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

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

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.11
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• pp.1043-1051
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• 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 Korean Society for Aeronautical & Space Sciences
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• v.34 no.7
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• pp.71-78
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• 2006

Sun sensors are frequently implemented by satellites for attitude sensing, due to its simple manufacturability and light weight. A modeling of sun sensors has an important effect on the accuracy of satellite attitude determination. This paper addresses a new modeling of a 2-axis miniature fine sun sensor with improved accuracy. Unlike other previous algebraic modeling methods, the newly suggested physical modeling method takes into account the shadowing effect of the slit thickness. It was shown that a newly proposed sun sensor modeling provides a substantial accuracy improvement of 29% compared to the generic algebraic modeling. The proposed sensor modeling was validated using 2-axis fine sun sensors with FOV(Field of View) of ${\pm}60^{\circ}$ mounted on HAUSAT-2 small satellite, currently under development by SSRL(Space System Research Lab.) at Hankuk Aviation University, Korea.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.10
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• pp.93-97
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• 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 Korea Academia-Industrial cooperation Society
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• v.17 no.11
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• pp.294-301
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• 2016

Recently, the solar tracker has been used to improve the efficiency of solar energy. Solar tracking technologies are classified into the sensor-based method, the program-based method, and the hybrid method. Solar trackers using an AC motor and CdS sensor are low in cost, but the precision of the positions is low, owing to the inertia of the motor and the scattering of sunlight. To compensate for the low precision, we implement a CdS sensor module and propose an AC motor control method using error value. To evaluate the performance of the solar tracker, we implemented a solar water heater. From the experimental results, the solar tracker can achieve ${\pm}2mm$ accuracy for sun, can satisfy ${\pm}15mm$ as a limited error value, and provides a 32% performance enhancement in KSB8202 criteria.

• Journal of Astronomy and Space Sciences
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• v.25 no.4
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• pp.491-504
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• 2008

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 ellipse. The paper shows the development process and test results of Path-finder & Qualified Model CSSA as the preceding development in order to develop the CSSA for low earth orbit satellite. We needs the definite and precision procedure and lots of experience. This paper shows that we can improve those through the development of Path-finder and Qualified Model CSSA. Therefore, we can obtain the results to meet the functional requirement.

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

• Journal of the Korean Society for Precision Engineering
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• v.24 no.6
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• pp.31-36
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• 2007

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