• International Journal of Aeronautical and Space Sciences
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• 제17권2호
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• pp.260-267
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• 2016

The design process of blended inlet body (BIB) for the preliminary design of a near-space high supersonic unmanned aerial vehicle (HSUAV) is presented. The mass flow rate and cowl area of inlet at a design point are obtained according to the cruise condition of the HSUAV. A mixed-compression axisymmetric supersonic inlet section with a fixed geometry reasonably matching the high supersonic cruise state is created by using the inviscid theory of aerodynamics. The inlet section is optimized and used as a baseline section for the BIB design. Three BIB concepts for the HSUAV are proposed, and their internal aerodynamic characteristics of inlet are evaluated using Euler computational fluid dynamics (Euler CFD) solver. The preferred concept is identified, in which the straight leading edge of the baseline HSUAV configuration is modified into the convex leading edge to accommodate the inlet and meet the requirements of the cowl area to capture the sufficient air flow. The total recovery of inlet for the preferred BIB concept and the aerodynamic characteristics of the modified HSUAV configuration are verified using Navier-Stokes computational fluid dynamics (NS CFD) solver. The validation indicates that the preferred BIB concept can meet both the requirements of the inlet and aerodynamic performance of the HSUAV.

• International Journal of Precision Engineering and Manufacturing
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• 제2권2호
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• pp.57-64
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• 2001

In recent years, the concern of designing multi-stage gear drives ha increased with more application of them in high-speed and high-load. Until now, however, the researches on the design of gear drives have been focused on single gear pairs. Thus the design practice for multi-stage gear drives has been depended on experiences and expertise of designers and carried out commonly by trial and error. We propose an automation algorithm for the design of two-and three-strage cylindrical gear drives. The two types of dimensional design processes have been proposed to determine gear dimensions in a formal way. The first design process(Process I) uses to total volume of gears to determine gear ration , and uses K factor , unit load and aspect ration to determine gear dimensions, The second one(Process II) makes use of Niemann's formula and center distance to calculate gear ratio and gear dimensions. Process I and Process II employ material date from AGMA and ISO standards, respectively. The configuration design determines the positions of gears with minimizing the volume of gearbox by using a simulated annealing algorithm. The availability of the design algorithm is validated by the design examples to two-and three=stage gear drives.

• 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.

• 한국항공운항학회지
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• 제19권3호
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• pp.1-9
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• 2011

In this paper, a conceptual design process for Very Light Jet aircraft has been proposed incorporating aircraft safety certification. During the proposed design process, satisfaction of the airworthiness certification for an intermediate resulting aircraft configuration is evaluated and then redesigns are carried out if necessary and until the designed aircraft configuration satisfies the airworthiness requirements. Certification database has been developed using FAR 23, AC 23, KAS 23, and CS 23 as the airworthiness certification. Based on the developed certification database Design Certifcation Related Table has been produced to use the airworthiness requirements as design constraints in the propsed design process. Using Quality Function Deployment the design variables for a redesign are carefully selected and a design optimization is performed. To demonstrate the feasibility and effectiveness of rapid aircraft conceptual design using the proposed approach, a Very Light Jet design optimization including a redesign of wing flap has been performed and the design results have been presented.

• 한국산학기술학회논문지
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• 제14권10호
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• pp.4733-4738
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• 2013

본 연구에서는 구속조건을 가진 기계계의 동적 평형위치를 다물체 동역학 해석방법을 이용하여 계산하였다. 다물체계에서 얻어지는 시간 구속조건을 가진 구속조건식과 동역학식으로부터 독립좌표계로 이루어진 동적평형식을 유도하였다. 동적 평형식은 구속조건식과 함께 비선형 대수방정식의 형태로서 Newton-Raphson 방법을 이용하여 수치해를 구하였다. 제안된 동적 평형 계산 방법을 조속기에 적용하여 동적 평형위치를 구하였다. 해석결과는 상용 프로그램의 동역학해석을 통한 평형위치의 결과와 비교하여 타당성을 검증하였다. 조속기의 회전 각속도에 대한 평형위치를 계산하고 설계 파라미터에 대한 평형위치의 영향을 분석하였다.

