• Journal of Astronomy and Space Sciences
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• 제19권3호
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• pp.197-206
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• 2002

NORAD Two Line Elements (TLE) are widely used for the increasing number of small satellite mission operations and analysis. However, due to the irregular periodicity of generation of the NORAD TLE, a new TLE that is independent of NORAD is required. A TLE type Orbit Determination (TLEOD) has been developed for the generation of a new TLE. Thus, the TLEOD system can provide an Antenna Control Unit (ACU) with the orbit determination result in the type of a TLE, which provides a simple interface for the commercialized ACU system. For the TLEOD system, NORAD SGP4 was used to make a new orbit determination system. In addition, a least squares method was implemented for the TLEOD system with the GPS navigation solutions of the KOMPSAT-1. Considering both the Orbit Propagation (OP) difference and the tendency of $B^{*}$ value, the preferable span of the day in the observation data was selected to be 3 days. Through the OD with 3 days observation data, the OP difference was derived and compared with that of Mission Analysis and Planning (MAPS) for the KOMPSAT-1. It has the extent from 2 km after sit days to 4 km after seven days. This is qualified enough for the efficiency of an ACU in image reception and processing center of the KOMPSAT-2.

• Journal of Astronomy and Space Sciences
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• 제19권4호
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• pp.385-394
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• 2002

SLR(Satellite Laser Ranging)은 위성과 관측소간 거리를 가장 정밀하게 측정할 수 있는 시스템이다. 1964년 발사된 Beacon-B 위성의 궤도결정을 위해 SLR 기술이 처음 사용되었는데 거리측정 정밀도가 m 수준이었다. 현재 single shot 정밀도는 cm, NP(Normal Point)는 mm수준으로 발전하였다. 이 연구에서는 SLR을 이용한 궤도결정 알고리즘을 개발하여 GPS(Global Positioning System)-36위성의 정밀 궤도를 결정하였다. 알고리즘의 정밀도를 검증하기 위해 산출한 정밀 궤도를 IGS(International GPS Service)에서 제공하는 정밀 궤도력과 비교하였는데 74cm의 RMS(Root Mean Square)를 얻었다. 또한, SLR 시스템의 관측잔차 RMS는 55mm 미만으로 알려져 있지만 이 연구에서는 44mm 결과를 얻을 수 있었다.

• 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 Positioning, Navigation, and Timing
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• 제1권1호
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• pp.59-64
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• 2012

Precise Point Positioning (PPP) has been widely used in navigation and orbit determination applications as we can obtain precise Global Positioning System (GPS) satellite orbit and clock products. Kinematic PPP, which is based on the GPS measurements only from the spaceborne GPS receiver, has some advantages for a simple precise orbit determination (POD). In this study, we developed kinematic PPP technique to estimate the orbits of GRACE-A satellite. The comparison of the mean position between the JPL's orbit product and our results showed the orbit differences 0.18 cm, 0.54 cm, and 0.98 cm in the Radial, in Along-track, and Cross-track direction respectively. In addition, we obtained the root mean square (rms) values of 4.06 cm, 3.90 cm, and 3.23 cm in the satellite coordinate components relative to the known coordinates.

• 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.

• 항공우주시스템공학회지
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• 제9권2호
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• pp.57-62
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• 2015

The satellite orbit is continuously changing due to space environment. Especially for low earth orbit, atmospheric drag plays an important role in the orbit altitude decay. Recently, solar activities are expected to be high, and relevant events are occurring frequently. In this paper, analysis on the impact of geomagnetic storm on LEO satellite orbit is presented. For this, real flight data of KOMPSAT-2, KOMPSAT-3, and KOMPSAT-5 are analyzed by using the daily decay rate of mean altitude is calculated from the orbit determination. In addition, the relationship between the solar flux and geomagnetic index, which are the metrics for solar activities, is statistically analyzed with respect to the altitude decay. The accuracy of orbit prediction with both the fixed drag coefficient and estimated one is examined with the precise orbit data as a reference. The main results shows that the improved accuracy can be achieved in case of using estimated drag coefficient.

