Package org.orekit.propagation.semianalytical.dsst.forces

Class DSSTAtmosphericDrag

java.lang.Object

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

org.orekit.propagation.semianalytical.dsst.forces.DSSTAtmosphericDrag

All Implemented Interfaces:

EventDetectorsProvider, DSSTForceModel, ParameterDriversProvider

public class DSSTAtmosphericDrag
extends AbstractGaussianContribution

Atmospheric drag contribution to the DSSTPropagator.

The drag acceleration is computed through the acceleration model of DragForce.

Author:

Pascal Parraud

Nested Class Summary

Nested classes/interfaces inherited from class org.orekit.propagation.semianalytical.dsst.forces.AbstractGaussianContribution

AbstractGaussianContribution.FieldFourierCjSjCoefficients<T extends CalculusFieldElement<T>>, AbstractGaussianContribution.FieldGaussianShortPeriodicCoefficients<T extends CalculusFieldElement<T>>, AbstractGaussianContribution.FieldIntegrableFunction<T extends CalculusFieldElement<T>>, AbstractGaussianContribution.FieldSlot<T extends CalculusFieldElement<T>>, AbstractGaussianContribution.FieldUijVijCoefficients<T extends CalculusFieldElement<T>>, AbstractGaussianContribution.FourierCjSjCoefficients, AbstractGaussianContribution.GaussianShortPeriodicCoefficients, AbstractGaussianContribution.GaussQuadrature, AbstractGaussianContribution.IntegrableFunction, AbstractGaussianContribution.Slot, AbstractGaussianContribution.UijVijCoefficients

Field Summary

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

DATATION_ACCURACY

Constructor Summary

Constructors

Constructor	Description
DSSTAtmosphericDrag(DragForce force, double mu)	Simple constructor with custom force.
DSSTAtmosphericDrag(Atmosphere atmosphere, double cd, double area, double mu)	Simple constructor assuming spherical spacecraft.
DSSTAtmosphericDrag(Atmosphere atmosphere, DragSensitive spacecraft, double mu)	Simple constructor with custom spacecraft.

Method Summary

Modifier and Type	Method	Description
Atmosphere	getAtmosphere()	Get the atmospheric model.
DragForce	getDrag()	Get drag force.
Stream<EventDetector>	getEventDetectors()	Get the discrete events related to the model.
<T extends CalculusFieldElement<T>> Stream<FieldEventDetector<T>>	getFieldEventDetectors(Field<T> field)	Get the discrete events related to the model.
protected <T extends CalculusFieldElement<T>> T[]	getLLimits(FieldSpacecraftState<T> state, FieldAuxiliaryElements<T> auxiliaryElements)	Compute the limits in L, the true longitude, for integration.
protected double[]	getLLimits(SpacecraftState state, AuxiliaryElements auxiliaryElements)	Compute the limits in L, the true longitude, for integration.
protected List<ParameterDriver>	getParametersDriversWithoutMu()	Get the drivers for force model parameters except the one for the central attraction coefficient.
double	getRbar()	Get the critical distance.
DragSensitive	getSpacecraft()	Get spacecraft shape.

Methods inherited from class org.orekit.propagation.semianalytical.dsst.forces.AbstractGaussianContribution

getMeanElementRate, getMeanElementRate, getMeanElementRate, getMeanElementRate, getParametersDrivers, init, init, initializeShortPeriodTerms, initializeShortPeriodTerms, registerAttitudeProvider, updateShortPeriodTerms, updateShortPeriodTerms

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

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

DSSTAtmosphericDrag

public DSSTAtmosphericDrag(DragForce force,
                           double mu)

Simple constructor with custom force.

Parameters:

force - atmospheric drag force model

mu - central attraction coefficient

DSSTAtmosphericDrag

public DSSTAtmosphericDrag(Atmosphere atmosphere,
                           double cd,
                           double area,
                           double mu)

Simple constructor assuming spherical spacecraft.

Parameters:

atmosphere - atmospheric model

cd - drag coefficient

area - cross sectionnal area of satellite

mu - central attraction coefficient

DSSTAtmosphericDrag

public DSSTAtmosphericDrag(Atmosphere atmosphere,
                           DragSensitive spacecraft,
                           double mu)

Simple constructor with custom spacecraft.

Parameters:

atmosphere - atmospheric model

spacecraft - spacecraft model

mu - central attraction coefficient

Method Detail

getAtmosphere

public Atmosphere getAtmosphere()

Get the atmospheric model.

Returns:

atmosphere model

getRbar

public double getRbar()

Get the critical distance.

The critical distance from the center of the central body aims at defining the atmosphere entry/exit.

Returns:

the critical distance from the center of the central body (m)

getEventDetectors

public Stream<EventDetector> getEventDetectors()

Get the discrete events related to the model.

This method is not intended to be called several time, only once by a propagator, as it has the side effect of rebuilding the events detectors when called.

Returns:

stream of event detectors

getFieldEventDetectors

public <T extends CalculusFieldElement<T>> Stream<FieldEventDetector<T>> getFieldEventDetectors(Field<T> field)

Get the discrete events related to the model.

This method is not intended to be called several time, only once by a propagator, as it has the side effect of rebuilding the events detectors when called.

Type Parameters:

T - extends CalculusFieldElement<T>

Parameters:

field - field to which the state belongs

Returns:

stream of event detectors

getLLimits

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

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

Specified by:

getLLimits in class AbstractGaussianContribution

Parameters:

state - current state information: date, kinematics, attitude

auxiliaryElements - auxiliary elements related to the current orbit

Returns:

the integration limits in L

getLLimits

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

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

Specified by:

getLLimits in class AbstractGaussianContribution

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

getParametersDriversWithoutMu

protected 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 AbstractGaussianContribution.getParametersDrivers() method.

Specified by:

getParametersDriversWithoutMu in class AbstractGaussianContribution

Returns:

drivers for force model parameters

getSpacecraft

public DragSensitive getSpacecraft()

Get spacecraft shape.

Returns:

spacecraft shape

getDrag

public DragForce getDrag()

Get drag force.

Returns:

drag force