Class EcksteinHechlerPropagator
- java.lang.Object
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- org.orekit.propagation.AbstractPropagator
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- org.orekit.propagation.analytical.AbstractAnalyticalPropagator
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- org.orekit.propagation.analytical.EcksteinHechlerPropagator
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- All Implemented Interfaces:
Propagator
,PVCoordinatesProvider
public class EcksteinHechlerPropagator extends AbstractAnalyticalPropagator
This class propagates aSpacecraftState
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).
Note that before version 7.0, there was a large inconsistency in the generated orbits, and it was fixed as of version 7.0 of Orekit, with a visible side effect. The problems is that if the circular parameters produced by the Eckstein-Hechler model are used to build an orbit considered to be osculating, the velocity deduced from this orbit was inconsistent with the position evolution! The reason is that the model includes non-Keplerian effects but it does not include a corresponding circular/Cartesian conversion. As a consequence, all subsequent computation involving velocity were wrong. This includes attitude modes like yaw compensation and Doppler effect. As this effect was considered serious enough and as accurate velocities were considered important, the propagator now generates
Cartesian orbits
which are built in a special way to ensure consistency throughout propagation. A side effect is that if circular parameters are rebuilt by user from these propagated Cartesian orbit, the circular parameters will generally not match the initial orbit (differences in semi-major axis can exceed 120 m). The position however will match to sub-micrometer level, and this position will be identical to the positions that were generated by previous versions (in other words, the internals of the models have not been changed, only the output parameters have been changed). The correctness of the initialization has been assessed and is good, as it allows the subsequent orbit to remain close to a numerical reference orbit.If users need a more definitive initialization of an Eckstein-Hechler propagator, they should consider using a
propagator converter
to initialize their Eckstein-Hechler propagator using a complete sample instead of just a single initial orbit.- Author:
- Guylaine Prat
- See Also:
Orbit
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Field Summary
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Fields inherited from interface org.orekit.propagation.Propagator
DEFAULT_MASS
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Constructor Summary
Constructors Constructor Description EcksteinHechlerPropagator(Orbit initialOrbit, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double c60)
Build a propagator from orbit and potential.EcksteinHechlerPropagator(Orbit initialOrbit, double mass, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double c60)
Build a propagator from orbit, mass and potential.EcksteinHechlerPropagator(Orbit initialOrbit, double mass, UnnormalizedSphericalHarmonicsProvider provider)
Build a propagator from orbit, mass and potential provider.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, 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.EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mass, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double c60, PropagationType initialType, double epsilon, int maxIterations)
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 attitude, double mass, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics, PropagationType initialType)
Private helper constructor.EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mass, UnnormalizedSphericalHarmonicsProvider provider, PropagationType initialType)
Build a propagator from orbit, attitude provider, mass and potential provider.EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, UnnormalizedSphericalHarmonicsProvider provider)
Build a propagator from orbit, attitude provider and potential provider.EcksteinHechlerPropagator(Orbit initialOrbit, UnnormalizedSphericalHarmonicsProvider provider)
Build a propagator from orbit and potential provider.EcksteinHechlerPropagator(Orbit initialOrbit, UnnormalizedSphericalHarmonicsProvider provider, PropagationType initialType)
Build a propagator from orbit and potential provider.
