BrouwerLyddanePropagator (ORbit Extrapolation KIT 11.1.2 API)

java.lang.Object
- org.orekit.propagation.AbstractPropagator
- - org.orekit.propagation.analytical.AbstractAnalyticalPropagator
  - - org.orekit.propagation.analytical.BrouwerLyddanePropagator

All Implemented Interfaces:

Propagator, PVCoordinatesProvider
```
public class BrouwerLyddanePropagator
extends AbstractAnalyticalPropagator
```
This class propagates a SpacecraftState using the analytical Brouwer-Lyddane model (from J2 to J5 zonal harmonics).
At the opposite of the EcksteinHechlerPropagator, the Brouwer-Lyddane model is suited for elliptical orbits, there is no problem having a rather small eccentricity or inclination (Lyddane helped to solve this issue with the Brouwer model). Singularity for the critical inclination i = 63.4° is avoided using the method developed in Warren Phipps' 1992 thesis.
By default, Brouwer-Lyddane model considers only the perturbations due to zonal harmonics. However, for low Earth orbits, the magnitude of the perturbative acceleration due to atmospheric drag can be significant. Warren Phipps' 1992 thesis considered the atmospheric drag by time derivatives of the mean mean anomaly using the catch-all coefficient M2Driver. Usually, M2 is adjusted during an orbit determination process and it represents the combination of all unmodeled secular along-track effects (i.e. not just the atmospheric drag). The behavior of M2 is close to the TLE.getBStar() parameter for the TLE. If the value of M2 is equal to 0.0, the along-track secular effects are not considered in the dynamical model. Typical values for M2 are not known. It depends on the orbit type. However, the value of M2 must be very small (e.g. between 1.0e-14 and 1.0e-15). The unit of M2 is rad/s². The along-track effects, represented by the secular rates of the mean semi-major axis and eccentricity, are computed following Eq. 2.38, 2.41, and 2.45 of Warren Phipps' thesis.

Since:

11.1

Author:

Melina Vanel, Bryan Cazabonne

See Also:

"Brouwer, Dirk. Solution of the problem of artificial satellite theory without drag. YALE UNIV NEW HAVEN CT NEW HAVEN United States, 1959.", "Lyddane, R. H. Small eccentricities or inclinations in the Brouwer theory of the artificial satellite. The Astronomical Journal 68 (1963): 555.", "Phipps Jr, Warren E. Parallelization of the Navy Space Surveillance Center (NAVSPASUR) Satellite Model. NAVAL POSTGRADUATE SCHOOL MONTEREY CA, 1992."

Field Summary

Fields
Modifier and Type Field and Description

static double M2
Default value for M2 coefficient.

static String M2_NAME
Parameter name for M2 coefficient.
- Fields inherited from interface org.orekit.propagation.Propagator
  DEFAULT_MASS

Fields
Modifier and Type	Field and Description
`static double`	`M2` Default value for M2 coefficient.
`static String`	`M2_NAME` Parameter name for M2 coefficient.

Constructor Summary

Constructors
Constructor and Description
`BrouwerLyddanePropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double M2)` Build a propagator from orbit, attitude provider and potential.
`BrouwerLyddanePropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mass, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double M2)` Build a propagator from orbit, attitude provider, mass and potential.
`BrouwerLyddanePropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mass, double referenceRadius, double mu, double c20, double c30, double c40, double c50, PropagationType initialType, double M2)` Build a propagator from orbit, attitude provider, mass and potential.
`BrouwerLyddanePropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mass, UnnormalizedSphericalHarmonicsProvider provider, double M2)` Build a propagator from orbit, attitude provider, mass and potential provider.
`BrouwerLyddanePropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mass, UnnormalizedSphericalHarmonicsProvider provider, PropagationType initialType, double M2)` Build a propagator from orbit, attitude provider, mass and potential provider.
`BrouwerLyddanePropagator(Orbit initialOrbit, AttitudeProvider attitude, double mass, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics, double M2)` Private helper constructor.
`BrouwerLyddanePropagator(Orbit initialOrbit, AttitudeProvider attitude, double mass, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics, PropagationType initialType, double M2)` Private helper constructor.
`BrouwerLyddanePropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, UnnormalizedSphericalHarmonicsProvider provider, double M2)` Build a propagator from orbit, attitude provider and potential provider.
`BrouwerLyddanePropagator(Orbit initialOrbit, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double M2)` Build a propagator from orbit and potential.
`BrouwerLyddanePropagator(Orbit initialOrbit, double mass, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double M2)` Build a propagator from orbit, mass and potential.
`BrouwerLyddanePropagator(Orbit initialOrbit, double mass, UnnormalizedSphericalHarmonicsProvider provider, double M2)` Build a propagator from orbit, mass and potential provider.
`BrouwerLyddanePropagator(Orbit initialOrbit, UnnormalizedSphericalHarmonicsProvider provider, double M2)` Build a propagator from orbit and potential provider.
`BrouwerLyddanePropagator(Orbit initialOrbit, UnnormalizedSphericalHarmonicsProvider provider, PropagationType initialType, double M2)` Build a propagator from orbit and potential provider.

