• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.5
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• pp.490-495
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• 2009

A small Hall-effect thruster with a thrust range near 10 mN and a specific impulse of about 1500 s has been designed to control or maintain the orbits of small satellites. The thruster system consists of a hall-effect thruster head, a power processing unit and a Xenon (Xe) gas feed system. The total mass, the consumed electric power and the efficiency of the thruster are approximately 10 kg, 300W and 30%, respectively. Analyses results that support the selection of the thruster for small satellites are provided along with a brief description of the thruster system.

• Journal of the Korean Society of Propulsion Engineers
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• v.26 no.2
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• pp.40-46
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• 2022

Hall thrusters are one of the electric propulsion, where ions are accelerated to generate thrust and are widely utilized in space missions due to their high specific impulses. Recently, as the utilization of small and micro satellites with the mass of similar or less than 100 kg is highly increasing, the importance of research and development of the low-power electric propulsion is also raised. In this study, we developed two sub-200 W or less class, laboratory model Hall thrusters and measured the thrust and analyzed the discharge characteristics. Consequently, we obtained 2.5-9.0 mN of thrust, 600-1,150 s of specific impulse, and 15-28% of anode efficiency at 50-175 W of anode power.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.5
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• pp.93-98
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• 2005

An Engineering Model(EM) of the Telemetry-Command Unit(TCU) for STSAT-2 was developed. The TCU of STSAT-2 has some improved features compared with that of STSAT-1. To reduce weight and size of TCU all logics are implemented in FPGA without CPU. EM I&T(Integration and Test) was successfully performed with no errors.

• The Bulletin of The Korean Astronomical Society
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• v.37 no.2
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• pp.192.2-192.2
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• 2012

위성시스템 소형화, 탑재체 수용증대, 발사비용절감, 탐사임무 효율화 등의 요구로 인하여, 위성 설계에 있어 경량화는 오랜 기간 진행되어온 연구 주제였다. 이러한 연구결과로서, 위성 구조체를 복합재료로 대신하기 위한 구조 경량화 연구와 적용이 성과를 거두었으며, 현재 위성체 프레임이나 전개형 안테나, 광학구조물 등에 경량 탄소섬유 강화 복합재료의 적용은 보편화되어 있다. 한편, 위성시스템에서 전력, 통신, 명령/데이터처리, 자세제어 및 관측기기의 각종 전자장비를 보호하는 하우징 구조물에는 여전히 금속재료가 광범하게 적용되고 있다. 특히, 알루미늄 합금은 하우징 재료로 널리 사용되는데, 강도, 강성, 열전달, 우주방사, 전기전도도 및 EMI 차폐특성과 더불어 가공성이 우수하다는 장점을 지닌 반면에, 금속재료로서 중량이 상당하여 위성 경량화 관점에서는 한계를 갖게 하는 단점이 있다. 전자장비에 부여된 전자기능 측면에서 보면, 하우징은 기생 구조물로서, 경량으로 제공될수록 전자장비 전체 무게에서 전자유닛만의 무게가 차지하는 전기전자기능비가 향상되고 위성 경량화에 크게 기여할 수 있다. 구조 경량화를 위하여 전자장비 하우징을 경량 복합재로 대체하여 설계 및 제작하였으며, 복합재 하우징의 강도, 강성, 열전달, 우주방사, 전기전도도 및 EMI 차폐를 검증할 수 있는 방법에 대하여 검토하였다.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.7 no.1
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• pp.53-60
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• 1996

The 8W hybrid MIC SSPA has been developed in the frequency range from 14.0 GHz to 14.5 GHz for uplink of KOREASAT's earth station. The whole system was designed of two parts with driving amplifier and high power amplifier to simplify the fabrication process. we reduced weight and volum of power amplifier through arranging the bias circuits in the same housing. The realized SSPA has a small signal gain of $26\pm1dB$within 500 MHz bandwidith, and the input and output return losses are over 7dB and 12dB respectively. The output power of 39.0 ~ 39.2dBm is achieved at the 1dB gain compression point of 14 GHz, 14.25 GHz, and 14.5 GHz. That reveals higher power than 8W of design target. The proposed SSPA manufacture techni- ques in this paper can be applied to the implementation of power amplifiers for some radars and SCPC.

