• 한국공작기계학회논문집
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• 제13권6호
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• pp.102-106
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• 2004

The purpose of the study is to perform structual analysis of 9 type bellows for automotive. The bellows joint which was used as a absorber or safety equipment to prevent the deformation or fracture of a structure, has been analyzed by the FEM modeling using axi-symmetric conical frustum element. Using FEM the general behavior of bellows analysis can be investigate easily, as well as the stability of the analysis can be guarantee. The results of finite element structual analysis and actual result gave a good agreement.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 1994년도 춘계학술대회논문집; 영남대학교, 20 May 1994
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• pp.128-133
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• 1994

본 논문에서는 이중 푸리에 사인시리즈를 통한 해석법으로 경계조건과 내부 구속조건을 라그랑지 상수들과 스토크 변환법으로 해결하는 방법이며 내부에 변위가 구속되는 평판의 경우에 대하여 FEM 프로그램인 NASTRAN과 본 방법으로 계산한 결과를 고찰하였으며 S-S-S-S의 경계조건에 내부구속조건이 있는 경우 FEM 계산값과 거의 일치하며 F-C-F-F 경우는 5차 모우드에서 최대 3% 정도의 오차를 보이고 있다. 그리고 그 밖의 다른 경계조건의 경우에도 진동해석시 적용이 가능하다. 위의 해석 결과들을 통해 여러 경계조건을 갖는 평판에 내부 구속조건을 갖는 경우 진동해석시 타당한 접근 방법이라 할 수 있다. 앞으로 본 방법을 이용하여 보강판에 여러 경계조건이 구속되어 있는 경우 진동해석에도 이용되어질 수 있다.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2001년도 춘계학술대회논문집
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• pp.374-379
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• 2001

The satellite electronic equipment is exposed to high level random vibration environment during the launch of spacecraft. The random vibration can cause damage of electronic equipment. Thus very careful consideration on the launch environment, especially for high level random vibration, is required in the design stage of transponder equipments of communication satellite. For the structural integrity of the communication satellite transponder equipment under qualification level random vibration, Finite Element analysis was carried out using the commercial code, MSC/Nastran and ANSYS and stress levels are presented. In order to validate the femodel, modal test was also performed and compared with numerical results.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2005년도 추계 학술대회논문집(수송기계편)
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• pp.49-52
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• 2005

Flutter analysis procedure can be divided into two steps such as the computation of generalized mass, stiffness, and unsteady aerodynamic matrices and the calculation of major vibration modes frequency and damping values at each flight speed by solving the complex eigenvalue problem. In aircraft flutter analyses, most of the time is spent in the process of computing the unsteady aerodynamic matrices at each Mach-reduced frequency pairs defined. In this study, the method has been presented for computation and extraction of unsteady aerodynamic matrix portions dependent only on aerodynamic model using DMAP ALTER in MSC/NASTRAN SOL 145. In addition, efficient flutter analysis method has been suggested by computing and utilizing the unsteady generalized aerodynamic matrices for each analysis condition using the unsteady aerodynamic matrix portions extracted above.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2002년도 추계학술대회논문초록집
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• pp.348.2-348
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• 2002

ER mount is often used instead of rubber mount in cylindrical shell to improve the vibration and noise performanec. The noise radiated by cylindrical shell will be reduced by reducing the force transmitted to the cylindrical shell through ER mount. In this paper, LQ control theory is used to reduce the transmitted force to the cylindrical shell. The finite element method of cylindrical shell is formulated by NASTRAN and its vibrating shape is calculated in frequency domain. (omitted)

• Journal of Ship and Ocean Technology
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• 제11권4호
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• pp.1-20
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• 2007

After the introduction of the World Trade Organization, large scale container ships are being used as a means of transportation for international trade. Therefore, improving the loading and unloading capability of container quays is the most economic way, considering the cost needed for the establishment or expansion of container quays. In this paper, a new container cargo handing system that is equipped with a high performance container crane is suggested. A structural analysis on the container crane is also conducted to decide the form and size of structural member scantlings, using NASTRAN, which is a general structure analysis program.

• 항공우주시스템공학회지
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• 제1권1호
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• pp.36-44
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• 2007

This study was performed on preliminary structural design of a small scale WIG craft which has been developed as a next generation high speed maritime transportation system in Korea. A composite structure design using the foam-sandwich for main wing and tail fins and the honeycomb sandwich and skin-stringer-ring frame for fuselage was applied for weight reduction as well as structural stability. A commercial FEM code, NASTRAN for was utilized to confirm the structural safety for the reiterate design modifications to meet design requirements including the target weight. Each main wing was jointed with the fuselage by eight high strength insert bolts for easy assembling and disassembling as well as for assuring the required 20 years service life. For control surface structural design, the channel type spar, the foam sandwich skin and the lug joint were adopted.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 1992년도 추계학술대회논문집; 반도아카데미, 20 Nov. 1992
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• pp.19-24
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• 1992

Design sensitivity analysis method for the vibration of vehicle structure is developed using adjoint variable method. A variational approach with complex response method is used to derive sensitivity expression. To evaluate sensitivity, FEM analysis of ship deck and vehicle structure are performed using MSC/NASTRAN on the super computer CRAY2S, and sensitivity computation is carried on PC. The accuracy of sensitivity is verified by the results of finite difference method. When compared to structural analysis time on CRAY2S, sensitivity computation is remarkably economical. The sensitivity of vehicle frame can be used to reduce the vibration responses such as displacement and acceleration of vehicle.

• 소음진동
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• 제8권4호
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• pp.690-699
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• 1998

This paper discusses the techniques, procedures and the results of the ground vibration test(GVT) performed on the development aircraft and the simple procedure of FE model updating technique from the GVT results. The GVT was carried out using random excitation technique with MIMO(Multi-Input-Multi-Output) data acquistion method, and taking full advantage of poly-reference global parameter estimation technique to identify the vibration modes. In dynamic FE modeling, the aircraft was represented by beam elements and all dynamic analysis was performed using MSC/NASTRAN for this model. In updating procedure, the stiffness of the beam model was adjusted iteratively so as to get the natural frequencies and mode shapes close to the GVT results.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2000년도 춘계학술대회논문집
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• pp.1180-1184
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• 2000

The dynamic design analysis method (DDAM) to analyze and evaluate shock response of the equipment system mounted in ships are discussed. Theoretical background of the DDAM based on the general shock response analysis was introduced. Spectrum dip effect between the equipment system and supporting structure was specially focused being peculiar to general shock response analysis. Actual shock design values used in the DDAM were reviewed in their category, general trend and establishing process. Aspects of DDAM analysis using MSC/NASTRAN were shortened. As a conclusion DDAM is regarded as a reasonable way of analysis for the onboard equipment system due to the underwater shock.