• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.8
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• pp.735-740
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• 2007

Star sensor provides highly accurate attitude information by imaging the stars in the dark space. The sensor output is disabled when the sensor avoidance of the Sunlight or the Earth's albedo is not satisfied. This paper studies the Sun and Earth avoidance characteristics of the star sensors according to the mounting direction. Then the paper proposes a systematic way of determining the star sensors mounting direction for typical remote sensing missions

• Proceedings of the KAIS Fall Conference
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• 2009.12a
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• pp.640-644
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• 2009

현재 태양광 산업에서는 고정식 태양광 발전장치보다 발전 효율이 우수한 추적식 태양광 발전장치를 개발하는 연구가 활발하게 진행되고 있다. 추적식 태양광 발전장치는 고정식에 대비하여 단위면적당 일사량을 최대로 유지할 수 있을 뿐만 아니라, 일조시간을 최대로 하여 태양전지의 발전효율을 극대화할 수 있다. 따라서 정밀하면서도 저렴한 태양위치 추적장치는 태양광 발전사업의 경제성을 높이고, 성능 대비 투자비용을 낮춰 태양광 발전설비의 보급을 촉진시켜줄 수 있는 중요한 기술이다. 본 연구는 태양위치를 감지하는데 센서를 사용하지 않고 천문학과 수학을 이용하여 정밀도 1분($0.016^{\circ}$)이내의 태양위치를 계산하는 알고리즘에 관한 것이다. 본 연구에서 제안하는 알고리즘은 장치의 제작비용을 낮추어 줄 뿐 아니라, 발전효율도 높여준다. 구현된 알고리즘을 적용시킨 추적식 태양광 발전장치를 운용 실측한 결과, 최대 30초($0.0038^{\circ}$)의 오차를 보여 추적식 발전장치의 경제성을 높일 수 있고, 시간복잡도(Time Complexity)와 공간복잡도(Spatial Complexity)가 낮아 실시간 태양 추적장치에 최적임을 확인하였다.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 2012.05a
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• pp.239-240
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• 2012

• 한국신재생에너지학회:학술대회논문집
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• 2010.06a
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• pp.92.1-92.1
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• 2010

본 기술개발은 기존 태양추적기의 구조를 크게 변화시킬 수 있는 무선망 활용 태양추적기 개발에 관한 내용이다. 기존의 태양추적기는 태양광어레이에 스탠드얼론 시스템으로 부착되어 태양추적 및 관련 제어기능을 수행한다. 그러나 본 무선망활용 태양추적기는 PC와 태양광어레이가 지그비 무선망으로 연결되는 구조이다. 무선망을 활용함으로서 기존 태양추적기 대비 제어모듈의 역할이 매우 단순화되어 장치의 강건함, 내구성 및 경제성이 증가되는 효과가 있다. 무선망을 활용함으로서 태양광에레이 측은 무선데이터 송수신 기능과 모터제어 부분만 구현되어도 되며 나머지 기능들은 PC에서 처리해서 무선으로 태양광에레이 모듈에게 전달된다. 또한 고가의 센서 등도 PC에만 구현되고 필요한 데이터는 PC에서 처리하고 계산해서 무선으로 태양광어레이에게 전달하는 구조이다. 그리고 태양추적을 위한 정밀한 자동제어 알고리즘도 PC에서는 충분히 구현할 수 있으며 이를 수행한 후 필요 데이터를 태양광어레이 모듈에게 무선으로 전달한다. 본 기술개발 내용에 대한 시제품이 완성단계에 있으며 필드테스트 수행을 준비하고 있다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.4
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• pp.40-46
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• 2006

It is required to develop a highly reliable attitude & orbit control system of satellite that is less expensive as the technology of satellite design & integration is recently matured dramatically. To accomodate this kind of needs, the two axis attitude control method for wheel-based momentum-biased satellite system whose momentum bias vector points to a certain direction(sun direction), is developed using simple but reliable sensors and actuator: three axis magnetometer and coarse sun sensor are used as sensors, and magnetic torque bars are used as actuator. Classical PD type controller design methodologies are applied on a satellite system for the two axis control with the proper assumptions. Nonlinear simulation results are included to demonstrate the long term stability and the performance of closed-loop system design results.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.10
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• pp.836-843
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• 2017

In lunar exploration, the necessity of utilizing rover is verified by the examples of the Soviet Union and China and the similar Mars missions of the United States. In order to achieve the successful management of a lunar rover, a high precision navigation technique is required, and accordingly, high precision initial alignment is essential. Even though it is general to perform initial alignment in a steady state, a multiposition alignment technique is applied when high performance is needed. On the lunar surface, however, the performance of initial alignment decreases from that on Earth, and it cannot be improved by applying multiposition alignment method owing to certain constraints of lunar environment. In this paper, a sun sensor aided multiposition alignment technique is proposed. The measurement model for a sun vector is established, and its observability analysis is performed. The performance of the proposed algorithm is verified through computer simulations, and the results show the estimation performance is improved dramatically.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.11 no.7
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• pp.2334-2340
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• 2010

Sun position computed by Michalsky shows maximum $1.5^{\circ}$, $0.88^{\circ}$ and 2 minutes differences in azimuth, altitude, and sunrise and sunset times respectively compared with Korean Almanac. The 2-axis solar tracking system, which consist control panel with ATmega128 CPU, BLDC motor-cylinder actuator and 2-axis link mechanism, was developed. Computed azimuth and altitude of sun for a current time, and latitude and longitude of tracker position built are controlled in real time by BLDC motor-cylinder actuators comparing with the position feed-backed by Hall sensor. The use of BLDC motor is free in maintenance. Implementation of a home-return function by Hall sensor is to minimize the cumulative error.

• Journal of the Korean Solar Energy Society
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• v.21 no.4
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• pp.55-62
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• 2001

A parabolic dish concentrator used in a high temperature application of solar energy tracks the sun's movement by two axis sun tracking system. In such a system, sun tracking performance affects the system efficiency directly. Generally the higher the tracking accuracy is, the better the system performance is. A large number of parabolic dish type concentrators has been developed and implemented in the world. However none of them clearly provided a qualitative method of how the accuracy of the sun tracking system can be evaluated. The work presented here is the evaluation of sun tracking performance of parabolic dish concentrator, which follows the sun's movement by the sensor, using a computer vision system. We install a camera on the parabolic dish concentrator. While the concentrator follows the sun, sun's images are captured continuously. Then the performance of sun tracking system was evaluated by analyzing the variation of the position of the sun in the captured images.

• Aerospace Engineering and Technology
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• v.5 no.2
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• pp.90-101
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• 2006

In this paper, the calibration parameters of the gyros and star hackers are estimated by using an on-orbit AOCS sensor calibration algorithm. The calibration algorithm was implemented by Kalman filter. In order to estimate gyro calibration parameters, the calibration algorithm requires calibration maneuver and it was analyzed whether the star trackers are protected by Sun, Moon and Earth or not. Also the star tracker calibration algorithm used the camera image information. This kinds of camera image information simulated ground control point and orbit information. The estimated accuracy of star tracker calibration parameters depends on camera image information.

• Aerospace Engineering and Technology
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• v.9 no.2
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• pp.36-43
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• 2010

A GEO satellite launched by Arian 5 ECA launcher will be located in a transfer orbit where it requires several Apogee burn maneuvers to reach the target orbit. To obtain the required performance of Apogee burn maneuvers, a calibration of gyro drift error needs to be performed before each maneuver. In this paper, a unique gyro calibration scheme which is applied to COMS is described and the calibration error budget analysis is performed.