Orbit Determination Using SLR Data for STSAT-2C: Short-arc Analysis

Kim, Young-Rok; Park, Eun-Seo; Kucharski, D.; Lim, Hyung-Chul

doi:10.5140/jass.2015.32.3.189

Cited by 5 publications

(4 citation statements)

References 24 publications

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“…Only normal point (NPT) data with a 15 s bin size were used for orbit determination instead of full-rate (FRD) data, because full-rate data proved to increase significantly the computational burden without visibly improving the orbit determination quality. Most works on SLR orbit determination also use NPT data only [24,25]. The Mendes-Pavlis model [27], available in the Orekit library, was used to model the tropospheric delay of the laser beam, based on weather data published by the SLR ground stations in the CRD pass files.…”

Section: Operational Orbit Determination From Slr and Gps Datamentioning

confidence: 99%

Initial Tracking, Fast Identification in a Swarm and Combined SLR and GNSS Orbit Determination of the TUBIN Small Satellite

et al. 2022

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Flight dynamics is a topic often overlooked by operators of small satellites without propulsion systems, as two-line elements (TLE) are easily accessible and accurate enough for most ground segment needs. However, the advent of cheap and miniaturized global navigation satellite system (GNSS) receivers and laser retroreflectors as well as modern, easy-to-use, open-source software tools have made it easier to accurately determine an orbit or to identify a spacecraft in a swarm, which helps with improving the space situational awareness in orbits that are more and more crowded. In this paper, we present tools for small satellite missions to generate orbit predictions for the launch and early orbit phase (LEOP), identify spacecraft in a swarm after a rideshare launch, and carry out routine orbit determination from multiple sources of tracking data. The TUBIN mission’s LEOP phase set a new standard at Technische Universität Berlin: the first global positioning system (GPS) data were downloaded less than four hours after separation, orbit predictions allowed successful tracking by the ground stations, and the spacecraft could be identified in the swarm as soon as the TLE were released by Space-Track. Routine orbit determination from GPS and satellite laser ranging (SLR) tracking data was carried out over several months, and the quality of the orbit predictions was analyzed. The range residuals and prediction errors were found to be larger than those of most SLR missions, which was due to the difficulty of modeling the atmospheric drag of a tumbling, non-spherical spacecraft at low orbital altitudes.

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Section: Operational Orbit Determination From Slr and Gps Datamentioning

confidence: 99%

Initial Tracking, Fast Identification in a Swarm and Combined SLR and GNSS Orbit Determination of the TUBIN Small Satellite

et al. 2022

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“…Recently, satellite laser ranging (SLR) gained attention owing to its high precision (Lim et al 2011;Choi et al 2014). The Science and Technology Satellite (STSAT)-2C OD was also successfully launched and enhanced orbit predictions can be generated owing to its cm-level range precision (Kim et al 2015). Although SLR is a subject of active research, owing to the technical assistance agreement (TAA) between Korea Aerospace Research Institute (KARI) and National Aeronautics and Space Administration (NASA), radiometric ranging techniques, which are supported by the Deep Space Network (DSN) and Near Earth Network (NEN), will be used for the KPLO mission.…”

Section: Introductionmentioning

confidence: 99%

Performance Analysis of Ranging Techniques for the KPLO Mission

Park,

Moon

2018

Journal of Astronomy and Space Sciences

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In this study, the performance of ranging techniques for the Korea Pathfinder Lunar Orbiter (KPLO) space communication system is investigated. KPLO is the first lunar mission of Korea, and pseudo-noise (PN) ranging will be used to support the mission along with sequential ranging. We compared the performance of both ranging techniques using the criteria of accuracy, acquisition probability, and measurement time. First, we investigated the end-to-end accuracy error of a ranging technique incorporating all sources of errors such as from ground stations and the spacecraft communication system. This study demonstrates that increasing the clock frequency of the ranging system is not required when the dominant factor of accuracy error is independent of the thermal noise of the ranging technique being used in the system. Based on the understanding of ranging accuracy, the measurement time of PN and sequential ranging are further investigated and compared, while both techniques satisfied the accuracy and acquisition requirements. We demonstrated that PN ranging performed better than sequential ranging in the signal-to-noise ratio (SNR) regime where KPLO will be operating, and we found that the T2B (weighted-voting balanced Tausworthe, voting v = 2) code is the best choice among the PN codes available for the KPLO mission.

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“…A femtosecond laser device that can be installed on the simulators to measure the range between the simulators is also being developed. Although laser ranging has been used extensively for satellite laser ranging (SLR) (Jo et al 2011;Lim et al 2011;Choi et al 2014;Kim et al 2015;Oh et al 2017), the technique can also be employed for measuring an inter-satellite distance (Jung et al 2012;Lee et al 2018). In this study, it was assumed that the satellite navigation algorithms were properly performed to figure out satellite's position and velocity vectors (Oh et al 2016;Shin et al 2016;Kim et al 2017;Lee et al 2017a, b).…”

Section: Introductionmentioning

confidence: 99%

Analysis of Inter-satellite Ranging Precision for Gravity Recovery in a Satellite Gravimetry Mission

Kim

Park²,

Kang

et al. 2018

Journal of Astronomy and Space Sciences

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In a satellite gravimetry mission similar to GRACE, the precision of inter-satellite ranging is one of the key factors affecting the quality of gravity field recovery. In this paper, the impact of ranging precision on the accuracy of recovered geopotential coefficients is analyzed. Simulated precise orbit determination (POD) data and inter-satellite range data of formation-flying satellites containing white noise were generated, and geopotential coefficients were recovered from these simulated data sets using the crude acceleration approach. The accuracy of the recovered coefficients was quantitatively compared between data sets encompassing different ranging precisions. From this analysis, a rough prediction of the accuracy of geopotential coefficients could be obtained from the hypothetical mission. For a given POD precision, a ranging measurement precision that matches the POD precision was determined. Since the purpose of adopting inter-satellite ranging in a gravimetry mission is to overcome the imprecision of determining orbits, ranging measurements should be more precise than POD. For that reason, it can be concluded that this critical ranging precision matching the POD precision can serve as the minimum precision requirement for an on-board ranging device. Although the result obtained herein is about a very particular case, this methodology can also be applied in cases where different parameters are used.

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Orbit Determination Using SLR Data for STSAT-2C: Short-arc Analysis

Cited by 5 publications

References 24 publications

Initial Tracking, Fast Identification in a Swarm and Combined SLR and GNSS Orbit Determination of the TUBIN Small Satellite

Initial Tracking, Fast Identification in a Swarm and Combined SLR and GNSS Orbit Determination of the TUBIN Small Satellite

Performance Analysis of Ranging Techniques for the KPLO Mission

Analysis of Inter-satellite Ranging Precision for Gravity Recovery in a Satellite Gravimetry Mission

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