• Title/Summary/Keyword: 탑재용궤도전파기

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Accuracy Analysis of GEO-KOMPSAT-2 Onboard Orbit Generator (정지궤도 복합위성 탑재용 궤도정보 생성기 정밀도 해석)

  • Park, Bong-Kyu;Choi, Jae Dong;Ahn, Sang Il;Kim, Bang Yeop
    • Aerospace Engineering and Technology
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    • v.11 no.2
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    • pp.19-25
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    • 2012
  • GEO-KOMPSAT2 shall provide higher quality of image than the COMS and uses star tracker instead of earth sensor, which requires precise onboard orbit information. This requires precise on-ground orbit determination. For COMS, orbit determination is performed using the ranging data obtained from tracking system located in DAEJON. For accurate orbit determination of GEO-KOMPSAT2, KARI is building a secondary tracking station in CHUUK Islands. In this paper, the achievable accuracy of table based onboard orbit parameter generator which interpolates orbit data obtained from on-ground orbit determination using tracking data collected from two ground stations. Two types of approaches have been applied; covariance analysis and numerical analysis. By combining two analysis results, total orbit error has been estimated.

On-board Realtime Orbit Parameter Generator for Geostationary Satellite (정지궤도위성 탑재용 실시간 궤도요소 생성기)

  • Park, Bong-Kyu;Yang, Koon-Ho
    • Aerospace Engineering and Technology
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    • v.8 no.2
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    • pp.61-67
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    • 2009
  • This paper proposes an on-board orbit data generation algorithm for geostationary satellites. The concept of the proposed algorithm is as follows. From the ground, the position and velocity deviations with respect to the assumed reference orbit are computed for 48 hours of time duration in 30 minutes interval, and the generated data are up-loaded to the satellite to be stored. From the table, three nearest data sets are selected to compute position and velocity deviation for asked epoch time by applying $2^{nd}$ order polynomial interpolation. The computed position and velocity deviation data are added to reference orbit to recover absolute orbit information. Here, the reference orbit is selected to be ideal geostationary orbit with a zero inclination and zero eccentricity. Thanks to very low computational burden, this algorithm allows us to generate orbit data at 1Hz or even higher. In order to support 48 hours autonomy, maximum 3K byte memory is required as orbit data storage. It is estimated that this additional memory requirement is acceptable for geostationary satellite application.

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