• 한국지반공학회지:지반
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• 제13권4호
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• pp.109-120
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• 1997

공용하중 상태에서 지반이 경험하는 변형률 크기는 0.1~1% 미만임이 밝혀지고 있다. 변형특성을 보다 엄밀히 평가하기 위하여는 미소변형률 영역에서의 신뢰성 있는 변형측정이 가능한 현장시험기기의 개발이 필요하다. 본 연구의 목적은 공내째하시험기(PMT)를 사용하여 지반의 미소변형률 전단탄성계수를 측정하는 것이다. 공내재하시험에서 시추공 설치에 따른 주위 지반의 교란효과를 제거하기 위하여 초기 하중재하단계가 아닌 역재하-재재하 단계에서 PMT 주위지 반의 응력상태 및 변형률 크기를 고려하여 미소변형률 잔단탄성계수를 결정하였다. 실내 토조에서 성형한 모래시료와 화강풍화토 현장지반에서 시험을 수행하였으며,시험결과로부터 본 연구 에서 사용한 PMT시험은 변형률 크기 10-2%~0.5% 범위에서 신뢰성 있는 전단탄성계수 측정이 가능하였다. 또한 변형률 크기를 고려하여 다른 실내외시험에서 결정된 전단탄성계수와 비교 하면 서로 잘일치하는 결과를 얻을 수 있었다.

• 대한환경공학회지
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• 제31권6호
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• pp.460-466
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• 2009

간이상수도 시스템에서 공급하는 식수는 일정한 잔류 약품(염소)량을 유지해야 하기 때문에 물과 약품의 혼합방법은 매우 중요하다. 본 연구에서는 물과 약품의 혼합방법을 최적화하기 위하여, 4가지 모델에 대한 농도분포 및 혼합지수를 구하였다. 그중 2가지 모델에 대해서는 혼합효과가 높게 나타났다. 하나는 지하수 공급 파이프 중앙에 약품을 공급하는 모델이고, 또 다른 하나는 약품공급 파이프 하류에 반원형태의 블록을 설치한 모델이다. 이러한 모델들은 유동의 확산 및 교란을 야기시켜 혼합효과를 증가시키는 결과를 가져왔다. 이와 같은 수치해석 결과는 최적의 혼합효과를 얻기 위한 시스템을 설계하는데 도움이 될 것으로 기대된다.

• 한국군사과학기술학회지
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• 제11권2호
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• pp.116-124
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• 2008

Current paper investigates the dynamic behavior and stability of an infrared search and track subjected to external disturbance having gimbal structure with three rotating axes keeping constant angular velocity in the azimuth direction. Euler-Lagrange equation is applied to derive the coupled nonlinear dynamic equation of motion of infrared search and track and the characteristics of dynamic coupling are investigated. Two equilibrium points with small variations from the nonlinear coupling system are derived and the specific condition from which a coupled equation can be three independent equations is derived. Finally, to examine the stability of system, Lyapunov direct method was used and system stability and stability boundaries are investigated.

• 제어로봇시스템학회논문지
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• 제7권1호
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• pp.1155-1161
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• 2001

We propose an adaptive nonlinear control algorithm for high precision tracking and stabilization of LOS(Line-of-Sight). The friction parameters of the LOS gimbal are estimated by off-line evolutionary strategy and the friction is compensated by estimated friction compensator. Especially, as the nonlinear control input in a small tracking error zone is enlarged by the nonlinear function, the steady state error is significantly reduced. The proposed algorithm is a direct adaptive control method based on the Lyapunov stability theory, and its convergence is guaranteed under the limited modeling error or torque disturbance. The performance of the pro-posed algorithm is verified by computer simulation on the LOS gimbal model of a moving vehicle.

