ParameterDriversProvider
getNbParametersDriversValue, getParameterDriver, getParameters, getParameters, getParameters, getParameters, getParametersAllValues, getParametersAllValues, isSupported

- Constructor Detail
  - FieldEcksteinHechlerPropagator
```
public FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
                                      UnnormalizedSphericalHarmonicsProvider provider)
```
    Build a propagator from FieldOrbit and potential provider.
    Mass and attitude provider are set to unspecified non-null arbitrary values.
    
    Using this constructor, an initial osculating orbit is considered.
    
    Conversion from osculating to mean orbit is done through a fixed-point iteration process.
    
    Parameters:
    
    initialOrbit - initial FieldOrbit
    
    provider - for un-normalized zonal coefficients
    
    See Also:
    
    FieldEcksteinHechlerPropagator(FieldOrbit, AttitudeProvider, UnnormalizedSphericalHarmonicsProvider), FieldEcksteinHechlerPropagator(FieldOrbit, UnnormalizedSphericalHarmonicsProvider, PropagationType)
  - FieldEcksteinHechlerPropagator
```
public FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
                                      AttitudeProvider attitude,
                                      T mass,
                                      UnnormalizedSphericalHarmonicsProvider provider,
                                      UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics)
```
    Private helper constructor.
    Using this constructor, an initial osculating orbit is considered.
    
    Conversion from osculating to mean orbit is done through a fixed-point iteration process.
    
    Parameters:
    
    initialOrbit - initial FieldOrbit
    
    attitude - attitude provider
    
    mass - spacecraft mass
    
    provider - for un-normalized zonal coefficients
    
    harmonics - provider.onDate(initialOrbit.getDate())
    
    See Also:
    
    FieldEcksteinHechlerPropagator(FieldOrbit, AttitudeProvider, CalculusFieldElement, UnnormalizedSphericalHarmonicsProvider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics, PropagationType)
  - FieldEcksteinHechlerPropagator
```
public FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
                                      double referenceRadius,
                                      T mu,
                                      double c20,
                                      double c30,
                                      double c40,
                                      double c50,
                                      double c60)
```
    Build a propagator from FieldOrbit and potential.
    Mass and attitude provider are set to unspecified non-null arbitrary values.
    
    The C_n,0 coefficients are the denormalized zonal coefficients, they are related to both the normalized coefficients C_n,0 and the J_n one as follows:
    C_n,0 = [(2-δ_0,m)(2n+1)(n-m)!/(n+m)!]^½ C_n,0
    C_n,0 = -J_n
    Using this constructor, an initial osculating orbit is considered.
    
    Conversion from osculating to mean orbit is done through a fixed-point iteration process.
    
    Parameters:
    
    initialOrbit - initial FieldOrbit
    
    referenceRadius - reference radius of the Earth for the potential model (m)
    
    mu - central attraction coefficient (m³/s²)
    
    c20 - un-normalized zonal coefficient (about -1.08e-3 for Earth)
    
    c30 - un-normalized zonal coefficient (about +2.53e-6 for Earth)
    
    c40 - un-normalized zonal coefficient (about +1.62e-6 for Earth)
    
    c50 - un-normalized zonal coefficient (about +2.28e-7 for Earth)
    
    c60 - un-normalized zonal coefficient (about -5.41e-7 for Earth)
    
    See Also:
    
    Constants, FieldEcksteinHechlerPropagator(FieldOrbit, AttitudeProvider, double, CalculusFieldElement, double, double, double, double, double)
  - FieldEcksteinHechlerPropagator
```
public FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
                                      T mass,
                                      UnnormalizedSphericalHarmonicsProvider provider)
```
    Build a propagator from FieldOrbit, mass and potential provider.
    Attitude law is set to an unspecified non-null arbitrary value.
    
    Using this constructor, an initial osculating orbit is considered.
    
    Conversion from osculating to mean orbit is done through a fixed-point iteration process.
    
