• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.2
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• pp.101-105
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• 2006

The Engineering Model of STSAT-2 on-board computer(OBC) was developed and tested completely with other sub-systems. The on-board computer of STSAT-2 has a high- performance PowerPC processors and a structure of centralized network communication. In addition, a lot of logics are implemented by Field Programmable Gate Array, such as interrupt controller, watchdog timer and UART. It could make the weight and size of OBC lighter and smaller. Also, the STSAT-2 on-board computer has more improved tolerance against Single Event Upsets and faults than that of the STSAT-1.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.2
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• pp.195-201
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• 2008

This paper compares the performance of Mass Memory Unit(MMU) between Science and Technology Satellite 1(STSAT-1) and STSAT-2 from developed Proto Flight Model(PFM) for Miniaturization, lightweight and low power consumption. MMU receives the payload data at 200Kbps and transmits them to XTX at 10Mbps in the STSAT-2. The performance of PFM MMU in the Functional and space environments test satisfies the requirements of STSAT-2.

• Journal of Satellite, Information and Communications
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• v.5 no.2
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• pp.82-86
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• 2010

In this paper, a power amplifier module for WCDMA base-station applications is designed and implemented using GaN field-effect transistors (FETs), which uses an envelope tracking bias system. The designed module consists of an high gain MMIC amplifier, a driver amplifier, a power amplifier, and bias circuits for envelope tracking applications. Especially, a FET bias sequencing circuit and two isolators are integrated for stable RF operations. All circuits are assembled within a single housing, so its dimension is just $17.8{\times}9.8{\times}2.0\;cm3$. Measured results show that the developed power amplifier module has good envelope tracking capability: the power-added efficiency of 35% at the output power range from 30dBm to 40dBm over a wide range of drain bias.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.12
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• pp.1222-1228
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• 2008

A small satellite, DubaiSat-1 FM(Flight Model), which is based on SI-200 standard bus platform and scheduled to be launched in 2008, is being developed by Satrec Initiative and EIAST(Emirates Institution for Advanced Science and Technology). The TCS(Thermal Control Subsystem) of DubaiSat-1 FM has been designed to mainly utilize passive thermal control in order to minimize power consumption, but the active control method using heaters has been applied to some critical parts. Also, thermal analysis has been performed for DubaiSat-1's mission orbit using a thermal analysis model. The thermal design is modified and optimized to satisfy the design temperature requirements for all parts according to the analysis result. The thermal control performance of DubaiSat-1 FM is verified by thermal vacuum space simulation, consisting of thermal cycling and thermal balance test. Also, to validate the thermal modeling of DubaiSat-1 FM, comparison of test results with analysis has been performed and model calibration has been completed.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.18 no.2
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• pp.466-474
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• 2014

According to wireless network technology and mobile processors performance were improved, the small wireless mobile device such as smart phones has been widely utilized. The mobile devices can be used GPS information, thereby the services based on location information was increased. GPS was impossible to provide location information in indoor and signal shading environment, and the tracking systems based on short distance wireless communication are required infrastructure. The IEEE 802.11 based tracking system is possible estimation using APs, however the tracking device is exhausted battery power seriously. In this paper, we propose IEEE 802.11 based low-power tracking system. We reduced power consumption from channel scanning and network connection. For performance evaluation, we designed and implemented the tracking tag device, and measured power consumption of the device. As the simulation result, we confirmed that the power consumption was reduced 46% compare to the standard execution.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.8 no.3
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• pp.554-562
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• 2004

It was recommended for all ship engaged in international voyages to carry the Satellite Emergency position Indicating Radio Beacon according to Global Maritime Distress ＆ Safety System but also it is tending to be diffused to require the satellite EPIRB installed in small vessel such as a fishery boat by domestic regulations of each countries. Otherwise the domestic regulation can't evaluate exactly the compatibility with the satellite system and the performance of the equipment itself required by international regulation. And even if it is required the performing of the performance inspection in accordance with international regulation, it is difficult to grasp the characteristics of equipment by a generalized measuring equipment. Hence this study performed the measurement for the matters related with an wave forms, modulation characteristics, frequency and the power, etc through the design and implementation of the test bench capable of ensuring most of test items regulated by international regulation. Through this study, it has been paved the way being capable of preparation of the standard regarding to transmission repetition period, phase variation and frequency stability related with the system compatibility and in conclusion, it is enable to improve the performance of a main distress communication equipment directly connected with the life of a survivor.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.21 no.4
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• pp.352-361
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• 2010

