Package org.orekit.files.ilrs

Class CPF.CPFEphemeris

java.lang.Object

org.orekit.files.ilrs.CPF.CPFEphemeris

All Implemented Interfaces:

EphemerisFile.EphemerisSegment<CPF.CPFCoordinate>, EphemerisFile.SatelliteEphemeris<CPF.CPFCoordinate,CPF.CPFEphemeris>

Enclosing class:

CPF

public class CPF.CPFEphemeris
extends Object
implements EphemerisFile.SatelliteEphemeris<CPF.CPFCoordinate,CPF.CPFEphemeris>, EphemerisFile.EphemerisSegment<CPF.CPFCoordinate>

An ephemeris entry for a single satellite contains in a CPF file.

Constructor Summary

Constructors

Constructor	Description
CPFEphemeris(String id)	Constructor.

Method Summary

Modifier and Type	Method	Description
CartesianDerivativesFilter	getAvailableDerivatives()	Get which derivatives of position are available in this ephemeris segment.
List<CPF.CPFCoordinate>	getCoordinates()	Get the coordinates for this ephemeris segment in EphemerisFile.EphemerisSegment.getFrame().
List<CPF.CPFCoordinate>	getEphemeridesDataLines()	Get the list of Ephemerides data lines.
Frame	getFrame()	Get the reference frame for this ephemeris segment.
String	getId()	Get the satellite ID.
int	getInterpolationSamples()	Get the number of samples to use in interpolation.
double	getMu()	Get the standard gravitational parameter for the satellite.
BoundedPropagator	getPropagator()	View this ephemeris as a propagator, combining data from all segments.
BoundedPropagator	getPropagator(AttitudeProvider attitudeProvider)	View this ephemeris as a propagator, combining data from all segments.
List<CPF.CPFEphemeris>	getSegments()	Returns a list containing only this.
AbsoluteDate	getStart()	Get the start date of the ephemeris.
AbsoluteDate	getStop()	Get the end date of the ephemeris.

Methods inherited from class java.lang.Object

clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait

Methods inherited from interface org.orekit.files.general.EphemerisFile.EphemerisSegment

getInertialFrame

Constructor Details

CPFEphemeris

public CPFEphemeris(String id)

Constructor.

Parameters:

id - satellite ID

Method Details

getFrame

public Frame getFrame()

Get the reference frame for this ephemeris segment. The defining frame for EphemerisFile.EphemerisSegment.getCoordinates().

Specified by:

getFrame in interface EphemerisFile.EphemerisSegment<CPF.CPFCoordinate>

Returns:

the reference frame for this segment. Never null.

getInterpolationSamples

public int getInterpolationSamples()

Get the number of samples to use in interpolation.

Specified by:

getInterpolationSamples in interface EphemerisFile.EphemerisSegment<CPF.CPFCoordinate>

Returns:

the number of points to use for interpolation.

getAvailableDerivatives

public CartesianDerivativesFilter getAvailableDerivatives()

Get which derivatives of position are available in this ephemeris segment.

While EphemerisFile.EphemerisSegment.getCoordinates() always returns position, velocity, and acceleration the return value from this method indicates which of those are in the ephemeris file and are actually valid.

Specified by:

getAvailableDerivatives in interface EphemerisFile.EphemerisSegment<CPF.CPFCoordinate>

Returns:

a value indicating if the file contains velocity and/or acceleration data.

getCoordinates

public List<CPF.CPFCoordinate> getCoordinates()

Get the coordinates for this ephemeris segment in EphemerisFile.EphemerisSegment.getFrame().

Specified by:

getCoordinates in interface EphemerisFile.EphemerisSegment<CPF.CPFCoordinate>

Returns:

a list of state vectors in chronological order. The coordinates are not necessarily evenly spaced in time. The value of EphemerisFile.EphemerisSegment.getAvailableDerivatives() indicates if the velocity or accelerations were specified in the file. Any position, velocity, or acceleration coordinates that are not specified in the ephemeris file are zero in the returned values.

getId

public String getId()

Get the satellite ID. The satellite ID is unique only within the same ephemeris file.

