• Journal of Aerospace System Engineering
• /
• v.12 no.3
• /
• pp.70-78
• /
• 2018

This research was carried out to develop an integrated folding wing made from carbon composite materials. Design requirements were reviewed and composite wing sizing was conducted using design optimization with commercial software. Three composite manufacturing processes including hot-press, pultrusion, and autoclave were evaluated and the most suitable processes for the integrated wing fabrication were selected, with consideration given to performance and cost. The determined manufacturing process was verified by two design development tests for selecting the design concept. Stiffness and strength of the composite wing were estimated through structural analyses. The test loads were calculated and static tests about design limit load and design ultimate load were performed using both wings. As a result, the evaluation criterions of the tests were satisfied and structural safety was verified through the series of structural analyses and testing.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.41 no.2
• /
• pp.127-133
• /
• 2013

In this paper, the study for the manufacture of the integrated composite wing is performed. The wing has a pivoting structure and high aspect ratio to increase lift drag ratio. The wing is designed with carbon fiber composite because the wing needs to be light and have sufficient strength and stiffness to satisfy structural design requirements. The number of structural members is decreased by part integration to reduce manufacturing cost and the wing is manufactured with the integrated molding process by an autoclave. The material properties are identified by the coupon tests and the structural strength and stiffness are verified through the component tests.

• Journal of Aerospace System Engineering
• /
• v.16 no.6
• /
• pp.8-17
• /
• 2022

This paper presents a novel geometric modeling technique to predict the mechanical properties of an aircraft wing's skin-stringer integrated panel. Due to mechanical and adhesive fastening, this panel is vulnerable to stress concentration and debonding, so we designed it to integrate the skin and stringer using three-dimensional woven composites. Geometric modeling was conducted by measuring the geometric parameters of the specimen and defining the pattern of the yarns as functions. We used a weighted average model with iso-strain and iso-stress assumptions to predict the mechanical properties of the panel parts. We then compared the results of a finite element analysis with a compression test to verify the accuracy of our model. Our proposed technique proved to be more efficient than the traditional experimental method for predicting the mechanical properties of skin-stringer integrated panels.

• Journal of computational fluids engineering
• /
• v.21 no.3
• /
• pp.48-54
• /
• 2016

In the present work, numerical simulations were conducted on the scaled model of the BWB type UCAV in the subsonic region using ANSYS FLUENT V15. The prediction method was validated through comparison with experimental results and the effect of the twisted wing was investigated. To consider the transitional flow phenomenon, ${\gamma}$ transition model based on SST model was adopted. The coefficients of lift, drag and pitching moment were compared with experimental results and the pressure distribution and streamlines were investigated. The twisted wing decreases the lift force but increases lift-to-drag ratio through delay of stall and leading edge vortex's movement to the front, also the non-linearity of the pitching moment is decreased.

• Journal of the Korea Fashion and Costume Design Association
• /
• v.15 no.3
• /
• pp.41-50
• /
• 2013

This study aims to contribute to development of sanitary pad meeting customers' requirements by examining types, sorts, sizes and specifications of cloth sanitary pads currently sold in the market, and the results are as follows. First, with respect to materials of inside cloth of cloth sanitary pads, in most cases, 100% cotton knit was used as materials of the inside cloth and the pads were finished with knit cotton(including organic cotton) and woven cotton bias. Second, for the structures of the cloth sanitary pads, the Jacquard knits in the shape of beehive or waffle are mostly used. Third, the sizes of cloth sanitary pads were classified with 7 sorts were discovered that can be divided into liner, small-size, medium-size, large-size, overnight, extra overnight, accounting for the most percentage among cloth sanitary pads. Fourth, 11 sorts among cloth sanitary pads whose front and back shapes are the same were discovered, accounting for the most percentage. Fifth, cloth sanitary pads can be largely classified into a wing type, all-in-one type and insertion type, which includes subsidiary absorption layer. 9 sorts were wing types and all-in-one types, accounting for the most and percentage. Compared with the scope of the market for women's articles, there is no relevant study, so this study is expected to provide basic materials for women's articles and contribute to development of environment-friendly products as an alternative to a disposable sanitary pad which not only causes environment pollution but also has bad effects on women's health.

• Proceeding of EDISON Challenge
• /
• 2016.03a
• /
• pp.554-559
• /
• 2016

본 논문은 EDISON CFD를 사용하여 스포일러가 장착된 무미익 BWB UCAV에 대하여 이차원 유동해석을 수행하였다. 무미익 형상은 일반적인 항공기보다 롤과 요 방향의 안정성과 조성성에 있어 불리한 특징을 갖는데 특히 이 착륙 시 고 받음각의 영역에서 발생하는 Pitch-up 현상이 항공기 안정성에 문제를 야기한다. 수직 미익 부재와 pitch-up 현상으로 인한 BWB형상의 UCAV가 지니는 단점을 보완하기 위해서 스포일러가 장착된 형상이 적용되기도 한다 본 연구에서는 윗면과 아랫면에 스포일러가 장착된 경우에 대해 전산유동해석을 수행하였다. 해석결과 윗면의 스포일러는 양력의 감소와 항력의 증가를 야기했으며, 아랫면의 스포일러는 양력과 항력을 모두 증가시켰다. 피칭모멘트의 경우 아랫면의 스포일러가 저받음각에서 안정성을 증가시켰다.