• 한국음향학회지
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• 제28권7호
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• pp.646-652
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• 2009

본 논문에서는 점용접 너깃의 피로수명을 고려한 차량 서브프레임의 용접간격 최적화 설계기법이 제안된다. 주파수영역 피로해석기법에 의해 점용접 너깃의 피로수명이 평가된다. 피로해석에서 사용되는 입력 데이터는 벨지안로 프로파일을 통과하는 차량동역학 해석과 차량 서브프레임 유한요소모델의 모드 주파수 해석을 통해 얻는다. 주파수 영역 피로해석으로 부터 얻은 피로수명 결과로부터 용접간격 최적화를 수행 할 설계점들이 선정된다. 점용접 너깃의 피로수명을 최대화시키는 용접간격을 얻기 위하여 4-요인, 3-수준 직교배열 실험계획법이 사용된다. 본 연구를 통하여 최적화된 서브프레임은 초기모델에 비하여 최소 피로수명을 갖는 용접 너깃의 피로수명이 약 65.8 % 증대되는 것을 알 수 있다.

• 한국지진공학회논문집
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• 제10권6호
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• pp.29-36
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• 2006

이 논문에서는 진동형상의 민감도로 유도한 피셔정보행렬(Fisher Information Matrix)를 이용하는 가속도계의 최적위치 결정 기법 MS-EIDV(modal sensitivity-effective independence distribution vector)을 제안하고, 이를 사용하여 구조물의 동적 거동을 잘 반영하여 가속도계의 최적위치를 결정할 수 있는 합리적인 기준을 제시한다. 실험을 위한 가속도계의 최적위치는 구조물의 변수가 기지값이어야 결정되지만 구조물의 변수값은 실험결과를 사용한 SI(system identification)기법과 같은 역해석을 통해 구해지기 때문에, 본 논문에서는 구조변수의 오차를 감안하여 미지의 구조물의 현 상태를 통계적으로 반영하는 방법을 제시하였다. 제안된 방법들의 검증을 위해 주파수영역 SI기법을 적용하였으며, 구조변수 추정 결과를 통해 현장에서 계측하고자하는 진동형상의 수에 따른 최소 필요 가속도계의 개수를 제시하였다. 수치예제에서는 진동형상만을 이용한 최적위치 결정법인 EIDV기법과 제안된 MS-EIDV기법에 의해 추정된 구조 변수 결과를 비교하였다.

• 항공우주시스템공학회지
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• 제12권3호
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• pp.26-37
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• 2018

한국항공우주연구원에서는 지구관측을 위한 고해상도 영상 및 이미지 촬영을 위해 6U급 초소형 위성 HiREV를 개발하였다. 6U급 초소형 위성은 1U/3U급 초소형 위성에 비하여 부피가 크기 때문에 1차 고유 진동수가 상대적으로 낮으며, 구조적 하중에 의한 큰 응력과 변형량이 생길 수 있어 구조 해석을 통한 검증이 필요하다. 본 논문에서는 임무 탑재체를 탑재하고 구조적 문제점을 보완하기 위한 6U급 HiREV 위성의 구조체 설계에 대해서 설명하였고 가속도 하중 해석, 모달 해석, 랜덤 진동 해석 등의 구조 해석을 수행하였으며, 6U급 HiREV의 구조체 설계가 구조적으로 안정성 있게 설계되었음을 입증하였다. 이러한 결과들은 향후 국내에서 다양한 임무에 적용될 6U급 초소형 위성의 구조체 개발 시 유용한 참고자료가 될 것으로 사료된다.

• 한국소음진동공학회논문집
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• 제25권12호
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• pp.866-873
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• 2015

The transverse vibration of the deploying beam from rigid hub was analyzed by simulation and experiment. The linear governing equation of the deploying beam was obtained using the Euler-Bernoulli beam theory. To discretize the governing equation, the Galerkin method was used. After transforming the governing equation into the weak form, the weak form was discretized. The discretized equation was expressed by the matrix-vector form, and then the Newmark method was applied to simulate. To consider the damping effect of the beam, we conducted the modal test with various beam length. The mass proportional damping was selected by the relation of the first and second damping ratio. The proportional damping coefficient was calculated using the acquired natural frequency and damping ratio through the modal test. The experiment was set up to measure the transverse vibration of the deploying beam. The fixed beam at the carriage of the linear actuator was moved by moving the carriage. The transverse vibration of the deploying beam was observed by the Eulerian description near the hub. The deploying or retraction motion of the beam had the constant velocity and the velocity profile with acceleration and deceleration. We compared the transverse vibration results by the simulation and experiment. The observed response by the Eulerian description were analyzed.

