• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.5
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• pp.431-438
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• 2012

Non-linear turbojet engine controller with high operational performance has been designed for the high maneuverability UAV. The turbojet engine dynamic performance code has been developed to reflect the non-linear characteristics on controller design, by which the necessity of non-linear controller design was justified by investigating the limitation of linear model derived from the dynamic performance. The PI-like fuzzy controller was designed and enhanced by combining with conventional derivative control. This designed fuzzy controller proves its effectiveness by showing superior control performances over the conventional PID controller along with guaranteeing the safe operation within compressor surge, flame out and turbine temperature limits etc.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.11 no.1
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• pp.75-82
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• 2007

In advanced countries, a gas turbine engine is developed to use in aircraft, vessels, and target weapons. Our nation also passed the level of producing engine components and now, we are developing small-sized gas turbine engine. The most important point of the gas turbine engine, the engine control technique, is evaded by the advanced nations. This document contains the research about the development of the gas turbine engine simulator. The simulator presented in this document has a mathematical engine model based on a capacity data of the gas turbine engine to advance the engine simulator. Through this process, it eases the development of the gas turbine engine control algorithm and helps to check the engine controller function. In this simulator, the engine sensor signal conversion board is designed, so the engine model shows like a real sensor signal during the simulation. Also, this paper contrasts the actual engine test with the simulation results to verify the performance.

• ICROS
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• v.2 no.2
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• pp.28-34
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• 1996

본 고에서는 엔진 제어 시스템의 이해를 돕기 위해 EMS의 구성 부품에 대해 설명하고, ULEV 규제를 만족시키기 위한 배기가스 제어기술에 대해 살펴보았다.

• Journal of the Korean Society of Propulsion Engineers
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• v.26 no.2
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• pp.72-78
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• 2022

A vacuum brazed cooling passage for an aircraft engine controller was designed. In order to predict the total pressure loss, which is the main design factor of the cooling passage, theoretical and numerical methods for the major loss and the minor loss considering the overall shape of the cooling passage are presented. This design and evaluation method can predict the pressure loss of the complex cooling passage shape for various flow conditions at the initial design step.

• Proceedings of the KAIS Fall Conference
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• 2010.11b
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• pp.839-841
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• 2010

기존의 범용 가솔린 소형엔진의 경우 대부분이 캬브레이터 연료 공급 방식으로 연비 및 배기가스성분이 매우 열악한 실정이다. 본 연구에서는 이러한 단점을 극복하고 배기규제에 대응하기위하여 전자제어식 연료분사방식으로 엔진을 변경하고, 관련핵심 부품의 개발을 수행하였다. 전자제어식 소형엔진에 적합한 인젝터, 연료펌프를 선정하였으며 연료레일은 새로이 설계하여 장착하였다. 최적의 작동조건을 선정하기위하여 엔진의 성능개발을 수행하였다. 개발된 소형엔진은 기존의 캬브레이터 방식의 엔진 대비 우수한 연비개선 효과와 배기가스 저감 효과가 있었다.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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• 2008.10a
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• pp.183-188
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• 2008

Engine control/performance model for helicopter simulator is one of the most important models which affect flight performance and handling quality. It is typical to develop the model based on the raw data and models from the engine designers/manufacturers. The approaches in this study were to develop the basic model based on the available resources and to tune and verify it based on the ground/flight test results. The maintenance manuals of TB3-117 which is installed in KA-32T were reviewed and the components to be simulated for the engine control model were categorized and modeled. Piece-wise linear modeling method was used for the engine performance model. The engine performance data in the engine maintenance manuals were incorporated into the engine steady state performance tables, which were incorporated with the transfer functions for the dynamic performance. Engine control/performance model was compared and tuned with the ground/flight test results. It was verified that the fidelity of the model was within the tolerances in FAA AC120-63.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.12 no.12
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• pp.2239-2246
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• 2008

Engine control/performance model for helicopter simulator if one of the most important models which affect flight performance and handling quality. It is typical to develop the model based on the raw data and models from the engine designers/manufacturers. The approaches in this study were to develop the basic model bated on the available resources and to tune and verify it based on the ground/flight test results. The maintenance manuals of TB3-117 which is installed in KA-327 were reviewed and the components to be simulated for the engine control model were categorized and modeled. Piece-wise linear modeling method was used for the engine performance model. The engine performance data in the engine maintenance manuals were incorporated into the engine steady state performance tablet, which were incorporated with the transfer functions for the dynamic performance. Engine control/performance model was compared and tuned with the round/flight test results. It was verified that the fidelity of the model was within the tolerances in FAA AC120-63.

