• The Bulletin of The Korean Astronomical Society
• /
• v.39 no.2
• /
• pp.106-106
• /
• 2014

SIGMA (Scientific cubesat with Instrument for Global Magnetic field and rAdiation)는 근 지구공간에서 우주방사선량 측정과 자기장 변화 검출의 과학적 목적과 교육적 목적을 가지고 개발하고 있는 초소형 큐브위성이다. $100mm{\times}100mm{\times}340.5mm$의 크기로 약 3.6 kg의 무게를 가지며, 탑재체는 방사선에 대하여 인체와 동일한 산란 흡수 특성을 가진 Tissue Equivalent Proportional Counter (TEPC)와 자기장 측정을 위한 Magnetometer (Mag)이다. 위성체는 구조계, 자세제어계, 전력계, 명령 및 데이터처리계, 통신계로 구성되어있다. 구조계는 위성의 뼈대인 Chassis와 Mag deployer로 이루어져있고, 위성의 안정적인 자세유지를 목적으로 Attitude Control System (ACS) Board와 Torque Coil이 자세제어계로 구성된다. 전력의 생산과 공급 및 충전은 태양전지판과 Electrical Power System (EPS), 리튬 배터리로 구성된 전력계에서 이뤄지며, 명령 및 데이터처리계는 On Board Computer (OBC)와 Instrument Interface board (IIB)를 중심으로 서브시스템의 명령체계와 데이터처리를 다룬다. 통신계는 Uplink인 VHF 안테나와 Downlink인 UHF, S-band 안테나로 구성되며 지상과 명령을 송수신한다. SIGMA는 타임인터럽트 기능을 활용한 Flight Software (FSW)로 운용되며 임무에 따른 6가지 모드의 시나리오로 위성을 운용한다. 이에 SIGMA의 개발과 테스트 결과를 소개한다. 본 큐브위성 개발기술을 바탕으로 향후 천문관측용 위성에도 활용할 예정이다.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.44 no.3
• /
• pp.274-280
• /
• 2016

Hinge driving type holding and release mechanism based on the burn wire release for application of cubesat is main payload of STEP Cube Lab. (Cube Laboratory for Space Technology Experimental Project) to be launched at 2015. It has high constraint force, low shock level as well as surmounting drawbacks of conventional nichrome burn wire release method that has relatively low constraint force and system complexity for application of multi-deployable systems. In this paper, we have proposed a flight model of holding and release mechanism for the verification of the constraint force and deployment status signal acquisition. To validate the effectiveness of the flight model, launch and on-orbit environment verification test have been performed.

• Proceedings of the Korean Institute of Electrical and Electronic Material Engineers Conference
• /
• 2010.06a
• /
• pp.130-130
• /
• 2010

고출력 레이저 다이오드는 광 디스크, 고체 레이저 여기, 광섬유 증폭기, 레이저 프린터, 위성 간 통신 등의 여러분야에 응용되고 있고. 고효율, 저가격, 초소형등과 같은 장점으로 수요가 점점 증가하고 있다. 최근 레이저 다이오드의 광출력 향상 및 열적 안성성를 위해 양자점(Quantum Dot) 응용에 대해 많은 연구가 진행되고 있다. 양자점 기반 레이저 다이오드는 전자가 3차원으로 구속되어 있어 열적 안정성이 우수할 뿐만 아니라 낮은 문턱전류밀도로 인해 열 발생이 적어 광출력 감소 현상을 지연시킬 수 있다. 또한 발광면에서의 재결합 확률이 낮아 표면재결합에 의한 신뢰성 열화 문제를 해결할 수 있어 고신뢰성의 레이저 다이오드를 개발할 수 있다. 고출럭 808 nm 양자점 레이저 다이오드 개발을 위해서는 레이저 다이오드의 활성 영역인 양자점 구조에 대한 연구가 필수적이다. 본 연구에서는 최적화된 고출력 808 nm 양자점 레이저 다이오드 에피 성장을 위해 에피 구조에 대한 2D 시뮬레이션을 수행하였고, 양자점 밀도 및 에피층 변화에 따른 최적 양자점 구조에 대한 연구를 수행하였다.

• Proceedings of the Korea Electromagnetic Engineering Society Conference
• /
• 2000.11a
• /
• pp.385-388
• /
• 2000

본 논문에서는 좀더 효율적이고 소형화한 GPS(Global Positioning System)용 안테나와 LNA(Low Noise Amplifier)를 IMT-2000 단말기에 내장함으로써 개인 휴대 통신 기능과 더불어 좀 더 정확한 위치추적 기능을 동시에 가능케 하고자 한다. 중심 주파수 1.575 GHz의 저잡음 증폭기와 안테나의 크기는, 합쳐서 10$\times$10$\times$4 (mm)로서 상층은 마이크로스트립 패치 안테나이고, 중간층은 안테나 ground와 LNA ground의 공통 ground이며, 제일 아래층에는 LNA가 위치하게 된다. LNA 의 경우 2단을 중첩하여, 첫째 단 16dB, 둘째 단 18dB의 이득 특성을 보였는데 첫째, 둘째 단의 대역통과 필터에서 삽입손실로 3dB의 손실을 가져와 총 3dB의 이득 특성을 보였다. 잡음 특성은 약 1.9의 특성을 보였다. 안테나의 경우 9$\times$9$\times$$\times$2 (mm)로써, 고유전율( $\varepsilon$$_{r}$ = 73 )의 세라믹을 사용하여 그 크기를 상당부분 줄였다. 그리고 유전체 밑의 ground를 옆면까지 높임으로써 좀 더 소형화한 안테나를 가능케 하였다. 고유전율의 유전체를 사용하였기에 안테나 자체의 이득 특성은 저잡음 증폭기에서 보상하고, 안테나의 임피던스 정합 또한 LNA의 입력 쪽에서 하도록 하였다. 또한 위성신호 수신을 위해 안테나는 RHCP 의 원형편파 특성을 갖는다.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
• /
• v.27 no.12
• /
• pp.1112-1115
• /
• 2016

