• Proceedings of the KSR Conference
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• 2011.10a
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• pp.2973-2978
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• 2011

In this paper, a system is developed to support multi-attribute decision making for designing light-weight of rolling stock. Conceptual design of light-weight of rolling stock does not only mean reducing weight. It should be considered about some attributes like safety and environment, technology, etc. So technical attributes and needs of customers, manufacturers and management companies, passengers, should be reflected and qualitative evaluation methods are required. AHP(Analytical Hierarchy Process) and QFD(Quality Function Deployment) are used to decide weighted values of technical attributes and needs from customers. Finally, Alternatives for light-weight of rolling stock that are composed of alternatives of equipment are evaluated by TOPSIS(Technique for Order Preference by Similarity to Ideal Solution). A series of this process are made as a S/W. It could suggest a near-optimal alternative for light-weight of rolling stock.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 2008.06a
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• pp.497-498
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• 2008

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2011.10a
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• pp.494-497
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• 2011

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.6
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• pp.130-141
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• 2002

• Proceedings of the Korean Nuclear Society Conference
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• 1999.10a
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• pp.105.2-105
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• 1999

• Proceedings of the Korean Operations and Management Science Society Conference
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• 2006.05a
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• pp.1832-1839
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• 2006

제품의 개념설계 단계는 제품의 주요특성과 라이프 사이클 전반에서 발생하는 Life Cycle Cost(LCC)의 대부분을 결정하는 중요한 단계이다. 이에 따라 개념설계 단계에서의 Life Cycle Cost Analysis(LCCA)의 필요성이 강조되고 있다. 그러나 LCCA는 제품의 경제성과 사용성, 친환경성 사이에서의 합리적인 의사결정을 지원하기에 한계가 있다. 본 논문은 개념설계 단계에서의 새로운 의사결정지원도구로서 기업 관점의 제품 라이프사이클 기업 가치(LCCV)분석 프레임워크를 제안하고, 그 핵심모듈인 기업 비용 예측모델 (LCCCEM)을 소개한다. 이 프레임워크를 통해 기업이 제품의 경제성과 시장성, 친환경성 사이에서 보다 전략적이고 합리적인 의사결정을 수행하도록 지원할 수 있을 것으로 기대한다.

• Annual Conference on Human and Language Technology
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• 1993.10a
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• pp.521-526
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• 1993

다언어간 번역을 지향하는 기계번역시스템의 개발을 위해서는, 의미 이해기반의 해석기술과 언어에 독립적인 생성기술의 설계가 기본이므로 원시언어와 목표언어가 어느 한쪽의 언어지식에 의존하지 않고 언어형식화가 가능한 중간언어 구조를 설정하는 것이 중요하다. 따라서, 한국어를 중심으로 하는 다언어 번역의 설계에서는 비교적 문구조의 정형화가 이루어진 영어와는 달리 어순 배열의 자유도가 높고 조사의 격표시로 문장구조가 결정되는 한국어의 특성을 고려한 해석 및 생성 메카니즘이 필요하다. 본 논문에서는 문장에 내포된 심층의미의 중간 표현으로써, 단어의 의미를 개념화시킨 개념소(Conceptual Primitive)간의 의미적 결합관계를 나타내는 개념 그래프(Conceptual Graph)를 채택하고 설계한 다언어 번역지향의 중간언어기반 번역시스템에 대하여 기술한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.5
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• pp.467-476
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• 2010

For the very light jet aircraft design, the design baseline configuration has been selected using the logical decision making process, and the design optimization problem is formulated by considering the airworthiness regulations as design constraints. Airworthiness regulations are the minimum requirements for the safe aircraft flight and must be considered from the conceptual design stage. After carefully selecting the airworthiness constraints and the user specified requirements, a series of design making models including the affinity diagram, nested column diagram, quality function deployment (QFD), Pugh concept selection matrix, are used to find and evaluate alternative configuration baselines. From the feasible design space searching process, the best altenative design, which satisfies the airworthiness constraints while excluding the user subjective decisions as much as possible, has been successfully derived.

• Journal of the Korean Society of Propulsion Engineers
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• v.7 no.4
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• pp.19-26
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• 2003

In this paper, the result of the conceptual study of a tipjet driven propulsion system is presented. The concept of a tipjet driven propulsion system is to employ tipjet as power source to drive a rotor Because the vehicle is supposed to takeoff and land vertically, a rotor system, which has tipjet nozzles, is adopted to fly like a helicopter. Exhaust gas, which is generated by an engine, Passes through an internal duct system and divided into four blade ducts. The design code is consists of two parts, engine model and internal duct model. Inside a rotating duct, compressible flow is affected by two additional force terms, centrifugal force and coriolis force and they govern the performance in rotary mode, The intention of this paper is to address the issues associated with sizing and optimizing configurations of a tipjet driven propulsion system especially in rotary wing mode.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.35-38
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• 2007

Aiming at time-dependent performance prediction of Liquid Rocket Engine(LRE) system, Modular Program for Conceptual Design of LRE is reviewed, and a modeling and dynamic analysis of rocket engine system with reference to Rocket Engine Dynamic Simulator(REDS) is outlined. Component modeling is based on classical thermodynamic and inviscid theories, and were formulated mathematically in terms of essential parameters. Essential design parameters are addressed. The rocket engine is modeled as a system of pipes with various hydraulic elements, and then the operate characteristic of that elements are simulated by solving conservation equation sequentially.