Fatal Error During Propagation

Hi all,

When attempting to compute the average orbital elements during propagation, using OsculatingToMeanElementsConverter, I encounter the following error:

A fatal error has been detected by the Java Runtime Environment:

EXCEPTION_UNCAUGHT_CXX_EXCEPTION (0xe06d7363) at pc=0x00007ffe5f635b0c, pid=10784, tid=0x0000000000005cb8

JRE version: OpenJDK Runtime Environment (Zulu (8.0_332-b09) (build 1.8.0_332-b09)

Java VM: OpenJDK 64-Bit Server VM (25.332-b09 mixed mode windows-amd64 compressed oops)

Problematic frame:

C [KERNELBASE.dll+0x65b0c]

Failed to write core dump. Minidumps are not enabled by default on client versions of Windows

If you would like to submit a bug report, please visit:

The crash happened outside the Java Virtual Machine in native code.

See problematic frame for where to report the bug.

Hi @emery,

Could you provide a sample of your code which reproduce the issue ? The error you got seems quite complex.


Hi @Vincent, here is the line that is causing the issue,

average_orbital_elements = OsculatingToMeanElementsConverter(self.logger.all_states[-1], 1, self.propagator, 1.0e-3).convert()

When I use this within my custom thrustDirProvider class I get the fatal error as seen above, however when I use it within my step handler class, I don’t get an error, but the propagator seems to get stuck in an infinite loop.

Hi @emery,

Seeing your answer could you precise :

  • What type of propagator do you use ?
  • Can you show your thrustDirProvider implementation ? (at least what methods you implemented or not ?)
  • What kind of orbit are you dealing with ?


Hi Vincent,

  • I am using a numerical propagator utilizing the DormandPrince853Integrator

  • I am calling the OsculatingToMeanElementsConverter within the computeThrustDirection method to reproduce the above fatal error, or within the handleStep method of my custom step handler to get what seems to be an infinite loop

  • When establishing my propagator I set up the orbit type as equinoctial

Sorry I don’t have a simple example to provide, the code I am currently running is fairly extensive.

Hi @emery,

I understand, would you be able to provide the state you are trying to use OsculatingToMeanElementsConverter on ?

I am using it on the current spacecraft state at each timestep during the propagation. An example of one is here, SpacecraftState{orbit=equinoctial parameters: {a: 7083103.538568227; ex: -0.0013210532708788317; ey: -1.4081767305645267E-6; hx: -1.9037319042813614E-8; hy: -8.163414117204461E-9; lv: -2.6310032315035407E-5;}, attitude=org.orekit.attitudes.Attitude@75fc1992, mass=7.98, additional={}, additionalDot={}}

Hi @emery,

I’m afraid that that i will not be able to investigate your issue in the next few days :sweat:. Thank you for the additional input, this may be key to find the error.