• Journal of Electrical Engineering and Technology
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• 제8권5호
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• pp.1221-1226
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• 2013

In this paper, the equivalent circuit for the efficiency calculation by precise estimation of the linkage flux, inductance and iron loss resistance was calculated accurately. In addition, the driving characteristics according to the current phase angle are analyzed and the maximum efficiency point is calculated. And then, analyzed and experimental values of the efficiency were compared. So, causes of error were expected to be vibration and noise by harmonic distortion of the voltage and current, and mechanical loss of dynamometer. In addition, the driving characteristics according to the current phase angle are analyzed and the maximum efficiency point is calculated.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2003년도 ICCAS
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• pp.1211-1215
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• 2003

Accurate mathematical models of spacecraft components are an essential of spacecraft attitude control system design, analysis and simulation. Gyro is one of the most important spacecraft components used for attitude propagation and control. Gyro errors may seriously degrade the accuracy of the calculated spacecraft angular rate and of attitude estimates due to inherent drift and bias errors. In order to validate this model, nominal case simulation has been performed and compared for the low range mode and high range mode, respectively. In this paper, a mathematical model of gyro containing the relationships for predicting spacecraft angular rate and disturbances is proposed.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2006년도 추계학술대회논문집
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• pp.531-536
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• 2006

In four cylinder engine, the second order inertia force occurs due to the reciprocating parts of the cylinder. Because the magnitude of the inertia force is proportional to a square of the angular velocity of crank shaft, engine gets suffered from vibration excited by unbalanced inertia force in high speed. This vibration excited by the unbalanced inertia force can be canceled by applying a balance shaft. Balance shaft has one or more unbalance mass and rotates twice quickly than the crank shaft. In this paper, an unbalanced force caused by the rotating of unbalance mass of balance shafts was calculated. The directional equivalent stiffness and damping coefficients of the journal bearing of balance shafts was calculated. Equations of rotational vibration modes were derived using directional stiffness and damping coefficients. The dynamic stability of balance shafts was analyzed and evaluated for two type models using the equivalent stiffness and damping coefficients. An efficient procedure to he able to evaluate dynamic stability and design optimal balance shaft was proposed.

• 한국음향학회지
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• 제26권7호
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• pp.353-360
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• 2007

급속한 도시화와 인구밀도의 증가로 도시의 주거지역은 점점 고층화, 고밀화 되어가는 추세이다. 그로 인하여 인구의 공간적 집중으로 발생하는 교통수요를 감당하기 위하여 도시내부 도로는 점차 증가하였으며, 주거지역은 도로에 바로 인접하여 개발되고 있다. 이에 따라 도로에 연접한 주거지역의 도로교통소음 문제를 해결하기 위하여 방음벽에 의존하는 실정이었으나, 경관저해, 소음차단성능저해 등 다양한 역기능이 발생하고 있다. 본 연구에서는 방음벽의 역기능을 해소하고 바람직한 개선방안을 제시하기 위하여 도로변에 위치한 주거지역의 현장측정을 통하여 시뮬레이션의 정확도를 검증한 후 방음시설별 성능평가 및 전체 지역을 분석하였다. 그리고 개선방안으로 건축물의 배치형태 변화와 도로단으로부터의 이격거리를 20m 증가시켰다. 분석 결과 도로변과 평행한 공동주택의 피해가 가장 심각하였고, 시설별 분석에서는 방음벽의 성능이 우수하였으며, 건물 배치형태는 $30^{\circ}$ 배치가 우수하며, 이격거리가 증가함에 따라 교통소음이 감소하는 것으로 나타났다.

• 한국소음진동공학회논문집
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• 제12권11호
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• pp.873-881
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• 2002

The fluid induced vibration (FIV) phenomena of an equivalent airfoil system of MAV have been investigated in low Reynolds number flow region. Unsteady flows with viscosity are computed using two-dimensional incompressible Navier-Stokes equations. The present fluid/structure interaction analysis is based on one of the most accurate computational approach with computational fluid dynamics (CFD) and computational structural dynamics (CSD) techniques. The highly nonlinear fluid/structure interaction phenomena due to severe flow separations have been analyzed for the low Reynolds region that has a dominancy of flow viscosity. The effects of Reynolds number and initial angle of attack on the fluid/structure coupled vibration instability are shown and the qualitative trend of FIV phenomenon is investigated.

• International Journal of Aeronautical and Space Sciences
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• 제18권4호
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• pp.688-696
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• 2017

This paper presents an integrated roll-pitch-yaw autopilot using an equivalent based sliding mode control for skid-to-turn nonlinear time-varying missile system with lumped disturbances in its six-equations of motion. The considered missile model are developed to integrate the model uncertainties, external disturbances, and parameters perturbation as lumped disturbances. Moreover, it considers the coupling effect between channels, the variation of missile velocity and parameters, and the aerodynamics nonlinearity. The presented approach is employed to achieve a good tracking performance with robustness in all missile channels simultaneously during the entire flight envelope without demand of accurate modeling or output derivative to avoid the noise existence in the real missile system. The proposed autopilot consisting of a two-loop structure, controls pitch and yaw accelerations, and stabilizes the roll angle simultaneously. The Closed loop stability is studied. Numerical simulation is provided to evaluate performance of the suggested autopilot and to compare it with an existing autopilot in the literature concerning the robustness against the lumped disturbances, and the aforesaid considerations. Finally, the proposed autopilot is integrated in a six degree of freedom flight simulation model to evaluate it with several target scenarios, and the results are shown.

