http://chineseinput.net/에서 pinyin(병음)방식으로 중국어를 변환할 수 있습니다.
변환된 중국어를 복사하여 사용하시면 됩니다.
신영석,김성태,김헌주,김재영,황철호,Shin, Young-Sug,Kim, Seong-Tae,Kim, Heon-Ju,Kim, Jae-Young,Hwang, Chul-Ho 한국군사과학기술학회 2011 한국군사과학기술학회지 Vol.14 No.5
The prediction method of future events using the time histories of velocity or pressure, etc., is a useful way for controlling various air vehicles. For example, the sensors of velocity or pressure can be used to extract the time mode coefficients of eigenmode of flow field, and then the result is applied to suppress wake or drag. The velocity information is mapped to the entire flow field, so this mapping function can be used to predict the future events based on the current information. The mapping function is composed of the huge amount of weight parameters, so the efficient way of finding these parameters is needed. Here, the neural network algorithm is studied to draw a mapping function using the number and location of velocity sensors.
신영석,황철규,양해석,이열화,Shin Young-Sug,Hwang Cheol-Gyu,Yang Hae-Seok,Lee Yeol-Wha 한국군사과학기술학회 2004 한국군사과학기술학회지 Vol.7 No.4
In order to model a connection part between a control fin and actuator, the related characteristics of a dynamic stiffness were extracted from experiments. These characteristics include the static stiffness of a control fin and the dynamic stiffness of an actuator, so they are called the mixed dynamic stiffness here. This mixed dynamic stiffness is used as the boundary condition of a control fin connected to an actuator when the flutter characteristics are analyzed. The simulated stiffness of an actuator is corrected from the experiment results and the mixed dynamic is finally formulated in the domain of frequencies.
신영석(Young-Sug Shin),김헌주(Heon-Ju Kim),김성태(Seong-Tae Kim),김재영(Jae Young Kim),황철호(Chul-Ho Hwang) 한국항공우주학회 2011 韓國航空宇宙學會誌 Vol.39 No.10
고속 비행체의 날개 구조물은 스킨과 튼튼한 골격으로 구성되어 있다. 플러터 해석시 날개 구조물의 고유진동모드를 이용하여 비정상공기력을 계산하고 모달접근법을 이용하여 시간영역이나 주파수 영역에서 구조물의 진동안정성을 분석하게 되므로, 사용되는 고유 진동 모드는 신중하게 선정되어야 한다. 이를 위해 날개 구조물과 같이 고차에서 스킨의 국부 진동모드가 있는 경우 이러한 모드가 비정상공기력 및 플러터 특성에 미치는 영향을 분석하였다. The fin of high speed air vehicle is composed of skins and strong skeletons. In the flutter analysis, the eigenmodes of a fin are used for evaluating the unsteady aerodynamic force and the modal approach is applied for solving the flutter equation in both time and frequency domain. Therefore, the proper eigenmodes used for a modal flutter analysis should be chosen. For the appropriate choice of eigenmodes, when there exist local modes of a skin in the high modes, the effects of those modes on the unsteady aerodynamic force and flutter characteristics are anlalyzed.
趙江來,愼英晳 연세대학교 산업기술연구소 1986 논문집 Vol.18 No.1
In this study, the flow in the centrifugal pumps is analyzed by the vortex panel method. The flow is assumed to be inviscid and incompressible. To stabilize the fluctation of the computations, linearly varying vortex is used on each panel. Distributions of vorticity, velocity and pressure on the impeller with and without casing are calculated. The results are in good agreement with that of Kamimoto.