• The Journal of the Korea institute of electronic communication sciences
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• v.17 no.4
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• pp.641-648
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• 2022

In this study, the performance of the NHPP software reliability model with exponential distribution (Exponential Basic, Inverse Exponential, Lindley, Rayleigh) characteristics was comparatively analyzed, and based on this, the optimal reliability model was also presented. To analyze the software failure phenomenon, the failure time data collected during system operation was used, and the parameter estimation was solved by applying the maximum likelihood estimation method (MLE). Through various comparative analysis (mean square error analysis, true value predictive power analysis of average value function, strength function evaluation, and reliability evaluation applied with mission time), it was found that the Lindley model was an efficient model with the best performance. Through this study, the reliability performance of the distribution with the characteristic of the exponential form, which has no existing research case, was newly identified, and through this, basic design data that software developers could use in the initial stage can be presented.

• Journal of Space Technology and Applications
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• v.2 no.3
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• pp.187-194
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• 2022

Although the magnitude of the disturbance caused by the driving of the motor operated to secure the high-speed and precise directivity of the antenna is small, it acts as a major cause of impairing the image quality of the observation satellite, which requires precision directing performance. In order to acquire high-resolution image information through the improvement of the high-resolution observation satellite, proper vibration isolation and reduction design are required so that jitter generated when the directional antenna motor is driven is not transmitted to the main mission equipment. In this paper, the development process of the directional antenna vibration reduction device applied to real satellites and the effect of micro vibration reduction before and after application will be examined. This device was designed as a way to significantly improve the jitter problem by replacing only one gear in the directional antenna driving unit with a spring damper gear without any additional interface equipment. It was first applied and launched to a high-resolution earth observation satellite, and has been successfully operated so far.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.4
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• pp.241-250
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• 2022

This paper addresses the Feasible Angular Momentum(FAM) chart that can be used as an indicator for maneuverability analysis of spacecraft installed with control moment gyros(CMGs). Recently, as the demands for high agility of spacecraft has been increasing in order to perform the space mission given to spacecraft more effectively, interest in CMGs, which is a high torque generator is increasing. However, since the CMG has a singularity problem that does not generate the control torque in the specific directions, in this paper, we consider the two pairs of parallel control moment gyros(TPCMGs) that follows the roof-type configuration. The Gimbal space was newly defined except for the space where singularity can be generated and the space where torque error is generated due to the hardware limits. The feasible angular momentum space is defined as a FAM chart, and it is very meaningful that it is possible to analyze the spacecraft's rotational maneuverability effectively by deriving the spacecraft's 3-axis parameters in the corresponding gimbal space mathematically.

• Journal of Korea Society of Industrial Information Systems
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• v.18 no.5
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• pp.81-92
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• 2013

The satellite includes many release mechanisms such as solar array deployment, antenna deployment, cover to protect contamination in scientific equipment, pyro value of the propulsion subsytem, and bypass device in Li-Ion cell module. A drive the initiators is a critical to the successful mission because the initiators of release mechanism driving by the pyrotechnic circuit is operated in single short. The pyrotechnic circuit has to provide switching network for safety. A typical switching network has defect consisting of high current rating fire switch to handle switching transient current during fire the initiator. The pyrotechnic circuit is required some form of power conditioning to reduce the peak power demanded from the bus if the initiators are to be fired from the main bus. This paper design a pyrotechnic circuit synchronized to the fire-command to activate the fire switch to overcome use high current rating fire switch to handle switching transient current during fire the initiator. The pyrotechnic circuit provides a current limited widow pulse for fire current synchronized to the fire-command to insure that fire switch will only carry the current but never switch it. The current limited widow pulse for fire current can be possible to use low current rating and light mass switch in switching network. The current limit function in the pyrotechnic circuit reduces supply voltage to initiator and provides the effect of power conditioning function to reduce peak bus power. The pyrotechnic circuit to apply satellite development on geostationary orbit is verified the function by test in development model.

• Proceedings of the Korea Technology Innovation Society Conference
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• 1999.05a
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• pp.539-563
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• 1999

