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류백능(Baekneung Ryoo),김백용(Baegyong Kim),유지창(Jichang Yoo) 한국추진공학회 2016 한국추진공학회 학술대회논문집 Vol.2016 No.12
유도탄 탄약고와 발사관(또는 저장 용기) 내부의 적정 저장 습도는 전자/기계 부품의 부식과 시효성 품목의 물성 저하를 방지하여 유도탄의 수명 연장 여부를 좌우하는 요소이다. 본 논문에서 철의 부식 속도가 급격히 증가하기 시작하는 경향을 고려하여 탄약고의 적정 저장 습도 기준을 제시하였고, Peck’s moisture model의 계산 결과와 실제 군에서 유지하고 있는 저장 습도 사례에 따라 발사관 내부의 적정 습도 기준을 제시하였다. The proper storage humidity in missile magazine and launch tube(and/or storage container) is very important factor that prevents the corrosion of electronic/mechanical components and deterioration of physical/mechanical properties of the energetic components, and affects the service life extension lifetime. In this paper, the proper storage humidity standards of inside the missile magazine and launch tube(and/or storage containers) is suggested.
김동륜(Dongryun Kim),류백능(Baekneung Ryoo) 한국추진공학회 2008 한국추진공학회지 Vol.12 No.2
It is known that the adhesive interface testing of the rocket motor using the ultrasonic wave is superior to the other testing methods about the ability to economical detect the defects. But, the signal analysis of the ultrasonic wave takes a lot of time and efforts because the time interval of the transmitted pulse and the received pulse is too short to separate the reflected signals due to the multi-layers of the rocket motor. The ultrasonic testing of rocket motor have only applied to the automatic system about extremely limited areas like the debond in adhesive interface between the motor case and the insulator. In this study the new technique to detect the debond between the liner and the propellant using the property of the resonance and the lamb waves instead of the existing ultrasonic testing was described.
HTPB 추진제 노화 특성 및 HFC 기반 수명 평가 기법
조원호(Wonho Cho),M. Westerlund,류백능(Baekneung Ryoo),정규동(Gyoodong Jung),유지창(Jichang Yoo) 한국추진공학회 2018 한국추진공학회지 Vol.22 No.5
During natural aging, hydroxyl-terminated polybutadiene(HTPB) propellant undergoes a series of slow physico-chemical degradation reactions. By using accelerated ageing conditions it is possible to simulate the material behavior at different time-temperatures focusing on in-service conditions. Aging behaviors of HTPB propellant are investigated using HFC(heat flow calorimeter), a universal technique for measuring the rate of slow chemical and physical processes in long-term storage.
류병태(Byungtae Ryu),이도형(Dohyung Lee),류백능(Baekneung Ryoo),최홍석(Hongseok Choi) 한국추진공학회 2011 한국추진공학회 학술대회논문집 Vol.2011 No.11
본 논문은 우발적 화재에 노출되면 이상 온도를 감지하고, 자동으로 반응하여 추진제를 연소시킴으로써, 고체 추진기관의 위험 정도를 완화시키는 둔감 점화 장치의 반응을 연구한 결과이다. Kissinger 식으로 구한 둔감 점화 장치 신호 화약의 자동 점화 온도는 165.5℃이었지만, 추진기관에 장착하고 MIL-STD-2105D의 규정에 따라 수행한 완속 가열 시험에서는 약 140℃에서 연소 반응을 하였다. This paper describes on the study of mitigation technique in which a pyrosensor is automatically sensing the rate of risk of fire or explosion of solid rocket motor exposed to an unexpected fire and makes the rocket motor burn itself safely. SCO test was carried out with a rocket motor loaded with HTPB propellant, in which a thermal pyrosensor igniter was installed. The rocket motor in SCO test was located in an oven at 50℃ for 7 hours. The temperature was regulated to be elevated at the rate of 3.3℃ per hour. Results showed Type V(Burning) reaction in this SCO test.
류병태(Byungtae Ryu),이도형(Dohyung Lee),류백능(Baekneung Ryoo),최홍석(Hongseok Choi) 한국추진공학회 2012 한국추진공학회지 Vol.16 No.6
This paper describes the results of study on reaction of insensitive igniter in which a pyrosensor is automatically sensing the rate of risk of fire or explosion of solid rocket motor exposed to an unexpected fire and makes the rocket motor burn itself safely. The Slow Cook Off(SCO) test following the regulation of MIL-STD-2105D was carried out with a rocket motor loaded with HTPB propellant, in which a thermal pyrosensor igniter was installed. The auto-ignition temperature measured was approximately 140℃ and it corresponded to Type V(Burning) reaction in SCO test, while the temperature by Kissinger equation was calculated to be 165.5℃.