Class DSSTJ2SquaredClosedForm
- java.lang.Object
-
- org.orekit.propagation.semianalytical.dsst.forces.DSSTJ2SquaredClosedForm
-
- All Implemented Interfaces:
EventDetectorsProvider
,DSSTForceModel
,ParameterDriversProvider
public class DSSTJ2SquaredClosedForm extends Object implements DSSTForceModel
Second order J2-squared force model.The force model implements a closed-form of the J2-squared perturbation. The full realization of the model is based on a gaussian quadrature. Even if it is very accurate, a gaussian quadrature is usually time consuming. A closed-form is less accurate than a gaussian quadrature, but faster.
- Since:
- 12.0
- Author:
- Bryan Cazabonne
-
-
Field Summary
-
Fields inherited from interface org.orekit.propagation.events.EventDetectorsProvider
DATATION_ACCURACY
-
-
Constructor Summary
Constructors Constructor Description DSSTJ2SquaredClosedForm(J2SquaredModel j2SquaredModel, UnnormalizedSphericalHarmonicsProvider provider)
Constructor.
-
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.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 attitudeProvider)
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
-
Methods inherited from interface org.orekit.propagation.semianalytical.dsst.forces.DSSTForceModel
extractParameters, extractParameters, getEventDetectors, getFieldEventDetectors, init, init
-
Methods inherited from interface org.orekit.propagation.events.EventDetectorsProvider
getEventDetectors, getFieldEventDetectors
-
Methods inherited from interface org.orekit.utils.ParameterDriversProvider
getNbParametersDriversValue, getParameterDriver, getParameters, getParameters, getParameters, getParameters, getParametersAllValues, getParametersAllValues, isSupported
-
-
-
-
Constructor Detail
-
DSSTJ2SquaredClosedForm
public DSSTJ2SquaredClosedForm(J2SquaredModel j2SquaredModel, UnnormalizedSphericalHarmonicsProvider provider)
Constructor.- Parameters:
j2SquaredModel
- model for second order termsprovider
- gravity field to use
-
-
Method Detail
-
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
-
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
-
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)
-
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)
-
getParametersDrivers
public List<ParameterDriver> getParametersDrivers()
Get the drivers for parameters..- Specified by:
getParametersDrivers
in interfaceParameterDriversProvider
- Returns:
- drivers for parameters
-
registerAttitudeProvider
public void registerAttitudeProvider(AttitudeProvider attitudeProvider)
Register an attitude provider.Register an attitude provider that can be used by the force model.
.- Specified by:
registerAttitudeProvider
in interfaceDSSTForceModel
- Parameters:
attitudeProvider
- theAttitudeProvider
-
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
-
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
-
-