• 한국항공운항학회지
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• 제14권4호
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• pp.17-23
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• 2006

This paper describes the preliminary design procedure for the hybrid propulsion system. For a given mission defined by velocity increment, the design of a polyethylene/LOX hybrid rocket was implemented. In addition, Seven-cluster multi-port fuel-grain was considered. After determining the system size including the combustion chamber, the performance parameters such as specific impulse, thrust, characteristic velocity, and thrust coefficient can be predicted by using empirical regression rate correlation, though most of preliminary design code assume constant regression rate. The results of the performance prediction indicated that besides the widely used HTPB/LOX, polyethylene/LOX hybrid motor can be a viable alternative to the more widely used SRMs.

• 한국유체기계학회 논문집
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• 제14권1호
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• pp.18-23
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• 2011

The hydraulic part in reactor coolant pump consists of suction nozzle, impeller, diffuser, and discharge nozzle. Among them, impeller is required to be designed to satisfy performance requirements such as head, NPSHR, and head curve slope at design point. Present study is intended to suggest the preliminary design method sizing the impeller size to satisfy the design requirement particularly including head curve slope at design point. On a basis of preliminary design result, hydraulic components have been designed in detail by CFD and then manufactured in a reduced scale. Experiment in parallel with computational analysis has been executed in order to confirm the hydraulic performance. Comparison results show good agreement with design result, confirming the validity of design method suggested in this study.

• 한국전산구조공학회:학술대회논문집
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• 한국전산구조공학회 1999년도 봄 학술발표회 논문집
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• pp.61-68
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• 1999

This paper is the study of methodology for development of preliminary structural design modules for an intergated system for reinforced concrete structures. To develop the modules. it is used that the iteratived and incremental development process of object-orientied methodology and affects. The aspect is a tool to capture characteristics of the objects. The aspects consists of .user, structure, and system. By using aspects, we can find that objects and relationships between the objects consisting of the modules in the phases of process. In this paper, UML(Unified Modeling Language) is used to the notation. It serves as the language for communicating decisions that are not obvious and provides semantics to capture all important stategic and tactical decisions. Therefore such a series of mothods is valuable to development of preliminary structural design modules. Then preliminary structural design modules were programed by using Visusl C++, a windows environmental development tool.

• Journal of Astronomy and Space Sciences
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• 제27권4호
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• pp.393-400
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• 2010

Korea Astronomy and Space Science Institute has been developing one mobile satellite laser ranging system named as accurate ranging system for geodetic observation-mobile (ARGO-M). Preliminary design of ARGO-M operation system (AOS) which is one of the ARGO-M subsystems was completed in 2009. Preliminary design results are applied to the following development phase by performing detailed design with analysis of pre-defined requirements and analysis of the derived specifications. This paper addresses the preliminary design of the whole AOS. The design results in operation and control part which is a key part in the operation system are described in detail. Analysis results of the interface between operation-supporting hardware and the control computer are summarized, which is necessary in defining the requirements for the operation-supporting hardware. Results of this study are expected to be used in the critical design phase to finalize the design process.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 추계학술대회논문집B
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• pp.670-675
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• 2001

This paper describes aerodynamic preliminary design performance prediction and flow analysis for turbine of the marine middle engine turbocharger. The performance characteristics of turbocharger turbine are investigated at various operating conditions using mass flow rate and computational flow analysis for rotor and nozzle at design point are performed. Preliminary design results are performed by applying mean line and radial equilibrium theory. Performance prediction and flow analysis results show good agreement with experiments. From 3 dimensional flow analysis result, efficiency is 0.6% greater than design point. Therefore, this design approach is useful for preliminary design, and helps to increase the design capability for optimized rotor blade.

