• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2005년도 Proceedings of ISRS 2005
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• pp.485-488
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• 2005

The 2nd KOrea Multi-Purpose Satellite (KOMPSAT -2) has been developed by Korea Aerospace Research Institute (KARI) since 2000. Multi Spectral Camera (MSC) is the payload for KOMPSAT -2, which will provide the observation imagery around Korean peninsula with high resolution. KOMPSAT-2 has adopted X-band Tracking System (XTS) for transmitting earth observation data to ground station. For this, data which describes and controls the pre-defined motion of each on-board X-Band antenna in XTS, must be transmitted to the spacecraft as S-Band command and it is called as Tracking Parameter Files (TPF). In this paper, the result of the development of TPF Generation S/W for KOMPSAT-2 X-Band Antenna Motion Control.

• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2004년도 Proceedings of ISRS 2004
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• pp.452-455
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• 2004

MSC (Multi-Spectral Camera) system is a remote sensing instrument to obtain high resolution ground image. EOS (Electro-Optic System) for MSC mainly consists of PMA (Primary Mirror Assembly), SMA (Secondary Mirror Assembly), HSTS (High Stability Telescope Structure) and DFPA (Detector Focal Plane Assembly). High performance of EOS makes it possible for MSC system to provide high resolution and high quality ground images. Temperature of the EOS needs to be controlled to be in a specific range in order not to have any thermal distortion which can cause performance degradation. It is controlled by full redundant CPU based electronics. The validity of thermistor readings can be checked because a few thermistors are installed on each control point on EOS. Various kinds of thermal control logics are used to prevent 'Single Point Failure'. Control logic has a few set of database in order not to be corrupted by SEU (Single Event Upset). Even though the thermal control logic is working automatically, it can also be monitored and controlled by ground-station operator. In this paper, various ways of thermal control logic for EOS in MSC will be presented, which include thermal control mode and logic, redundancy design and status monitoring and reporting scheme.

• 한국위성정보통신학회논문지
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• 제1권2호
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• pp.76-82
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• 2006

한국전자통신연구원이 개발하여 항공우주연구원의 관제소에 설치한 아리랑2호 위성 관제시스템은 지난 7월 28일 발사된 아리랑2호 위성의 운용에 사용되고 있다. 아리랑2호 관제시스템의 대표적인 기능으로는 원격측정데이터 수신 및 처리, 원격명령 생성 및 송신, 위성 추적 및 거리측정, 궤도 예측 및 결정, 위성자세 조정계획, 그리고 위성 시뮬레이션 등이 있다. 아리랑2호 위성은 아리랑1호 위성의 임무를 이어받아 수행하며, MSC (Multi Spectral Camera) 및 정밀궤도결정, 정밀자세결정 등을 통해 아리랑1호에 비해 훨씬 향상된 해상도의 사진을 제공하는 성능을 가지고 있다.

• 항공우주기술
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• 제4권1호
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• pp.211-220
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• 2005

본 연구의 목적은 향후 발사될 KOMPSAT-2 MSC와 유사한 분광특성을 가지는 Landsat ETM+ 영상자료와 동시기에 지상에서 관측한 surface reflectance 자료를 이용하여 영상기반의 대기보정 모델을 검토하는 것이다. 이러한 영상기반의 대기보정은 현장관측 자료가 필요하지 않다는 이점이 있다. TOA reflectance와 현장 관측치 간에 상당한 차이를 보이며, 연구결과는 COST 모델을 기반으로 하는 Case 1이 세 가지 경우 중에서 가장 정확함을 나타냈다. 한편 Case 2_1의 경우 Case 1처럼 정확하나 그 값은 현장 자료보다 낮게 나타났다. 또한 Case 3_1은 일부 밴드에서 관측치와 전혀 상관성이 없는 것으로 나타났다. 향후 IKONOS와 같은 고해상도 영상자료에 본 연구방법을 적용하면 MSC 데이터 특성에 맞는 대기보정 모델을 개발할 수 있을 것으로 판단된다.

• 대한전자공학회:학술대회논문집
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• 대한전자공학회 2003년도 통신소사이어티 추계학술대회논문집
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• pp.378-381
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• 2003

The Channel Coding Unit (CCU) is an integral component of Payload Data Transmission System (PDTS) for the Multi-Spectral Camera (MSC) data. The main function of the CCU is channel coding and encryption. CCU has two channels (I ＆ Q) for data processing. The input of CCU is the output of DCSU (Data Compression ＆ Storage Unit). The output of CCU is the input of QTX which modulate data for RF communication. In this paper, there are the overview, short H/W description and operation concept of CCU.

