• Wind and Structures
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• 제16권6호
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• pp.561-577
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• 2013

Rational Functions are used to express the self-excited aerodynamic forces acting on a flexible structure for use in time-domain flutter analysis. The Rational Function Approximation (RFA) approach involves obtaining of these Rational Functions from the frequency-dependent flutter derivatives by using an approximation. In the past, an algorithm was developed to directly extract these Rational Functions from wind tunnel section model tests in free vibration. In this paper, an algorithm is presented for direct extraction of these Rational Functions from section model tests in forced vibration. The motivation for using forced-vibration method came from the potential use of these Rational Functions to predict aerodynamic loads and response of flexible structures at high wind speeds and in turbulent wind environment. Numerical tests were performed to verify the robustness and performance of the algorithm under different noise levels that are expected in wind tunnel data. Wind tunnel tests in one degree-of-freedom (vertical/torsional) forced vibration were performed on a streamlined bridge deck section model whose Rational Functions were compared with those obtained by free vibration for the same model.

• International Journal of Naval Architecture and Ocean Engineering
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• 제13권1호
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• pp.746-757
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• 2021

To investigate the mechanism of friction-induced vibration and noise of ship water lubricated stern bearings, a two-degree-of-freedom (2-DOF) nonlinear self-excited vibration model is established. The novelty of this work lies in the detailed analysis of influence of different parameters on the stability and nonlinear vibration characteristics of the system, which provides a theoretical basis for the various friction vibration and noise phenomenon and has a very important directive meaning for low noise design of water lubricated stern bearings. The results reveal that the change of any parameter, such as rotating speed of shaft, contact pressure, friction coefficient, system damping and stiffness, has an important influence on the stability and nonlinear response of the system. The vibration amplitudes of the system increase as (a) rotating speed of shaft, contact pressure, and the ratio of static friction coefficient to dynamic friction coefficient increase and (b) the transmission damping between motor and shaft decreases. The frequency spectrum of the system is modulated by the first mode natural frequency, which is continuous multi-harmonics of the first mode natural frequency. The response of the system presents a quasi-periodic motion.

• Wind and Structures
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• 제37권1호
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• pp.39-56
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• 2023

To ensure the wind stability of a long-span suspension bridge during deck erection under skew wind, based on the aerostatic and self-excited aerodynamic force models under skew wind, a computational approach of refined flutter analysis for long-span bridges under skew wind is firstly established, in which the effects of structural nonlinearity, the static wind action and full-mode coupling etc are fully considered, and the corresponding computational procedure is programmed. By taking the Runyang suspension bridge over the Yangtze River as example, the flutter stability of the bridge in completion under skew wind is then analyzed with the aerodynamic parameters of a similar bridge deck measured from the sectional model wind tunnel test under skew wind. Finally, through simulating the girder segments erected symmetrically from the midspan to towers, from the towers to midspan and simultaneously from the towers and midspan to the quarter points, respectively, the evolutions of flutter stability limits during the deck erection under skew wind are investigated numerically, the favorable aerodynamically deck erection sequence is proposed, and the influences of skew wind and static wind effect on the flutter stability of suspension bridge under construction are ascertained.

• 한국결정성장학회지
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• 제26권1호
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• pp.35-40
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• 2016

엔드밀링 공정은 3차원 형상의 다양한 부품, 제품, 금형을 가공하는데 널리 사용되고 있는 핵심 가공 프로세스이다. 가공정밀도 요구수준과 가공형상 난이도 수준이 날로 높아짐에 따라 가공정밀도 요구특성의 지속적인 향상에도 불구하고, 공작기계와 절삭공구를 이용한 절삭가공공정에서의 채터 진동은 아직도 개선의 여지가 많이 남아있다. 특히, 더욱 고속화, 고정밀화 되고 있는 가공현장에서 채터진동의 효과적인 감소대책에 대한 다양한 연구가 필요하다. 본 연구에서는 이러한 문제점을 해결하기 위해 엔드밀링공정에서 발생하기 쉬운 채터진동의 안정성을 향상시키기 위해 절삭모델에 근거한 채터진동 안정성 시뮬레이션 방법론을 연구하고, 엔드밀링 절삭조건이 채터진동에 미치는 영향을 다양한 조건하에서 예측하고자 하였다. 본 연구결과를 더욱 발전시켜 채터진동과의 상관성을 연구하고, 향후 채터진동 저감형 가공시스템 개발을 위한 근간 기술자료로 활용코자 한다.

