• Aerospace Engineering and Technology
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• v.3 no.1
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• pp.27-34
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• 2004

Tail-wing, gondola and thrust motor mount(EMS) were built by carbon/glass fiber composites. Structural strength & stiffness was verified by specimen tests. Static strength tests for each structural components were conducted separately. Boundary conditions are specially designed for each components to simulate exact joint conditions. Tests shows no detriment deformation at 100% DLL and no failure at 150% DLL.

• Aerospace Engineering and Technology
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• v.1 no.2
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• pp.179-185
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• 2002

In this study, the structural design method for the modified long-endurance UAV is presented. Composite materials using room temperature curing method and wet lay up procedure is applied to all wing structures. The modified wing is composed of 3-piece component for improvement of ground handling. As the sandwich structure is efficient for light weight and high stiffness, all skin is used the sandwich consisting of glass/ epoxy fabric and balsa wood. The proof test is performed up to limit load corresponding to 4g load condition for the modified wing structure.

• Journal of the Korea institute for structural maintenance and inspection
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• v.24 no.6
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• pp.92-101
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• 2020

It is necessary to develop a rational method for evaluating the safety of bridges for the passage of inseparable crane vehicles exceeding the limit weight. In this study, the same method applied to the development of the recently introduced reliability-based highway bridge design code - limit state design method is applied to the calibration of the live load factor for the crane vehicle. Structural analysis was performed on the concrete bridge and the required strengths of the previous design code, the current design code and AASHTO LRFD were compared. When comparing the unfactored live load effect, the live load of the crane was greater than that of the current and previous design code. When comparing the required strength by applying the calibrated live load factor, the previous design code demands the largest strength and the current design code and the crane live load effect yields similar value. The results of safety evaluation of the actual bridges on the candidate route for the crane passage secured the same reliability as the target reliability index required by the design code and the strength of the cross section of the actual bridge is calculated greater than the required strength for the passage of the crane, which confirms the safety for the passage of the crane.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.9
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• pp.607-616
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• 2019

Free body diagram analysis is done for key parts of pilot stage of LLV (Load Limit Valve) which is used to protect overload for static structural test of aerospace flight vehicle. It is shown through the analysis that diameter ratio($D_2)^{ten}/D_2)^{comp}$) of two poppets in a pilot stage must be equal to piston area ratio($A_{comp}/A_{ten}$) of a hydraulic actuator for making a poppet open consistently at constant force applied by an actuator. The result of the analysis is verified by measuring geometries of the poppets in the four different LLVs which are corresponding to four actuators with different capacity and have been used after being imported in this laboratory. Results of "Adjuster resolution tests" with two different pilot stages show the max. deviation of Fi(actuator force in instant of opening poppet) from average Fi obtained for each turn of adjuster is 0.3KN and max. deviation of the Fi normalized by average Fi of each turn of adjuster is 3.7%. From the results, it is verified that the two pilot stages with same poppet diameter ratio make a poppet consistently open at Fis within ${\pm}3.7%$ deviation from the average Fi. The deviation is shown to be caused from frictional force of O-ring in the poppet. Additionally, design factors for poppet spring and adjuster, which are also key parts of the pilot stage, are distinguished and procedure for deciding the factors are also shown in this study.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2011.10a
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• pp.768-768
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• 2011

선박/잠수함에 설치하는 소나(sonar)는 외부 해양 환경 및 유체 흐름을 위해 소나 돔을 설치하여 운용한다. 하지만 소나 돔 설치로 인해 핵심 기능인 음향신호 송/수신 기능 저하를 야기 시킨다. 따라서 소나돔을 설계시, 구조적으로는 수중 폭팔 등의 각종 하중으로부터 센서를 보호할 수 있도록 설계하고 음향적으로는 음파의 송수신 신호를 저하시키지 않는 재질을 고려하여 설계 및 제작을 하여야 한다. 소나돔에 의한 음향 손실을 최소화하기 위하여 설계 시, 소나돔음향창 시편을 통하여 음향신호가 이를 투과하면서 생기는 신호 왜곡 혹은 투과 손실 측정을 수행한다. 제한된 크기의 수조 시험장에서 투과 손실이 측정이 되는데, 음원 반사, 회절(diffraction) 등의 문제로 인하여 다양한 주파수 대역에서의 측정이 불가피 하다. 이때, 좁은 빔폭 (Beamwidth)을 갖는 Parametric array를 이용하여 음원 회절이 생기지 않는 범위 내에서 음향창 시편의 크기를 최소화 시킬 수 있으며 제한된 공간에서도 효율적으로 음향창 시편의 투과 손실을 측정 할 수 있다. 본 논문에서는 parametric array를 이용하여 음향창 시편의 크기를 최소화 하고 이를 이용하여 음향창 투과 손실을 측정하는 연구를 수행하였다.