    Parameters:
    
    initialOrbit - initial FieldOrbit
    
    mass - spacecraft mass
    
    provider - for un-normalized zonal coefficients
    
    See Also:
    
    FieldEcksteinHechlerPropagator(FieldOrbit, AttitudeProvider, CalculusFieldElement, UnnormalizedSphericalHarmonicsProvider)
  - FieldEcksteinHechlerPropagator
```
public FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
                                      T mass,
                                      double referenceRadius,
                                      T mu,
                                      double c20,
                                      double c30,
                                      double c40,
                                      double c50,
                                      double c60)
```
    Build a propagator from FieldOrbit, mass and potential.
    Attitude law is set to an unspecified non-null arbitrary value.
    
    The C_n,0 coefficients are the denormalized zonal coefficients, they are related to both the normalized coefficients C_n,0 and the J_n one as follows:
    
    C_n,0 = [(2-δ_0,m)(2n+1)(n-m)!/(n+m)!]^½ C_n,0
    C_n,0 = -J_n
    Using this constructor, an initial osculating orbit is considered.
    
    Conversion from osculating to mean orbit is done through a fixed-point iteration process.
    
    Parameters:
    
    initialOrbit - initial FieldOrbit
    
    mass - spacecraft mass
    
    referenceRadius - reference radius of the Earth for the potential model (m)
    
    mu - central attraction coefficient (m³/s²)
    
    c20 - un-normalized zonal coefficient (about -1.08e-3 for Earth)
    
    c30 - un-normalized zonal coefficient (about +2.53e-6 for Earth)
    
    c40 - un-normalized zonal coefficient (about +1.62e-6 for Earth)
    
    c50 - un-normalized zonal coefficient (about +2.28e-7 for Earth)
    
    c60 - un-normalized zonal coefficient (about -5.41e-7 for Earth)
    
    See Also:
    
    FieldEcksteinHechlerPropagator(FieldOrbit, AttitudeProvider, CalculusFieldElement, double, CalculusFieldElement, double, double, double, double, double)
  - FieldEcksteinHechlerPropagator
```
public FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
                                      AttitudeProvider attitudeProv,
                                      UnnormalizedSphericalHarmonicsProvider provider)
```
    Build a propagator from FieldOrbit, attitude provider and potential provider.
    Mass is set to an unspecified non-null arbitrary value.
    
    Using this constructor, an initial osculating orbit is considered.
    
    Conversion from osculating to mean orbit is done through a fixed-point iteration process.
    
    Parameters:
    
    initialOrbit - initial FieldOrbit
    
    attitudeProv - attitude provider
    
    provider - for un-normalized zonal coefficients
  - FieldEcksteinHechlerPropagator
```
public FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
                                      AttitudeProvider attitudeProv,
                                      double referenceRadius,
                                      T mu,
                                      double c20,
                                      double c30,
                                      double c40,
                                      double c50,
                                      double c60)
```
    Build a propagator from FieldOrbit, attitude provider and potential.
    Mass is set to an unspecified non-null arbitrary value.
    
    The C_n,0 coefficients are the denormalized zonal coefficients, they are related to both the normalized coefficients C_n,0 and the J_n one as follows:
    
    C_n,0 = [(2-δ_0,m)(2n+1)(n-m)!/(n+m)!]^½ C_n,0
    C_n,0 = -J_n
    Using this constructor, an initial osculating orbit is considered.
    
    Conversion from osculating to mean orbit is done through a fixed-point iteration process.
    
    Parameters:
    
    initialOrbit - initial FieldOrbit
    
    attitudeProv - attitude provider
    
    referenceRadius - reference radius of the Earth for the potential model (m)
    
    mu - central attraction coefficient (m³/s²)
    
    c20 - un-normalized zonal coefficient (about -1.08e-3 for Earth)
    
    c30 - un-normalized zonal coefficient (about +2.53e-6 for Earth)
    
    c40 - un-normalized zonal coefficient (about +1.62e-6 for Earth)
    
    c50 - un-normalized zonal coefficient (about +2.28e-7 for Earth)
    
    c60 - un-normalized zonal coefficient (about -5.41e-7 for Earth)
  - FieldEcksteinHechlerPropagator
```
public FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
                                      AttitudeProvider attitudeProv,
                                      T mass,
                                      UnnormalizedSphericalHarmonicsProvider provider)
```
    Build a propagator from FieldOrbit, attitude provider, mass and potential provider.
    Using this constructor, an initial osculating orbit is considered.
    
    Conversion from osculating to mean orbit is done through a fixed-point iteration process.
    
