org.orekit.propagation.semianalytical.dsst.forces

Class AbstractGaussianContribution

java.lang.Object

org.orekit.propagation.semianalytical.dsst.forces.AbstractGaussianContribution

All Implemented Interfaces:

EventDetectorsProvider, DSSTForceModel, ParameterDriversProvider

Direct Known Subclasses:

DSSTAtmosphericDrag, DSSTSolarRadiationPressure

public abstract class AbstractGaussianContribution
extends Object
implements DSSTForceModel

Common handling of DSSTForceModel methods for Gaussian contributions to DSST propagation.

This abstract class allows to provide easily a subset of DSSTForceModel methods for specific Gaussian contributions.

This class implements the notion of numerical averaging of the DSST theory. Numerical averaging is mainly used for non-conservative disturbing forces such as atmospheric drag and solar radiation pressure.

Gaussian contributions can be expressed as: da_i/dt = δa_i/δv . q
where:

• a_i are the six equinoctial elements
• v is the velocity vector
• q is the perturbing acceleration due to the considered force

The averaging process and other considerations lead to integrate this contribution over the true longitude L possibly taking into account some limits.

To create a numerically averaged contribution, one needs only to provide a ForceModel and to implement in the derived class the methods: getLLimits(SpacecraftState, AuxiliaryElements) and getParametersDriversWithoutMu().

Author:

Pascal Parraud, Bryan Cazabonne (field translation)

Nested Class Summary

Nested Classes

Modifier and Type	Class and Description
protected class	AbstractGaussianContribution.FieldFourierCjSjCoefficients<T extends org.hipparchus.CalculusFieldElement<T>> Compute the Cij and the Sij coefficients with field elements.
protected static class	AbstractGaussianContribution.FieldGaussianShortPeriodicCoefficients<T extends org.hipparchus.CalculusFieldElement<T>> This class handles the short periodic coefficients described in Danielson 2.5.3-26.
protected class	AbstractGaussianContribution.FieldIntegrableFunction<T extends org.hipparchus.CalculusFieldElement<T>> Internal class for numerical quadrature.
protected static class	AbstractGaussianContribution.FieldSlot<T extends org.hipparchus.CalculusFieldElement<T>> Coefficients valid for one time slot.
protected static class	AbstractGaussianContribution.FieldUijVijCoefficients<T extends org.hipparchus.CalculusFieldElement<T>> The Uij and Vij coefficients described by equations 2.5.3-(21) and 2.5.3-(22) from Danielson.
protected class	AbstractGaussianContribution.FourierCjSjCoefficients Compute the Cij and the Sij coefficients.
protected static class	AbstractGaussianContribution.GaussianShortPeriodicCoefficients This class handles the short periodic coefficients described in Danielson 2.5.3-26.
protected static class	AbstractGaussianContribution.GaussQuadrature Class used to integrate a function of the orbital elements using the Gaussian quadrature rule to get the acceleration.
protected class	AbstractGaussianContribution.IntegrableFunction Internal class for numerical quadrature.
protected static class	AbstractGaussianContribution.Slot Coefficients valid for one time slot.
protected static class	AbstractGaussianContribution.UijVijCoefficients The Uij and Vij coefficients described by equations 2.5.3-(21) and 2.5.3-(22) from Danielson.

Field Summary

Fields inherited from interface org.orekit.propagation.events.EventDetectorsProvider

DATATION_ACCURACY

Constructor Summary

Constructors

Modifier	Constructor and Description
protected	AbstractGaussianContribution(String coefficientsKeyPrefix, double threshold, ForceModel contribution, double mu) Build a new instance.

