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요구사항 명세서에 첨부하는 요구사항 추적표 작성 양식 제안
김대승,Kim, DaeSeung 한국시스템엔지니어링학회 2016 시스템엔지니어링학술지 Vol.12 No.1
Most of systems engineers make a traceability matrix and attach it to their technical documents as a result of systems engineering activities. I have been working in the field of systems engineering for many years and have been watching traceability matrices created by systems engineers or developers from various companies. I have been thinking that some of them are not suitable in terms of purposes of traceability matrix. In this paper, I would like to suggest a right template for the traceability matrix in conformance to traceability purposes. The key is that traceability matrix should be created from higher level of requirements to current level of requirements.
김수용(SooYong Kim),김대승(DaeSeung Kim),S. Yepifanov 한국유체기계학회 2006 유체기계 연구개발 발표회 논문집 Vol.- No.-
The purpose of the present study is investigate the part load performance of an auxiliary power unit(APU)) gas turbine engine AI-9. The AI-9V auxiliary power unit works as an airborne compressor air source serving for starting of the helicopter/air craft main engine, as a stand-by DC power source for the helicopter/ airplane mains. Part load performance with constant bleed air rate is studied as well as influence of ambient air temperature. To secure the safe control of the engine operation, constant speed of rotation is preferred during part-load operation. considered important Transient performance with bleed air is also investigated.
김경식(Kyungsik Kim),임설(Seol Lim),김대승(Daeseung Kim),조승환(Seunghwan Cho) 한국추진공학회 2011 한국추진공학회 학술대회논문집 Vol.2011 No.11
금속 소재의 열구조 안정성을 파악하기 위해 고체연료 추진기관의 노즐에 대해 열구조 해석을 수행하였다. 금속 소재 노즐은 짧은 연소 시간이지만 고온, 고압의 연소가스에 직접 노출되어 열하중이 상당히 클 것으로 판단된다. 해석 결과를 통해 열하중의 영향을 예측하고 향 후 추력기 설계 자료로 이용하고자 한다. The thermo-structural analysis of the solid-fuel propulsion Nozzle is studied to estimate the thermo-structural safety of the metal nozzle. The thermal load is determined to be significantly large, Because the metal nozzle in a short combustion time is directly exposed to high pressure and temperature of combustion gas. Through a analysis result, the influence of a thermal load is estimated and henceforward a design data of thruster is used.
김수용(SooYong Kim),김대승(DaeSeung Kim),최범석(BumSeok Choi) 대한기계학회 2006 대한기계학회 춘추학술대회 Vol.2006 No.6
In most of the cases, the size of gas turbine unit depends on flow rate through it. It is generally known that, with a cooling air of 1%, gas turbine cycle efficiency drops about 1.2% and therefore determination of cooling mass flow rate and its properties is very important to both economy and performance of the gas turbine unit. The maximum efficiency of gas turbine unit occurs at turbine inlet gas temperature around T<SUB>c</SUB>=1600℃ and further increasing the temperature only leads to lowering the thermal efficiency due to significant increase of loss caused by cooling. Therefore, effective description of temperature distribution around the blade and disk will help in selecting the optimum amount of cooling flow rate and is important for practical engine design. Particulars related to heat exchange between cooling air and materials surface is considered in this report.