    Parameters:
    
    initialOrbit - initial FieldOrbit
    
    attitudeProv - attitude provider
    
    mass - spacecraft mass
    
    provider - for un-normalized zonal coefficients
    
    See Also:
    
    FieldEcksteinHechlerPropagator(FieldOrbit, AttitudeProvider, CalculusFieldElement, UnnormalizedSphericalHarmonicsProvider, PropagationType)
  - FieldEcksteinHechlerPropagator
```
public FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
                                      AttitudeProvider attitudeProv,
                                      T mass,
                                      double referenceRadius,
                                      T mu,
                                      double c20,
                                      double c30,
                                      double c40,
                                      double c50,
                                      double c60)
```
    Build a propagator from FieldOrbit, attitude provider, mass and potential.
    The C_n,0 coefficients are the denormalized zonal coefficients, they are related to both the normalized coefficients C_n,0 and the J_n one as follows:
    
    C_n,0 = [(2-δ_0,m)(2n+1)(n-m)!/(n+m)!]^½ C_n,0
    C_n,0 = -J_n
    Using this constructor, an initial osculating orbit is considered.
    
    Conversion from osculating to mean orbit is done through a fixed-point iteration process.
    
    Parameters:
    
    initialOrbit - initial FieldOrbit
    
    attitudeProv - attitude provider
    
    mass - spacecraft mass
    
    referenceRadius - reference radius of the Earth for the potential model (m)
    
    mu - central attraction coefficient (m³/s²)
    
    c20 - un-normalized zonal coefficient (about -1.08e-3 for Earth)
    
    c30 - un-normalized zonal coefficient (about +2.53e-6 for Earth)
    
    c40 - un-normalized zonal coefficient (about +1.62e-6 for Earth)
    
    c50 - un-normalized zonal coefficient (about +2.28e-7 for Earth)
    
    c60 - un-normalized zonal coefficient (about -5.41e-7 for Earth)
    
    See Also:
    
    FieldEcksteinHechlerPropagator(FieldOrbit, AttitudeProvider, CalculusFieldElement, double, CalculusFieldElement, double, double, double, double, double, PropagationType)
  - FieldEcksteinHechlerPropagator
```
public FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
                                      UnnormalizedSphericalHarmonicsProvider provider,
                                      PropagationType initialType)
```
    Build a propagator from orbit and potential provider.
    Mass and attitude provider are set to unspecified non-null arbitrary values.
    
    Using this constructor, it is possible to define the initial orbit as a mean Eckstein-Hechler orbit or an osculating one.
    
    Conversion from osculating to mean orbit will be done through a fixed-point iteration process.
    
    Parameters:
    
    initialOrbit - initial orbit
    
    provider - for un-normalized zonal coefficients
    
    initialType - initial orbit type (mean Eckstein-Hechler orbit or osculating orbit)
    
    Since:
    
    10.2
  - FieldEcksteinHechlerPropagator
```
public FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
                                      AttitudeProvider attitudeProv,
                                      T mass,
                                      UnnormalizedSphericalHarmonicsProvider provider,
                                      PropagationType initialType)
```
    Build a propagator from orbit, attitude provider, mass and potential provider.
    Using this constructor, it is possible to define the initial orbit as a mean Eckstein-Hechler orbit or an osculating one.
    
    Conversion from osculating to mean orbit will be done through a fixed-point iteration process.
    
    Parameters:
    
    initialOrbit - initial orbit
    
    attitudeProv - attitude provider
    
    mass - spacecraft mass
    
    provider - for un-normalized zonal coefficients
    
    initialType - initial orbit type (mean Eckstein-Hechler orbit or osculating orbit)
    
    Since:
    
    10.2
  - FieldEcksteinHechlerPropagator
```
public FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
                                      AttitudeProvider attitude,
                                      T mass,
                                      UnnormalizedSphericalHarmonicsProvider provider,
                                      UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics,
                                      PropagationType initialType)
```
    Private helper constructor.
    Using this constructor, it is possible to define the initial orbit as a mean Eckstein-Hechler orbit or an osculating one.
    
    Conversion from osculating to mean orbit will be done through a fixed-point iteration process.
    
