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소정수,도규성,장윤제,송승호,한정수,문희장,So, Jungsoo,Do, Gyusung,Jang, Yunje,Song, Seungho,Han, Jungsoo,Moon, Heejang 항공우주시스템공학회 2008 항공우주시스템공학회지 Vol.2 No.2
This paper describes the performance characteristics of flow and structure in the post-chamber and nozzle. Using the computational fluid dynamics (CFD) technique, the stress and compressible flow fields in the downstream of the post chamber and nozzle were numerically calculated. Besides, the stress characteristics at the wall of post-chamber and nozzle were investigated under different thickness (2mm, 5mm and 10mm) of the nozzle wall. The stress pattern demonstrates that the strength of nozzle wall having 10mm is safer than that of 5mm or 2mm according to von Mises stress irrespective to the pressure field
다공 포트 연소기 후기 챔버의 유동 및 성능 특성 연구
소정수 ( Jung Soo So ),김소라 ( So Ra Kim ),송재천 ( Jae Chon Song ),이동훈 ( Dong Hoon Lee ),윤창진 ( Chang Jin Yoon ),문희장 ( Hee Jang Moon ) 한국항공운항학회 2007 한국항공운항학회지 Vol.15 No.4
This paper describes the flow and performance characteristics inside the post-chamber of the multi-port hybrid rocket motor. Using the computational fluid dynamics (CFD) technique, the non reactive compressible flow fields in the downstream of the fuel grain was numerically calculated. The motor performance obtained from computational results were in agreement with that conducted by the ground motor firing test. Besides, the flow field characteristics inside the post-chamber were discussed under different port numbers (1 port and 3 ports) of the fuel grain. The flow pattern showed that the performance of multi-port hybrid rocket motor having three grain ports is higher than that of the single-port one due mainly to the difference of incoming mass flow rate irrespective to the pressure field.
초음속 비행체 모델의 연성기법을 이용한 구조 안전성 해석
도규성,소정수,강지훈,김형진,박대훈,오정수,문희장,Do, Gyu-Sung,So, Jung-Soo,Kang, Ji-Hoon,Kim, Hyung-Jin,Park, Dae-Hun,Oh, Jeong-Su,Moon, Hee-Jang 항공우주시스템공학회 2008 항공우주시스템공학회지 Vol.2 No.2
The structural stability for preliminary model of supersonic rocket which has large L/D ratio is investigated. Large L/D ratio can cause a critical problem on the structural stability by the increase of bending-moment. By using the ANSYS and the CFX codes, we inspected the structural stability for Ma=2 and angle of attack for $20^{\circ}$. The optimum number of bolts and their joints required on the rocket surface are predicted.
김수종(Soojong Kim),김기훈(Gihun Kim),조정태(Jungtae Cho),조민경(Minkyoung Cho),도규성(Gyusung Do),소정수(Jungsoo So),허준영(Junyoung Heo),이정표(Jungpyo Lee),박수향(Suhayng Park),문희장(Heejang Moon),성홍계(Honggye Sung),김진곤(Jinkon 한국추진공학회 2008 한국추진공학회 학술대회논문집 Vol.2008 No.11
하이브리드 로켓엔진의 연소시험을 수행하기 위해 시험 설비를 제작하고 지상연소시험장을 구축하였다. 연소시험장 설비는 하이브리드 로켓엔진, 추력 시험대, 산화제 저장 및 공급 장치, 제어 장치, 데이터 획득 장치로 구성되었다. 추력 50 kgf 급의 연소 시험을 수행하여 안정적으로 성능 데이터를 획득할 수 있었으며, 연소시험장 설비의 작동 신뢰성을 확인하였다. Ground firing test facility and test field for firing test of hybrid rocket engine were constructed. Ground firing test facility were composed of hybrid rocket engine, thrust stand, oxidizer storage/supply system, control system and data acquisition system. Firing tests of thrust 50 kgf class were conducted. Stable performance data was obtained and operational reliability of ground firing test facility were found.
추력 650 kgf 급 하이브리드 로켓 모터의 연소시험
이정표(Jungpyo Lee),김수종(Soojong Kim),김기훈(Gihun Kim),조정태(Jungtae Cho),김학철(Hakchul Kim),우경진(Kyongjin Woo),도규성(Gyu-Sung Do),소정수(Jungsoo So),오정수(Jung-soo OH),조민경(Mingyung Cho),문희장(Heejang Moon),성홍계(Honggye S 한국추진공학회 2009 한국추진공학회 학술대회논문집 Vol.2009 No.11
본 연구에서는 추력 650 kgf 급의 PE/N2O 하이브리드 로켓 모터의 지상 연소시험을 수행하였다. 초기 실험에서 산화제 유량이 작게 유입됨으로 인해 연소실 압력 및 추력이 설계치 만큼 확보되지 못함을 확인 하였다. 이를 보완하기 위해 노즐목 감소 및 산화제 유량을 증대하여 실험을 수행하였고, 실험에서 발생하는 연소현상을 분석하였다. 또한 sub-scale과 lab-scale의 실험결과를 통해 scale에 따른 연소특성 변화를 비교? 분석 하였고, 동일 산화제 유속에서 sub-scale의 후퇴율이 lab-scale의 후퇴율보다 차이는 작지만 낮게 나타남을 확인했다. 본 연구의 결과를 통해 실제 하이브리드 사운딩 로켓 개발을 위해 고려되어야 할 사항을 파악할 수 있었다. In this study, we presented the results of static firing tests on the PE/LN2O hybrid rocket motor, which has a thrust of 650 kgf level. Through the early tests, we found that the combustion chamber pressure and the thrust were lower than design values because an actual oxidizer flow rate was less than that expected. In order to complement this result, the methods of decrease of nozzle throat and the increase of oxidizer mass flow rate were conducted in the next experiment, and we studied the combustion phenomena with the experimental results. Also we compared and analyzed a difference of combustion characteristics on scale effect. It show that a sub-scale motor regression rate was a little less than that of a lab-scale motor with the same oxidizer mass flux. Results of this study might be used as a basic data for development of hybrid sounding rocket.