• 한국화재소방학회논문지
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• 제23권2호
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• pp.55-61
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• 2009

본 연구에서는 서지나 순간 과전압 등에 의한 과도현상으로부터 보호될 수 있는 높은 신뢰성의 화재수신기가 될 수 있도록 과도현상 보호시스템의 개발에 대한 연구를 수행하였고, 보호시스템의 성능을 시험으로 입증함으로써 과도현상 보호시스템을 개발할 수 있는 기틀을 마련하였다. 과도현상 보호시스템의 개발을 위한 프로세스 정립과 이론을 바탕으로 과도현상으로부터 보호될 수 있는 1단계 및 2단계 보호시스템을 개발하였고, 소방법 및 관련규정에서 제시하는 제반 성능조건으로 시험하고 만족스런 결과를 얻음으로써, 과도현상 보호시스템을 개발할 수 있는 엔지니어링 데이터 구축과 원천기술을 확립하였다.

• 한국항공우주학회지
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• 제30권5호
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• pp.62-70
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• 2002

항공기용 가스터빈엔진에 대한 경제적인 시험 기법 개발을 위해 천이상태 성능 시험 결과로부터 정상상태 성능을 예측할 수 있는 방안을 모색하였다. 천이상태 성능과 정상상태 성능이 상이한 원인을 동역학적 천이 효과, 열적 천이 효과, 공기역학적 천이 효과로 구분하고, 각각을 모델링해서 엔진의 천이상태 성능을 통해 정상상태 성능을 계산하는 보정 인자를 정량화 하였다. 엔진 성능시험은 한국항공우주연구원이 보유한 고공환경시험설비에서 이루어졌다. 먼저 천이상태 성능시험 시 나타나는 엔진 입 출구의 온도 변화가 엔진 성능에 미치는 영향을 보정했으며, 그 후 도입된 보정 인자를 사용해 정상상태 성능을 예측하였다. 이렇게 예측된 결과와 실제 정상상태 성능시험 결과를 비교한 결과, 연료 소모량의 차이 3.68% 이내로 정상상태 성능을 예측할 수 있어, 본 연구에서 사용한 보정 기법이 상당한 정도의 정확도를 보장하고 있는 것으로 나타났다.

• 항공우주기술
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• 제2권1호
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• pp.1-10
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• 2003

항공기용 가스터빈엔진에 대한 경제적인 시험 기법 개발을 위해 천이상태 성능 시험 결과로부터 정상상태 성능을 예측할 수 있는 방안을 모색했다. 천이상태 성능과 정상상태 성능이 서로 달라지는 현상의 원인을 동역학적 천이 효과, 열적 천이 효과, 공기역학적 천이 효과로 구분하고, 각각을 모델링해서 엔진의 천이상태 성능을 통해 정상상태 성능을 계산하는 보정 인자를 정량화했다. 먼저 천이상태 성능시험 시 나타나는 엔진 입ㆍ출구의 온도 변화가 엔진 성능에 미치는 영향을 보정했고, 그 후 도입된 보정 인자를 사용해 정상상태 성능을 예측했다. 이렇게 예측된 결과와 실제 정상상태 성능시험 결과를 비교한 결과, 연료 소모량의 차이 3.68% 이내로 정상상태 성능을 예측할 수 있었다.

• 연구논문집
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• 통권30호
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• pp.5-13
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• 2000

The computation scheme of simulating gas turbine transient behavior was developed. The basic principles of this scheme and main input data required are described. Calculation results are presented in terms of whole operating regime of the cycle. The influence of main initial parameters such as starting engine power, moment of inertia of the rotor, fuel supplying schedule etc. on performance characteristics of has turbine during transient operation is studied In addition, bleeding air influence on transient behavior was also considered For validation of the developed code, comparison of present calculation with that of measurement data of the experimental data for the range of operating period studied.

• 전기학회논문지
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• 제59권10호
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• pp.1727-1732
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• 2010

The Current transformer is classified measuring CT and protective CT for their purpose. The measuring CT is required to retain a specified accuracy over the normal range of load currents, but the protective CT must be capable of providing an adequate output over wide range of fault condition. Therefore, the protective CT must determine the transient performance during fault condition. This paper measured peak instantaneous error of the TPY class CT to determine the transient performance directly and indirectly and studied the test results.