Method Summary

All Methods Instance Methods Concrete Methods
Modifier and Type	Method and Description
`protected AbstractMatricesHarvester`	`createHarvester(String stmName, RealMatrix initialStm, DoubleArrayDictionary initialJacobianColumns)` Create the harvester suitable for propagator.
`double[]`	`getCk0()` Get the un-normalized zonal coefficients.
`protected List<String>`	`getJacobiansColumnsNames()` Get the names of the parameters in the matrix returned by `MatricesHarvester.getParametersJacobian(org.orekit.propagation.SpacecraftState)`.
`double`	`getM2()` Get the value of the M2 drag parameter.
`protected double`	`getMass(AbsoluteDate date)` Get the mass.
`double`	`getMu()` Get the central attraction coefficient μ.
`List<ParameterDriver>`	`getParametersDrivers()` Get the parameters driver for propagation model.
`double`	`getReferenceRadius()` Get the reference radius of the central body attraction model.
`KeplerianOrbit`	`propagateOrbit(AbsoluteDate date)` Extrapolate an orbit up to a specific target date.
`void`	`resetInitialState(SpacecraftState state)` Reset the propagator initial state.
`void`	`resetInitialState(SpacecraftState state, PropagationType stateType)` Reset the propagator initial state.
`protected void`	`resetIntermediateState(SpacecraftState state, boolean forward)` Reset an intermediate state.

Methods inherited from class org.orekit.propagation.analytical.AbstractAnalyticalPropagator
acceptStep, addEventDetector, basicPropagate, clearEventsDetectors, getEphemerisGenerator, getEventsDetectors, getPvProvider, propagate

Methods inherited from class org.orekit.propagation.AbstractPropagator
addAdditionalStateProvider, getAdditionalStateProviders, getAttitudeProvider, getFrame, getHarvester, getInitialState, getManagedAdditionalStates, getMultiplexer, getPVCoordinates, getStartDate, initializePropagation, isAdditionalStateManaged, propagate, setAttitudeProvider, setStartDate, setupMatricesComputation, stateChanged, updateAdditionalStates, updateUnmanagedStates

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.Propagator
clearStepHandlers, getDefaultLaw, setStepHandler, setStepHandler

- Field Detail
  - M2_NAME
```
public static final String M2_NAME
```
    Parameter name for M2 coefficient.
    
    See Also:
    
    Constant Field Values
  - M2
```
public static final double M2
```
    Default value for M2 coefficient.
    
    See Also:
    
    Constant Field Values
- Constructor Detail
  - BrouwerLyddanePropagator
```
public BrouwerLyddanePropagator(Orbit initialOrbit,
                                UnnormalizedSphericalHarmonicsProvider provider,
                                double M2)
```
    Build a propagator from orbit and potential provider.
    Mass and attitude provider are set to unspecified non-null arbitrary values.
    
    Using this constructor, an initial osculating orbit is considered.
    
    Parameters:
    
    initialOrbit - initial orbit
    
    provider - for un-normalized zonal coefficients
    
    M2 - value of empirical drag coefficient in rad/s². If equal to M2 drag is not computed
    
    See Also:
    
    BrouwerLyddanePropagator(Orbit, AttitudeProvider, UnnormalizedSphericalHarmonicsProvider, double), BrouwerLyddanePropagator(Orbit, UnnormalizedSphericalHarmonicsProvider, PropagationType, double)
  - BrouwerLyddanePropagator
```
public BrouwerLyddanePropagator(Orbit initialOrbit,
                                AttitudeProvider attitude,
                                double mass,
                                UnnormalizedSphericalHarmonicsProvider provider,
                                UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics,
                                double M2)
```
    Private helper constructor.
    Using this constructor, an initial osculating orbit is considered.
    
