• Nuclear Engineering and Technology
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• 제47권6호
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• pp.678-699
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• 2015

Although the harsh space environment imposes many severe challenges to space pioneers, space exploration is a realistic and profitable goal for long-term humanity survival. One of the viable and promising options to overcome the harsh environment of space is nuclear propulsion. Particularly, the Nuclear Thermal Rocket (NTR) is a leading candidate for nearterm human missions to Mars and beyond due to its relatively high thrust and efficiency. Traditional NTR designs use typically high power reactors with fast or epithermal neutron spectrums to simplify core design and to maximize thrust. In parallel there are a series of new NTR designs with lower thrust and higher efficiency, designed to enhance mission versatility and safety through the use of redundant engines (when used in a clustered engine arrangement) for future commercialization. This paper proposes a new NTR design of the second design philosophy, Korea Advanced NUclear Thermal Engine Rocket (KANUTER), for future space applications. The KANUTER consists of an Extremely High Temperature Gas cooled Reactor (EHTGR) utilizing hydrogen propellant, a propulsion system, and an optional electricity generation system to provide propulsion as well as electricity generation. The innovatively small engine has the characteristics of high efficiency, being compact and lightweight, and bimodal capability. The notable characteristics result from the moderated EHTGR design, uniquely utilizing the integrated fuel element with an ultra heat-resistant carbide fuel, an efficient metal hydride moderator, protectively cooling channels and an individual pressure tube in an all-in-one package. The EHTGR can be bimodally operated in a propulsion mode of $100MW_{th}$ and an electricity generation mode of $100MW_{th}$, equipped with a dynamic energy conversion system. To investigate the design features of the new reactor and to estimate referential engine performance, a preliminary design study in terms of neutronics and thermohydraulics was carried out. The result indicates that the innovative design has great potential for high propellant efficiency and thrust-to-weight of engine ratio, compared with the existing NTR designs. However, the build-up of fission products in fuel has a significant impact on the bimodal operation of the moderated reactor such as xenon-induced dead time. This issue can be overcome by building in excess reactivity and control margin for the reactor design.

• Journal of Astronomy and Space Sciences
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• 제26권4호
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• pp.677-692
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• 2009

최근 미국, 유럽, 일본 등 우주선진국을 중심으로 달, 화성 등 행성 탐사를 위한 로버(Rover) 시스템에 대해 많은 연구 개발이 진행되고 있다. 행성탐사용 로버 시스템 기술 중 특히 주행장치, 자율 주행 알고리즘, 탑재체 등을 중심으로 많은 연구가 수행되고 있다. 이 논문에서는 실제 행성탐사에 앞서 지상에서 로버 주행장치의 주행성 및 안정성을 평가하기 위해 지상시험모델용 로버의 주행장치에 대한 개념 설계 내용을 소개하였다. 또한, 로버 주행장치의 기술적인 관점에서 해외 연구개발 사례를 분석, 기술하였다. 이를 통해 로버 주행장치 개발을 위한 요구사항들을 주행성과 안정성 관점을 고려하여 도출하였다. 설계된 로버 주행장치는 높은 주행성과 안정성을 만족하기 위해 6족을 가지고 있으며, 각 다리의 관절을 제어하는 능동 서스펜션(Active Suspension)을 적용하였다. 이러한 종류의 주행장치 개념은 근미래 (Constellation 프로그램)에 수행될 유인달 탐사에서 이동 및 거주 장치로써 NASA의 ATHELE을 통해 처음 적용하여 개발하고 있다. 이 연구에서 제안된 장치 개념은 이와 달리 우리나라에서 앞으로 수행할 무인소형 달탐사에 적용하고자 설계되었다. 이 논문에서 소개된 내용은 향후 국내에서 행성탐사용 로버시스템을 본격적으로 개발하고자 할 때 유용한 참고자료 및 경험을 제공할 것 이다.

