• Journal of the Korean Society of Propulsion Engineers
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• 제2권2호
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• pp.64-73
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• 1998

In twin spool aero-engine, there may be a S shaped annular duct between high pressure and low pressure spools. The flow passing this S shaped duct experiences the flow acceleration and deceleration due to the convex and concave surface of the duct as well as the increase of blockage according to the boundary layer growth along the surfaces. So, the high pressure compressor which is located behind the S shaped duct is influenced by the non-uniform flow field generated by the geometry of inlet duct. To study the influence of the S shaped duct on the centrifugal stage, performance tests were implemented for the compressor with straight cylindrical inlet duct and with S shaped inlet duct, respectively. The test results showed that the performance, such as pressure ratio and efficiency, of the compressor with S shaped duct was worse than that of the compressor with cylindrical duct. And the compressor with S shaped duct had reduced maximum flow rate around design speed. To investigate the cause of performance degradation, flow anlaysis was performed for the impeller in front of which is located S shaped annular duct. The result of CFD showed the strong acceleration of the flow in the axial direction around the inducer tip region which caused the increase of relative mach number and the decrease of incidence angle of the flow.

• Proceedings of the Korean Information Science Society Conference
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• 한국정보과학회 2006년도 한국컴퓨터종합학술대회 논문집 Vol.33 No.1 (C)
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• pp.196-198
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• 2006

소프트웨어 프러덕트 라인 개발 방법론이란 개발 초기에 시스템의 공통적인 부분과 가변적인 부분을 명확히하여 소프트웨어 자산을 구축한 후 다양한 요구 사항에 따라 가변적인 부분을 커스터마이징하여 목표 시스템을 생성하는 소프트웨어 개발 패러다임이다. 일반적인 소프트웨어 프러덕트 라인에 대한 연구는 활발히 진행되고 있지만, 병렬성을 지원하는 소프트웨어 프러덕트 라인에 대한 연구는 상대적으로 미약하다. 본 논문에서는 병렬 소프트웨어 프러덕트 라인 구축에 있어서 특성 모델을 통해 기능적 가변성을 지원하고 상태 다이어그램을 통해 동시성을 지원하는 컴포넌트의 코드를 자동 생성하는 도구를 제안한다. 본 연구 결과는 병렬성이 중요한 실시간 임베디드 소프트웨어 프러덕트 라인 구축에 활용될 수 있다.

• Proceedings of the Korean Information Science Society Conference
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• 한국정보과학회 2005년도 가을 학술발표논문집 Vol.32 No.2 (2)
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• pp.427-429
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• 2005

최근 컴포넌트 기반의 소프트웨어 프로덕트 라인에 대한 연구와 소프트웨어 프로덕트 라인에 자동 생성 프로그래밍 기법을 적용하기 위한 연구가 활발히 진행 중이다. 본 논문에서는 재사용 가능한 컴포넌트 자산을 구축하고, 재구성 자동화를 통해 컴포넌트 코드를 생성하는 시스템을 제안한다. 본 도구는 컴포넌트 기반 프로덕트 라인 개발 방법론과 자동 생성 프로그래밍 기법, XML/XSLT 기술을 이용하여 구축되었다. Component Asset 개발자 레벨에서 사용하는 컴포넌트 자산 구축기와 재사용자 레벨에서 사용하는 컴포넌트 코드 생성기로 구성되어 있으며, 컴포넌트 기반의 소프트웨어 프로덕트 라인 개발에 효과적으로 활용될 수 있다.

• Journal of the Korea Academia-Industrial cooperation Society
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• 제13권9호
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• pp.4234-4243
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• 2012

USN(Ubiquitous Sensor Network) application S/W has a complex characteristic that it controls various kind of sensor nodes organically based on the core modules of various target operating systems. Currently, various researches for efficient S/W development are being performed in USN application field. In order to increase S/W productivity, the method such as product line development approach to specify core common functions of applications according to the domain and develop applications with the core common functions and variant functions selected according to the workflow of applications is efficient. To apply this approach to the USN domain, characteristics of USN application S/W and product line development should be specified with one consistent view. However, it is difficult to efficiently specify the characteristics using general UML notations. In order to solve the problem, this paper proposes a method to effectively specify the characteristics of USN applications and product line development using UML profile which is the extension mechanism of UML. The proposed UML profile for produce line based USN application development enables developers to effectively develop product line based USN applications using existing UML and UML support tools without new design methods or tools which are specified for USN or product line development.

• Journal of Power System Engineering
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• 제15권3호
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• pp.31-37
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• 2011

직조 금속 스크린 리브(rib) 이 바닥에 설치된 사각 덕트에서 열전달과 유체유동의 압력강하를 측정하기 위해 실험적 연구를 수행하였다. 시험부의 치수는 200 mm(W) ${\times}$ 40 mm(H) ${\times}$ 712 mm(L)이고 수력직경은 66.6 mm이다. 입구영역에는 1.72m 길이의 가열되지 않은 동일한 치수의 채널을 설치하였다. 메쉬가 다른 4가지의 직조금속 스크린 리브에 대해 측정하였다. 그리고 비교를 위해 일체형 리브에 대해서도 측정하였다. 국부 열전달 계수의 측정에는 스테인레스 강제 포일(foil) 히터와 T형 열전대률 이용하였다. 레이놀즈 수는 23,000에서 58,000의 범위이다. 덕트의 수력직경($D_h$)에 대한 직조 금속 리브의 높이(e)의 비($e/D_h$)는 0.075 이고 리브 간격(p)과 높이의 비(p/e)는 10이다. 실험 결과 메쉬가 없는 일체형 리입에서 가장 누셀트 수와 마찰계수가 컷다.

