• 한국건축시공학회:학술대회논문집
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• 한국건축시공학회 2017년도 추계 학술논문 발표대회
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• pp.199-200
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• 2017

The Configuration Management(CM) of Nuclear Power Plant(NPP) is an activity that maintains consistency among the design requirement, facility configuration information and physical configuration. It is a systematic approach to performing various engineering tasks such as change management by identifying, documenting the characteristics of plant Structures, Systems and Component(SSC). The first activity that should be performed the configuration baseline setting at the start of project. The configuration baseline of the NPP construction phase is the status of the SSC of the plant at a specified process and time, and the actual configuration changes depending on the condition of plant. In this paper, I have studied the current status of configuration baseline used in the software industry and general plant industry, method of establishment for the configuration baseline which was first applied to the construction of NPP.

• International Journal of Aeronautical and Space Sciences
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• 제15권3호
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• pp.219-231
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• 2014

We develop a preliminary design optimization procedure in this paper regarding the wing planform in a solar-powered high-altitude long-endurance unmanned aerial vehicle. A high-aspect-ratio wing has been widely adopted in this type of a vehicle, due to both the high lift-to-drag ratio and lightweight design. In the preliminary design, its characteristics need to be addressed correctly, and analyzed in an appropriate manner. In this paper, we use the three-dimensional Euler equation to analyze the wing aerodynamics. We also use an advanced structural modeling approach based on a geometrically exact one-dimensional beam analysis. Regarding the structural integrity of the wing, we determine detailed configuration parameters, specifically the taper ratio and the span length. Next, we conduct a multi-objective optimization scheme based on the response surface method, using the present baseline configuration. We consider the structural integrity as one of the constraints. We reduce the wing weight by approximately 25.3 % from that in the baseline configuration, and also decrease the power required approximately 3.4 %. We confirm that the optimized wing has sufficient flutter margin and improved static longitudinal/directional stability characteristics, as compared to those of the baseline configuration.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1997년도 한국자동제어학술회의논문집; 한국전력공사 서울연수원; 17-18 Oct. 1997
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• pp.1338-1341
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• 1997

In this paper, we propose angular rate computation algorithm using GPS carrier phase. A direct angylar rate masurement has not previously been available form GRS, although its availability is highly desirable for use in state feedback control. So we propose angular rate computationalgorithm which derive angular rate from the velocity of differentiated carrier phase og GPS. The proposed algorithm contains attitude determination using double-differentiated carrier phase and 2 baseline configuration whcih provide more practical applications than 3 baseline.

• 제어로봇시스템학회논문지
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• 제12권3호
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• pp.300-306
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• 2006

In this paper an error analysis of 3-dimensional GNSS attitude determination system is given. The attitude error covariance matrix is derived and analyzed. It implies that attitude errors are affected by the baseline length and configuration, the satellites numbers and geometry, receiver measurement noises and the nominal attitude of the vehicle. By defining Euler Angle Dilution Of Precision (EADOP) which is analogous to GDOP, roll, pitch and yaw errors can be efficiently analyzed. However the expression of the attitude error is too complex to get some intuitions. Therefore with a commonly adopted assumption, new expressions for attitude error are derived. The formulas are easy to compute and represent the attitude error as a function of the nominal attitude of a vehicle, the baseline configuration and the receiver noise. Using the formula, the accuracy of the attitude can be analytically predicted without the computer simulations. Applications to some widely used configurations reveal the effectiveness of the proposed method.

• Wind and Structures
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• 제32권3호
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• pp.205-217
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• 2021

