http://chineseinput.net/에서 pinyin(병음)방식으로 중국어를 변환할 수 있습니다.
변환된 중국어를 복사하여 사용하시면 됩니다.
Park, Gilsu,Park, Hyunbum Elsevier 2018 COMPOSITE STRUCTURES -BARKING THEN OXFORD- Vol.184 No.-
<P><B>Abstract</B></P> <P>In this study, it was performed structural design and analysis of the automobile bonnet with natural flax composite. The composite structure is weak to external impact damage. Therefore, the structural design through impact damage analysis was performed. For manufacturing flax/vinyl ester applied composite, RTM (resin transfer molding), which is a manufacturing process suitable for light weight and mass production, was applied. The impact test of specimen was performed to analyze the safety of structure from impact. In addition, compression strength test was performed for specimen applied with impact to measure residual strength of structure after impact to analyze structural behavior. Through the structural design and test, it is confirmed that the designed bonnet structure is acceptable.</P>
Park, Gwanglim,Oh, Kyungwon,Kong, Changduk,Park, Hyunbum The Society for Aerospace System Engineering 2014 International Journal of Aerospace System Engineer Vol.1 No.1
Recently, various kinds of study on light weight structure are performing in the world. The Al honeycomb sandwich structural type adopt for improvement of lightness and structural stability to major part structure of aircraft or spacecraft. Adhesion badness properties of adhesive and adhesion properties of fillet mainly studied about al honeycomb structure. But study for adhesive properties of sandwich construction with surface treatment of Aluminum alloy barely performed. In this study, adhesive film was used between Al and honeycomb core of honeycomb panel[1]. The study for adhesive properties of sandwich construction with surface treatment of AA 5052 skin was performed.
Park, Hyunbum The Society for Aerospace System Engineering 2019 International Journal of Aerospace System Engineer Vol.6 No.1
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.