• 한국실내디자인학회논문집
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• 제22권4호
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• pp.149-157
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• 2013

As a period of pluralism, today's museum architecture has been expanding social and cultural meaning. So, Various expressions are appearing in museum architecture. Accordingly, the museum must be very reproducible and comply with aesthetic requirements. At the same time, museum construction in urban design and features must satisfy professional requirements. SANAA is one of contemporary architects has been decisively deleted existing fixed and functional layout type of program through 'The new hierarchy'. Thus, the experience of the space will vary. Now, museum space is urgently needed than ever before crustal movements. Thus, this study aims to contribute an alternative to the museum space configuration according to the trend of the times through 'The new hierarchy' of SANAA. This paper is limited to the cases of the SANAA's museum architecture. We analyze the characteristics of representation on 'The new hierarchy' appear in the museum space configuration and then, examine the value of the spatial. SANAA's 'New Hierarchy' is going to set the cognitive boundary by expression targeting plane and the surface. It is completely different than the previous boundaries. Characteristics of the expression represents non-centrality, decentrally, non-oriented, uncertainty, non-territorialization, uniformity. It is steady that identity of Space, Human, Environment in Museum. They have a relationship each concept of Independence, autonomy, equality.

• 산업공학
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• 제11권3호
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• pp.23-40
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• 1998

In this paper, a method to determine the optimal configuration of operating policies in an integrated-automated manufacturing system using the Taguchi method and computer simulation experiments is presented. An integrated-automated manufacturing system called direct-input-output manufacturing system(DIOMS) is described. We only consider the operational aspect of the DIOMS. Four operating policies including input sequencing control, dispatching rule for the storage/retrieval(S/R) machine, machine center-based part type selection rule, and storage assignment policy are treated as design factors. The number of machine centers, the number of part types, demand rate, processing time and the rate of each part type, vertical and horizontal speed of the S/R machine, and the size of a local buffer in the machine centers are considered as noise factors in generating various manufacturing system environment. For the performance characteristics, mean flow time and throughput are adopted. A robust design experiment with inner and outer orthogonal arrays are conducted by computer simulation, and an optimal configuration of operating policies is presented which consists of a combination of the level of each design factor. The validity of the optimal configurations is investigated by comparing their signal-to-noise ratios with those obtained with full factorial designs.

• 한국광학회지
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• 제28권6호
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• pp.263-272
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• 2017

넓은 시야를 가지는 광학계에서는 전반부는 음의 굴절능, 후반부는 양의 굴절능을 가지는 inverted telephoto 구조가 일반적으로 사용되고 있고, 2반사광학계에서는 inverse Cassegrain system이 inverted telephoto 구조에 해당한다. 하지만 통상적인 회전대칭 구성의 inverse Cassegrain system에서는 시야가 가려지고 광선의 차폐가 심한 문제점이 있다. 이 연구에서는 이점을 고려하여 inverse Cassegrain system의 제2면에 조리개를 두어 시야를 넓히고, 광선의 차폐가 없는 비축시야만을 사용하는 광시야 비축 2반사광학계를 설계하였다.

• 항공우주기술
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• 제12권1호
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• pp.73-80
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• 2013

한국형발사체 시스템설계 형상에 대해 전산유동해석(CFD) 기법을 이용하여 공력 특성 및 하중을 예측하였다. 이전 형상에 비하여 엔진 카울이 없어짐에 따라 축력과 수직력이 감소하였으며, 압력 중심이 전방으로 크게 이동하였다. 그리고 하중 해석을 위해 비행 중 및 발사대 대기 중의 공력 하중을 산출하였다. 공력 계수 및 공력 하중 해석 결과는 다음 설계 단계의 임무 설계 및 구조 해석 분야에 활용된다.

• 한국철도학회논문집
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• 제14권2호
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• pp.116-120
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• 2011

현재 초고속 자기부상열차시스템에 적용하고 있는 위치검지기술은 불연속적으로 열차위치를 파악하는 절대위치검지기술과 연속적으로 열차의 위치를 파악하는 상대위치검지기술로 구분된다. 본 논문에서는 대표적인 초고속자기부상열차인 독일 Transrapid에 적용된 절대위치검지장치의 구조와 수치모델을 분석하고, Transrapid에 적용된 절대위치검지장치와 유사한 구조를 가지는 절대위치검지장치의 인식구조별 모델을 설계하고 시뮬레이션을 통해 설계한 모델의 적합성을 검증하고 최적의 절대위치검지장치 구조를 제안한다.