• 한국원자력학회:학술대회논문집
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• 한국원자력학회 2004년도 요약집 춘계학술발표대회
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• pp.65.2-65.2
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• 2004

• 한국원자력학회:학술대회논문집
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• 한국원자력학회 2003년도 추계학술발표대회 요약집
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• pp.67.2-67.2
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• 2003

• 한국공간구조학회논문집
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• 제5권3호
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• pp.75-82
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• 2005

초고층건물 구조설계를 효율적으로 수행하고 설계정보를 합리적으로 처리하기 위해서 통합설계에 대한 필요성이 증가하고 있으며, 또한 기존의 설계사례를 D/B화하여 초기 설계단계에 적용하는 연구가 필요하다. 구조설계 초기 단계에서는 주재료와 구조형태를 선정하고 대략적인 부재치수를 선정하게 되는데, 이것은 건물높이, 사용하중, 기본풍속, 설계가속도, 최대수평변위, 기둥간격, 층고 등과 같은 정보와 유사 사례에 대한 정보를 토대로 결정하게 된다. 그리고 초기 개념설계 단계에서 주어진 문제를 해결하는 방법은 과거 유사한 문제의 해결지식이 유용하게 적용된다. 본 논문에서는 초고층건물의 통합설계시스템에서의 개념구조설계법을 소개하고, 초기 설계단계에서의 적합성을 초고층건물 적용 예제를 이용하여 검토하고자 한다.

• 한국농공학회지
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• 제43권4호
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• pp.79-88
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• 2001

Agricultural facilities can be designed by conceptual preliminary primary and detailed design stages. because each stage has a different objective, it must be applied to dissimilar design and analysis level. Engineers have to judge from evaluation that is estimated agricultural resources in the conceptual design stage. Methods of computer aided design are achieved to individual functions however it is inefficient to perform entire processes of design and hard to systematically accumulate results o design. Study on the integrated structural design system has been continued. but those system have adopted “closed architecture”which is known to inflexible method for developing applications. In this study the design platform is an environment that can support to integrated design system independently and an design platform is proposed by analyzing design processes using object oriented method. The concepts of software platform have resulted from several practical ideas, OOA/OOP and related some points. This paper aims at developing the software platform of a software environment to support the design phases of the agricultural facilities.

• 한국멀티미디어학회논문지
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• 제21권3호
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• pp.423-431
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• 2018

In this paper, we try to verify a normative module based house design procedure consisted of several sequential steps. The first step is to suggest formalization of designing so that we could clarify each phase and operation we are adopting in our design process. The second step is the clearing up the conceptual schema of traditional skills that we adopt and utilize from traditional Hanok framing techniques. The third step is to formulate adequate modular kits for the assembly of house design solutions for the schematic, conceptual and preliminary phases of designing. The fourth step is to implementing our ideas and methods to a proper computational platform such as Unity3D. The final step is to verify our symbolic descriptions of design formalization with the output of our experiments so that we have better understanding of design reasoning characteristics such as in house design.

• 시스템엔지니어링학술지
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• 제9권2호
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• pp.83-90
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• 2013

Integrated aircraft synthesis process for rapid analysis and design is described in this paper. Data flow between different analysis fields is described in details. All the data are divided into several groups according to importance and source of the data. Analysis of design requirements and certification regulations is carried out to determine baseline configuration of an aircraft. Overall design process can be divided into initial sizing, conceptual and preliminary design phases. Basic data for conceptual design are obtained from initial sizing, CAD and geometry analysis. Basic data are required input for weight, aerodynamics and propulsion analyses. Results of this analysis are used for stability and control, performance, mission, and load analysis. Feasibility of design is verified based on analysis results of each discipline. Design optimization that involves integrated process for aircraft analysis is performed to determine optimum configuration of an aircraft on a conceptual design stage. The process presented in this paper was verified to be used for light aircraft design.

• 대한조선학회논문집
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• 제35권4호
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• pp.109-117
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• 1998

선박의 개념설계 단계는 이용 가능한 정보가 매우 제한되어 있기 때문에 새로운 설계를 위하여 대부분의 경우 기존 선박의 설계 사례를 이용하게 된다. 본 논문에서는 이러한 과정을 시스템화하여 사례기반 선박 개념설계 시스템을 개발하였다. 개발된 시스템은 사례 인덱싱을 통한 설계후보의 생성뿐만 아니라 nearest neighbor algorithm을 이용하여 사례베이스에서 추출된 설계 사례들의 우선 순위를 결정하여 주고 이를 바탕으로 변용(adaptation) 과정을 거쳐 설계선에 대한 해를 제시해 준다. 이러한 사례기반 추론 기법을 선박 개념설계 단계에 적용하여 그 유용성을 검증하였다.