Specified by:

getId in interface EphemerisFile.SatelliteEphemeris<CPF.CPFCoordinate,CPF.CPFEphemeris>

Returns:

the satellite's ID, never null.

getMu

public double getMu()

Get the standard gravitational parameter for the satellite.

Specified by:

getMu in interface EphemerisFile.EphemerisSegment<CPF.CPFCoordinate>

Specified by:

getMu in interface EphemerisFile.SatelliteEphemeris<CPF.CPFCoordinate,CPF.CPFEphemeris>

Returns:

the gravitational parameter used in EphemerisFile.SatelliteEphemeris.getPropagator(AttitudeProvider), in m³/s².

getSegments

public List<CPF.CPFEphemeris> getSegments()

Returns a list containing only this.

Specified by:

getSegments in interface EphemerisFile.SatelliteEphemeris<CPF.CPFCoordinate,CPF.CPFEphemeris>

Returns:

the segments contained in the ephemeris file for this satellite.

getStart

public AbsoluteDate getStart()

Get the start date of the ephemeris.

The date returned by this method is equivalent to getPropagator().getMinDate().

Specified by:

getStart in interface EphemerisFile.EphemerisSegment<CPF.CPFCoordinate>

Specified by:

getStart in interface EphemerisFile.SatelliteEphemeris<CPF.CPFCoordinate,CPF.CPFEphemeris>

Returns:

ephemeris start date.

getStop

public AbsoluteDate getStop()

Get the end date of the ephemeris.

The date returned by this method is equivalent to getPropagator().getMaxDate().

Specified by:

getStop in interface EphemerisFile.EphemerisSegment<CPF.CPFCoordinate>

Specified by:

getStop in interface EphemerisFile.SatelliteEphemeris<CPF.CPFCoordinate,CPF.CPFEphemeris>

Returns:

ephemeris end date.

getPropagator

public BoundedPropagator getPropagator()

View this ephemeris as a propagator, combining data from all segments.

In order to view the ephemeris for this satellite as a Propagator several conditions must be met. An Orekit Frame must be constructable from the frame specification in the ephemeris file. This condition is met when EphemerisFile.EphemerisSegment.getFrame() return normally for all segments. 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 an OrekitException may be thrown by this method or by one of the methods of the returned Propagator.

The attitude provider used is a FrameAlignedProvider aligned with the inertial frame from the first segment.

Each call to this method creates a new propagator.

Specified by:

getPropagator in interface EphemerisFile.EphemerisSegment<CPF.CPFCoordinate>

Specified by:

getPropagator in interface EphemerisFile.SatelliteEphemeris<CPF.CPFCoordinate,CPF.CPFEphemeris>

Returns:

a propagator for all the data in this ephemeris file.

getPropagator

public BoundedPropagator getPropagator(AttitudeProvider attitudeProvider)

View this ephemeris as a propagator, combining data from all segments.

In order to view the ephemeris for this satellite as a Propagator several conditions must be met. An Orekit Frame must be constructable from the frame specification in the ephemeris file. This condition is met when EphemerisFile.EphemerisSegment.getFrame() return normally for all segments. 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 an OrekitException may be thrown by this method or by one of the methods of the returned Propagator.

Each call to this method creates a new propagator.

Specified by:

getPropagator in interface EphemerisFile.EphemerisSegment<CPF.CPFCoordinate>

Specified by:

getPropagator in interface EphemerisFile.SatelliteEphemeris<CPF.CPFCoordinate,CPF.CPFEphemeris>

Parameters:

attitudeProvider - provider for attitude computation

Returns:

a propagator for all the data in this ephemeris file.

getEphemeridesDataLines

public List<CPF.CPFCoordinate> getEphemeridesDataLines()

Get the list of Ephemerides data lines.

Returns:

a reference to the internal list of Ephemerides data lines