• International Journal of Aeronautical and Space Sciences
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• 제10권1호
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• pp.14-19
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• 2009

The typical aeroelastic analysis for a complex configuration such as a complete aircraft was done using the aerodynamic results of the wing and the structural modes of a complete aircraft; that is, the aerodynamics of a wing of a complete aircraft is assumed to be not much influenced by the body shape. Nevertheless, the body shape can cause a distortion of aerodynamic pressure on the wing surface and it is necessary to investigate the body effect in flutter analysis. In this reseasrch, MGM inverse design method is applied to include the body effect of a wing-body model which disturbs the pressure distribution on the wing surface.

• 한국조명전기설비학회:학술대회논문집
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• 한국조명전기설비학회 2005년도 춘계학술대회논문집
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• pp.372-377
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• 2005

EMC(Electromagnetic Compatibility) is the ability of an electronic device that operates properly in its intended electromagnetic environment and not be a source of pollution to that environment. The designer anticipates EMC problems at beginning of the process and finds remaining problems in early prototype stages, and tests the final prototypes for EMC as thoroughly as possible. This is a more cost-effective method. In this paper, it analyzes EMC problems that were appeared in actual measurement of electric power control device and presents reduction technique of these problems.

• 한국소음진동공학회논문집
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• 제19권10호
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• pp.1053-1061
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• 2009

The goal of this paper is to investigate the generation characteristics of the main impulsive noise sources generated by the supersonic flow discharging from a muzzle. For this, this paper investigates two fundamental mechanisms to sound generation in shocked flows: shock motion and shock deformation. Shock motion is modeled numerically by examining the interaction of a sound wave with a shock. The numerical approach is validated by comparison with results obtained by linear theory for a small disturbance case. Shock deformations are modeled numerically by examining the interaction of a vortex ring with a blast wave. A numerical approach of a dispersion-relation-preserving(DRP) scheme is used to investigate the sound generation and propagation by their interactions in near-field.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2001년도 ICCAS
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• pp.124.1-124
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• 2001

Control of pH neutralization process plays a very important role in some chemical process. Because of their high nonlinearity, frequent disturbance, and time-varying characteristics, it is difficult to control and estimate pH processes. For the adaptive control of pH processes, a lot of researchers have made an efforts in the modeling and control of pH processes. It is very difficult to obtain information of influent stream such as concentrations and dissociation constants and the titration curve equation is very complex. Therefore, several simple models, which hate small number of unknown parameters and estimate the titration curve, have been available, These models were considered here and were transformed into forms that can applied the linear least square method.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1991년도 한국자동제어학술회의논문집(국내학술편); KOEX, Seoul; 22-24 Oct. 1991
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• pp.197-202
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• 1991

Recently, an output feedback variable structure control scheme(OFVSCS) is proposed to remove the assumption of full state availability and to make the application of VSC scheme to the high order systems with unmeasurable state variables possible. In this paper, a design method of an output feedback variable structure control system (IOFVSCS) that guarantees the invariance of the sliding mode against process parameter variation and external disturbance is proposed. The IOFVSCS is composed of two components; dynamic switching surface driven by measured I/0 informations and switching control input generator driven by switching surface information and measured output, where the two components are constructed by adopting unknown vector modelling approach. The invariance condition for the IOFVSCS is proved to be the same as that of the conventional VSCS. Simulation results show that the IOFVSCS can be designed to have robust properties better than that of the conventional VSCS in spite that the IOFVSCS is driven by small amount of measured information.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2000년도 춘계학술대회논문집
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• pp.1198-1203
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• 2000

In this study, a nonlinear aeroelastic analysis system for the fighter wing with tip-store has been developed additionally in the transonic and supersonic flow region. The unsteady CFD code based on the transonic small disturbance theory has been incorporated to consider the numerical capability for the aerodynamic nonlinear effects. The coupled time-integration method is used to observe the detailed nonlinear aeroelastic responses for elastic wings in their flight. condition. A conservative wing-box model of a fighter wing with tip-store is modeled by MSC/PATRAN and the corresponding free vibration analysis has been performed by MSC/NASTRAN. The results of flutter analyses are presented in the subsonic, transonic and supersonic flow regime.