org.orekit.propagation.analytical
Class AbstractLyddanePropagator

java.lang.Object
  org.orekit.propagation.AbstractPropagator
      org.orekit.propagation.analytical.AbstractLyddanePropagator

All Implemented Interfaces:

Serializable, MeanOsculatingElementsProvider, Propagator, PVCoordinatesProvider

Direct Known Subclasses:

LyddaneLongPeriodPropagator, LyddaneSecularPropagator

public abstract class AbstractLyddanePropagator
extends AbstractPropagator
implements MeanOsculatingElementsProvider

Abstract Lyddane propagator. This class contains common algorithms to all Lyddane propagators.

Since:

3.2

Version:

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

Author:

Emmanuel Bignon

See Also:

Serialized Form

Nested Class Summary

static class

AbstractLyddanePropagator.LyddaneParametersType Lyddane parameters types.

Field Summary

protected Orbit

secularOrbitIn Secular orbit.

Fields inherited from class org.orekit.propagation.AbstractPropagator

MASS

Fields inherited from interface org.orekit.propagation.Propagator

EPHEMERIS_GENERATION_MODE, MASTER_MODE, SLAVE_MODE

Constructor Summary

protected

AbstractLyddanePropagator(Orbit secularOrbit, double referenceRadiusIn, double muIn, double c20In, double c30In, double c40In, double c50In, Frame frameIn, ParametersType parametersTypeIn, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents, MassProvider massProvider) Generic constructor.

Method Summary

protected Orbit	computeSecular(Orbit orbit, AbstractLyddanePropagator.LyddaneParametersType fromType) Compute secular orbit in body frame from provided orbit.
protected Orbit	convertFrame(Orbit orbit, Frame outputFrame) Convert provided orbit in output frame.
Orbit	propagateMeanOrbit(AbsoluteDate date) Propagate mean orbit until provided date.
Orbit	propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
protected Orbit	propagateOrbit(AbsoluteDate date, Orbit secularOrbit, Frame outputFrame, AbstractLyddanePropagator.LyddaneParametersType returnType) Propagate orbit to provided date.
void	resetInitialState(SpacecraftState state) Reset the propagator initial state.
void	setThreshold(double newThreshold) Setter for relative convergence threshold for osculating to mean algorithm.
protected void	updateSecularOrbit(Orbit secularOrbit) Update for secular Orbit.

Methods inherited from class org.orekit.propagation.AbstractPropagator

acceptStep, addAdditionalStateProvider, addAdditionalStateProvider, addEventDetector, basicPropagate, clearEventsDetectors, getAttitudeProvider, getAttitudeProviderEvents, getAttitudeProviderForces, getEventsDetectors, getFrame, getGeneratedEphemeris, getInitialState, getMode, getPVCoordinates, getPvProvider, 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

Methods inherited from interface org.orekit.propagation.MeanOsculatingElementsProvider

mean2osc, osc2mean

Field Detail

secularOrbitIn

protected Orbit secularOrbitIn

Secular orbit.

Constructor Detail

AbstractLyddanePropagator

protected AbstractLyddanePropagator(Orbit secularOrbit,
                                    double referenceRadiusIn,
                                    double muIn,
                                    double c20In,
                                    double c30In,
                                    double c40In,
                                    double c50In,
                                    Frame frameIn,
                                    ParametersType parametersTypeIn,
                                    AttitudeProvider attitudeProvForces,
                                    AttitudeProvider attitudeProvEvents,
                                    MassProvider massProvider)
                             throws OrekitException

Generic constructor.

Parameters:

secularOrbit - initial secular 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 - frame in which model coefficients are expressed (must be inertial or quasi-inertial).

parametersTypeIn - initial orbit parameters type (mean or osculating)

attitudeProvForces - attitude provider for force computation

attitudeProvEvents - attitude provider for events computation

massProvider - mass provider

Throws:

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

Method Detail

resetInitialState

public void resetInitialState(SpacecraftState state)
                       throws PropagationException

Reset the propagator initial state.

Specified by:

resetInitialState in interface Propagator

Overrides:

resetInitialState in class AbstractPropagator

Parameters:

state - new initial state to consider

Throws:

PropagationException - if initial state cannot be reset

propagateOrbit

public Orbit propagateOrbit(AbsoluteDate date)
                     throws PropagationException

Extrapolate an orbit up to a specific target date.

Specified by:

propagateOrbit in class AbstractPropagator

Parameters:

date - target date for the orbit

Returns:

extrapolated parameters

Throws:

PropagationException - if some parameters are out of bounds

propagateMeanOrbit

public Orbit propagateMeanOrbit(AbsoluteDate date)
                         throws OrekitException

Propagate mean orbit until provided date.

Specified by:

propagateMeanOrbit in interface MeanOsculatingElementsProvider

Parameters:

date - a date

Returns:

mean orbit at provided date

Throws:

OrekitException - thrown if computation failed

propagateOrbit

protected Orbit propagateOrbit(AbsoluteDate date,
                               Orbit secularOrbit,
                               Frame outputFrame,
                               AbstractLyddanePropagator.LyddaneParametersType returnType)
                        throws PropagationException

Propagate orbit to provided date.

Parameters:

date - a date

secularOrbit - a secular orbit in body frame

outputFrame - output frame

returnType - return type : SECULAR, MEAN or OSCULTATING

Returns:

propagated orbit in output frame to provided date

Throws:

PropagationException - if some parameters are out of bounds

computeSecular

protected Orbit computeSecular(Orbit orbit,
                               AbstractLyddanePropagator.LyddaneParametersType fromType)
                        throws OrekitException

Compute secular orbit in body frame from provided orbit.

An iterative algorithm is used. threshold parameter is used to check convergence of iterations.

Parameters:

orbit - an orbit

fromType - input type

Returns:

secular orbit in body frame

Throws:

OrekitException - thrown if conversion to body frame failed

setThreshold

public void setThreshold(double newThreshold)

Setter for relative convergence threshold for osculating to mean algorithm.

Parameters:

newThreshold - new relative threshold

updateSecularOrbit

protected void updateSecularOrbit(Orbit secularOrbit)
                           throws OrekitException

Update for secular Orbit.

Parameters:

secularOrbit - secular orbit

Throws:

OrekitException - thrown if conversion failed

convertFrame

protected Orbit convertFrame(Orbit orbit,
                             Frame outputFrame)
                      throws OrekitException

Convert provided orbit in output frame.

Parameters:

orbit - orbit

outputFrame - output frame

Returns:

converted orbit in output frame

Throws:

OrekitException - thrown if conversion failed