fr.cnes.sirius.patrius.propagation.analytical

Class LyddaneSecularPropagator

java.lang.Object

fr.cnes.sirius.patrius.propagation.AbstractPropagator

fr.cnes.sirius.patrius.propagation.analytical.AbstractLyddanePropagator

fr.cnes.sirius.patrius.propagation.analytical.LyddaneSecularPropagator

All Implemented Interfaces:

PVCoordinatesProvider, MeanOsculatingElementsProvider, Propagator, SpacecraftStateProvider, Serializable

public class LyddaneSecularPropagator
extends AbstractLyddanePropagator

Lyddane secular propagator.

Lyddane propagator is an analytical propagator taking into account only mean secular effects of J2 to J5 zonal harmonics.

This propagator is valid for orbits with eccentricity lower than 0.9 and inclination not close to critical inclinations

Since:

3.2

Version:

$Id: LyddaneSecularPropagator.java 17582 2017-05-10 12:58:16Z bignon $

Author:

Emmanuel Bignon

See Also:

Serialized Form

Nested Class Summary

Nested classes/interfaces inherited from class fr.cnes.sirius.patrius.propagation.analytical.AbstractLyddanePropagator

AbstractLyddanePropagator.LyddaneParametersType

Field Summary

Fields inherited from class fr.cnes.sirius.patrius.propagation.analytical.AbstractLyddanePropagator

secularOrbitIn

Fields inherited from class fr.cnes.sirius.patrius.propagation.AbstractPropagator

MASS

Fields inherited from interface fr.cnes.sirius.patrius.propagation.Propagator

EPHEMERIS_GENERATION_MODE, MASTER_MODE, SLAVE_MODE

Constructor Summary

Constructors

Constructor and Description
LyddaneSecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn) Constructor without attitude provider and mass provider.
LyddaneSecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, AttitudeProvider attitudeProvider) Constructor without mass provider.
LyddaneSecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents) Constructor without mass provider.
LyddaneSecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents, MassProvider massProvider) Generic constructor.
LyddaneSecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, AttitudeProvider attitudeProvider, MassProvider massProvider) Generic constructor.
LyddaneSecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, MassProvider massProvider) Constructor without attitude provider.

Method Summary

Modifier and Type	Method and Description
Orbit	mean2osc(Orbit orbit) Convert provided mean orbit into osculating elements.
Orbit	osc2mean(Orbit orbit) Convert provided osculating orbit into mean elements.
Orbit	propagateMeanOrbit(AbsoluteDate date) Propagate mean orbit until provided date.

Methods inherited from class fr.cnes.sirius.patrius.propagation.analytical.AbstractLyddanePropagator

computeSecular, convertFrame, propagateOrbit, propagateOrbit, resetInitialState, setThreshold, updateSecularOrbit

Methods inherited from class fr.cnes.sirius.patrius.propagation.AbstractPropagator

acceptStep, addAdditionalStateProvider, addAdditionalStateProvider, addEventDetector, basicPropagate, clearEventsDetectors, getAttitudeProvider, getAttitudeProviderEvents, getAttitudeProviderForces, getEventsDetectors, getFrame, getGeneratedEphemeris, getInitialState, getMode, getPVCoordinates, getPvProvider, getSpacecraftState, manageStateFrame, propagate, propagate, setAttitudeProvider, setAttitudeProviderEvents, setAttitudeProviderForces, setEphemerisMode, setMasterMode, setMasterMode, setOrbitFrame, setSlaveMode, setStartDate

Methods inherited from class java.lang.Object

clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait

Constructor Detail

LyddaneSecularPropagator

public LyddaneSecularPropagator(Orbit initialOrbit,
                                double referenceRadiusIn,
                                double muIn,
                                double c20In,
                                double c30In,
                                double c40In,
                                double c50In,
                                Frame frameIn,
                                ParametersType parametersTypeIn)
                         throws PatriusException

Constructor without attitude provider and mass provider.

