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이종섭(Jongseop Lee),이용규(Yongkyu Lee),박진일(Jinil Park),이종화(Jonghwa Lee) 한국자동차공학회 2012 한국자동차공학회 학술대회 및 전시회 Vol.2012 No.11
Because of environment degradation, development of electric vehicles have been actively taken place. However, because the electric vehicles cannot drive a long distance, automotive companies are developing an EREV to overcome a limitation of a driving distance for an electric vehicle. EREV is abbreviation of Extended-Ranged-Electric-Vehicle as a means Electric vehicle which increase the driving distance. In this study, a EREV simulation model is developed to predict a fuel-economy and performance. This program is developed using Matlab-Simulink based on research of the energy flow or EREV. Using the program, User can predict the fuel economy, All electric range, Performance and etc. Simulation results are come in useful to testing many cases of EREV specification and test condition. This simulation will be useful to set a EREV specification to improve an fuel-economy and performance.
적외선(IR, Infrared) 신호가 감소된 고체추진제 개발
이종섭,임유진,박의용,한혁섭,Lee, Jongseop,Yim, Yoojin,Park, Euiyong,Han, Houkseop 항공우주시스템공학회 2013 항공우주시스템공학회지 Vol.7 No.4
In this paper, a study of solid rocket propellant formulation is performed to suppress plume and reduce IR(infrared) signature which occurs in propellant combustion. The solid propellant to enhance the stealthy ability was formulated in terms of the kinds and the effects of afterburning suppressant on the ballistic performance and the amount of primary smoke. In addition, substantial decrease in plume and IR signature is confirmed by static firing test by a 4 inch standard motor.
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.
임유진(Yoojin Yim),이종섭(Jongseop Lee),박의용(Euiyong Park),최성한(Sunghan Choi),유지창(Jichang Yoo),조영(Young Cho) 한국추진공학회 2013 한국추진공학회지 Vol.17 No.5
This paper describes a study on after-burning suppressant in a solid propellant to reduce the plume formed outside of rocket nozzles, which could expose the launch site and the flight track. The minimum smoke propellant to enhance the stealth ability was formulated in terms of the kinds and the effects of after-burning suppressant on the ballistic performance and the amount of primary smoke. A after-burning suppressant, K2SO4 of about 1.1% weight content was found to show profound reduction of the rocket plume, giving negligibly slight increase in pressure exponent of burning rate. Also minimum smoke propellant with less than 1.1% of K2SO4 corresponds to A-class satisfaction in primary smoke by AGARD standard.
임유진(Yoojin Yim),이종섭(Jongseop Lee),박의용(Euiyong Park),한혁섭(Houkseop Han),장명욱(Myungwook Jang),송순호(Soonho Song),김민택(Mintaek Kim),유지창(Jichang Yoo),윤명원(Myongwon Yoon) 한국추진공학회 2014 한국추진공학회 학술대회논문집 Vol.2014 No.5
전술용 고체 로켓은 연소 중에 발생되는 기체가 가시적으로 보이는 일차 및 이차 연기가 없는 복기 추진제 또는 희연 추진제가 많이 사용된다. 로켓의 연소 기체 플룸 속에는 다양한 에너지가 방출되는데, 이 중에서 적외선은 유도 조종에도 활용되지만, 로켓의 탐지에도 이용될 수 있기 때문에 적외선의 방출을 줄이는 것이 필요하다. 본 연구에서는 나이트레이트 폴리이서(nitrate ester polyether: NEPE)계열의 희연 추진제에서 AGARD 연기등급이 AA를 만족시키는 조건하에 황산칼륨의 함량에 따른 후연소 반응과 적외선 방출량의 차이점을 고찰하였다. 황산칼륨을 추진제 성분에 첨가함으로서 플룸의 길이 및 중파장의 적외선 방출량이 크게 감소하였다. The solid rocket for tactical missile is favorably charged with double base or minimum smoke propellant not to show a visible primary and secondary smoke. One of the plume characteristics from this kind of rocket is the infrared radiation signature which may be useful for detection of rocket. Therefore the reduction of IR radiation should be necessary within rocket motor plume. In this paper minimum smoke propellant with nitrate ester polyether system has been researched for the afterburning and IR irradiance difference with potassium sulfate content in propellant formulation satisfied with AGARD smoke class AA. The plume length and mid-range IR irradiance is found to be greatly reduced by potassium sulfate addition in propellant.
임유진(Yoojin Yim),이종섭(Jongseop Lee),박의용(Euiyong Park),최성한(Sunghan Choi),유지창(Jichang Yoo),조영(Young Cho) 한국추진공학회 2013 한국추진공학회 학술대회논문집 Vol.2013 No.5
고체 추진제를 적용한 추진기관은 추진제의 연소 중에 완전하게 연소되지 못한 연소기체가 노즐 뒷쪽에서 발생하는 후연소 반응으로 인하여 큰 플룸(plume)을 형성하게 된다. 이 플룸으로 인해 적외선 방출량이 증가하므로 적외선 감지기에 의해 발사 위치나 비행궤적이 노출될 수 있다. 열경화성 무연계 고체추진제에 후연소 반응 방지제로 K<sub>2</sub>SO<sub>4</sub>를 적용하여 후연소 반응이 크게 감소하는 것을 알 수 있었다. K<sub>2</sub>SO<sub>4</sub>의 함량이 증가하면 압력지수가 점차 증가하며, 1차 연기의 발생량도 증가하므로 약 1%를 사용해야 AGARD 기준으로 일차연기 A등급에 부합되는 것으로 계산되었다. The large scale plume could be produced behind nozzle outside during combustion of solid rocket motor by the afterburning of combustion gases which weren’t completely oxidized. The infrared emission increased due to plume could cause the exposure of launch site or flight track by infrared detector. The thermosetting minimum smoke propellant was found to be profoundly reduced the plume by application of potassium sulfate as afterburning suppressant. It was shown that the potassium sulfate increase in propellant increased pressure exponent in burning rate and primary smoke. In order to satisfy A class in primary smoke by AGARD standard, potassium sulfate in propellant was calculated to be contained about 1 mass percentage.