• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.283-291
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• 2011

A computational investigation has been carried out to study the heat transfer characteristics of jet vane assembly used for the thrust vector control(TVC) of a vertical launch motor. In this study, the coefficients of convective heat transfer on the jet vane are calculated using the solutions of thermal boundary-layer equation and several semi-empirical equations. The calculation of 3-dimensional temperature distribution for the jet vane assembly was performed using the softwares called PATRAN and ABAQUS. The accuracy of the present numerical method is verified by comparing with the measured and calculated temperatures within jet vane shaft. The temporal variation of jet vane temperatures for three deflection angles(0o, 12.5o, 25o) was discussed.

• Journal of the Korean Society of Propulsion Engineers
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• v.7 no.4
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• pp.39-45
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• 2003

Of the various means for active trajectory correction, a thrust vector control system represents the only principle independent of missile external forces so that this method is operative. The purpose of this study is to analyze the characteristic of jet vane TVC(Thrust vector control) system among mechanical jet deflection. To ensure high performance leading edge shape, aspect ratio and ablated condition is optimized. Supersonic flow system, jet vanes and nozzle with Mach number 2.88 and under expansion ratio 2 were designed to study aerodynamic characteristics of leading edge shape, aspect ratio and ablated conditions.

• Journal of the Korean Society of Propulsion Engineers
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• v.5 no.4
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• pp.94-101
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• 2001

The shock structure of dual coaxial jet is experimentally investigated. Eight different kinds of coaxial, dual nozzles are employed to observe the major features of the near field shock structure on the supersonic, coaxial, dual jets. Four convergent-divergent supersonic nozzles having the Mach number 2.0 and 3.0 are used to compare the coaxial jet flows discharging from two sonic nozzles. The primary pressure ratio is changed in the range between 1.0 and 10.0, and the assistant jet ratio from 1.0 to 4.0. The results show that the impinging angle, nozzle geometry and pressure ratio significantly affect the near field shock structure, Mach disk location and Mach disk diameter.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.32 no.2
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• pp.133-140
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• 2019

In this paper, the penetration process of Shaped charge jet(SCJ) was simulated through finite element analysis to obtain physical quantities such as jet incidence velocity, penetration rate, and penetration increment. As a result of applying these physical quantities to the hydrodynamic theory, it was confirmed that the penetration efficiency of the jet with a high incident velocity is higher than that of the following slow jet. This efficiency decreased sharply when the jet was slower than the hydrodynamic limit(HL). On the other hand, the comparison of penetration increment and jet consumption over time showed that the length extension effect should be considered for SCJ's theoretical penetration analysis.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.12
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• pp.986-993
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• 2018

Lateral thrust jet has better maneuverability performance than the control surface like the conventional fin for attitude control or orbital transition of guided weapons. However, in the supersonic region, a jet interaction flow occurs due to the lateral thrust jet during flight, and a complicated flow structure is exhibited by the interaction of the shock wave, boundary layer flow, and the vortex flow. Especially, hit-to-kill interceptors require precise control and maneuvering, so it is necessary to analyze the effect of jet interaction flow. Conventional jet interaction analyses were performed under low altitude conditions, but there are not many cases in the case of medium altitude condition, which has different flow characteristics. In this study, jet interaction flow analysis is performed on the lateral jet controlled interceptor operating at medium altitude. Based on the results, the structural characteristics of the flow field and the changes of aerodynamic coefficient are analyzed.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.4
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• pp.84-91
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• 2002

Thrust vector characteristics of jet vanes installed in a shroud are very unique and much more complicated than those of the jet vane acting without any shroud by the fact of additional physical phenomena. The fluid dynamic interferences induced by jet vanes and shroud as well as jet vane's aerodynamic performance are investigated to characterize thrust vector control by semi-empirical model, three dimensional numerical analysis including real complex geometry, and ground firing test of real motors.

