Abstract: Real time, continuous and high precision orbit is needed for the geostationary satellite (GEO) orbit maneuver. How to recover orbit rapidly for GEO based on short-arc tracking is the key factor. This paper introduced a new kinematic orbit determination approach in order to solve this problem, which was based on 9-parameter ephemeris parameter fitting. The mathematical model and partial derivative model were deduced in detail. And the coordinate rotation method was introduced to solve the singular problem in the ephemeris parameter fitting for the GEO satellite. In order to check the precision and availability of this method, the short-arc orbit determination tests were carried out using real COMPASS GEO C-band transfer ranging data. The results indicated that: 1) with a 10 minutes tracking arc the position accuracy was better than 19 m, the velocity accuracy was 4mm/s, which was better than the MEO satellite; 2) the 5-minute orbit prediction accuracy was 17.76m, and the 10-minute orbit prediction accuracy was 18.168 m; 3) several problems in the dynamics orbit determination and single point position determination were solved, the rapid orbit recovery for GEO was achieved, which satisfied the requirement of RDSS.