Class DSSTNewtonianAttraction
- java.lang.Object
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- org.orekit.propagation.semianalytical.dsst.forces.DSSTNewtonianAttraction
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- All Implemented Interfaces:
EventDetectorsProvider
,DSSTForceModel
,ParameterDriversProvider
public class DSSTNewtonianAttraction extends Object implements DSSTForceModel
Force model for Newtonian central body attraction for theDSST propagator
.- Since:
- 10.0
- Author:
- Bryan Cazabonne, Luc Maisonobe
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Field Summary
Fields Modifier and Type Field Description static String
CENTRAL_ATTRACTION_COEFFICIENT
Name of the single parameter of this model: the central attraction coefficient.-
Fields inherited from interface org.orekit.propagation.events.EventDetectorsProvider
DATATION_ACCURACY
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Constructor Summary
Constructors Constructor Description DSSTNewtonianAttraction(double mu)
Simple constructor.
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Method Summary
All Methods Instance Methods Concrete Methods Modifier and Type Method Description <T extends CalculusFieldElement<T>>
T[]getMeanElementRate(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters)
Computes the mean equinoctial elements rates dai / dt.double[]
getMeanElementRate(SpacecraftState state, AuxiliaryElements auxiliaryElements, double[] parameters)
Computes the mean equinoctial elements rates dai / dt.double
getMu(AbsoluteDate date)
Get the central attraction coefficient μ at specific date.List<ParameterDriver>
getParametersDrivers()
Get the drivers for parameters.List<ShortPeriodTerms>
initializeShortPeriodTerms(AuxiliaryElements auxiliaryElements, PropagationType type, double[] parameters)
Performs initialization prior to propagation for the current force model.<T extends CalculusFieldElement<T>>
List<FieldShortPeriodTerms<T>>initializeShortPeriodTerms(FieldAuxiliaryElements<T> auxiliaryElements, PropagationType type, T[] parameters)
Performs initialization prior to propagation for the current force model.void
registerAttitudeProvider(AttitudeProvider provider)
Register an attitude provider.void
updateShortPeriodTerms(double[] parameters, SpacecraftState... meanStates)
Update the short period terms.<T extends CalculusFieldElement<T>>
voidupdateShortPeriodTerms(T[] parameters, FieldSpacecraftState<T>... meanStates)
Update the short period terms.-
Methods inherited from class java.lang.Object
clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait
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Methods inherited from interface org.orekit.propagation.semianalytical.dsst.forces.DSSTForceModel
extractParameters, extractParameters, getEventDetectors, getFieldEventDetectors, init, init
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Methods inherited from interface org.orekit.propagation.events.EventDetectorsProvider
getEventDetectors, getFieldEventDetectors
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Methods inherited from interface org.orekit.utils.ParameterDriversProvider
getNbParametersDriversValue, getParameterDriver, getParameters, getParameters, getParameters, getParameters, getParametersAllValues, getParametersAllValues, isSupported
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Field Detail
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CENTRAL_ATTRACTION_COEFFICIENT
public static final String CENTRAL_ATTRACTION_COEFFICIENT
Name of the single parameter of this model: the central attraction coefficient.- See Also:
- Constant Field Values
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Method Detail
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getMu
public double getMu(AbsoluteDate date)
Get the central attraction coefficient μ at specific date.- Parameters:
date
- date at which mu wants to be known- Returns:
- mu central attraction coefficient (m³/s²)
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initializeShortPeriodTerms
public List<ShortPeriodTerms> initializeShortPeriodTerms(AuxiliaryElements auxiliaryElements, PropagationType type, double[] parameters)
Performs initialization prior to propagation for the current force model.This method aims at being called at the very beginning of a propagation.
- Specified by:
initializeShortPeriodTerms
in interfaceDSSTForceModel
- Parameters:
auxiliaryElements
- auxiliary elements related to the current orbittype
- type of the elements used during the propagationparameters
- values of the force model parameters for specific date (1 value only per parameter driver) obtained for example by callingParameterDriversProvider.getParameters(AbsoluteDate)
on force model.- Returns:
- a list of objects that will hold short period terms (the objects are also retained by the force model, which will update them during propagation)
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initializeShortPeriodTerms
public <T extends CalculusFieldElement<T>> List<FieldShortPeriodTerms<T>> initializeShortPeriodTerms(FieldAuxiliaryElements<T> auxiliaryElements, PropagationType type, T[] parameters)
Performs initialization prior to propagation for the current force model.This method aims at being called at the very beginning of a propagation.
