Hi all,
First of all, great job on OREKIT, it’s a really nice tool!
I’m trying to compare its orbit determination and propagation (so far it seems very accurate) with other softwares like STK or GMV but I have some trouble writing an OEM file after an orbit propagation.
I based my code on the tutorials « EphemerisMode » and « MasterMode » (found in Propagation) and modified it in order to obtain the « bounded propagator » containing the computed ephemeris data (that works well) :
<definition of the different useful data, initial orbit, integrator, etc.>
// Propagator
NumericalPropagator propagator = new NumericalPropagator(
integrator); propagator.setOrbitType(
propagationType);
// Set up initial state in the propagator
propagator.setInitialState(
initialState);
// Set the propagator to ephemeris mode
propagator.setEphemerisMode();
// Extrapolate from the initial to the final date
SpacecraftState finalState = propagator.propagate(lastDate)
;
// Getting the integrated ephemeris
BoundedPropagator ephemeris = propagator.
getGeneratedEphemeris();
Now what I would like to do is export that data in an OEM file.
Therefor, I looked into the OEMWriterTest file in order to see how you did it for the tests but it seems that you always use an EphemerisFile/OEMFile created by parsing an existing OEM file !
final OEMFile oemFile = parser.parse(inEntry, "OEMExample.txt");
final EphemerisFile ephemerisFile = (EphemerisFile) oemFile;
OEMWriter writer = new OEMWriter(interpolationMethod, originator, objectID, objectName);
writer.write(tempOEMFilePath, ephemerisFile);
Is there a way to create such OEMFile or EphemerisFile based on a BoundedPropagator ephemeris ? Or is it possible to write directly from the BoundedPropagator ?
I couldn’t find any constructor using such parameter…
Other quick question : is it possible to write the OEM file with the covariance matrix ? Is this covariance matrix even available after a propagation ?
Thanks in advance for your help
Nicolas