Orbit Determination from Tracking Data of Artificial Satellite Using the Method of Differential Correction
The differential correction process determining osculating orbital elements as correct as possible at a given instant of time from tracking data of artificial satellite was accomplished. Preliminary orbital elements were used as an initial value of the differential correction procedure and iterated...
| Main Authors: | , , , , |
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| Format: | Article |
| Language: | English |
| Published: |
The Korean Space Science Society
1988-06-01
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| Series: | Journal of Astronomy and Space Sciences |
| Online Access: | http://ocean.kisti.re.kr/downfile/volume/kosss/OJOOBS/1988/v5n1/OJOOBS_1988_v5n1_31.pdf |
| Summary: | The differential correction process determining osculating orbital elements as correct as possible at a given instant of time from tracking data of artificial satellite was accomplished. Preliminary orbital elements were used as an initial value of the differential correction procedure and iterated until the residual of real observation(O) and computed observation(C) was minimized. Tracking satellite was NOAA-9 or TIROS-N series. Two types of tracking data were prediction data precomputed from mean orbital elements of TBUS and real data obtained from tracking 1.707GHz HRPT signal of NOAA-9 using 5 meter auto-track antenna in Radio Research Laboratory. According to tracking data either Gauss method or Herrick-Gibbs method was applied to preliminary orbit determination. In the differential correction stage we used both of the Escobal(1975)'s analytical method and numerical ones are nearly consistent. And the differentially corrected orbit converged to the same value in spite of the differences between preliminary orbits of each time span. |
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| ISSN: | 2093-5587 2093-1409 |