    Parameters:
    
    initialOrbit - initial orbit
    
    attitude - attitude provider
    
    mass - spacecraft mass
    
    provider - for un-normalized zonal coefficients
    
    harmonics - provider.onDate(initialOrbit.getDate())
    
    initialType - initial orbit type (mean Eckstein-Hechler orbit or osculating orbit)
    
    Since:
    
    10.2
  - FieldEcksteinHechlerPropagator
```
public 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.
    The C_n,0 coefficients are the denormalized zonal coefficients, they are related to both the normalized coefficients C_n,0 and the J_n one as follows:
    
    C_n,0 = [(2-δ_0,m)(2n+1)(n-m)!/(n+m)!]^½ C_n,0
    C_n,0 = -J_n
    Using this constructor, it is possible to define the initial orbit as a mean Eckstein-Hechler orbit or an osculating one.
    
    Conversion from osculating to mean orbit will be done through a fixed-point iteration process.
    
    Parameters:
    
    initialOrbit - initial FieldOrbit
    
    attitudeProv - attitude provider
    
    mass - spacecraft mass
    
    referenceRadius - reference radius of the Earth for the potential model (m)
    
    mu - central attraction coefficient (m³/s²)
    
    c20 - un-normalized zonal coefficient (about -1.08e-3 for Earth)
    
    c30 - un-normalized zonal coefficient (about +2.53e-6 for Earth)
    
    c40 - un-normalized zonal coefficient (about +1.62e-6 for Earth)
    
    c50 - un-normalized zonal coefficient (about +2.28e-7 for Earth)
    
    c60 - un-normalized zonal coefficient (about -5.41e-7 for Earth)
    
    initialType - initial orbit type (mean Eckstein-Hechler orbit or osculating orbit)
    
    Since:
    
    10.2
  - FieldEcksteinHechlerPropagator
```
public FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
                                      AttitudeProvider attitudeProv,
                                      T mass,
                                      double referenceRadius,
                                      T mu,
                                      double c20,
                                      double c30,
                                      double c40,
                                      double c50,
                                      double c60,
                                      PropagationType initialType,
                                      double epsilon,
                                      int maxIterations)
```
    Build a propagator from FieldOrbit, attitude provider, mass and potential.
    The C_n,0 coefficients are the denormalized zonal coefficients, they are related to both the normalized coefficients C_n,0 and the J_n one as follows:
    
    C_n,0 = [(2-δ_0,m)(2n+1)(n-m)!/(n+m)!]^½ C_n,0
    C_n,0 = -J_n
    Using this constructor, it is possible to define the initial orbit as a mean Eckstein-Hechler orbit or an osculating one.
    
    Conversion from osculating to mean orbit will be done through a fixed-point iteration process.
    
    Parameters:
    
    initialOrbit - initial FieldOrbit
    
    attitudeProv - attitude provider
    
    mass - spacecraft mass
    
    referenceRadius - reference radius of the Earth for the potential model (m)
    
    mu - central attraction coefficient (m³/s²)
    
    c20 - un-normalized zonal coefficient (about -1.08e-3 for Earth)
    
    c30 - un-normalized zonal coefficient (about +2.53e-6 for Earth)
    
    c40 - un-normalized zonal coefficient (about +1.62e-6 for Earth)
    
    c50 - un-normalized zonal coefficient (about +2.28e-7 for Earth)
    
    c60 - un-normalized zonal coefficient (about -5.41e-7 for Earth)
    
    initialType - initial orbit type (mean Eckstein-Hechler orbit or osculating orbit)
    
    epsilon - convergence threshold for mean parameters conversion
    
    maxIterations - maximum iterations for mean parameters conversion
    
    Since:
    
    11.2
  - FieldEcksteinHechlerPropagator
```
public FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
                                      AttitudeProvider attitudeProv,
                                      T mass,
                                      double referenceRadius,
                                      T mu,
                                      double c20,
                                      double c30,
                                      double c40,
                                      double c50,
                                      double c60,
                                      PropagationType initialType,
                                      OsculatingToMeanConverter converter)
```
    Build a propagator from FieldOrbit, attitude provider, mass and potential.
    The C_n,0 coefficients are the denormalized zonal coefficients, they are related to both the normalized coefficients C_n,0 and the J_n one as follows:
    
    C_n,0 = [(2-δ_0,m)(2n+1)(n-m)!/(n+m)!]^½ C_n,0
    C_n,0 = -J_n