• Nuclear Engineering and Technology
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• 제45권6호
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• pp.721-730
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• 2013

Within the framework of the ASTRID project, core design studies are being conducted by the CEA with support from AREVA and EDF. The pre-conceptual design studies are being conducted in accordance with the GEN IV reactor objectives, particularly in terms of improving safety. This involves limiting the consequences of 1) a hypothetical control rod withdrawal accident (by minimizing the core reactivity loss during the irradiation cycle), and 2) an hypothetical loss-of-flow accident (by reducing the sodium void worth). Two types of cores are being studied for the ASTRID project. The first is based on a 'large pin/small spacing wire' concept derived from the SFR V2b, while the other is based on an innovative CFV design. A distinctive feature of the CFV core is its negative sodium void worth. In 2011, the evaluation of a preliminary version (v1) of this CFV core for ASTRID underlined its potential capacity to improve the prevention of severe accidents. An improved version of the ASTRID CFV core (v2) was proposed in 2012 to comply with all the control rod withdrawal criteria, while increasing safety margins for all unprotected-loss-of-flow (ULOF) transients and improving the general design. This paper describes the CFV v2 design options and reports on the progress of the studies at the end of pre-conceptual design phase 1 concerning: - Core performance, - Intrinsic behavior during unprotected transients, - Simulation of severe accident scenarios, - Qualification requirements. The paper also specifies the open options for the materials, sub-assemblies, absorbers, and core monitoring that will continue to be studied during the conceptual design phase.

• Nuclear Engineering and Technology
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• 제35권4호
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• pp.356-368
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• 2003

Material properties such as coolant specific heat, film heat transfer coefficient, cladding thermal conductivity, surface diffusion coefficient of the multi-bubble are improved in MACSIS-Mod1. The axial power and flux profile module was also incorporated with irradiation history. The performance and feasibility of the updated driver fuel pin have been analyzed for nominal parameters based on the conceptual design for the KALIMER breakeven core by MACSIS-MOD1 code. The fuel slug centerline temperature takes the maximum at 700mm from the bottom of the slug in spite of the nearly symmetric axial power distribution. The cladding mid-wall and coolant temperatures take the maximum at the top of the pin. Temperature of the fuel slug surface over the entire irradiation life is much lower than the fuel-clad eutectic reaction temperature. The fission gas release of the driver fuel pin at the end of life is predicted to be $68.61\%$ and plenum pressure is too low to cause cladding yielding. The probability that the fuel pin would fail is estimated to be much less than that allowed in the design criteria. The maximum radial deformation of the fuel pin is $1.93\%$, satisfying the preliminary design criterion ($3\%$) for fuel pin deformation. Therefore the conceptual design parameters of the driver fuel pin for the KALIMER breakeven core are expected to satisfy the preliminary criteria on temperature, fluence limit, deformation limit etc.

• Journal of Astronomy and Space Sciences
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• 제38권2호
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• pp.105-117
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• 2021

In this study, a preliminary trajectory design is conducted for a conceptual spacecraft mission to a near-Earth asteroid (NEA) (99942) Apophis, which is expected to pass by Earth merely 32,000 km from the Earth's surface in 2029. This close approach event will provide us with a unique opportunity to study changes induced in asteroids during close approaches to massive bodies, as well as the general properties of NEAs. The conceptual mission is set to arrive at and rendezvous with Apophis in 2028 for an advanced study of the asteroid, and some near-optimal (in terms of fuel consumption) trajectories under this mission architecture are to be investigated using a global optimization algorithm called monotonic basin hopping. It is shown that trajectories with a single swing-by from Venus or Earth, or even simpler ones without gravity assist, are the most feasible. In addition, launch opportunities in 2029 yield another possible strategy of leaving Earth around the 2029 close approach event and simply following the asteroid thereafter, which may be an alternative fuel-efficient option that can be adopted if advanced studies of Apophis are not required.