• Aerospace Engineering and Technology
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• v.3 no.1
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• pp.1-8
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• 2004

In this study, the method of computing and extracting the generalized unsteady aerodynamic matrices using MSC/NASTRAN and MSC/NASTRAN DMAP ALTER has been suggested for the analysis and control of aeroelastic phenomena such as flutter and gust response analysis. In addition to that, the method of approximating the generalized unsteady aerodynamic matrices using minimum state approximation method has been proposed in order to cast the aeroelastic equations of motion in state space form for aeroelastic analysis and control application. Simplified aircraft wing box model has been used for the validation of the methods suggested in this study.

• Transactions of the Korean Society for Noise and Vibration Engineering
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• v.15 no.11 s.104
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• pp.1223-1231
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• 2005

Recently, the issue of ship nitration due to the large scale, high speed and lightweight of ship is emerging. For pleasantness in the cabin, shipbuilders are asked for strict vibration criteria and the degree of nitration level at a deckhouse became an important condition for taking order from customers. This study proposes a new optimization framework that is NASTRAN external call type optimization method (OptShip) and applies to an optimum design to decrease the nitration level of a deckhouse. The merits of this method are capable of using of global searching method and selecting of various objective function and design variables. The global optimization algorithms used here are random tabu search method which has fast converging speed and searches various size domains and genetic algorithm which searches multi-point solutions and has a good search capability in a complex space. By adapting OptShip to full-scale model, the validity of the suggested method was investigated.

• Transactions of the Korean Society for Noise and Vibration Engineering
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• v.11 no.8
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• pp.303-313
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• 2001

The identification of power flow in dynamically loaded structures Is essential in the analysis of structure-borne noise. However there are no general purpose tools to estimate powers flow. To make matters worse. It is very difficult to measure it. The power flow can be formulated in terms of balance forces(ELFORCE) at each element and velocities at the associated node obtained with MSC/NASTHAN. In this paper the procedure which is consist of the computations of the balance forces of al1 elements and the velocities at all nodes using MSC/NASTRAN. The calculations of the power f1ow at each element using PCL(PATRAN Command Language) and the Preparation of post -processes is set UP.

• The Korean Journal of Ceramics
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• v.5 no.3
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• pp.235-238
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• 1999

In a ceramic green body, some degree of nonuniformity in density always presents. These differences in green density will appear as nonuniform shrinkage after sintering takes place. For the complex ceramic bodies with various curves and angles, therefore, it is quite difficult to foresee the final dimensions precisely after sintering. This simulation study shows that, considering the sintering process as a thermal shrinkage phenomenon, the use of NASTRAN enables to predict the precise shape of a sintered body. Based on this result, 'the reverse engineering technique' has been developed that can unfold the exact dimensions of a green body to have the desired shape after sintering. This approach will provide a simple and useful tool for ceramic engineers to fabricate complicate bodies with tight dimensional tolerances.

• Proceedings of the Korean Society For Composite Materials Conference
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• 2005.04a
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• pp.46-50
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• 2005

Smart skin, a multi-layer structure of composed of a round shape antenna, was designed and fabricated. Tests and analyses was conducted to study its behavior under compressive loads. It was confirmed that the designed smart skin failed due to premature buckling before compression failure. Numerical prediction of structural behavior of smart skin by MSC.NASTRAN agreed well with experimental data.

• Computational Structural Engineering
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• v.4 no.3
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• pp.40-43
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• 1991

한국과학기술연구원(KIST)부설 시스템공학연구소(SERI)가 보유하여 일반 사용자들에게 공개하고 있는 구조해석 S/W/로는 ABAQUS, ADINA, BOPACE-3D, DYNA-3D, MSC/NASTRAN, DIS/ADLPIPE, SAP5, KISTRAS, NONSAP, MARC 등을 들 수 있다. 이들 중 DIS/ADLPIPE, SAP5, KISTRAS, NONSAP은 CDC CYBER 960-31에 설치되어 있고 MARC는 NAS AS/XLV50에 설치되어 있으며 나머지는 CRAY-25 슈퍼컴퓨터에 설치되어 있다. 본 고에서는 이들 중에서 CRAY-2S 슈퍼컴퓨터에 설치되어 있으며 다양한 비선형 구조해석기능을 가지고 있는 ABAQUS, ADINA, MSC/NASTRAN 및 DYNA-3D에 대하여 개요, 기능 및 사용방법을 간략히 소개하고저 한다.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 1995.10a
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• pp.116-122
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• 1995

본 논문에서는 컴프레서 쉘의 구조해석을 수행하기 위하여, 범용 구조 해석 패키지인 MSC/NASTRAN을 이용하여 컴프레서 쉘 전체의 동특성 해석을 수행하였으며, MSC/NASTRAN의 Superelement 모듈인 부분구조합성법을 이용하여 구조물 전체의 동특성해석을 수행하였다. 그리고, 각 분계의 변형 및 운동 에너지를 산출하여 전체 구조물의 고유모드에 대한 분계의 기여도를 평가하였으며, 각각의 에너지에 기여가 높은 분계의 형상을 변경하여 구조물 전체가 원하는 동특성을 얻도록 하였다.

• Transactions of the Korean Society of Mechanical Engineers
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• v.15 no.3
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• pp.1044-1056
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• 1991

본 연구에서는 균일압축력을 받으며 네변이 단순지지된 비균일 두께를 가진 평판의 좌굴응력을 Rayleigh-Ritz방법으로 해석하여 평판두께를 적절히 분포함으로써 동일한 평판중량으로 더 큰 좌굴하중을 얻을 수 있음을 보이며 또한 동일한 문제를 NASTRAN프로그램을 사용하여 해석함으로써 그 정확도를 입증한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.5
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• pp.34-40
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• 2005

Most analyses and researches on Micro Aerial Vehicle(MAV) have focused upon propulsion, automatic control, aerodynamic configuration in low Reynolds number region, and miniaturization of telemetric parts. In the present study, a structural concept for MAV is designed by using the composite material suitable for light flight structures. In order to study the load path and stress state of the MAV, the load and structural analyses are simultaneously performed by the aeroelasticity module of MSC/NASTRAN. The stability derivatives of the MAV are obtained for three symmetric, two antisymmetric, and four unsymmetric maneuvering conditions. Although the aerodynamic theory in MSC/NASTRAN could not be proper for MAV analysis, it provides an traditional and effective tool for trim and load analyses and may be corrected with the results by more accurate theory or test. The results show that the inertial load due to payloads has a more effect on stress rather than the aerodynamic load.

• Journal of the Society of Naval Architects of Korea
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• v.36 no.2
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• pp.114-120
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• 1999

The DDAM(Dynamic Design Analysis Method) has been the most popular method for the shock response analysis of naval shipboard equipment. It was common to model the equipment as a simplified mass-spring system with multi degree of freedom in DDAM. Nowadays, however, it is necessary to adopt the finite element method for the shock response analysis due to the complexity of equipment. In this study, the DDAM program is developed to evaluate the performance of shock-resistance of FEM models using MSC/NASTRAN DMAP(Direct Matrix Abstraction Program) which provides the practical tools in interfacing with the externally developed program. Through the numerical test of the structural components and comparison with the results of ANSYS DDAM, it is confirmed that the developed program can be applicable to analyze the shock responses of the shipboard equipments.