• 대한기계학회논문집A
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• 제35권3호
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• pp.317-323
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• 2011

본 논문에서는 원자력 발전소 폴라 크레인(polar crane)의 설계를 위해 유한요소법을 통한 내진해석을 수행하였다. 모드 해석(modal analysis)을 통하여 폴라 크레인의 고유진동수와 진동형상을 파악하고 응답스펙트럼(response spectrum)을 통해 폴라 크레인의 내진 안전성을 평가하였다. 그리고 액체저장탱크에 대한 내진해석을 유한요소법을 이용하여 수행하였는데, 탱크가 요동시에 액체가 탱크 외벽에 가하는 힘을 고려한 슬로싱해석과 안전정지지진 하중 조건에서의 해석을 수행하였다. 본 논문에서 유한요소해석 상용코드인 ANSYS를 이용하여 내진해석에 필요한 해석기법과 과정 등을 설계 시에 활용할 수 있도록 제안하였다.

• Earthquakes and Structures
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• 제15권3호
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• pp.335-350
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• 2018

This paper presents numerical modelling, modal testing, finite element model updating, linear and nonlinear earthquake behavior of a reinforced concrete building model. A 1/2 geometrically scale, two-storey, reinforced concrete frame model with raft base were constructed, tested and analyzed. Modal testing on the model using ambient vibrations is performed to illustrate the dynamic characteristics experimentally. Finite element model of the structure is developed by ANSYS software and dynamic characteristics such as natural frequencies, mode shapes and damping ratios are calculated numerically. The enhanced frequency domain decomposition method and the stochastic subspace identification method are used for identifying dynamic characteristics experimentally and such values are used to update the finite element models. Different parameters of the model are calibrated using manual tuning process to minimize the differences between the numerically calculated and experimentally measured dynamic characteristics. The maximum difference between the measured and numerically calculated frequencies is reduced from 28.47% to 4.75% with the model updating. To determine the effects of the finite element model updating on the earthquake behavior, linear and nonlinear earthquake analyses are performed using 1992 Erzincan earthquake record, before and after model updating. After model updating, the maximum differences in the displacements and stresses were obtained as 29% and 25% for the linear earthquake analysis and 28% and 47% for the nonlinear earthquake analysis compared with that obtained from initial earthquake results before model updating. These differences state that finite element model updating provides a significant influence on linear and especially nonlinear earthquake behavior of buildings.

• 한국산학기술학회논문지
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• 제17권12호
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• pp.652-658
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• 2016

본 논문에서는 유한 요소법(FEM) 시뮬레이션을 사용하여 초음파 미세패턴 성형에 사용되는 초음파 공구혼을 이론적 연구와 유한요소해석을 통하여 조사 하였다. 이 방법은 FEM 해석으로 얻어진 초기 설계 추정치에 기초한다. 초음파 미세패턴 성형에 필요한 고유주파수와 공구 혼의 공진주파수를 유한요소해석을 통하여 예측하였다. ANSYS S/W를 이용한 FEM 분석은 초음파 혼의 진동모드 형상의 최적 설계기술로 공진 주파수를 예측하기 위해 사용하였다. 초음파 진동자에 전원이 공급되면, 초음파 진동자에 공급된 전기에너지가 기계적인 운동에너지로 변환되어 진동이 발생하게 된다. 초음파 공구혼의 종진동 에너지를 이용하여 절연시트위에 RFID TAG 패턴 성형을 하게 된다. 초음파 진동을 이용한 마이크로 단위의 형상정밀도 향상을 위해서는 공구혼의 종진동모드만을 이용하여 성형 해야 한다. 본 연구에서는 초음파 마이크로패턴 성형에 필요한 공구혼의 고유진동수 및 진동모드를 갖는 설계변수를 고찰하고, 유한요소해석 결과를 바탕으로 공구혼을 제작함으로써 마이크로패턴 성형에 응용하고자 한다. 유한요소해석 결과를 바탕으로 RFID TAG의 미세패턴 성형을 위한 초음파 공구혼의 최적설계 및 제작에 반영하였다.

