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신정우,박상욱,이무형,김태욱,Shin, Jeong Woo,Park, Sang Wook,Lee, Mu-Hyoung,Kim, Tae-Uk 한국항공운항학회 2014 한국항공운항학회지 Vol.22 No.2
There are several methods to improve the flight efficiency of HALE(High Altitude Long Endurance) UAV(Unmaned Aerial Vehicle). Airframe structural point of view, weight reduction of the airframe structure is the most important method to improve the flight efficiency. In order to reduce the weight of airframe structures, new concepts which are different from traditional airframe structure design such as the mylar wing skin should be introduced. The spar is the most important component in a mylar skin wing structure, so the spar weight reduction is the key point for reduction of the wing structural weight. In this study, design trade-off study for the front spar of the HALE UAV wing is conducted in order to reduce the weight. Design and analysis procedure of high aspect ratio wing spar are introduced. Several front spar structures are designed and trade-off study regarding the weight and strength for the each spar are performed. Spar design configurations are verified by the static strength test. Finally, optimal front spar design is decided and applied to the HALE UAV wing design.
신정우,김성찬,김성준,채동철,이상욱,김태욱,심재열,Shin, Jeong-Woo,Kim, Sung-Chan,Kim, Sung-Jun,Chae, Dong-Chul,Lee, Sang-Wook,Kim, Tae-Uk,Shim, Jae-Yeul 한국군사과학기술학회 2006 한국군사과학기술학회지 Vol.9 No.4
In this paper, full-scale airframe static test of 4-seater canard airplane(the Firefly) was explained. From the results of the structural analysis, 5 design limit loads test conditions and 11 design ultimate loads test conditions were selected. Test loads analysis was performed and test fixtures and load control system(LCS) were prepared to realize the test loads. To protect the test article during the test, the overload protection system was prepared. Strain and deflection values were acquired through the data acquisition system(DAS) to verify the structural analysis results.
멜트블로운 폴리프로필렌/실리카 에어로겔 부직포의 제조와 단열 특성 분석
신정우,정영규,Shin, Jung Woo,Jeong, Young Gyu 한국섬유공학회 2018 한국섬유공학회지 Vol.55 No.6
To develop heat insulation fabrics with lightweight, low volume and excellent thermal insulation properties, in this study, a binder-free polypropylene/silica aerogel nonwoven fabric with an area density of ${\sim}79.7g/m^2$ was fabricated via a facile melt-blowing process, and its structure, thermal conductivity and thermal insulation properties were investigated. For comparison, a polyester hollow fiber nonwoven having a similar area density of ${\sim}84.6g/m^2$ was prepared by needle-punching. Additionally, a series of composite nonwoven fabrics was prepared by layering the melt-blown polypropylene/silica aerogel nonwoven and the polyester hollow fiber nonwoven in various combinations, and their thermal insulation properties and thermal conductivity were analyzed. Scanning electron microscopic analyses revealed that 5 wt% silica aerogel added during the melt-blown process was adhered well to polypropylene fiber surfaces of the nonwoven fabric. As a result, the melt-blown polypropylene/silica aerogel nonwoven fabric exhibited a low thermal conductivity of $43mW/m{\cdot}K$ and relatively high level of thermal insulation performance, although its thickness (~1.5 mm) was lower than that (~2.2 mm) of needle-punched polyester hollow fiber nonwoven with a similar area density. The thermal conductivity was lowered and thermal insulation performance was improved, as the melt-blown polypropylene/silica aerogel nonwoven fabric was layered. It was also found that increasing the number of melt-blown polypropylene/silica aerogel nonwoven fabric layers in the composite nonwoven fabrics layered in various combinations decreased the thermal conductivity and improved the thermal insulating properties.
고고도 장기체공 태양광 무인기 EAV-3 기체구조 개발
신정우,박상욱,이상욱,김태욱,Shin, Jeong Woo,Park, Sang Wook,Lee, Sang Wook,Kim, Tae-Uk 한국항공운항학회 2017 한국항공운항학회지 Vol.25 No.3
Research for solar-powered high altitude long endurance(HALE) UAV was conducted by Korea Aerospace Research Institute(KARI), and the EAV-3 with 19.5m wing span was developed. For HALE flight, aircraft should be lightly designed. Especially, airframe structure that accounts for a large portion of the total weight of aircraft should be lightweight. In this paper, development process of airframe structure for solar-powered HALE UAV, EAV-3, is described briefly. Domestic developed T-800 grade CFRP(Carbon Fiber Reinforced Plastic) composite material with high modulus and strength was used to design main load carrying structures. Flightloads analysis that takes into account large structural deformation was carried out. Stress and flutter analyses for airframe structure sizing were conducted. Static strength test for main wing and aircraft ground vibration test were conducted successfully and structural integrity was secured.
