• Journal of Astronomy and Space Sciences
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• 제31권3호
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• pp.247-264
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• 2014

In this paper, a brief but essential development strategy for the lunar orbit determination system is discussed to prepare for the future Korea's lunar missions. Prior to the discussion of this preliminary development strategy, technical models of foreign agencies for the lunar orbit determination system, tracking networks to measure the orbit, and collaborative efforts to verify system performance are reviewed in detail with a short summary of their lunar mission history. Covered foreign agencies are European Space Agency, Japan Aerospace Exploration Agency, Indian Space Research Organization and China National Space Administration. Based on the lessons from their experiences, the preliminary development strategy for Korea's future lunar orbit determination system is discussed with regard to the core technical issues of dynamic modeling, numerical integration, measurement modeling, estimation method, measurement system as well as appropriate data formatting for the interoperability among foreign agencies. Although only the preliminary development strategy has been discussed through this work, the proposed strategy will aid the Korean astronautical society while on the development phase of the future Korea's own lunar orbit determination system. Also, it is expected that further detailed system requirements or technical development strategies could be designed or established based on the current discussions.

• Journal of Astronomy and Space Sciences
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• 제29권3호
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• pp.275-285
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• 2012

In this study, we present preliminary results of precise orbit determination (POD) using satellite laser ranging (SLR) observations for International Laser Ranging Service (ILRS) Associate Analysis Center (AAC). Using SLR normal point observations of LAGEOS-1, LAGEOS-2, ETALON-1, and ETALON-2, the NASA/GSFC GEODYN II software are utilized for POD. Weekly-based orbit determination strategy is applied to process SLR observations and the post-fit residuals check, and external orbit comparison are performed for orbit accuracy assessment. The root mean square (RMS) value of differences between observations and computations after final iteration of estimation process is used for post-fit residuals check. The result of ILRS consolidated prediction format (CPF) is used for external orbit comparison. Additionally, we performed the precision analysis of each ILRS station by post-fit residuals. The post-fit residuals results show that the precisions of the orbits of LAGEOS-1 and LAGEOS-2 are 0.9 and 1.3 cm, and those of ETALON-1 and ETALON-2 are 2.5 and 1.9 cm, respectively. The orbit assessment results by ILRS CPF show that the radial accuracies of LAGEOS-1 and LAGEOS-2 are 4.0 cm and 5.3 cm, and the radial accuracies of ETALON-1 and ETALON-2 are 30.7 cm and 7.2 cm. These results of station precision analysis confirm that the result of this study is reasonable to have implications as preliminary results for administrating ILRS AAC.

• Journal of Astronomy and Space Sciences
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• 제33권1호
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• pp.37-44
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• 2016

This paper presents an algorithm for Real-Time Orbit Determination (RTOD) of navigation satellites for the Korean Regional Navigation Satellite System (KRNSS), when the navigation satellites generate ephemeris by themselves in abnormal situations. The KRNSS is an independent Regional Navigation Satellite System (RNSS) that is currently within the basic/preliminary research phase, which is intended to provide a satellite navigation service for South Korea and neighboring countries. Its candidate constellation comprises three geostationary and four elliptical inclined geosynchronous orbit satellites. Relative distance ranging between the KRNSS satellites based on Inter-Satellite Ranging (ISR) is adopted as the observation model. The extended Kalman filter is used for real-time estimation, which includes fine-tuning the covariance, measurement noise, and process noise matrices. Simulation results show that ISR precision of 0.3-0.7 m, ranging capability of 65,000 km, and observation intervals of less than 20 min are required to accomplish RTOD accuracy to within 1 m. Furthermore, close correlation is confirmed between the dilution of precision and RTOD accuracy.