• 한국지구과학회지
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• 제30권1호
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• pp.141-151
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• 2009

탐구는 학교과학에서 지속적으로 강조되어 왔다. 하지만 학교에서 주어지는 문제는 학생들이 일상생활에서 경험하고 부딪치는 문제들과는 여러 면에서 다르다. 본 연구의 목적은 학생들이 문제에 대한 인지도식을 거의 갖고 있지 않을 때, 과제에 대한 태도와 사고력이 문제해결과정, 특히, 문제공간의 형성과 정교화에 어떻게 영향을 미치는지를 알아보는 것이다. 이를 위하여 연구자는 미국의 한 영재센터 여름방학 프로그램 중 4-6학년 영재학생 대상 '레고 로봇 수업'에 참여한 학생들의 문제해결전략을 추적하였다. 결과는 다음과 같다. (1) 과제의 선택과 파악방법, 작동자에 대한 인식의 차이 등 과제에 대한 태도는 서로 다른 문제공간을 형성하게 하였다. (2) 분석적 사고, 융통성, 효율적인 정교화 기술, 기존 인지도식의 적용 등의 사고력의 수준 차이는 문제공간의 정교화 차이와 문제해결의 성공여부로 이어졌다. (3) 초기의 문제공간의 차이는 문제해결전략의 형성 차이를 가져왔지만, 사고력 없이는 효과적인 문제해결전략의 정교화가 이루어지지 못하였다. 마지막으로, 위의 결과를 바탕으로 과학탐구를 증진시킬 몇 가지 사항이 제안되었다.

• 천문학회지
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• 제37권5호
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• pp.571-574
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• 2004

Clusters of galaxies are filled with X-ray emitted hot gas with the temperature of T ${\~}$2-10 keV. Recent X-ray observations have been revealing unexpectedly that many cluster cores have complicated, peculiar X-ray structures, which imply dynamical motion of the hot gas. Moreover, X-ray spectra indicate that radiative cooling of the cool gas is suppressed by unknown heating mechanisms (the 'cooling flow problem'). Here we propose a novel mechanism reproducing both the inhomogeneous structures and dynamics of the hot gas in the cluster cores, based on state-of-the-art hydrodynamic simulations. We showed that acoustic-gravity waves, which are naturally expected during the process of hierarchical structure formation of the universe, surge in the X-ray hot gas, causing a serous impact on the core. This reminds us of tsunamis on the ocean surging into an distant island. We found that the waves create fully-developed, stable turbulence, which reproduces the complicated structures in the core. Moreover, if the wave amplitude is large enough, they can suppress the cooling of the core. The turbulence could be detected in near-future space X-ray missions such as ASTRO-E2.

• 천문학회보
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• 제40권2호
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• pp.45.1-45.1
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• 2015

Hayabusa is the JAXA's space mission that succeeded in sample-return from S-type asteroid (25143) Itokawa. During the rendezvous phase, more than a thousand of images were taken with the Asteroid Multi-band Imaging Camera (AMICA). It is valuable to study the regional variation of the optical properties on the asteroid using these images to know the generality and uniqueness of the returned samples. In addition, AMICA images are important in that they provide unique data set at low phase angle (i.e Sun-Itokawa-AMICA's angle) that have not been explored in the previous asteroidal missions. At the previous conference (2015 KAS spring meeting), we introduced our preliminary data analysis of AMICA data without considering the shape model of Itokawa and mentioned. In this study, we present a new result obtained through further analysis, taking account of the shape model of the asteroid. We thus utilized "plate_renderer" tool to derive Hapke model parameters at different terrains. It is found that the opposition amplitude (parameter B0) is consistent with those of the other S-type asteroids while the opposition width (parameter h) is significantly narrower than those of the other S-type asteroids. At this conference, we plan to describe the regional variation of photometric properties on Itokawa.

• Advances in aircraft and spacecraft science
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• 제4권5호
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• pp.543-553
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• 2017

Vibration is a source of performance degradation in all optical imaging systems. Performance of high resolution remote sensing payloads is often limited due to satellite platform vibrations. Effects of Linear and high frequency sinusoidal vibrations on the system MTF are known exactly in closed form but the low frequency vibration effects is a random process and must be considered statistically. Usually the vibration MTF budget is defined based on the mission requirements and the overall MTF limitations. For analyzing low frequency effects, designer must know all the systems specifications and parameters. With a good understanding of harmful vibration frequencies and amplitudes in the system preliminary design phase, their effects could be removed totally or partially. This procedure is cost effective and let the designer to eliminate just harmful vibrations and avoids over-designing. In this paper we have analyzed the effects of low-frequency platform vibrations on the payload's modulation transfer function. We have used a statistical analysis to find the probability of imaging with a MTF equal or greater than a pre-defined budget for different missions. The worst and average cases have been discussed and finally we have proposed "look-up figures". Using these look-up figures, designer can choose the electro-optical parameters in such a way that vibration effects be less than its pre-defined budget. Furthermore, using the results, we can propose a damping profile based on which vibration frequencies and amplitudes must be eliminated to stabilize the payload system.