• Journal of Astronomy and Space Sciences
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• 제20권4호
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• pp.393-402
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• 2003

The Multi-Spectral Camera (MSC) is the payload of KOMPSAT-2 which is designed for earth imaging in optical and near-infrared region on a sun-synchronous orbit. The telescope in the MSC is a Ritchey-Chretien type with large aperture. The telescope structure should be well stabilized and the optical alignment should be kept steady so that best images can be achieved. However, the MSC is exposed to adverse thermal environment on the orbit which can give impacts on optical performance. Solar incidence can bring non-uniform temperature rise on the telescope tube which entails unfavorable thermal distortion. Three ways of preventing the solar radiation were proposed, which were installing external mechanical shield, internal shield, and maneuvering the spacecraft. After trade-off study, internal sun shield was selected as a practical and optimal solution to minimize the effect of the solar radiation. In addition, detailed designs of the structure and sunshield were produced and analyses have been performed. The results were assessed to verify their impacts to the image quality. It was confirmed that the internal sunshield complies with the requirements and would improve image quality.

• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2004년도 Proceedings of ISRS 2004
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• pp.436-439
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• 2004

Output data streams of the MSC contain flags, Headers and image data according to the established protocols and data formats. Especially the Header added to each data lines contain information of a line sync, a line counter and, ancillary data which consist of ancillary identification bit and one ancillary data byte. This information is used by ground station to calculate the geographic coordinates of the image and get the on-board time and several EOS(Electro-Optical Subsystem) parameters used at the time of imaging. Therefore, the EGSE(Electrical Ground Supporting Equipment) that is used for testing MSC has to have functions of interpreting and displaying this Header information correctly following the protocols. This paper describes the design of the header data processing module which is in EOS­EGSE. This module provides users with various test functions such as header validation, ancillary block validation, line-counter and In-line counter validation checks which allow convenient and fast test on imagery data.

• 한국항공우주학회지
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• 제39권12호
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• pp.1150-1159
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• 2011

신뢰도란 임의 시스템이 주어진 운용환경 하에서 의도한 기간 동안 의도된 기능을 정상적으로 수행할 확률로 정의된다. 신뢰도-중복 최적화 문제(RROP)는 비용, 무게 등의 제약내에서 시스템의 신뢰도를 최대화할 수 있는 최적의 부품을 선택하고, 부품수와 중복전략(활성/대기중복)을 결정하는 문제이다. 본 연구에서는 아리랑위성 2호의 다채널광학카메라(MSC) 시스템의 설계 구조를 바탕으로 RROP의 수리모형을 제시하고, NP-hard인 RROP의 해법으로써 병렬 개체군집최적화(PPSO) 알고리즘을 제안하였다. RROP 예제의 수치실험 결과는 계획된 수명기간에서 신뢰도를 최대화하는 시스템의 설계 구조를 제시한다.

• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2003년도 추계학술발표대회 논문집
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• pp.132-136
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• 2003

A Multi-Spectral Camera (MSC) is the payload of KOMPSAT-2 which is designed for earth imaging in visible and near-Infrared region on a sun-synchronous orbit. The telescope in the MSC is a Ritchey-Chretien type with large aperture. The telescope structure should be well stabilized and the optical alignment should be kept steady so that best images can be achieved. However, the MSC is exposed to adverse thermal environment on the orbit which can give impacts on optical performance. Metering structure which is exposed to adverse space environment should have tight requirement of low thermal expansion and hygroscopic stability. In order to meet those stability requirements in addition to fundamental structural ones telescope structure was designed with newly developed graphite-cyanate composite which has high tensile modulus, high thermal conductivity and low moisture absorption compared with conventional graphite-epoxy composite. In this paper, space-borne telescope structure with new composite material will be presented and fulfillment of stability requirements will be verified with designed structure.

• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2002년도 Proceedings of International Symposium on Remote Sensing
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• pp.229-234
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• 2002

Under the hostile influence of the extreme space environmental conditions due to the deep space and direct solar flux, the thermal control in space applications is especially of major importance. There are tight temperature range restrictions for electro-optical elements while on the other hand there are low power consumption requirements due to the limited energy sources on the spacecraft. So, we usually have strong requirement of thermal and power control module in space applications. In this paper, the design concept of a thermal and power control module in the MSC(Multi-Spectral Camera) system which will be a payload on KOMPSATII is described in terms of H/W & S/W. This thermal and power control module, called THTM(Thermal and Telemetry Module) in MSC, resides inside the PMU(Payload Management Unit) which is responsible for the proper management of the MSC payload for controlling and monitoring the temperature insides the EOS(Electro-Optic System) and gathering all the analog telemetry from all the MSC sub-units, etc. Particularly, the designed heater controller has the special mode of "duty cycle" in addition to normal closed loop control mode as usual. THTM controls heaters in open loop according to on/off set time designed through analysis in duty cycle mode in case of all thermistor failure whereas it controls heaters by comparing the thermistor value to temperature based on closed loop in normal mode. And a designed THTM provides a checking and protection method against the failure in thermal control command using the test pulse in command itself.