Method Summary

Modifier and Type	Method and Description
protected abstract <T extends org.hipparchus.CalculusFieldElement<T>> T[]	getLLimits(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements) Compute the limits in L, the true longitude, for integration.
protected abstract double[]	getLLimits(SpacecraftState state, AuxiliaryElements auxiliaryElements) Compute the limits in L, the true longitude, for integration.
protected <T extends org.hipparchus.CalculusFieldElement<T>> T[]	getMeanElementRate(FieldSpacecraftState<T> state, AbstractGaussianContribution.GaussQuadrature gauss, T low, T high, FieldAbstractGaussianContributionContext<T> context, T[] parameters) Computes the mean equinoctial elements rates dai / dt.
<T extends org.hipparchus.CalculusFieldElement<T>> T[]	getMeanElementRate(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements, T[] parameters) Computes the mean equinoctial elements rates dai / dt.
protected double[]	getMeanElementRate(SpacecraftState state, AbstractGaussianContribution.GaussQuadrature gauss, double low, double high, AbstractGaussianContributionContext context, double[] 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.
protected abstract List<ParameterDriver>	getParametersDriversWithoutMu() Get the drivers for force model parameters except the one for the central attraction coefficient.
<T extends org.hipparchus.CalculusFieldElement<T>> void	init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target) Initialize the force model at the start of propagation.
void	init(SpacecraftState initialState, AbsoluteDate target) Initialize the force model at the start of propagation.
List<ShortPeriodTerms>	initializeShortPeriodTerms(AuxiliaryElements auxiliaryElements, PropagationType type, double[] parameters) Performs initialization prior to propagation for the current force model.
<T extends org.hipparchus.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 org.hipparchus.CalculusFieldElement<T>> void	updateShortPeriodTerms(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

Methods inherited from interface org.orekit.utils.ParameterDriversProvider

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

Methods inherited from interface org.orekit.propagation.events.EventDetectorsProvider

getEventDetectors, getFieldEventDetectors

Constructor Detail

AbstractGaussianContribution

protected AbstractGaussianContribution(String coefficientsKeyPrefix,
                                       double threshold,
                                       ForceModel contribution,
                                       double mu)

Build a new instance.

Parameters:

coefficientsKeyPrefix - prefix for coefficients keys

threshold - tolerance for the choice of the Gauss quadrature order

contribution - the ForceModel to be numerically averaged

mu - central attraction coefficient

Method Detail

init

public void init(SpacecraftState initialState,
                 AbsoluteDate target)

Initialize the force model at the start of propagation.

The default implementation of this method does nothing.

Specified by:

init in interface DSSTForceModel

Parameters:

initialState - spacecraft state at the start of propagation.

target - date of propagation. Not equal to initialState.getDate().

init

public <T extends org.hipparchus.CalculusFieldElement<T>> void init(FieldSpacecraftState<T> initialState,
                                                                    FieldAbsoluteDate<T> target)

Initialize the force model at the start of propagation.

The default implementation of this method does nothing.

Specified by:

init in interface DSSTForceModel

Type Parameters:

T - type of the elements

Parameters:

initialState - spacecraft state at the start of propagation.

target - date of propagation. Not equal to initialState.getDate().

getParametersDrivers

public List<ParameterDriver> getParametersDrivers()

Get the drivers for parameters.

Specified by:

getParametersDrivers in interface ParameterDriversProvider

Returns:

drivers for parameters

getParametersDriversWithoutMu

protected abstract List<ParameterDriver> getParametersDriversWithoutMu()

Get the drivers for force model parameters except the one for the central attraction coefficient.

The driver for central attraction coefficient is automatically added at the last element of the ParameterDriver array into getParametersDrivers() method.

Returns:

drivers for force model parameters

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 interface DSSTForceModel

Parameters:

auxiliaryElements - auxiliary elements related to the current orbit

type - type of the elements used during the propagation

parameters - values of the force model parameters for specific date (1 value only per parameter driver) obtained for example by calling ParameterDriversProvider.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 org.hipparchus.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 interface DSSTForceModel

Type Parameters:

T - type of the elements

Parameters:

auxiliaryElements - auxiliary elements related to the current orbit

type - type of the elements used during the propagation

parameters - values of the force model parameters for specific date (1 value only per parameter driver) obtained for example by calling ParameterDriversProvider.getParameters(AbsoluteDate) on force model or AbstractGradientConverter.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)

getMeanElementRate

public double[] getMeanElementRate(SpacecraftState state,
                                   AuxiliaryElements auxiliaryElements,
                                   double[] parameters)

Computes the mean equinoctial elements rates da_i / dt.

Specified by:

getMeanElementRate in interface DSSTForceModel

Parameters:

state - current state information: date, kinematics, attitude

auxiliaryElements - auxiliary elements related to the current orbit

parameters - values of the force model parameters at state date (only 1 span for each parameter driver) obtained for example by calling ParameterDriversProvider.getParameters(AbsoluteDate) on force model.