    Parameters:
    
    initialOrbit - initial orbit
    
    attitude - attitude provider
    
    mass - spacecraft mass
    
    provider - for un-normalized zonal coefficients
    
    harmonics - provider.onDate(initialOrbit.getDate())
    
    M2 - value of empirical drag coefficient in rad/s². If equal to M2 drag is not computed
    
    See Also:
    
    BrouwerLyddanePropagator(Orbit, AttitudeProvider, double, UnnormalizedSphericalHarmonicsProvider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics, PropagationType, double)
  - BrouwerLyddanePropagator
```
public BrouwerLyddanePropagator(Orbit initialOrbit,
                                double referenceRadius,
                                double mu,
                                double c20,
                                double c30,
                                double c40,
                                double c50,
                                double M2)
```
    Build a propagator from orbit 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.
    
    Parameters:
    
    initialOrbit - initial orbit
    
    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)
    
    M2 - value of empirical drag coefficient in rad/s². If equal to M2 drag is not computed
    
    See Also:
    
    Constants, BrouwerLyddanePropagator(Orbit, AttitudeProvider, double, double, double, double, double, double, double, double)
  - BrouwerLyddanePropagator
```
public BrouwerLyddanePropagator(Orbit initialOrbit,
                                double mass,
                                UnnormalizedSphericalHarmonicsProvider provider,
                                double M2)
```
    Build a propagator from orbit, mass and potential provider.
    Attitude law is set to an unspecified non-null arbitrary value.
    
    Using this constructor, an initial osculating orbit is considered.
    
    Parameters:
    
    initialOrbit - initial orbit
    
    mass - spacecraft mass
    
    provider - for un-normalized zonal coefficients
    
    M2 - value of empirical drag coefficient in rad/s². If equal to M2 drag is not computed
    
    See Also:
    
    BrouwerLyddanePropagator(Orbit, AttitudeProvider, double, UnnormalizedSphericalHarmonicsProvider, double)
  - BrouwerLyddanePropagator
```
public BrouwerLyddanePropagator(Orbit initialOrbit,
                                double mass,
                                double referenceRadius,
                                double mu,
                                double c20,
                                double c30,
                                double c40,
                                double c50,
                                double M2)
```
    Build a propagator from orbit, 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.
    
    Parameters:
    
    initialOrbit - initial orbit
    
    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)
    
    M2 - value of empirical drag coefficient in rad/s². If equal to M2 drag is not computed
    
    See Also:
    
    BrouwerLyddanePropagator(Orbit, AttitudeProvider, double, double, double, double, double, double, double, double)
  - BrouwerLyddanePropagator
```
public BrouwerLyddanePropagator(Orbit initialOrbit,
                                AttitudeProvider attitudeProv,
                                UnnormalizedSphericalHarmonicsProvider provider,
                                double M2)
```
    Build a propagator from orbit, attitude provider and potential provider.
    Mass is set to an unspecified non-null arbitrary value.
    
    Using this constructor, an initial osculating orbit is considered.
    
    Parameters:
    
    initialOrbit - initial orbit
    
    attitudeProv - attitude provider
    
    provider - for un-normalized zonal coefficients
    
    M2 - value of empirical drag coefficient in rad/s². If equal to M2 drag is not computed
  - BrouwerLyddanePropagator
```
public BrouwerLyddanePropagator(Orbit initialOrbit,
                                AttitudeProvider attitudeProv,
                                double referenceRadius,
                                double mu,
                                double c20,
                                double c30,
                                double c40,
                                double c50,
                                double M2)
```
    Build a propagator from orbit, 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.
    
    Parameters:
    
    initialOrbit - initial orbit
    
    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)
    
    M2 - value of empirical drag coefficient in rad/s². If equal to M2 drag is not computed
  - BrouwerLyddanePropagator
```
public BrouwerLyddanePropagator(Orbit initialOrbit,
                                AttitudeProvider attitudeProv,
                                double mass,
                                UnnormalizedSphericalHarmonicsProvider provider,
                                double M2)
```
    Build a propagator from orbit, attitude provider, mass and potential provider.
    Using this constructor, an initial osculating orbit is considered.
    