    Using this constructor, it is possible to define the initial orbit as a mean Eckstein-Hechler orbit or an osculating one.
    
    Conversion from osculating to mean orbit will be done through the given converter.
    
    Parameters:
    
    initialOrbit - initial FieldOrbit
    
    attitudeProv - attitude provider
    
    mass - spacecraft mass
    
    referenceRadius - reference radius of the Earth for the potential model (m)
    
    mu - central attraction coefficient (m³/s²)
    
    c20 - un-normalized zonal coefficient (about -1.08e-3 for Earth)
    
    c30 - un-normalized zonal coefficient (about +2.53e-6 for Earth)
    
    c40 - un-normalized zonal coefficient (about +1.62e-6 for Earth)
    
    c50 - un-normalized zonal coefficient (about +2.28e-7 for Earth)
    
    c60 - un-normalized zonal coefficient (about -5.41e-7 for Earth)
    
    initialType - initial orbit type (mean Eckstein-Hechler orbit or osculating orbit)
    
    converter - osculating to mean orbit converter
    
    Since:
    
    13.0
- Method Detail
  - computeMeanOrbit
```
public static <T extends CalculusFieldElement<T>> FieldCircularOrbit<T> computeMeanOrbit(FieldOrbit<T> osculating,
                                                                                         UnnormalizedSphericalHarmonicsProvider provider,
                                                                                         UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics)
```
    Conversion from osculating to mean orbit.
    Compute mean orbit in a Eckstein-Hechler sense, corresponding to the osculating SpacecraftState in input.
    
    Since the osculating orbit is obtained with the computation of short-periodic variation, the resulting output will depend on the gravity field parameterized in input.
    
    The computation is done through a fixed-point iteration process.
    
    Type Parameters:
    
    T - type of the filed elements
    
    Parameters:
    
    osculating - osculating orbit to convert
    
    provider - for un-normalized zonal coefficients
    
    harmonics - provider.onDate(osculating.getDate())
    
    Returns:
    
    mean orbit in a Eckstein-Hechler sense
    
    Since:
    
    11.2
  - computeMeanOrbit
```
public static <T extends CalculusFieldElement<T>> FieldCircularOrbit<T> computeMeanOrbit(FieldOrbit<T> osculating,
                                                                                         UnnormalizedSphericalHarmonicsProvider provider,
                                                                                         UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics,
                                                                                         double epsilon,
                                                                                         int maxIterations)
```
    Conversion from osculating to mean orbit.
    Compute mean orbit in a Eckstein-Hechler sense, corresponding to the osculating SpacecraftState in input.
    
    Since the osculating orbit is obtained with the computation of short-periodic variation, the resulting output will depend on the gravity field parameterized in input.
    
    The computation is done through a fixed-point iteration process.
    
    Type Parameters:
    
    T - type of the filed elements
    
    Parameters:
    
    osculating - osculating orbit to convert
    
    provider - for un-normalized zonal coefficients
    
    harmonics - provider.onDate(osculating.getDate())
    
    epsilon - convergence threshold for mean parameters conversion
    
    maxIterations - maximum iterations for mean parameters conversion
    
    Returns:
    
    mean orbit in a Eckstein-Hechler sense
    
    Since:
    
    11.2
  - computeMeanOrbit
```
public static <T extends CalculusFieldElement<T>> FieldCircularOrbit<T> computeMeanOrbit(FieldOrbit<T> osculating,
                                                                                         double referenceRadius,
                                                                                         double mu,
                                                                                         double c20,
                                                                                         double c30,
                                                                                         double c40,
                                                                                         double c50,
                                                                                         double c60,
                                                                                         double epsilon,
                                                                                         int maxIterations)
```
    Conversion from osculating to mean orbit.
