• International Journal of Aeronautical and Space Sciences
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• 제17권4호
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• pp.565-578
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• 2016

A probabilistic based systems approach is addressed in this study for the reliability prediction of solid rocket motors (SRM). To achieve this goal, quantitative Failure Modes, Effects and Criticality Analysis (FMECA) approach is employed to determine the reliability of components, which are integrated into the Fault Tree Analysis (FTA) to obtain the system reliability. The quantitative FMECA is implemented by burden and capability approach when they are available. Otherwise, the semi-quantitative FMECA is taken using the failure rate handbook. Among the many failure modes in the SRM, four most important problems are chosen to illustrate the burden and capability approach, which are the rupture, fracture of the case, and leak due to the jointed bolt and O-ring seal failure. Four algorithms are employed to determine the failure probability of these problems, and compared with those by the Monte Carlo Simulation as well as the commercial code NESSUS for verification. Overall, the study offers a comprehensive treatment of the reliability practice for the SRM development, and may be useful across the wide range of propulsion systems in the aerospace community.

• 품질경영학회지
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• 제48권3호
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• pp.395-408
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• 2020

Purpose: This study was performed for advancement of aviation security equipments certification system. Methods: We investigated aviation security equipments certification-related registrations and the latest research trends of explosive detection technologies. Based on the literature studies, we draw the critical issues of the aviation security equipment certification system and suggested improvement direction. Results: We found some inaccuracies of the definition of explosive trace detection equipments, accreditation review committee, and performance evaluation test method. These problems should be modified to suit being practical. Conclusion: The present results would be useful for basic data for modifying aviation security equipments certification systems.

• 한국신뢰성학회지:신뢰성응용연구
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• 제8권3호
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• pp.145-154
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• 2008

인공위성은 지상 시스템과는 달리 극한 발사환경 및 우주환경에 노출되고, 운용 중 수리가 불가능하며, 임무 실패에 따른 위험비용이 매우 크기 때문에 고신뢰성, 고비용의 부품, 장비 및 시스템을 채택하여 개념설계단계에서부터 신뢰성을 관리한다. 신뢰성 관리의 주요 목적은 설계변경 및 개발 사이클의 반복을 최소화하고, 개발비용을 절감하며, 시스템의 신뢰성을 향상시키기 위한 것으로서, 대부분의 우주시스템 개발 프로젝트에서는 제품보증(Product Assurance) 활동의 일환으로 수행된다. 제품보증 업무는 크게 품질보증, 신뢰성 관리, EEE 부품관리, 재료 및 공정(Material & Process) 관리, 오염관리, 소프트웨어 품질보증 등으로 구분되지만, 포괄적인 의미의 신뢰성 관리 범주에 이를 모두 포함시키기도 한다. 인공 위성의 개발과정에서 기술성능지표 중 하나로서 중점 관리되고 있는 시스템 신뢰성 관리의 세부기법, 프로세스, 개선 필요사항 등에 대하여 살펴보고자 한다.

• 품질경영학회지
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• 제49권2호
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• pp.113-125
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• 2021

Purpose: This study focused on reality and quality improvement of aviation security equipment performance certification system. Methods: For this propose, we analyzed aviation security equipment performance certification system related legislations. Using analyzed data, we suggested advancement plan of aviation security equipment performance certification system. Results: In results, South Korea has been implementing aviation security performance certification system since October 2018. Parts for improvement of system are mutual certification with major countries that operate aviation security equipment performance certification systems, the spread of the defense industry's system, development of similar substances for handling explosives, and introduction of preliminary inspections. Conclusion: The research result could be used as a basic data for upgrading Korea's aviation security performance certification system.

