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고밀도 지르코늄(Zr) 금속연료 조성의 추진제를 이용한 무노즐 부스터 성능 연구
길태옥,정은희,이기연,류태하 한국추진공학회 2018 한국추진공학회지 Vol.22 No.2
This study was carried out to improve the performance characteristics of nozzleless boosters that are used in ramjet boosters. A propellant using Zr as the metal fuel was developed, which provided a higher density than the propellant using Al as the metal fuel. The developed propellant was cast using the nozzleless booster and a ground test was carried out by varying the length-to-diameter ratio (L/D ratio) of the propellant. From a comparison between the performance characteristics of propellants using Zr and Al, it was proved that the performance of the propellant using Zr is higher than that of propellant using Al, except for the specific impulse, under all tested conditions. As the length-to-diameter ratio was increased, the specific impulse of the propellant using Zr was decreased by 88% compared with that of the propellant with Al. However, because of the density difference between the propellants, the impulse density of the propellant with Zr was higher than that of the propellant with Al under all tested conditions. 무노즐 부스터의 성능을 향상시키기 위한 연구를 수행하였다. 알루미늄 금속연료와 비교하여 고 밀도를 갖는 지르코늄을 사용한 고밀도 추진제를 개발하였고, 이 추진제를 이용하여 세장비에 따른 성능 특성을 알아보았다. 알루미늄 조성의 추진제 성능과 비교하여 모든 세장비에서 지르코늄 조성의 추진제가 비추력을 제외하고 높게 나타났다. 지르코늄 조성의 추진제의 비추력은 세장비가 증가함에 따라 시험조건 내에서 알루미늄 조성의 추진제와 비교하여 88%까지 감소하였다. 그러나, 추진제의 밀도차이로 인하여 모든 세장비에서 알루미늄 조성의 추진제보다 지르코늄 조성의 추진제가 높게 나타났다.
저주파 압력섭동 범위 내에서의 단일 스월 인젝터의 진폭-위상 특성 연구
길태옥(Taeock Khil),정연재(Yunjae Chung),윤영빈(Youngbin Yoon) 한국추진공학회 2010 한국추진공학회지 Vol.14 No.2
Generally, combustion instability is generated by the mutual coupling between the heat release and the acoustic pressure in the combustor. On the occasion, the acoustic pressure generates the oscillation of the mass flow rate of propellant injected from injector, and this oscillation again affects combustion in the combustor. So, the dynamic characteristics of the injector have been studied to control combustion instability using injector itself in Russia from 1970’s. In order to study injector dynamics, a mechanical pulsator for forced pressure pulsation is produced and the method to quantify the mass flow rate of the propellant that is oscillating at the exit of the injector is developed. With the pulsator and the method, pulsating values of the mass flow rate, pressure, liquid film thickness, and axial velocity generated at the exit of the simplex swirl injector are measured in real time. And phase-amplitude characteristics of each parameter are analyzed using these pulsating values acquired at the exit of the simplex swirl injector.
알루미늄(Al) 금속연료 조성의 추진제를 이용한 무노즐 부스터 개발
길태옥(Taeock Khil),정은희(Eunhee Jung),이기연(Kiyeon Lee),류태하(Taeha Ryu),이형진(Hyoungjin Lee) 한국추진공학회 2017 한국추진공학회지 Vol.21 No.4
The study for the performance characteristics of the nozzleless booster used in ramjet booster was carried out. Performances related to pressure and thrust for nozzleless booster are lower than classical motor those because of absence of convergent and divergent sections of nozzle. To solve this problem, it developed a high-performance propellant with maximum impulse density included Al as metal fuel. Using the nozzleless booster casted the propellant, ground test of it was carried out by varying the length-to-diameter ratio (L/D ratio) of the propellant. Specific impulse of nozzleless booster was limited to about 75 percents of its value compared with that of classical motor adapted nozzle in the same propellant and propellant length and will be estimated approximately 85 percents of its value compared with that of classical motor at same average pressure in terms of the curve fitting by our test results.