• 대한공업교육학회지
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• v.33 no.2
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• pp.312-324
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• 2008

To improve the newly designed HKS(hinge kit system) in common refrigerators, it was investigated the new robust methodologies. There were the study of failure modes, mechanisms in the marketplace, and the design parameters of HKS with various improvements using accelerated life testing. Based on the claimed marketplace product returns and 1st ALT reproduction, the fracturing and cracking occur in the housing of the HKS. The missing design parameters of the failed HKS in the design phase of the refrigerator was the housing hinge kit structure. The corrective action plans are the modifications of the housing hinge kit structure from the open supporting to all supporting structure. Based on 2nd ALTs, the fracturing and cracking occur in the torsion shaft. The missing design parameter was the roundness of torsion shaft. After a sequence of ALT testing, the levels of the missing design parameters were setup. The yearly failure rate and B1 life of the redesigned HKS, based on the results of ALT, were over 0.01 percent and 10 years, respectively. The parameter design through the inspection of the failed product, load analysis, and three rounds of ALT, was very effective in the new robust design methodologies of the mechanical system and this method can be applied to other design system.

• Aerospace Engineering and Technology
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• v.6 no.1
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• pp.109-113
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• 2007

In this paper, the design process of the High Voltage Power Supply for RLG(Ring Laser Gyroscope) is described. The specification for High Voltage Power Supply(HVPS) is proposed. Also, The analysis of Flyback converter topology is explained. The Design for the HVPS is composed of the inverter circuit, feedback control circuit, high frequency switching transformer design, and voltage doubler circuit.

• Bulletin of the Korean Space Science Society
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• 2003.10a
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• pp.57-57
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• 2003

우리별 3호는 1996년 5월 26일 발사하여 2002년 12월까지 수명 초과에 따른 성능 하락으로 임무 수행을 마칠 때까지 설계 예상 수명 3년을 초과하여 약 3년 7개월 동안 운용되었다. 인공위성은 운용 되는 동안 종종 예측하지 못한 이상현상을 겪는다. 이러한 이상현상은 인공위성의 임무 수행을 일시적으로 중지시키며 심지어는 인공위성의 작동을 완전히 불가능하게 만들기도 한다. 이러한 이상현상 발생은 매년 수백 건씩 기록되고 있으며 인공위성 시스템이 복잡해짐에 따라 더욱 증가하고 있는 실정이다. 인공위성에서 발생하는 이상현상은 다양한 원인에 기인하며 시스템 설계 오류, 제작 오류, 운용 오류, 우주환경이 끼치는 영향 등이 있다. 우리별 3호 또한 운용 동안 발생한 이상현상으로 임무를 제한적으로 수행하기도 하였다. 인공위성에서 발생한 이상현상을 분석 및 해결함으로서 임무수행을 원활히 할 수 있을 뿐만 아니라 더 나아가서 분석 경험과 축적된 자료를 통해서 이상현상을 예측 및 대비할 수 있고 위성의 성능과 수명 평가의 지표로 삼을 수 있으며 위성의 문제점을 보완하여 향 후 향상된 위성을 개발하는데 기여할 수 있다. 본 연구에서는 궤도상에서 발생한 이상현상을 각 서브시스템 별로 임무 수행에 끼치는 영향, 위성체에 미치는 영향, 발생원인, 이상현상 종류, 처리 방법으로 분류하여 살펴보았고 그 분석 결과를 과학위성 1호 개발 시 문제점 보완에 적용한 사항에 대하여 살펴보았다.

• Journal of the Korean Data and Information Science Society
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• v.24 no.3
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• pp.571-584
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• 2013

Various risk factors other than age and sex affecting human mortality have been identified and quantitatively analyzed by previous studies in many area of research. Marital status is one of key mortality risk factors which affect life expectancy directly or indirectly. Relevant results have implication on risk management for both of social and private insurance. In this paper, a mortality model to reflect mortality differential according to marital status and possible transitions among marital status is designed. Various actuarial calculations were performed and related issues were discussed.