이 논문은 정보통신정책 목표와의 연관성 속에서 정보통신연구개발사업의 우선순위를 설정함과 아울러 비용효과성에 바탕을 둔 적정 자원배분 도출하는데 주안점을 두고 있다. 복합적인 목표를 가진 연구개발사업에 대해 사업부문별 그리고 기술분야별로 객관적이면서도 설득력있는 자원배분지침을 마련하기 위하여 본 연구는 다기준의사결정(MCDA: Multi-criteria Decision Analysis) 방법을 채택하고 있다. 이 방법론에서는 사업의 목표와 우선순위 판단기준 및 사업대안이 계층적으로 연계된 분석구조를 설계하여 사업대안의 우선순위를 먼저 설정하고, 여기에 정수계획법(Integer Programming)을 결합하여 사업의 목표와 연계된 비용-편익 관계(Cost-benefit relationship)를 최적화하는 바탕 위에서 사업대안별 자원배분 시나리오를 제시하게 된다. 이러한 절차로 사업부문별 및 기술분야별로 각각 도출된 8개의 자원배분 시나리오는 자원배분 경향치의 안정성(Stability) 분석과 자금지원의 과부족에 대한 현실적 적합성(Relevance) 분석을 거쳐 최종적으로 하나의 적정 자원배분방안으로 수렴되도록 하였다. 우선순위 설정에 기초가 되는 사업대안의 편익에 대한 자료는 전문가의 정성적 판단을 통해 수집되었는데, 이를 위해 정보통신기술 부문에서 활동 중인 중견 이상의 총 58명의 산학연 전문가를 대상으로 한 조사를 실시하였다. 먼저, 기초기반ㆍ전략기술개발사업, 연구ㆍ기술인력양성사업, 산업응용기술개발사업, 기술기반조성사업 등 4대 사업부문에 대해서는 (ⅰ) 정보통신 기술능력의 축적, (ⅱ) 정보통신산업의 경쟁력 강화, (ⅲ) 정보통신기반의 기술고도화, (ⅳ) 정보화를 위한 기술역량의 제고 등 주요 사업의 편익을 나타내는 4개 기준으로 우선 순위를 판단하였고, 정보통신망기술, 전파 및 RF 기술, 정보처리기술, 반도체 소자/설계 기술 등 13개 기술분야에 대해서는 (ⅰ) 공공정책적 임무에 대한 기여, (ⅱ) 기술자립기반의 확충, (ⅲ) 기술발전성과 기술적 파급효과, (ⅳ) 기술적 산물의 시장잠재력 등 기술분야 연구개발을 통한 편익을 나타내는 4개 기준으로 우선순위를 판단하였다. 우선순위는 사업대안에 대한 가중치로 표시되었고, 적정 자원배분방안은 추정된 총예산 규모에 따라 지원수준에 대한 일정한 제약조건 하에서 비용-편익 관계에 따른 자원의 최적 할당량으로 제시되었다. 본 연구는 총예산 규모의 가변성, 사업 및 기술분야 대안의 분류체계에 대한 공감대 부족, 사업목표의 상호연관성과 우선순위 판단기준의 부분적 중첩성 등 여러 제약요인이 있어 도출된 구체적인 수치보다는 방향성에 더 큰 의미를 부여하는 것이 바람직하다. 그러나, 이러한 연구의 한계에도 불구하고 도출된 우선순위와 적정 자원배분방안은 문제해결의 실행타당성을 감안하여 비교적 객관적이고 균형있는 결과로 판단된다.

• Journal of Aerospace System Engineering
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• v.14 no.1
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• pp.54-61
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• 2020

For operating military aircraft, military certificate of airworthiness (MCA) must be obtained from military authority. Among procedures of general airworthiness certification, there is a military type certification process that aircraft design complies with military airworthiness certification criteria. The Surion is the first military rotorcraft which has obtained military type certificate, production validation and airworthiness certificate in Korea, and the Surion derivatives for special mission are being operated for government services. Based on Aviation Safety Act, in order to operate the Surion derivatives (military aircraft) for special purpose (such as emergency patient transportation and firefighting), the issuance of special airworthiness certificates was needed from civil airworthiness authority, and the restricted category type certification (RTC) is one of design approvals for special airworthiness certification to be streamlined. This study discussed the procedures for acquiring RTC for special purpose operation of the Surion derivatives classified as military derived aircraft, and suggested procedural ideas to improve Korean RTC system.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.17 no.8 s.111
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• pp.773-787
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• 2006

An airborne radar is an essential aviation electronic system for the aircraft to perform various civil and/or military missions in all weather environments. This paper presents the design, development, and test results of the multi-mode X-band pulsed Doppler radar system test model for helicopter-borne flight test. This radar system consists of 4 LRUs(Line-Replacement Unit), which include antenna unit, transmitter and receiver unit, radar signal & data processing unit and display Unit. The developed core technologies include the planar array antenna, TWTA transmitter, coherent I/Q detector, digital pulse compression, MTI, DSP based Doppler FFT filter, adaptive CFAR, moving clutter compensation, platform motion stabilizer, and tracking capability. The design performance of the developed radar system is verified through various ground fixed and moving vehicle test as well as helicopter-borne field tests including MTD(Moving Target Detector) capability for the Doppler compensation due to the moving platform motion.

