• Journal of Astronomy and Space Sciences
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• 제37권1호
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• pp.11-18
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• 2020

Satellite optical communication has gained significant attention owing to its many quality features (e.g., a larger bandwidth, license free spectrum, higher data rate, and better security) compared to satellite microwave communication. Various experiments have been performed during many space missions to demonstrate and characterize inter-satellite links, downlinks, and uplinks. Korea has also planned to establish an experimental communication system using a geostationary earth orbit (GEO) satellite and the Geochang station as an optical ground station for low Earth orbit (LEO)-to-ground optical relay links. In this study, the performance of inter-satellite communication links and downlinks was investigated for the new Korean experimental communication system in terms of link margin, bit error rate (BER), and channel capacity. In particular, the performance of the inter-satellite links was analyzed based on the receiving apertures and the transmitting power, while that of the downlink was analyzed in terms of atmospheric turbulence conditions and transmitting power. Finally, we discussed two system parameters of receiving aperture and transmitting power to meet the three criteria of link margin, BER, and channel capacity.

• 항공우주시스템공학회지
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• 제16권3호
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• pp.105-114
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• 2022

본 연구는 저궤도에서 3 m급 광학 영상을 획득하기 위한 6U 초소형위성 시스템의 개념설계를 제안한다. 3 m급 광학 영상을 촬영하기 위한 광학계를 설계하고 최적화한다. 광학계는 구경 Ø78 mm, 길이 250 mm의 공간 내, 유효 초점거리 1400 mm를 가진다. 이를 탑재할 수 있는 6U 초소형위성의 시스템에 대한 요구조건과 제한조건을 도출한다. 이러한 조건들을 만족하는 자세 및 궤도제어계, 추진계, 명령 및 데이터처리계, 전력계, 통신계, 구조 및 메커니즘계, 열제어계를 설계한다. 설계된 광학 탑재체와 COTS 부품으로 구성된 본체의 서브시스템을 통합하여 6U 초소형위성의 시스템을 완성한다. 전체 시스템의 질량, 전력, 통신에 대한 버짓 분석을 통해 설계규격을 확인한다. 저궤도에서 광학 영상을 획득하기 위한 6U 초소형위성의 운용 개념을 제시한다. 이러한 초소형위성을 대량으로 생산하여 위성군을 구축한다면 감시·정찰 임무나 재난·재해 관리에 활용할 수 있다.

• 항공우주시스템공학회지
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• 제13권4호
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• pp.26-36
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• 2019

고해상도 지구 관측위성에서는 광학 부품간 정밀한 위치 정렬도가 요구된다. 그러나, 가혹한 위성 발사환경 및 우주환경 같은 외부 요인에 의해 광부품의 정렬오차가 발생한다. 이러한 정렬오차에 의해 저하된 영상품질을 보상하기 위해 포커스 메커니즘이 적용된 위성광학계의 설계가 필요하다. 본 논문에서는 위성카메라 정렬오차 보상이 가능한 목표광학계의 제작 및 성능 실험에 대한 연구를 수행하였다. 먼저 설계된 목표광학계를 제작/조립/정렬하였으며, 이 완료된 목표 광학계를 사용하여 영상 촬영 실험을 수행하였다. 영상 촬영 실험은 포커스 메커니즘에 의한 상의 변화를 이미지로 확인하는 실험과 오토콜리메이터를 이용하여 USAF 타깃을 촬영해 MTF를 분석하는 실험을 수행하였다. 실험 결과를 통해 포커스 메커니즘을 통하여 정렬오차를 충분히 보상할 수 있음을 확인하였으며, 궤도상에서 정렬오차를 보상할 수 있는 리포커싱의 기초자료를 확보하였다.

• Journal of Astronomy and Space Sciences
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• 제36권3호
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• pp.169-180
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• 2019

In this study, a batch least square estimator that utilizes optical observation data is developed and utilized to determine geostationary orbits (GEO). Through numerical simulations, the effects of error sources, such as clock errors, measurement noise, and the a priori state error, are analyzed. The actual optical tracking data of a GEO satellite, the Communication, Ocean and Meteorological Satellite (COMS), provided by the optical wide-field patrol network (OWL-Net) is used with the developed batch filter for orbit determination. The accuracy of the determined orbit is evaluated by comparison with two-line elements (TLE) and confirmed as proper for the continuous monitoring of GEO objects. Also, the measurement residuals are converged to several arcseconds, corresponding to the OWL-Net performance. Based on these analyses, it is verified that the independent operation of electro-optic space surveillance systems is possible, and the ephemerides of space objects can be obtained.

• 항공우주시스템공학회지
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• 제10권4호
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• pp.17-25
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• 2016

본 연구에서는 초점면부 영상안정화 기법 중 렌즈 시프팅 영상안정화 기법에 적용될 광학설계를 수행하였다. 렌즈 시프팅 기법은 광학탑재체로 전달되는 미세진동외란을 보상하기 위해 광 경로를 바꿔주는 영상 안정화 기법이다. 실제 위성카메라의 제원을 참고하여 렌즈 시프팅 기법이 적용될 광학계의 요구도를 수립하였으며, 광학설계 프로그램인 Code-V를 이용해 광학계를 설계하였다. 설계된 광학계가 요구 조건을 충족하였는지 검증하기 위해 시야에 따른 광선 수차분석, 스팟 다이어그램 분석, MTF 선도분석을 수행하였다. 최종적으로 설계된 광학계는 슈미트 카세그라인 타입에 필드 플래트너와 진동보상 렌즈가 삽입된 형태이며, 주반사경 직경은 200 mm, GSD 2.87m, 나이퀴스트 주파수에서 MTF 33%으로 광학계 성능요구도를 만족하였다. 본 연구에서 설계된 진동보상렌즈의 입사광선에 대한 진동계수는 0.95~1.00 으로 성능 요구도를 만족하였다.