- Specified by:
initializeShortPeriodTerms
in interfaceDSSTForceModel
- Type Parameters:
T
- type of the elements- Parameters:
auxiliaryElements
- auxiliary elements related to the current orbittype
- type of the elements used during the propagationparameters
- values of the force model parameters for specific date (1 value only per parameter driver) obtained for example by callingParameterDriversProvider.getParameters(AbsoluteDate)
on force model orAbstractGradientConverter.getParametersAtStateDate(FieldSpacecraftState, ParameterDriversProvider)
on gradient converter.- Returns:
- a list of objects that will hold short period terms (the objects are also retained by the force model, which will update them during propagation)
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getMeanElementRate
public double[] getMeanElementRate(SpacecraftState state, AuxiliaryElements auxiliaryElements, double[] parameters)
Computes the mean equinoctial elements rates dai / dt.- Specified by:
getMeanElementRate
in interfaceDSSTForceModel
- Parameters:
state
- current state information: date, kinematics, attitudeauxiliaryElements
- auxiliary elements related to the current orbitparameters
- values of the force model parameters at state date (only 1 span for each parameter driver) obtained for example by callingParameterDriversProvider.getParameters(AbsoluteDate)
on force model.- Returns:
- the mean element rates dai/dt
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getMeanElementRate
public <T extends CalculusFieldElement<T>> T[] getMeanElementRate(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters)
Computes the mean equinoctial elements rates dai / dt.- Specified by:
getMeanElementRate
in interfaceDSSTForceModel
- Type Parameters:
T
- type of the elements- Parameters:
state
- current state information: date, kinematics, attitudeauxiliaryElements
- auxiliary elements related to the current orbitparameters
- values of the force model parameters at state date (only 1 span for each parameter driver) obtained for example by callingParameterDriversProvider.getParameters(Field, FieldAbsoluteDate)
on force model orAbstractGradientConverter.getParametersAtStateDate(FieldSpacecraftState, ParameterDriversProvider)
on gradient converter.- Returns:
- the mean element rates dai/dt
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registerAttitudeProvider
public void registerAttitudeProvider(AttitudeProvider provider)
Register an attitude provider.Register an attitude provider that can be used by the force model.
- Specified by:
registerAttitudeProvider
in interfaceDSSTForceModel
- Parameters:
provider
- theAttitudeProvider
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updateShortPeriodTerms
public void updateShortPeriodTerms(double[] parameters, SpacecraftState... meanStates)
Update the short period terms.The
short period terms
that will be updated are the ones that were returned during the call toDSSTForceModel.initializeShortPeriodTerms(AuxiliaryElements, PropagationType, double[])
.- Specified by:
updateShortPeriodTerms
in interfaceDSSTForceModel
- Parameters:
parameters
- values of the force model parameters (all span values for each parameters) obtained for example by callingParameterDriversProvider.getParametersAllValues()
on force model. The extract parameter methodDSSTForceModel.extractParameters(double[], AbsoluteDate)
is called in the method to select the right parameter corresponding to the mean state date.meanStates
- mean states information: date, kinematics, attitude
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updateShortPeriodTerms
public <T extends CalculusFieldElement<T>> void updateShortPeriodTerms(T[] parameters, FieldSpacecraftState<T>... meanStates)
Update the short period terms.The
short period terms
that will be updated are the ones that were returned during the call toDSSTForceModel.initializeShortPeriodTerms(AuxiliaryElements, PropagationType, double[])
.- Specified by:
updateShortPeriodTerms
in interfaceDSSTForceModel
- Type Parameters:
T
- type of the elements- Parameters:
parameters
- values of the force model parameters (all span values for each parameters) obtained for example by callingParameterDriversProvider.getParametersAllValues(Field)
on force model orAbstractGradientConverter.getParameters(FieldSpacecraftState, ParameterDriversProvider)
on gradient converter. The extract parameter methodDSSTForceModel.extractParameters(CalculusFieldElement[], FieldAbsoluteDate)
is called in the method to select the right parameter.meanStates
- mean states information: date, kinematics, attitude
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getParametersDrivers
public List<ParameterDriver> getParametersDrivers()
Get the drivers for parameters.- Specified by:
getParametersDrivers
in interfaceParameterDriversProvider
- Returns:
- drivers for parameters
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