• Journal of the Korean Society of Propulsion Engineers
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• v.25 no.6
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• pp.74-86
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• 2021

The composite lattice structure is a structure that supports the required load with the minimum weight and thickness. Composite lattice structure is manufactured by the filament winding process using impregnating high-strength carbon fiber with an epoxy resin. Filament winding process can laminate and manufacture only structurally necessary parts, composite lattice structure can be applied to aircraft fuselages, satellite and launch vehicles, and guided weapons to maximize weight reduction. In this paper, the development and evaluation of the composite lattice structure corresponding to the entire process from design, analysis, fabrication, and evaluation of large-scale cylindrical and conical composites lattice structure were performed. To be applicable to actual projectiles and guided weapons, we developed a cylindrical lattice structure with a diameter of 2,600 mm and a length of 2,000 mm, and a conical lattice structure with an upper diameter of 1,300 mm, a lower diameter of 2,500 mm, and a length of 900 mm. The performance of the developed composite lattice structure was evaluated through a load test.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.3
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• pp.257-264
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• 2015

The structure of SpaceEye-1 developed by Satrec Initiative is designed to carry out various earth observation missions in harsh launch and orbit environments. This paper describes methodology of the structure design and analysis performed during the SpaceEye-1 development. The SpaceEye-1 structure is designed not only to endure the static/dynamic loads but also to protect a main payload and all other components under the launch environments. The structural design requirements were derived from the requirements of the launch vehicle, payload, and other subsystems from the initial development phase. Three-dimensional modeling process was used to verify geometric compatibility of the structure with the other subsystems, and finite element analysis was used to confirm whether the designed structure satisfied all the mechanical requirements derived from the launch vehicle and payload.

• Proceedings of the Korean Vacuum Society Conference
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• 2015.08a
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• pp.223.1-223.1
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• 2015

본 연구에서는 지름이 다른 두 개의 디스크가 적층된 구조를 갖는 금 나노 구조체를 제작하고 그 광학적 특성에 대해 연구하였다. 나노임프린팅을 통하여 패턴된 폴리머 포어 어레이에 금 박막을 증착하고, 포어 내부에 증착된 금 나노구조체를 선택적으로 수거하는 방법을 이용하였다 [1]. 특히 금 증착 시, 빗각으로 증착 (oblique-angle deposition)을 하여 지름이 다른 두 개의 디스크가 적층되어 있는 구조를 형성하는 것이 가능하였다. 증착 각도의 조절을 통해 적층된 두 디스크의 지름 비율을 변화시킬 뿐만 아니라, 2차원 디스크 형태의 나노구조체부터 3차원 디쉬 형태의 구조체도 제작이 가능함을 확인하였다. 제안된 하향식 나노공정을 통하여 합성된 금 나노구조체를 이용하여 광열 전환(photothermal heat conversion)과 광 간섭성 단층 (optical coherence tomography) 측정을 진행하였고, 서로 다른 두 개의 디스크가 적층된 형태의 금 나노구조체는 상용 금 나노로드 (Au nanorod) 보다 높은 광 열 전환 효율을 갖을 뿐 아니라 우수한 OCT 이미징 특성을 보였다. 광열 전환 및 OCT 이미징 실험 결과는 각각 플라즈모닉 나노구조의 광흡수, 광산란 특성에 기반하므로, 본 연구를 통하여 제안된 금 나노구조체는 광흡수 및 광산란을 기반한 바이오이미징 나노프로브로 유용하게 사용될 수 있을 것으로 전망된다.

• KSCE Journal of Civil and Environmental Engineering Research
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• v.32 no.2A
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• pp.75-83
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• 2012

In this study, an analytical studies were carried out for the buoyancy preflexion method to improve structural performance of concrete floating structures. The buoyancy preflexion means that the preflexion effects were induced to the floating structure due to the difference in buoyancy between the pontoon modules composing the floating structures. In order to verify the buoyancy preflexion effects, an analytical studies were carried out for the floating structures. The size and dimensions of FE model were determined through the structural design process. The parameter of this analytical study was length ratios of central module part, which induces buoyancy preflexion effects, to the total length. The analysis results were pre-compression on the bottom concrete slab and displacement of freeboard due to buoyancy preflexion effects. These results were processed according to the loading step, buoyancy preflexion loads on the bottom and live loads on the topside. Then, the buoyancy preflexion effects on structural performance was analyzed. As the results of this study, it was found that the buoyancy preflexion significantly influence on structural performance of floating structures. According to the length ratio, the buoyancy preflexion effects have a tendency of parabolic form and maximized at the length ratio of 40~60%. The buoyancy preflexion method is simple in principle and easy in application. Also, it can effectively induce pre-compression on the bottom concrete slab. Therefore, it can be concluded that the buoyancy preflexion method contribute to the improvement of structural performance and decreasing of the cross-sectional depth of floating structures.

