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:

DSSTForceModel

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

Constructor Summary

Constructors

Constructor and Description
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 and Description
Atmosphere	getAtmosphere() Get the atmospheric model.
EventDetector[]	getEventsDetectors() Get the discrete events related to the model.
<T extends RealFieldElement<T>> FieldEventDetector<T>[]	getFieldEventsDetectors(Field<T> field) Get the discrete events related to the model.
protected <T extends RealFieldElement<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 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, getParametersDrivers, initialize, initialize, 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

getParameters, getParameters

Constructor Detail

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)

getEventsDetectors

public EventDetector[] getEventsDetectors()

Get the discrete events related to the model.

Returns:

array of events detectors or null if the model is not related to any discrete events

getFieldEventsDetectors

public <T extends RealFieldElement<T>> FieldEventDetector<T>[] getFieldEventsDetectors(Field<T> field)

Get the discrete events related to the model.

Type Parameters:

T - type of the elements

Parameters:

field - field used by default

Returns:

array of events detectors or null if the model is not related to any discrete events

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 RealFieldElement<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 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