• 제어로봇시스템학회:학술대회논문집
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• 1991.10a
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• pp.951-956
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• 1991

굴삭기 엔진 펌프시스템을 실험결과에 근거해서 모델링하여 수치적으로 시뮬레이션을 행하였다. 엔진.펌프시스템은 그 구성이 복잡할 뿐만 아니라 시스템자체의 비선형성,작업에 따라 시스템에 가해지는 불확실한 외란, 파라미터의 변동으로 인하여 정확한 모델링을 행하기는 다소 어려움이 있었다. 비례제어만을 사용시는 정상상태오차의 발생,초기의 회전수저하등으로 인하여 적합하지 않았다. 이를 개선하기 위하여 PID제어를 사용하였을 경우 정상상태오차는 제거할 수 있으나 정착시간이 길어지는 것을 볼 수 있었다. 슬라이딩모우드에 의한 제어법을 적용하였을 경우 정상상태오차,정착시간,최대회전수저하량을 모두 만족하였으나 과도상태에서 오실레이션이 발생하는 현상을 볼 수 있었다.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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• 2012.05a
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• pp.391-394
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• 2012

Recently, for appling to industrial engines to CRDI diesel engine to meet enhanced emission regulatory standards in native and foreign, ECU that be controlled only automaker develop engine control algorithm that adjust injection timing and injection as user's need and use testing, verification for engine performance and emissions reduction. For development only CRDI diesel engine emulator, using CKP and CMP sensor performance property of CRDI engine control ECU input element, in this paper, there determine the diesel knocking and propose design methodology of engine balance correction algorithm design of the correction algorithm. And there propose efficient Improvement for fuel efficiency increasing and reduction of emissions.

• Proceedings of the Korea Information Processing Society Conference
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• 2003.05b
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• pp.975-978
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• 2003

엔진을 도입하여 개발할 경우 단지 하부 구조를 구현하지 않았을 뿐, 엔진 내용을 이해할 정도의 수준이 되어야 한다는 것이다. 그러므로 게임 업계에서는 양질의 게임을 개발하기 위해서 여전히 고급 프로그래머를 필요로 하고 있으며, 이러한 부분은 여전히 개발비 상승에 영향을 미치고 있다. 그러므로 프로그램을 이해하는 기획자 수준에서도 게임을 개발할 수 있는 좀 더 상위 개념의 개발 방법의 필요성이 대두되고 있다. 본 논문에서는 이러한 문제를 해결하기 위해 스크립트를 이용하여 게임게임 전체 관리 부분, 모델의 AI부분 카메라 조작 부분으로 게임을 구성할 수 있도록 하였다. 그리고 스크립트 언어는 2 계층의 구조를 갖고 있으며, 하부 계층은 직접적으로 엔진을 제어하게 되어있다. 그러나 스크립트의 목표는 직접적인 엔진 제어를 줄이는 추상화작업을 목표로 하기 때문에 이를 추상화한 상부계층의 스처립트 언어를 설계하여 하부계층의 엔진제어 모듈로 변환하도록 하였다. 따라서 본 논문에서는 게임엔진을 직접적으로 모델링 하지 않고 개발하기 위한 추상화된 상위 단계의 스크립트 언어를 이용하여 기획단계예서 게임을 구성해 볼 수 있으며, 직접적으로 하부구조의 엔진 구현 및 엔진의 내용을 잘 이해할 정도의 수준이 아니더라도 스크립트언어를 이용하여 게임을 개발할 수 있다.