• Journal of Astronomy and Space Sciences
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• 제28권3호
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• pp.183-192
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• 2011

The current study analyzes the effects of the scaling parameters of the batch unscented transformation on precision satellite orbit determination. Satellite laser ranging (SLR) data are used in the orbit determination algorithm, which consists of dynamics model, observation model and filtering algorithm composed of the batch unscented transformation. TOPEX/Poseidon SLR data are used by utilizing the normal point (NP) data observed from ground station. The filtering algorithm includes a repeated series of processes to determine the appropriate scaling parameters for the batch unscented transformation. To determine appropriate scaling parameters, general ranges of the scaling parameters of ${\alpha}$, ${\beta}$, k, $\lambda$ are established. Depending on the range settings, each parameter was assigned to the filtering algorithm at regular intervals. Appropriate scaling parameters are determined for observation data obtained from several observatories, by analyzing the relationship between tuning properties of the scaling parameters and estimated orbit precision. The orbit determination of satellite using the batch unscented transformation can achieve levels of accuracy within several tens of cm with the appropriate scaling parameters. The analyses in the present study give insights into the roles of scaling parameters in the batch unscented transformation method.

• Journal of Astronomy and Space Sciences
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• 제34권2호
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• pp.139-151
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• 2017

This paper presents an overview of deep space orbit determination software (DSODS), as well as validation and verification results on its event prediction capabilities. DSODS was developed in the MATLAB object-oriented programming environment to support the Korea Pathfinder Lunar Orbiter (KPLO) mission. DSODS has three major capabilities: celestial event prediction for spacecraft, orbit determination with deep space network (DSN) tracking data, and DSN tracking data simulation. To achieve its functionality requirements, DSODS consists of four modules: orbit propagation (OP), event prediction (EP), data simulation (DS), and orbit determination (OD) modules. This paper explains the highest-level data flows between modules in event prediction, orbit determination, and tracking data simulation processes. Furthermore, to address the event prediction capability of DSODS, this paper introduces OP and EP modules. The role of the OP module is to handle time and coordinate system conversions, to propagate spacecraft trajectories, and to handle the ephemerides of spacecraft and celestial bodies. Currently, the OP module utilizes the General Mission Analysis Tool (GMAT) as a third-party software component for high-fidelity deep space propagation, as well as time and coordinate system conversions. The role of the EP module is to predict celestial events, including eclipses, and ground station visibilities, and this paper presents the functionality requirements of the EP module. The validation and verification results show that, for most cases, event prediction errors were less than 10 millisec when compared with flight proven mission analysis tools such as GMAT and Systems Tool Kit (STK). Thus, we conclude that DSODS is capable of predicting events for the KPLO in real mission applications.

• 항공우주기술
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• 제11권2호
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• pp.149-157
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• 2012

본 논문에서는 우주파편 충돌위험 종합관리시스템에 적용할 연속추정필터의 성능에 대해 아리랑 2호의 실제 비행데이터를 이용하여 분석한다. 궤도결정 시스템의 성능을 분석하기 위해서 아리랑 2호의 지상국에서 사용하고 있는 일괄처리 방식의 배치필터(Batch Filter)와 비교하고, 궤도결정 정밀도 평가를 위해 중첩법(Overlap Method)을 적용한다. 본 연구결과 연속추정 필터가 기존의 아리랑 2호의 지상국 비행역학 시스템에서 사용하고 있는 배치필터와 유사한 성능을 보임을 확인하고, 필터의 방식에 따른 특성 차이가 있음을 확인한다. 또한, 30시간 GPS 항행해에 대한 6시간 중첩법을 적용하여 1m($1{\sigma}$) RMS (Root Mean Square) 수준의 궤도결정 정밀도를 얻을 수 있음을 보인다..

• 항공우주기술
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• 제12권2호
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• pp.123-130
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• 2013

우주파편의 지속적인 증가로 인해 우주파편으로부터 자국의 위성을 보호하기 위한 시스템이 등장하게 되었다. 이에 한국항공우주연구원에서도 자국의 운영위성의 보호를 위해 우주파편에 의한 충돌위험 종합관리시스템을 개발 중에 있다. 이러한 충돌위험 종합관리시스템은 자국의 위성에 대한 충돌위험을 가지고 접근해오는 우주파편에 대한 궤도정보의 정밀도에 의해 성능의 차이를 보일 수 있다. 따라서 이러한 충돌위험 종합관리시스템은 우주파편에 대한 여러 정밀 관측데이터의 처리기능을 가지고 있어야 한다. 본 논문에서는 우주파편에 대해 가장 널리 사용하고 있는 레이더 관측 데이터를 처리하기 위해 비교적 정밀한 궤도결정 정보를 가지고 있는 아리랑 2호 위성에 대한 가상 레이더 관측데이터를 이용하여 정밀 궤도결정을 수행해 봄으로써 개발 중인 충돌위험 종합관리시스템의 성능을 확인하고자 한다.