Introduction: Some characteristics and remarks about the satellite
of CEI (Central European Initiative),called CESAR (Central European Satellite for Advanced Research) are introduced in paper presented. First of all, they are connected with the planned registration of the acceleration caused by the non-gravitational forces acting on the motion of the near-Earth satellite. The
investigation will be realised by a very sensitive microaccelerometer
(Peřestý, Sehnal, [1]). Therefore we calculated and constructed the graphs of acceleration curves for input orbital elements and for the TD88 (Total Density 1988) atmosphere model (Sehnal, [2]).
We used a non-rotating and a rotating atmosphere. We paid attention to determination of the time interval of the CESAR satellite illumination during the year 1997, which is planned for its launching. The calculation of sun-synchronous orbital elements completes the preventing considerations.