• Aerospace Engineering and Technology
• /
• v.9 no.1
• /
• pp.42-49
• /
• 2010

CSSA(Coarse Sun Sensor Assembly) is the essential sensor for satellite attitude control. CSSA measures the direction of the sun's rays and determines whether the satellite is in the eclipse or not. The paper shows the development process and test results of CSSA flight model for low earth orbit satellite. After analyzing the functional test results, we can make a decision whether the unit meets the requirements. We needs the definite and precision procedure and lots of experience. We could improve those through the development of Qualified Model for CSSA and so obtain the results to meet the functional requirement at the Flight model.

• Aerospace Engineering and Technology
• /
• v.10 no.2
• /
• pp.87-93
• /
• 2011

FSSA(Fine Sun Sensor Assembly) is the important sensor for satellite attitude control. FSSA measures the direction of the sun's rays and determines whether the satellite is in the eclipse or not. FSSA for GEO Satellite is also used to acquire the attitude error information in the attitude control reference frame and acquire the Sun direction during transfer orbit or mission Process. This paper shows the configuration of Fine Sun Sensor for LEO and GEO Satellite and their principle of operation that angle measurement is obtained by using the transfer function which is the ratio of the difference between output currents of Solar Cell to the sum of all output currents.

• Current Industrial and Technological Trends in Aerospace
• /
• v.7 no.2
• /
• pp.121-130
• /
• 2009

In this paper, the attitude and orbit control subsystem technology of new GEO communication and observation satellite using Sun sensors are introduced and analyzed. COMS is new GEO communication and Earth observation satellite based on EUROSTAR 3000 space bus technology. The attitude and orbit control subsystem of COMS adopts a configuration using three BASS and three LIASS Sun sensors to acquire the attitude error information in the specific reference frames. These Sun sensors are used to acquire Sun direction and to control the spacecraft to keep the relative attitude with respect to a reference Sun direction in both transfer and operational orbits. In this paper, the mathematical models of BASS and LIASS are described as well as their operational implementation in the flight software.

• The Bulletin of The Korean Astronomical Society
• /
• v.37 no.2
• /
• pp.231.1-231.1
• /
• 2012

한국해양과학기술원 해양위성센터에서 주관운영을 수행하고 있는 천리안 위성의 해양탑재체인 천리안 해양관측위성(이하 GOCI)은 정지궤도위성용 해색센서로서, 태양을 광원으로 지구상의 해수 표면 부근에서 반사되어 대기를 통과한 가시광 및 근적외 대역을 8개 밴드로 분광하여 관측하는 센서이다. 해색센서의 경우, 일반적으로 센서에 입사되는 광신호의 약 90%가 대기에 의한 신호이며, 약 10%에 해당되는 신호만 원래 관측목적인 해수에 의한 신호이기 때문에, 5% 이내의 높은 복사보정 정확도가 요구된다. 이러한 높은 복사보정 정확도를 만족시키기 위해서는, 지상에서의 현장관측을 통한 위성자료 검보정 뿐만 아니라, 발사 후 위성 궤도상에서 센서의 복사보정을 수행하는 궤도상 복사보정이 체계적으로 수행되어야 한다. GOCI는 태양을 기준광원으로 하는 태양광 복사보정을 채택하여, 센서의 셔터부에 태양광 복사보정을 위한 2개의 태양광확산기(Solar Diffuser)를 장비하고 있다. 본 발표에서는 궤도상 시험 후 약 16개월에 걸친 궤도상 복사보정 운영결과와 관련하여, 발사 후 일별, 월별, 계절별 등 각 기간별 센서의 이득변화를 관찰하였으며, 그 결과 1년을 기준으로 약 3% 범위로 주기적인 이득 변화가 있음을 확인하였다. 지상시험결과와의 비교에 의해, 태양광확산기에 대한 태양입사각이 이러한 주기적인 이득 변화의 주 원인임을 궤도상 복사보정 운영결과를 통해 밝히고자 한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.35 no.11
• /
• pp.1043-1051
• /
• 2007

The digital sun sensor calculates the incident sunlight angle using the sunlight image registered on a CMOS image sensor. In order to accomplish this, an exact center of the sunlight image has to be determined. Therefore, an accurate estimate of the centroid is the most important factor in digital sun sensor development. The most general method for determining the centroid is the thresholding method, and this method is also the simplest and easy to implement. Another centering algorithm often used is the image filtering method that utilizes image processing. The sun sensor accuracy using these methods, however, is quite susceptible to noise in the detected sunlight intensity. This is especially true in the thresholding method where the accuracy changes according to the threshold level. In this paper, a template method that uses the sunlight image model to determine the centroid of the sunlight image is suggested, and the performance has been compared and analyzed. The template method suggested, unlike the thresholding and image filtering method, has comparatively higher accuracy. In addition, it has the advantage of having consistent level of accuracy regardless of the noise level, which results in a higher reliability.

