• Aerospace Engineering and Technology
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• v.2 no.2
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• pp.76-82
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• 2003

To guarantee the proper functions of a satellite in the extreme space environment, the several test models are developed generally. There are advantages that the design and the analysis of Flight Model(FM) can be validated through these test models, and the functional reliabilities can be increased by reflecting the modifications on the final design of FM. The integration and test of Structure & Thermal Model(STM) of KOMPSAT, being currently developed, have been completed. In this paper, the processes of design and analysis of the STM propulsion system, one of the KOMPSAT modules, are described.

• Proceedings of the KIEE Conference
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• 2009.07a
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• pp.814_815
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• 2009

본 논문은 로봇관절 구동 및 제어에 활용될 중공모터의 설계 및 특성해석에 대해 연구하였다. 로봇관절에 사용될 중공모터의 경우고 토크출력이 요구될 뿐만 아니라, 저속에서 제어 및 구동 신뢰성이 높은 운전특성이 요구된다. 또한 로봇 관절에 활용하기 위하여 배선처리가 간편한 중공타입의 구조가 요구된다. 따라서 우리는 로봇 구동 및 경량화가 가능하도록 유성기어와 결합이 가능한 외전형 타입의 영구자석 동기전동기의 설계 및 특성해석을 하였다. 먼저 로봇 관절에 적합하도록 FEA 기법을 이용하여 설계하였으며, 실제 시작기 모델을 제작하여 성능실험을 통해 제안된 모터의 특성을 분석하였다.

• Computational Structural Engineering
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• v.4 no.3
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• pp.23-26
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• 1991

본 고에서는 막구조의 설계, 시공, 유지관리에 대해 개략적으로 기술하였다. 막구조는 그 여러가지 특성이 아직 규명이 안된 부분이 많고 시공오차가 비교적 큰 편이므로 막 재료의 역학적, 재료적 특성에 대한 연구와 형상해석 모델의 공식화, 막재단의 컴퓨터화가 필요하며 초기장력 도입에 따른 시공과정의 해석이 더욱 필요하다. 따라서 설계, 형상해석, 재단에서 시공 및 유지관리에 이르는 일괄적인 System의 개발이 시급하다 하겠다.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 2001.10a
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• pp.26-30
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• 2001

Audio deck의 160여개의 부품이 정확한 위치 및 정밀도를 유지하는 것은 Deck구동에 있어 매우중요하다. 최근 선진 Audio Deck와이 경쟁 우의를 위하여 치수정 밀도를 유지하면서 Deck Mechamism에 대한 VE(Value Engineering)를 실시하여 기존의 Press 또는 Die Casting으로 제작하던 부품 등을 Plastic부품으로의 변경을 실시하고 있다. 그러나 부품의 재질변경은 Deck의 오작동 및 구동부의 WOW/FLLTTER 수치중가등의 악영향 을 수반하고 있다. 본 연구는 부품의 재질을 Plastic으로 변경함에 의하여 발생하는 구조적 약화 및 Creep 변형 등을 유한요소 해석(FEM)하였으며, 이 해석결과에 근거하여 Audio Deck의 설계강성에 만족되는 부품설계형상 및 WOW/FLUTTTER 불량 등에 대한 대처방안을 제시하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.5
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• pp.474-480
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• 2011

Space Imaging Sensor operated on LEO is affected from the Earth IR and Albedo as well as the Sun Radiation. The Imaging Sensor exposed to extreme environment needs thermal control subsystem to be maintained in operating/non-operating allowable temperature. Generally, units are periodically dissipated on spacecraft panel, which is designed as radiator. Because thermal design of the imaging sensor inside a spacecraft is isolated, heat pipes connected to radiators on the panel efficiently transfer dissipation of the units. First of all, preliminary thermal design of radiating area and heater power is performed through steady energy balance equation. Based on preliminary thermal design, on-orbit thermal analysis is calculated by SINDA, so calculation for thermal design could be easy and rapid. Radiators are designed to rib-type in order to maintain radiating performance and reduce mass. After on-orbit thermal analysis, thermal requirements for Space Imaging Sensor are verified.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.97-100
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• 2008