• 전력전자학회논문지
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• 제21권5호
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• pp.396-403
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• 2016

Usually, large-sized buses and trucks have a very high load. In addition, frequent braking during downhill or long-distance driving, causes the conventional method using the brake friction to have a problem in safety because of brake fade and brake burst phenomenon. Auxiliary brakes dividing the braking load is essential. Hence, environment-friendly auxiliary brakes, such as contactless brake rather than the engine auxiliary brake system are needed. A study aimed at improving the energy efficiency by recharging electric energy with changing mechanical to electrical energy that occurs when braking is actively in progress. In this paper, the voltage control method is utilized to recover the electric energy generated in the electromagnetic retarder instead of the eddy current. To regenerate the braking energy into the electrical energy, the resonant L-C circuit is configured in the retarder. The voltage generated in the retarder is simply modeled as a transformer. However, retarder voltage control in this paper is simulated by modeling the induction generator because this induction generator modeling is more practical than transformer modeling. The changes in the voltage of the resonance circuit, which depends on the switch pulse duration of the control device, were analyzed. A PI controller algorithm to control this voltage is proposed. The feasibility of modeling retarder and voltage controller are shown by using MATLAB Simulink in this paper.

• 천문학회지
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• 제43권2호
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• pp.25-39
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• 2010

We perform kinetic simulations of diffusive shock acceleration (DSA) in Type Ia supernova remnants (SNRs) expanding into a uniform interstellar medium (ISM). Bohm-like diffusion due to self-excited $Alfv\acute{e}n$ waves is assumed, and simple models for $Alfv\acute{e}nic$ drift and dissipation are adopted. Phenomenological models for thermal leakage injection are considered as well. We find that the preshock gas temperature is the primary parameter that governs the cosmic ray (CR) acceleration efficiency and energy spectrum, while the CR injection rate is a secondary parameter. For SNRs in the warm ISM of $T_0\lesssim10^5K$, if the injection fraction is $\xi\gtrsim10^{-4}K$, the DSA is efficient enough to convert more than 20% of the SN explosion energy into CRs and the accelerated CR spectrum exhibits a concave curvature flattening to $E^{-1.6}$, which is characteristic of CR modified shocks. Such a flat source spectrum near the knee energy, however, may not be reconciled with the CR spectrum observed at Earth. On the other hand, SNRs in the hot ISM of$T_{0}\approx10^{6}K$ with a small injection fraction, $\xi$<$10^{-4}$, are inefficient accelerators with less than 10% of the explosion energy getting converted to CRs. Also the shock structure is almost test-particle like and the ensuing CR spectrum can be steeper than $E^{-2}$. With amplified magnetic field strength of order of $30{\mu}G$ $Alfv\acute{e}n$ waves generated by the streaming instability may drift upstream fast enough to make the modified test-particle power-law as steep as $E^{-2.3}$, which is more consistent with the observed CR spectrum.

• 한국항공우주학회지
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• 제38권10호
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• pp.973-978
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• 2010

본 논문에서는 유격을 고려한 항공기 전방 착륙 장치의 쉬미 현상을 연구하였다. 쉬미는 항공기의 이착륙 시 랜딩기어가 주행도중 측방향과 조향방향으로 진동에 놓이는 현상이다. 이 현상은 스트럿의 낮은 강성, 랜딩기어 내부의 마찰과 유격, 휠의 불균형이나 마모된 부품 등으로 인해 발생하며, 항공기의 안정성을 저하시킨다. 유격은 비선형 요소이기 때문에 기술 함수로 선형화 하여 주파수 영역에서 안정성해석을 수행하였고, 4차 Runge - Kutta를 이용하여 시간영역에서 안정성해석을 수행하였다. 본 연구에서는 수치적인 해석법을 통해 쉬미현상의 선형 동특성과 비선형 동특성을 조사하였다. 유격을 고려한 비선형 수치 해석결과, 선형 임계속도보다 낮은 속도에서 제한주기진동이 발생하는 등, 유격으로 인해 쉬미 안정성이 저감되는 결과를 관찰하였다.