Global Positioning System(GPS) is a useful system used in both civilian and military applications. However, the signal of GPS is susceptible to jamming attacks due to low receive sensitivity, since the signals come from the satellite located at over 20,000 km above the earth. In this paper, we have conducted a preceding research on a non-Foster matching circuit that efficiently matches an electrically ultra-small GPS antenna. Electrically Small Antennas(ESAs) are inefficient radiators and are difficult to match in wideband due to extremely high quality factor. In order to match small GPS antenna in wideband, a non-Foster matching circuit for a small GPS antenna was designed. A negative impedance converter circuit consisting of Linvill's cross-coupled pair transistors was fabricated and its stability was verified by the time-domain stability analysis. In addition, anechoic chamber measurements show that the non-Foster matching circuit for small GPS antenna can lead bore-sight gain improvement by more than 17 dB.

• The Journal of Korean Institute of Communications and Information Sciences
• /
• v.17 no.2
• /
• pp.99-113
• /
• 1992

In general, TDMA and FDMA have been used for multiple access communication methods. Recently. However, ALOHA and CSMA protocols came to exist as new schemes for VSAT data networks and LANs, respectively. These schemes are proven to be effective for packet switched communication systems that has bursty traffic but packet collisions. In this paper we analyze capture statistics arising from fading channels in packet radio communication systems in the context of ALOHA protocol. We derive general results of the exact form of capture probabilities and present numerical data for wide range of fading parameters. Since the capture probabilities are found to approach zero when the number of transmitted signals become larger, we are able to determine the achievable channel throughput by a least squares fitting of an exponential-type function to the probabilities.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.23 no.6
• /
• pp.95-108
• /
• 2019

Electric propulsion is a type of space propulsion with a high specific impulse by accelerating propellant using electrical energy and brings about reduction of the fuel mass and launch costs of satellites so that it is being extensively studied in the world. Electric thrusters are widely used for various purposes from micro satellites to large satellites and from low Earth orbit satellites to spacecraft for exploration. Recently, satellites using full-electric propulsion have been developed, and the number of satellites with electric propulsion is also gradually increasing. In this paper, the current status and trends of research on electric propulsion in the United States, Europe, and Japan will be reported.

• The Journal of the Korea Contents Association
• /
• v.8 no.9
• /
• pp.42-54
• /
• 2008

In recent years, embedded systems have been expanding their application domains from traditional embedded systems such as military weapons, robots, satellites and digital convergence systems such as celluar phones, PMP(Portable Multimedia Player), PDAs(Personal Digital Assistants) to Next Generation Personal Computers(NGPCs) such as eating PCs, wearable computers. The NGPCs are network-based, human-centric digital information devices diverged from the traditional PCs used mainly for document writing, internet searching and database management. Wearable computers with battery capacity and memory size limitations have to use real-time operating systems with small footprints and low power management techniques to provide user's QoS in spite of hardware constraints. In this paper, we have designed and implemented a low-power RTOS (called eRTOS) for wearable computers. The implemented eRTOS has 18KB footprints and the dynamic power management and the device power management schemes are adapted in it. Experimental results with wearable computer applications show that the low power techniques could save energy up to 47 %.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.32 no.9
• /
• pp.103-113
• /
• 2004

The satellite is exposed to the severe vibration environments such as random vibration environments such as random vibration, acceleration, shock, and acoustics during launch ascent and transportation. It is also faced with various space environments such as thermal vacuum, radiation and microgravity during the mission life. The satellite should be designed, manufactured, assembled and tested to be able to endure in these harsh environments. This paper addresses the results of the structural and thermal design and analyses for the HAUSAT-1 picosatellite which is scheduled to launch in the first quarter of 2005 by Russian launch vehicle "Dnepr". The qualification vibration and thermal vacuum tests have been conducted and passed at the satellite level to ensure that the HAUSAT-1 mechanical system was designed to be stable with enough margin.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.34 no.2
• /
• pp.56-67
• /
• 2006

The reliability and failure mode effect analysis are effective means to achieve efficient and cost-reduction design for satellite development. The failure rate of COTS (Commercial-Off-The-Shelf) parts required for reliability analysis is not usually provided from the manufacturer. Space environment factors based on empirical data obtained from MIL-HDBK-217F can be applicable to the reliability calculation. As a radiation environment factor, the occurrence rate of SEL (Single Event Latch-up) is additionally incorporated for the failure rate prediction. In this paper, the statistical reliability analysis method for low-cost small satellite using COTS parts is suggested. This statistical reliability analysis was applied to HAUSAT-2 small satellite whose electronic boxes are consisted of many COTS parts to calculate the system reliability at the end of design mission life.