• Journal of the Korea Society for Simulation
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• v.29 no.1
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• pp.31-38
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• 2020

Mission reliability is defined by the probability of accomplishing the requirements task that were targeted in product development, and in the case of combat systems, mission reliability is an important factor that will determine victory or defeat, unlike commercial equipment. The mission reliability of the existing domestic combat system was calculated by considering only the physical connections of the equipment involved in the mission performance, but as the equipment becomes increasingly sophisticated and complex, it is impossible to determine the mission relevance solely by physical connection. Thus, in this paper, improved mission reliability was calculated using SysML, the system design modeling language, by taking into account the functional connection as well as physical connection. Based on this research, we look forward that the mission reliability of the combat system that will be developed in the future will be used as a verification material.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.20 no.9
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• pp.451-458
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• 2019

Reliability in the course of weapons system development and operation is a key measure of the ability of a system to perform the required functions under specified conditions over a specified period of time, and the mission confidence for the assessment of mission fulfillment is an important indicator of victory or defeat in a battle. Mission reliability indicates the probability that a given task will succeed or fail in an event or environmental situation over a given period of time. The existing mission reliability was calculated after creating a confidence blow map with only physical connections based on the mission. However, as modern weapons systems evolve and advance, the related equipment structure becomes increasingly complex, making it impossible to express mission relevance when mission classification is required based on functional or physical connections. In this study, the mission reliability was calculated for a gun control system, which is part of a ship's combat system, by expressing the association between the physical and functional structures using the design structure matrix technique and the interface matrix technique. We expect the study results to be used as verification data for mission reliability.

• The KIPS Transactions:PartA
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• v.15A no.6
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• pp.309-316
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• 2008

The mission-critical engagement control computer for air defense has to maintain its operation without any fault for a long mission time. The mission performed by large-scale and complex embedded software is extremely critical in terms of dependability and safety of computer system, and it is very important that engagement control computer has high reliability. The engagement control computer was implemented using four processors. The distributed computer composed of four processors quarantees the dependability and safety, and ASR fault-tolerant technique applied to each processor guarantees the reliability. In this paper, the mechanism and performance of ASR fault-tolerant technique are analysed. And MTBF, reliability, availability, and cost-effectiveness for ASR, DMR and TMR techniques applied to the engagement control computer are analysed. The mission-critical engagement control computer using software-based ASR fault-tolerant technique provides high reliability and fast recovery time at a low cost. The mission reliability of the engagement control computer using ASR technique in 4 processors board is almost same the reliability of the computer using TMR technique in 6 processors board. ASR technique is most suitable to the mission-critical engagement control computer.

• The KIPS Transactions:PartA
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• v.16A no.4
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• pp.235-244
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• 2009

The mission-critical computer for air defense has to maintain its operation without any fault for a long mission time and is required to implement at low cost. Now the reliability of the mission critical-computer using Active Sparing Redundancy fault-tolerant technique is inferior to that of the computer using TMR technique. So in this paper are proposed Extended ASR(EASR) technique that provides higher reliability than that of the computer using TMR technique. The fault-tolerant performance of the implemented mission-critical computer is proven through reliability analysis and numbers of fault recovery test. Also, the reliability of the mission-critical computer using EASR technique is compared with those of computer using ASR and TMR techniques. EASR technique is very suitable to the mission-critical computer.

• Proceedings of the Korean Operations and Management Science Society Conference
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• 1993.04a
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• pp.294-300
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• 1993

어떤 무기체계의 임무신뢰도분석에 베이지안기법을 사용하는데 있어 고장율이 주어졌을 때 고장간 시간이 지수분포를 따른다는 가정하에 이의 Conjugate Prior인 감마분포의 추정문제를 다룬다. 임무별 고장간시간에 대한 예측분포를 유도하였으며, 실제 측정된 기존의 임무별 고장간시간이 이 예측분포를 따른다는 전제하에 비선형 최소자승법을 이용하여 감마분포의 두 파라메터를 추정하는 방안을 제시하였다. 또한 대상 무기체계의 실제 고장자료를 이용하여 추정치를 구하였다.