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Method Summary
All Methods Static Methods Instance Methods Concrete Methods Modifier and Type Method Description static CircularOrbit
computeMeanOrbit(Orbit 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 CircularOrbit
computeMeanOrbit(Orbit osculating, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics)
Conversion from osculating to mean orbit.static CircularOrbit
computeMeanOrbit(Orbit osculating, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics, double epsilon, int maxIterations)
Conversion from osculating to mean orbit.protected AbstractMatricesHarvester
createHarvester(String stmName, RealMatrix initialStm, DoubleArrayDictionary initialJacobianColumns)
Create the harvester suitable for propagator.double[]
getCk0()
Get the un-normalized zonal coefficients.protected double
getMass(AbsoluteDate date)
Get the mass.double
getMu()
Get the central attraction coefficient μ.double
getReferenceRadius()
Get the reference radius of the central body attraction model.CartesianOrbit
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.void
resetInitialState(SpacecraftState state, PropagationType stateType, double epsilon, int maxIterations)
Reset the propagator initial state.protected void
resetIntermediateState(SpacecraftState state, boolean forward)
Reset an intermediate state.protected void
resetIntermediateState(SpacecraftState state, boolean forward, double epsilon, int maxIterations)
Reset an intermediate state.-
Methods inherited from class org.orekit.propagation.analytical.AbstractAnalyticalPropagator
acceptStep, addEventDetector, basicPropagate, clearEventsDetectors, getEphemerisGenerator, getEventsDetectors, getJacobiansColumnsNames, getPvProvider, propagate
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Methods inherited from class org.orekit.propagation.AbstractPropagator
addAdditionalStateProvider, getAdditionalStateProviders, getAttitudeProvider, getFrame, getHarvester, getInitialState, getManagedAdditionalStates, getMultiplexer, getStartDate, initializeAdditionalStates, initializePropagation, isAdditionalStateManaged, propagate, setAttitudeProvider, setStartDate, setupMatricesComputation, stateChanged, updateAdditionalStates, updateUnmanagedStates
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Methods inherited from class java.lang.Object
clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait
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Methods inherited from interface org.orekit.propagation.Propagator
clearStepHandlers, getPosition, getPVCoordinates, setStepHandler, setStepHandler
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Constructor Detail
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EcksteinHechlerPropagator
public EcksteinHechlerPropagator(Orbit initialOrbit, UnnormalizedSphericalHarmonicsProvider provider)
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 orbitprovider
- for un-normalized zonal coefficients- See Also:
EcksteinHechlerPropagator(Orbit, AttitudeProvider, UnnormalizedSphericalHarmonicsProvider)
,EcksteinHechlerPropagator(Orbit, UnnormalizedSphericalHarmonicsProvider, PropagationType)
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EcksteinHechlerPropagator
public EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitude, double mass, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics)
Private helper constructor.Using this constructor, an initial osculating orbit is considered.
- Parameters:
initialOrbit
- initial orbitattitude
- attitude providermass
- spacecraft massprovider
- for un-normalized zonal coefficientsharmonics
-provider.onDate(initialOrbit.getDate())
- See Also:
EcksteinHechlerPropagator(Orbit, AttitudeProvider, double, UnnormalizedSphericalHarmonicsProvider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics, PropagationType)
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EcksteinHechlerPropagator
public EcksteinHechlerPropagator(Orbit initialOrbit, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double c60)
Build a propagator from orbit and potential.Mass and attitude provider are set to unspecified non-null arbitrary values.
The Cn,0 coefficients are the denormalized zonal coefficients, they are related to both the normalized coefficients Cn,0 and the Jn one as follows:
Cn,0 = [(2-δ0,m)(2n+1)(n-m)!/(n+m)!]½ Cn,0
Cn,0 = -Jn
Using this constructor, an initial osculating orbit is considered.
- Parameters:
initialOrbit
- initial orbitreferenceRadius
- 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
,EcksteinHechlerPropagator(Orbit, AttitudeProvider, double, double, double, double, double, double, double, double)
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EcksteinHechlerPropagator
public EcksteinHechlerPropagator(Orbit initialOrbit, double mass, UnnormalizedSphericalHarmonicsProvider provider)
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 orbitmass
- spacecraft massprovider
- for un-normalized zonal coefficients- See Also:
EcksteinHechlerPropagator(Orbit, AttitudeProvider, double, UnnormalizedSphericalHarmonicsProvider)
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EcksteinHechlerPropagator
public EcksteinHechlerPropagator(Orbit initialOrbit, double mass, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double c60)
Build a propagator from orbit, mass and potential.Attitude law is set to an unspecified non-null arbitrary value.
The Cn,0 coefficients are the denormalized zonal coefficients, they are related to both the normalized coefficients Cn,0 and the Jn one as follows:
Cn,0 = [(2-δ0,m)(2n+1)(n-m)!/(n+m)!]½ Cn,0
Cn,0 = -Jn
Using this constructor, an initial osculating orbit is considered.
- Parameters:
initialOrbit
- initial orbitmass
- spacecraft massreferenceRadius
- 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:
EcksteinHechlerPropagator(Orbit, AttitudeProvider, double, double, double, double, double, double, double, double)
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EcksteinHechlerPropagator
public EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, UnnormalizedSphericalHarmonicsProvider provider)
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 orbitattitudeProv
- attitude providerprovider
- for un-normalized zonal coefficients
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EcksteinHechlerPropagator
public 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.Mass is set to an unspecified non-null arbitrary value.