• 품질경영학회지
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• 제42권4호
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• pp.633-646
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• 2014

Purpose: The conventional predicted MFTBF by military standard has a wide discrepancy to that of real-world operation, which leads to overstock and increase operation cost. This paper introduces a analyzing frame using operational reliability and cost data to overcome the discrepancy, and provides reliability improvement process employing the analyzing frame. Methods: This paper suggests Reliability-Cost Matrix (R-C Matrix) and Operational Reliability & Cost Index (ORCI) as a tool for reliability evaluation. Results: KOREIP(KAI's Operational Reliability Evaluation and Improvement Process) is developed employing Reliability-Cost Matrix and Operational Reliability & Cost Index. Conclusion: KOREIP provides a process and its activities based on Reliability-Cost Matrix frame. The process and activities leads reliability improvement of aerospace electronic equipments by means of categorizing and follow-up action based on the concept of frame.

• 시스템엔지니어링학술지
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• 제1권1호
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• pp.61-66
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• 2005

In executing the large scale national project, such as development of space launch vehicle, it is most important to guarantee the technological reliability. However the reliability analysis of launch vehicle is different from other mass product goods because of the limitation of budget and number of tests. In this study, the reliability analysis technique of the propulsion system, which is one of the major sub-systems of launch vehicle is illustrated and applied to the liquid rocket engine of KSR-III.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2004년도 한국우주과학회보 제13권2호
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• pp.341-343
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• 2004

In executing the large scale national project, such as development of space launch vehicle, it is most important to guarantee the technological reliability. However the reliability analysis of launch vehicle is different from other mass product goods because of the limitation of budget and number of tests. In this study, the reliability analysis technique of the propulsion system, which is one of the major sub-systems of launch vehicle is illustrated and applied to the liquid rocket engine of KSR-III.

• 한국신뢰성학회지:신뢰성응용연구
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• 제4권2호
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• pp.105-119
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• 2004

Reliability program is essential to the development of space systems like launch vehicles and satellites, as they are non-repairable after launch and the failure of a launch vehicle resulted in catastrophic consequences for the mission. Foreign advanced space organizations have developed and implemented their own reliability management programs for launch vehicles from the conceptual design stage to the detail processes for the individual components, procedures and test reports. A study on the launch failures and the reliability analysis methods for one-shot devices contained in this paper will contribute to the reliability improvement for Korean launch vehicle and components.

• 한국항공우주학회지
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• 제47권10호
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• pp.747-752
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• 2019

신뢰성 성장 시험을 수행하며 획득하게 되는 고장 정보와 누적 시험수행시간을 이용하면 신뢰성 성장 모델의 모수 추정이 가능하며, 모수 추정을 통해 해당 제품의 MTBF를 예측할 수 있다. 그러나 시험에 대한 비용, 시간 혹은 제품의 특성 등의 여러 제약으로 인해 고장 정보가 구간적으로 획득되거나, 획득한 고장 정보의 샘플 데이터(Sample Data)의 수가 작을 수 있다. 이는 신뢰성 성장 모델의 모수 추정의 오차를 커지게 하는 원인이 될 수 있다. 본 논문에서는 샘플 데이터의 수가 작을 경우 신뢰성 성장 모델의 모수 추정 시 베이지안 기법 기반의 모수 추정 방법의 적용에 대해 연구를 수행하였다. 시뮬레이션 결과 신뢰성 성장 모델의 모수를 추정할 때, MLE를 적용하여 추정하는 방법보다 베이지안 기법을 적용하는 방법이 추정 정확도가 높음을 확인하였다.

• Structural Engineering and Mechanics
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• 제62권2호
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• pp.125-138
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• 2017

Reliability-based design optimization (RBDO) is a powerful tool for design optimization when considering probabilistic characteristics of design variables. However, it is often computationally intensive because of the coupling of reliability analysis and cost minimization. In this study, the concept of reliability mapping function is defined based on the relationship between the reliability index obtained by using the mean value first order reliability method and the failure probability obtained by using an improved response surface method. Double-loop involved in the classical RBDO can be converted into single-loop by using the reliability mapping function. Since the computational effort of the mean value first order reliability method is minimal, RBDO by using reliability mapping functions should be highly efficient. Engineering examples are given to demonstrate the efficiency and accuracy of the proposed method. Numerical results indicated that the proposed method has the similar accuracy as Monte Carlo simulation, and it can obviously reduce the computational effort.