Returns:

the mean element rates dai/dt

getMeanElementRate

public <T extends org.hipparchus.CalculusFieldElement<T>> T[] getMeanElementRate(FieldSpacecraftState<T> state,
                                                                                 FieldAuxiliaryElements<T> auxiliaryElements,
                                                                                 T[] parameters)

Computes the mean equinoctial elements rates da_i / dt.

Specified by:

getMeanElementRate in interface DSSTForceModel

Type Parameters:

T - type of the elements

Parameters:

state - current state information: date, kinematics, attitude

auxiliaryElements - auxiliary elements related to the current orbit

parameters - values of the force model parameters at state date (only 1 span for each parameter driver) obtained for example by calling ParameterDriversProvider.getParameters(Field, FieldAbsoluteDate) on force model or AbstractGradientConverter.getParametersAtStateDate(FieldSpacecraftState, ParameterDriversProvider) on gradient converter.

Returns:

the mean element rates dai/dt

getLLimits

protected abstract double[] getLLimits(SpacecraftState state,
                                       AuxiliaryElements auxiliaryElements)

Compute the limits in L, the true longitude, for integration.

Parameters:

state - current state information: date, kinematics, attitude

auxiliaryElements - auxiliary elements related to the current orbit

Returns:

the integration limits in L

getLLimits

protected abstract <T extends org.hipparchus.CalculusFieldElement<T>> T[] getLLimits(FieldSpacecraftState<T> state,
                                                                                     FieldAuxiliaryElements<T> auxiliaryElements)

Compute the limits in L, the true longitude, for integration.

Type Parameters:

T - type of the elements

Parameters:

state - current state information: date, kinematics, attitude

auxiliaryElements - auxiliary elements related to the current orbit

Returns:

the integration limits in L

getMeanElementRate

protected double[] getMeanElementRate(SpacecraftState state,
                                      AbstractGaussianContribution.GaussQuadrature gauss,
                                      double low,
                                      double high,
                                      AbstractGaussianContributionContext context,
                                      double[] parameters)

Computes the mean equinoctial elements rates da_i / dt.

Parameters:

state - current state

gauss - Gauss quadrature

low - lower bound of the integral interval

high - upper bound of the integral interval

context - container for attributes

parameters - values of the force model parameters at state date (1 values for each parameters)

Returns:

the mean element rates

getMeanElementRate

protected <T extends org.hipparchus.CalculusFieldElement<T>> T[] getMeanElementRate(FieldSpacecraftState<T> state,
                                                                                    AbstractGaussianContribution.GaussQuadrature gauss,
                                                                                    T low,
                                                                                    T high,
                                                                                    FieldAbstractGaussianContributionContext<T> context,
                                                                                    T[] parameters)

Computes the mean equinoctial elements rates da_i / dt.

Type Parameters:

T - type of the elements

Parameters:

state - current state

gauss - Gauss quadrature

low - lower bound of the integral interval

high - upper bound of the integral interval

context - container for attributes

parameters - values of the force model parameters(1 values for each parameters)

Returns:

the mean element rates

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 interface DSSTForceModel

Parameters:

provider - the AttitudeProvider

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 to DSSTForceModel.initializeShortPeriodTerms(AuxiliaryElements, PropagationType, double[]).

Specified by:

updateShortPeriodTerms in interface DSSTForceModel

Parameters:

parameters - values of the force model parameters (all span values for each parameters) obtained for example by calling ParameterDriversProvider.getParametersAllValues() on force model. The extract parameter method DSSTForceModel.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 org.hipparchus.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 to DSSTForceModel.initializeShortPeriodTerms(AuxiliaryElements, PropagationType, double[]).

Specified by:

updateShortPeriodTerms in interface DSSTForceModel

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 calling ParameterDriversProvider.getParametersAllValues(Field) on force model or AbstractGradientConverter.getParameters(FieldSpacecraftState, ParameterDriversProvider) on gradient converter. The extract parameter method DSSTForceModel.extractParameters(CalculusFieldElement[], FieldAbsoluteDate) is called in the method to select the right parameter.

meanStates - mean states information: date, kinematics, attitude