• Korean Journal of Computational Design and Engineering
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• v.9 no.3
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• pp.246-252
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• 2004

Presented in this Paper is a Micro Machining Service .(MIMS) based on the World Wide Web technologies. In order to ensure easy access to the service, the web browsers are used as the user interface. The pan geometry as an STL file is uploaded with process parameter for 3-axis CNC milling. Depending on the predefined user level, novice or expert, the user interface requires different parameters for process planning. An STL-based CAM resides in the server and automatically provides NC codes upon user's request. Tool-paths for scanning and pencil-cut, which are interference-free and precise, are created by the curve-based polyhedral machining method. A couple of sample parts were fabricated by a micro endmill with 127 fm diameter. From the tests, the parts fabricated by scanning followed by pencil-cut resulted in less error(within 2%) than the parts machined only by scanning tool-path.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 2004.05a
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• pp.265-265
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• 2004

최근 IT산업으로 대표되는 광통신 및 광신호 전달에 이용되는 광 반사경 및 렌즈어레이, 광가이드 판넬(BLU, FLU)등 광부품의 수요가 급증하고 있고, 이의 생산을 위한 다양한 제조공정이 연구 개발되고 있다 근년까지 이러한 마이크로 광부품의 제조방법은 포토리소그래피, 에칭기술을 베이스로 한 MEMS 기술, PDMS를 이용한 복재기술에 크게 의존하고 있다. 기계적 가공법으로는 오래전부터 초정밀 경면 선삭이나 연삭에 의한 마이크로 렌즈와 미세 패턴의 금형가공이 이루어져 왔다.(중략)

• Design & Manufacturing
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• v.2 no.1
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• pp.27-31
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• 2008

The object of this study is a manufacture of buff die using CAM systems. Systems are consist of AutoCAD, CAM software and CNC milling machine. CAM software is purpose of G-code generation for CNC programming. Then CAM software and CNC milling machine are connect to RS-232-C cable for networking.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.9
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• pp.32-37
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• 2003

The trend of miniaturization has been applied to the research on micro rockets resulting in prototype rockets fabricated by MEMS processes. In this paper, the development of three-dimensional micro rockets using micro milling as well as the results of combustion and flight tests are discussed. The body of rocket was made of 6061 aluminum cylinder. The three-dimensional micro nozzles were fabricated on brass by micro endmill with 127${\mu}m$ diameter. Two different micro nozzles were fabricated, one with 1.0mm of throat diameter and the other with 0.5mm. The total mass of rocket was 7.32g and that of propellant was 0.65g. The thrust-to-weight ratio was between 1.58 and 1.74, and the flight test with 45 degree launch angle form the ground resulted in 46m-53m of horizontal flight distance