Class DSSTAtmosphericDrag
- java.lang.Object
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- org.orekit.propagation.semianalytical.dsst.forces.AbstractGaussianContribution
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- org.orekit.propagation.semianalytical.dsst.forces.DSSTAtmosphericDrag
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- All Implemented Interfaces:
DSSTForceModel
public class DSSTAtmosphericDrag extends AbstractGaussianContribution
Atmospheric drag contribution to theDSSTPropagator
.The drag acceleration is computed through the acceleration model of
DragForce
.- Author:
- Pascal Parraud
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Constructor Summary
Constructors Constructor Description DSSTAtmosphericDrag(Atmosphere atmosphere, double cd, double area)
Simple constructor assuming spherical spacecraft.DSSTAtmosphericDrag(Atmosphere atmosphere, DragSensitive spacecraft)
Simple constructor with custom spacecraft.
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Method Summary
All Methods Instance Methods Concrete Methods 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.-
Methods inherited from class org.orekit.propagation.semianalytical.dsst.forces.AbstractGaussianContribution
getMeanElementRate, initialize, initializeStep, registerAttitudeProvider, updateShortPeriodTerms
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Constructor Detail
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DSSTAtmosphericDrag
public DSSTAtmosphericDrag(Atmosphere atmosphere, double cd, double area)
Simple constructor assuming spherical spacecraft.- Parameters:
atmosphere
- atmospheric modelcd
- drag coefficientarea
- cross sectionnal area of satellite
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DSSTAtmosphericDrag
public DSSTAtmosphericDrag(Atmosphere atmosphere, DragSensitive spacecraft)
Simple constructor with custom spacecraft.- Parameters:
atmosphere
- atmospheric modelspacecraft
- spacecraft model
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Method Detail
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getAtmosphere
public Atmosphere getAtmosphere()
Get the atmospheric model.- Returns:
- atmosphere model
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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)
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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
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getLLimits
protected double[] getLLimits(SpacecraftState state)
Compute the limits in L, the true longitude, for integration.- Specified by:
getLLimits
in classAbstractGaussianContribution
- Parameters:
state
- current state information: date, kinematics, attitude- Returns:
- the integration limits in L
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getSpacecraft
public DragSensitive getSpacecraft()
Get spacecraft shape.- Returns:
- spacecraft shape
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