• Bulletin of the Korean Space Science Society
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• 2003.10a
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• pp.109-109
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• 2003

원자외선분광기(FIMS), 우주물리탑재체(SPP)를 탑재한 과학기술위성 1호는 무게 약 106kg으로 고도 690km의 원형궤도에 러시아의 COSMOS-3M에 의해 플레세츠크(Plesetsk)에서 발사 되었다. 과학기술위성 1호는 적층타입(Stack Type)으로 구조체가 설계되었으며, 하나의 모듈을 하나의 구조물로 만들어 여러 개의 구조물을 쌓아 타이바(Tie Bar)를 사용하여 체결하는 방식을 채택하고 있다. 이것은 모듈을 구조체로 사용함으로써 무게를 줄일 수 있으며, 강성이 높고, 하니스 처리가 용이한 장점이 있다. 구조체는 발사환경과 우주환경을 견디도록 설계되어야 하며, 그 과정을 지상에서 시험으로 검증을 하게 된다. 본 논문은 과학기술위성 1호의 구조물 개발과정과 제작과정을 설명하고, 제작된 구조물의 시험과정과 결과를 살펴보았다.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.13 no.2
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• pp.257-270
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• 2000

The objective of this study is to develop a damage model based on damage mechanics that can be used to analyze the mechanical behavior of structures with defects and the global behavior of damaged structures. A modified second order damage tensor that can be applied to finite element analysis is used to reflect the effect of damage. The damage stress computed from the effective stress is considered as an additional loading term acting on nodes and can represent the effect of crack surface. The accuracy of the proposed algorithm is verified by comparing the analysis results with the experimental data from other studies and the analysis results based on transverse isotropic theory. The developed damage model is applied to the analyses of structures with cracks under linear elastic condition. The comparisons confirmed that the quantitative analysis of the structural behavior due to crack orientation and multiple sets of cracks is possible. Also, the damage caused by rock excavation and fault zone is analyzed. The results also showed that the developed model can effectively analyze the global behavior of damaged structures.

• Journal of the Korean Magnetics Society
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• v.14 no.3
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• pp.105-108
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• 2004

Array of magnetic Ni nanostructures has been fabricated on Si substrate by using nanoporous alumina film as a mask during deposition. The nanostructures are truncated cone-shape and the lateral sizes are comparable to height. While the continuous film shows well-defined in-plane magnetization, the nanostructure shows perpendicular component of magnetization at remanence. The hysterectic behavior of nanostructures is dominated by the demagnetizing field instead of interaction among them.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.4
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• pp.106-113
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• 2002

In spacecraft system, structure subsystem has the mission of supporting all the components safely under various space environmental conditions. The safety of spacecraft structure is finally verified from the coupled load analysis, which is a branch of load analysis which combines the launch vehicle and satellite. This study introduces the optimization algorithm to reduce the weight of spacecraft structure under launch environmental conditions directly. The acceleration responses are obtained by the introduction of coupled load analysis, which lead to check the failure of spacecraft structural members. The results show a 12% saving of structural weight and this saving is mainly driven by the thickness of honeycomb core, which strongly affects the natural frequencies of platforms and panels.

• Proceedings of the Korea Concrete Institute Conference
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• 2008.11a
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• pp.965-968
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• 2008

The KS F 2403 method used on domestic sites for checking the compressive strength of a structure, sets the compressive strength of the concrete used in structural specimens as the compressive strength of testing specimens. Under this regulation, the curing method used for testing the specimens must be the standard ponding curing method (20$\pm$2$^{\circ}$C). However, because in-placed concrete is exposed to open air and cured under the seasonal temperature changes, the compressive strength of a real structure is different from the tested compressive strength. (Therefore,) This thesis first identifies the distinct characteristics of the strength development by applying the curing method listed under the KS and used for testing specimens on compressive strength tests; the atmospheric curing method, the sealed curing method, and the structural specimen core strength testing methods used for the in-sites quality checks including reckoning of the compressive strength of the structural specimens and form-demolding period; and the curing method suggested in this research, which sets the internal conditions of the structural specimens as the conditions of the applied curing method. Then, the thesis suggests the specimen curing method that most closely reenacts the compressive strength of the concrete used on the structural specimens

• Proceedings of the KAIS Fall Conference
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• 2011.05a
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• pp.474-477
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• 2011

본 논문에서는 내진보강공법의 내진성능향상을 평가하기 위하여 진동대실험을 실시하였다. 실험 구조체는 비보강, 보강 구조체로 각각 실규모 크기의 구조체를 2개 제작하였다. 기둥 상, 중, 하부 및 보에 각각 Strain게이지, 가속도계를 설치한 후 설계펙트럼가속도 0.15g의 30~150%까지 가속도를 증가 시키면서 실험을 수행하였다. 그 결과 비 보강 구조체는 0.2g에서 최대 80cm균열이 발생하였으나 보강 구조체는 균열이 발생하지 않았다. Strain의 변화량에서는 비 보강이 보강보다 최대 1700%크게 나타났다. 가속도의 변화량은 비 보강이 176%크게 나타났다. 진동대 실험결과 본 내진보강공법이 내진성능향상에 지대한 영향을 주고 있음이 증명되었다.