• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.414-416
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• 2009

In order to build a transient simulation program for a high thrust liquid rocket engine(LRE), a static performance simulation program for components were made. The components were the thrust chamber (combustion chamber and supersonic nozzle), centrifugal pump (impeller and volute casing), impulse turbine, and flow control devices (control valve and orifice). Simplified mathematical models based on classical thermodynamic and inviscid theories were used to remove complexity and enhance the utility of the program. We examined the results of each program qualitatively for validate each component modeling.

• Proceedings of the Korean Nuclear Society Conference
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• 1997.10a
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• pp.317-322
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• 1997

앞으로 건설되는 원전의 계측제어계통은 디지털 기술로 설계될 전망이다. 그러나 디지털 기술을 원전 계측제어계통에 적용하는데 있어서 디지털 기술이 원전의 안전성이나 신뢰도에 영향을 미치지 않는다는 사실을 보증하여야 하며, 디지털계통의 기능과 성능에 대한 확인/검증은 원전에 설치되기 전에 수행되어야 한다. 계측제어 시험검증설비의 목적은 새롭게 개발되는 디지털 제어 및 보호 알고리즘, 경보축약 알고리즘 또는 운전지원계통등의 성능을 검증하기 위함이다. 시험검증설비의 소프트웨어는 웨스팅하우스형 993 MWe 가압경수로를 모델링한 수학적 모델링과 시험검증설비를 운용하기 위하여 필요한 종합운용프로그램으로 구성된다. 하드웨어는 공학용 워크스테이션, 시험용 패널, 개발되는 계통과의 인터페이스를 위한 VXI 인터페이스 모듈, 그리고 공유메모리의 값을 시험대상 시작품으로 전송하는 Ethernet 모듈 등으로 구성된다. 사용자 인터페이스로 할덴 원자로 프로젝트에서 개발된 Picasso 그래픽 도구를 이용한 화면과 60개의 주요변수의 값을 CRT에 표시하는 기능을 제공한다. 계측제어 시험검증설비를 응용한 계측제어계통 시작품은 정상운전 및 과도상태에서 적절한 시험결과를 제공하였다.

• 프린팅코리아
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• v.9 no.3
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• pp.62-62
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• 2010

마이크로콘트롤스(대표 조병우)에서 공급하고 있는 액화금속코팅 재킷인 J750BL시리즈는 뛰어난 성능과 다양한 기능으로 주목을 받고 있다. 3층으로 구성되어 있는 특수코팅층은 이른바 '연잎 효과(Lotus Effect)'를 구현하고 있다. 연잎 효과는 반발력을 최대화하는 기능을 발휘하는데 있어 중요한 역할을 감당하며 장기간 사용해도 성능 발휘에 지장이 없다. 인쇄작업의 효율성 제고와 친환경성을 감안하고 있다.

• Defense and Technology
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• no.9 s.283
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• pp.56-65
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• 2002

앞으로는 전투기와 마찬가지로 한 나라가 독자적으로 신형 전차를 개발할 수 있을 것이라고는 생각하지 않는다. 아마 신형 전차를 한 나라가 독자적으로 만든 예는 Leclerc가 마지막일 것이다. 그러나 베를린 장벽의 붕괴 이후 간격은 전차의 판매에 영향을 미치고 있으며 최근까지 야심에 찬 계획을 가졌던 많은 국가들이 계획을 수정하거나 성능개량으로 전환하고 있다. 현세대 전차 구성품의 방향은 모듈(modular)화로써 보다 높은 성능을 제공하면서 점유 공간은 줄이는 효과를 가져오고 있다.

• Journal of the Korean Society of Propulsion Engineers
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• v.17 no.1
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• pp.80-88
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• 2013

In currently developed engine condition monitoring systems, most field engine maintenance engineers have difficulties to use them in fields due to complexity, unpractical use, lack of understanding, etc. Therefore a practical usable engine condition monitoring system must be needed. This work proposes a practical performance condition monitoring of a small turbojet engine through comparing between the on-line performance monitoring data and the initial clean performance data calculated by the base engine performance model. Moreover the proposed monitoring system checks the gas path components' on-line health condition through comparing the component performance characteristics between the running engine represented as a deteriorated engine or a degraded engine and the base engine performance model represented as a clean engine. The proposed condition monitoring system is coded in a friendly GUI type program for easy practical application by a commercial tool, MATLAB/SIMULINK and LabVIEW.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.579-583
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• 2011

The component based propulsion modeling and simulation of an air-breathing engine such as ramjet and scramjet is studied. The simulation model has been realized considering the characteristics of the air-breathing engine which is composed of air intake, combustor and nozzle including engine controller and fuel supply system. To estimate the engine performance and to verify the engine controller, real time based Hardware in the Loop System simulating actual environment is constructed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.245-249
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• 2007

In this study a model-based diagnostic method using the Neural Network was proposed for PW206C turbo shaft engine and performance model was developed by SIMULINK. Fault and test database to build the NN was obtained at various off-design operating range such as flight altitude, flight Mach number and gas generator rotational speed variation. According to the fault detection analysis results, it was confirmed that the proposed fault detection method could find well the fault of compressor, compressor turbine and power turbine at on-design point as well as off-design point conditions.

• Journal of the Korean Society of Propulsion Engineers
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• v.11 no.3
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• pp.29-34
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• 2007

In this study a model-based diagnostic method using the Neural Network was proposed for PW206C turbo shaft engine and performance model was developed by SIMULINK. Fault and test database to build the NN was obtained at various off-design operating range such as flight altitude, flight Mach number and gas generator rotational speed variation. According to the fault detection analysis results, it was confirmed that the proposed fault detection method could find well the fault of compressor, compressor turbine and power turbine at on-design point as well as off-design point conditions.

• Journal of the Korean Society of Propulsion Engineers
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• v.4 no.3
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• pp.83-94
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• 2000

A systematic humidity correction technique that can be used for any type of engine control mode is developed to predict the variation of engine performance due to inlet humidity. Limitation of conventional method is rot identified and then, a new method is proposed to take into account the humidity effects on each engine component characteristics and to find the variation of equilibrium running point through a re-match process between the components with a given engine control variable depending on the humidity of inlet. Comparisons are made between two methods for a single spool gas turbine engine, and it was found that the conventional method leads to invalid correction when a physical variable such as rotational speed is controlled for engine operation in humid environment. It was also found that the accuracy of the conventional method depends on the engine control mode and the engine configuration whereas the proposed method can be used for any type of engine control mode and engine configuration.

• Journal of the Korean Society of Propulsion Engineers
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• v.13 no.5
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• pp.57-63
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• 2009

A modeling and simulation program for an environmental control system (ECS) of a pod installed under wings of an aircraft was developed in order to estimate the system‘s performance during a flight. First, through the system configuration analysis in the main operational condition of the aircraft system, an ECS configuration adopting an air cycle machine (ACM) was selected. Therefore the modeling program was developed to simulate the ECS with an ACM. Second, the sensitivity analyses on performance variation of main components were conducted to complete the conceptual design of the ECS. A design point for the system and its components was obtained through the analysis with the modeling and simulation program. The design point for the system and components was obtained through the analysis with the modeling and simulation program. Third, in order to study the feasibility of the ECS configuration, off-design performances of the ECS on various flight conditions, such as take off, maneuver, cruise and landing etc were estimated. Dynamic characteristics were analyzed by transient performance evaluations.