• 대한기계학회논문집A
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• 제33권5호
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• pp.521-528
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• 2009

One of reliability measurements of vehicle is estimated by driving mileage but the reliability of component, such as an hydraulic clutch system, is defined from the number of successful operational cycle. Relationship between these reliability measurement variables(mileage and cycle) should be examined first of all in the reliability estimation of components. Relationship between mileage and cycles is commonly known as linear function. However, the gradient depends on the operational environmental condition. Therefore, estimation of mission profile variable should be done with correlation analysis at the same time. In this paper, we derive mission profile variable of an hydraulic clutch system by field vehicle test and suggest the determination process of durability test parameters of CMC(Clutch Master Cylinder) with mission profile variable.

• 항공우주시스템공학회지
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• 제18권1호
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• pp.11-20
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• 2024

최근 뉴스페이스 시대에는 과거의 고신뢰성 위성과 다르게 낮은 신뢰성 위성을 저가의 개발/양산 비용으로 개발하여 군집위성을 발사하고 있다. 경제적인 군집위성 개발을 위해서는 위성 사용자/개발자는 군집위성으로 발사되었을 때 기대되는 수명기간 동안 임무 성능의 유지 가능성 여부를 검토해야 한다. 또한, 성능유지를 위해 임의 고장에 의한 교체 계획도 수립되어야 한다. 본 연구에서는 지구관측 군집위성의 임무 성능의 유지와 교체 전략 수립을 위해 시스템 신뢰성 및 가용성 평가 방법을 제안하였다. 본 연구에서는 위성 백업 및 지상 추가 발사 백업 상황과 군집위성에 요구되는 임무 성능을 고려한 군집위성 신뢰성 및 가용성 모델을 구성하였다. 신뢰성 모델은 k-out-of-n system의 개념으로 구성되었고 가용성 모델은 마르코프 체인 모델을 이용하였다. 제안된 신뢰성 모델을 바탕으로 임무 요구사항에 필요한 최소 위성 개수를 정의하고, 요구 임무기간 동안 요구 임무 신뢰성 만족을 위해 궤도상 필요한 위성을 계산하였다. 또한 가용성 분석을 통해 요구 서비스기간 동안 요구 가용성 만족을 위한 궤도상 위성 여분 및 지상 여분의 개수를 분석하였다. 마지막으로 비용모델을 적용하여 위성의 신뢰성 및 개발 위성 개수간에 절충분석 개념을 제안하였다.

• 한국경영과학회지
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• 제18권1호
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• pp.71-78
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• 1993

A Baysian approach is proposed is estimating the mission failure rates by criticalities. A mission failure which occurs according to a Poisson process with unknown rate is assumed to be classified as one of the criticality levels with an unknown probability. We employ the Gamma prior for the mission failure rate and the Dirichlet prior for the criticality probabilities. Posterior distributions of the mission rates by criticalities and predictive distributions of the time to failure are derived.

• 한국국방경영분석학회지
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• 제15권1호
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• pp.14-27
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• 1989

This paper deals with the mission effectiveness of an airfleet, Airfleet operating system consists of a finite number of units performing the several mission types. Earlier works for the mission effectiveness of a fleet is limited to only one mission type and computer simulation approaches. The mission effectiveness. model of a fleet is constructed by three attributes - the mission readiness of the units, the mission reliability and capability of units. The environmental conditions and human factors affecting the mission success are considered together. The solution of the model is obtained by analytical technique. Especially, AOS is considered a closed queueing network with a finite number of units and a single job class. And then, the mission readiness of the units is found by the mean value analysis. The model would be a useful tool to readily evaluate mission effectiveness of a airfleet as it is and provide a criterion for determining the optimal operating policy.

• 전력전자학회논문지
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• 제27권3호
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• pp.221-227
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• 2022

The reliability improvement of PV systems is an important factor in reducing the cost of PV energy because it is closely related to the annual energy production as well as the maintenance cost of PV systems. The reliability of PV inverters plays a key role in the reliability of PV systems because it is regarded as one of the most reliable critical parts of PV systems. The lifetime evaluation of PV inverters considering the mission profile in the design phase plays an important role in reliability design to ensure the required lifetime of PV inverters. In this paper, the lifetime of representative single-phase T-type and I-type NPC inverters are comparatively evaluated by considering the mission profile of a PV system recorded at Iza, Spain. Furthermore, the effect of the pulse width modulation methods on the lifetime is also discussed. The lifetime evaluation of PV inverters is performed at the component-level first and then the system level by considering all power devices.

