A Japanese first spaceborne GPS receiver, within the Orbital Reentry Experiment (OREX) vehicle, was lanuched by the H-II launch vehicle on February 4, 1994. The observed GPS data are analyzed in this report to evaluate the accuracy of orbit determination by GPS. We examined four techniques for orbit determination; GPS stand-alone navigation, differential GPS navigation, GPS navigation with the precise ephemeris, and GPS/IMU hybrid navigation. These results were evaluated by comparison with independent radar data and the efficiency of GPS orbit determination is confirmed.
Orbit Determination of the Orbital Reentry Experiment (OREX) Vehicle by GPS
1995
34 pages
Report
No indication
English
Spacecraft Trajectories & Flight Mechanics , Unmanned Spacecraft , Satellite orbits , Japanese spacecraft , Global positioning system , Receivers , Spacecraft reentry , Satellite navigation systems , Position indicators , Orbital position estimation , Ephemeris time , Hybrid navigation systems , Orbit calculation , Position(Location) , Minimum variance orbit determination , Radar , Kalman filters , Reentry vehicles , Renetry guidance , Spacecraft control , Foreign technology , OREX(Orbital Reentry Experiment) , Orbital Reentry Experiment
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