• The Journal of Korean Institute of Communications and Information Sciences
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• v.37 no.8C
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• pp.637-644
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• 2012

In this paper, a new compact power divider is suggested. Instead of the quarter wavelength transmission line(TX-line)s for the branches of the conventional Wilkinson's power divider design method, we use our composite right- and left-handed(CRLH) TX-line zeroth order resonator(ZOR) bandpass filters of one twelfth wavelength and reduce the physical length of the power divider. Besides, the filters in the branches can secure the passband for power-division. To validate the proposed power divider, we take an L-band for millitary satellaite transponder as the test case and the performances of the circuit and full-wave simulation results with the CRLH properties of the structure are shown with the dispersion curve and E-field at the ZOR. The measurement is compared with the simulation results. Also, the size reduction effect by the proposed scheme is addressed

• Journal of Satellite, Information and Communications
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• v.12 no.4
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• pp.110-114
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• 2017

Using a small mobile wireless network as a supplement to the disaster safety network can be useful for eliminating small radio shadowing areas, reducing traffic overloads in disaster areas, and quickly building a disaster communication network in difficult access areas. Potable base station is needed to build a small mobile wireless network, and the portable base station using TVWS(TV White Space) is effective in terms of utilization of radio frequency resources and construction cost of wireless networks. In this paper, we design and implement a power amplifier for portable base station operating in TVWS. The implemented power amplifier operates at 470 ~ 698MHz. The gain of the implemented amplifier is more than 20.1dB, the input/output return loss is more than 11.4dB, and the isolation is more than 39.9dB when the output is off. The IMD characteristic of the power amplifier has characteristics of 61.0dBc with 18.8dBm output at 470MHz, 59.3dBc wih 18.6dBm output at 550MHz and 56.5dBc with 19.0dBm output at 690MHz. The power amplifier implemented in this paper can be used as a power amplifier for portable base station.

• Journal of Astronomy and Space Sciences
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• v.13 no.2
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• pp.41-51
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• 1996

KITSAT-1 and 2 are microsatellites weighting 50kg and all the on-board data are processed by the on-board computer system. Hence, these on-board computers require to be highly reliable and be designed with tight power consumption, mass and size constraints. On-board computer(OBC) systems for KITSAT-1 and 2 are also designed with a simple flexible hardware for reliability and software takes more responsibility than hardware. KITSAT-1 and 2 on-board computer system consist of OBC 186 as the primary OBC and OBC80 as its backup. OBC186 runs spacecraft operating system (SCOS) which has real-time multi-tasking capability. Since their launch, OBC186 and OBC80 have been operating successfully until today. In this paper, we describe the development of OBC186 hardware and software and analyze its in-orbit operation performance.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.4
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• pp.413-418
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• 2009

The S-band Transponder for telemetry and command of small satellite is designed and fabricated as prototype model using COTS(Commercial Off-The-Shelf) components. QPSK modulator and demodulator of transponder is implemented by using FPGA for system extension. The transponder consists of RF Front End, RF Modulator, RF Demodulator, and MODEM. The measured results of fabricated transponder show BER of less than $1.1{\times}10^{-6}$ at -105 dBm input power.

• Proceedings of the Korean Vacuum Society Conference
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• 2016.02a
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• pp.192.2-192.2
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• 2016

전기추력기는 화학식 추력기에 비해 비추력이 높아 인공위성의 자세제어, 궤도수정, 궤도천이를 포함한 행성 탐사활동 및 우주 임무수행을 위한 우주선의 엔진 등으로 다양하게 활용된다. 홀 추력기는 전기추력기 중 하나로 고리형 방전공간을 가진 고리형 추력기와 원통형 방전영역을 가진 원통형 추력기가 있으며, 원통형 추력기는 고리형에 비하여 넓은 방전공간으로 저전력 방전에 적합한 추력기이다. 또한, 저전력 추력기는 큐브셋(cubesat) 및 마이크로 위성(microsatellite)의 증가하는 수요에 따라 필요성이 증가하고 있으며, 활용도가 높아 다양하게 연구 및 개발되고 있다. 홀 추력기는 자기장과 전기장을 서로 수직되게 인가하여, 자화된 전자는 플라즈마 방전을 유지시키고 자화되지 않은 이온은 전기장 방향으로 가속되어 이온빔을 발생시킨다. 하지만, 저전력 소형 추력기는 작은 소모전력과 방전채널로 인한 성능 저하 및 자기장 구조 설계 등 많은 어려움들을 가지고 있다. 본 연구에서는, 약 50 W급의 소모전력을 바탕으로 영구자석을 이용한 저전력 플라즈마 추력기를 개발하였다. 방전 채널은 지름 15 mm, 길이 16 mm, 무게는 약 0.6 kg으로 원통형 구조의 채널로 제작되었으며, 약 1500-2000 G의 자기장 세기를 갖도록 설계하였다. 방전 기체는 제논을 사용하여 1-5 sccm영역에서 방전 특성을 살펴보았으며, 방전 전류는 0.02-0.4 A로 나타났다. 100-550 V영역에서 방전을 시도하였고, 채널길이를 16-24 mm 에서 약 1mN 급의 추력특성을 보였다. 본 발표에서, 홀 추력기의 제작 특성과 성능 및 플라즈마 특성에 대한 더 자세한 연구결과가 발표될 예정이다.