• 한국신재생에너지학회:학술대회논문집
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• 한국신재생에너지학회 2008년도 추계학술대회 논문집
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• pp.295-298
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• 2008

The major function of the nacelle cover is protecting the inside equipments. Therefore, it is required not only sufficient strength and stability but also light weight. In this paper, design loads are calculated according to the GL Wind guideline Ed. 2003. To ensure the structural safety, a composite structure is selected. The structural design is processed by two steps which are preliminary design and detail design. In the preliminary design step, a structural analysis is performed with initial thickness, 5mm. As reviewing above analysis results, weak regions of the nacelle cover reinforced using the spar cap structure which is same as the blade structure. In the analysis model, the support structure is connected with the nacelle cover and analyzed its structural safety at the same time.

• International Journal of Aeronautical and Space Sciences
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• 제10권2호
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• pp.134-139
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• 2009

Various modules are generally combined with one another in order to perform rotorcraft preliminary design and its optimization. At the stage of the preliminary design, analysis fidelity is less important than the rapid assessment of a design is. Most of the previous researchers attempted to implement sophisticated applications in order to increase the fidelity of analysis, but the present paper focuses on a rapid assessment while keeping the similar level of fidelity. Each small-sized module will be controlled by an externally-operated global optimization module. Results from each module are automatically handled from one discipline to another which reduces the amount of computational effort and time greatly when compared with manual execution. Automatically handled process decreases computational cycle and time by factor of approximately two. Previous researchers and the rotorcraft industries developed their own integrated analysis for rotorcraft design task, such as HESCOMP, VASCOMP, and RWSIZE. When a specific mission profile is given to these programs, those will estimate the aircraft size, performance, rotor performance, component weight, and other aspects. Such results can become good sources for the supplemental analysis in terms of stability, handling qualities, and cost. If the results do not satisfy the stability criteria or other constraints, additional sizing processes may be used to re-evaluate rotorcraft size based on the result from stability analysis. Trade-off study can be conducted by connecting disciplines, and it is an important advantage in a preliminary design study. In this paper among the existing rotorcraft design programs, an adequate program is selected for a baseline of the design framework, and modularization strategy will be applied and further improvements for each module be pursued.

• 한국신재생에너지학회:학술대회논문집
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• 한국신재생에너지학회 2006년도 춘계학술대회
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• pp.241-244
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• 2006

Recently wind turbines become large, constructed as farms and going out to offshore. Different design approach from onshore is needed for offshore wind turbine. At this paper concept and preliminary design of an offshore wind turbine of 3MW rated power are performed. The concept design started from modelling of the generator and gearbox. With these modelling the optimum specifications was acquired. Integrated type of drive train is designed with all parts are mounted on the tower top as the offshore maintenance strategy. At the preliminary stage control system, power production algorithm and safety system are designed. Load calculation is also performed. The 3MW offshore wind turbine concept/preliminary design and the process of design are obtained as results.

• 한국항공우주학회지
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• 제38권4호
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• pp.309-314
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• 2010

기본설계 단계에서 회전익 항공기의 가격을 보다 정확하게 예측하기 위해서 Harris & Scully에 의해 제시된 가격 예측 식을 최신의 추세식으로 수정하였다. 이를 위해 1997년 이후의 총 74개에 대한 회전익기 가격 및 제원 정보를 이용하여 가격 예측 식을 업데이트하였다. 업데이트 된 가격 예측식을 Tishchenko의 기본설계 기법과 통합하여 기본설계 단계에서 가격을 고려하도록 구성하였다. 본 기본설계 및 가격예측 프로그램을 현재 운용되고 있는 미국 Sikorsky사의 S-76C+를 비롯한 여러 기종의 헬리콥터에 적용하여 가격과 제원 결과를 도출하고 검증하여 본 연구의 유효성을 확인하였다.

• 한국해양공학회지
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• 제14권2호
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• pp.117-120
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• 2000

In the Step of preliminary ship design a designer should decide a economic ship. The economic ship has the least building cost to a annual freight amount satisfying a given design condition That is RFR is minimum among alternatives.