• Journal of the KSME
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• v.22 no.4
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• pp.304-307
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• 1982

미국을 비롯한 선진제국은 자동차 차체의 구조해석및 자료분석에 컴퓨터의 전용 프로그램을 이미 1960년대 이전에 개발하여 1970년대부터는 그 활용이 광범위하게 실시중이며 선박설계 및 기타 장비에도 구조 해석 및 설계에 컴퓨터 프로그램을 상용화하여 판매되고 있으며 우리나라도 1980년대에 들어오면서 한국과학기술원(KAIST)은 NASTRAN, 한국기계연구소(KIMM)는 AN-SYS 및 AUTOKON등의 컴퓨터 프로그램을 도입했거나 도입중에 있어, 특히 수송기계, 선 박기타의 산업기계의 구조해석 및 설계, 시험분석에 응용이 활발해 질 것으로 보여 이제까지 널리 알려진 유한요소법상의 구조해석용 컴퓨터 프로그램을 중심으로 그 응용예를 소개코자 한다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1998.04a
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• pp.23-23
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• 1998

Jet Vane Type 추력방향제어 시스템의 구조적 안정성을 검토하기 위해 시스템의 해석을 Vane, Ablation & Bracket Interface, Nozzle flange & Housing Interface 및 Fastener의 세 부분으로 나누어 수행하였다. 해석을 위한 외력조건은 유동해석을 통해 얻어진 온도 및 압력분포에 근거하였으며, Vane의 응력해석을 위해서는 상용 Software인 Patran 및 Nastran이 사용되었다. 이번 연구는 Test Model 단계로서 충분한 강도의 고정 Housing이 사용되어, 이에 대한 해석은 수행되지 않았지만 추후 Flight Model 단계에서는 함께 고려되어질 것이며, 각 경우의 Margin of Safety값들을 도출하여 구조적 안정성을 검토하였다.

• Journal of the Korea Institute of Military Science and Technology
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• v.8 no.2 s.21
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• pp.22-29
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• 2005

In this study we performed topology optimization and size optimization about support structure of pressure container which is installed in a Common Bed. The optimization study shows that structure weight optimization results can be applied to navy ship. The topology optimization is performed by static load, homogenization and optimality criteria method and size optimization is performed by SOL200 of NASTRAN.

• Journal of Aerospace System Engineering
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• v.14 no.5
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• pp.1-8
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• 2020

The aeroservoelastic analysis that deals with the interactions of the inertial, elastic, and aerodynamic forces and the influence of the control system have been performed. MSC Nastran was used for the free vibration analysis of the structure model as the pre-analysis. ZAERO was used to calculate the unsteady aerodynamic forces. The unsteady aerodynamic forces were verified by comparing with Doublet Hybrid Method. Karpel's Minimum-State Approximation method was used for approximation of the aerodynamic forces to the Laplace domain in the frequency domain. The aeroservoelastic state-space equation was obtained by combining the aeroelastic equation with the actuator dynamics. The analysis of aeroservoelastic stability concerning the elevator input of the high aspect ratio model was performed. The root-locus method and time-integration method were used for the analysis of aeroservoelastic in frequency and time domain.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.24 no.1
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• pp.61-67
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• 2011

This study is concerned with the shape optimization of structural members frequently found in critical area in a structure system, that is, highly stressed zone. Isogeometry analysis is well known to be the very efficient way to integrate the geometric modeling(CAD) and computational analysis(CAE). This can be accomplished by directly using the geometric modeling by NURBS(Non-Uniform Rational Basis Spline). In this study, an efficient computer code adopting the isogeometry concept has been developed for the structural analysis, in which CAD information can be directly used in the finite element modeling. In order to show the validity of the present code, the present results are compared with those by using the commercial package, that is, MSC/NASTRAN. The present isogeometric analysis procedure has been integrated with the optimization procedure to deal with the optimization problem found in the context of structural mechanics. The present system has been successfully applied to the shape optimization of cantilever structure having bracket. From the present study, it can be seen the validity of the present approach and computer codes developed in this study. This paper ends with some discussions about the practical usefulness of the present approach which is based on isogeometry analysis, and extension of the present study.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.33 no.3
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• pp.187-192
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• 2020

