• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.05a
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• pp.105-109
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• 2003

A new scaling method for the prediction of gas turbine components characteristics using experimental data of gas turbine test unit has been proposed. In order to minimize the analyzed performance error in the this study, firstly component maps were constructed by real experimental performance data at some operating conditions and a polynomial obtained from scaling factors at given conditions, and then the simulated performance using the identified maps was compared with the performance result using the currently used traditional scaling method. In comparison, the performance analysis result by the currently used traditional scaling method was met well agreed with the real engine performance at most off-design points except for the design point. However the performance analysis result using the newly proposed scaling method had good agreement with the experimental results within maximum 5％ error.

• The Optical Journal
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• s.139
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• pp.44-49
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• 2012

일본이 참가를 표명하고 있는 차세대 초대형 광적외선망원경 TMT는 무엇인가. TMT는 국제협력으로 하나의 초대형망원경을 건설하는 프로젝터이고, 각국 각 파트너가 주요 구성품을 제조해서 하나의 큰 망원경시스템을 구축한다. 따라서 이들 구성품을 통합해서 종합성능을 달성하는 프로젝트관리가 매우 중요하게 된다. 기술적 요소뿐만 아니라 시스템설계와 구성품 간의 인터페이스 정의 관리에도 큰 도전이 필요한 프로젝트이다. 마찬가지로 국립천문대가 참가하고 있는 국제적인 거대천문시설인 ALMA 전파망원경도 3개의 주요 파트너가 구성품을 제조해 완성하고 있다. 본고는 자연과학연구기구 국립천문대 TMT프로젝터실 야마시타 타쿠야 연구원이 월간 광기술 컨텍트 2012년 2월에 기고한 내용으로서 그린광학의 유정훈 팀장이 번역에 도움을 주었다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.7
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• pp.36-43
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• 2002

A new scaling method for the prediction of gas turbine components characteristics using experimental data or partially given data from engine manufacturers has been proposed. In order to minimize the analyzed performance error in the this study, firstly component maps were constructed by identifying performance data given by engine manufacturers at some operating conditions, then the simulated performance using the identified maps was compared with the performance result using the currently used traditional scaling method. In comparison, the performance result by the currently used traditional scaling method was well agreed with the real engine performance at on-design point but it had maximum 12% error at off-design points within the flight envelope of a study turboprop engine. However because the analysed performance by the newly proposed scaling method had maximum 6% reasonable error even within all flight envelope.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.537-541
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• 2009

The gas turbine engine performance is greatly relied on its component performance characteristics. Generally, acquisition of component maps is not easy for engine purchasers because it is an expensive intellectual property of gas turbine engine supplier. In the previous work, the maps were inversely generated from engine performance deck data, but this method is limited to obtain the realistic maps due to calculated performance deck data. Therefore this work proposes newly to generate more realistic compressor map from experimental performance test data. And then a realistic compressor map can be generated form those processed data using the proposed extended scaling method at each rotational speed. Evaluation can be made through comparison between performance analysis results using the performance simulation program including the generated compressor map and on-condition monitoring performance data.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.3
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• pp.16-22
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• 2010

The gas turbine engine performance relies greatly on its component performance characteristics. Generally, engine manufacturers do not provide engine purchasers the component performance characteristics which can be obtained by lots of experimental tests at various operating conditions and big amount of expenses. In previous works the component maps have mostly been generated by scaling from a similar component map. However this scaling method has large error at off design points, specially in high altitude operation. Therefore this work proposes an inverse modeling method that can generate components maps of PT6A-67A turboprop engine using performance data provided by the engine manufacturer. In addition, evaluation can be made through comparison between performance analysis results using the performance simulation program including the generated compressor map and performance data.

• Fire Science and Engineering
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• v.20 no.3 s.63
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• pp.21-28
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• 2006

Since hot toxic gas included in the fire is the most principal reason of the death and has the fluid mechanical characteristics unlike air, smoke control method appropriate for the figure and structure of a fire room is needed and each unit of the smoke control system requests high performance according to this characteristics, for which performance test procedures and evaluation criteria must be established. Domestic criteria involved with the smoke control consist of the pre-investigation by documents and the part inspection, which has lots of problems because they are far from the performance based evaluation method compared with the references of developed countries. Consequently, domestic and international references were compared and analyzed, problems being emerged and standardization scheme of the test procedure was presented.

• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.1
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• pp.44-50
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• 2008

In this study a turboshaft engine for a helicopter propulsion system was modeled using SIMULINK and the components' maps were generated from the limited performance deck data provided by engine supplier using a hybrid method with the genetic algorithms and the system identification method. In order to verify the SIMULINK performance model and the component maps generated by the hybrid method, the steady-state performance analysis results were compared with the performance data provided by engine manufacturer. In this investigation, it was confirmed that the analysis results by the proposed model are closely met with those by engine manufacturer's data.

• Bulletin of the Korean Space Science Society
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• 2003.10a
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• pp.105-105
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• 2003

인공위성의 개발과정에서 비행모델을 만들기 전 EM (Engineering Model) 들로 구성하는 Electrical Test Bed (ETB) 를 개발하여 위성의 하니스를 포함함 각 서브시스템 전장품들의 성능을 점검하게 되고, ETB 시험기간 동안 발생된 문제점 들은 비행모델 설계와 제작에 반영하게 된다. 다목적실용위성 2호에 대한 ETB를 개발하여 각종 위성 전장품에 대한 성능과 부분품들간의 인터페이스 신호들의 점검을 성공적으로 완료하였으며, 시험기간 동안 발생된 각종 문제점들은 비행모델 설계와 제작에 이미 반영하였다. 본 논문에서는 다목적실용위성 2호 비행모델에 대한 시험을 위하여 각 서브시스템 즉, 원격측 정명령계, 전력계, 자세제어계의 전장품과 탑재소프트웨어 그리고 각종 시뮬레이터들의 구성과 전기/전자적인 기능시험을 위한 시험항목 및 방법에 대해 고찰하고자 한다.

• Fire Science and Engineering
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• v.27 no.1
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• pp.46-51
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• 2013

In this study a lab scale seismic test method which is able to evaluate seismic resistant performance of the fire protecting components in case of earthquake was developed. This seismic test consists of equivalent accelerating and temporary accelerating. The former is to search for resonance frequency and the latter is to simulate vibrating by earthquake with intensive magnitude. The frequency and displacement accelerated to the components was decided by maximum acceleration of gravity, and whether or not they could maintain function was tried to be confirmed. This test method is expected as an effective one for evaluating seismic resistant performance for the fire protecting components.

• Proceedings of the Korean Society of Computer Information Conference
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• 2019.01a
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• pp.419-422
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• 2019

해군은 계획된 함정 수리기간을 통해 성능 유지를 위한 장비 정비를 수행한다. 함정의 수리기간이 한정되어있고, 장비는 많은 정비 대상 구성품으로 이루어져 통상의 경우 성능이 저하된 구성품을 미리 선정하여 일부분에 대해서만 정비가 수행된다. 본 연구에서는 SNA 분석을 통해 함정 수리 시 정비 대상 구성품을 더욱 효과적으로 선정할 수 있도록, 집중적으로 정비가 수행된 개체를 확인하고 이를 예방정비를 위한 정비요소로 도출하고자 하였다. 이를 위해 특정 모델을 샘플로, 도입시부터 ${\bigcirc}{\bigcirc}{\bigcirc}{\bigcirc}$년까지의 정비데이터를 수집하여 분석을 진행하였다.