• 소음진동
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• 제9권5호
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• pp.1019-1028
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• 1999

Free vibration characteristics of cantilevered laminated composite beams with a transverse non0propagating open carck are investigated. In the present analysis a special ply-angle distribution referred to as asymmetric stiffness configuration inducing the elastic coupling between chord-wise bending and extension is considered. The open crack is modelled as an equivalent rotational spring whose spring constant is calculated on the basis of fracture mechanics of composite material structures. Governing equations of a composite beam with a open crack are derived via Hamilton's Principle and Timoshenko beam theory encompassing transverse shear and rotary inertia effect. the effects of various parameters such as the ply angle, fiber volume fraction, crack depth, crack position and transverse shear on the free vibration characteristics of the beam with a crack is highlighted. The numerical results show that the natural frequencies obtained from Timoshenko beam theory are always lower than those from Euler beam theory. The presence of intrinsic cracks in anisotropic composite beams modifies the flexibility and in turn free vibration characteristics of the structures. It is revealed that non-destructive crack detection is possible by analyzing the free vibration responses of a cracked beam.

• ETRI Journal
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• 제22권1호
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• pp.12-19
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• 2000

Wireless communication systems using airship have been proposed in worldwide. The airship will be located at the stratosphere about $20{\sim}23\;km$ above the sea level. The position of airship will vary within the station keeping range with time due to the drag of the wind in the stratosphere. When the earth station antenna has a high gain without the tracking function, the antenna performance may be degraded by a small variation of the airship. This means that variation of airship location could result in serious degradation of the system performance. In this paper, degradation in earth station's Equivalent Isotropic Radiated Power (EIRP) and Gain to noise Temperature ratio (G/T) due to the stratospheric platform movements has been derived by calculating the deviation angle of the main beam directions between the earth station and the platform antenna. In this case, the antenna of the earth station has been assumed circular and/or patch array antennas.

• 항공우주기술
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• 제11권2호
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• pp.87-95
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• 2012

본 기술논문에서는 고기동 고정밀 위성의 별 추적기 초기 점검 원격측정 데이터가 분석되었다. 최근에 발사된 위성은 고기동 고정밀 위성이므로 고도의 요구조건을 만족하기 위해 광학계, 전자부, 배플이 분리된 형태로 광학계 부분의 온도를 20 degC 근처로 유지하면서 저주파 오차 성능을 향상 시킨 프랑스 SODERN사의 SED36을 사용하였다. 본 논문에서는 위성으로부터 내려 받은 원격측정 데이터의 처리를 통해 초기 점검 상태, 요구 조건 만족 여부, 이상 현상 및 주요 임무 기동에서의 별 추적기 잡음각 성능 분석 결과를 제시하였다.

• 해양환경안전학회지
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• 제29권4호
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• pp.389-394
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• 2023

근래 산업은 기계 자동화로 변화하고 있는 추세이며, 선박도 센서를 통해 기기 정보를 디지털 정보로 얻는다. 하지만 선박은 기기상태 점검을 위해 선원들이 정해진 시간마다 기관실을 순찰하며 기기들의 정보를 아날로그 게이지를 통해 확인하는데, 이는 순찰 중에 선원에게 발생할 수 있는 모든 안전 위험은 물론 시간과 기회비용 또한 소모된다. 자율이동로봇을 이용한 기관실 순찰 방법은 선원의 안전 위험은 물론 시간과 기회비용도 소모되지 않기 때문에 해결책으로 활발히 연구 중이다. 자율이동로봇을 이용한 아날로그 게이지 판독은 로봇이 게이지를 인식하기 위한 디지털화가 필요하다. 이를 위해 본 연구에서는 이미지 처리를 이용하였다. 아날로그 게이지 이미지는 이미지 전처리를 통해 노이즈 제거 및 특징을 부각 시켰다. 이미지 전처리를 완료한 이미지는 이미지 처리를 통해 아날로그 게이지의 중심점, 지침점, 최소값 및 최대값을 검출하였다. 이 점들을 연결한 직선을 통해 최소값부터 최대값까지의 각도 및 최소값부터 지침점까지의 각도를 획득하였다. 각도는 수식을 통해 현재 아날로그 게이지가 나타내고 있는 값을 디지털화하여 나타내었다. 실험을 통해 이미지 처리를 통한 아날로그 게이지의 디지털화가 잘되어 게이지의 현재 지시값을 근사하게 나타냄을 확인할 수 있었다. 본 알고리즘을 순찰로봇에 적용한다면 기관실 순찰을 위한 선원의 안전 위험 및 시간과 기회비용까지 보전 할 수 있을 것으로 사료된다.