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Some Considerations to Change the CAD System of the Configuration Design Program from I-DEAS to NX
Kang-Soo Lee,Byung Hoon Park,Bang-Eop Lee,Won-Hoon Kim,Do Hyeong Lee,Tae-Kyung Hwang,Yeon-Cheol Kim,Seong-Gyo Jang,Byeong-Wook Choi,Hyuk-Sun Kwon,Sung Hwan Kim (사)한국CDE학회 2013 한국CAD/CAM학회 국제학술발표 논문집 Vol.2010 No.8
Approaches to avoid corruption of CAD models in configuration design method for solid rocket motors
Kang-Soo Lee,Won-Hoon Kim,Bang-Eop Lee,Do Hyeong Lee,Tae-Kyung Hwang,Yeon-Cheol Kim,Seong-Gyo Jang,Byeong-Wook Choi,Jun-Hui Shin,Hyuk-Sun Kwon,Dong-Pil Shin,Sung Hwan Kim 한국생산제조학회 2012 한국생산제조시스템학회 학술발표대회 논문집 Vol.2012 No.10
이응조(Yeung Jo Lee),구송회(Song Hoe Koo),장홍빈(Hong Bin Jang),이방업(Bang Eop Lee) 한국추진공학회 2011 한국추진공학회지 Vol.15 No.2
Launching tube is a kind of case to protect the guided weapons from external environments and conducted as a guide when they are fired. The guided weapons have been firmly kept at the launching tube and transferred, and would be separated at the required time when they are fired To meet the aim, it has been used explosive bolts which are reliable and efficient mechanical fastening devices having the special feature of a built-in release. The disadvantage of explosive bolt lies in that it is based on the high explosive effect of a pyrotechnic charge. When the explosive bolt is ignited, there are some bad effects; a flame, fragments and pyro-shock. Because of these bad effects there are many restriction to use bolt as joining devices to precision guided weapons. To solve these problems, the aim of the present work is to invent the ball-type separation bolt which is a pyrotechnically releasable mechanical linking device for two mechanical elements that does not suffer from such drawbacks. A standard pressure cartridge can moreover be easily integrated inside the device according to the present work and this with no modification to its structure. The present work was represented quantitatively the margin of separation safety and analysed separation mechanism in ball type separating bolt to perform the dynamic separation test.
부하-강도 분석을 이용한 격막형 펄스분리장치의 내열강도에 대한 신뢰성 예측 사례연구
이동원(Dong-Won Lee),정세용(Se-Yong Jeong),이방업(Bang-Eop Lee),정규동(Gyoo-Dong Jung),박부희(Boo-Hee Park),안동근(Dong-Geun An),장중순(Joong-Soon Jang) 한국신뢰성학회 2015 신뢰성응용연구 Vol.15 No.2
A stress-strength analysis is used to assess the reliability of a multi-pulse rocket motor system. Main stress is found to be thermal during explosion and the distribution is obtained by simulation. The strength distribution is derived from the results of actual specimen tests. The failure rate of barrier type pulse separation device is estimated.
고체 추진기관 구조체 설계 프로그램 개발을 위한 설계 부품 자료 구조
이강수(Kang-Soo Lee),김원훈(Won-Hoon Kim),이방업(Bang-Eop Lee) (사)한국CDE학회 2012 한국CDE학회 논문집 Vol.17 No.5
In this paper, we proposed a data structure to represent structural components of solid rocket motors (SRM) in an automated design program. To propose the data structure, we searched the necessary functions for the automated design program should have. In order to design the structural components of solid rocket motors sufficiently with a design program, it should have the functions to represent the shapes of the components, the drawing and analysis models, the design variables, various product structures, interferences, characteristic properties, design equations, and tightening sets. By modifying the data structure of an element object that is a general purpose data structure to represent a general component of a product, a new data structure was proposed to satisfy all the necessary functions with optimum. Finally, a design program for the structural components of solid rocket motors was developed successfully with the proposed data structure.
한혁섭(Houkseop Han),이원복(Wonbok Lee),구송회(Song-Hoe Koo),이방업(Bang-Eop Lee) 한국추진공학회 2011 한국추진공학회 학술대회논문집 Vol.2011 No.11
본 논문은 파열판 시험결과와 유한요소해석 결과를 비교하기 위한 것이다. 파열판은 고압장치에서 안전장치로 사용하고 있으며, 추진기관에서는 파열을 임의로 제어하기 위한 장치로서 사용한다. 탄소성 물성치를 이용하여 재해석을 수행한 이유는 탄소성 해석을 사용하여 압력용기 파열판의 한계하중 계산결과를 검증하고 임의의 형상에 대한 파열판의 한계하중을 계산하기 위한 것이다. 본 논문에서는 내식성이 우수한 고연성 소재인 AISI 316L을 이용하여 제작한 파열판의 파열시험을 수행하였다. 결과를 통하여 파열판의 크기에 대한 파열압력의 변화를 확인하고 유한요소해석 결과를 비교하여 탄소성 물성의 수정을 통해 정확성을 향상시켰으며, 임의의 형상에 대한 파열판 해석을 수행함으로써 계산 결과를 검증하였다. This paper provides a comparison between finite element analysis results and test data of rupture disc. Rupture disc is safety device of high pressure equipment. Rupture disc of solid rocket motor is a device to control rupture pressure. Rupture discs were made of AISI 316L. By the elastic-plastic analysis, the stress limit of rupture discs were compared to the test results. The results can be used to control the rupture pressure by the change of the disc size.
한혁섭(Houkseop Han),이원복(Wonbok Lee),구송회(Song-Hoe Koo),이방업(Bang-Eop Lee) 한국추진공학회 2012 한국추진공학회지 Vol.16 No.3
Rupture disks are a kind of safety device in high pressure equipment and they are used to control rupture pressure in the solid rocket motor. In this paper, a series of rupture experiments was performed using rupture disks made of AISI 316L and rupture pressure of rupture disks was calculated through various assumptions in relation between elasto-plastic material properties and true stress-strain curve. Experiment and FEA indicated rupture pressure is determined by size of rupture disks. As a result of elasto-plastic analysis, only multi-linear stress-strain curve was able to calculate meaningful estimations. Experimental results also showed rupture location are decided by the size of rupture disks. Experimental and FEA results will be applied to control rupture pressure of disks.
로켓 추진기관의 추력방향 조종 장치(TVC) 기술 분석
구송회(Song-Hoe Koo),이방업(Bang-Eop Lee),조원만(Won-Man Cho),이영신(Young-Shin Lee) 대한기계학회 2004 대한기계학회 춘추학술대회 Vol.2004 No.10
The characteristics and classifications of thrust vector control(TVC) systems for rocket motors are reviewed and the development trend and the applications of the TVC systems are studied. The TVC system is mainly effective while the rocket motor is operating, but that auxiliary motors can be used after the operation of the rocket motors. The TVC system is applied to the movable or fixed nozzle in accordance with the purpose of the rocket motors.