• Journal of the Korean Society of Manufacturing Process Engineers
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• v.17 no.1
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• pp.116-121
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• 2018

In this paper, we propose the SIIM fuzzy Quasi-sliding mode controller for the system of a double inverted pendulum on a cart. Since it is difficult to handle this 6th-order system, we decoupled the entire system into three $2^{nd}$ order subsystem, and we designed the SIIM fuzzy Quasi-sliding mode controller for each subsystem, which was easy and did not require the derivation of the equivalent control. The stability of the entire system is guaranteed using Lyapunov function. The validity and robustness of the proposed controller are demonstrated through the computer simulation, and the results are compared with the results of former studies.

• 한국항공운항학회:학술대회논문집
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• 2015.11a
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• pp.242-246
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• 2015

항공기 엔진 체계의 신뢰성과 안전성을 분석하는 것은 RAM 분석이라고 한다. RAM은 제작자가 개발한 시스템의 지속가능성 혹은 그 체계의 수명주기비용(Lice Cycle Cost)에 중대한 영향을 줄 수 있는 시스템 설계특성을 의미한다. 또한 RAM은 시스템이 개발될 당시에 의도된 임무를 수행할 수 있는 능력 혹은 임수수행을 성공할 수 있도록 담보하는 중요한 역할을 한다. RAM은 1970년대 이후 미국 군수분야에서는 군수지원성분석(LSA, Logistic Support Analysis) 과 밀접히 연계되어 활용되어 왔으며, RAM과 LSA를 통합하여 종합군수지원체계(ILS, Integrated Logistics Support)라고 부른다. 본 연구에서는 항공기 엔진에 대한 신뢰성 분석에 Weibull 분포를 활용하였다. Weibull 분포는 2개의 변수 적용에서 다음과 같이 정의된다. 변수가 그 계의 어떤 값을 나타내느냐에 따라 분포도 곡선의 특성 의미는 변수에 의존된다. 예를 들어 시험성적, 사회적 특성을 표현하는 인지도, 산업 제품의 고장이나 결함을 나타내는 고장관련 모수(변수) 등에 따라 그 특징을 나타내게 된다. 항공기 엔진의 신뢰성 분석을 통해 항공기 엔진의 수명 판단이 가능해졌으며 임무 불가능 수준의 In-Flight Shut-Down 비율이 현격히 감소됨을 확인할 수 있었다.

• Nuclear Engineering and Technology
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• v.29 no.6
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• pp.433-443
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• 1997

In this work, an analytic approach to the dependability of software in the operational phase is suggested with special attention to the hardware fault effects on the software behavior : The hardware faults considered are memory faults and the dependability measure in question is the reliability. The model is based on the simple reliability theory and the graph theory which represents the software with graph composed of nodes and arcs. Through proper transformation, the graph can be reduced to a simple two-node graph and the software reliability is derived from this graph. Using this model, we predict the reliability of an application software in the digital system (ILS) in the nuclear power plant and show the sensitivity of the software reliability to the major physical parameters which affect the software failure in the normal operation phase. We also found that the effects of the hardware faults on the software failure should be considered for predicting the software dependability accurately in operation phase, especially for the software which is executed frequently. This modeling method is particularly attractive for the medium size programs such as the microprocessor-based nuclear safety logic program.

• Current Industrial and Technological Trends in Aerospace
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• v.5 no.1
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• pp.93-103
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• 2007

3차원의 공간을 비행하는 항공기의 항행은 조종사가 직접 지상의 지형지물을 참조하며 비행하는 시각비행과 지상의 항행안전시설로부터 무선신호를 받아 비행하는 계기비행으로 구분되어 발전되었다. 현재 계기비행을 수행하기 위한 계기비행절차 수립에 기반이 되는 항행안전무선시설은 기존의 VOR(VHF Omni-directional Range), ILS(Instrument Landing System) 등의 지상기반 항행안전무선시설에서 GNSS (Global Navigation Satellite System)를 이용한 위성기반 항행으로 전환을 목표로 하고 있으며 항행체제 또한 기존의 Fix to Fix 항행체제에서 RNAV(Area Navigation) 체제로 전환되고 있는 추세이다. 계기비행절차는 항공기가 활주로를 이륙하여 항로로 진입하기 위한 계기출발절차(SID), 항로절차(Enroute), 항로에서 목적 공항의 지정된 활주로에 설정된 접근절차(Approach)로 인도하는 도착절차(STAR), 지정된 활주로에 착륙하기 위한 접근절차로 구분될 수 있으며 본문에서는 GNSS를 기반으로 하는 RNAV 절차(RNAVGNSS)에 대한 개괄적인 소개, 설계요건 및 RNAVGNSS 계기비행절차를 성공적으로 이행하기 위한 절차이행모델, RNAVGNSS 절차 수립에 중요하게 고려해야할 사항 등에 대하여 소개하도록 한다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1995.05a
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• pp.71-81
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• 1995