論文(논문) : 중형항공기 주익 구조개발 선행연구를 위한 비행하중해석
신정우 ( Jeong Woo Shin ),강왕구 ( Wang Gu Kang ),김성준 ( Sung Joon Kim ),황인희 ( In Hee Hwang ) 한국항공운항학회 2011 한국항공운항학회지 Vol.19 No.4
For loads analysis of airplane, applicable regulation should be determined. Then, loads conditions are prepared from the regulation. Modeling for aerodynamic, mass, and structure are performed. Panel method is usually adopted for aircraft loads analysis to obtain air loads. The ARGON which is a multidisciplinary fixed wing aircraft design software co-developed by the KARI and TsAGI are used for loads analysis. The ARGON can be utilized for flutter and stress analysis as well as for flight and ground loads analysis. In this paper, flight loads analysis for wing structural design of the regional aircraft at the conceptual design phase are performed with the ARGON. FAR 25 is used for the regulation for the load analysis. Shear force, bending moment and torsion diagrams for the wing and shear force and hinge moment for the aileron are presented.
신정우(Jeong Woo Shin),김태욱(Tae-Uk Kim),김성찬(Sung-Chan Kim),황인희(In-Hee Hwang),이정선(Jeong-Sun Lee) 대한기계학회 2010 대한기계학회 춘추학술대회 Vol.2010 No.11
Role of landing gear is to absorb the energy which is generated by aircraft ground maneuvering and landing. Generally, in order to absorb the impact energy, oleo-pneumatic type shock absorber is used in aircraft landing gear. For the rotorcraft landing gear development, it is necessary to conduct static strength test in order to verify structural integrity. The objective of the static test is to prove the structural integrity and justify the static strength of the rotorcraft landing gear when submitted to the limit and ultimate loads. For static strength test, first, test conditions selection and test load analysis were conducted. Then, the loading system and load control system (LCS) were prepared to apply the test load to the landing gear, and data acquisition system (DAS) was prepared to measure the test data. At limit load tests, any permanent deformation which is detrimental to the safe operation of the landing gear is considered as a failure. At ultimate load tests, a failure is considered if the landing gear is unable to support the ultimate loads for a minimum of 3 seconds.
고고도 장기체공 무인기 고세장비 초경량 주익 정적구조시험
신정우(Jeong Woo Shin),박상욱(Sang Wook Park),김태욱(Tae-Uk Kim) 대한기계학회 2018 大韓機械學會論文集A Vol.42 No.2
고고도 장기체공 무인기의 세장비가 큰 초경량 주익은 작용하중이 작고 변형이 큰 특징이 있다. 때문에, 기존의 유압작동기를 이용한 구조시험 기법을 적용하기 어렵고 새로운 개념의 적용이 필요하다. 본 논문에서는 고고도 장기체공 무인기 고세장비 초경량 주익의 정적구조시험에 대해 간략히 기술한다. 작용하중이 작으므로 작동기를 사용하지 않고 추를 이용하여 하중을 부가한다. 시험체의 상면이 아래로 향하도록 크레인에 설치하고, 지상에서 각 단계별 시험하중에 해당하는 추를 시험체에 장착한 후 크레인을 이용해 시험체를 상승시켜 하중을 부가하는 방식을 채택하였다. 주익의 주요부위에 변형률 게이지를 장착하고 변위를 측정하기 위해 변위 게이지를 장착하였다. 설계제한하중 하에서 주 하중부재의 좌굴 및 파손이 발생하지 않았으며, 설계극한하중 하에서 주 하중부재의 파손이 발생하지 않았다. The ultra-lightweight wing with a high aspect ratio of high altitude long endurance (HALE) UAV is characterized by small airloads and large deflections. Thus, the existing structural testing concepts whereby hydraulic actuators are used are difficult to apply, and a new testing concept is required. In this paper, the static strength test for the ultra-lightwing with a high aspect ratio of HALE UAV is shown briefly. Test loads are applied with dead weight because of the small test loads. The test specimen is installed such that upper surface faces down at the crane; then, the test specimen is lifted up with dead weight until test loads are applied to the test specimen. Strain gages and deflection transducers are installed on the test specimen to measure the strains and deflections, respectively. No buckling and failure of the main loading parts occurred under design limit load, and no detrimental failure of the main loading parts occurred under the design ultimate load.