• Journal of the KSME
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• v.28 no.4
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• pp.408-414
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• 1988

근년에 항공 산업이 많은 관심을 불러일으키고 있음에 즈음하여 독자적인 항공기 구조개발시 구조적 안전성 확보를 위해서는 구조시험 기술의 확보가 필수적이다. 또한 구조시험 관련기술은 다른 기계 구조물의 초기 설계단계에서 구조 강도 및 피로 강도의 확인을 위해서도 응력될 수 있어 구조물의 설계 및 제작공정 결정에 큰 도움이 될 수 있으므로 기업체나 연구소에서도 충 분히 응용할 수 있도록 노력을 기울여야 할 분야이다.

• Aerospace Engineering and Technology
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• v.7 no.1
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• pp.15-23
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• 2008

This paper describes the structural analysis results of KARI General Small-scaled Rotor Test System (GSRTS) operated in KARI to verify operational safety. This GSRTS was developed to conduct a froude and mach small-scaled rotor test. This analysis was performed to investigate the structural Factor of Safety for the various small-scale rotor system like articulated or hingeless rotor and to check the operational capability using given operational design load. Specially, drive system has several bearings, mechanical gears, shaft, etc. and these parts must be required to achieve an operational safety. The calculation was done by using geometric data and material properties by analytical method. This rotor test system should be operated within these calculated Factor of Safety. Furthermore, the operational limitation should be defined as applied to small-scale rotor system of KUH in future.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.36 no.9
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• pp.1087-1094
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• 2012

This study deals with structural analysis and testing under loading conditions calculated by computational fluid dynamics for a small composite blade that is utilized in a dual rotor wind turbine system. First, the aerodynamic forces were analyzed at the rated and cutout wind speed to identify the bending moment distribution along the blade length in previous research. Then, full-scale structural tests were conducted according to IEC 61400-2 to evaluate the structural integrity of the composite blade. These results were compared with finite element analysis to identify the accuracy of the structural analysis. Based on these results, it was revealed that the existing blade has a very high safety margin. Then, the layup of the composite blade was redesigned and analyzed using finite element analysis to achieve structural integrity and economic efficiency.

• Journal of the Korean Society for Railway
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• v.13 no.4
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• pp.363-370
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• 2010

This paper describes the evaluation of structural integrity and dynamic characteristic of inertial load test equipments for performance test of railway vehicle propulsion control system. The propulsion control system of railway vehicle has to be confirmed of safety and reliability prior to its application. Therefore, inertial load test equipments were designed through theoretical equation for performance test of propulsion control system. The structural analysis of inertial load test equipments was conducted using Ansys v11.0 and the dynamic characteristic was evaluated using Adams. The results showed that the structural integrity of inertial load test equipment was satisfied with a safety factor of 10.2 on the bearing part under combined load. Also, the structural stability of flywheel according to dynamic simulation was secured by the maximum oscillation displacement within 0.83mm.

• Aerospace Engineering and Technology
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• v.6 no.2
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• pp.35-39
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• 2007

In this paper, we have presented structural analysis procedure and full scale test results for 4-seater canard airplane. Construction of the finite element model is critical path for the aircraft structural analysis and directly affects the structural integrity. The refinement of the finite element model should be determined depending on full scale test results. From the results of the structural analysis, 5 design limit loads test conditions and 11 design ultimate loads test conditions were selected. By the presented procedure, the structural integrity of 4-Seater Canard Airplane is successfully obtained.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.99-105
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• 2005

To evaluate structural safety factor of the jet vane for the thrust deflection system under the dynamic pressure and very high temperature($2700^{\circ}C$) of the combustion gas flow, the high temperature tension tests of refractory metals and 3-D nonlinear numerical simulations are performed. Through the analysis of high temperature structural behavior for jet vane, the structural safety of jet vane is evaluated, and numerical results are compared with static pound tests of jet vanes. It has been found that most of structural and thermal loading is concentrated on the vane shaft which worked as safe under $1400^{\circ}C$. From the comparison of static ground tests and numerical results, the evaluation criterion using the vane load and shaft displacement is more useful to estimate the structural safety than using the equivalent stress.