• Transactions of the Korean Society of Mechanical Engineers
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• v.7 no.2
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• pp.218-225
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• 1983

측벽부착형 순유체조자에서 제어입력이 존재할 때 2차원 난류제트가 오프셋된 경사면에 재접합하 는 현상을 연구하였고 정상상태하의 재접합모델을 이론적으로 전개하였다. 순유체조자의 상하면 이 제트의 확산에 미치는 영향을 조사하기 위하여 제트의 중심선에 따라 최대속도를 측정하였고, 그 결과에 따라 본 모델에 사용한 제트확산계수(.sigma.)의 값은 자유제트의 것 (.sigma.=7.67)보 다 큰 .sigma.=10.5로 택하였다. 이론적 모델을 확증하기 위하여 제트의 재접합점과 변형각도에 관한 기존 논문에 보고된 실험적 연구결과와 비교하여 좋은 일치를 보았다.

• Bulletin of the Korean Space Science Society
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• 2003.10a
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• pp.38-38
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• 2003

전리층은 우주환경의 변화에 매우 중요한 역할을 하고 있다. 그 중 전리층에서 발생하는 오로라는 우주환경의 변화를 가시적으로 보여주는 유일한 현상이다. 본 연구에서는 오로라 타원체를 따라 흐르는 오로라 제트전류의 위도에 따른 분포를 알아보고 그 특징을 조사하였다. 그리고 오로라 발생지역과 이들 전류분포를 비교하였으며 전기장과 전기전도도를 계산하여 오로라 제트전류에 대한 상대적인 기여도를 알아보았다. 먼저 CANOPUS 지자기 관측소의 1998년 데이터를 사용하여 1년간 발생했던 Isolated Substorm을 추려내었다. 그리고 이들 Substorm이 발생하는 동안 위도에 따른 오로라 제트전류 분포의 특징을 구하여 전류의 방향에 따라 이들 분포가 어떠한 형태로 나타나는지 알아보았으며, 이때 오로라 발생지역과의 연관성을 조사하였다. 여기서 전리층에 흐르는 전류를 무한판상으로 가정하여 오로라 제트전류의 분포를 지자기변화 성분으로부터 추론하였다. 또한 DMSP의 하강입자를 이용하여 계산한 전기전도도를 이용해 전기장을 추정함과 동시에 오로라제트전류에 대한 이들의 상대적 기여도를 조사해보았다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.93-95
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• 2009

This is a reviewing paper on the ramjet development programs of the U.S.A. and European countries through the presented papers at the ISABE 2005 and Joint Propulsion Conference 2008. Interestingly, the programs which are developing now are only limited on the ducted rocket, neither liquid nor pure solid fuel ramjet.

• Proceedings of the Korean Vacuum Society Conference
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• 2012.02a
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• pp.506-506
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• 2012

플라즈마 제트 장치를 이용하여 두 개의 플라즈마 plume을 평행하게 발생시킨다. 두 개의 플라즈마 plume의 전위차를 전극에서부터 plume 끝단까지 위치별로 측정한다. 두 개의 플라즈마 제트 장치에 인가하는 전압의 위상이 서로 반대일 경우, 두 개의 플라즈마 plume의 전위차로 인하여 plume사이에 streamer가 발생한다. 대기압에서 streamer가 발생하려면 십여 kV 이상의 전위차가 있어야 한다. 반대로 동일한 위상의 전압을 인가할 경우, 두 개의 플라즈마 plume의 전위차는 없기 때문에 plume사이에 streamer가 발생하지 않는다. 두 개의 플라즈마 제트 장치를 등가회로로 구성하고 위상차로 인한 streamer 발생여부를 확인한다. 그리고 두 개의 플라즈마 plume 사이에 발생한 streamer와 플라즈마 제트 장치를 등가회로로 구성하여 발생시킨 streamer 양을 비교한다. 이를 통해 플라즈마 plume의 전위차를 확인한다.