org.orekit.propagation.analytical
public class EcksteinHechlerPropagator extends AbstractAnalyticalPropagator
SpacecraftState
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).
Orbit
DEFAULT_LAW, DEFAULT_MASS, EPHEMERIS_GENERATION_MODE, MASTER_MODE, SLAVE_MODE
Constructor and Description |
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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.
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EcksteinHechlerPropagator(Orbit initialOrbit,
AttitudeProvider attitudeProv,
double mass,
double referenceRadius,
double mu,
double c20,
double c30,
double c40,
double c50,
double c60)
Build a propagator from orbit, attitude provider, mass and potential.
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EcksteinHechlerPropagator(Orbit initialOrbit,
AttitudeProvider attitudeProv,
double mass,
UnnormalizedSphericalHarmonicsProvider provider)
Build a propagator from orbit, attitude provider, mass and potential provider.
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EcksteinHechlerPropagator(Orbit initialOrbit,
AttitudeProvider attitude,
double mass,
UnnormalizedSphericalHarmonicsProvider provider,
UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics)
Private helper constructor.
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EcksteinHechlerPropagator(Orbit initialOrbit,
AttitudeProvider attitudeProv,
UnnormalizedSphericalHarmonicsProvider provider)
Build a propagator from orbit, attitude provider and potential provider.
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EcksteinHechlerPropagator(Orbit initialOrbit,
double referenceRadius,
double mu,
double c20,
double c30,
double c40,
double c50,
double c60)
Build a propagator from orbit and potential.
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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.
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EcksteinHechlerPropagator(Orbit initialOrbit,
double mass,
UnnormalizedSphericalHarmonicsProvider provider)
Build a propagator from orbit, mass and potential provider.
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EcksteinHechlerPropagator(Orbit initialOrbit,
UnnormalizedSphericalHarmonicsProvider provider)
Build a propagator from orbit and potential provider.
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Modifier and Type | Method and Description |
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protected double |
getMass(AbsoluteDate date)
Get the mass.
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Orbit |
propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date.
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void |
resetInitialState(SpacecraftState state)
Reset the propagator initial state.
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acceptStep, addEventDetector, basicPropagate, clearEventsDetectors, getEventsDetectors, getGeneratedEphemeris, getPvProvider, propagate
addAdditionalStateProvider, getAdditionalStateProviders, getAttitudeProvider, getFixedStepSize, getFrame, getInitialState, getManagedAdditionalStates, getMode, getPVCoordinates, getStartDate, getStepHandler, isAdditionalStateManaged, propagate, setAttitudeProvider, setEphemerisMode, setMasterMode, setMasterMode, setSlaveMode, setStartDate, updateAdditionalStates
public EcksteinHechlerPropagator(Orbit initialOrbit, UnnormalizedSphericalHarmonicsProvider provider) throws PropagationException, OrekitException
Mass and attitude provider are set to unspecified non-null arbitrary values.
initialOrbit
- initial orbitprovider
- for un-normalized zonal coefficientsOrekitException
- if the zonal coefficients cannot be retrievedPropagationException
- if the mean parameters cannot be computedpublic EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitude, double mass, UnnormalizedSphericalHarmonicsProvider provider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics) throws OrekitException
initialOrbit
- initial orbitattitude
- attitude providermass
- spacecraft massprovider
- for un-normalized zonal coefficientsharmonics
- provider.onDate(initialOrbit.getDate())
OrekitException
- if the zonal coefficients cannot be retrievedpublic EcksteinHechlerPropagator(Orbit initialOrbit, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double c60) throws PropagationException
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)!]½Cn,0
Cn,0 = -Jn
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)PropagationException
- if the mean parameters cannot be computedConstants
public EcksteinHechlerPropagator(Orbit initialOrbit, double mass, UnnormalizedSphericalHarmonicsProvider provider) throws PropagationException, OrekitException
Attitude law is set to an unspecified non-null arbitrary value.
initialOrbit
- initial orbitmass
- spacecraft massprovider
- for un-normalized zonal coefficientsOrekitException
- if the zonal coefficients cannot be retrievedPropagationException
- if the mean parameters cannot be computedpublic EcksteinHechlerPropagator(Orbit initialOrbit, double mass, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double c60) throws PropagationException
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)!]½Cn,0
Cn,0 = -Jn
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)PropagationException
- if the mean parameters cannot be computedpublic EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, UnnormalizedSphericalHarmonicsProvider provider) throws PropagationException, OrekitException
Mass is set to an unspecified non-null arbitrary value.
initialOrbit
- initial orbitattitudeProv
- attitude providerprovider
- for un-normalized zonal coefficientsOrekitException
- if the zonal coefficients cannot be retrievedPropagationException
- if the mean parameters cannot be computedpublic EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double c60) throws PropagationException
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)!]½Cn,0
Cn,0 = -Jn
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)PropagationException
- if the mean parameters cannot be computedpublic EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mass, UnnormalizedSphericalHarmonicsProvider provider) throws PropagationException, OrekitException
initialOrbit
- initial orbitattitudeProv
- attitude providermass
- spacecraft massprovider
- for un-normalized zonal coefficientsOrekitException
- if the zonal coefficients cannot be retrievedPropagationException
- if the mean parameters cannot be computedpublic EcksteinHechlerPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mass, double referenceRadius, double mu, double c20, double c30, double c40, double c50, double c60) throws PropagationException
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)!]½Cn,0
Cn,0 = -Jn
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)PropagationException
- if the mean parameters cannot be computedpublic void resetInitialState(SpacecraftState state) throws PropagationException
resetInitialState
in interface Propagator
resetInitialState
in class AbstractPropagator
state
- new initial state to considerPropagationException
- if initial state cannot be resetpublic Orbit propagateOrbit(AbsoluteDate date) throws PropagationException
propagateOrbit
in class AbstractAnalyticalPropagator
date
- target date for the orbitPropagationException
- if some parameters are out of boundsprotected double getMass(AbsoluteDate date)
getMass
in class AbstractAnalyticalPropagator
date
- target date for the orbitCopyright © 2002–2015 CS Syst?mes d'Information. All rights reserved.