• Journal of the Korean Society for Railway
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• v.13 no.3
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• pp.257-263
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• 2010

Operation and maintenance cost of a rolling stock is generally higher than its acquisition cost. Therefore, it is necessary for reducing life cycle cost (LCC) to make rolling stocks easy and low costly for operation and maintenance. In addition, their operation and maintenance support systems should be effective and efficient. To accomplish this, operator should specify LCC requirements in the early stage of acquisition and make a contractor to provide the rolling stocks of low LCC. This article presents a procedure and a verifiable LCC model available in the general acquisition process where an operator specify requirements and a contractor provide the rolling stock meeting the requirements.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 2004.05a
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• pp.63-63
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• 2004

구동 및 동력 전달용으로 많이 쓰이는 기어장치는 최근 고속도비에서 사용이 증가함에 따라 다단기어장치의 설계에 대한 관심이 높아지고 있다. 하지만 다단 기어장치의 설계는 장치의 파손확률을 고려하지 않고 정적인 하중과 균일한 강도를 유지하는 차원에서 접촉해석과 강도설계 등이 주류를 이루었으며 대부분 설계자의 경험과 감각에 의해 시행착오적이고 반복적인 방식으로 이루어지고 있다. 또한 임의의 시간에서 다단 기어장치가 설계자의 의도대로 작동할 확률인 신뢰성에 대한 연구가 미흡하였다.(중략)

• Transactions of the Korean Society of Mechanical Engineers
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• v.15 no.6
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• pp.1908-1918
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• 1991

Fatigue tests have been carried out to measure the degradation of the residual strength and the fatigue life in carbon/epoxy (0/45/90/-45)$_{2s}$ composite materials. Theoretical predictions of residual strength and fatigue life were compared with experimental results. Distribution characteristics were studied using the probability of failure based on the cumulative distribution function and median rand. The static ultimate strength of carbon/epoxy composites used herein is observed to be relatively higher than that of existing similar composites ; while fatigue life is shorter due to the brittleness of matrix. The fatigue life obtained in these experiments is shorter than that estimated by residual strength degradation model when the stress level above 0.6 For the stress level of 0.6, the experimental value was abruptly increased. The cumulative distribution function for the static ultimate strength is well correlated to that for the strength converted from the measured fatigue life. Also, the predicted distribution of residual strength shows good agreement with the experimental results. Therefore, it is proven that the residual strength degradation model is reasonable.e.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.5
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• pp.127-133
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• 2002

The general requirements to achieve the structural integrity of the airframe are described in the military specification, MIL-STD-1530A. One of these requirements is the durability and damage tolerance of the airframe, which should be shown through the analysis and test based on the related specifications. This paper introduces the full scale durability test to evaluate the structural safety and durability of the basic trainer, KT-1. The test was performed according to the procedure in the military specification. The flight by flight load spectrum was developed by KT-1 fatigue load criteria and used for the durability test. The durability test had been performed for 4 service lives and was completed successfully. Therefore, it was shown that KT-1 airframe satisfied the durability requirements.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.8
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• pp.661-669
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• 2021

A mechanical stiffener has been mainly applied on a PCB to secure fatigue life of a solder joint of an electronic components in spaceborne electronics by minimizing bending displacement of the PCB. However, it causes an increase of mass and volume of the electronics. The high damping PCB implemented by multi-layered viscoelastic tapes of a previous research was effective for assuring the fatigue life of the solder joint, but it also has a limitation to decrease accommodation efficiency for the components on the PCB. In this study, we proposed high damping PCB with a multi-layered superelastic shape memory alloy stiffener for spatialminimized, light-weighted, high-integrated structure design of the electronics. To investigate the basic characteristics of the proposed PCB, a static load test, a free vibration test were performed. Then, the high damping characteristic and the design effectiveness of the PCB were validated through a random vibration test.

• Proceedings of the Korean Nuclear Society Conference
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• 1998.05b
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• pp.777-782
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• 1998

원자로 압력용기의 건전성은 원전의 수명과 직결되며, 압력용기는 운전기간동안 중성자의 조사에 의해 재료의 성질이 저하된다. 중성자 조사량 감소방안을 도출하기 위해 MCNP코드를 이용, 고리 1호기 14주기 원자로심을 3차원으로 모델링하고, 원자로심 핵연료집합체를 제외한 주변구조물에 새로운 추가차폐체를 설치하여 조사량 감소에 효과가 있는 위치를 찾고, 여러 재질의 차폐 성능도 평가하였다. 분석결과, Ta 패드를 이용한 설계안의 경우에 압력용기 용접부위에서 약 32% 정도의 속중성자 조사량 감소가 있음을 확인하였다.