1.2톤급 소형 위그선의 구조 안전성 평가에 관한 연구

Abstract

In this study, structural analysis of the main wing, tail plane and fulselage for the small scale WIG(Wing In Ground effect) flight vehicle, which will be a high speed marine transportation system for the next generation, was performed. The high stiffness and strength Carbon-Epoxy material was used for the major structure. The skin-spar with skin-stresssed structural type and the skin-ringframe-longeron 'semi-monocoque' type structure was adopted for improvement of lightness and structural stability. As a structurel design result for this study, the design load was estimated with maximum flight load. In order to investigate the structural safety adn stability, stress analysis was performed by Finite Element Codes such as NASTRAN/PATRAN. 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 bukling load. It was founded that the joint part between the main wing and the skin of fuselage was locally weak on a strength point of view, and the weight of the structure was slightly heavier than the target weight. Therefore in order to solve this problem, three stiffeners at the buckled region were added. After design modification, even though the weight og the wing was a little bit heavier thant the target weight, the structural safety and stability of the design feature was satisfied for design requirements.