Interface EphemerisFile.SatelliteEphemeris<C extends TimeStampedPVCoordinates,S extends EphemerisFile.EphemerisSegment<C>>
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- Type Parameters:
C
- type of the Cartesian coordinatesS
- type of the segment
- All Known Implementing Classes:
CPF.CPFEphemeris
,OcmSatelliteEphemeris
,OemSatelliteEphemeris
,OrekitEphemerisFile.OrekitSatelliteEphemeris
,SP3Ephemeris
,STKEphemerisFile.STKEphemeris
- Enclosing interface:
- EphemerisFile<C extends TimeStampedPVCoordinates,S extends EphemerisFile.EphemerisSegment<C>>
public static interface EphemerisFile.SatelliteEphemeris<C extends TimeStampedPVCoordinates,S extends EphemerisFile.EphemerisSegment<C>>
Contains the information about a single satellite from anEphemerisFile
.A satellite ephemeris consists of one or more
EphemerisFile.EphemerisSegment
s. Segments are typically used to split up an ephemeris at discontinuous events, such as a maneuver.- Author:
- Evan Ward
- See Also:
EphemerisFile
,EphemerisFile.EphemerisSegment
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Method Summary
All Methods Instance Methods Abstract Methods Default Methods Modifier and Type Method Description String
getId()
Get the satellite ID.double
getMu()
Get the standard gravitational parameter for the satellite.default BoundedPropagator
getPropagator()
View this ephemeris as a propagator, combining data from allsegments
.default BoundedPropagator
getPropagator(AttitudeProvider attitudeProvider)
View this ephemeris as a propagator, combining data from allsegments
.List<S>
getSegments()
Get the segments of the ephemeris.AbsoluteDate
getStart()
Get the start date of the ephemeris.AbsoluteDate
getStop()
Get the end date of the ephemeris.
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Method Detail
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getId
String getId()
Get the satellite ID. The satellite ID is unique only within the same ephemeris file.- Returns:
- the satellite's ID, never
null
.
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getMu
double getMu()
Get the standard gravitational parameter for the satellite.- Returns:
- the gravitational parameter used in
getPropagator(AttitudeProvider)
, in m³/s².
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getSegments
List<S> getSegments()
Get the segments of the ephemeris.Ephemeris segments are typically used to split an ephemeris around discontinuous events, such as maneuvers.
- Returns:
- the segments contained in the ephemeris file for this satellite.
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getStart
AbsoluteDate getStart()
Get the start date of the ephemeris.The date returned by this method is equivalent to
getPropagator().getMinDate()
.- Returns:
- ephemeris start date.
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getStop
AbsoluteDate getStop()
Get the end date of the ephemeris.The date returned by this method is equivalent to
getPropagator().getMaxDate()
.- Returns:
- ephemeris end date.
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getPropagator
default BoundedPropagator getPropagator()
View this ephemeris as a propagator, combining data from allsegments
.In order to view the ephemeris for this satellite as a
Propagator
several conditions must be met. An OrekitFrame
must be constructable from the frame specification in the ephemeris file. This condition is met whenEphemerisFile.EphemerisSegment.getFrame()
return normally for allsegments
. If there are multiple segments they must be adjacent such that there are no duplicates or gaps in the ephemeris. The definition of adjacent depends on the ephemeris format as some formats define usable start and stop times that are different from the ephemeris data start and stop times. If these conditions are not met anOrekitException
may be thrown by this method or by one of the methods of the returnedPropagator
.The
attitude provider
used is aFrameAlignedProvider
aligned with theinertial frame
from the first segment.Each call to this method creates a new propagator.
- Returns:
- a propagator for all the data in this ephemeris file.
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getPropagator
default BoundedPropagator getPropagator(AttitudeProvider attitudeProvider)
View this ephemeris as a propagator, combining data from allsegments
.In order to view the ephemeris for this satellite as a
Propagator
several conditions must be met. An OrekitFrame
must be constructable from the frame specification in the ephemeris file. This condition is met whenEphemerisFile.EphemerisSegment.getFrame()
return normally for allsegments
. If there are multiple segments they must be adjacent such that there are no duplicates or gaps in the ephemeris. The definition of adjacent depends on the ephemeris format as some formats define usable start and stop times that are different from the ephemeris data start and stop times. If these conditions are not met anOrekitException
may be thrown by this method or by one of the methods of the returnedPropagator
.Each call to this method creates a new propagator.
- Parameters:
attitudeProvider
- provider for attitude computation- Returns:
- a propagator for all the data in this ephemeris file.
- Since:
- 12.0
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