• 한국군사과학기술학회지
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• 제15권5호
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• pp.660-666
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• 2012

The weapon system is getting more and more expensive, complex and smarter. Therefore, efficiently and effectively, it is important to operate the weapon system. OMS/MP is a document to quantify operational factors like as environment, mission, mode etc. It is important data to perform RAM analysis in early weapon development phase and operate better a weapon system. This paper present a process and framework of OMS/MP for a naval ship with a deep analysis of relevant domestic and abroad case studies. It propose OMS/MP analysis framework based on wartime scenario and mission area analysis. This result will contribute not only improvement for the availability of a naval ship but also enhancement of RAM analysis process.

• 한국정보통신학회논문지
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• 제24권3호
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• pp.435-440
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• 2020

최근 무인이동체를 활용한 서비스 수요가 다양해지고 무인이동체 서비스 시장의 규모가 급격하게 증가하고 있다. 특히 산불 진압, 우편 배송, 시설 관리 등 공공임무 분야에서의 무인이동체 활용 서비스 요구도가 높아지고 있다. 이러한 요구도의 증가와 함께 무인이동체 기반의 다양한 임무 수행을 지원하기 위한 무인이동체 탑재용 임무소프트웨어 개발의 중요도가 갈수록 높아지고 있는 추세이다. 공통화 된 임무소프트웨어 개발을 위해서는 다양한 공공기관에서 공통적으로 필요한 임무 분석을 통해 재사용 가능한 기능들을 라이브러리로 개발하고, 이를 활용하여 무인이동체 관련 기업들이 쉽게 임무소프트웨어를 개발할 수 있도록 구조 설계가 이루어져야 한다. 본 논문에서는 공공임무용 무인이동체 전용 임무소프트웨어 연구 동향에 대해서 언급하고, 소프트웨어 개발을 위한 정형화된 임무소프트웨어의 구조 설계를 제안한다. 마지막으로, 임무소프트웨어와 데이터 플랫폼 간 데이터 전송 아키텍처를 제안한다.

• 한국항공운항학회지
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• 제16권4호
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• pp.41-48
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• 2008

Functional analysis of air transport mission is conducted to establish the performance requirements of the commercial transport designs. The analysis process begins by making a top-down analysis to the aircraft system level mission functions. Correctly interpreting the top-level performance requirements is the first step in designing and building an aircraft system. Each function and sub-function is allocated and examined to the aircraft level and flight operations phase to optimize the system performance and design requirements, such that these lower-level requirements can be traced back to the top-level requirements they are designed to fulfill. Special attention is given to making sure all interfaces, both internal and external, are addressed. The results are also in good resources of functional hazard assessment involved in certification processes.

• 한국군사과학기술학회지
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• 제19권2호
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• pp.244-251
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• 2016

In defense domain, mission level and engagement level simulation tools exist. In order to experiment a simulation scenario for obtaining results of both mission level and engagement level simulations, we should write a same simulation scenario in a mission level simulation tool as well as an engagement level simulation tool, and we have to operate these tools for analysis of each purpose. Moreover, we could not guarantee that these scenarios are completely same since each scenario is composed of different fidelities of simulation models, although the scenarios are written by a same experimenter and with same simulation purpose. To deal with the difficulties, I propose an approach to analysis of both mission level and engagement level simulations from one simulation result. For this, I have built Composite Combat Mission Planning Simulation Environment (CCMPSE). In this paper, the HLA/RTI based simulation composition technology and my experiences for the designed Composite Combat Mission Planning Simulation Control System (CCMPSCS) are explained. Moreover, This paper also conducts a case study with EADSIM, SADM, and the CCMPSCS. Finally, this paper provides lesson learned from the case study.

• Journal of Astronomy and Space Sciences
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• 제17권2호
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• pp.285-294
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• 2000

The post-launch mission analysis of the KOMPSAT-1 spacecraft was carried out. The injection accuracy of the Taurus launch vehicle was analyzed by comparison of the target and the realized orbit parameters. The tracking station contact analysis was also performed based on the state vectors applied at the day of launch. The offset angles between the predicted orbit and realized orbit were calculated for various tracking stations. The injection orbit parameters of the KOMPSAT-1 were analyzed for the possible options in Launch and Early Orbit Phase(LEOP) operations. Variations of the Local Time of Ascending Node(LTAN) were also obtained.

