The orbital elements collections:
 "Version 1"
of the orbital elements collection, determined by KIAM during flight and
used for operations planning
 "Version 2" of the of the orbital elements collection,
modified by IKI during flight and recommended for the orbital
calculations during scientific data
processing
 "Version 3"  postflight determined by KIAM orbital elements, recommended for apostriori orbit calculations

Three kinds of the INTERBALL Auroral probe (IB_AUR)
orbital elements' collections are presented here.

The "Version 1" contains the orbital elements, determined by KIAM
(Ballistic center at the Keldysh Institute
of Applied Mathematics of Russian Academy of Sciences)
during the treatment of the inflight SC trajectory measurements.
This data are connected with the last point of the used
measuring time intervals. The orbit determination root mean
square error (RMS) of 3040
km inside the measuring intervals was estimated by KIAM.
It have to be mentioned, that the IB_AUR motion is not passive one, it
is subjected to nongravitational accelerations generated by
the work of the attitude control system.
The later estimations show the
discrepance between the predicted and real positions of the IB_AUR.
The IB_AUR position prediction in 15 days give the RMS error 150  500 km.
It is not possible to avoid this error during the IB_AUR positions
prediction on the operations planning stage, but it is possible to avoid this
error during such calculations for the next stage,
connected with the scientific data processing. It was done via
the orbital elements of the "Version 2"
 For the "Version 2" orbital elements constructing
the backward in time integration was fulfilled at IKI on the
base of the the orbital elements "Version 1".
For each epoche Tn the new state vector was obtained by
integration from the old state vector, corresponding to the epoch Tn+1.
The resulting modified orbital elements are
valid to use for the standard scheme of the forward
integration on the time interval Tn  Tn+1 with accuracy not worth then one
obtained during orbit determination (with RMS error 3040 km).
"Version2" orbital elements ware used for all aposteriori orbital calculations
presented up to now in the IKI servers arc.iki.rssi.ru and stda.iki.rssi.ru.
 The last orbital elements collection "Version 3" is a result of the
postflight reconstruction of the orbit fulfilled in the Ballistic
Center of the Keldysh Institute of Applied Mathematics (KIAM)
of Russian Academy of Sciences. This work was based on the
statistical processing of the complete information related to
the trajectory measurements summarised with the information
concerning the spacecraft (SC) reorientation moments. The
nongravitational accelerations generated by the work of the
attitude control system were taken into consideration.
The rootmeansquare (RMS) error of the SC position
determination inside the measuring intervals is about 23 km (till 20 km on some sections of the orbit).
In all mentioned collections the orbital elements are presented in the
same format F1, as a
state vectors (the satellite position and velocity) in the
inertial frame (Standard reference of the Earth's equator and
Equinox J2000).
