Validation of Geostationary Satellite Orbit Determination Using Single-Station Antenna Tracking Data

Hwang, Yoola; Lee, Byoung-Sun; Kim, Bang-Yeop; Kim, Hae-Yeon; Kim, Hae-Dong

doi:10.2514/1.a32334

Cited by 4 publications

(8 citation statements)

References 12 publications

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“…The optical observation results were tested to confirm the estimation accuracy of the orbit estimation using antenna data with the azimuth bias correction (Hwang et al, 2013). Thus, regular optical observation is expected to be useful for the accurate satellite position determination and antenna bias correction.…”

Section: Casementioning

confidence: 98%

“…After 10 days, the differences of the KARI and KASI estimates were very small. In case of the KARI ephemeris, the orbit estimation uncertainty was approximately 1-2 km root-sum-squares for 48 h in a 3-dimension sense (Hwang et al, 2013). The uncertainty of the estimated orbit by the KASI 2-day optical observation was 0.2 km from the sequential filter.…”

Section: Comparison For the Longitudinal And Latitudinal Positionsmentioning

confidence: 99%

“…A single antenna was used to receive the tonal range and angular data of the COMS in 60-s intervals or receive burst data 8 times daily to determine the orbit of the COMS. Hwang et al (2008Hwang et al ( , 2013 performed a COMS orbit determination analysis using tracking data from a single satellite communication antenna. This study revealed that the COMS orbit determination can achieve 3-sigma position uncertainty on the order of 1.5-km root-sum-square as the filter results.…”

Section: Pre-processing Of the Measurement And Orbit Determination Prmentioning

confidence: 99%

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Analysis of the angle-only orbit determination for optical tracking strategy of Korea GEO satellite, COMS

Choi

Roh

et al. 2015

Advances in Space Research

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Section: Casementioning

confidence: 98%

Section: Comparison For the Longitudinal And Latitudinal Positionsmentioning

confidence: 99%

Section: Pre-processing Of the Measurement And Orbit Determination Prmentioning

confidence: 99%

See 1 more Smart Citation

Analysis of the angle-only orbit determination for optical tracking strategy of Korea GEO satellite, COMS

Choi

Roh

et al. 2015

Advances in Space Research

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“…OD using ranging and angle tracking data estimates the satellite position, velocity, and solar radiation pressure coefficient, as well as additional measurement bias, if necessary. 2) Batch least-square estimator (BLSE) is used for normal operational OD, and an extended Kalman filter (EKF) is utilized for real-time OD. 3,4) The OP provides propagated orbit ephemeris and generates the ground track data, antenna pointing data, and orbit states in a type of two-line element (TLE) to provide to the TTC M&C of the ground station.…”

Section: Orbit Determination and Predictionmentioning

confidence: 99%

“…Initially or after calibration, a bias estimate using BLSE is normally conducted for a single ground station. 2,16,17) Figure 7 shows the radial, along-track, and cross-track component differ- Trans. Japan Soc.…”

Section: Orbit Determination and Predictionmentioning

confidence: 99%

Development of a Novel Core Component-based Flight Dynamics Subsystem Software Platform

Hwang

Lee

2019

Trans. Japan Soc. Aero. S Sci.

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The flight dynamics subsystem (FDS) of a geostationary satellite ground control system conducts estimates of the orbital states, keeping within its mission box, and calculating the satellite operational parameters to be uploaded. A new FDS has been designed and implemented by dividing it into core-and bus-dependent modules for a recent Korean geostationary satellite ground control system. The core modules include orbit determination and prediction, event prediction, and station-keeping and relocation (SKR) planning; whereas the bus-dependent modules include fuel accounting, thruster modeling and maneuver reconstructions of SKR, and calculate all of the bus-dependent parameters. In particular, separate designs based on the components of the SKR planning and maneuver reconstruction using thruster modeling allow the system to be reusable and replaceable. We also designed and implemented a conjunction analysis tool and collocation control and monitoring units for multiple-satellite control. A FDS database has been developed and is managed using SQLite, which is freely distributed. The FDS is easy to develop and operate thanks to a novel separation concept introduced for the core-platform and spacecraft bus-dependent modules. It is the same concept used for operation and the graphical user interfaces (GUIs) applicable to the FDS. All of the FDS modules for new geostationary satellites have been validated through function and performance testing, and have proven to work successfully after the launch of satellites.

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Monitoring of GEO satellite thruster efficiency

Hwang

Lee

2018

2018 SpaceOps Conference

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Geostationary-earth-orbiter (GEO) satellites perform station-keeping (SK) maneuver once per week or every other week, which is dependent on the satellite missions. In order to perform SK maneuver, the flight-dynamics-subsystem (FDS) plans amounts of the velocity increments and the firing time, and it reconstructs the planned velocity increments based on the thruster modeling provided by satellite manufacturer. Then parameters related to the maneuver are uploaded to the satellite. However, the maneuver parameters are up to satellite flight software: some upload the firing time and the planned velocity increments and the others transmit the firing time and the reconstructed velocity increments. The satellite executes the command by following flight software mounted onboard. After carrying out the maneuver, the telemetry, related to the each thruster information such as pulse numbers and accumulated on time, is transmitted to the ground. In the ground control center, it calculates fuel usage amounts and estimates the GEO satellite's service lifetime. The thruster efficiency can be calculated and monitored by several methods. First is to conduct the orbit determination (OD) using tracking and ranging data classifying before and after maneuver at the epoch of the firing time. The velocity differences of the OD results by the before and after maneuver at the epoch of the firing time provide the delta velocity due to the maneuver. Second is to estimate the velocity increments at the epoch of the firing impulse time during the OD. Third is to compare the reconstructed velocity increments by thruster modeling and actually calculated velocity increments by fuel accounting (FA). In this paper, we monitor and analyze each thruster efficiency by suggested theoretical methods and estimate the GEO satellite lifetime.

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Validation of Geostationary Satellite Orbit Determination Using Single-Station Antenna Tracking Data

Cited by 4 publications

References 12 publications

Analysis of the angle-only orbit determination for optical tracking strategy of Korea GEO satellite, COMS

Analysis of the angle-only orbit determination for optical tracking strategy of Korea GEO satellite, COMS

Development of a Novel Core Component-based Flight Dynamics Subsystem Software Platform

Monitoring of GEO satellite thruster efficiency

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