• 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.

• Magazine of the Korea Concrete Institute
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• v.9 no.6
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• pp.243-254
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• 1997

최근들어 구조물의 노후화와 차량하중 등의 증가로 구조물의 손상이 커지고 있으며 보강의 필요성이 절실히 대두되고 있다. 강판보강공법은 강성의 확실한 증가와 내구성 등으로 인하여 그 동안 폭넓게 사용되어 오고 있으나 효율적 보강을 위한 공법과 이론이 아직까지도 정립되지 않은 상태이다. 따라서 본 연구의 목적은 그 동안의 실험결과를 중심으로 보강도니 철근콘크리트보의 파괴기구와 박리거동을 분석하고 이로부터 합리적인 박리하중 산정이론을 제한하는데 그 목적을 두고 있다. 보강된 강판의 길이와 두께 등의 영향을 고찰하고,기존의 이론을 분석하여 기존이론의 불합리한 점을 밝혔으며, 이들을 보완한 수정이론을 제시하엿다. Roberts의 이론은 강판의 두께가 증가함에 따라 오히려 박리하중이 약간 증가하고 있어 실제적인 실험거동과 차이가 나고 있다. 본 연구의 제안식은 실제 거동을 합리적으로 표현하고 있으며, 앞으로 보강설계에 유용한 자료가 될 것으로 기대되고 있다.

• Proceedings of the KSR Conference
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• 2007.11a
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• pp.1370-1378
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• 2007

High speed railway bridge is affected on safety of bridge by dynamic amplification effect, when dynamic response of bridge is equal to effect cycle load for rolling stock axle according to high speed operation train. And excessive deformation of structure has negative effect on operation safety of train and comfort of passenger due to fluctuation of wheel load by torsion of track etc. and decrease of contact force on vehicle wheel-rail. To ensure the safety of track and train operation safety, it is have to perform the study on resonance and deformation of structure. That criteria and requirement of railway bridge is limitation of vertical acceleration on deck for dynamic behavior of structure, contact of vehicle wheel and rail, limitation of face distortion and rotation angle of end deck, and limitation of vertical displacement by train. Unlike KYEONGBU High Speed Railway, New constructed HONAM High Speed Railway have to applied the new requirement for dynamic behavior safety according to change of condition which is type of ballast (slab ballast), interval of track, and actual rolling stock load. Therefore, in this paper, it was conformed the dynamic characteristic due to parameter, which related with above mentioned criteria, for steel composite bridges.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.2
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• pp.157-164
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• 2007

Launch Interface Ring roles as connection department of satellite and launcher for to deliver all structure loads that occur from the satellite, and one of the most intensive load received parts. Especially COMS, the first Korean developing GEO satellite, needs Launch Interface Ring with Tank Support Beam because of dissymmetry fuel tanks. The purpose of this study is the suitable form decision of Launch Interface Ring at preliminary design of COMS. In this study, launch mass and design constraints are investigated. Moreover, optimization algorithm and simplification technique are used. At the beginning of this study, three types of launch interface ring were presented and finally model 3 was the lightest design for resistance of launch environment. Nevertheless, model 1 can be suggested for application to COMS because of the satellite gravity center control and ease of fabrication.

• International Journal of Highway Engineering
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• v.5 no.4 s.18
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• pp.13-22
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• 2003

Several design methods from overseas are employed without considering different conditions such as material properties, climate, and traffic condition in this country. Therefore, there are limitations in application. Therefore, new pavement analysis system which is able to design a pavement efficiently and economically should be set up. In this study, 243 probable sections are classified depending on values of layer thickness and elastic modulus, and the effect of load types for the probable sections are analyzed. The section showing larger load distribution is chosen for analysis. As a result of sensitivity, a layer thickness has more influence on pavement than an elastic modulus does. The stress distribution of FWD test load is larger than that of circular load. This study compares outputs between nonlinear elastic model and linear elastic model. Based on the result, this study finds nonlinear elastic model considering stress condition in the ground is recommended for subbase.