Cold regions with high air density and wind speed attract wind energy producers across the globe exhibiting its potential for wind exploitation. However, exposure of wind turbine blades to such cold conditions bring about devastating impacts like aerodynamic degradation, production loss and blade failures etc. A series of wind tunnel tests were performed to investigate the effect of icing on the aerodynamic properties of wind turbine blades. A baseline clean wing configuration along with four different ice accretion geometries were considered in this study. Aerodynamic force coefficients were obtained from the surface pressure measurements made over the test model using MPS4264 Simultaneous pressure scanner. 3D printed Ice templates featuring different ice geometries based on Icing Research Tunnel data is utilized. Aerodynamic characteristics of both the clean wing configuration and Ice accreted geometries were analysed over a wide range of angles of attack (α) ranging from 0° to 24° with an increment of 3° for three different Reynolds number in the order of 105. Results show a decrease in aerodynamic characteristics of the iced aerofoil when compared against the baseline clean wing configuration. The key flow field features such as point of separation, reattachment and formation of Laminar Separation Bubble (LSB) for different icing geometries and its influence on the aerodynamic characteristics are addressed. Additionally, attempts were made to understand the influence of Reynolds number on the iced-aerofoil aerodynamics.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2007년도 제28회 춘계학술대회논문집
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• pp.38-42
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• 2007

본 연구에서는, 다분야 통합 해석을 이용한 순항미사일 형상 최적설계를 수행하였다. FORTRAN을 이용하여 개발한 공력, 중량, 성능 및 임무 해석 모듈을 프레임워크를 통하여 통합하였으며 최적화를 위하여 전역최적화 도구인 다윈 알고리즘을 사용하였다. 최적설계 결과, 다른 설계 구속조건을 만족시키면서 17% 가량 전체 무게를 줄일 수 있었다.

• 한국통신학회논문지
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• 제12권4호
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• pp.357-364
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• 1987

본 논문에서는 다중프로세서 시스템을 구성하는 중요한 요소인 다단상호결합 네트웍의 성능을 고찰한다. Baseline 네트웍을 이용한 Star네트웍 시스템의 Hardware적인 구성을 고찰하며 Analytical Model로 Request가 받아들여질 확률과 Clustering 확률을 구한다. 그리고 Baseline네트웍 대신에 Delta네트웍을 이용하여 위에서 언급한 확률을 구한 다음 네트웍의 성능을 비교한다.

• 한국통신학회논문지
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• 제31권10A호
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• pp.988-995
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• 2006

본 논문에서는 방위각과 고각을 동시에 탐지하는 2차원 멀티베이스라인 센서 배열 설계에서 DOA(Direction Of Arrival) 정확도를 유지하면서 센서 안테나수를 최소화하기 위해 위상차 공간에서 유클리드 최소 거리함수를 이용한 논하모닉 배열 구조 설계 메소드를 제안한다. 제안된 메소드는 기존 메소드와 달리 최소 이격 거리비가 반파장 이상인 경우에도 적용 가능할뿐더러 임의 배열구조에서도 적용이 가능한 장점을 갖는다. 다중신호 입사조건에서 초분해능 알고리즘을 적용한 모의 실험을 통해 설계 접근성의 효율성을 제시하였다. 또한 제안된 메소드를 적용하여 2차원 비대칭 배열 안테나를 설계하였고, 제작된 배열 안테나를 이용한 실험 결과를 통해 그 성능을 확인하였다.

• 한국항공운항학회지
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• 제20권4호
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• pp.31-38
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• 2012

In this paper, requirements of GNSS receiver station installation are derived for optimizing the performance of network based GNSS precise positioning by concern of international organization(IGS, NGS) recommendation. Also a analysis method of network based GNSS precise positioning is suggested in order to evaluate the availability depending on various network configurations. To evaluate network candidates, a performance evaluation method is proposed for positioning of users according to a geometric configuration and the baseline distance. After the proposed method is used to Ochang region that is a the test area 6 network candidates are derived and the performance of positioning was analyzed. Finally, Ansung, Gongju, Eumsung, Boeun network configuration was selected as the best positioning performance. An optimal Receiving station network was selected using the proposed method.

• 한국군사과학기술학회지
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• 제8권3호
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• pp.33-41
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• 2005

This paper describes the conceptual design of medium size helicopter rotor system. Based on assumed design requirements, trade-off study for rotor configuration has been conducted in terms of rotor tip speed, disk loading, blade area, solidity, etc for estimated primary mission gross weight. For the main rotor, four-blade and five-blade rotors are studied with the conventional tail rotor. The performance analysis for baseline configuration is conducted using a helicopter performance analysis program. The analysis shows design results satisfy the design requirements.