org.orekit.propagation.analytical
Class J2SecularPropagator

java.lang.Object
  org.orekit.propagation.AbstractPropagator
      org.orekit.propagation.analytical.J2SecularPropagator

All Implemented Interfaces:

Serializable, Propagator, PVCoordinatesProvider

public class J2SecularPropagator
extends AbstractPropagator

J2 secular propagator.

This propagator is an analytical propagator taking into account only mean secular effects of J2 zonal harmonic.

Since:

3.2

Version:

$Id: J2SecularPropagator.java 17582 2017-05-10 12:58:16Z bignon $

Author:

Emmanuel Bignon

See Also:

Serialized Form

Field Summary

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

J2SecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, Frame frameIn)
Constructor without attitude provider and mass provider.

J2SecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, Frame frameIn, AttitudeProvider attitudeProvider)
Constructor without mass provider.

J2SecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, Frame frameIn, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents)
Constructor without mass provider.

J2SecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, Frame frameIn, AttitudeProvider attitudeProvForces, AttitudeProvider attitudeProvEvents, MassProvider massProvider)
Generic constructor.

J2SecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, Frame frameIn, AttitudeProvider attitudeProvider, MassProvider massProvider)
Generic constructor.

J2SecularPropagator(Orbit initialOrbit, double referenceRadiusIn, double muIn, double c20In, Frame frameIn, MassProvider massProvider)
Constructor without attitude provider.

Method Summary

Orbit	propagateOrbit(AbsoluteDate date) Extrapolate an orbit up to a specific target date.
void	resetInitialState(SpacecraftState state) Reset the propagator initial state.

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

Constructor Detail

J2SecularPropagator

public J2SecularPropagator(Orbit initialOrbit,
                           double referenceRadiusIn,
                           double muIn,
                           double c20In,
                           Frame frameIn)
                    throws OrekitException

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)

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

Throws:

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

J2SecularPropagator

public J2SecularPropagator(Orbit initialOrbit,
                           double referenceRadiusIn,
                           double muIn,
                           double c20In,
                           Frame frameIn,
                           MassProvider massProvider)
                    throws OrekitException

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)

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

massProvider - mass provider

Throws:

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

J2SecularPropagator

public J2SecularPropagator(Orbit initialOrbit,
                           double referenceRadiusIn,
                           double muIn,
                           double c20In,
                           Frame frameIn,
                           AttitudeProvider attitudeProvider)
                    throws OrekitException

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)

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

attitudeProvider - attitude provider

Throws:

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

J2SecularPropagator

public J2SecularPropagator(Orbit initialOrbit,
                           double referenceRadiusIn,
                           double muIn,
                           double c20In,
                           Frame frameIn,
                           AttitudeProvider attitudeProvForces,
                           AttitudeProvider attitudeProvEvents)
                    throws OrekitException

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)

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

attitudeProvForces - attitude provider for force computation

attitudeProvEvents - attitude provider for events computation

Throws:

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

J2SecularPropagator

public J2SecularPropagator(Orbit initialOrbit,
                           double referenceRadiusIn,
                           double muIn,
                           double c20In,
                           Frame frameIn,
                           AttitudeProvider attitudeProvider,
                           MassProvider massProvider)
                    throws OrekitException

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)

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

attitudeProvider - attitude provider

massProvider - mass provider

Throws:

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

J2SecularPropagator

public J2SecularPropagator(Orbit initialOrbit,
                           double referenceRadiusIn,
                           double muIn,
                           double c20In,
                           Frame frameIn,
                           AttitudeProvider attitudeProvForces,
                           AttitudeProvider attitudeProvEvents,
                           MassProvider massProvider)
                    throws OrekitException

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)

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

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

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

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