    Parameters:
    
    initialOrbit - initial orbit
    
    attitudeProv - attitude provider
    
    mass - spacecraft mass
    
    provider - for un-normalized zonal coefficients
    
    M2 - value of empirical drag coefficient in rad/s². If equal to M2 drag is not computed
    
    See Also:
    
    BrouwerLyddanePropagator(Orbit, AttitudeProvider, double, UnnormalizedSphericalHarmonicsProvider, PropagationType, double)
  - BrouwerLyddanePropagator
```
public BrouwerLyddanePropagator(Orbit initialOrbit,
                                AttitudeProvider attitudeProv,
                                double mass,
                                double referenceRadius,
                                double mu,
                                double c20,
                                double c30,
                                double c40,
                                double c50,
                                double M2)
```
    Build a propagator from orbit, 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.
    
    Parameters:
    
    initialOrbit - initial orbit
    
    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)
    
    M2 - value of empirical drag coefficient in rad/s². If equal to M2 drag is not computed
    
    See Also:
    
    BrouwerLyddanePropagator(Orbit, AttitudeProvider, double, double, double, double, double, double, double, PropagationType, double)
  - BrouwerLyddanePropagator
```
public BrouwerLyddanePropagator(Orbit initialOrbit,
                                UnnormalizedSphericalHarmonicsProvider provider,
                                PropagationType initialType,
                                double M2)
```
    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 Brouwer-Lyddane orbit or an osculating one.
    
    Parameters:
    
    initialOrbit - initial orbit
    
    provider - for un-normalized zonal coefficients
    
    initialType - initial orbit type (mean Brouwer-Lyddane orbit or osculating orbit)
    
    M2 - value of empirical drag coefficient in rad/s². If equal to M2 drag is not computed
  - BrouwerLyddanePropagator
```
public BrouwerLyddanePropagator(Orbit initialOrbit,
                                AttitudeProvider attitudeProv,
                                double mass,
                                UnnormalizedSphericalHarmonicsProvider provider,
                                PropagationType initialType,
                                double M2)
```
    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 Brouwer-Lyddane orbit or an osculating one.
    
    Parameters:
    
    initialOrbit - initial orbit
    
    attitudeProv - attitude provider
    
    mass - spacecraft mass
    
    provider - for un-normalized zonal coefficients
    
    initialType - initial orbit type (mean Brouwer-Lyddane orbit or osculating orbit)
    
    M2 - value of empirical drag coefficient in rad/s². If equal to M2 drag is not computed
  - BrouwerLyddanePropagator
```
public BrouwerLyddanePropagator(Orbit initialOrbit,
                                AttitudeProvider attitude,
                                double mass,
                                UnnormalizedSphericalHarmonicsProvider provider,
                                UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics,
                                PropagationType initialType,
                                double M2)
```
    Private helper constructor.
    Using this constructor, it is possible to define the initial orbit as a mean Brouwer-Lyddane orbit or an osculating one.
    
    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 Brouwer-Lyddane orbit or osculating orbit)
    
    M2 - value of empirical drag coefficient in rad/s². If equal to M2 drag is not computed
  - BrouwerLyddanePropagator
```
public BrouwerLyddanePropagator(Orbit initialOrbit,
                                AttitudeProvider attitudeProv,
                                double mass,
                                double referenceRadius,
                                double mu,
                                double c20,
                                double c30,
                                double c40,
                                double c50,
                                PropagationType initialType,
                                double M2)
```
    Build a propagator from orbit, 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 Brouwer-Lyddane orbit or an osculating one.
    
    Parameters:
    
    initialOrbit - initial orbit
    
    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)
    
    initialType - initial orbit type (mean Brouwer-Lyddane orbit or osculating orbit)
    
    M2 - value of empirical drag coefficient in rad/s². If equal to M2 drag is not computed
- Method Detail
  - resetInitialState
```
public void resetInitialState(SpacecraftState state)
```
    Reset the propagator initial state.
    The new initial state to consider must be defined with an osculating orbit.
    
    Specified by:
    
    resetInitialState in interface Propagator
    
    Overrides:
    
    resetInitialState in class AbstractPropagator
    
    Parameters:
    
    state - new initial state to consider
    
    See Also:
    
    resetInitialState(SpacecraftState, PropagationType)
  - resetInitialState
```
public void resetInitialState(SpacecraftState state,
                              PropagationType stateType)
```
    Reset the propagator initial state.
    
