Kalman Filter-Based Orbit Determination with Dynamic Model Compensation for a Maneuvered GEO Satellite
Kalman Filter-Based Orbit Determination with Dynamic Model Compensation for a Maneuvered GEO Satellite
Orbit determination methods for a geostationary (GEO) satellite are introduced. In order to control or model the thrust force, a Kalman filter based on dynamic model compensation is proposed for the orbit determination of a maneuvered GEO satellite. The main idea is to use a first-order Gauss-Markov process to compensate the unmodeled or inaccurately modeled accelerations caused by orbital maneuver in Kalman filter-based orbit determination. Simulation with Chinese ground tracking network for a maneuvered GEO satellite was conducted to verify the performance of the proposed orbit determination technique. The results show that it can efficiently compensate the influence of orbital maneuver and achieve high orbit accuracy.
Document information
Kalman Filter-Based Orbit Determination with Dynamic Model Compensation for a Maneuvered GEO Satellite
Advanced Materials Research ; 383-390 ; 5626-5631
2011-11-22
6 pages
Article (Journal)
Electronic Resource
English
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