• 대한산업공학회지
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• 제19권2호
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• pp.83-93
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• 1993

Conventional computer programs developed and used by practicing engineers can be considered to contain expert knowledge and design experience. If these conventional programs are converted into expert systems, the difficult and time consuming process of knowledge acquisition can be simplified. Also the constructed knowledge-base can have higher confidence level than that constructed by the usual knowledge acquisition method of interviews. An existing computer program which is being used by ship structural designers has been reformulated as a design expert system by applying an expert system development shell-Nexpert. Utilizing the callable interface provided by the development shell, external design tools have also been integrated. The interfaced external functions are a graphical user interface (GUI) for the design process control, and graphics functions for the visualization of design results. It is observed that the developed system for design support is useful in two aspects. The trace-back function shows what portion of design rules are applied in arriving at certain design decisions. Also the knowledge-base can be conveniently updated as design rules of the classification societies are updated.

• 품질경영학회지
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• 제43권3호
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• pp.453-466
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• 2015

Purpose: The purpose of this study is to design a systematic method to estimate optimal operation conditions of design variables for an electronic device alignment system. Method: The 2-level factorial design and the central composite design are used in order to plan experiments. Based on the experiment results, a regression model is established to find optimal conditions for the design variables. Results: 3 of 5 design variables are selected as major factors that affect the alignment system significantly. The optimized condition for each variable is estimated by using a sequential experiment plan and a quadratic regression model. Conclusion: The method designed in this study provides an efficient and systematic plan to select the optimized operation condition for the design variables. The method is expected to improve inspection accuracy of the system and reduce the development cost and period.

• 동력기계공학회지
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• 제13권1호
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• pp.19-25
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• 2009

This paper is a study on the link composition design of a double link type level luffing jib crane using path generation synthesis passing through three precision points according to parameters, the length of backstay, the ratio of fly jib length between two moving hinges to the total length of fly jib, the location of a intermediate passing point etc. when the maximum and minimum working radius of the crane are given. The performance of the crane depends on the deviation of the luffing trajectory at fly jib tip. The luffing trajectories according to the above parameters are analyzed and shown in graphs by the developed computer program. In a real-life design, some trials are needed to arrive at a proper link composition design. Therefore, it is expected that the present computer program can rapidly and exactly deal with a link composition design proper to the design criteria of the crane.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2000년도 유체기계 연구개발 발표회 논문집
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• pp.145-152
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• 2000

A turbopump system composed of two pumps and one turbine is considered. The turbine composed of a nozzle and a rotor is used to drive the pumps while gas passes through the nozzle, potential energy is converted to kinematic energy, which forces the rotor blades to spin. In this study, an aerodynamic design of turbine system is investigated using compressible fluid dynamic theories with some pre-determined design requirements (i.e., pressure ratio, rotational speed, required power etc.) obtained from liquid rocket engine (L.R.E.) system design. For simplicity of turbine system, impulse-type rotor blades for open type L.R.E. have been chosen. Usually, the open-type turbine system requires low mass flow rate compared to close-type system. In this study, a partial admission nozzle Is adopted to maximize the efficiency of the open-type turbine system. A design methodology of turbine system has been introduced. Especially, partial admission nozzle has been designed by means of simple empirical correlations between efficiency and configuration of the nozzle. Finally, a turbine system design for a 10 ton thrust level of L.R.E is presented.

• International Journal of Aeronautical and Space Sciences
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• 제18권4호
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• pp.675-687
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• 2017

In the aerospace industry, we have produced various models according to operational conditions and the environment after development of the base model is completed. Therefore, when design change is necessary, there are modification and updating costs of the circuit whenever environment variables change. For these reasons, recently, in various fields, system designs that can flexibly respond to changing environmental conditions using field programmable gate arrays (FPGAs) are attracting attention, and the rapidly changing aerospace industry also uses FPGAs to organize the system environment. In this paper, we design the controller area network (CAN) intellectual property (IP) protocol used instead of the avionics protocol that includes ARINC-429 and MIL-STD-1553, which are not suitable for small unmanned aerial vehicle (UAV) systems at the register transistor logic (RTL) level, which does not depend on the FPGA vender, and we verify the performance. Consequentially, a Spartan 6 FPGA model-based system on chip (SoC) including an embedded system is constructed by using the designed CAN communications IP and Xilinx Microblaze, and the configured SoC only recorded an average 32% logic element usage rate in the Spartan 6 FPGA model.