• Journal of Astronomy and Space Sciences
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• v.15 no.2
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• pp.459-473
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• 1998

As the satellite system becomes more complex, the probability of unpredictable failures may be increased due to design inadequacy, experience deficiency, lack of problem recognition. Poor quality control, improper testing, and workmanship fault. Consequently, these problems can lead to the reduction or end of the satellite mission lifetime. This article addresses general satellite failure modes and factors influencing satellite mission life. The mission life factors of LEO sun-synchronous KOMPSAT spacecraft are investigated, in which its mission life is predicted based on these factors. Since the end of mission due to random failures is not predictable, the predictable mission life factors such as power budget, propellant budget, battery charging/discharging cycle, radiation effects payload reliability, single point failure, and redundancy are primarily investigated.

• Journal of Aerospace System Engineering
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• v.18 no.1
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• pp.11-20
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• 2024

In the recent era of NewSpace, unlike high-reliability satellites of the past, low-reliability satellites are being developed and mass-produced at a lower cost to launch constellations satellites. To achieve cost-effective cluster satellite development, satellite users and developers need to assess the feasibility of maintaining mission performance over the expected lifespan when cluster satellites are launched. Plans for replacements due to random failures should also be established to maintain performance. This study proposed a method for assessing system reliability and availability to maintain mission performance and establish replacement strategies for Earth observation constellation satellites. In this study, a constellation reliability and availability model considering mission performance required for a satellite constellation, situations of satellite backup, and additional ground backups was established. The reliability model was structured based on the concept of a k-out-of-n system and the availability model used a Markov chain model. Based on the proposed reliability model, the minimum number of satellites required to meet mission requirements was defined and satellites needed in orbit during the required mission period to satisfy mission reliability were calculated. This research also analyzed the number of spare satellites in orbit and on the ground required to meet the desired availability during required service period through availability analysis.

• Aerospace Engineering and Technology
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• v.7 no.1
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• pp.183-193
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• 2008

This paper shows the results of failure mode analysis and the system-level reliability model for the flight test of KSLV-I upper stage. First, the critical 14 functions of KSLV-I upper stage are identified and the mission profile of the flight test is analyzed. Then, based on the functional analysis and the mission profile analysis, we construct a hierarchical structure of failure modes and a system-level reliability model for the flight test of KSLV-I upper stage.

• Journal of Applied Reliability
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• v.6 no.2
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• pp.115-134
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• 2006

This paper deals with OO aircraft mission reliability prediction. To demonstrate user-required mission reliability, it is calculated with use general formulae which are used in reliability engineering. The mission reliability of OO aircraft is calculated in considering conversion factor (CF) on the each subsystems' MTBF. The prediction results are explained only the state at present time. Because these data are not real data in operational environments. Therefore, in the case of OO aircraft, it has to be needed collecting the real and renewal data which are operational and empirical. After that, continuing the data upgrading, it is easily closed to the more exact reliability value.

• Proceedings of the Korean Society of Machine Tool Engineers Conference
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• 1998.10a
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• pp.102-114
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• 1998

항공기 개발단계에서의 RAM(Reliability, Availability, Maintainability) 예측은 진행중인 설계개념이 RAM 개발 목표값을 달성할 수 있는지를 판단하여 이를 설계에 반영하기 위한 것이다. 본 연구에서 신뢰도 예측 모델은 항공기의 임무에 초점을 둔 임무신뢰도와 시스템신뢰도를 산출하고, 정비도 예측 모델은 군수지원분석자료(LSAR)와의 호환성을 유지할 수 있도록 하였으며, 가용도 예측 모델은 신뢰도와 정비도 자료를 활용한 운용가용도를 예측하는 데에 기준을 두었다. 본 연구는 기존의 RAM 예측이 각각 독립적으로 수행된 점을 보완하여 서로간의 상호관계를 반영한 통합 예측 모델을 개발하는 데에 초점을 두었으며, 실제적인 운용개념을 반영한 모델링으로서 항공기 개발단계에서 뿐만 아니라 실제 운용단계에서의 RAM 분석에 효과적이라 판단된다.