Parameters:

initialOrbit - initial orbit

referenceRadiusIn - reference radius of the central body attraction model (m)

muIn - central attraction coefficient (m³/s²)

c20In - un-normalized 2nd zonal coefficient (about -1.08e-3 for Earth)

c30In - un-normalized 3rd zonal coefficient (about +2.53e-6 for Earth)

c40In - un-normalized 4th zonal coefficient (about +1.62e-6 for Earth)

c50In - un-normalized 5th zonal coefficient (about +2.28e-7 for Earth)

frameIn - Inertial or quasi-inertial frame in which the model is supposed valid, the Z axis of the frame being the polar axis of the body

parametersTypeIn - initial orbit parameters type (mean or osculating)

Throws:

PatriusException - thrown if failed to build initial state or coefficients frame is not inertial

LyddaneSecularPropagator

public LyddaneSecularPropagator(Orbit initialOrbit,
                                double referenceRadiusIn,
                                double muIn,
                                double c20In,
                                double c30In,
                                double c40In,
                                double c50In,
                                Frame frameIn,
                                ParametersType parametersTypeIn,
                                MassProvider massProvider)
                         throws PatriusException

Constructor without attitude provider.

Parameters:

initialOrbit - initial orbit

referenceRadiusIn - reference radius of the central body attraction model (m)

muIn - central attraction coefficient (m³/s²)

c20In - un-normalized 2nd zonal coefficient (about -1.08e-3 for Earth)

c30In - un-normalized 3rd zonal coefficient (about +2.53e-6 for Earth)

c40In - un-normalized 4th zonal coefficient (about +1.62e-6 for Earth)

c50In - un-normalized 5th zonal coefficient (about +2.28e-7 for Earth)

frameIn - Inertial or quasi-inertial frame in which the model is supposed valid, the Z axis of the frame being the polar axis of the body

parametersTypeIn - initial orbit parameters type (mean or osculating)

massProvider - mass provider

Throws:

PatriusException - thrown if failed to build initial state or coefficients frame is not inertial

LyddaneSecularPropagator

public LyddaneSecularPropagator(Orbit initialOrbit,
                                double referenceRadiusIn,
                                double muIn,
                                double c20In,
                                double c30In,
                                double c40In,
                                double c50In,
                                Frame frameIn,
                                ParametersType parametersTypeIn,
                                AttitudeProvider attitudeProvider)
                         throws PatriusException

Constructor without mass provider.

Parameters:

initialOrbit - initial orbit

referenceRadiusIn - reference radius of the central body attraction model (m)

muIn - central attraction coefficient (m³/s²)

c20In - un-normalized 2nd zonal coefficient (about -1.08e-3 for Earth)

c30In - un-normalized 3rd zonal coefficient (about +2.53e-6 for Earth)

c40In - un-normalized 4th zonal coefficient (about +1.62e-6 for Earth)

c50In - un-normalized 5th zonal coefficient (about +2.28e-7 for Earth)

frameIn - Inertial or quasi-inertial frame in which the model is supposed valid, the Z axis of the frame being the polar axis of the body

parametersTypeIn - initial orbit parameters type (mean or osculating)

attitudeProvider - attitude provider

Throws:

PatriusException - thrown if failed to build initial state or coefficients frame is not inertial

LyddaneSecularPropagator

public LyddaneSecularPropagator(Orbit initialOrbit,
                                double referenceRadiusIn,
                                double muIn,
                                double c20In,
                                double c30In,
                                double c40In,
                                double c50In,
                                Frame frameIn,
                                ParametersType parametersTypeIn,
                                AttitudeProvider attitudeProvForces,
                                AttitudeProvider attitudeProvEvents)
                         throws PatriusException

Constructor without mass provider.

