DSSTForceModel
public class DSSTAtmosphericDrag extends AbstractGaussianContribution
DSSTPropagator
.
The drag acceleration is computed through the acceleration model of
DragForce
.
Constructor | Description |
---|---|
DSSTAtmosphericDrag(Atmosphere atmosphere,
double cd,
double area) |
Simple constructor assuming spherical spacecraft.
|
DSSTAtmosphericDrag(Atmosphere atmosphere,
DragSensitive spacecraft) |
Simple constructor with custom spacecraft.
|
Modifier and Type | Method | Description |
---|---|---|
Atmosphere |
getAtmosphere() |
Get the atmospheric model.
|
EventDetector[] |
getEventsDetectors() |
Get the discrete events related to the model.
|
protected double[] |
getLLimits(SpacecraftState state) |
Compute the limits in L, the true longitude, for integration.
|
double |
getRbar() |
Get the critical distance.
|
DragSensitive |
getSpacecraft() |
Get spacecraft shape.
|
getMeanElementRate, initialize, initializeStep, registerAttitudeProvider, updateShortPeriodTerms
public DSSTAtmosphericDrag(Atmosphere atmosphere, double cd, double area)
atmosphere
- atmospheric modelcd
- drag coefficientarea
- cross sectionnal area of satellitepublic DSSTAtmosphericDrag(Atmosphere atmosphere, DragSensitive spacecraft)
atmosphere
- atmospheric modelspacecraft
- spacecraft modelpublic Atmosphere getAtmosphere()
public double getRbar()
The critical distance from the center of the central body aims at defining the atmosphere entry/exit.
public EventDetector[] getEventsDetectors()
protected double[] getLLimits(SpacecraftState state)
getLLimits
in class AbstractGaussianContribution
state
- current state information: date, kinematics, attitudepublic DragSensitive getSpacecraft()
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