• Proceedings of the KIEE Conference
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• 1995.07b
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• pp.907-909
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• 1995

The SaTReC is to develop, deploy, and operate a low Earth orbiting small satellite system, KITSAT-3, carrying a remote sensing payload, a space science payload, and a data collection system. Through the development of KITSAT-3, the SaTReC is to demonstrate the small satellite system which provides highly accurate attitude control, high speed data transmission, and a unique spacecraft configuration and to provide educational opportunities to Korean space industries and research institute. The KITSAT-3 is expected to be launched in the beginning of 1997 by Chinese Long March IV as a secondary payload into about 800 km's sunsynchronous orbit.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.19 no.3
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• pp.10-15
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• 2011

The separation actuator for the small satellite should fix satellite appendages with high clamping force. After operation, it has to be separated from the satellite body without any damage on satellite system and release the appendages such as a solar panel and an antenna successfully. Therefore, we invent a non-explosive separation actuator for the small satellite which generates low shock and is resettable. In order to confirm performance of the proposed separation actuator, we carried out experiments for separation time, maximum preload for activation, and shock level.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.1
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• pp.93-103
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• 2005

SEDT(System Engineering Design Tool) has been developed for small satellite conceptual design with an aim to verifying the nanosatellite HAUSAT-2 design. The program can calculate the mass and power of whole satellite system having specific mission and estimate the system cost based on mission and user requirements. It is containing various analysis data of more than 200 small satellites. The database will provide the trend analysis results of the small satellites which will become important design factors. This tool has also been verified by applying more than 10 small satellite data through case studies.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.9
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• pp.771-780
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• 2012

Naro-science satellite which will be launched by KSLV-1 has been successfully developed. Naro-science satellite is a 100kg-class small size science satellite whose structure is composed of one of a typical light and high strength aluminum honeycomb sandwich panel. In this research, dynamic responses of the satellite with respect to the design requirements were investigated by means of real experiments and numerical finite element analyses. The core technologies of the structure design and analysis about fracture and safety has been obtained through a wide range of analyses and tests. The results obtained in this study can be significantly utilized for the next generation satellite development.

• 제어로봇시스템학회:학술대회논문집
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• 2000.10a
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• pp.458-458
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• 2000

Quick evaluations of two in-plane orbit maneuvers using small see of real-time CPS navigation solutions were peformed lot the KOMPSAT-1 spacecraft operation. Real-time GPS navigation solutions of the KOMPSAT-1 were collected during the Korean Ground Station(KGS) pass. Only a few sets of position and velocity data after completion of the thruster firing were used for the quick maneuver evaluations. The results were used for antenna pointing data predictions for the next station contact. Normal orbit maneuver evaluations using large see of playback GPS navigation solutions were also performed and the result were compared with the quick evaluation results.

• Journal of Mechanical Science and Technology
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• v.19 no.spc1
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• pp.473-480
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• 2005

A three axes marine satellite antenna has been developed. As a design step, a CAD model for the antenna has been created according to the design requirements. Kinematic analyses are carried out to insure design specification and to check collision detection of the CAD model. Marine satellite antennas experience base motions, and a relevant control system should control the three antenna axis to point to the satellites accurately. A sensor fusion algorithm and a PIDA (Proportional, Integral, Derivative, Acceleration) control algorithm are designed and implemented to control the yaw, level, and cross-level angle of a small size satellite marine antenna. Antenna stabilization control experiments are performed using a test simulator which gives the antenna base motions. Experimental results show small pointing errors, which is less than 0.2 degree for the level, cross-level, and yaw axis.

• Journal of the Korean Solar Energy Society
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• v.37 no.5
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• pp.49-63
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• 2017

Solar cells have widely been utilized for a satellite to convert sunlight energy into electricity in space. Many different types of solar cells appropriate for each satellite program are available in current markets, which enables us to construct a solar array light and small often required from a low Earth orbit (LEO) synthetic aperture radar (SAR) satellite. Thus, it is important to choose a proper solar cell satisfying the requirements of mass and size for the solar array. In this article, we have surveyed typical suppliers and have discussed some characteristics of solar cells. Conceptual design examples of the solar array for LEO SAR satellites using several types of solar cells have been performed to show the pros and cons of solar cells by comparison of the total mass and size necessary for the solar array.

• Journal of Astronomy and Space Sciences
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• v.22 no.1
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• pp.47-58
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• 2005

This paper addresses development of the ultra-light analog sun sensors for small satellite applications. The sun sensor is suitable for attitude determination for small satellite because of its small, light, low-cost, and low power consumption characteristics. The sun sensor is designed, manufactured and characteristic-tested with the target requirements of ${\pm}60^{\circ}$ FOV (Field of View) and pointing accuracy of ${\pm}2^{\circ}$. Since the sun sensor has nonlinear characteristics between output measurement voltage and incident angle of sunlight, a higher order calibration equation is required for error correction. The error was calculated by using a polynomial calibration equation that was computed by the least square method obtained from the measured voltages vs. angles characteristics. Finally, the accuracies of 1-axis and 2-axes sun sensors, which consist of 2 detectors, are compared.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.10
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• pp.80-91
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• 2006

A method of multidisciplinary education has been implemented for satellite design, based on HAUSAT-1 and 2 ultra-small satellite development projects, in order to provide practical knowledge and experience to students studying satellite engineering. HAUSAT-1 was the nation's first 1kg-class ultra-small satellite. HAUSAT-2 nano-satellite is currently under a Proto-Flight Model development. These design projects make it possible to achieve the goal of science and technical research, which is representative of a university function, and the goal of molding professionals through providing an integrated function of system design education. An integrated system design, like satellite system, provides all participating students with an opportunity to directly/indirectly experience the entire system development process and encourage growth of multidisciplinary system education that has lately become an important issue.

• Journal of Aerospace System Engineering
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• v.12 no.3
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• pp.9-17
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• 2018

For Earth observation, a small satellite camera has relatively weak structural stability compared to medium-sized satellite, resulting in misalignment of optical components due to severe launching and space environments. These alignment errors can deteriorate the optical performance of satellite cameras. In this study, we proposed a 3-axis focus mechanism to compensate misalignment in a small satellite camera. This mechanism consists of three piezo-electric actuators to perform x-axis and y-axis tilt with de-space compensation. Design requirements for the focus mechanism were derived from the design of the Schmidt-Cassegrain target optical system. To compensate the misalignment of the secondary mirror (M2), the focus mechanism was installed just behind the M2 to control the 3-axis movement of M2. In this case, flexure design with Box-Behnken test plan was used to minimize optical degradation due to wave front error. The wave front error was analyzed using ANSYS. The fabricated focus mechanism demonstrated excellent servo performance in experiments with PID servo control.