The Cn,0 coefficients are the denormalized zonal coefficients, they are related to both the normalized coefficients Cn,0 and the Jn one as follows:
Cn,0 = [(2-δ0,m)(2n+1)(n-m)!/(n+m)!]½ Cn,0
Cn,0 = -Jn
Using this constructor, an initial osculating orbit is considered.
- Parameters:
initialOrbit
- initial orbitattitudeProv
- attitude providerreferenceRadius
- 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)
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EcksteinHechlerPropagator
public EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mass, UnnormalizedSphericalHarmonicsProvider provider)
Build a propagator from orbit, attitude provider, mass and potential provider.Using this constructor, an initial osculating orbit is considered.
- Parameters:
initialOrbit
- initial orbitattitudeProv
- attitude providermass
- spacecraft massprovider
- for un-normalized zonal coefficients- See Also:
EcksteinHechlerPropagator(Orbit, AttitudeProvider, double, UnnormalizedSphericalHarmonicsProvider, PropagationType)
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EcksteinHechlerPropagator
public 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.The Cn,0 coefficients are the denormalized zonal coefficients, they are related to both the normalized coefficients Cn,0 and the Jn one as follows:
Cn,0 = [(2-δ0,m)(2n+1)(n-m)!/(n+m)!]½ Cn,0
Cn,0 = -Jn
Using this constructor, an initial osculating orbit is considered.
- Parameters:
initialOrbit
- initial orbitattitudeProv
- attitude providermass
- spacecraft massreferenceRadius
- 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:
EcksteinHechlerPropagator(Orbit, AttitudeProvider, double, double, double, double, double, double, double, double, PropagationType)
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EcksteinHechlerPropagator
public EcksteinHechlerPropagator(Orbit 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.
- Parameters:
initialOrbit
- initial orbitprovider
- for un-normalized zonal coefficientsinitialType
- initial orbit type (mean Eckstein-Hechler orbit or osculating orbit)- Since:
- 10.2
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EcksteinHechlerPropagator
public EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double 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.
- Parameters:
initialOrbit
- initial orbitattitudeProv
- attitude providermass
- spacecraft massprovider
- for un-normalized zonal coefficientsinitialType
- initial orbit type (mean Eckstein-Hechler orbit or osculating orbit)- Since:
- 10.2
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EcksteinHechlerPropagator
public EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitude, double 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.
- Parameters:
initialOrbit
- initial orbitattitude
- attitude providermass
- spacecraft massprovider
- for un-normalized zonal coefficientsharmonics
-provider.onDate(initialOrbit.getDate())
initialType
- initial orbit type (mean Eckstein-Hechler orbit or osculating orbit)- Since:
- 10.2
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EcksteinHechlerPropagator
public 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.The Cn,0 coefficients are the denormalized zonal coefficients, they are related to both the normalized coefficients Cn,0 and the Jn one as follows:
Cn,0 = [(2-δ0,m)(2n+1)(n-m)!/(n+m)!]½ Cn,0
Cn,0 = -Jn
Using this constructor, it is possible to define the initial orbit as a mean Eckstein-Hechler orbit or an osculating one.
- Parameters:
initialOrbit
- initial orbitattitudeProv
- attitude providermass
- spacecraft massreferenceRadius
- 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
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EcksteinHechlerPropagator
public EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mass, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double c60, PropagationType initialType, double epsilon, int maxIterations)
Build a propagator from orbit, attitude provider, mass and potential.The Cn,0 coefficients are the denormalized zonal coefficients, they are related to both the normalized coefficients Cn,0 and the Jn one as follows:
Cn,0 = [(2-δ0,m)(2n+1)(n-m)!/(n+m)!]½ Cn,0
Cn,0 = -Jn
Using this constructor, it is possible to define the initial orbit as a mean Eckstein-Hechler orbit or an osculating one.
