• International Journal of Aerospace System Engineering
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• 제4권2호
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• pp.1-4
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• 2017

This work dealt with design and manufacturing of WIG vehicle wing using carbon/epoxy composite materials. In this study, structural design and analysis of carbon composite structure for WIG craft were performed. Firstly, structural design requirement of wing for WIG vehicle was investigated. After structural design, the structural analysis of the wing was performed by the finite element analysis method. It was performed that the stress, displacement and buckling analysis at the applied load condition. And also, manufacturing of subscale wing using carbon/epoxy composite materials was carried out. After structural test of target structure, structural test results were compared with analysis results. Through the structural analysis and test, it was confirmed that the designed wing structure is safety.

• Advanced Composite Materials
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• 제17권4호
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• pp.343-358
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• 2008

This present study provides the structural design and analysis of main wing, horizontal tail and control surface of a small scale WIG (Wing-in-Ground Effect) craft which has been developed as a future high speed maritime transportation system of Korea. Weight saving as well as structural stability could be achieved by using the skin.spar.foam sandwich and carbon/epoxy composite material. Through sequential design modifications and numerical structural analysis using commercial FEM code PATRAN/NASTRAN, the final design structural features to meet the final design goal such as the system target weight, structural safety and stability were obtained. In addition, joint structures such as insert bolts for joining the wing with the fuselage and lugs for joining the control surface to the wing were designed by considering easy assembling as well as more than 20 years service life.

• 한국항공우주학회지
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• 제46권6호
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• pp.471-478
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• 2018

본 연구에서는 복합재 날개 구조물에 손상허용설계를 적용하고 이를 입증하기 위한 정하중 시험을 수행하였다. 복합재 날개 구조의 정적강도를 입증하기 위하여 5 조건의 설계 제한하중 시험과 3 조건의 설계 극한하중 시험을 수행하였다. 그 다음으로 손상허용 설계를 입증하기 위하여 관련 규정에 따라서 복합재 주익 주요 취약부위에 BVID 10개, Open hole 11개를 생성 후, 설계 극한하중 시험과 파단시험을 실시하였다. 날개 주요 부위의 변위 및 변형률 시험 결과는 구조해석 결과와 비교적 잘 일치하였으며, 파단시험의 최초 파단부위도 최소안전여유를 갖는 부위에서 발생하여 구조해석 모델 및 강도평가 결과가 실제 구조의 정적 거동과 유사함을 확인하였다.

• 한국정밀공학회지
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• 제30권10호
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• pp.1061-1068
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• 2013

In this research, the design optimization of a composite sandwich has been performed for using as an airplane wing skin. Automated analysis framework for aero-structure interaction is used for calculating load data on the wing. For automated analysis framework, FLUENT is used for computational fluid dynamics (CFD) analysis. CFD mesh is generated automatically by using parametric modeling of CATIA and GAMBIT. A computational structure mechanics (CSM) mesh is generated automatically by the parametric method of the CATIA and visual basic script of NASTRAN-FX. The structure is analyzed by ABAQUS. Composite sandwich optimization is performed by NASTRAN SOL200. Design variables are thicknesses of the sandwich core and composite skin panel plies. The objective is to minimize the weight of the wing and constraints are applied for wing tip displacement, global failure index and local failure indexes.

• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2005년도 추계학술발표대회 논문집
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• pp.179-184
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• 2005

In the present study, conceptual design of the main wing for 20 seats WIG{wing in Ground Effect) flight vehicle, which will be a high speed maritime transportation system for the next generation, was performed. The high stiffness and strength Carbon-Epoxy material was used for the major structure and the skin-spar with a foam sandwich structural type was adopted for improvement of lightness and structural stability. As a design procedure for this study, firstly the design load was estimated with maximum flight load, and then flanges of the front and the rear spar from major bending load and the skin structure and the webs of the spars were preliminarily sized using the netting rules and the rule of mixture. In order to investigate the structural safety and stability, stress analysis was performed by Finite Element Codes such as NASTRAN/PA TRAN[6] and NISA II [7]. From the stress analysis results, it was confirmed that the upper skin structure between the front spar and rear spar was very unstable for the buckling. Therefore in order to solve this problem, a middle spar and the foam sandwich structure at the upper skin and the web were added. After design modification, even thought the designed wing weight was a little bit heavier than the target wing weight, the structural safety and stability of the final design feature was confirmed. Moreover, in order to fix the wing structure at the fuselage, the insert bolt type structure with six high strength bolts was adopted for easy assembly and removal.