In this paper, a compact 20 W block-up-converter for C-band satellite communication is designed and implemented. The designed block up-converter consists of an intermediate frequency circuit, a mixer and local oscillator, a driver amplifier, a solid-state power amplifier, waveguide circuits, and a power supply module. To reduce the size of the block-up-converter, all circuits are assembled within an housing, so its dimension is just $21{\times}14{\times}11cm^3$. Especially, the waveguide filter and microstirp-to-waveguide transition are easily implemented using an housing. Also, to meet spurious and harmonics specification, various compact microstrip filters including an elliptic filter are integrated. Measurement results show that the developed block up-converter has good electrical performances: the output power of 43.7 dBm, the minimum gain of 65 dB, the gain flatness of ${\pm}1.84$, the IMD3 of -35 dBc, and the harmonic level of -105 dBc.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.8
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• pp.798-804
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• 2009

A high-resolution electro-optical camera system, EOS-C, is under development in Satrec Initiative. This system is the mission payload of a 400-kg Earth observation satellite. We designed this system to give improved opto-mechanical and thermal performance compared with a similar camera system to be flown on the DubaiSat-1 system. The thermal control subsystem (TCS) of the EOS-C system uses heaters to meet the opto-mechanical requirements during in-orbit operation and it uses different thermal coating materials and multi-layer insulation (MLI) blankets to minimize the heater power consumption. We performed its thermal analysis for the mission orbit using a thermal analysis model and the result shows that its TCS satisfies the design requirements.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.5
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• pp.430-436
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• 2014

The mission objective of STEP Cube Lab. (Cube Laboratory for Space Technology Experimental Project) classified as a pico-class satellite is to verify the technical effectiveness of payloads such as variable emittance radiator, SMA washer, oscillating heat pipe and MEMS based solid propellant thruster researched at domestic universities. In addition, the MEMS concentrating photovoltaic power system and the non-explosive holding and separation mechanism with the advantages of high constraint force and low shock level will be developed as the primary payloads for on-orbit verification. In this study, the feasibility of the mission actualization has been confirmed by the preliminary system design.

• The Bulletin of The Korean Astronomical Society
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• v.37 no.2
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• pp.231.2-231.2
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• 2012

원격탐사를 위한 지구관측용 전자광학 카메라는 높은 해상도, 넓은 관측 폭 및 높은 선명도를 제공하기 위하여 부피가 크고 무거우며, 큰 전력을 소모하여, 위성본체의 대부분을 차지하도록 개발된다. 그러나, 달 탐사를 위해 달 궤도선이나 달 착륙선에 장착되는 전자광학 카메라는, 고해상도의 고성능을 가지도록 개발되기 보다는, 다기능의 집적도 높은 소형카메라로 개발되는 것이 일반적이다. 이에 따라, 달 탐사용 다기능 전자광학 카메라 개발을 위한 기술검증을 위하여 지상모델이 개발되었다. 본 카메라는 CMOS 센서를 사용하여 컴팩트하게 설계하였고, 스테레오 영상생성을 위해 두 개의 카메라가 동시에 운영되며, 줌 기능을 구현하여 다양한 조건에서도 영상획득이 가능하도록 설계 되었다. 또한 달 궤도선과 착륙선에서 1D 관측 및 2D 관측이 선택적으로 가능하도록 설계되었다. 개발된 지상모델은 실험실에서 수행하는 통상적인 기능 및 성능시험을 수행하였고, 스테레오 영상의 생성기능 등의 검증을 위하여 야외에서 카메라를 정속으로 회전하며 push broom 방식의 1D 촬영모드에 대한 시험을 수행한다. 또한, 항공촬영을 통해 1D 및 2D 촬영을 수행하여, 영상데이터의 처리 및 스테레오 영상데이터 생성 등의 검증 단계를 거친다. 본 논문 발표에서는 다기능의 전자광학 카메라를 지상에서 동작시켜 실제영상을 뽑아내고, 생성된 데이터를 처리하여, 설계된 카메라의 여러 가지 기능들에 대해 검증하는 방법들에 대해 정리 및 발표한다. 즉, 달 궤도에 맞게 설계된 카메라의 노출시간 등을 조절하고, push broom 방식을 모사하기 위하여 카메라를 정속으로 회전시켜 영상을 획득하여 다양한 카메라의 기능을 검증하였다.