A hybrid sounding rocket carrying about 10kg payload reaching up to 15km altitude has been designed. The commercial seamless aluminium tube and liquid ${N_2}O$ without pressurization devices were chosen as rocket motor case and oxidizer supply system respectively. A hybrid rocket engine performing required propulsion impulse is designed with time dependent internal ballistic scheme. Engine performance, aerodynamic characteristics, and trajectory were predicted by a integral technique of internal ballistics and external ballistics. The design results were evaluated by comparison with previous experimental data, technical reports, and literatures.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.34-37
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• 2009

The present study presents a numerical methodology for early conceptual trade-off study between propulsive performance, cooling efficiency, weight and size, in which combustion and cooling precesses in regeneratively cooled rocket thrust chamber are interactively simulated. To address the capabilities and reliability of the design tool, some application results are given involving contour design, performance analysis, and wall cooling prediction as well as a systematic design evaluation.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.8
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• pp.695-702
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• 2012

In this study, Multi-fidelity analysis is performed to improve the accuracy of analysis result during conceptual design stage. Multidisciplinary Design Optimization(MDO) method is also considered to satisfy the total system requirements. Low-fidelity analysis codes which are based on empirical equations are developed and validated for analyzing the Unmanned Aerial Vehicle(UAV) which have unconventional configurations. Analysis codes consist of initial sizing, aerodynamics, propulsion, mission, weight, performance, and stability modules. Design synthesis program which is composed of those modules is developed. To improve the accuracy of the design method for UAV, Vortex Lattice Method is used for the strategy of MFA. Multi-Disciplinary Feasible(MDF) method is used for MDO technique. To demonstrate the validity of presented method, the optimization results of both methods are compared. According to those results, the presented method is demonstrated to be applicable to improve the accuracy of the analyses during conceptual design stage.

• Composites Research
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• v.22 no.1
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• pp.22-31
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• 2009

Recently the wind energy has been alternatively used as a renewable energy resource instead of the mostly used fossil fuel due to its lack and environmental issues. This work is to propose a structural design and analysis procedure for development of the 500W class small wind turbine system which will be applicable to relatively low speed region like Korea and for the domestic use. The wind turbine blade was performed structural analysis including stress, deformation, buckling, vibration and fatigue. In addition, the blade should be safe from the impact damage due to FOD(Foreign Object Damage) including the bird strike. MSC.Dytran was used in order to analyze the bird strike penomena on the blade, and the applied method Arbitrary Lagrangian-Eulerian was evaluated by comparison with the previous study results. Finally, the structural test was carried out and its test results were compared with the estimated results for evaluation of the designed structure.

• Proceedings of the Computational Structural Engineering Institute Conference
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• 2010.04a
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• pp.396-399
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• 2010

본 논문에서는 실제 건설중인 초고층건물을 대상으로 상시 풍하중을 이용한 풍진동 모니터링을 통해 고유주기와 감쇠비를 예측하고 이를 설계단계에서의 구조해석 및 가정에 의한 고유주기 및 감쇠비와 비교하였다. 이를 위해 시공중 풍진동계측을 실시하여 고유주기와 감쇠비를 측정하고, 시공단계를 고려한 구조해석모델을 통해 고유주기와 감쇠비가 유사하도록 모델을 수정한 후 이를 바탕으로 완공단계에서의 구조해석모델을 재구성하였다. 이 완공단계에서의 구조해석모델을 바탕으로 완공후의 고유주기 및 감쇠비를 예측하고 이를 설계단계에서의 값과 비교하였다. 향후 이러한 실계측 및 분석을 충분히 축적된다면 초고층설계시의 보수적인 가정사항들을 개선시키고, 풍동실험에 의한 풍진동 산정시의 정확성을 크게 향상시킬 것으로 기대된다.