• Journal of the Korean Society of Propulsion Engineers
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• v.9 no.3
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• pp.18-24
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• 2005

To evaluate structural safety factor of the jet vane for the thrust deflection system under the dynamic pressure and very high temperature(2700$^{\circ}C$ ) of the combustion gas flow, the high temperature tension tests of refractory metals and 3-D nonlinear numerical simulations are performed. Through the analysis of high temperature structure behavior for jet vane, the structure safety of jet vane is evaluated, and numerical results are compared with static ground tests of jet vanes. It has been found that most of structural and thermal loading is concentrated on the vane shaft which worked as safe under 1400$^{\circ}C$. From the comparison of static ground tests and numerical results, the evaluation criterion using the vane load and shaft displacement is more useful to estimate the structural safety than using the equivalent stress.

• Journal of Aerospace System Engineering
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• v.12 no.1
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• pp.42-46
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• 2018

The subject of this study dealt with the structural safety analysis regarding the measured thrust test equipment as noted on a small engine. In this work, the structural design and analysis of steel and aluminum alloy structure for a small engine test of equipment were performed. Firstly, the structural design requirements of the engine test equipment were identified and investigated. After the structural design was reviewed, next the structural analysis of the engine test equipment was performed by the utilization of the finite element analysis method. The study was performed to determine that the stress and displacement analysis was appropriately managed regarding the applied load condition. As a result, it was determined that through the structural analysis, this study has confirmed that the designed engine test equipment is approved for safety, and meets its design purpose at this time.

• Proceedings of the Korean Vacuum Society Conference
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• 2015.08a
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• pp.103.2-103.2
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• 2015

10-3 Pa 이하의 고진공 환경과 $180^{\circ}C$ 이하의 극저온 환경에서 대형정지궤도위성의 고온 열평형 환경구현을 위한 열제어패널이 설계되었다. 열제어패널은 가로 2.2 m, 세로 2.6 m, 두께 2 mm의 구리판에 구리 튜브가 브레이징되어 있는 형태로 설계되었으며, 지상에서 6 m 이상의 높이에 설치되고 위성의 위치에 따라 이동이 가능해야 하기 때문에, 별도의 지지 구조물이 함께 설계되었다. 따라서, 열제어패널 설치 및 고정을 위한 지지구조물의 경우 160 kg의 무게를 견뎌내야 하며 이동 및 설치에 있어 구조적인 안전성이 확보 되어야 한다. 이에 본 연구에서는 상용유한요소해석 프로그램을 사용하여 열평형시험 시 위성체 상단부의 고온 환경모사를 위한 열제어패널 지지구조물에 대한 구조 안전성을 확인 하였다.

• Journal of Korea Ship Safrty Technology Authority
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• s.28
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• pp.46-63
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• 2010

플레저보트의 고강도 및 경량화 추세에 따라 복합재료 등 관련 소재의 경량화가 요구되었고, 이에 부응하여 관련 신소재 개발과 진공성형 신건조공법 등이 출현하였으며, 이러한 신공법을 이용한 선박건조가 증가하고 있는 실정에 따라 선박의 구조강도 평가가 중요한 과제로 부각되고 있다. 또한 선박의 안전성 확보와 고객의 편리 도모를 위한 플레저보트 구조강도 확인을 위한 시험방법 등도 다양화할 필요가 있다. 따라서 진공적층 및 수적층 성형방법으로 건조한 플레저보트를 대상으로 선체구조 강도 시험 결과를 비교 분석하여 우리 실정에 적합하고 플레저보트의 안정성 평가를 위한 선체구조 강도 시험 기준안을 제시하고자 한다.