• 한국항공운항학회지
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• 제16권4호
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• pp.63-68
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• 2008

Compared with past, helicopters have remarkably high level of safety and accidents due to mechanical defects are decreased about 15%. Most of their duties, however, are to commit at duty area which is hard to access. Because of them, collision probability is high and also has relatively higher accident rates than other aircraft with special mission. A result of analysis is that accident rate is relative high with prevention of disasters, putting out a fire and crop-dusting missions under 500ft. In addition, most of accidents are related with human factors. According to this, it is required to pilots who carry these mission that safety education and detailed analysis about their mission.

• 천문학회보
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• 제41권1호
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• pp.78.4-79
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• 2016

This study aims to overview research articles on extrasolar planets using Kepler mission data during the period of 2009-2015 in order to discover research trends in them. Kepler space observatory is a NASA space observatory for extrasolar planet expedition launched in March 2009, contributed to the discovery and tracking of extrasolar planets and its candidates. In order to achieve the goal of this study, we classified research subjects from studies on Kepler mission data year by year and found the most frequent research topics each year. We also conducted a comparative analysis on the research subjects based on time series and examined any changes with respect to the goal of Kepler mission. Statistical meta-analysis is employed as the analysis method for the key words presented in the research articles. This study is a part of on-going research to find the correlation between the physical parameters of the host star and extrasolar planets. The results of this study could offer new directions in researches utilizing Kepler mission data as those meta-analyses in social sciences often suggest new opportunities. We have high expectations that more extrasolar planet studies will follow as we make further progresses in various analyses.

• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2004년도 Proceedings of ISRS 2004
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• pp.512-514
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• 2004

The Electro-Optical Camera (EOC) is a high spatial resolution, visible imaging sensor which collects visible image data of the earth's sunlit surface and is the primary payload on KOMPSAT-l. The purpose of the EOC payload is to provide high resolution visible imagery data to support cartography of the Korean Peninsula. The EOC is a push broom-scanned sensor which incorporates a single nadir looking telescope. At the nominal altitude of 685Km with the spacecraft in a nadir pointing attitude, the EOC collects data with a ground sample distance of approximately 6.6 meters and a swath width of around 17Km. The EOC is designed to operate with a duty cycle of up to 2 minutes (contiguous) per orbit over the mission lifetime of 3 years with the functions of programmable gain/offset. The EOC has no pointing mechanism of its own. EOC pointing is accomplished by right and left rolling of the spacecraft, as needed. Under nominal operating conditions, the spacecraft can be rolled to an angle in the range from +/- 15 to 30 degrees to support the collection of stereo data. In this paper, the status of EOC such as temperature, dark calibration, cover operation and thermal control is checked and analyzed by continuously monitored state of health (SOH) data and image data during the mission life of 3 years. The aliveness of EOC and operation continuation beyond mission life is confirmed by the results of the analysis.

• 정보처리학회논문지A
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• 제16A권4호
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• pp.235-244
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• 2009

대공방어용 임무지향 컴퓨터는 장시간의 대공방어 임무를 성공적으로 완수하기 위하여 고장감내 기능이 필수적으로 요구되며, 고장감내 기법으로는 지상 장비인 임무지향 컴퓨터에 적합한 저비용의 기법이 요구된다. 현재 기본형의 임무지향 컴퓨터에는 저비용의 ASR 고장 감내 기법이 적용되어 있으나, ASR 기법은 TMR 기법을 적용한 컴퓨터에 비해 낮은 임무 신뢰도를 제공한다. 그러므로 본 논문에서는 TMR 기법을 적용한 컴퓨터 보다 적은 수량의 프로세서 보드를 사용하여 우수한 신뢰도를 제공하는 확장형 ASR(EASR) 고장 감내 기법을 제안하였으며, 제안된 EASR 기법 을 적용한 임무지향 컴퓨터의 고장 감내 성능을 입증하였다. EASR 기법의 임무지향 컴퓨터는 고장 감내 성능과 저비용성 측면에서 대공방어 시스템의 컴퓨터에 적합하였다.

• 항공우주기술
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• 제2권2호
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• pp.96-104
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• 2003

정지궤도 인공위성의 추진시스템은 위성발사에서부터 모든 임무궤도의 자세제어와 마지막 임무단계인 폐기궤도 기동을 위한 다양한 속도증분을 제공한다. 이러한 추진시스템은 위성제작사에 따라 매우 다양하게 구성되고 있으며 버스체마다 사용되는 추력기 또한 매우 다양하다. 따라서 각 정지궤도위성 제작사에서는 각각의 추진시스템에 맞는 모든 궤도 관련 임무를 계획하고 검증하는 임무해석소프트웨어를 개발하고 있다. 이러한 범용화된 임무해석소프트웨어를 개발하기 위하여 다양한 추력기 데이터를 검토하였고 이를 토대로 일반화된 추력기 모델링식을 구축하였다.