• Journal of Advanced Marine Engineering and Technology
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• 제12권2호
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• pp.21-34
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• 1988

Machinery enclosures are widely adopted to reduce the noise emission in various fields of application. Emitted noise, which is due to the vibration of enclosure's outer surface, is composed of two kinds of sound with different path of propagation. One is the "structure-borne sound", while the other is "air-borne sound". In order to get a most efficient machinery enclouser a prudent consideration upon the above structure-borne and air-borne sound is required, as the guiding principle of contermeasure for each noise is quite different. The controlling of input vibration and its isolation are major subjects for the structure-borne sound, and the specifications of absorbing members and damping panels are the major related matters for the air-borne sound. Hence, it seems very efficient to separate the total sounds into two categories with a great accuracy when one think of further reduction of noise from the existing enclosure, although its separating methods have not been made clear for many years. Author proposes an application method of experimental modal analysis to extract the structure-borne sound from the measured total radiation sound, as the air-borne sound is deduced by the vectorial difference between the measured total radiation sound and the calculated structure-borne sound. In order to calculate the correct structure-borne sound by the excitation at an arbitrary point on the enclosure structure, it is important to decide 1) how to estimate the enclosure's surface vibration velocity and 2) how to compute the radiation sound which is considered as the effect of vibration modes of enclosure surface. The former can be solved with total frequency response function calculated by the application of experimental modal analysis. The latter is to be solved by the author's new approaches for radiation sound computation by means of the Rayleigh's integral equation and the boundary-element method applied complex surface vibration velocity. As a first step, structure-borne sound by the excitation at an arbitry point on the rectangular plate with fixed edges, has been calculated to verified the reliability of the developed computation methods. The results of calculation show good agreements with those of the actual measurements.actual measurements.

• Advances in aircraft and spacecraft science
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• 제2권2호
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• pp.217-232
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• 2015

To prevent over-testing of the test-item during random vibration testing Scharton proposed and discussed the force limited random vibration testing (FLVT) in a number of publications. Besides the random vibration specification, the total mass and the turn-over frequency of the load (test item), $C^2$ is a very important parameter for FLVT. A number of computational methods to estimate $C^2$ are described in the literature, i.e., the simple and the complex two degrees of freedom system, STDFS and CTDFS, respectively. The motivation of this work is to evaluate the method for the computation of a realistic value of $C^2$ to perform a representative random vibration test based on force limitation, when the adjacent structure (source) description is more or less unknown. Marchand discussed the formal description of getting $C^2$, using the maximum PSD of the acceleration and maximum PSD of the force, both at the interface between load and source. Stevens presented the coupled systems modal approach (CSMA), where simplified asparagus patch models (parallel-oscillator representation) of load and source are connected, consisting of modal effective masses and the spring stiffness's associated with the natural frequencies. When the random acceleration vibration specification is given the CSMA method is suitable to compute the value of the parameter $C^2$. When no mathematical model of the source can be made available, estimations of the value $C^2$ can be find in literature. In this paper a probabilistic mathematical representation of the unknown source is proposed, such that the asparagus patch model of the source can be approximated. The chosen probabilistic design parameters have a uniform distribution. The computation of the value $C^2$ can be done in conjunction with the CSMA method, knowing the apparent mass of the load and the random acceleration specification at the interface between load and source, respectively. Data of two cases available from literature have been analyzed and discussed to get more knowledge about the applicability of the probabilistic method.

• Smart Structures and Systems
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• 제11권6호
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• pp.589-604
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• 2013

Identification of damage has become an evolving area of research over the last few decades with increasing the need of online health monitoring of the large structures. The visual damage detection can be impractical, expensive and ineffective in case of large structures, e.g., offshore platforms, offshore pipelines, multi-storied buildings and bridges. Damage in a system causes a change in the dynamic properties of the system. The structural damage is typically a local phenomenon, which tends to be captured by higher frequency signals. Most of vibration-based damage detection methods require modal properties that are obtained from measured signals through the system identification techniques. However, the modal properties such as natural frequencies and mode shapes are not such good sensitive indication of structural damage. Identification of damaged jacket type offshore platform members, based on wavelet packet transform is presented in this paper. The jacket platform is excited by simple wave load. Response of actual jacket needs to be measured. Dynamic signals are measured by finite element analysis result. It is assumed that this is actual response of the platform measured in the field. The dynamic signals first decomposed into wavelet packet components. Then eliminating some of the component signals (eliminate approximation component of wavelet packet decomposition), component energies of remained signal (detail components) are calculated and used for damage assessment. This method is called Detail Signal Energy Rate Index (DSERI). The results show that reduced wavelet packet component energies are good candidate indices which are sensitive to structural damage. These component energies can be used for damage assessment including identifying damage occurrence and are applicable for finding damages' location.