• 한국철도학회논문집
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• 제20권5호
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• pp.569-576
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• 2017

전동차의 공기 작동식 출입문을 작동하기 위한 공기를 공급 또는 차단의 역할을 하는 전자변은 고장발생시 승객의 안전은 물론 정상운행을 불가능하게 하는 중요한 부품이므로 높은 신뢰도가 요구되지만 누기로 인한 고장 비율이 높은 편이다. 국내 도시철도 운영기관들은 고정주기와 임의 여유기간을 적용한 전동차 중정비 주기로 전자변을 정비한다. 현행 중정비 주기 방식의 대안으로 고장 신뢰도를 고려한 정비주기를 제시하고자 지하철 6호선 전동차 전자변 고장 통계자료에 상용 통계프로그램(MINITAB)을 적용하여 신뢰도 함수(Reliability Function)와 임무신뢰도(Mission Reliability)를 계산하고 적정 정비주기를 도출하였다. 도출된 정비 주기는 현 4년 주기의 정비의 부품신뢰도를 68%에서 95%로 향상시키는 것이므로 전자변의 신뢰도를 획기적으로 향상시킬 수 있을 것이다.

• 품질경영학회지
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• 제40권3호
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• pp.278-285
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• 2012

Purpose: Weapon systems have the long life cycle unlike the consumer product. Thus, the reliability of weapon system is improved during the life cycle through the steady technical change. In this paper, we deal with the method of evaluating the reliability of weapon system with the field failure data. Methods: Especially, we present how to gather the field failure data and evaluate the reliability through the case of K-series weapon system. To evaluate reliability, the reliability growth model is used and the result is discussed. Results: It is steadily improved the reliability of K-series weapon system deployed from 2000 to 2004. The frequency of the failures that affect the mission is largely reduced and MTBMF(mean time between mission failure) is also improved. Conclusion: We can guess the trend of the reliability of weapon system with the field data through this study. Furthermore, it can be used to improve the reliability and make maintenance policy.

• 항공우주기술
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• 제7권1호
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• pp.183-193
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• 2008

본 논문은 KSLV-I 상단부에 대한 고장모드 분석 결과와 시스템 수준의 비행시험 신뢰도 모델을 기술한다. 먼저, KSLV-I 상단부의 14개의 주요 기능과 비행시험 임무 프로파일을 분석하고, 기능 분석 결과와 임무 구간별 수행 기능 목록을 바탕으로 시스템 체계에 따른 상단부의 고장모드 계층 구조와 시스템 수준의 비행시험 신뢰도 모델을 구성한다.

• 한국항공운항학회지
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• 제23권4호
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• pp.117-124
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• 2015

RAM (Reliability, Availability and Maintenance) has been applied to design and analysis tools which affects system's operational sustainability and its life cycle cost as RAM-c(2009 DoD). RAM-c plays also an important role to guarantee the system engineering for mission assurance. Reliability is highly related to the probability of system failure. Availability means mission capability or the condition of ready to mission. Maintenance includes both the repair to recover the system in the event of failure/unexpected breakdown and proactive maintenance to prolong the design service life of the system or machinery. It is the purpose that this paper is to analyze and conclude the objective service life of UAV. The more UAV is operated, the less the level of its reliability becomes. Repairing failures and supplying spare parts on time, system reliability could be improved up until the time over target. Applying statistical Weibull distributions, this paper suggests the analysis of the design service life and economic life of UAV based on RAM-c with operational data.

• Journal of Astronomy and Space Sciences
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• 제26권4호
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• pp.635-642
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• 2009

This paper describes the Flight Dynamics Automation (FDA) system for COMS Flight Dynamics System (FDS) and its test result in terms of the performance of the automation jobs. FDA controls the flight dynamics functions such as orbit determination, orbit prediction, event prediction, and fuel accounting. The designed FDA is independent from the specific characteristics which are defined by spacecraft manufacturer or specific satellite missions. Therefore, FDA could easily links its autonomous job control functions to any satellite mission control system with some interface modification. By adding autonomous system along with flight dynamics system, it decreases the operator's tedious and repeated jobs but increase the usability and reliability of the system. Therefore, FDA is used to improve the completeness of whole mission control system's quality. The FDA is applied to the real flight dynamics system of a geostationary satellite, COMS and the experimental test is performed. The experimental result shows the stability and reliability of the mission control operations through the automatic job control.