• Proceedings of the Korean Institute of IIIuminating and Electrical Installation Engineers Conference
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• 2005.05a
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• pp.265-269
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• 2005

본 논문에서는 최대 견인력 제어를 위해서 최소 차원 부하 토크 외란 관측기를 이용하여 점착력 계수를 추정하고 추정한 점착력 계수의 미분치를 PI 토크 제어하는 Anti-slip제어를 제안한다. 최소차원 부하 토크 외란 관측기는 회전자의 위치 정보와 토크 전류의 정보를 이용하여 부하 외란토크를 추정하고, 부하 외란 토크에 철도차량 상수를 이용하여 점착력 계수를 추정한다. 또한 부하토크외란 관측기는 구조가 간단하며, 시스템의 외란 및 각종 제어이득, 시스템의 상수 변화에 대해서도 견실한 견인력 제어 특성을 가지고 있다. 이와 같은 시스템의 모델링과 전동기 토크에 대한 회전자의 위치 정보를 이용하여 최소차원 부하 토크 외란 관측기의 상태변수인 점착력 계수를 추정하고, 추정한 점착력 계수의 미분치를 PI토크 Anti-Slip제어하여, 최대 견인력 제어가 되도록 하였다.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 2004.05a
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• pp.80-80
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• 2004

베어링리스 모터는 기존의 전동기와 자기베어링을 결합한 기술로 축 길이가 줄어들어 회전 속도를 높일 수 있으며 소형화가 가능하다는 장점이 있다(Fig. 1). 베어링리스 모터를 설계하기 위한 첫 번째 단계는 베어링리스 모터의 수학적 모델을 도출하는 것인데, 기존의 연구에서 부상용 전류와 부상력의 관계는 잘 정립되어 있다. 그러나, 회전자의 변위에 따른 부상력의 변화는 명확히 정의되어 있지 안다. 본 논문에서는 분산 자기 회로 이론을 이용하여 회전자의 움직임에 따른 부상력의 변화를 스프링계수의 형태로 모델링하였다.(중략)

• Journal of Korean Society of Steel Construction
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• v.15 no.6 s.67
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• pp.693-700
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• 2003

An evaluation method for flutter derivatives is proposed, using indicial functions of structural members produced by Computational Fluid Dynamics (CFD). Flutter derivatives are obtained by Fourier integration of indicial functions. Instead of direct simulation of oscillating objects, only the calculation of time-dependent lift and moment variations of fixed objects with constant attack angle are necessary.The Finite Element Method (FEM) is developed as a tool for the numerical method. For two rectangular sections having different aspect ratios, the numerical analysis and wind tunnel test are carried out to inspect the adequacy of this study. The results proved to be good, and they could be used for a preliminary design.

• Proceedings of the KIEE Conference
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• 2002.07b
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• pp.935-938
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• 2002

본 논문은 회전자에 영구자석을 사용한 2극 단상 브러시리스 모타에서의 기동토오크 특성에 관한 연구결과를 소개함에 목적이 있다. 본 논문에서와 같은 구조의 모타에서의 토오크는 전자기력에 의한 기동력과 코깅 토오크에 의한 영향력 두가지로 구분다. 본 논문에서는 기동토오크의 이론적 구조식을 유도하고, 문리 적 운동방정식과 결합하여 기동시 나타나는 특성을 나타내었다. 본 논문의 목적은 보다 보편적인 기동토오크에 의한 회전자의 운동을 구명하고자 함인데, 이 목적을 위하여 일반적 전원으로 사용하는 연속 직류전류가 아니라, 비연속적이고 정현파 형태의 일펄스 반파 전류를 전원으로 사용하였다. 이때 나타나는 임펄스 응답특성은, 전류를 흘렸을 때, 대부분의 경우 모타의 회전자는 전류의 주기와 다른 주기를 가지고 반회전하였다. 모타 회전자의 반전주기는 입력전압, 영구자석의 자화의 강도, 그리고 관성계수 및 마찰 계수와 같은 기계적 상수에 의해 영향을 받는 것을 알수 있는데, 반전주기 속도가 모타의 동기속도와 적절하지 않는 경우, 모타의 회전은 이루어 지지 않거나 심한 흔들림(CHATTERINC)의 현상이 나타남을 발견하였다. 이러한 결과를 바탕으로 모타의 회전자를 동기속도로 구동을 하도록 하기위한 조건을 구하였다.