    Compute mean orbit in a Eckstein-Hechler sense, corresponding to the osculating SpacecraftState in input.
    
    Since the osculating orbit is obtained with the computation of short-periodic variation, the resulting output will depend on the gravity field parameterized in input.
    
    The computation is done through a fixed-point iteration process.
    
    Type Parameters:
    
    T - type of the filed elements
    
    Parameters:
    
    osculating - osculating orbit to convert
    
    referenceRadius - reference radius of the Earth for the potential model (m)
    
    mu - central attraction coefficient (m³/s²)
    
    c20 - un-normalized zonal coefficient (about -1.08e-3 for Earth)
    
    c30 - un-normalized zonal coefficient (about +2.53e-6 for Earth)
    
    c40 - un-normalized zonal coefficient (about +1.62e-6 for Earth)
    
    c50 - un-normalized zonal coefficient (about +2.28e-7 for Earth)
    
    c60 - un-normalized zonal coefficient (about -5.41e-7 for Earth)
    
    epsilon - convergence threshold for mean parameters conversion
    
    maxIterations - maximum iterations for mean parameters conversion
    
    Returns:
    
    mean orbit in a Eckstein-Hechler sense
    
    Since:
    
    11.2
  - computeMeanOrbit
```
public static <T extends CalculusFieldElement<T>> FieldCircularOrbit<T> computeMeanOrbit(FieldOrbit<T> osculating,
                                                                                         double referenceRadius,
                                                                                         double mu,
                                                                                         double c20,
                                                                                         double c30,
                                                                                         double c40,
                                                                                         double c50,
                                                                                         double c60,
                                                                                         OsculatingToMeanConverter converter)
```
    Conversion from osculating to mean orbit.
    Compute mean orbit in a Eckstein-Hechler sense, corresponding to the osculating SpacecraftState in input.
    
    Since the osculating orbit is obtained with the computation of short-periodic variation, the resulting output will depend on the gravity field parameterized in input.
    
    The computation is done through the given osculating to mean orbit converter.
    
    Type Parameters:
    
    T - type of the filed elements
    
    Parameters:
    
    osculating - osculating orbit to convert
    
    referenceRadius - reference radius of the Earth for the potential model (m)
    
    mu - central attraction coefficient (m³/s²)
    
    c20 - un-normalized zonal coefficient (about -1.08e-3 for Earth)
    
    c30 - un-normalized zonal coefficient (about +2.53e-6 for Earth)
    
    c40 - un-normalized zonal coefficient (about +1.62e-6 for Earth)
    
    c50 - un-normalized zonal coefficient (about +2.28e-7 for Earth)
    
    c60 - un-normalized zonal coefficient (about -5.41e-7 for Earth)
    
    converter - osculating to mean orbit converter
    
    Returns:
    
    mean orbit in a Eckstein-Hechler sense
    
    Since:
    
    13.0
  - resetInitialState
```
public void resetInitialState(FieldSpacecraftState<T> state)
```
    Reset the propagator initial state.
    The new initial state to consider must be defined with an osculating orbit.
    
    Specified by:
    
    resetInitialState in interface FieldPropagator<T extends CalculusFieldElement<T>>
    
    Overrides:
    
    resetInitialState in class FieldAbstractPropagator<T extends CalculusFieldElement<T>>
    
    Parameters:
    
    state - new initial state to consider
    
    See Also:
    
    resetInitialState(FieldSpacecraftState, PropagationType)
  - resetInitialState
```
public void resetInitialState(FieldSpacecraftState<T> state,
                              PropagationType stateType)
```
    Reset the propagator initial state.
    
    Parameters:
    
    state - new initial state to consider
    
    stateType - mean Eckstein-Hechler orbit or osculating orbit
    
    Since:
    
    10.2
  - resetInitialState
```
public void resetInitialState(FieldSpacecraftState<T> state,
                              PropagationType stateType,
                              double epsilon,
                              int maxIterations)
```
    Reset the propagator initial state.
    
    Parameters:
    
    state - new initial state to consider
    
    stateType - mean Eckstein-Hechler orbit or osculating orbit
    
    epsilon - convergence threshold for mean parameters conversion
    