The Propulsion System Integration can be defined as the optimization technology of combining the propulsion system components with the airframe to achieve the overall aircraft misson performance goals. The disposition of propulsion system components on engine compartment enveloped by front fuselage and fire bulkhead is very restricted because of the interference with nose L/G and engine mountig strut. The design of components depends on the traditional technical data base. The engine satisfying a customer's ROC was selected among worldwide existing engines by the comparision studies of performance analysis with enigine installed effect, future growth potential, ILS, and application to aircrafts, etc. The ground test of the propulsion system integration was performed in the test cell and on the aircraft to assure the function of the components. The flight test was performed to confirm complying the performance requirements.

• Journal of Aerospace System Engineering
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• v.1 no.4
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• pp.22-27
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• 2007

The 150 gal Ion EFT(External Fuel Tank) used to enlarge the aircraft operation range was adopted an import equipment in T-50 FSD phase. But in Production phase the EFT was planed to develop for the stable ILS(Integrated Logistics Support) and technical ability improvement by using the composite materials. The design for configuration and fuel system is intended to maintain compatibility with aircraft systems and the development test is performed on component, assembly and aircraft. This study is conducted to provide the technology of design and test for the 150 gallon composite EFT in LRU level. The test results show that the composite EFT is satisfied with structural, functional and environment requirements which are described in specification.

• Journal of the Korean Data and Information Science Society
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• v.17 no.3
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• pp.727-742
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• 2006

In general, weapon systems require very high reliability. Recently Korean defense reliability technologies growth rapidly. However, there are some matters of reform in reliability management, reliability assurance, and defense acquisition environment, etc. In this paper, we propose the reliability development plan for Korean defense system as follows; 1) reliability improvement programs for each acquisition stages, 2) reliability improvement methods for logistics support, 3) reliability improvement programs for developers and manufacturers, 4) reform matters for the defense acquisition law, 6) establishment of defense reliability assessment center and defense reliability committee.

• Journal of Korean Institute of Industrial Engineers
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• v.39 no.6
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• pp.461-472
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• 2013

In this paper, we deal with a simulation-based reliability and maintainability design problem of a warship and want to determine the optimal values of MTBF and MTTR of all units and ALDT of the warship. The system availability and life cycle cost are used as optimization criteria and estimated by simulation. A hybrid genetic algorithm with a heuristic method is proposed to find near-optimal solutions and numerical examples are also studied to investigate the effect of model parameters to the optimal solutions and compare with a general genetic algorithm.

• Journal of Applied Reliability
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• v.7 no.3
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• pp.101-110
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• 2007

The works of defence reliability have begun since the ILS team was organized in ROKA on March 2003. After that DAPA was opened at January 1st 2006 and those of defence reliability were reinforced. But the present of defence reliability is not enough. Many development and changes are required in the following area. The first is Master-plan making of defence reliability, and the second is making of the process of reliability. And then we have to enhance reliability of weapon system in the operation and support phase. The last is that policy is firmly executed among the defence organizations.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.26 no.4
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• pp.110-115
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• 2018

This paper introduces Korea Airport Corporation's own research and development contents and plans for navigation aids check using drone which is actively research and developed mainly in advanced countries. The hardware, algorithm, operating program of the drone system, the drone flight trajectory setting, and real-time measurement results were analyzed and verified. By securing domestic technology for the latest technology utilizing drone, we plan to promote more thorough aviation safety and advanced technology in related field and commercialized it in domestic and overseas.