• 설비공학논문집
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• 제11권1호
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• pp.81-90
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• 1999

The performance evaluation technique of a heat exchanger is described by using a transient response analysis for the determination of an average heat transfer coefficient. The model using a finite difference method can accommodate arbitrary inlet fluid temperature as well as longitudinal conduction. Temperature histories are obtained from the experiments at the inlet and outlet of test core. Heat transfer coefficient and friction factor of the plate array are obtained in short times using the data reduction program of transient response analysis in the single-blow method. The results agree very well with theoretical results. It is shown that the rms deviations are very small and the performance evaluation technique gives rapid and accurate results.

• 대한전기학회:학술대회논문집
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• 대한전기학회 2004년도 하계학술대회 논문집 B
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• pp.839-841
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• 2004

IEC 60044-6 (Requirements for protective current transformers for transient performance) was established to Korea Standard (KS C IEC 60044-6 ; Instrument transformers Part 6 ; Requirements for protective current transformers for transient performance) in December 11, 2003. In this paper, requirements, test items and test methods protective current transformers for transient performance.

• 조명전기설비학회논문지
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• 제25권6호
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• pp.28-34
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• 2011

This paper describes the development of the transient analysis model of 345[kV] 100[MVA] STATCOM and the result of the performance analysis. The Korea power utility company, KEPCO began a commercial operation of a 100[MVA] STATCOM(Static synchronous COMpensator) at 345[kV] Migeum substation in Seoul. In order to operate a new control device like STATCOM to the power system, suitable transient model is needed. Therfore, Korea Electric Power Coporation(KEPCO) developed a transient analysis models using EMTDC/PSCAD. The development of this transient analysis model is based on the actual STATCOM S/W algorithm and H/W specification that was provided by its manufacture. Through this model, the transient/dynamic performance of STATCOM at Migeum substation can be analyzed.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
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• pp.513-520
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• 2004

A steady-state/transient performance simulation model was newly developed for the propulsion system of the CRW (Canard Rotor Wing) type UAV (Unmanned Aerial Vehicle) during flight mode transition. The CRW type UAV has a new concept RPV (Remotely Piloted Vehicle) which can fly at two flight modes such as the take-off/landing and low speed forward flight mode using the rotary wing driven by engine bypass exhaust gas and the high speed forward flight mode using the stopped wing and main engine thrust. The propulsion system of the CRW type UAV consists of the main engine system and the duct system. The flight vehicle may generally select a proper type and specific engine with acceptable thrust level to meet the flight mission in the propulsion system design phase. In this study, a turbojet engine with one spool was selected by decision of the vehicle system designer, and the duct system is composed of main duct, rotor duct, master valve, rotor tip-jet nozzles, and variable area main nozzle. In order to establish the safe flight mode transition region of the propulsion system, steady-state and transient performance simulation should be needed. Using this simulation model, the optimal fuel flow schedules were obtained to keep the proper surge margin and the turbine inlet temperature limitation through steady-state and transient performance estimation. Furthermore, these analysis results will be used to the control optimization of the propulsion system, later. In the transient performance model, ICV (Inter-Component Volume) model was used. The performance analysis using the developed models was performed at various flight conditions and fuel flow schedules, and these results could set the safe flight mode transition region to satisfy the turbine inlet temperature overshoot limitation as well as the compressor surge margin. Because the engine performance simulation results without the duct system were well agreed with the engine manufacturer's data and the analysis results using a commercial program, it was confirmed that the validity of the proposed performance model was verified. However, the propulsion system performance model including the duct system will be compared with experimental measuring data, later.

• 제어로봇시스템학회논문지
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• 제19권4호
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• pp.285-289
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• 2013

In switching from the track-seeking or track-jumping control mode to track-following control mode in hard disk drives or optical disk drives, initial values of the feedback controller are tuned to improve the transient response. In general, all the initial values of the controller have been compensated for this purpose. In this paper, by partially compensating initial values of digital controllers, we achieve a good performance of the transient response. In the proposed method for IVC (Intial Value Compensation), LMIs (Linear Matrix Inequalities) are used, which includes conditions for improving the performance of the transient response such as reducing a tracking error and control efforts. We obtain optimal initial values of the controller by solving an optimization problem with constraints represented by only one LMI. Although initial values of the controller are partially compensated, we can show that not only a sufficient performance of the transient response is obtained but also control efforts are diminished. The feasibility of the method is verified by simulation studies.