• 유체기계공업학회:학술대회논문집
• /
• 유체기계공업학회 2006년 제4회 한국유체공학학술대회 논문집
• /
• pp.415-421
• /
• 2006

The unsteady flow calculation around the proprotor of Smart UAV was conducted. Using the flight scenario of SUAV which composed of hover, transition, and airplane mode, the aerodynamic analysis of proprotor were performed for the variation of collective pitch, rpm, forward speed, and tilt angle. The unsteady compressible Navier-Stokes equations were used for the calculation and the dynamic overset grid technique was applied for the rotating proprotor. The aerodynamic performance of proprotor calculated in this way were validated by comparing with the performance data obtained from the blade element momentum method.

• International Journal of Fuzzy Logic and Intelligent Systems
• /
• 제14권1호
• /
• pp.26-33
• /
• 2014

This study addresses the control problem of an unmanned aerial vehicle (UAV) during the transition period when the flying mode changes from hovering to translational motion in the horizontal plane. First, we introduce a compensation algorithm that improves height stabilization and reduces altitude drop. The main principle is to incorporate pitch and roll measurements into the feedforward term of the altitude controller to provide a larger thrust force. To further improve altitude control, we propose the fuzzy logic controller that improves system behavior. Simulation results presented in the paper highlight the effectiveness of the proposed controllers.

• 한국군사과학기술학회지
• /
• 제8권3호
• /
• pp.24-32
• /
• 2005

This paper describes the tracking filter performance for Naval Gun Ballistic Computation Unit(BCU). BCU needs tracing filter for gun firing. Using data of tracking sensor, BCU calculates the future position of Target and Gun order in the time of flight. In this paper, tracing filter is designed with interacting multiple model(IMM). The tracking algorithm based on the IMM requirers a considerable number of sub-model for the various maneuvering target in order to have a good performance. But, in the case of ship target, the maneuvering is restricted compared with the air target. Considering the maneuvering properties and adjusting the mode transition probabilities and the process noise of sub-model, We designed the IMM3 algorithm for Naval tracking filter with three sub-model.

• International Journal of Computer Science & Network Security
• /
• 제22권2호
• /
• pp.297-303
• /
• 2022

The main purpose of the study is to determine the main aspects of the problem of socio-economic development in the conditions of the digital economy. The post-industrial era is characterized by the development of the electronic environment and the transition to an information civilization. In this regard, the developed countries of the world pay considerable attention to the development of the digital economy. However, there are a significant number of problems associated with this process. The country cannot be successful in the development of the digital economy in the absence of the necessary legal framework, an economic development strategy based on digital technologies. The research methodology involves the use of several theoretical methods for analyzing and synthesizing information. As a result of the study, the key problems of socio-economic development in the digital economy were characterized.

• 대한화학회지
• /
• 제36권6호
• /
• pp.832-839
• /
• 1992

Time-of-Flight(TOF) 질량분석기가 설치된 분광분석장치를 이용하여 레이저 공명이온화 분광법으로 극미량의 납을 정량하였다. 납에 대한 극미량 분석을 위해 단색 2광자 공명이온화, 2색 2광자 공명이온화 및 3색 3광자 공명 이온화의 세 가지 광이온화 경로가 시도되었다. 이 때, 첫번째 들뜬 준위는 바닥준위로부터 283.3 nm의 파장에 해당하는 6p7s($^3P_1$)준위를 공통적으로 사용하였다. 이들 이온화경로를 통해 여러가지 농도의 납 표준용액을 사용하여 0.1 ${\mu}g$에서 1pg의 영역에 해당하는 검정곡선을 얻었다. 검정곡선으로부터 얻은 본 분석법의 검출한계는 2색 2광자 공명이온화 및 3색 3광자 공명이온화의 경우 각각 20 및 10pg 이었다. 또한 각각의 이온화 경로에 따른 이온화 효율도 함께 비교 검토하였다.

• 한국환경농학회지
• /
• 제34권3호
• /
• pp.230-237
• /
• 2015

BACKGROUND: To identify the sources of inaccuracy in LC/MS/MS methods used in the routine quantitation of small molecules are described and discussed. METHODS AND RESULTS: Various UPLC coupled to triple quadrupole mass spectrometer and time of flight (TOF) were used to identify the potential sources of inaccuracy and inducing the pitfalls of qualification and quntitation during the veterinary drug residue analysis. Some of stable isotope labelled veterinary drugs, which were used as internal standards, presented "cross-talk", regardless of manufactures of mass spectrometer and types of spectrometer. Group of sulfonamides also presented inaccuracy qualification and quantitation due to the multi-residue analytical method with the same fragment ions at the close retention times. CONCLUSION: The phenomena of "cross-talk" occurring between subsequently monitored transition from stable isotope labelled and isotope non-labelled authentic chemical were identified. To prevent errors and achieve more accurate data during the analysis of small molecules by LC/MS/MS SRM method, Followings should be taken care of and kept checking; purity and concentration of stable isotope as an internal standard, prevention of carry-over during the separation in column, minimizing the ion suppression by matrix effect, identification of retention time, precursor ion and product ion, and full knowledge of data processing including smoothing and peak integration.