• Journal of the Korean Geotechnical Society
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• v.25 no.1
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• pp.55-64
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• 2009

One of the important use of piles is to furnish lateral support and nowadays it is getting highlighted due to the increase of skyscrapers, transmission towers, wind turbines, and other lateral action dependent structures. After Broms (1964), many researchers have suggested methods for estimating lateral capacity of pile. But each method assumes different earth pressure distribution and lateral earth pressure coefficient causing confusion on the part of pile designers. Lateral earth pressure, essential in lateral capacity estimation, is influenced by pile's rotational behavior under lateral load. Prasad and Chari (1999) assumed the rotation point of pile and suggested an equation of ultimate lateral load capacity. In this study, we investigate the depth of rotation point in both homogeneous soil and multi layered soil, and compare with the estimation value by previous research. Test results show that measured rotation point and estimated value by Prasad and Chari's equation show good agreement and multi layered condition affects the location of rotation point to be changed.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.18 no.8
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• pp.41-47
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• 2017

With the introduction of new technologies, ground weapons have led to the development of artificial intelligence and the attention of major developed countries. In this study, CFD was performed through the BLU-103 model to obtain aerodynamic data for aircraft that are subjected to rotational motion. To simulate the steady-state of a rotating body, the body was fixed and the principle of rotating the body by rotating the surrounding air was used. In order to examine the aerodynamic feasibility of the rotating aircraft, the analysis was carried out at intervals of $30^{\circ}$ angle from $0^{\circ}$ to $90^{\circ}$ for the simple shape and the side slip angle. It was confirmed that the drag coefficient for the simple model satisfies the quantitative results of 1.0 ~ 1.2 through CD presented in "Drag Book". The aerodynamic data was constructed by applying the valid input verified through the simple type analysis conditions to the actual shape, and the tendency was analyzed. The analysis confirmed that CX, CZ and CY increase not only in the simple model but also in the rotation of the actual model. Especially, the influence of CZ was judged to have contributed to the flight.

• Journal of the Earthquake Engineering Society of Korea
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• v.11 no.2 s.54
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• pp.11-17
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• 2007

In current seismic design practice, the response modification factor (R-factor) is used as a factor to reduce the elastic base shear demand to the design force level. As is well-known, the R-factor is a committee-consensus factor and, as such, highly qualitative and empirical. The relationship between the R-factor and the connection rotation capacity available in a particular structural system has remained a missing link. In this paper, a rational procedure to evaluate the R-factor is proposed. To this end, the relationship between the available connection rotation capacity and the R-factor is defined and quantified using nonlinear pushover analysis. An RRS steel frame designed according to IBC 2000 was used to illustrate and verify the proposed procedure. Nonlinear time history analysis results indicated that the R-factor definition proposed in this study is generally conservative from design perspective.

• Journal of Navigation and Port Research
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• v.41 no.6
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• pp.389-394
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• 2017

In this paper, the captive model test of a submarine using the RA test was carried out in a square basin. The target model submarine consisted of four types varying according to the position of conning tower and control planes. Hydrodynamic derivatives were acquired by multi-regression analysis. As a result, horizontal dynamic stability indexes of the four types presented positive values and satisfied dynamic stability requirements. In addition, the stability index of type 1 and type 4 - each with the same cruciform configuration of the aft planes - scored within the acceptable range of motion stability.

• Journal of Dental Rehabilitation and Applied Science
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• v.25 no.2
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• pp.157-169
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• 2009

The aim of this study was to evaluate effect of implant abutment screw coating treatment on joint stability, investigating mechanical properties of these. For this study used $ExFeel^{(R)}$ external hexed implant system and $15mm{\times}1mm$ discs. Experimental group was $1{\mu}m$ TiN, TiCN, TiC coated abutment screws and discs. To know mechanical property, i evaluated adhesion strength, surface hardness, using disc, corrosion test using screw. The results were as follows : rotation angle of coated screws increased than that of non-coated screw because of lower friction coefficient, especially TiC coated screw group had the largest value, but removal torque decreased in all coated screws (p<0.05). Torque loss before and after fatigue test was the smallest in TiC-coated screws, and the largest in non-coated screws (p<0.05), and there was no statistically significant difference between dry condition and wet condition of screws because of higher surface hardness and lower friction coefficient. From the above results, TiN, TiCN, TiC coating group had high abrasion resistance, especially TiC coated group which had low torque-consuming, high rotation angle as low friction coefficient will be considered to influence on implant abutment screw joint stability positively.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.9
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• pp.97-103
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• 2006

This paper described the design and performance evaluation of fiber optic gyro using digital closed-loop processing. For the feedback to null the gyro input rate, digital serrodyne modulation was employed, and for scale factor stabilization, the control circuits of modulation amplitude and optical power are implemented. Performance tests show that prototype fiber optic gyro has bias stability of 0.34 deg/hr, scale factor non-lineality of about 100ppm, and maximum measurement range of ${\pm}500$ deg/sec.