    Parameters:
    
    state - new initial state to consider
    
    stateType - mean Brouwer-Lyddane orbit or osculating orbit
  - resetIntermediateState
```
protected void resetIntermediateState(SpacecraftState state,
                                      boolean forward)
```
    Reset an intermediate state.
    
    Specified by:
    
    resetIntermediateState in class AbstractAnalyticalPropagator
    
    Parameters:
    
    state - new intermediate state to consider
    
    forward - if true, the intermediate state is valid for propagations after itself
  - propagateOrbit
```
public KeplerianOrbit propagateOrbit(AbsoluteDate date)
```
    Extrapolate an orbit up to a specific target date.
    
    Specified by:
    
    propagateOrbit in class AbstractAnalyticalPropagator
    
    Parameters:
    
    date - target date for the orbit
    
    Returns:
    
    extrapolated parameters
  - getM2
```
public double getM2()
```
    Get the value of the M2 drag parameter.
    
    Returns:
    
    the value of the M2 drag parameter
  - getMu
```
public double getMu()
```
    Get the central attraction coefficient μ.
    
    Returns:
    
    mu central attraction coefficient (m³/s²)
  - getCk0
```
public double[] getCk0()
```
    Get the un-normalized zonal coefficients.
    
    Returns:
    
    the un-normalized zonal coefficients
  - getReferenceRadius
```
public double getReferenceRadius()
```
    Get the reference radius of the central body attraction model.
    
    Returns:
    
    the reference radius in meters
  - getParametersDrivers
```
public List<ParameterDriver> getParametersDrivers()
```
    Get the parameters driver for propagation model.
    
    Returns:
    
    drivers for propagation model
  - createHarvester
```
protected AbstractMatricesHarvester createHarvester(String stmName,
                                                    RealMatrix initialStm,
                                                    DoubleArrayDictionary initialJacobianColumns)
```
    Create the harvester suitable for propagator.
    
    Overrides:
    
    createHarvester in class AbstractPropagator
    
    Parameters:
    
    stmName - State Transition Matrix state name
    
    initialStm - initial State Transition Matrix ∂Y/∂Y₀, if null (which is the most frequent case), assumed to be 6x6 identity
    
    initialJacobianColumns - initial columns of the Jacobians matrix with respect to parameters, if null or if some selected parameters are missing from the dictionary, the corresponding initial column is assumed to be 0
    
    Returns:
    
    harvester to retrieve computed matrices during and after propagation
  - getJacobiansColumnsNames
```
protected List<String> getJacobiansColumnsNames()
```
    Get the names of the parameters in the matrix returned by MatricesHarvester.getParametersJacobian(org.orekit.propagation.SpacecraftState).
    
    Overrides:
    
    getJacobiansColumnsNames in class AbstractAnalyticalPropagator
    
    Returns:
    
    names of the parameters (i.e. columns) of the Jacobian matrix
  - getMass
```
protected double getMass(AbsoluteDate date)
```
    Get the mass.
    
    Specified by:
    
    getMass in class AbstractAnalyticalPropagator
    
    Parameters:
    
    date - target date for the orbit
    
    Returns:
    
    mass mass

Class BrouwerLyddanePropagator

Field Summary

Fields inherited from interface org.orekit.propagation.Propagator

Constructor Summary

Method Summary

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

Methods inherited from class org.orekit.propagation.AbstractPropagator

Methods inherited from class java.lang.Object

Methods inherited from interface org.orekit.propagation.Propagator

Field Detail

M2_NAME

M2

Constructor Detail

BrouwerLyddanePropagator

BrouwerLyddanePropagator

BrouwerLyddanePropagator

BrouwerLyddanePropagator

BrouwerLyddanePropagator

BrouwerLyddanePropagator

BrouwerLyddanePropagator

BrouwerLyddanePropagator

BrouwerLyddanePropagator

BrouwerLyddanePropagator

BrouwerLyddanePropagator

BrouwerLyddanePropagator

BrouwerLyddanePropagator

Method Detail

resetInitialState

resetInitialState

resetIntermediateState

propagateOrbit

getM2

getMu

getCk0

getReferenceRadius

getParametersDrivers

createHarvester

getJacobiansColumnsNames

getMass