• 한국항공우주학회지
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• 제30권2호
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• pp.108-114
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• 2002

본 연구에서는 KSR-Ⅲ 로켓의 날개-동체 조인트에 대한 비선형 유한요소해석을 수행하므로 적절한 설계 개선을 제시하였으며, 최종 설계의 검증을 위해 수행된 구조 시험 결과와 비교하여 해석의 타당성을 평가하였다. 날개-동체 조인트는 동체 프레임 상에 존재하는 체결 홈에 날개의 체결부가 끼워짐으로 연결되는 방식으로 설계되었다. 이 방식은 연결 구조물간의 하중 전달을 주로 구조물간의 접촉면을 통해 이루어지게 하며, 체결 볼트를 통해서는 구조물을 고정하되 전달 하중은 최소화하기 위한 것이다. 조인트 구조의 정확한 해석을 위해 연결 구조물간의 접촉 및 체결 볼트를 통한 하중 전달을 묘사할 수 있는 세심한 구조 모델링을 적용하였다. 해석 결과에 의해 제시된 설계 개선은 구조시험을 통해 안전성이 검증되었으며, 해석 및 시험 결과가 잘 일치하였다.

• 항공우주시스템공학회지
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• 제1권1호
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• pp.36-44
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• 2007

This study was performed on preliminary structural design of a small scale WIG craft which has been developed as a next generation high speed maritime transportation system in Korea. A composite structure design using the foam-sandwich for main wing and tail fins and the honeycomb sandwich and skin-stringer-ring frame for fuselage was applied for weight reduction as well as structural stability. A commercial FEM code, NASTRAN for was utilized to confirm the structural safety for the reiterate design modifications to meet design requirements including the target weight. Each main wing was jointed with the fuselage by eight high strength insert bolts for easy assembling and disassembling as well as for assuring the required 20 years service life. For control surface structural design, the channel type spar, the foam sandwich skin and the lug joint were adopted.

• 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.