To reduce fuel consumption by reducing the weight of the deck of a dump truck and to design an eco-friendly deck, accurate structural analysis is required. To date, the load on the deck has been calculated based on the hydrostatic pressure or by applying the earth pressure theory. However, these methods cannot be used to determine the non-uniformity of the load on the deck. Load distribution varies depending on the size distribution and interaction of aggregate particles. Compared with the finite element method, the discrete element method can simulate the behavior of aggregate particles more effectively. In this study, major properties were obtained by measuring bulk density and repose. The deck of a 15 ton dump truck was simulated using the obtained properties and bumping, breaking, and turning load conditions were applied. EDEM, which is a discrete element analysis software, was employed. The stress and strain distribution of the deck were calculated by NASTRAN and compared with the measured values. The study revealed that the results derived from a DEM simulation were more accurate than those based on mathematical assumption.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.4
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• pp.277-282
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• 2018

In this study, the accuracy and efficiency of a composite rotor blade cross-section analysis program, Ksec2d-AE, which is available at an educational web-based platform called EDISON-CSD, are assessed for possible use in undergraduate structural analysis projects. To this purpose, the convergence of cross-sectional constants by varying the number of finite elements in the cross-section of a wind turbine blade is investigated. The stiffness constants along with the cross-sectional engineering offsets obtained using Ksec2d-AE are validated against a 3D finite element analysis program MSC NASTRAN.

• Composites Research
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• v.16 no.4
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• pp.10-21
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• 2003

Proposed is a new method to determine the characteristic lengths for the failure analysis of composite joint without experiments. New method uses the result that the stress distribution in the characteristic length specimens is linearly proportional to the applied load. The compressive characteristic lengths calculated by the present method are exactly same as the lengths obtained by the conventional method based on experiment. The new tensile characteristic length is defined using the strength of the notched laminate, while previous methods use the strength of the sound laminate. That change allows calculating the tensile characteristic length numerically without experiment like the compressive characteristic length. Finite element analyses are conducted by MSC/NASTRAN. The interface between the fastener and laminate is modeled by the contact surface element. The finite element results based on the new characteristic lengths show the excellent agreement with experimental results for the Graphite/Epoxy composite .joints.

• Composites Research
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• v.24 no.2
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• pp.22-29
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• 2011

To increase the performance of thick-walled cylinders recently their length is continually enlarged. For that reason it is important to reduce weight of the thick-walled cylinders. In this paper the FE models to predict and estimate effects on the composite tapes were created with MSC.Nastran/Patran v.2005. First of all a autofrettage method was applied to the 2D model of the AISI4340 cylinder reduced the thick. And then the comparison of the numerical results with analysis results showed and verified by using T300/5208, IM7/PETI5, IM7/8552 tapes. Those are predicted to the effects of the angle of the composite tapes and elastic modulus according to the composite properties.

• Composites Research
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• v.24 no.4
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• pp.17-22
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• 2011

In this paper, as a basic research to apply the composite sandwich to underwater vehicle, the manufacturing, analysis and test methods, and weight saving effect of a composite sandwich cylinder under external pressure were studied. A two-step manufacturing method to prevent the wrinkling of the sandwich cylinder face was proposed and the three cylinders were made and tested. Finite element results based on the shell and solid model using MSC.Nastran were compared with test results. The comparison showed that the linear finite element analysis using the shell and solid elements can predict the buckling pressure of the sandwich cylinder with approximately 3% difference. The parametric study of the filament wound cylinders revealed that the composite sandwich can reduce the weight of the cylinder more than 30% compared with the filament wound cylinder supporting the same pressure.