• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2010.05a
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• pp.552-553
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• 2010

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2010.05a
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• pp.191-192
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• 2010

• Bulletin of the Korean Space Science Society
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• 2007.10a
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• pp.121-121
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• 2007

• Journal of Satellite, Information and Communications
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• v.10 no.3
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• pp.121-126
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• 2015

This paper proposes a novel reconfigurable microstrip antenna based on alternating a perturbation structure to achieve circular polarization diversity. The proposed antenna consists of an annular ring microstrip radiator for simultaneously loading stub and slot perturbations which support right- and left-handed circular polarization senses and two PIN diodes for choosing the operating polarization sense. By controlling the states of two PIN diodes between perturbing slot and stub at one diagonal corner of the radiator, reconfigurable circular polarization senses of the proposed antenna are successfully obtained and alternated. The proposed antenna has been theoretically analyzed and experimentally demonstrated at 2.4 GHz of S-band for satellite communication system. The simulation and measurement results of the proposed antenna show in good agreement with the reflection coefficients, axial-ratios, realized antenna gains, and radiation patterns.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.5
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• pp.432-439
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• 2015

MEMS solid thruster module is composed of solid thruster and its control board. It was developed for the purpose of an academic research. Therefore, thermo-mechanical design and verification for space usage were not considered in the design phase. To mount it on a cube satellite without any design modification, technical efforts at the system level structure design is required. In this study, we proposed a structural design concept to mount the MEMS thruster module by using brackets for guaranteeing structure safety under launch loads and easier mating and de-mating of MEMS thruster module during test phase. The effectiveness of the design has been verified through structural analysis and vibration test. In addition, electrical connection method using spring pins between MEMS thruster and control board is effective for guaranteeing the structural safety under launch vibration loads.

• Journal of Aerospace System Engineering
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• v.12 no.4
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• pp.98-105
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• 2018

The satellite is exposed to various launch environments such as random vibrations and shock. Accordingly, structural design of electronic equipment mounted on satellite must meet reliability requirements at the box level. In addition, it is essential to secure the reliability of the solder joint applied to electronic equipment. In this paper, we performed a modal and quasi-static analysis for the purpose of satisfaction of the design requirements of the CCB (Camera Controller Box) present on the 500 kg-class compact advanced satellite (CAS500). In addition, structural safety of electronic components was verified by the Steinberg's method and random equivalent static analysis.

• The Journal of Korean Institute of Communications and Information Sciences
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• v.39C no.4
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• pp.380-386
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• 2014

In this paper, a higher-order mode coupler using coaxial-structure waveguide for Ku-band monopulse satellite tracking is proposed. The proposed higher-order mode coupler is built in a coaxial structure for compactness and weight reduction, making it suitable for mobile tracking systems. The inner circular waveguide of coaxial-structure is used to extract the fundamental mode signal and the high-order mode signal is extracted from the four slots of the outer circular waveguide and then transmitted via given stepped rectangular waveguide structure. The simulated results show that proposed higher-order mode coupler covers 250 MHz(12.75 GHz ~ 13.00 GHz) bandwidth with return loss and insertion loss characteristics. The antenna patterns of fundamental mode and higher-order mode applicable to monopulse tracking are generated successfully. Designed higher-order mode coupler using coaxial waveguide structure for Ku-band is expected to be used for high precision monopulse satellite tracking systems.

• Korean Journal of Remote Sensing
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• v.27 no.4
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• pp.495-506
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• 2011

COMS In-Orbit Tests(IOT), performed from July, 2010 to Jan, 2011, were successfully completed and the scientific data from MI and GOCI has been distributed officially from April, 2011. This paper focuses on the geometric calibration system tests conducted during the IOT. The geometric calibration process, which is one of the primary objectives of the IOT is the final step of COMS data pre-processing. The basic principles of the geometric calibration (or image navigation and registration, INR) algorithm for COMS are described and the functional and performance tests of COMS INR system were summarized according to the COMS IOT phases. Final performance testes were carried out using data sets acquired from the real-time COMS data pre-processing system. Geometric calibration accuracy of the COMS data showed excellent quality and met requirement specifications.

• Proceedings of the Korean Vacuum Society Conference
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• 2015.08a
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• pp.130-130
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• 2015

플라즈마를 이용한 cleaning, etching, sputtering 공정에서 발생하는 마이크로아크방전이나 turn-off후의 잔류정전기는 공정대상물의 절연파괴나 전자소자에 전기적 손상을 유발함으로서 공정의 불량률을 증가시키는 중요한 요인이 된다. 본 연구에서는 잔류정전기를 관찰하기위하여 실린더형 챔버구조의 평행평판 전극구조를 지닌 용량결합형 플라즈마에서 powered electrode에 부착된 유전체 기판 표면의 잔류 정전기의 변화 양상을 planar type probe로 측정해보았다. 300mtorr 압력에서 아르곤가스로 발생시킨 플라즈마가 존재할 때 낮은 음전위 평균값을 가지던 기판표면 전위가 전력인가가 중지되었을때 20V 가량의 양전위를 가질 수 있음을 측정 하였고, 이것을 COMSOL MULTIPHYSICS TOOL을 활용한 시뮬레이션과 비교하였다. 이 현상이 파워인가 전극이 플라즈마 영역에 노출되느냐에 따라 발생할 수 있음을 알게 되었고, 그 크기와 지속시간은 입력전력 및 블로킹 커패시터와 유전체 기판의 정전용량에 의존함을 확인 하였다.

• Proceedings of the KIEE Conference
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• 2006.10c
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• pp.407-409
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• 2006

우주발사체I 상단 시스템은 비행 중에 킥 모터 점화, 위성분리와 같은 HBW 점화기 기폭이 순차적으로 발생 한다. HBW 점화기의 기폭시에는 일반적으로 전도성 구조물을 통한 단락전류가 일시적으로 발생한다. 이러한 단락전류는 구동 전원 측으로 최대 전류 값 및 루프 면적에 비례한 일시적인 자기장을 형성시키고 near 필드(${\lambda}/2{\pi}$) 내의 인접하게 위치한 하니스에 자계 결합을 통한 역기전력 발생의 원인이 될 수 있다. 이러한 인접 하니스에 자계 노이즈 결합은 여러 자료를 통해 우주시스템 환경에서 일시적인 데이터 손실의 원인이 되는 것으로 분석되고 있다. 본 논문은 우주발사체의 HBW 점화기 기폭시 발생되는 전도성 구조물 단락전류 귀환현상으로 인한 자계노이즈 분석 및 감쇄방안에 대해 논의하고자 한다.