• 시스템엔지니어링학술지
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• 제7권1호
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• pp.1-7
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• 2011

This work describes a study on the Analysis of Alternatives (AoA) based defense decision making. Future battle-space is transformed into a System of Systems (SoS) concept which is accomplished missions and their functions through network based battle management systems under forming their grids of various sensors and shooters in a single theater. The acquisition process is, therefore, changing over from single system requirements to capabilities based acquisition of SoS. AoA help to justify the need for starting, stopping, or continuing an acquisition program. AoA identify potentially viable solutions and provide comparative cost, effectiveness, and risk assessments of each solution to a baseline. The decision making must consider not only cost-effectiveness, risk, and military worth, but also domestic policy, foreign policy, technological maturity of the solution, the environment, the budget, treaties, and a host of additional factors. In this point of view, this paper analyzes AoA template which are critical elements of the defense decision making. From results of this analysis of AoA template for Korean acquisition environment are presented.

• 항공우주산업기술동향
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• 제6권2호
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• pp.116-124
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• 2008

한국항공우주연구원이 개발하고 있는 통신해양기상위성은 2009년 6월경에 발사될 예정이다. 지구 자전속도와 같은 속도로 돌기 때문에 24시간 기상 및 해양관측과 통신서비스가 가능한 국내에서 개발되는 최초의 정지궤도위성이다. 2008년 11월에 프랑스에서 해양 탑재체가 들어옴으로써 세 가지 탑재체를 장착할 수 있게 되었고 그 후에는 우주환경시험 등을 거쳐서 프랑스령 기아나 우주센터에서 발사될 전망이다. 본 논문에서는 통신해양기상위성이 세계적으로도 첫 번째 정지궤도 복합위성이 되기 때문에 국내 및 세계적으로 정지궤도 복합위성과 관련된 개발 동향을 살펴보고자 한다.

• 대한기계학회논문집B
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• 제31권10호
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• pp.823-831
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• 2007

This paper presents the experimental and simulation study of a loop heat pipe (LHP) that can be applied to present electronics, space missions and thermal control systems. The present experimental study was carried out employing sintered alumina ceramic wick ($d=2.96\;{\mu}m$, ${\phi}=0.61$). High purity R-134a, R-22 and water were also used as alternative working fluids in addition to ammonia. The experimental study showed that the maximum heat transfer performance for the test LHP in the vertical top heating mode was over 100 Watts when ammonia was used as the working fluid. The simulation results have been compared with the experimental results to validate a simulation model based on the thermal resistance network that was developed to evaluate the performance of LHPs, focusing on their prospective applications in electronics. The simulation model is based on the loop overall energy, mass, and momentum balance. The simulation program can predict the effects of various parameters which affect the performance of LHP within 5% compared with the experimental results.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2017년도 제48회 춘계학술대회논문집
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• pp.1061-1067
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• 2017

1960년대 이후부터 하이드라진($N_2H_4$)은 로켓, 인공위성 또는 심우주 임무용 추진제로 사용되어 왔다. 하지만 하이드라진의 높은 독성과 운영비용으로 이온성 액체 추진제(ADM, HAN) 및 아산화질소 연료 혼합물(NOFB)과 같은 친환경 추진제에 대한 요구가 증가하고 있다. 아산화질소 연료 혼합물(NOFB)은 이원추진제가 갖는 높은 성능과 단일추진제의 단순한 공급시스템 장점을 모두 갖는 추진제로서, 적절한 취급방법과 설계가 적용된다면 전통적인 하이드라진 추진 시스템을 대체할 만한 추진제로 사용가능할 것이다.