• 융합신호처리학회논문지
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• 제10권2호
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• pp.141-145
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• 2009

본 논문에서는 입력 동작에 대하여 상위수준 합성을 수행한 후, 합성결과를 SystemC 코드로 전환하는 C-to-SystemC 합성기를 설계 및 구현하였다. 구현된 합성기의 처리과정은 C 소스코드로 기술된 입력 동작을 list 스케줄링 알고리즘을 이용하여 스케줄링한 후, 스케줄링 결과에 left-edge 알고리즘을 이용하여 레지스터 할당을 수행한다. 레지스터 할당 정보를 이용하여 합성기는 채널 및 포트와 같은 SystemC 특성들로 표현된 SystemC 모듈의 코드를 최종적으로 생성한다. C-to-SystemC 합성기의 동작은 EWF(elliptic wave filter)의 합성결과인 SystemC 모듈의 코드를 시뮬레이션하여 검증한다. C-to-SystemC 합성기는 SystemC 설계방법론의 모델링단계부터 합성단계에 이르는 툴 체인의 한 부분으로 사용될 수 있으며, 생성된 SystemC 모듈은 C 모듈에 비해 재사용이 용이하고 다른 SystemC 모듈과 SystemC 채널을 통하여 별도의 추가처리 없이 통신할 수 있다.

• International Journal of CAD/CAM
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• 제5권1호
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• pp.99-109
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• 2005

This paper introduces an approach to an ontology-based multi-level knowledge framework for a knowledge management system for discrete-product development. Participants in a product life cycle want to share comprehensive product knowledge without any ambiguity and heterogeneity. However, previous knowledge management approaches are limited in providing those aspects: therefore, we suggest an ontology-based multi-level knowledge framework (OBMKF). The bottom level, the axiom, specifies the semantics of concepts and relations of knowledge so ambiguity can be alleviated. The middle level is a product development knowledge map; it defines the concepts and the relations of the product domain knowledge and guides the engineer to process their engineering decisions. The middle level is then classified further into more detailed levels, such as generic product level, specific product level, product version level, and manufactured item level, according to the various viewpoints. The top level is specialized knowledge for a specific domain that gives the solution of a specific task or problem. It is classified into three knowledge types: expert knowledge, engineering function knowledge, and data-analysis-based knowledge. This proposed framework is based on ontology to accommodate a comprehensive range of knowledge and is represented with first-order logic to maintain a uniform representation.

• 한국정보과학회논문지:시스템및이론
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• 제29권1호
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• pp.42-56
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• 2002

WHDL이나 Verilog와 같은 기존의 하드웨어 기술 언어(Hardware Description Language)를 이용하여 비동기 마이크로세서를 모델링하고 시뮬레이션을 수행할수 있으나 핸드셰이크 프로토콜 (handshake protocol) 에 의해 동작하는 비동기 마이크로프로세서의 기술이 지나치게 복잡해진다. 결과적으 로 성능 평가 시간이 너무 길어져 상위 수준(system level)에서의 효과적인 설계 공간 탐색에 많은 어려움을 겪는다. 따라서 상위 수준에서 비동기적 특성인 핸드 셰이크 프로토콜을 쉽게 모델링하고 빠른시간 내에 효과적으로 시뮬레이션할수 있는 방법론과 도구가 필요하다. 이런 목적 하에 프로세서 모델링과 시 뮬레이션을 통하여 성능 평가를 수행할수 있는 자동화 도구 SLEDS(System Level Event Driven Simulator)를 개발하였다. 본 도구의 궁극적 목표는 프로세서를 구성하는 모듈들의 지연을 조절하여 (delay balancing)전체적으로 프로세서가 고성능을 얻을수 있도록 최적화 조건을 구하는 것이다. 이와 더불어 정의된 행위를 실제로 수행함으로써 예상한 결과와 실제 결과를 비교하여 설계가 제대로 되었는지 상위 수준에서의 검증을 목표로 한다.

• 한국항공운항학회지
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• 제16권4호
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• pp.41-48
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• 2008

Functional analysis of air transport mission is conducted to establish the performance requirements of the commercial transport designs. The analysis process begins by making a top-down analysis to the aircraft system level mission functions. Correctly interpreting the top-level performance requirements is the first step in designing and building an aircraft system. Each function and sub-function is allocated and examined to the aircraft level and flight operations phase to optimize the system performance and design requirements, such that these lower-level requirements can be traced back to the top-level requirements they are designed to fulfill. Special attention is given to making sure all interfaces, both internal and external, are addressed. The results are also in good resources of functional hazard assessment involved in certification processes.

• 대한전기학회:학술대회논문집
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• 대한전기학회 2006년도 춘계학술대회 논문집 전기기기 및 에너지변환시스템부문
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• pp.95-98
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• 2006

This paper proposes high speed SRM drive system for blower with a new 4-level inverter and precise excitation position generator. For the high speed blower, a proper inverter and control method are proposed and the output characteristics are analyzed. In order to get a fast build-up and demagnetization of excitation a current, 4-level inverter system is proposed. The proposed 4-level inverter has additional charge capacitor, power switch and diode in the conventional asymmetric converter. The charged high voltage is supplied to the phase winding for fast current build-up, and demagnetization current is charged to additional capacitor of 4-level inverter. In addition, a precise excitation position generator can reduce turn-on and turn-off angle error according to sampling period of digital control system. The proposed high speed SRM drive system is verified by computer simulation and experimental result.