• Journal of Astronomy and Space Sciences
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• 제34권1호
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• pp.19-30
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• 2017

The optical wide-field patrol network (OWL-Net) is a Korean optical surveillance system that tracks and monitors domestic satellites. In this study, a batch least squares algorithm was developed for optical measurements and verified by Monte Carlo simulation and covariance analysis. Potential error sources of OWL-Net, such as noise, bias, and clock errors, were analyzed. There is a linear relation between the estimation accuracy and the noise level, and the accuracy significantly depends on the declination bias. In addition, the time-tagging error significantly degrades the observation accuracy, while the time-synchronization offset corresponds to the orbital motion. The Cartesian state vector and measurement bias were determined using the OWL-Net tracking data of the KOMPSAT-1 and Cryosat-2 satellites. The comparison with known orbital information based on two-line elements (TLE) and the consolidated prediction format (CPF) shows that the orbit determination accuracy is similar to that of TLE. Furthermore, the precision and accuracy of OWL-Net observation data were determined to be tens of arcsec and sub-degree level, respectively.

• Journal of Astronomy and Space Sciences
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• 제26권1호
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• pp.75-88
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• 2009

이 연구의 목적은 선형화 과정이 필요 없는 Unscented 변환(Unscented Transformation)을 사용한 후처리 배치 알고리즘을 소개하고, 기존 최소자승법을 이용한 후처리 배치 필터와 반복 UKF 스무더(Iterative Unscented Kalman Filter Smoother)들과 비교하여 추정 방법 간의 성능비교와 장단점을 분석하는 것이다. 연구에 사용된 위성 궤도 결정시스템의 동역학 방정식은 지구의 비대칭 중력장의 영향, 대기항력, 태양복사압 및 달과 태양의 중력으로 구성되었다. 관측 데이터로는 지상국으로부터 측정한 위성의 거리, 방위각과 고도각이 사용되었다. 특히, 비선형성의 영향에 대한 추정 방법 간의 성능과 장단점의 비교를 위해 위성의 포기 궤도오차별, 관측데이터의 관측 잡음의 크기별 테스트를 수행하였다. 이 연구를 통해 소개된, 선형화 과정이 필요 없는 Unscented 변환 기반의 후처리 배치 필터는, 비선형성의 특징이 증대된 상황에서 기존의 후처리 배치 알고리즘들에 비해 초기 궤도오차별, 관측데이터 잡음의 크기별 테스트 시 평균적으로 각각 약 5%와 12%정도의 정밀도 향상결과를 보였다. 또한, 기존 최소자승법을 이용한 후처리 배치필터가 발산한 상황에서도, 수렴성을 확보하는 안정적인 결과를 얻을 수 있었다. 그러므로 Unscented 변환 기반의 후처리 배치필터가 인공위성 궤도 결정 시스템에 효율적으로 사용할 수 있음을 제시하였다.

• Journal of Astronomy and Space Sciences
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• 제36권4호
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• pp.249-264
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• 2019

In this study, the precise orbit determination (POD) software is developed for optical observation. To improve the performance of the estimation algorithm, a nonlinear batch filter, based on the unscented transform (UT) that overcomes the disadvantages of the least-squares (LS) batch filter, is utilized. The LS and UT batch filter algorithms are verified through numerical simulation analysis using artificial optical measurements. We use the real optical observation data of a low Earth orbit (LEO) satellite, Cryosat-2, observed from optical wide-field patrol network (OWL-Net), to verify the performance of the POD software developed. The effects of light travel time, annual aberration, and diurnal aberration are considered as error models to correct OWL-Net data. As a result of POD, measurement residual and estimated state vector of the LS batch filter converge to the local minimum when the initial orbit error is large or the initial covariance matrix is smaller than the initial error level. However, UT batch filter converges to the global minimum, irrespective of the initial orbit error and the initial covariance matrix.

• Journal of Positioning, Navigation, and Timing
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• 제13권2호
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• pp.199-206
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• 2024

The GEO-KOMPSAT-2A (GK2A) satellite, which was launched in December 2018, carries weather observation payloads and uses the image navigation and registration system to calibrate the observation images. The calibration system requires accurate orbit prediction data and depends on the accuracy of the orbit determination accuracy. In order to find a possible way to improve the current orbit determination accuracy of the GK2A flight dynamic subsystem module, orbit determination software was developed to independently evaluate the orbit determination accuracy. A comprehensive satellite dynamic model is applied for a batch-type least squares filter. When determining the orbit, thrust firing during station-keeping maneuvers and wheel-off loading maneuvers is taken into account. One month of GK2A ranging data were processed to estimate the satellite position on a daily basis. The orbit determination error was evaluated by comparing estimates during overlapping estimation intervals.

• 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).