An algorithm of state estimation with attitude motion for the powered flight phase by apogee boost motor of a geostationary satellite is presented. The measured Doppler data oscillate with a spin period for the satellite equipped with an offset antenna, or fluctuate due to the occurrence of apogee motor firing error. A technique for specification of the error resource against the orbit injection error is outlined. The estimation results by the simplified filter with attitude motion are discussed. The technique is especially suited to real time estimation during maneuvers with a liquid propellant motor.
State Estimation Algorithm Considering Attitude Motion for Apogee Motor Burning of Geostationary Satellite
1986
17 pages
Report
Keine Angabe
Englisch