public class DeSitterRelativity extends AbstractForceModel
De Sitter term causes a precession of the orbital plane at a rate of 19 mas per year.
Modifier and Type | Field and Description |
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static String |
ATTRACTION_COEFFICIENT_SUFFIX
Suffix for parameter name for attraction coefficient enabling Jacobian processing.
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Constructor and Description |
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DeSitterRelativity()
Constructor.
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DeSitterRelativity(CelestialBody earth,
CelestialBody sun)
Simple constructor.
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Modifier and Type | Method and Description |
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<T extends CalculusFieldElement<T>> |
acceleration(FieldSpacecraftState<T> s,
T[] parameters)
Compute acceleration.
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Vector3D |
acceleration(SpacecraftState s,
double[] parameters)
Compute acceleration.
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boolean |
dependsOnPositionOnly()
Check if force models depends on position only.
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CelestialBody |
getEarth()
Get the Earth model used to compute De Sitter effect.
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Stream<EventDetector> |
getEventsDetectors()
Get the discrete events related to the model.
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<T extends CalculusFieldElement<T>> |
getFieldEventsDetectors(Field<T> field)
Get the discrete events related to the model.
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List<ParameterDriver> |
getParametersDrivers()
Get the drivers for parameters.
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CelestialBody |
getSun()
Get the sun model used to compute De Sitter effect.
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complainIfNotSupported, getParameterDriver, isSupported
clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait
addContribution, addContribution, getParameters, getParameters, init, init
public static final String ATTRACTION_COEFFICIENT_SUFFIX
@DefaultDataContext public DeSitterRelativity()
It uses the DataContext.getDefault()
to initialize the celestial bodies.
public DeSitterRelativity(CelestialBody earth, CelestialBody sun)
earth
- the Earthsun
- the Sunpublic CelestialBody getSun()
public CelestialBody getEarth()
public boolean dependsOnPositionOnly()
public Vector3D acceleration(SpacecraftState s, double[] parameters)
s
- current state information: date, kinematics, attitudeparameters
- values of the force model parameterspublic <T extends CalculusFieldElement<T>> FieldVector3D<T> acceleration(FieldSpacecraftState<T> s, T[] parameters)
T
- type of the elementss
- current state information: date, kinematics, attitudeparameters
- values of the force model parameterspublic Stream<EventDetector> getEventsDetectors()
public <T extends CalculusFieldElement<T>> Stream<FieldEventDetector<T>> getFieldEventsDetectors(Field<T> field)
T
- extends CalculusFieldElement<T>field
- field to which the state belongspublic List<ParameterDriver> getParametersDrivers()
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