    maxIterations - maximum iterations for mean parameters conversion
    
    Since:
    
    11.2
  - resetInitialState
```
public void resetInitialState(FieldSpacecraftState<T> state,
                              PropagationType stateType,
                              OsculatingToMeanConverter converter)
```
    Reset the propagator initial state.
    
    Parameters:
    
    state - new initial state to consider
    
    stateType - mean Eckstein-Hechler orbit or osculating orbit
    
    converter - osculating to mean orbit converter
    
    Since:
    
    13.0
  - resetIntermediateState
```
protected void resetIntermediateState(FieldSpacecraftState<T> state,
                                      boolean forward)
```
    Reset an intermediate state.
    
    Specified by:
    
    resetIntermediateState in class FieldAbstractAnalyticalPropagator<T extends CalculusFieldElement<T>>
    
    Parameters:
    
    state - new intermediate state to consider
    
    forward - if true, the intermediate state is valid for propagations after itself
  - resetIntermediateState
```
protected void resetIntermediateState(FieldSpacecraftState<T> state,
                                      boolean forward,
                                      double epsilon,
                                      int maxIterations)
```
    Reset an intermediate state.
    
    Parameters:
    
    state - new intermediate state to consider
    
    forward - if true, the intermediate state is valid for propagations after itself
    
    epsilon - convergence threshold for mean parameters conversion
    
    maxIterations - maximum iterations for mean parameters conversion
    
    Since:
    
    11.2
  - resetIntermediateState
```
protected void resetIntermediateState(FieldSpacecraftState<T> state,
                                      boolean forward,
                                      OsculatingToMeanConverter converter)
```
    Reset an intermediate state.
    
    Parameters:
    
    state - new intermediate state to consider
    
    forward - if true, the intermediate state is valid for propagations after itself
    
    converter - osculating to mean orbit converter
    
    Since:
    
    13.0
  - propagateOrbit
```
public FieldCartesianOrbit<T> propagateOrbit(FieldAbsoluteDate<T> date,
                                             T[] parameters)
```
    Propagate an orbit up to a specific target date.
    
    Specified by:
    
    propagateOrbit in class FieldAbstractAnalyticalPropagator<T extends CalculusFieldElement<T>>
    
    Parameters:
    
    date - target date for the orbit
    
    parameters - model parameters
    
    Returns:
    
    propagated orbit
  - getOsculatingCircularOrbit
```
public FieldCircularOrbit<T> getOsculatingCircularOrbit(FieldAbsoluteDate<T> date)
```
    Get the osculating circular orbit from the EH model.
    This method is only relevant for the conversion from osculating to mean orbit.
    
    Parameters:
    
    date - target date for the orbit
    
    Returns:
    
    the osculating circular orbite
  - getMass
```
protected T getMass(FieldAbsoluteDate<T> date)
```
    Get the mass.
    
    Specified by:
    
    getMass in class FieldAbstractAnalyticalPropagator<T extends CalculusFieldElement<T>>
    
    Parameters:
    
    date - target date for the orbit
    
    Returns:
    
    mass mass
  - getParametersDrivers
```
public List<ParameterDriver> getParametersDrivers()
```
    Get the drivers for parameters.
    
    Returns:
    
    drivers for parameters

Class FieldEcksteinHechlerPropagator<T extends CalculusFieldElement<T>>

Field Summary

Fields inherited from interface org.orekit.propagation.FieldPropagator

Constructor Summary

Method Summary

Methods inherited from class org.orekit.propagation.analytical.FieldAbstractAnalyticalPropagator

Methods inherited from class org.orekit.propagation.FieldAbstractPropagator

Methods inherited from class java.lang.Object

Methods inherited from interface org.orekit.propagation.FieldPropagator

Methods inherited from interface org.orekit.utils.ParameterDriversProvider

Constructor Detail

FieldEcksteinHechlerPropagator

FieldEcksteinHechlerPropagator

FieldEcksteinHechlerPropagator

FieldEcksteinHechlerPropagator

FieldEcksteinHechlerPropagator

FieldEcksteinHechlerPropagator

FieldEcksteinHechlerPropagator

FieldEcksteinHechlerPropagator

FieldEcksteinHechlerPropagator

FieldEcksteinHechlerPropagator

FieldEcksteinHechlerPropagator

FieldEcksteinHechlerPropagator

FieldEcksteinHechlerPropagator

FieldEcksteinHechlerPropagator

FieldEcksteinHechlerPropagator

Method Detail

computeMeanOrbit

computeMeanOrbit

computeMeanOrbit

computeMeanOrbit

resetInitialState

resetInitialState

resetInitialState

resetInitialState

resetIntermediateState

resetIntermediateState

resetIntermediateState

propagateOrbit

getOsculatingCircularOrbit

getMass

getParametersDrivers