• Journal of the Korea Institute of Information and Communication Engineering
• /
• v.13 no.9
• /
• pp.1913-1920
• /
• 2009

An intelligent accurate sun tracking controller for solar lighting system was developed. This controller can detect the faulty sensor and correct the error signal based on Principle Component Analysis theory. A fuzzy controller was developed to control the tracker by using the collected sensor signal for precise position control. Also a multiple range searching sensor module for sun tracking was designed. To show the validity of the developed system, some experiments in the field were illustrated.

• Proceedings of the KIEE Conference
• /
• 2011.07a
• /
• pp.1354-1355
• /
• 2011

화석에너지의 유한성과 공해문제로 인해 대체에너지 개발에 대한 관심이 고조되는 가운데 태양광발전과 풍력발전이 그 중에서 가장 활발하게 연구되고 실제 이용비율도 상당히 높은 편이다. 이는 외기 기후변화에 대한 상대적인 보완성을 가진 두 가지 형태의 에너지원으로부터의 에너지변환과정으로 인해 그 이용이 더욱 부각되고 있다. 기존의 풍력발전시스템, 태양광발전시스템 또는 풍력/태양광 복합발전시스템 중 대형발전시스템의 경우는 일사량센서나 풍속센서를 부착하여 최대 출력점 제어나 외기환경 인식을 위해서 일사량이나 풍속과 같은 외기환경정보를 획득하여 사용하며 이를 교육용 또는 외기환경정보를 분석하는데 이용하기도 하고, 다양한 표시장치를 통해 표시하기도 한다. 그러나, 일사량센서나 풍속센서는 고가의 센서로 대형 태양광발전시스템이나 풍력발전시스템에서는 여러 개소의 설치를 통해 보다 정확한 정보를 획득해야 하며, 이를 위해 많은 개수의 센서가 필요하다. 현실적으로 여러 개의 센서는 고가의 설치 비용으로 인해 샘플링을 위해서만 설치될 뿐 발전시스템의 설치사이트의 다양한 분석이 어려운 점이 있었다. 본 논문에서는 풍속센서나 일사량센서 없이 태양전지모듈로부터 직접 일사량을 검출하는 방식의 일사량 정보획득과 풍력발전시스템에서의 풍속정보를 획득하는 방법을 제안한다.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
• /
• 2011.10a
• /
• pp.843-845
• /
• 2011

Due to the short lifetime of the battery-based sensor network, study on the environmental energy-harvesting sensor network is being performed widely. In this paper, we analyze the system-level requirements on the sensor node which is needed for the efficient solar-powered wireless sensor network for the target application. In addition, we explain how the HW/SW components of our real solar-powered sensor node can satisfy the requirements mentioned above.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.33 no.10
• /
• pp.93-97
• /
• 2005

We have developed the FDSS (Fine Digital Sun Sensor) for the space technology of the STSAT-2 (Seience & Technology Satellite 2). The FDSS is firstly developed by using CMOS image sensor(CIS) in South Korea. The FDSS consists of the optics part, FPGA(Field Programable Gate Array) part, and MCU(Micro controller unit)part. This paper will focus on the optical characteristics of the optics part and describe the configuration of FDSS with the design of aperture. We also analyze the characteristic of optics about the pixel of the CMOS image sensor.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.35 no.5
• /
• pp.460-465
• /
• 2007

This paper deals with the Fine Digital Sun Sensor (FDSS) for Science & Technology Satellite 2(STSAT-2). The FDSS was firstly developed by using CMOS-Image sensor(CIS) in South Korea. This paper will describe the configuration of the FDSS, the design of the optical part, the analysis result of the optical characteristics of the sunlight, and the calibration result measured by solar simulator.