• 한국산학기술학회논문지
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• 제20권8호
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• pp.579-585
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• 2019

수중 표적의 탐지 효율을 증대시키기 위하여 능동 예인 음탐기는 적정 심도에서 바른 자세로 예인 되어야 한다. 본 연구에서는 능동 예인 음탐기의 꼬리 날개 형상이 예인 자세 및 예인 안정성에 미치는 영향을 확인하기 위하여 축소 모형 실험 2회 및 해상 실험 1회를 수행하고 그 결과를 분석하였다. 축소 모형 실험은 선형 수조에서 꼬리 날개 형상에 따른 속력 별 예인 거동을 측정하였으며, 축소 모형 실험에 활용된 꼬리 날개 형상은 I 형 꼬리 날개 1개와 Y 형 꼬리 날개 4개로 총 2종 5개에 대하여 실험을 수행하였다. 1차 축소 모형 실험에서는 Y형 꼬리 날개가 I 형 꼬리 날개 대비 예인 자세 및 예인 안정성이 우수함을 확인하였다. 2차 축소 모형 실험에서는 Y형 꼬리 날개를 기본으로 수직 꼬리 날개 높이 증가, 하부 수평 꼬리 날개 경사각 적용 형상에 대하여 속력 별 거동 특성을 확인하였으며, 하부 수평 꼬리 날개 경사각 적용 형상이 가장 우수한 성능을 나타내었다. 축소 모형 실험 결과를 검증하기 위해 실물 모형을 제작하여 해상 실험을 수행하였으며, 축소 모형 실험 결과와 유사함을 확인하였다.

• 대한수학회보
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• 제40권4호
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• pp.663-669
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• 2003

This paper investigates the tail asymptotic behavior of the severity of ruin (the deficit at ruin) in the renewal model. Under the assumption that the tail probability of the claimsize is dominatedly varying, a uniform asymptotic formula for the tail probability of the deficit at ruin is obtained.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2007년도 춘계학술대회B
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• pp.2868-2872
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• 2007

In this study, a passive control using a boat-tail device is conducted for a three-dimensional car model in ground proximity. We consider various boat-tails and investigate the mechanism of drag reduction by them. By varying the length and slant angle of boat-tail, we obtain drag reductions up to 40%. From the oil-surface flow visualization and hot-wire measurement, the drag reduction by the boat-tail is characterized by the shear-layer instability and reattachment on the boat-tail, forming a small separation bubble at the upstream part of boat-tail surface, resulting in the delay of main separation and drag reduction. At high slant angles, the flow fully separates and drag is nearly same as that of no control.

• 전자공학회논문지A
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• 제32A권3호
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• pp.100-109
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• 1995

A new Hydrodynamic model for the high energy tail electrons(Tail Electron Hydrodynamic Model : TEHD) is developed using the moment method. The Monte Carlo method is applied to a $n^{+}-n^{-}-n^{+}$ device to calibrate the TEHD equations. the discretization method and numerical procedures are explained. New models for the impact ionization and injection into the gate oxide using the tail electron density are proposed. The simulated results of the impact ionization rate for a $n^{+}-n^{-}-n^{+}$ device and MOSFET devices, and the gate injection experiment are shown to give good agreement with the Monte Carlo simulation and the measurements.

• Journal of the Korean Data and Information Science Society
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• 제17권4호
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• pp.1405-1412
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• 2006

We shall derive the UMVUE of the tail probability in Poisson, Binomial, and negative Binomial distributions, and compare means squared errors of the UMVUE and the MLE of the tail probability in each case.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1991년도 한국자동제어학술회의논문집(국내학술편); KOEX, Seoul; 22-24 Oct. 1991
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• pp.889-893
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• 1991

This paper describe the mathematical model of helicopter rotor, which is suitable for the calculation of trim condition to develop the stability and control. The mathematical model is a nonlinear, total force and moment model of a single main rotor helicopter. The effects of fuselage, tail rotor, horizontal tail, and vertical tail are included. The phase angle and stick displacement are obtained and compared at the trim condition.

• 천문학회보
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• 제43권1호
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• pp.72.3-72.3
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• 2018

Since there are two-different observational constraints for the lunar exosphere data, it is interesting to find the best exospheric model that can account for the observed characteristics of the lunar coma and tail simultaneously (Lee & Kim, 2017).The characteristics of the lunar exosphere can be constrained by comparing simulated models with observational data of the coma and tail. In this work, considering effects of triple sodium sources (two dayside sources: a low- and a high-velocity component; and an Isotropic source component), we present time-dependent simulations showing initial conditions around the lunar coma and the final stage of the lunar tail. Based on an updated 3-D lunar exosphere model (Lee & Kim, 2017), we are presenting the simulated images of the lunar sodium coma and its correlation with lunar tail's physical parameters.

• 동력기계공학회지
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• 제19권4호
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• pp.24-29
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• 2015

This paper designs a looper-tension controller for strip top-tail parts in hot strip finishing mills. A three-degree linear model of the looper-tension system is derived by a Taylor's linearization method, where the actuator's dynamics are ignored because of their fast responses. A feedforward shaping controller for the strip top part and a feedforward model reference controller for the strip tail part are respectively designed, they are combined with an ILQ(Inverse Linear Quadratic optimal control) feedback controller for the strip middle part. It is shown from by a computer simulation that the proposed controller is very effective to the strip top-tail parts including the middle part.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2000년도 제15차 학술회의논문집
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• pp.2-2
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• 2000

This paper presents an adaptive control against uncertainties in tail-controlled STT (skid-to-Turn) missiles. First, we derive an analytic uncertainty model from a parametricaffine missile model developed by the authors. Based on this analytic model, an adaptive feedbacklinearizing control law accompanied by a sliding model control law is proposed. We provide analyses of stability and output tracking performance of the overall adaptive missile system. The performance and validity of the proposed adaptive control scheme is demonstrated by simulation.

• 상하수도학회지
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• 제27권2호
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• pp.177-184
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• 2013

This study analyzed the hydraulic characteristics of a venturi flume with a circular cone using a 3-D numerical model which uses RANS(Reynolds-Averaged Navier-Stokes Equation) as the governing equation. The venturi flume with the circular cone efficiently measures the discharge in the low-flow to high-flow range and offers the advantage of accurate discharge measurements in the case of a low flow. With no influence of the tail-water depth, the stage-discharge relationship and the flow behaviors were analyzed to verify the numerical simulation results. Additionally, this study reviewed the effect of the tail-water depth on the flow. The stage-discharge relationship resulting from a numerical simulation in the absence of an effect by the tail-water depth showed a maximum margin of error of 4 % in comparison to the result of a hydraulic experiment. The simulation results reproduced the overall flow behaviors observed in the hydraulic experiment well. The flow starts to become influenced by the tail-water depth when the ratio of the tail-water depth to the total head exceeds approximately 0.7. As the ratio increases, the effect on the flow tends to grow dramatically. As shown in this study, a numerical simulation is effective for identifying the stage-discharge relationship of a venturi flume with various types of venturi bodies, including a venturi flume with a circular cone.