• 항공우주시스템공학회지
• /
• 제18권1호
• /
• pp.72-78
• /
• 2024

공전하는 행성 간 천이 궤도 설계에서 우주 탐사기의 위치는 목표 행성의 미래 도착 시점에 변경된 위치와 일치되어야 한다. 람베르트 문제의 해를 얻는 것은 우주 탐사기 초기 위치벡터, 비행시간, 최종 위치벡터로부터 천이궤도 요소들을 결정할 수 있기 때문이다. 두 지점 경계치 궤도 문제이며 지정된 제한 조건이 최적화되는 적절한 원하는 행성 간 천이궤도를 선택 할 수 있다. 이와 같은 논리에서 람베르트 해로 얻을 수 있는 행성 간 천이 궤도는 출발 속도에 제한이 없다면 수리적으로 무한히 존재한다. 현재까지 우주 탐사기의 출발 시점 초기 속도는 우주 발사체 역량에 크게 의존하고 있다. 본 논문에서는 미국 엠브리 리들 항공대학의 하워드 교수의 알고리즘을 사용하여 람베르트 해와 천이 궤도 요소를 결정하였다.

• 천문학회지
• /
• 제31권1호
• /
• pp.1-17
• /
• 1998

To understand the basic physics underlying large spatial fluctuations of intensity and Doppler shift, we have investigated the dynamical charctersitics of the transition region of the quiet sun by analyzing a raster scan of high resolution UV spectral band containing H Lyman lines and a S VI line. The spectra were taken from a quiet area of $100'\times100'$ located near the disk center by SUMER on board SOHO. The spectral band ranges from 906 A to 950 A with spatial and spectral resolution of 1v and $0.044 {\AA}$, respectively. The parameters of individual spectral lines were determined from a single Gaussian fit to each spectral line. Then, spatial correlation analyses have been made among the line parameters. Important findings emerged from the present analysis are as follows. (1) The integrated intensity maps of the observed area of H I 931 line $(1\times10^4 K)$ and S VI 933 line $(2\times10^5 K)$ look very smilar to each other with the same characterstic size of 5". An important difference, however, is that the intensity ratio of brighter network regions to darker cell regions is much larger in S VI 933 line than that in H I 931 line. (2) Dynamical features represented by Doppler shifts and line widths are smaller than those features seen in intensity maps. The features are found to be changing rapidly with time within a time scale shorter than the integration time, 110 seconds, while the intensity structure remains nearly unchanged during the same time interval. (3) The line intensity of S VI is quite strongly correlated with that of H I lines, but the Doppler shift correlation between the two lines is not as strong as the intensity correlation. The correlation length of the intensity structure is found to be about 5.7' (4100 km), which is at least 3 times larger than that of the velocity structure. These findings support the notion that the basic unit of the transition region of the quiet sun is a loop-like structure with a size of a few $10^3 km$, within which a number of unresolved smaller velocity structures are present.

• 한국전산유체공학회:학술대회논문집
• /
• 한국전산유체공학회 2009년 춘계학술대회논문집
• /
• pp.19-19
• /
• 2009

Dynamic Stall is a flow phenomenon which occurs on the retreating side of helicopter rotor blades during forward flight. It also occurs on blades of stall regulated wind turbines under yawing conditions as well as during gust loads. Time scales occurring during this process are comparable on both helicopter and wind turbine blades. Dynamic Stall limits the speed of the helicopter and its manoeuvrability and limits the amount of power production of wind turbines. Extensive numerical as well as experimental investigations have been carried out recently to get detailed insight into the very complex flow structures of the Dynamic Stall process. Numerical codes have to be based on the full equations, i.e. the Navier-Stokes equations to cover the scope of the problems involved: Time dependent flow, unsteady flow separation, vortex development and shedding, compressibility effects, turbulence, transition and 3D-effects, etc. have to be taken into account. In addition to the numerical treatment of the Dynamic Stall problem suitable wind tunnel experiments are inevitable. Comparisons of experimental data with calculated results show us the state of the art and validity of the CFD-codes and the necessity to further improve calculation procedures. In the present paper the phenomenon of Dynamic Stall will be discussed first. This discussion is followed by comparisons of some recently obtained experimental and numerical results for an oscillating helicopter airfoil under Dynamic Stall conditions. From the knowledge base of the Dynamic Stall Problems, the next step can be envisaged: to control Dynamic Stall. The present discussion will address two different Dynamic Stall control methodologies: the Nose-Droop concept and the application of Leading Edge Vortex Generators (LEVoG's) as examples of active and passive control devices. It will be shown that experimental results are available but CFD-data are only of limited comparison. A lot of future work has to be done in CFD-code development to fill this gap. Here mainly 3D-effects as well as improvements of both turbulence and transition modelling are of major concern.

• 한국항공우주학회지
• /
• 제38권6호
• /
• pp.586-595
• /
• 2010

초음속에서 극초음속 영역까지 작동 가능한 이중램제트(이중연소/이중모드) 추진기관의 성능특성을 파악하고 설계인자를 도출하기 위하여 램제트/스크램제트 추진기관의 작동원리에 대한 물리적인 이해를 바탕으로 공기 및 열역학적 관점에서 각 추진기관의 성능특성에 대한 이론적인 연구를 수행하였다. 사이클 해석을 기반으로 하여 각 추진기관의 연소기 입구 마하수와 연소기 형상에 따른 성능특성 및 작동영역의 한계를 연구하였다. 이를 바탕으로 이중램제트의 작동천이 마하수를 파악하고 효율적인 작동영역분배특성을 살펴보았다.