Package org.orekit.propagation.analytical.intelsat

Class FieldIntelsatElevenElementsPropagator<T extends CalculusFieldElement<T>>

java.lang.Object

org.orekit.propagation.FieldAbstractPropagator<T>

org.orekit.propagation.analytical.FieldAbstractAnalyticalPropagator<T>

org.orekit.propagation.analytical.intelsat.FieldIntelsatElevenElementsPropagator<T>

All Implemented Interfaces:

FieldPropagator<T>, FieldPVCoordinatesProvider<T>, ParameterDriversProvider

public class FieldIntelsatElevenElementsPropagator<T extends CalculusFieldElement<T>>
extends FieldAbstractAnalyticalPropagator<T>

This class provides elements to propagate Intelsat's 11 elements.

Intelsat's 11 elements propagation is defined in ITU-R S.1525 standard.

Since:

12.1

Author:

Bryan Cazabonne

Field Summary

Fields inherited from interface org.orekit.propagation.FieldPropagator

DEFAULT_MASS

Constructor Summary

Constructors

Constructor	Description
FieldIntelsatElevenElementsPropagator(FieldIntelsatElevenElements<T> elements)	Default constructor.
FieldIntelsatElevenElementsPropagator(FieldIntelsatElevenElements<T> elements, Frame inertialFrame, Frame ecefFrame)	Constructor.
FieldIntelsatElevenElementsPropagator(FieldIntelsatElevenElements<T> elements, Frame inertialFrame, Frame ecefFrame, AttitudeProvider attitudeProvider, T mass)	Constructor.

Method Summary

Modifier and Type	Method	Description
FieldUnivariateDerivative2<T>	getEastLongitudeDegrees()	Get the computed satellite's east longitude.
Frame	getFrame()	Get the frame in which the orbit is propagated.
FieldUnivariateDerivative2<T>	getGeocentricLatitudeDegrees()	Get the computed satellite's geocentric latitude.
FieldIntelsatElevenElements<T>	getIntelsatElevenElements()	Get the Intelsat's 11 elements used by the propagator.
protected T	getMass(FieldAbsoluteDate<T> date)	Get the mass.
FieldUnivariateDerivative2<T>	getOrbitRadius()	Get the computed satellite's orbit.
List<ParameterDriver>	getParametersDrivers()	Get the drivers for parameters.
FieldPVCoordinates<T>	propagateInEcef(FieldAbsoluteDate<T> date)	Converts the Intelsat's 11 elements into Position/Velocity coordinates in ECEF.
protected FieldOrbit<T>	propagateOrbit(FieldAbsoluteDate<T> date, T[] parameters)	Extrapolate an orbit up to a specific target date.
void	resetInitialState(FieldSpacecraftState<T> state)	Reset the propagator initial state.
protected void	resetIntermediateState(FieldSpacecraftState<T> state, boolean forward)	Reset an intermediate state.

Methods inherited from class org.orekit.propagation.analytical.FieldAbstractAnalyticalPropagator

acceptStep, addEventDetector, basicPropagate, clearEventsDetectors, getEphemerisGenerator, getEventDetectors, getPvProvider, propagate

Methods inherited from class org.orekit.propagation.FieldAbstractPropagator

addAdditionalStateProvider, getAdditionalStateProviders, getAttitudeProvider, getField, getInitialState, getManagedAdditionalStates, getMultiplexer, getStartDate, initializeAdditionalStates, initializePropagation, isAdditionalStateManaged, propagate, setAttitudeProvider, setStartDate, stateChanged, updateAdditionalStates, updateUnmanagedStates

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.FieldPropagator

clearStepHandlers, getPosition, getPVCoordinates, setStepHandler, setStepHandler

Methods inherited from interface org.orekit.utils.ParameterDriversProvider

getNbParametersDriversValue, getParameterDriver, getParameters, getParameters, getParameters, getParameters, getParametersAllValues, getParametersAllValues, isSupported

Constructor Detail

FieldIntelsatElevenElementsPropagator

@DefaultDataContext
public FieldIntelsatElevenElementsPropagator(FieldIntelsatElevenElements<T> elements)

Default constructor.

This constructor uses the default data context.

The attitude provider is set by default to be aligned with the inertial frame.
The mass is set by default to the DEFAULT_MASS.
The inertial frame is set by default to the TOD frame in the default data context.
The ECEF frame is set by default to the CIO/2010-based ITRF simple EOP in the default data context.

