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>
- Type Parameters:
T- type of the field elements
- 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
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Field Summary
Fields inherited from interface org.orekit.propagation.FieldPropagator
DEFAULT_MASS -
Constructor Summary
ConstructorsConstructorDescriptionDefault 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 TypeMethodDescriptionGet the computed satellite's east longitude.getFrame()Get the frame in which the orbit is propagated.Get the computed satellite's geocentric latitude.Get the Intelsat's 11 elements used by the propagator.protected TgetMass(FieldAbsoluteDate<T> date) Get the mass.Get the computed satellite's orbit.Get the drivers for parameters.propagateInEcef(FieldAbsoluteDate<T> date) Converts the Intelsat's 11 elements into Position/Velocity coordinates in ECEF.propagateOrbit(FieldAbsoluteDate<T> date, T[] parameters) Propagate an orbit up to a specific target date.voidresetInitialState(FieldSpacecraftState<T> state) Reset the propagator initial state.protected voidresetIntermediateState(FieldSpacecraftState<T> state, boolean forward) Reset an intermediate state.Methods inherited from class org.orekit.propagation.analytical.FieldAbstractAnalyticalPropagator
acceptStep, addEventDetector, basicPropagate, clearEventsDetectors, getEphemerisGenerator, getEventDetectors, propagateMethods inherited from class org.orekit.propagation.FieldAbstractPropagator
addAdditionalDataProvider, getAdditionalDataProviders, getAttitudeProvider, getField, getInitialState, getManagedAdditionalData, getMultiplexer, getStartDate, initializeAdditionalData, initializePropagation, isAdditionalDataManaged, propagate, removeAdditionalDataProvider, setAttitudeProvider, setStartDate, stateChanged, updateAdditionalData, updateUnmanagedDataMethods inherited from class java.lang.Object
clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, waitMethods inherited from interface org.orekit.propagation.FieldPropagator
clearStepHandlers, getPosition, getPVCoordinates, getVelocity, setStepHandler, setStepHandlerMethods inherited from interface org.orekit.utils.ParameterDriversProvider
getNbParametersDriversValue, getParameterDriver, getParameters, getParameters, getParameters, getParameters, getParametersAllValues, getParametersAllValues, isSupported
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Constructor Details
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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 theDEFAULT_MASS.
The inertial frame is set by default to theTOD framein the default data context.
The ECEF frame is set by default to theCIO/2010-based ITRF simple EOPin the default data context.- Parameters:
elements- Intelsat's 11 elements
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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 theDEFAULT_MASS.
- Parameters:
elements- Intelsat's 11 elementsinertialFrame- inertial frame for the output orbitecefFrame- ECEF frame related to the Intelsat's 11 elements
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FieldIntelsatElevenElementsPropagator
public FieldIntelsatElevenElementsPropagator(FieldIntelsatElevenElements<T> elements, Frame inertialFrame, Frame ecefFrame, AttitudeProvider attitudeProvider, T mass) Constructor.- Parameters:
elements- Intelsat's 11 elementsinertialFrame- inertial frame for the output orbitecefFrame- ECEF frame related to the Intelsat's 11 elementsattitudeProvider- attitude providermass- spacecraft mass
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Method Details
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propagateInEcef
Converts the Intelsat's 11 elements into Position/Velocity coordinates in ECEF.- Parameters:
date- computation epoch- Returns:
- Position/Velocity coordinates in ECEF
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resetInitialState
Reset the propagator initial state..- Specified by:
resetInitialStatein interfaceFieldPropagator<T extends CalculusFieldElement<T>>- Overrides:
resetInitialStatein classFieldAbstractPropagator<T extends CalculusFieldElement<T>>- Parameters:
state- new initial state to consider
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getMass
Get the mass..- Specified by:
getMassin classFieldAbstractAnalyticalPropagator<T extends CalculusFieldElement<T>>- Parameters:
date- target date for the orbit- Returns:
- mass mass
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resetIntermediateState
Reset an intermediate state..- Specified by:
resetIntermediateStatein classFieldAbstractAnalyticalPropagator<T extends CalculusFieldElement<T>>- Parameters:
state- new intermediate state to considerforward- if true, the intermediate state is valid for propagations after itself
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propagateOrbit
Propagate an orbit up to a specific target date..- Specified by:
propagateOrbitin classFieldAbstractAnalyticalPropagator<T extends CalculusFieldElement<T>>- Parameters:
date- target date for the orbitparameters- model parameters- Returns:
- propagated orbit
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getEastLongitudeDegrees
Get the computed satellite's east longitude.- Returns:
- the satellite's east longitude in degrees
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getGeocentricLatitudeDegrees
Get the computed satellite's geocentric latitude.- Returns:
- the satellite's geocentric latitude in degrees
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getOrbitRadius
Get the computed satellite's orbit.- Returns:
- satellite's orbit radius in meters
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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:
getFramein interfaceFieldPropagator<T extends CalculusFieldElement<T>>- Overrides:
getFramein classFieldAbstractPropagator<T extends CalculusFieldElement<T>>- Returns:
- frame in which the orbit is propagated
- See Also:
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getParametersDrivers
Get the drivers for parameters..- Returns:
- drivers for parameters
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getIntelsatElevenElements
Get the Intelsat's 11 elements used by the propagator.- Returns:
- the Intelsat's 11 elements used by the propagator
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