• The Bulletin of The Korean Astronomical Society
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• v.35 no.2
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• pp.55.2-55.2
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• 2010

한국천문연구원은 과학기술위성 3호의 주탑재체인 다목적 적외선영상시스템(Multipurpose Infra-Red Imaging System, MIRIS)을 개발하고 있다. 이 연구개발 사업은 2007년 교육과학기술부의 과학위성 3호 사업 주탑재체 공모를 통하여 10여개의 후보 탑재체 제안서 중에서 최종적으로 채택되었고, 2011년 발사를 목표로, 3년 동안의 연구개발 기간을 거쳐 현재 비행모델 (FM, Flight Model) 개발이 진행 중이다. MIRIS는 한국천문연구원이 개발하여 2003년 발사에 성공한 과학위성 1호 주탑재체인 원자외선 영상분광기 (FIMS, Far ultra-violet IMaging Spectroscope)에 이어 국내에서 자체 개발되는 두 번째 우주망원경이다. MIRIS는 우주공간에서 0.9~2 micron 사이 적외선 영역의 파쉔 알파 방출선 (Paschen Alpha Emiision Line)과 광대역 I, H 파장영역을 관측할 예정이다. 주요 과학임무로는 아직까지 국제 천문학계에서 잘 알려지지 않은 우리은하 내부에 분포한 고온 플라즈마 (Warm Ionized Medium, WIM)의 기원 연구와 아울러 우리은하 성간난류(Interstellar Turbulence)의 특성 및 적외선 우주배경복사의 (Cosmic Infrared Background; CIB) 거대구조 등을 관측연구할 예정이다. 특히 MIRIS는 저온상태 (절대온도 77K, 약 $-200^{\circ}C$)에서 우주공간 관측을 수행할 예정이므로, 국내에서는 연구기반이 취약한 극저온 광학계 및 기계부 설계기술, 극저온 냉각기술 및 열해석 설계기술과 적외선 센서기술 및 자료처리 기술 등 관련기술을 개발하고 있으며 이러한 기반기술을 바탕으로, 아직까지 국내에서 시도된 바 없는 적외선우주망원경 개발을 통하여, 우리나라의 관련 우주기술 분야의 기초원천 기술로서 크게 활용될 것으로 기대하고 있다.

• Journal of Bio-Environment Control
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• v.14 no.3
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• pp.218-231
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• 2005

This paper reviews the engineering approach needed to support humans during their long-term missions in space. This approach includes closed plant production systems under microgravity or low pressure, mass recycling, air revitalization, water purification, waste management, elimination of trace contaminants, lighting, and nutrient delivery systems in controlled ecological life support system (CELSS). Requirements of crops f3r space use are high production, edibility, digestibility, many culinary uses, capability of automation, short stems, and high transpiration. Low pressure on Mars is considered to be a major obstacle for the design of greenhouses fer crop production. However interest in Mars inflatable greenhouse applicable to planetary surface has increased. Structure, internal pressure, material, method of lighting, and shielding are principal design parameters for the inflatable greenhouse. The inflatable greenhouse operating at low pressure can reduce the structural mass and atmosphere leakage rate. Plants growing at reduced pressure show an increasing transpiration rates and a high water loss. Vapor pressure increases as moisture is added to the air through transpiration or evaporation from leaks in the hydroponic system. Fluctuations in vapor pressure will significantly influence total pressure in a closed system. Thus hydroponic systems should be as tight as possible to reduce the quantity of water that evaporates from leaks. And the environmental control system to maintain high relative humidity at low pressure should be developed. The essence of technologies associated with CELSS can support human lift even at extremely harsh conditions such as in deserts, polar regions, and under the ocean on Earth as well as in space.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.20 no.12
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• pp.271-279
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• 2019

In extreme environment regions, unmanned rovers equipped with various sensors and devices are being developed for long-term exploration on behalf of humans. On the other hand, due to the harsh weather conditions and rough terrain, the rover camera has limited visible distance and field of view. Therefore, the rover cameras should be located for safe navigation and efficient terrain mapping. In this regard, to minimize the cost and time to manufacture the camera system on a rover, the simulation method using the rover design is presented to optimize the camera locations on the rover efficiently. In the simulation, a simulated terrain was taken from cameras with different locations and angles. The visible distance and overlapped extent of camera images, and terrain data accuracy calculated from the simulation were compared to determine the optimal locations of the rover's cameras. The simulated results will be used to manufacture a rover and camera system. In addition, self and system calibrations will be conducted to calculate the accurate position of the camera system on the rover.