Parameters:

elements - Intelsat's 11 elements

FieldIntelsatElevenElementsPropagator

public FieldIntelsatElevenElementsPropagator(FieldIntelsatElevenElements<T> elements,
                                             Frame inertialFrame,
                                             Frame ecefFrame)

Constructor.

The attitude provider is set by default to be aligned with the inertial frame.
The mass is set by default to the DEFAULT_MASS.

Parameters:

elements - Intelsat's 11 elements

inertialFrame - inertial frame for the output orbit

ecefFrame - ECEF frame related to the Intelsat's 11 elements

FieldIntelsatElevenElementsPropagator

public FieldIntelsatElevenElementsPropagator(FieldIntelsatElevenElements<T> elements,
                                             Frame inertialFrame,
                                             Frame ecefFrame,
                                             AttitudeProvider attitudeProvider,
                                             T mass)

Constructor.

Parameters:

elements - Intelsat's 11 elements

inertialFrame - inertial frame for the output orbit

ecefFrame - ECEF frame related to the Intelsat's 11 elements

attitudeProvider - attitude provider

mass - spacecraft mass

Method Detail

propagateInEcef

public FieldPVCoordinates<T> propagateInEcef(FieldAbsoluteDate<T> date)

Converts the Intelsat's 11 elements into Position/Velocity coordinates in ECEF.

Parameters:

date - computation epoch

Returns:

Position/Velocity coordinates in ECEF

resetInitialState

public void resetInitialState(FieldSpacecraftState<T> state)

Reset the propagator initial state..

Specified by:

resetInitialState in interface FieldPropagator<T extends CalculusFieldElement<T>>

Overrides:

resetInitialState in class FieldAbstractPropagator<T extends CalculusFieldElement<T>>

Parameters:

state - new initial state to consider

getMass

protected T getMass(FieldAbsoluteDate<T> date)

Get the mass..

Specified by:

getMass in class FieldAbstractAnalyticalPropagator<T extends CalculusFieldElement<T>>

Parameters:

date - target date for the orbit

Returns:

mass mass

resetIntermediateState

protected void resetIntermediateState(FieldSpacecraftState<T> state,
                                      boolean forward)

Reset an intermediate state..

Specified by:

resetIntermediateState in class FieldAbstractAnalyticalPropagator<T extends CalculusFieldElement<T>>

Parameters:

state - new intermediate state to consider

forward - if true, the intermediate state is valid for propagations after itself

propagateOrbit

protected FieldOrbit<T> propagateOrbit(FieldAbsoluteDate<T> date,
                                       T[] parameters)

Extrapolate an orbit up to a specific target date..

Specified by:

propagateOrbit in class FieldAbstractAnalyticalPropagator<T extends CalculusFieldElement<T>>

Parameters:

date - target date for the orbit

parameters - model parameters

Returns:

extrapolated parameters

getEastLongitudeDegrees

public FieldUnivariateDerivative2<T> getEastLongitudeDegrees()

Get the computed satellite's east longitude.

Returns:

the satellite's east longitude in degrees

getGeocentricLatitudeDegrees

public FieldUnivariateDerivative2<T> getGeocentricLatitudeDegrees()

Get the computed satellite's geocentric latitude.

Returns:

the satellite's geocentric latitude in degrees

getOrbitRadius

public FieldUnivariateDerivative2<T> getOrbitRadius()

Get the computed satellite's orbit.

Returns:

satellite's orbit radius in meters

getFrame

public Frame getFrame()

Get the frame in which the orbit is propagated.

The propagation frame is the definition frame of the initial state, so this method should be called after this state has been set, otherwise it may return null.

.

Specified by:

getFrame in interface FieldPropagator<T extends CalculusFieldElement<T>>

Overrides:

getFrame in class FieldAbstractPropagator<T extends CalculusFieldElement<T>>

Returns:

frame in which the orbit is propagated

See Also:

FieldPropagator.resetInitialState(FieldSpacecraftState)

getParametersDrivers

public List<ParameterDriver> getParametersDrivers()

Get the drivers for parameters..

Returns:

drivers for parameters

getIntelsatElevenElements

public FieldIntelsatElevenElements<T> getIntelsatElevenElements()

Get the Intelsat's 11 elements used by the propagator.

Returns:

the Intelsat's 11 elements used by the propagator