• 한국측량학회지
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• 제27권1호
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• pp.693-700
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• 2009

장기선 네트워크 RTK(Real-Time Kinematic) 측량, 정밀단독측위(precise point positioning) 및 전리층/대류권 지연 모니터링등 GPS를 이용한 실시간 데이터 처리를 위해서는 IGS(International GNSS Service)에서 제공하는 정밀궤도 수준의 정확도가 시간지연 없이 확보되어야 한다. 본 연구는 준 실시간 위성궤도결정을 위한 선행연구로서 일반적인 위성궤도 결정 방법, 특히 동역학적 방법에 대한 이론적 고찰과 가속도 적분을 위한 지구기준/관성좌표계 변환 방법에 대한 테스트를 수행하였다. IAU 1976/1980 세차/장동모델은 IAU 2000A 모델과 0.05mas 수준의 허용범위 내 차이를 보였다. IAU 2000A 모델은 기본적으로 복잡한 장동모델로 인해 변환행렬 계산에 많은 시간이 소요된다. IAU 2000A 모델에 기존 변환 방법을 사용하는 경우가 NRO(non-rotating origin) 방법에 비해 2배정도 빠른 결과를 보인 반면 회전행렬의 실질적인 차이는 없는 것으로 나타났다.

• 한국항해항만학회:학술대회논문집
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• 한국항해항만학회 2006년도 International Symposium on GPS/GNSS Vol.1
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• pp.141-144
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• 2006

The deviations in the injection orbital parameters, resulting from launcher dispersions, need to be estimated and used for autonomous satellite operations. For the proposed small satellite mission of the university there will be two GPS receivers onboard the satellite to provide the instantaneous orbital state to the onboard data handling system. In order to meet the power requirements, the satellite will be sun-tracking whenever there is no imaging operation. For imaging activities, the satellite will be maneuvered to nadir-pointing mode. Due to such different modes of orientation the geometry for the GPS receivers will not be favorable at all times and there will be instances of poor geometry resulting in no output from the GPS receivers. Onboard the satellite, the orbital information should be continuously available for autonomous switching on/off of various subsystems. The paper presents the strategies to make use of small arcs of data from GPS receivers to compute the mean orbital parameters and use the updated orbital parameters to calculate the position and velocity whenever the same is not available from GPS receiver. Thus the navigation message from the GPS receiver, namely the position vector in Earth-Centered-Earth-Fixed (ECEF) frame, is used as measurements. As for estimation, two techniques - (1) batch least squares method, and (2) Kalman Filter method are used for orbit estimation (in real time). The performance of the onboard orbit estimation has been assessed based on hardware based multi-channel GPS Signal simulator. The results indicate good converge even with short arcs of data as the GPS navigation data are generally very accurate and the data rate is also fast (typically 1Hz).

• 한국항행학회논문지
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• 제23권6호
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• pp.535-541
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• 2019

이 논문에서는 한국형 GPS 정밀궤도 결정 기술 개발을 위한 기반 연구로써 항법위성의 기준궤도 추정을 위한 스크립트를 개발하고 성능을 분석하였다. 이를 위해 JPL Flinn AC의 자료처리 전략을 적용하였으며, GIPSY-OASIS를 이용하여 리눅스기반 스크립트를 개발하였다. 추정된 기준궤도의 정확도 분석을 위해 국제 데이터센터에서 제공되고 있는 정밀궤도력과 비교하였다. 그 결과 추정된 기준궤도와 정밀궤도력 간 위성좌표가 거의 동일한 경향을 보였으며, 분석 시작 및 종료 시점에서 일부 위성의 오차가 비교적 큰 것으로 나타났으나 대부분의 위성이 ±2 cm 범위에서 수렴하는 것으로 나타났다. 두 궤도력 간 평균오차는 모든 방향으로 1 cm 이하로 나타났으며, 표준편차 역시 1 cm 수준으로 나타나 기준궤도 추정성능이 우수한 것을 알 수 있었다.

• Journal of Astronomy and Space Sciences
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• 제37권4호
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• pp.237-247
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• 2020