• International Journal of Aerospace System Engineering
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• 제6권1호
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• pp.1-7
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• 2019

In the present study, structural safety and stability on the main wing and tail planes of the 1.2 ton WIG(Wing in Ground Effect) flight vehicle, which will be a high speed maritime transportation system for the next generation, was performed. The carbon-epoxy composite material was used in design of wing structure. The skin-spar with skin-stressed structural type was adopted for improvement of lightness and structural stability. As a design procedure for this study, the design load was estimated with maximum flight load. From static strength analysis results using finite element method of the commercial codes. From the stress analysis results of the main wing, it was confirmed that the upper skin structure between the second rib and the third rib was unstable for the buckling load. Therefore in order to solve this problem, three stiffeners at the buckled region were added. After design modification, even though the weight of the wing was a little bit heavier than the target weight, the structural safety and stability was satisfied for design requirements.

• 한국항공우주학회지
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• 제32권3호
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• pp.74-81
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• 2004

복합재 주익을 실험용 경항공기급에 적용하기 위하여, 복합재료의 특성과 제작공정을 고려한 일련의 기본 설계와 해석과정을 보이고 그 결과를 수록하였다. Schrenk 방식 (NACA TM No. 948) 과 FAR part 23 Appendix A의 근사방법을 이용하여 공력하중해석을 수행하였으며, 이에 의거한 구조하중 조건을 만족함과 동시에 복합재 구조의 장점을 반영할 수 있도록 주요 부재를 배치하였다. 제작공정과 동일한 조건에서 성형된 시편들에 대해 실험을 수행하여 선정재료의 설계기준치를 확보하였고, 단순화된 상자형 날개보에 대해 최대 변형 률 파괴기준식을 적용하여 구조의 안전도를 평가하였다.

• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2004년도 춘계학술발표대회 논문집
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• pp.75-78
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• 2004

Traditionally aluminum alloy have been used in manufacturing of aircraft structures, and semi-monocoque structural concept have been mainly applied in structural design of fuselage and wing. However, recently monocoque structural concept is applied in many small-size aircraft structures manufactured with composite materials. In such case appling monocoque structural concept, in initial conceptual design stage on wing, it is not easy to analyze shear flow using classical shear flow analytical method because composite skin structure can support span-wise tension/compression stress as well as sectional shear stress. In this study, an extended shear-flow analytical method to apply to composite monocoque structural concept was developed through extending the classical shear-flow analytical method.

• International Journal of Aerospace System Engineering
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• 제8권2호
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• pp.1-3
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• 2021

This study proposed a specific preliminary structural design procedure of the main wing for a small scale WIG vehicle to meet the target weight of the system requirement. The high stiffness and strength Carbon-Epoxy material was used for lightness, and the foam sandwich type structure at the upper skin and the spar webs was adopted for improvement of structural stability. After structural design, wing joint part was designed. Through investigation on structural design result, design modification was performed. After design modification, even thought the designed wing weight was a little bit heavier than the target wing weight, the structural safety and stability of the final design feature was confirmed.

• Composites Research
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• 제30권1호
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• pp.52-58
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• 2017

본 논문에서 제시한 복합재 날개 구조물의 최적설계 기법은 파손모드를 통합한 최적화 프레임 웍을 사용하여 복합재 날개 구조물의 안전율을 자동으로 계산한다. 개발된 최적화 프레임 웍은 복합재 구조물의 설계요소에 가장 큰 영향을 주는 파손모드 즉, 최초 파손모드, 좌굴 파손 모드 및 베어링-바이패스 파손을 확인하여 구축된 적층 데이터베이스 안에서 적층수를 찾아낸다. 이는 개발과정에서 수정 및 반복되는 설계 및 해석 시간을 단축시킬 수 있는 효과가 있다. 설계변수는 계단형태로 이루어진 적층 데이터베이스이며 응답은 변형률, 좌굴, 볼트 주변부의 응력장이며 목적함수는 날개구조의 질량이다. 그리고 최적화 프레임 윅을 구동하는 Composite Optimizer의 해석결과를 검증하기 위하여 유한요소모델의 좌굴해석 결과와 비교하여 유효성을 검증하였다.