• 한국소음진동공학회논문집
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• 제22권8호
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• pp.748-755
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• 2012

Friction causes self-excited vibration, stick-slip vibration and any other friction-induced phenomena. That kinds of vibrations cause chatter and squeal. In order to predict such vibrations accurately, employing an accurate friction model is very important because a dynamic behavior of a system with friction is dominantly governed by a friction model. A Coulomb friction model is the most widely known model. Coulomb friction model is useful model to obtain analytical solutions of the system with friction and the model gives relatively good simulation result. However, defining a friction force at a stick state in simulation is hard because of the characteristic itself and a Coulomb friction model is discontinuous function between a static and a dynamic friction coefficient. Therefore, applying the Coulomb friction model to a simulation is not appropriate. In order to resolve these problems, an approximated Coulomb friction model was developed using simple and continuous function. However, an approximated Coulomb friction model cannot realize stick. Therefore, an approximated Coulomb friction model cannot describe friction phenomena accurately. In order to analyze a friction phenomenon accurately, a friction model for a simulation was proposed in this paper. A proposed friction model realizes stick and gives reasonably good results compared to results obtained by the simulation employing an approximated Coulomb friction model. Accuracy of a proposed friction model was verified by comparing experimental results.

• 조명전기설비학회논문지
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• 제24권4호
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• pp.166-176
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• 2010

태양전지의 출력 특성은 비선형이고 온도와 일사량에 많은 영향을 받는다. 최대전력점 추종 제어는 태양광 발전의 출력을 최대로 하기 위해 사용되는 제어기법이다. 태양광발전 시스템의 출력 및 효율을 증가 시키기 위해 더욱 우수한 최대전력점 추종 제어기법이 필요하다. 본 논문에서는 태양광 발전 시스템의 효율을 개선하기 위해 일사량을 고려한 새로운 최대전력점 추종 제어 알고리즘을 제시한다. 제시한 알고리즘은 종래의 P&O방법과 CV 방법을 혼합한 것이며, PSIM 시뮬레이터를 통하여 종래의 MPPT 알고리즘과 다양한 일사량 조건에서 성능시험을 비교하였다. 제시한 알고리즘은 종래의 알고리즘에 비해 출력의 자려진동없이 다양한 일사량에서 우수한 성능을 나타냈다. 이로서 본 논문에서 제시한 HB 방법의 최대전력점 추종 제어 알고리즘의 타당성을 입증하였다.

• 한국항공우주학회지
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• 제39권7호
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• pp.605-611
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• 2011

쉬미는 항공기의 이착륙 시 랜딩기어가 주행도중 측방향 및 조향방향의 진동이 발생하는 현상이다. 쉬미 현상은 스트럿의 낮은 강성, 랜딩기어 내부의 유격, 휠의 불균형이나 마모된 부품 등으로 인해 발생하며, 항공기의 안정성을 저하시킨다. 본 연구는 소형항공기의 쉬미 안정성 검토를 위해 수행되었다. 수치해석을 위하여 소형항공기의 전방 착륙장치를 선형시스템으로 모델링하고 상태방정식을 수립하였다. 근궤적 기법을 이용한 주파수 영역 해석과 4차 Runge-Kutta 방법을 이용한 시간영역 해석을 통해 쉬미 현상을 예측하였고 주요 변수의 설계범위를 검토하였다. 현 착륙장치는 와셔의 압축력을 이용하여 조향 방향 마찰을 가함으로써 쉬미현상을 저감하는 기법을 채택하고 있으므로 마찰을 기술함수를 이용하여 선형화시키고 상태방정식에 적용하여 해석을 수행함으로써 쉬미의 발생이 저감되는 결과를 확인하였다.