• Journal of Animal Environmental Science
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• 제16권3호
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• pp.193-204
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• 2010

The goal of this study was to develop a high-rise hog building(HRHB) for growing-fattening stages. HRHB was two story building and was suitable for specific environment in Korea. Manure was treated in a first floor and pigs were raised on the slatted second floor. Three ventilation systems - 1) duct inlet to wall exhaust system(V1), 2) eave inlet to wall exhaust system(V2), and 3) ceiling inlet to wall exhaust system(V3) - were used. This experiment was conducted during winter and from summer to fall. Air temperature, air speed, ammonia, hydrogen sulfide in HRHB, and swine growth rate were measured. During winter, air temperature in V1 system tended to be slightly high without any effect of outside air temperature. Maximum temperature from summer to fall was between 33.4 and $33.8^{\circ}C$ and there was no significant difference among systems. Continuously measured daily temperature was lower in V2 system than other systems and the fluctuation of air temperature was high. Air speed in V1 and V2 systems were similar (0.02~0.21 m/s), and was 0.04~0.15 m/s in V3 during winter. From summer to fall, air speed in V1, V2, and V3 systems were 0.10~0.41 m/s, 0.10~0.83 m/s, and 0.11~0.26 m/s, respectively. V2 system showed bigger fluctuation of air speed than other systems. During winter, the highest concentrations of ammonia in V1, V2, and V3 systems were 7.0, 3.5, and 8.7 ppm, respectively. Hydrogen sulfide was not detected. The highest concentrations of ammonia from summer to winter in V1, V2, and V3 systems were 6.1, 2.8, and 5.6 ppm, respectively. Swine growth showed no statistical significance among systems. However, daily weight gain was approximately 4% higher in V1 and V3 than in V2. Feed intake/daily weight gain was approximately 4% higher in V1 than other systems. From summer to fall, daily weight gain in V1 and V3 tended to approximately 3% higher than other systems, and feed intake/daily weight gain was approximately 2% higher in V1 than other systems. Hence, V2 system for the ventilation system of HRHB should not be utilized.

• Journal of the Korea Society for Simulation
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• 제19권4호
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• pp.179-188
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• 2010

The concern of Software Product Line(SPL) engineering is spreading widely because the program or product developers are able to satisfy the customer's demands quickly and give a way to handle maintenance efficiently. SPL is a reuse paradigm that reuse common parts and adopts variable parts optionally to form a differentiated product by analyzing domains. Purposes of this paper are to design an architecture which has a dynamic reconfiguration function and to develop basic components which are the basic unit of reconfiguration to raise the reuse level of the guided weapon system using the SPL. Initially we design an architecture and define basic components for developing a dynamic reconfigurable components based on SPL. Then we develop the composer for physical components and behavior components referenced by behavior models of OneSAF.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• 제47권1호
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• pp.17-25
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• 2019

An intake of Aircraft becomes S-shaped geometry due to spatial limitation or procuring survivability. But curvature of the S-shaped geometry makes secondary flow or flow separation which is the cause of non-uniform pressure distribution. In this study, boundary layer suction is applied to RAE M 2129 S-Duct by attaching sub duct. Design variable is suction location and angle. A mass flow rate drawn out by suction at the sub duct outlet is constant over every model. A grid dependency test was conducted to verify validity of computation. The comparison among the CFD (Computation Fluid Dynamics), ARA experimental result, and ARA computation result of non-dimensional pressure distribution on the Port side and Starboard Side confirmed the validity of CFD. In this study, Distortion Coefficient was used for evaluating aerodynamic performance of S-Duct. The analysis, which was about flow separation, vortex, mass flow rate distribution, and pressure distribution were also investigated. Maximum 26.14% reduction in Distortion Coefficient was verified.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 한국추진공학회 2011년도 제36회 춘계학술대회논문집
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• pp.144-152
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• 2011

In order to investigate the operation performance behaviors of the UAV's propulsion system to be operated long time in high altitude, the engine performance tests, which are simulated in the altitude engine test facility should be needed. If the test is performed in a existing altitude engine test facility, additional test apparatuses are required. Among them a proper design of the inlet and exhaust ducts that may directly affect the engine performance is very important. If the design is not adequate, the engine performance loss due to the flow behavior change and the pressure loss may be not similar to the real engine performance. In this work, firstly the engine inlet and exhaust ducts to be mounted to the existing altitude facility are modelled in 3D and its flow behaviors and pressure losses are analyzed using a commercial CFD tool, ANSYS's CFX, and the engine performance with the duct losses is calculated using the performance analysis program developed by C. Kong et al. Finally, the optimized inlet and exhaust ducts' configurations are proposed through the repeated analyses of various duct configurations.

• The Journal of the Acoustical Society of Korea
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• 제31권1호
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• pp.11-18
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• 2012

In this paper, the occurrence of a stopband phenomenon when an acoustic wave propagates through periodically corrugated ducts is discussed using theoretical and BEM analyses. A 2-D duct with sinusoidally corrugated upper and lower walls is considered. When the magnitude of the sinusoidal corrugation is sufficiently small compared to the duct's height, the wave equation is solved with the multiple scaling perturbation method. Then stopbands for Bragg and non-Bragg resonances are computed from the condition where frequency becomes a complex number. A 2-D BEM analysis is performed to compute insertion loss of the duct, and stopbands are confirmed as predicted by analytical analysis.