The ground tracking support is a critical factor for the navigation performance of spacecraft orbiting around the Moon. Because of the tracking limit of antennas, only a small number of facilities can support lunar missions. Therefore, case studies for various ground tracking support conditions are needed for lunar missions on the stage of preliminary mission analysis. This study analyzes the ground supporting condition effect on orbit determination (OD) of Korea Pathfinder Lunar Orbiter (KPLO) in the lunar orbit. For the assumption of ground support conditions, daily tracking frequency, cut-off angle for low elevation, tracking measurement accuracy, and tracking failure situations were considered. Two antennas of deep space network (DSN) and Korea Deep Space Antenna (KDSA) are utilized for various tracking conditions configuration. For the investigation of the daily tracking frequency effect, three cases (full support, DSN 4 pass/day and KDSA 4 pass/day, and DSN 2 pass/day and KDSA 2 pass/day) are prepared. For the elevation cut-off angle effect, two situations, which are 5 deg and 10 deg, are assumed. Three cases (0%, 30%, and 50% of degradation) were considered for the tracking measurement accuracy effect. Three cases such as no missing, 1-day KDSA missing, and 2-day KDSA missing are assumed for tracking failure effect. For OD, a sequential estimation algorithm was used, and for the OD performance evaluation, position uncertainty, position differences between true and estimated orbits, and orbit overlap precision according to various ground supporting conditions were investigated. Orbit prediction accuracy variations due to ground tracking conditions were also demonstrated. This study provides a guideline for selecting ground tracking support levels and preparing a backup plan for the KPLO lunar mission phase.

• Journal of Astronomy and Space Sciences
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• 제5권1호
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• pp.31-43
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• 1988

인공위성의 추적자료로부터 예비궤도를 결정하고 이것을 초기값으로 해서 계산한 관측치 (C) 와 실제의 관측치(O)의 차이가 최소가 될때까지 반복계산함으로써, 어떤 시각에 있어서 실제의 궤도에 가장 가까운 접융궤도 요소를 얻어내는 미분보정의 과정을 수행했다. 추적한 인공 위성은 TIROS-N계열 위성인 NOAA - 9이고 추척자료는 컴퓨터에 의한 프로그랭 추척을 위해서 TBUS의 평균궤도요소로부터 미리 계산한 예측자료와 위성으후부터 송신되는 1.707GHz의 HRPT신호를 전파연구소의 직경 5m인 자동추적안테나로 추적해서 얻은 실제 자료를 이용했다. 예비궤도의 결정은 추적 자료에 따라 Gauss 방법과 Herrick -Gibbs 방법을 사용했고 미분보정의 과정에 있어서 미분보정행렬의 각 원소들은 Escobal(1975)의 해석적인 방법과 f, g급수를 이용한 수치적인 방법으로 각각 구해서 그 결과를 비교해 보았다. 해석적인 방법파 수치적인 방법의 결과는 거의 일치하였고 각 시간간격에 따른 예비궤도가 다름에도 불구하고 미분보정된 궤도는 같은 값으로 수령했다.

• Journal of Astronomy and Space Sciences
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• 제5권1호
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• pp.45-51
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• 1988

지주주위를 선회하는 안공위성의 예"1궤도를 결정하는 대부분의 모든 땅뱀을을 채조사하였다. 조사판 앙법들을 이용하켜 기상위성 NOAA-10호의 예비궤도릎 결청하였고 그 결과들을 NASA에서 계산된 NOAA-10호 위성의 평균궤도요소와 비교하였다. 이 비교를 통하여 Ga-uss형 방법들에 의하여 결정된 예비궤도요소들이 Laplace형 방법들에 의한결과보다NASA의 평균궤도요소에 더 가깝게 계산되었다. 우리의 결과는 Gauss방법에 대한 Taff(l984) 의 비판이 재고되어야 함을 보여 주며 따라서 Marsden ( 1985 )의 견해를 뒷받침한다.

• Journal of Positioning, Navigation, and Timing
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• 제10권4호
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• pp.371-377
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• 2021

This research proposes the best combination of tropospheric delay models for Korean Positioning System (KPS). The overall results are based on real observation data of Japanese Quasi-Zenith satellite system (QZSS), whose constellation is similar to the proposed constellation of KPS. The tropospheric delay models are constructed as the combinations of three types of zenith path delay (ZPD) models and four types of mapping functions (MFs). Two sets of International GNSS Service (IGS) stations with the same receiver are considered. Comparison of observation residuals reveals that the ZPD models are more influential to the measurement model rather than MFs, and that the best tropospheric delay model is the combination of GPT3 with 5 degrees grid and Vienna Mapping Function 1 (VMF1). While the bias of observation residual depends on the receivers, it still remains to be further analyzed.