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정봉구,Jeong, Bonggu 항공우주시스템공학회 2012 항공우주시스템공학회지 Vol.6 No.3
Until now, The Market of aviation parts had led by OEM(Original Equipment Manufacturer) parts because of aviation industry's nature required higher reliability and safety. But recently, The interest about PMA parts in aviation market is increasing continuously with various environmental changes, such as economic stagnation, oil price rise, development of the manufacture technique and newly rising market of Asia-Pacific region. So, this paper introduces the trend and the requirements of FAA PMA / EASA EPA in order to enhance understanding for certification for aviation parts.
비행 중인 항공기에 발생할 수 있는 연기에 대한 인증기준 및 적합성 입증방법
정봉구,진영권,김유광,박근영,Jeong, Bonggu,Jin, Yongkwon,Kim, Yougwang,Park, Guenyoung 항공우주시스템공학회 2007 항공우주시스템공학회지 Vol.1 No.4
From the beginning of aviation history, in-flight smoke/fire events have been a serious issue. As aircraft are getting larger and are becoming more auto-piloted and aircraft systems are getting more complex, it is an increasing risk of in-flight smoke/fire accidents accompanied with fire events. Therefore, we review the statistics of fire/smoke accidents in order to enhance an understanding for risk of in-flight smoke events, and present the certification requirements for smoke per KAS Part 25. In addition, we provide acceptable methods of complying with related requirements, such as smoke detection test, smoke penetration test and smoke evacuation test.
축소형 모델 연소기에서 상온상압기상연소시험을 통한 FOOF 충돌형 분사기의 연소안정성 평가
정봉구(Bonggoo Jeong),김홍집(Hong Jip Kim) 한국연소학회 2013 KOSCOSYMPOSIUM논문집 Vol.2013 No.12
The objective of present study is to investigate the combustion stability boundaries of FOOF impinging injectors. For model tests. subscale chamber was adopted. Gaseous oxygen and methane/propane mixture are used to simulate actual propellants like liquid oxygen and kerosene. Experimental tests were performed under conditions of ambient temperature and pressure. Major instability region was determined and extrapolated by the parameters of combustion-chamber pressure and mixture ratio. This methodology can be used to quantify the stability margin of various injectors.
고고도 모사를 위한 축소형 디퓨저의 성능 특성에 대한 수치적 연구
정봉구(Bonggoo Jeong),임경진(Kyungjin Yim),조성휘(Seonghwi Jo),김홍집(Hongjip Kim),전준수(Junsoo Jeon),고영성(Youngsung Ko),김승한(Seung-han Kim),한영민(Yeoung-Min Han) 한국추진공학회 2012 한국추진공학회 학술대회논문집 Vol.2012 No.5
고고도 모사를 위한 축소형 디퓨저의 성능특성을 파악하기 위해 수치적 연구를 수행하였다. 입구길이를 노즐 출구직경과 비교해 0%, 50%, 100%로 변화시켰고, 디퓨저 목의 길이는 디퓨저 목의 직경과 비교해 3, 5, 7, 8, 12로 다양화하여 수치해석하고 실제 모사실험 값과 비교하였다. 그 결과 디퓨저의 입구길이가 짧아질수록 plume의 형상은 수축되었다. 또한, 디퓨저의 이차목 길이가 디퓨저 지름의 최소 7~8배보다 작으면 내부에 마하디스크가 형성되어 압력의 급격한 상승을 일으킨다. Performance characteristics of subscale diffuser for high-altitude simulation have been numerically investigated. The length of diffuser entrance with respect to nozzle exit diameter was changed to 0, 50, 100%, respectively. In addition, flow characteristics have been studied for various length to diameter ratio of secondary throat diffuser. As a result, the shape of plume was contracted for insufficient length of diffuser entrance. Also, if the length to diameter ratio of secondary throat diffuser were less than 7 or 8, mach disk has been formed inside the diffuser.