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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.
Multi-port 하이브리드 로켓 연소기에서 고온 산화제 유동에 의한 고체연료의 구조적 안전성에 대한 연구
도규성 ( Gyu Sung Do ),윤창진 ( Chang Jin Yoon ),문희장 ( Hee Jang Moon ),김진곤 ( Jin Kon Kim ) 한국항공운항학회 2007 한국항공운항학회지 Vol.15 No.4
This paper describes the structural safety of solid fuel in the Hybrid Rocket Motor (HRM). Hybrid rocket combustion has the distinct regression characteristics which include the process of thermal pyrolysis and fuel vaporization. Most of all, this regression characteristics would structurally affect the strength of the fuel having a multi-port configuration, and even may cause the breaking from the fuel grain. This problem would probably influence the performance and operating safety of HRM. Therefore, for the safe operation of HRM, the critical port radius which determines the structurally safe region was discussed from the heat analysis of the solid fuel.
경사진 그레인 포트를 가진 하이브리드 로켓의 연소 특성
김재우(Jae-woo Kim),김수종(Soo-jong Kim),오정수(Jung-soo Oh),도규성(Gyu-sung Do),소정수(Jung-soo So),문희장(Hee-jang Moon) 한국추진공학회 2011 한국추진공학회지 Vol.15 No.2
In this paper, the combustion characteristics of hybrid rocket fuel with tapered grain port were investigated experimentally. The charging efficiency of convergent and divergent port shape fuel with 1° taper angle was 6.8% higher than that of cylindrical port shape fuel. The regression rate was increased about 17.5% by using the convergent port shape fuel. On the other hand, in case of divergent port shape fuel, no notable difference of regression rate was observed when compared to that of the cylindrical port shape fuel. In the case of convergent port shape fuel, characteristic velocity and its efficiency were notably increased with respect to cylindrical port fuel. It was found that convergent port shape of hybrid rocket fuel can lead to a better option compared to the conventional cylindrical port in terms of combustion efficiency and performance improvement.
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.