• The Bulletin of The Korean Astronomical Society
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• v.34 no.1
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• pp.110.2-110.2
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• 2009

• Journal of Advanced Navigation Technology
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• v.26 no.6
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• pp.487-495
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• 2022

This paper describes the design and development of a high-power transmit receive module(TRM) for mounting on X-band synthetic aperture radar(SAR) of the NEXTSat-2. The TRM generates a high-power pulse signal with a bandwidth of 100 MHz in the target frequency range of X-band and amplifies a low-noise on the received signal. Tx. path of the TRM has output signal level of more than 200 watts (53.01 dB), pulse droop of 0.35 dB, signal strength change of 0.04 dB during transmission signal output, and phase change of 1.7 ˚. Rx. path has noise figure of 3.99 dB and gain of 37.38 ~ 37.46 dB. It was confirmed the TRM satisfies all requirements. The TRM mounted on the NEXTSat-2 flight model(FM) which will be launched using the KSLV-II (Nuri).

• Korean Journal of Remote Sensing
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• v.14 no.2
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• pp.137-148
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• 1998

An algorithm developed for the precision correction of high resolution satellite images is introduced in this paper. In general, the polynomial warping algorithm which derives polynomial equations between GCPs extracted from an image and a base map requires many GCPs well-distributed over the image. The precision correction algorithm described in this paper is based on a sensor-orbit-Earth geometry, and therefore, it is capable of correcting a raw image using only 2-3 GCPs. This algorithm estimates the errors on the orbit determination and the attitude of the satellite by using a Kalman filter. This algorithm was implemented, tested and integrated into the KITSAT-3 image preprocessing software.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.298-302
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• 2009

Low power Hall thruster is under development as one of the core technologies for STSAT-3. The Hall thruster has several advantages such as its simple structure, high thrust density and specific impulse etc. Development target values deduced by analyzing requirements are consumed electrical power, thrust, thrust efficiency, and specific impulse of < 300 W, > 10 mN, ~ 35%, and > 1000 s, respectively. In order to achieve the target specifications, two prototype Hall thrusters were developed and compared. To date, thrust and efficiency are 11 mN and 37% under the total power of 290 W with 0.97 mg/s Xe propellent supply.

• Bulletin of the Korean Space Science Society
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• 2010.04a
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• pp.32.6-33
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• 2010

현재 우리나라에서는 고해상도 광학관측위성인 다목적실용위성 3호(EO), 3A호(EO/IR)를 개발 중에 있으며, 이들의 개발 현황과 앞으로의 발전 방향에 대한 소개를 하고자 함. 지구표면의 정밀/광역 관측에 큰 장점을 지닌 관측위성은 많은 기술적 난관이 있으며, 이를 극복하기 위한 위성 본체 및 대구경 광학계 기술을 소개하고자 한다. 일반 천문 망원경용 광학계와의 차이점을 위주로 다목적실용위성 3호, 3A호의 위성광학계 설계의 특징과 현재 개발 중인 위성용 카메라의 조립 시험에 대한 현황을 위주로 향후 우리가 나아가야할 방향에 대한 고찰이 있을 예정이다. 또한 위성의 운영 특성과 운영 시 필요한 검보정 (Cal/Val) 과정에 대한 준비 상황도 소개하고자 한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.11
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• pp.1157-1163
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• 2009

This paper introduces the lithium ion battery management system for STSAT-3 satellite. The specifications of lithium ion battery unit are proposed to supply power to the satellite and the overall electrical design for lithium ion battery BMS is presented. Furthermore, the test results of battery management system are shown to verify the design.

• The Science & Technology
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• s.511
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• pp.88-90
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• 2011

• Bulletin of the Korean Space Science Society
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• 2009.04a
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• pp.53.2-53.2
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• 2009

• Bulletin of the Korean Space Science Society
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• 2009.10a
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• pp.45.3-46
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• 2009

홀 추력기는 비교적 간단한 구조와 작은 크기 및 높은 연료효율로 미래 소형위성의 핵심기술로 주목 받고 있다. 이 연구실에서는 2010년 발사예정인 과학기술위성 3호에 탑재할 소형위성용 저 전력 홀 추력기를 연구 개발하였다. 성능에 가장 큰 영향을 미치는 자기장 구조는 FEMM전산코드를 이용한 해석을 통해 설계되었으며, 제작된 프로토타입의 실험을 통해 자기장의 세기 및 모양, 양극전압 및 기체유량에 따른 성능 특성을 관찰하였다. 또한 Faraday Probe와 Retarding Potential Analyzer (RPA), 랑뮈어 탐침 등을 이용해 이온빔의 분사각도 및 전류밀도, 이온에너지 분포, 플라즈마 전위 등을 측정하고 관찰된 특성을 물리적으로 분석하였다. 이러한 최적화 과정을 통해 설계된 비행모델의 시험 결과 양극전력 200 W, 제논 연료유량 0.85 mg/s 을 통해 11.2 mN 추력, 1350 s 비추력, 37% 추력효율을 획득하여 개발목표를 상회하는 만족할만한 결과를 얻었다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.10
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• pp.992-997
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• 2010

The Propulsion Control Module(PCM) of Hall-thruster Propulsion System(HPS) for Science and Technology Satellite-3 (STSAT-3) has the flow control accuracy of less than ${\pm}$3% and the pressure control accuracy of less than ${\pm}$5%. The pressure controller adjusts pressure around the set point by using a Proportional Flow Control Valve (PFCV) and a high pressure transducer, while the flow controller regulates the flow rate using PFCV and the anode current telemetry of the Hall Thruster. The controllers are chosen as the Proportional and Integral(PI) type, and the PI gains are tuned based on the Matlab simulations. The result of the PCM test had the flow control accuracy of less than ${\pm}$1.87% and the pressure control accuracy of less than ${\pm}$5%. This paper describes the design, realization, and performance test results of the PCM.