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김수겸(Su Kyum Kim),원수희(Soo Hee Won),감호동(Ho Dong Kam),이준희(Jun Hui Lee),이재원(Jae Won Lee),전형열(Hyong Yoll Jun) 한국추진공학회 2015 한국추진공학회 학술대회논문집 Vol.2015 No.11
한국항공우주연구원에서는 달탐사를 위해 30N급 하이드라진 추력기 개발이 수행되고 있다. 30N급 추력기 DM은 초기 설계를 검증하기 위한 용도로 제작되었으며 성능 검증은 진공 시험장치를 수명 검증은 지상시험 장비를 이용하여 수행되었다. DM 모델에 대한 시험은 요구조건의 50% 정도가 수행되었으며 아직까지 성능저하가 나타나지 않고 있어 향후 추가시험을 계획하고 있다. 본 논문에서는 현재까지 수행된 DM 개발 결과 및 시험 결과를 정리하였다. A development of 30N class hydrazine thruster for lunar exploration is on going by Korea Aerospace Research Institute. Development model was manufactured to verify preliminary thruster design and firing test was performed at vacuum and atmospheric condition. In this paper, 30N hydrazine thruster DM design and test results will be presented.
조덕래(Deok-Rae Cho),원수희(Su-Hee Won),신재렬(Jae-Ryul Shin),이수한(Soo-Han Lee),최정열(Jeong-Yeol Choi) 한국추진공학회 2007 한국추진공학회지 Vol.11 No.1
Three dimensional structures of detonation waves propagating in a square tube were investigated using a high resolution CFD code coupled with a conservation equation of reaction progress variable and an one-step irreversible reaction. The code were parallelized based on domain decomposition technique using MPI library. The computations were carried on an in-house Windows cluster with AMD processors. Three-dimensional unsteady analysis results in the smoked-foil records caused by the instabilities of the detonation waves, which showed the rectangular and diagonal modes of detonation instabilities depending on the initial condition of disturbances and the spinning detonation for case of small reaction constant.
조덕래(Deokrae Cho),원수희(Soo-Hee Won),신재렬(Jae-Ryul Shin),최정열(Jeong-Yeol Choi) 한국추진공학회 2008 한국추진공학회지 Vol.12 No.3
The three-dimensional structure of detonation wave propagating in a circular tube was investigated using a parallel computational code developed previously. A series of parametric study for a circular tube of a fixed diameter gave the formation mechanism of the detonation cell structures depending on pre-exponential factor, k. The unsteady results in three-dimension showed the mechanisms of two, three and four cell mode of detonation wave front structures. The detonation cell number was increased but cell width and length were decreased with increased pre-exponential factor k. In the all multi-cell mode, the detonation wave structure and smoked-foil records on the wall are made by the moving of transverse waves. The detonation wave front structures have the regular polygon and windmill shapes periodically.
하이드라진 추력기 열차폐관의 최적설계를 위한 열/구조 해석
감호동(Hodong Kam),고준복(Joon Bok Ko),이준희(Jun Hui Lee),이재원(Jaewon Lee),김수겸(Soo Kyum Kim),원수희(Soo Hee Won),조승환(Seung Hwan Cho) 한국추진공학회 2015 한국추진공학회 학술대회논문집 Vol.2015 No.11
1 N급 하이드라진 추력기 열차폐관의 최적설계를 위한 열전달 및 랜덤진동 해석이 수행되었다. 침열회피용 홀 사이즈의 변화가 열전달 특성에 미치는 영향을 분석하기 위하여 침열회피용 홀의 크기가 각기 다른 열차폐관 모델을 전산모사 한다. 크기가 커질수록 열차폐 효과가 증가하였으며, 크기가 작아질수록 열확산속도가 증가됨이 확인되었다. 또한 해당 모델들의 랜덤 진동해석을 통해 운용조건에서 구조적 문제가 없음을 확인하였다. Heat conduction and random vibration of the thermal-barrier tube employed on the 1 N-class hydrazine thruster is conducted to optimize its design. The barrier-tubes having different hole sizes are simulated to investigate a correlation between thermal conduction characteristics and the size. Heat transfer rates though the barrier tube decreased with the increase of the hole diameter and is augmented when the diameter of hole becomes smaller. After the random vibration test, it was founded that the models have enough rigidity under the required environments.