- Parameters:
initialOrbit
- initial orbitattitudeProv
- attitude providermass
- spacecraft massreferenceRadius
- 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 conversionmaxIterations
- maximum iterations for mean parameters conversioninitialType
- initial orbit type (mean Eckstein-Hechler orbit or osculating orbit)- Since:
- 11.2
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Method Detail
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computeMeanOrbit
public static CircularOrbit computeMeanOrbit(Orbit 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.
- Parameters:
osculating
- osculating orbit to convertprovider
- for un-normalized zonal coefficientsharmonics
-provider.onDate(osculating.getDate())
- Returns:
- mean orbit in a Eckstein-Hechler sense
- Since:
- 11.2
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computeMeanOrbit
public static CircularOrbit computeMeanOrbit(Orbit 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.
- Parameters:
osculating
- osculating orbit to convertprovider
- for un-normalized zonal coefficientsharmonics
-provider.onDate(osculating.getDate())
epsilon
- convergence threshold for mean parameters conversionmaxIterations
- maximum iterations for mean parameters conversion- Returns:
- mean orbit in a Eckstein-Hechler sense
- Since:
- 11.2
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computeMeanOrbit
public static CircularOrbit computeMeanOrbit(Orbit 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.
- Parameters:
osculating
- osculating orbit to convertreferenceRadius
- 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 conversionmaxIterations
- maximum iterations for mean parameters conversion- Returns:
- mean orbit in a Eckstein-Hechler sense
- Since:
- 11.2
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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 interfacePropagator
- Overrides:
resetInitialState
in classAbstractPropagator
- Parameters:
state
- new initial state to consider- See Also:
resetInitialState(SpacecraftState, PropagationType)
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resetInitialState
public void resetInitialState(SpacecraftState state, PropagationType stateType)
Reset the propagator initial state.- Parameters:
state
- new initial state to considerstateType
- mean Eckstein-Hechler orbit or osculating orbit- Since:
- 10.2
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resetInitialState
public void resetInitialState(SpacecraftState state, PropagationType stateType, double epsilon, int maxIterations)
Reset the propagator initial state.- Parameters:
state
- new initial state to considerstateType
- mean Eckstein-Hechler orbit or osculating orbitepsilon
- convergence threshold for mean parameters conversionmaxIterations
- maximum iterations for mean parameters conversion- Since:
- 11.2
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resetIntermediateState
protected void resetIntermediateState(SpacecraftState state, boolean forward)
Reset an intermediate state.- Specified by:
resetIntermediateState
in classAbstractAnalyticalPropagator
- Parameters:
state
- new intermediate state to considerforward
- if true, the intermediate state is valid for propagations after itself
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resetIntermediateState
protected void resetIntermediateState(SpacecraftState state, boolean forward, double epsilon, int maxIterations)
Reset an intermediate state.- Parameters:
state
- new intermediate state to considerforward
- if true, the intermediate state is valid for propagations after itselfepsilon
- convergence threshold for mean parameters conversionmaxIterations
- maximum iterations for mean parameters conversion- Since:
- 11.2
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propagateOrbit
public CartesianOrbit propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date.- Specified by:
propagateOrbit
in classAbstractAnalyticalPropagator
- Parameters:
date
- target date for the orbit- Returns:
- extrapolated parameters
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getMu
public double getMu()
Get the central attraction coefficient μ.- Returns:
- mu central attraction coefficient (m³/s²)
- Since:
- 11.1
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getCk0
public double[] getCk0()
Get the un-normalized zonal coefficients.- Returns:
- the un-normalized zonal coefficients
- Since:
- 11.1
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getReferenceRadius
public double getReferenceRadius()
Get the reference radius of the central body attraction model.- Returns:
- the reference radius in meters
- Since:
- 11.1
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createHarvester
protected AbstractMatricesHarvester createHarvester(String stmName, RealMatrix initialStm, DoubleArrayDictionary initialJacobianColumns)
Create the harvester suitable for propagator.- Overrides:
createHarvester
in classAbstractPropagator
- Parameters:
stmName
- State Transition Matrix state nameinitialStm
- initial State Transition Matrix ∂Y/∂Y₀, if null (which is the most frequent case), assumed to be 6x6 identityinitialJacobianColumns
- 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
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getMass
protected double getMass(AbsoluteDate date)
Get the mass.- Specified by:
getMass
in classAbstractAnalyticalPropagator
- Parameters:
date
- target date for the orbit- Returns:
- mass mass
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