Class OsculatingToMeanElementsConverter
- java.lang.Object
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- org.orekit.propagation.conversion.OsculatingToMeanElementsConverter
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public class OsculatingToMeanElementsConverter extends Object
This class converts osculating orbital elements into mean elements.As this process depends on the force models used to average the orbit, a
Propagator
is given as input. The force models used will be those contained into the propagator. This propagator must support its initial state to be reset, and this initial state must represent some mean value. This implies that this method will not work withTLE propagators
because their initial state cannot be reset, and it won't work either withEckstein-Hechler propagator
as their initial state is osculating and not mean. As of 6.0, this works mainly forDSST propagator
.- Author:
- rdicosta, Pascal Parraud
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Constructor Summary
Constructors Constructor Description OsculatingToMeanElementsConverter(SpacecraftState state, int satelliteRevolution, Propagator propagator, double positionScale)
Constructor.
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Method Summary
All Methods Instance Methods Concrete Methods Modifier and Type Method Description SpacecraftState
convert()
Convert an osculating orbit into a mean orbit, in DSST sense.
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Constructor Detail
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OsculatingToMeanElementsConverter
public OsculatingToMeanElementsConverter(SpacecraftState state, int satelliteRevolution, Propagator propagator, double positionScale)
Constructor.- Parameters:
state
- initial orbit to convertsatelliteRevolution
- number of satellite revolutions in the averaging intervalpropagator
- propagator used to compute mean orbitpositionScale
- scaling factor used for orbital parameters normalization (typically set to the expected standard deviation of the position)
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Method Detail
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convert
public final SpacecraftState convert()
Convert an osculating orbit into a mean orbit, in DSST sense.- Returns:
- mean orbit state, in DSST sense
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