Re: [Orekit Users] error using boxAndSolarArraySpacecraft with numerical integrator

[MAISONOBE Luc <luc.maisonobe@c-s.fr>]

Hi,

mrt67@msstate.edu a écrit :

> I am having a problem using  boxAndSolarArraySpacecraft under solar radiation
> pressure with numerical integrators.  I am trying to run one year simulations
> for spacecraft of different shapes under solar radiation pressure.   
> If I choose
> the spherical spacecraft shape, the simulation runs fine, but if I change the
> shape to boxAndSolarArray, I will either get NaN position and velocity, or I
> will get the error:  "Java exception occurred:
> org.orekit.errors.PropagationException: out of range date for SUN  
> ephemerides:
> 2000-08-04T00:00:?" for a long enough propagation time .  The NaN  
> error occurs

We encountered this type of error when an infinity appeared in a date  
in older versions of Orekit (the exclamation point in the seconds part  
of the error message was due to the infinity unicode symbol not being  
rendered correctly).

This was fixed some time ago and the fix will be released along with  
version 6.0 of Orekit. Which version of Orekit do you use, is it one  
of the official version (5.x) or the development version from the Git  
repository?

> when I used a fixed step size numerical integrator (classical runge kutta),
> while the other error occurs when I use any adaptive step size numerical
> integrator.  Also, these errors only appear for longer simulations (> one
> month).  The orbital parameters will influence the amount of time the
> simulation can run without error.   Also, for what it's worth, I am calling
> these classes from Matlab.

This should not make any differences, the underlying code is the same  
and the error occurs at a deep layer.

best regards,
Luc

> Any help would be much appreciated!!!



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