http://chineseinput.net/에서 pinyin(병음)방식으로 중국어를 변환할 수 있습니다.
변환된 중국어를 복사하여 사용하시면 됩니다.
백국현(Gookhyun Baek),오종윤(Jongyun Oh),이영원(Youngwon Lee),이지형(Jihyung Lee),정진석(Jinsuk Jung) 한국추진공학회 2011 한국추진공학회 학술대회논문집 Vol.2011 No.11
유도탄의 저온 사출 시스템 구현에 있어서 요구된 이탈모타 개발 중 나타난 복기 추진제의 연소불안정, 특히 chuffing 현상을 해결하기 위해 시도되었던 여러 가지 기술적 접근방법과 이들의 시험 결과를 수록하였다. 본 이탈모타에서는 일반적으로 점화 에너지와 관련이 깊은 것으로 알려진 chuffing 현상이 점화 에너지의 공급량이나 공급 방법 등에 의해는 억제 효과가 나타나지 않았고, 추진제에 damping 물질인 ZrC를 2% 첨가함으로써 억제되었다. 이로써 복기 추진제의 연소불안정을 해결할 수 있는 새로운 경험을 얻게 되었다. To solve the combustion instability, especially chuffing phenomena, happened during development process of the drive-away motor that was required for cold launch system of missile, we tried various technical approaches and performed ground firing tests. The supplying content or method of ignition energy, generally that is deeply related with the chuffing phenomena, does not affect suppression of the chuffing, but the addition of 2% ZrC as a damping material is effective to suppress the chuffing. Therefore we could newly experience a special solution of the combustion instability in double base propellant.
백국현(Gookhyun Baek),오종윤(Jongyun Oh),이영원(Youngwon Lee),이지형(Jihyung Lee),정진석(Jinsuk Jung) 한국추진공학회 2012 한국추진공학회지 Vol.16 No.4
To solve the combustion instability, especially chuffing phenomena, happened during development process of a drive-away motor that was required for cold launch system of missile, various technical approaches have been performed through ground firing tests. The ignition energy or its supply system, generally closely related with the chuffing phenomena, does not affect suppression of the chuffing, but the increase of characteristic length(L<SUP>*</SUP>) as well as the addition of 2% ZrC as a damping material is effective to suppress the chuffing. Therefore we could have a typical experience on the combustion instability in double base propellant.
김상민(Sangmin Kim),김민택(Mintaek Kim),송순호(Soonho Song),백국현(Gookhyun Baek),윤웅섭(Woongsup Yoon) 한국추진공학회 2014 한국추진공학회지 Vol.18 No.5
Infrared signature of rocket plume plays an important role for detection, recognition, tracking and minimzing for low observability. Infrared signatures of rocket plume with reduced smoke propellant and smokeless propellant are measured. In order to estimate the infrared signature of rocket plume, CFD analysis for flow structure of plume is performed, and layered integration method for estimating of infrared signature is used. Numerical and experimental results were in good agreement. Both propellants had similar infrared signature. Strong peak at 4.3 μm region in the experimental results is appeared due to experimental error arising from the calibration procedure.
Composite 추진제 적용 사출용 가스발생기 성능 최적화 연구
한재욱(Jaeuk Han),이종섭(Jongseop Lee),류정헌(Junghun Ryu),김한준(Hanjun Kim),정세용(Seyoung Jung),백국현(Gookhyun Baek),이도형(Dohyung Lee) 한국추진공학회 2018 한국추진공학회 학술대회논문집 Vol.2018 No.5
유도탄 사출용 가스발생기는 일정 값 이상의 사출 종말 속도와 허용 조건 이하의 가속도를 동시에 만족시켜야 한다. 또한 발사 플랫폼 보호를 위해 일관된 성능과 안정적인 연소가 일어나야한다, 이를 위해서는 가스발생기 설계/제작 최적화가 필요하다. 본 연구에서는 가스발생기의 점화 성능에 영향을 미치는 점화기 주장약 양과 추진제 그레인의 연소속도를 변경하여 가스발생기를 제작, 시험 하였다, 점화기 주장약 양을 줄여 점화초기 압력을 낮추어 최대가속도를 저감 할수 있게 하였고 추진제 연소속도, 조성 변경을 통해 연소불안정성이 줄어든 것을 확인 하였다. Ejection gas generator for missile launching must satisfy the maximum initial acceleration of the missile and minimum missile ejection velocity at the same time. Also, to protect the launching platform, consistent performance and stable combustion are needed. To satisfy these requirements, optimization of gas generator design and manufacturing are essential. In this study, gas generator are manufactured and tested changing the igniter agent and propellant grain burning rate which influence the initial combustion performance. Reducing igniter agent makes the lower initial pressure profiler. And combustion instability is decreased by changing the propellant grain bring rate and composition.