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황오식(Oh-sik Hwang),김형모(Hyungmo Kim),박부민(Poomin Park),조명득(MyeongDeuk Cho) 한국추진공학회 2012 한국추진공학회 학술대회논문집 Vol.2012 No.11
인간 동력 항공기는 인간의 근력으로만 비행을 하는 항공기이다. 하지만 인간의 근력은 다른 동력기관에 비해 좋지 못한 동력원이다. 그래서 인간의 근력을 최대한 손실없이 동력으로 사용하는 것이 중요하다. 이를 위하여 동력전달 메카니즘을 파악하고 인간의 근력을 효과적으로 전달하기 위한 방법을 모색하기 위해 인간 동력 항공기의 동력부를 모사한 아이언버드를 제작하였다. 또한, 아이언버드를 이용하여 조종사의 훈련을 수행하였다. 아이언버드를 이용하여 동력전달장치의 구성에 따른 성능을 파악하였으며, 이를 인간 동력 항공기에 적용하기 위한 기초 자료로 활용하였다. A human powered aircraft flies using only human muscular strength. The human power is not efficient as power source compared with other engines. So, it is important to use the human power as lossless as possible. For this reason, Ironbird was manufactured by simulating the power system of the human powered aircraft in order to comprehend the mechanism of power transmission and develop the method to deliver the human power to a propeller with high efficiency. It can be also used for training pilots. To evaluate the performance of Ironbird, torque and speed were measured with various composition of power transmission system. And these data were used as supporting references to improve the human powered aircraft.
친환경 추진제를 이용한 200N급 엔진의 설계 및 성능에 관한 연구
이양석,전준수,황오식,고영성,김유,김선진,Lee, Yang-Suk,Jun, Jun-Su,Hwang, Oh-Sik,Ko, Young-Sung,Kim, Yoo,Kim, Sun-Jin 한국군사과학기술학회 2010 한국군사과학기술학회지 Vol.13 No.6
In the last decade, hydrogen peroxide has received renewed interest as a green propellant which is non-toxic, environmentally clean and relatively easy to handle. This study was performed to acquire the design technique and combustion performance of a 200N bi-propellant engine using hydrogen peroxide and kerosene. The engine which used a catalytic ignition method was designed and cold flow tests were carried out to investigate atomization characteristics. Combustion tests including a pulse mode operation were performed to investigate the combustion performance on various O/F ratios. The results showed that the combustion efficiency and the repeatability of the engine performance were enough to use as an essential database for the development of a high performance engine.
다단 천음속 압축기의 유동 불안정성에 관한 실험적 연구
강영석(Young-Seok Kang),박태춘(Tae-Choon Park),황오식(Oh-Sik Hwang),양수석(Soo-Seok Yang) 한국유체기계학회 2011 유체기계 연구개발 발표회 논문집 Vol.2011 No.11
This study presents unsteady and unstable characteristics of three stage transonic axial compressor, developed by Korea Aerospace Research Institute. As approaching to the unstable operating region at the 103% design speed of the compressor, a modal type stall precursor appears in front of highly loaded 3rd rotor row at first, and it propagates to the upstream. On the contrary, actual stall cell initiates from the stall precursor in front of the 1st rotor row, and it propagates to the downstream of the compressor. After the stall region reached the 3rd stage and stall cell rotates circumferentially about 360deg, it develops to the one dimensional compressor surge mode. It shows a mild surge behaviour with 3~4 Hz frequency. From the test data, it can be suggested that there is a priority to give an optimum blade loading distributions to construct a multi stage transonic axial compressor stages either to secure more stable compressor operating ranges, or to maximize the compressor efficiency.