• Journal of Astronomy and Space Sciences
• /
• v.26 no.2
• /
• pp.229-236
• /
• 2009

KOorea Multi-purpose SATellite(KOMPSAT)-5 will be launched at 550km altitude in 2010. Accurate satellite position(20 cm) and velocity(0.03 cm/s) are required to treat highly precise Synthetic Aperture Radar(SAR) image processing. Ionosphere delay was eliminated using dual frequency GPS data and double differenced GPS measurement removed common clock errors of both GPS satellites and receiver. SAC-C carrier phase data with 0.1 Hz sampling rate was used to achieve precise orbit determination(POD) with ETRI GNSS Precise Orbit Determination(EGPOD) software, which was developed by ETRI. Dynamic model approach was used and satellite's position, velocity, and the coefficients of solar radiation pressure and drag were adjusted once per arc using Batch Least Square Estimator(BLSE) filter. Empirical accelerations for sinusoidal radial, along-track, and cross track terms were also estimated once per revolution for unmodeled dynamics. Additionally piece-wise constant acceleration for cross-track direction was estimated once per arc. The performance of POD was validated by comparing with JPL's Precise Orbit Ephemeris(POE).

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.33 no.7
• /
• pp.92-97
• /
• 2005

In this paper, the performance of the KOMPSAT-1 GPS receiver on orbit was analyzed. OD (Orbit Determination) accuracy using GPS navigation solutions and GPS visibility were investigated with respect to the configuration of the GPS receiver. Indeed, the problem such as ‘3D Fix Loss’ observed during the mission was presented. As a result, the OD accuracy of ‘Best-of-4’ Position Fix Algorithm with 0 degree of mask angle was slightly better than that of ‘N-in-View’ Position Fix Algorithm. On the other hand, the GPS visibility under ‘N-in-View’ Algorithm is better than that of ‘Best-of-4’ Algorithm. The occurrence of temporal 3D Fix Loss is reduced when the ‘N-in-View’ Position Fix Algorithm was selected.

• Aerospace Engineering and Technology
• /
• v.10 no.2
• /
• pp.65-73
• /
• 2011

After launch, in order to inject the geostationary satellite into its operational orbit, the perigee altitude are forced to be raised to geostationary altitude by firing onboard LAE(Liquid Apogee Engine) at apogee of the transfer orbit. In this process, the LAE burn is divided into three or four separated burns in order to control the orbit very precisely by giving feedback the determined orbit informations and to inject the satellite in predefined longitude. This paper proposes an algorithm to determine LAE firing time slots and ${\Delta}V$ vectors under assumption of impulsive LAE burning, and additionally, a method to compensate errors induced by continuous burning. And computer simulations have been performed to validate proposed algorithms.

• Bulletin of the Korean Space Science Society
• /
• 2010.04a
• /
• pp.28.2-28.2
• /
• 2010

영상레이더 위성으로부터 획득된 SAR 영상의 상대적/절대적 방사(radiometric) 정밀도를 만족시키기 위해서는 궤도상에서 검보정을 수행하여야 한다. 일반적으로 상대 방사 정밀도의 보정을 위해서는 아마존 일대와 같이 일정한 지표 반사도를 지니는 넓은 지역을 촬영함으로써, 지상에서 모델링된 안테나 패턴의 이상 유무를 검증한다. 절대 방사 정밀도를 결정하기 위해서는 보정계수(calibration constant)를 구해야 하는데, 이를 위해서 RCS(radar cross section) 값이 기 알려져 있는 지상의 CR(corner reflector)를 관측해야 한다. 대부분의 SAR 위성의 경우, 각 입사각별로 여러 개의 빔(beam)이 독립적으로 운용되고, 위성의 경로가 각 pass 사이 거의 일정한 간격을 가지기 때문에, 지상의 CR들에 대한 빔의 접근성이 상당히 제약을 많이 받게 된다. 즉, 개별 빔이 촬영할 수 있는 CR의 개수 및 동일 CR에 대한 촬영 빈번도가 많이 작을 수 있다는 것을 의미한다. 특히, CR이 빔폭의 중심에서 관측되어야 하는 요구사항이 추가로 반영될 경우 그 빈도수는 더욱더 영향을 받게된다. 이 연구에서는 고도 550 km, 28일의 지상반복주기(repeat ground track)를 가지는 여명 궤도(dawn-dusk orbit)를 가정하고, 각 빔별로 그 빔에 할당된 하나의 CR만을 촬영해야 된다는 조건하에, 빔 접근성의 요구사항을 최대로 만족시킬 수 있는 CR의 좌표들을 구하였다. 동시에, J2항만을 고려한 이상적 28일 지상반복궤도를 적용한 경우와 모든 중력섭동항을 적용한 최적궤도를 적용한 경우를 비교하여, 실질적 검보정 일정을 수립하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.38 no.11
• /
• pp.1136-1143
• /
• 2010

One-way laser ranging technology is applied for the precise orbit determination of LRO, which is the first trial for supporting the missions of lunar or planetary spacecraft. In this paper, LRO payload and ground system are discussed for LRO laser ranging, and some errors effecting on time of flight and tracking mount accuracy are analyzed. Additionally several technologies are also analyzed to make laser pulses shot from ground stations to arrive in the LRO earth window. Measurement data of LRO laser ranging verified that these technologies could be implemented for one-way laser ranging of lunar spacecraft.

• Bulletin of the Korean Space Science Society
• /
• 1995.04a
• /
• pp.33-33
• /
• 1995

• Bulletin of the Korean Space Science Society
• /
• 1997.04a
• /
• pp.27.2-27
• /
• 1997

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.35 no.12
• /
• pp.1135-1142
• /
• 2007

STSAT-2 has an on-board satellite retroreflector array for precise orbit determination. Satellite retroreflector array reflects photon emitted from laser and uses to determine precisely the distance from ground station to satellite by the round-trip travel time of photon. The retroreflector array of protoflight model has been developed and verified through environmental tests. This paper describes the protoflight model of retroreflector array and reports environmental test results. The environmental tests of protoflight model retroreflector array were performed successfully without damage of corner cube prism occurred in engineering model development.

• Aerospace Engineering and Technology
• /
• v.11 no.2
• /
• pp.149-157
• /
• 2012

In this paper, the performance of the sequential filter for a space debris collision management system is analyzed by using the flight data of KOMPSAT-2. To analyze the performance of the sequential filter, the results of batch filter used in the orbit determination system of the KOMPSAT-2 ground station is used as reference data. The overlap method is also used to evaluate the orbit accuracy. This paper shows that the orbit determination accuracy of the sequential filter is similar to that of the KOMPSAT-2 ground station, but dissimilar characteristics exist due to the filter difference. In addition, it is also shown that the orbit determination accuracy is order of 1m root mean square by using 30 hour GPS navigation solutions and 6 hour comparison period for the overlap method.

• Aerospace Engineering and Technology
• /
• v.13 no.2
• /
• pp.7-17
• /
• 2014

This technical paper deals with development of on-board orbit generation algorithm for GEO Satellite. This paper presents the research analysis results performed in order to improve the accuracy of the existing algorithm used for generating real-time orbit information for GEO satellite. The error impact on orbit accuracy due to the orbit error sources were analyzed with the algorithm suggested by this research. As a result of the analyses, it is found that the initial orbit should be determined with an accuracy of less than 50 m and the reference position angle error for the ground station and the satellite should be maintained within ${\pm}0.0025deg$ in order to meet the orbit accuracy specification. The development of on-board flight software based on the new algorithm was accomplished and the performance verification is ongoing by using a software based performance verification tool.