• Journal of Korean Association for Spatial Structures
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• v.4 no.3 s.13
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• pp.20-26
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• 2004

• 건축구조
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• v.9 no.3
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• pp.44-46
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• 2002

• 건축구조
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• v.11 no.3
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• pp.30-35
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• 2004

• Journal of Korean Association for Spatial Structures
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• v.8 no.5
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• pp.9-13
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• 2008

• Proceedings of the Computational Structural Engineering Institute Conference
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• 1997.04a
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• pp.219-223
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• 1997

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.3
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• pp.74-81
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• 2004

In this study preliminary structural design has been performed to develop an all composite wing box for experimental aircraft(classified in FAR Part 21). Considerations on composite materials and their manufacturing process were taken into account throughout the design phase. Aerodynamic loads were estimated by using Shrenk method(NACA TM No 948) and FAR Part 23 Appendix A. The structural layout has been determined to carry effectively the critical loads and to maximize the benefit of composite structure. Maximum strain failure allowable and first ply failure criteria were applied for the sizing of major structural members. Finally, the designed composite wing box structure is presented in the form of drawings, which include material specifications, stacking sequences and joint design.

• Composites Research
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• v.29 no.5
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• pp.231-235
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• 2016

In this study, integrated co-bonded panels with the same configuration of hat stiffeners were fabricated and measured for ply waviness phenomenon. Total specimens consisted of 2 types; 1) the general co-bonded panel and 2) the co-bonded panel with caul plate made of carbon epoxy composite materials. The first general co-bonded panel specimen exhibited that laminate thickness on the stiffener location area was much thicker than the non-stiffener area and, there was ply waviness with 0.61 mm height and 3.29 mm length. In the second co-bonded panel specimen, the reduced waviness with 0.22 mm height and 1.37 length resulted in more than 50% improvements, which is due to the uniform pressure distribution of co-bonded interface by caul plate.

• Aerospace Engineering and Technology
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• v.10 no.2
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• pp.146-153
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• 2011

Some methods of calculation of test load value from design load data were investigated which will be applied at strap installed full-scale airframe of composite aircraft. These methods were applied to left wing of KC-100 composite aircraft and the calculated test load values were compared with each others. Generally since test load values are differently calculated according to each aircraft type and position of straps, all calculation methods mentioned at this study need to be applied and compared to each aircraft. Finally the most appropriate method needs to be selected.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.832-834
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• 2017

In this paper, the finite element models for composite lattice structures were verified through natural frequency test. Finite element models of composite lattice structure were generated using beam, shell and solid element. Natural frequencies were measured using impact test method under free-boundary condition. The natural frequencies of finite element analysis for shell and solid element showed a good agreement with experimental results. But beam element did not show a good agreement with experimental results, because beam element could not consider the degradation of mechanical properties of non-intersection parts for composite lattice structure.

• Journal of the Architectural Institute of Korea Structure & Construction
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• v.34 no.6
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• pp.19-27
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• 2018

The stone pagoda structure is treated as a discontinuous masonry structure, and the contact surface characteristics between stones is a very important factor in the discontinuum behavior analysis. So, it is necessary to find out material and structural characteristics of stone contact surface to perform the structural analysis for safety evaluation. Accordingly, it is important to analyze the material properties of stone surface and secure the structural characteristics through various contact surface states. Therefore, in this study, various test specimens applying the filler between the surface roughness and the stone in the contact surface treatment technique of the stone pagoda were manufactured, and compression test and shear test were carried out. Also, we analyzed the material and structural characteristics of the stone contact surface through the comparison of experimental results.