Parameters:

initialOrbit - initial orbit

referenceRadiusIn - reference radius of the central body attraction model (m)

muIn - central attraction coefficient (m³/s²)

c20In - un-normalized 2nd zonal coefficient (about -1.08e-3 for Earth)

c30In - un-normalized 3rd zonal coefficient (about +2.53e-6 for Earth)

c40In - un-normalized 4th zonal coefficient (about +1.62e-6 for Earth)

c50In - un-normalized 5th zonal coefficient (about +2.28e-7 for Earth)

frameIn - Inertial or quasi-inertial frame in which the model is supposed valid, the Z axis of the frame being the polar axis of the body

parametersTypeIn - initial orbit parameters type (mean or osculating)

attitudeProvForces - attitude provider for force computation

attitudeProvEvents - attitude provider for events computation

Throws:

PatriusException - thrown if failed to build initial state or coefficients frame is not inertial

LyddaneSecularPropagator

public LyddaneSecularPropagator(Orbit initialOrbit,
                                double referenceRadiusIn,
                                double muIn,
                                double c20In,
                                double c30In,
                                double c40In,
                                double c50In,
                                Frame frameIn,
                                ParametersType parametersTypeIn,
                                AttitudeProvider attitudeProvider,
                                MassProvider massProvider)
                         throws PatriusException

Generic constructor.

Parameters:

initialOrbit - initial orbit

referenceRadiusIn - reference radius of the central body attraction model (m)

muIn - central attraction coefficient (m³/s²)

c20In - un-normalized 2nd zonal coefficient (about -1.08e-3 for Earth)

c30In - un-normalized 3rd zonal coefficient (about +2.53e-6 for Earth)

c40In - un-normalized 4th zonal coefficient (about +1.62e-6 for Earth)

c50In - un-normalized 5th zonal coefficient (about +2.28e-7 for Earth)

frameIn - Inertial or quasi-inertial frame in which the model is supposed valid, the Z axis of the frame being the polar axis of the body

parametersTypeIn - initial orbit parameters type (mean or osculating)

attitudeProvider - attitude provider

massProvider - mass provider

Throws:

PatriusException - thrown if failed to build initial state or coefficients frame is not inertial

LyddaneSecularPropagator

public LyddaneSecularPropagator(Orbit initialOrbit,
                                double referenceRadiusIn,
                                double muIn,
                                double c20In,
                                double c30In,
                                double c40In,
                                double c50In,
                                Frame frameIn,
                                ParametersType parametersTypeIn,
                                AttitudeProvider attitudeProvForces,
                                AttitudeProvider attitudeProvEvents,
                                MassProvider massProvider)
                         throws PatriusException

Generic constructor.

Parameters:

initialOrbit - initial orbit

referenceRadiusIn - reference radius of the central body attraction model (m)

muIn - central attraction coefficient (m³/s²)

c20In - un-normalized 2nd zonal coefficient (about -1.08e-3 for Earth)

c30In - un-normalized 3rd zonal coefficient (about +2.53e-6 for Earth)

c40In - un-normalized 4th zonal coefficient (about +1.62e-6 for Earth)

c50In - un-normalized 5th zonal coefficient (about +2.28e-7 for Earth)

frameIn - Inertial or quasi-inertial frame in which the model is supposed valid, the Z axis of the frame being the polar axis of the body

parametersTypeIn - initial orbit parameters type (mean or osculating)

attitudeProvForces - attitude provider for force computation

attitudeProvEvents - attitude provider for events computation

massProvider - mass provider

Throws:

PatriusException - thrown if failed to build initial state or coefficients frame is not inertial

Method Detail

propagateMeanOrbit

public Orbit propagateMeanOrbit(AbsoluteDate date)
                         throws PatriusException

Propagate mean orbit until provided date.

Specified by:

propagateMeanOrbit in interface MeanOsculatingElementsProvider

Overrides:

propagateMeanOrbit in class AbstractLyddanePropagator

Parameters:

date - a date

Returns:

mean orbit at provided date

Throws:

PatriusException - thrown if computation failed

osc2mean

public Orbit osc2mean(Orbit orbit)
               throws PatriusException

Convert provided osculating orbit into mean elements.

Warning: Used algorithm often consists in an iterative algorithm with a convergence criterion. As a result convergence is not always ensured, depending on the underlying theory.

Parameters:

orbit - an orbit (osculating elements)

Returns:

mean elements of provided orbit

Throws:

PatriusException - if conversion fails

mean2osc

public Orbit mean2osc(Orbit orbit)
               throws PatriusException

Convert provided mean orbit into osculating elements.

Parameters:

orbit - an orbit (mean elements)

Returns:

osculating elements of provided orbit

Throws:

PatriusException - if conversion fails