• 한국항공우주학회지
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• 제43권3호
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• pp.265-271
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• 2015

본 연구에서는 소형 위성카메라의 영상성능 저하를 궤도상에서 능동적으로 보정하기 위해 광학보정장치를 적용한 위성카메라의 광학설계를 수행하였다. 2개의 광학 보정장치는 각각 부반사경 및 초점면부에 부착되며 총 5자유도의 운동이 가능하다. 본 논문에서 설계한 광학부는 슈미트-카세그레인(Schmidt-Cassegrain)타입으로 주반사경의 직경은 200mm이고, GSD 3.8m, MTF 성능은 약 50% 정도이다. 설계된 광학계는 수차곡선과 Spot diagram과 MTF를 통해 성능평가를 수행하였다. 수차곡선을 통해 광학성능에 가장 큰 영향을 미치는 수차가 구면수차인 것을 확인 할 수 있고, MTF 해석을 통해서 나이퀴스트 주파수에서 MTF 30%이상의 요구 성능을 충분히 만족하는 것을 확인하였다.

• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2008년도 International Symposium on Remote Sensing
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• pp.232-235
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• 2008

The mission of the EO(electro-optical) based low earth orbit satellite is provision of the high-resolution images required for GIS(Geographical Information Systems) establishment and the applications for environmental, agriculture and ocean monitoring. AEISS(Advanced Earth Imaging Sensor System) which is the main payload on the satellite consists of EOS(electro-optical subsystem) and PDTS(Payload Data Transmission Sub-system). IDHU(Image Data Handling Unit) which is one of the major unit in PDTS is capable of compression, storage, encryption and encoding. In this paper, the payload system of the EO based satellite is briefly introduced and the influence of the compression on AEISS is analyzed.

• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2005년도 Proceedings of ISRS 2005
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• pp.637-640
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• 2005

In the development of a electronic system for a optical payload comprising mainly EOS(Electro-Optical Sub-system) and PDTS(Payload Data Transmission Sub-system), many aspects should be investigated and discussed for the easy implementation, for th e higher reliability of operation and for the effective ness in cost, size and weight as well as for the secure interface with components of a satellite bus, etc. As important aspects the interfaces between a satellite bus and a payload, and some design features of the CEU(Camera Electronics Unit) inside the payload are described in this paper. Interfaces between a satellite bus and a payload depend considerably on whether t he payload carries the PMU(Payload Management Un it), which functions as main controller of the Payload, or not. With the PMU inside the payload, EOS and PDTS control is performed through the PMU keep ing the least interfaces of control signals and primary power lines, while the EOS and PDTS control is performed directly by the satellite bus components using relatively many control signals when no PMU exists inside the payload. For the CEU design the output channel configurations of panchromatic and multi-spectral bands including the video image data inter face between EOS and PDTS are described conceptually. The timing information control which is also important and necessary to interpret the received image data is described.

• 한국군사과학기술학회지
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• 제27권2호
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• pp.127-139
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• 2024

This paper discusses a gravity compensation technique designed to reduce wavefront error caused by gravity during the assembly and alignment of satellite multi-band optical sensor. For this study, the wavefront error caused by gravity was analyzed for the opto-mechanical structure of multi-band optical sensor. Wavefront error, an indicator of optical performance, was computed by using the displacements of optics calculated through structural analysis and optical sensitivity calculated through optical analysis. Since the calculated wavefront error caused by gravity exceeded the allocated budget, the gravity compensation technique was required. This compensation technique reduces wavefront error effectively by applying the compensation load to the appropriate position of the housing tube. This method successfully meets the wavefront error budget for all bands. In the future, a gravity compensation equipment applying this technique will be manufactured and used for assembly and alignment of multi-band optical sensor.

• Journal of Astronomy and Space Sciences
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• 제32권3호
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• pp.229-235
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• 2015

We estimated the orbit of the Communication, Ocean and Meteorological Satellite (COMS), a Geostationary Earth Orbit (GEO) satellite, through data from actual optical observations using telescopes at the Sobaeksan Optical Astronomy Observatory (SOAO) of the Korea Astronomy and Space Science Institute (KASI), Optical Wide field Patrol (OWL) at KASI, and the Chungbuk National University Observatory (CNUO) from August 1, 2014, to January 13, 2015. The astrometric data of the satellite were extracted from the World Coordinate System (WCS) in the obtained images, and geometrically distorted errors were corrected. To handle the optically observed data, corrections were made for the observation time, light-travel time delay, shutter speed delay, and aberration. For final product, the sequential filter within the Orbit Determination Tool Kit (ODTK) was used for orbit estimation based on the results of optical observation. In addition, a comparative analysis was conducted between the precise orbit from the ephemeris of the COMS maintained by the satellite operator and the results of orbit estimation using optical observation. The orbits estimated in simulation agree with those estimated with actual optical observation data. The error in the results using optical observation data decreased with increasing number of observatories. Our results are useful for optimizing observation data for orbit estimation.