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RE: [Orekit Developers] From osculating parameters to mean parameters for LEO orbits
Hi all,
The problem is solved with both the use of the DSST propagator and the trick.
Thank you for your help and for the note about what does the model include.
Best,
Lara
-----Original Message-----
From: orekit-developers-request@orekit.org [mailto:orekit-developers-request@orekit.org] On Behalf Of paulcefo
Sent: Monday, April 18, 2016 3:08 PM
To: orekit-developers@orekit.org
Cc: orekit-developers-request@orekit.org; HUE, Lara
Subject: Re: [Orekit Developers] From osculating parameters to mean parameters for LEO orbits
All,
I have started on a comment on the osculating to mean conversion. I will
finish it later today but I wanted to send the current draft now.
regards,
Paul
--
Dr. Paul J. Cefola
Consultant in Aerospace Systems, Spaceflight Mechanics, & Astrodynamics
Adjunct Faculty, Dept. of Mechanical and Aerospace Engineering,
University at Buffalo (SUNY)
4 Moonstone Way
Vineyard Haven, MA 02568
USA
508-696-1884 (phone on Martha's Vineyard)
978-201-1393 (cell)
paulcefo@buffalo.edu
paul.cefola@gmail.com
On 04/15/2016 7:52 am, HUE, Lara wrote:
> Hi to all,
>
> Thanks for the use of the great Orekit tool !
> My question is about the computation of mean parameters from a LEO
> osculating orbit.
> In order to get some operational parameters, I need to compute the
> mean parameters at each steps of the global propagation.
> One way is to use the OsculatingToMeanElementsConverter with a
> specific propagator.
> I tried with a classical EcksteinHechlerPropagator, however the
> following exception has been raised :
>
> Exception in thread "main" org.orekit.errors.PropagationException:
> impossible de calculer les paramètres moyens au sens de
> Eckstein-Hechler après 101 itérations
> at
> org.orekit.propagation.analytical.EcksteinHechlerPropagator.<init>(EcksteinHechlerPropagator.java:318)
>
> at
> org.orekit.propagation.analytical.EcksteinHechlerPropagator.<init>(EcksteinHechlerPropagator.java:200)
>
> at main.Init.main(Init.java:91)
> Caused by: org.orekit.errors.PropagationException: impossible de
> calculer les paramètres moyens au sens de Eckstein-Hechler après 101
> itérations
> at
> org.orekit.propagation.analytical.EcksteinHechlerPropagator.computeMeanParameters(EcksteinHechlerPropagator.java:394)
>
> at
> org.orekit.propagation.analytical.EcksteinHechlerPropagator.resetInitialState(EcksteinHechlerPropagator.java:327)
>
> at
> org.orekit.propagation.analytical.EcksteinHechlerPropagator.<init>(EcksteinHechlerPropagator.java:311)
>
> ... 2 more
>
> Indeed, when calling the EcksteinHechlerPropagator constructor, it
> takes more than 100 iterations to compute mean parameters at the
> initial state, and therefore the exception is raised.
> Here is a specific orbit among others, retrieved from the simulation,
> for which the computation in mean elements is not possible :
>
> AbsoluteDate t = NEW AbsoluteDate(2016, 07, 22, 9, 35, 42.562,
> TimeScalesFactory._getUTC_());
> Frame frame = FramesFactory._getEME2000_();
> Orbit orbit = NEW EquinoctialOrbit(7075842.806163763,
> 0.0012957331188810572, -4.760791390305797E-4, 0.14011350699555794,
> -1.1457596828634813, 79339.41232985309, PositionAngle._TRUE_, frame,
> t, Constants._WGS84_EARTH_MU_);
> Double mass = 436.5;
> DOUBLE c20 = Constants._EIGEN5C_EARTH_C20_;
> DOUBLE c30 = Constants._EIGEN5C_EARTH_C30_;
> DOUBLE c40 = Constants._EIGEN5C_EARTH_C40_;
> DOUBLE c50 = Constants._EIGEN5C_EARTH_C50_;
> DOUBLE c60 = Constants._EIGEN5C_EARTH_C60_;
> EcksteinHechlerPropagator analyticalPropagatorWrong = NEW
> EcksteinHechlerPropagator(orbit, mass,
> Constants._WGS84_EARTH_EQUATORIAL_RADIUS_, Constants._WGS84_EARTH_MU_,
> c20, c30, c40, c50, c60);
>
> Is there a better way to convert osculating parameters to mean
> parameters?
> Best,
>
> Lara Hué
>
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