• Proceedings of the Korean Society For Composite Materials Conference
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• 2002.05a
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• pp.1-4
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• 2002

With the wide application of fiber-reinforced composite material in aero-structures and mechanical parts, the design of composite joint have become a very important research area because they are often the weakest areas in composite structures. In this paper, the failure area index method to predict the strength of the mechanically fastened composite joint which has the same stacking sequence was suggested and evaluated. By the suggested failure area index method, the strength of the mechanically fastened composite joint could be predicted within 6.03%.

• Proceedings of the Korean Society For Composite Materials Conference
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• 2002.10a
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• pp.106-109
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• 2002

With the wide application of fiber-reinforced composite material in aero-structures and mechanical parts, the design of composite joint have become a very important research area because they are often the weakest areas in composite structures. In this paper, the failure area index method to predict the strength of the mechanically fastened composite joint which has the same stacking sequence was used and evaluated. By the used failure area index method, the strength of the mechanically fastened composite joint which has the specimen of different shape and stacking sequence could be predicted within 9.96%.

• Journal of the Korea Institute of Military Science and Technology
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• v.4 no.2
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• pp.9-16
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• 2001

In this paper, general design process for Tracked Fighting Vehicle has been suggested. Stress analysis and optimal design for ply angle of IFV's composite upper hull has been calculated using KMA CIFV and it is contained exploratory development of design process. In this point, this paper applied composite to IFV's upper hull. Finite element mesh has been made using Matlab program, and we have analyzed stress based on the given material properties and ply arrangement. For each load condition, load distribution in plane and failure index are calculated by using Tasi-Hill criterion, which is composite failure criterion and analyzing change of failure index as change of ply angle. Finally, optimal ply angles of upper hull are calculated using KMA CIFV. We can estimate the decrease of weight for IFV's upper hull.

• Proceedings of the Korean Society For Composite Materials Conference
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• 2005.04a
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• pp.84-89
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• 2005

The design of composite joint is a very important research area because they are often the weakest areas in composite structures. In this paper, the failure load of the mechanically fastened composite joint with the clamping force was predicted by the failure area index method. By the suggested failure area index method, the strength of the mechanically fastened composite joint could be predicted within 22.5% when clamping force was applied to the composite joint.

• Composites Research
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• v.18 no.5
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• pp.9-14
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• 2005

The design of composite joint is a very important research area because they are often the weakest areas in composite structures. In this paper, the failure load of the mechanically fastened composite joint with the clamping force was predicted by the failure area index method. By the suggested failure area index method, the strength of the mechanically fastened composite joint could be predicted within $22.5\%$ when the clamping force was applied to the composite joint.

• Proceedings of the Korean Society For Composite Materials Conference
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• 2003.04a
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• pp.79-82
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• 2003

With the wide application of fiber-reinforced composite material in aero-structures and mechanical parts, the design of composite joint have become a very important research area because they are often the weakest areas in composite structures. In this paper, the failure area index method to predict the failure load of the mechanically fastened composite joint was used and the prediction accuracies of the linear finite element analysis were compared with those of nonlinear finite element analysis.

• Journal of Korean Society of Steel Construction
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• v.15 no.4 s.65
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• pp.389-401
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• 2003

The purpose of this study is to develop an algorithm, which can be designed the optimal sections of the composite framed structures constituted with the beams and the columns consisted of H type of steel section and concrete considering the reliability index. The optimized problem or the composite framed structures is formulated with the objective function and the constraints taking the section sizes as the design variables. The objective functions are constituted by the total costs of constructions. Also, the constraints are derived by considering the reliability index of section stress and allowable stress. The algorithm optimized the section of the composite framed structures utilizes the SUMT method using the modified Newton-Raphson direction method. The optimizing algorithm developed in this study is applied to the numerical examples with respecting a one-bay, one-story composite framed structure and a one-bay five-story one for the practical utilization of design on the composite framed structures using the reliability indices$({\beta})$ three and zero. In addition, their numerical results are compared and analyzed to examine the possibility of optimization the applicability, and the convergence this algorithm.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.3
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• pp.21-27
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• 2018

In this paper the laminate design parameters are researched to maximize the performance index of a composite pressure vessel. To maximize the performance index, the three design variables that the thickness of each of helical and hoop layers and the length of hoop layer are considered under the assumption of fixed internal space. To optimize the variables, the response surface method is introduced for construction of the surrogate model and the ANOVA(analysis of variance) is performed to evaluate the effects of the variables. The optimization problem is formulated to maximize performance index under the burst pressure constraint. To verify the effectiveness of the research, numerical analyses are performed for the optimum model.

• Journal of the Korean Society of Manufacturing Technology Engineers
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• v.26 no.3
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• pp.292-298
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• 2017

Numerical analysis for various design parameters should be preceded by optimal design of composite materials. Numerous studies have been conducted on the bolting of interconnecting beams. In this study, the response surface method was applied to optimize the design of bolted joints connected by laminated wood composite beams. The response surface was created by combining the FEA code for composite analysis and the algorithm for forming the response surface. Optimization on this response surface was performed with a genetic algorithm to derive the results. The determination of the optimum bolt-hole position for the connection of composite beams is an optimization problem. Tsai-Wu composite failure index, maximum deflection, and simple von Mises stress are set as the objective functions. It has been proved that the design results of the optimized bolt-hole are superior to the design performance of the existing conventional bolt-hole position.

• Structural Engineering and Mechanics
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• v.88 no.4
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• pp.369-377
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• 2023

In this study, previously developed algorithm is used for Optimization of hybrid composite plates using Tsai-Wu criteria. For the stress-based Design Optimization problems, Von-Mises stress uses as design variable for isotropic materials. Maximum stress, maximum strain, Tsai Hill, and Tsai-Wu criteria are generally used to determine failure of composite materials. In this study, failure index value is used as design variable in the optimization algorithm and Tsai-Wu criteria is utilized to calculate this value. In the analyses, commonly used design domains according to different hybrid orientations are optimized and results are presented. When the optimization algorithm was applied, 50% material reduction was obtained without exceeding allowable failure index value.