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측방 제트가 아음속 유도탄 종방향 공력특성에 미치는 영향 연구
고범용,허기훈,GO, Beom Yong,HUR, Ki Hoon 한국군사과학기술학회 2017 한국군사과학기술학회지 Vol.20 No.3
Side jet effect on the aerodynamic characteristics of a missile was investigated using experimental and computational methods. A couple of side jets were injected toward outward downstream at mid point of missile body. Cold air jet was used in the wind tunnel test, and cold and hot jet were used in the computation. Wind tunnel test was carried out with jet and without jet, and calculation was performed for three cases ; no jet, cold air jet, and hot mixture gas jet. From the comparison of measured and calculated data for all cases, two points could be deduced. Firstly, side jet made static stability to be unstable by increasing body normal force near the side jet exit and by decreasing tail normal force. Secondly, hot mixture gas had more significant effect on the static stability of a missile-type body than cold air jet.
고범용(B.Y. GO),백연식(Y.S. Baik),이은석(E.S. Lee),이재은(J.E. Lee),허기훈(K.H. Hur) 한국전산유체공학회 2013 한국전산유체공학회 학술대회논문집 Vol.2013 No.5
A control fin is necessary for the flying object in order to satisfy its stability and maneuverability. In general, a tail is selected as a control fin and the control effectiveness of the tail is very important. Therefore, it is required to study the variables which have influence on tail performance. When side jets are located ahead of tails, the flow field around tails has interferences with side jets. So the aerodynamic characteristics of a missile with side jet is different from that of a missile without side jet. In this study, the influences of side jet on the missile aerodynamics are investigated by use of the computational fluid dynamics. The aerodynamic characteristics are found be affected by not only the free stream conditions, e.g. free stream velocity, angle of attack and bank angle but also the jet conditions, e.g. the temperature and gas property of jet.
경사진 전방 접힘 날개의 전개 모델링 및 전개 성능 예측
허진영,고범용,허기훈,이영준,박진석 한국전산유체공학회 2023 한국전산유체공학회지 Vol.28 No.1
This paper deals with the development of prediction method of deployment performance of a inclined forward folding wing. It uses the inclined forward folding wing mechanism, whose motion is three-dimensional. Within the analysis axis, this motion is well described and the governing equation can be well established. External moments, such as the deploying moment due to torsional spring, friction moment, aerodynamic moment, and gravity moments are well modelled and the governing equations is solved numerically. Thus the deployment performance of a inclined forward folding wing can be predicted successfully.
조영태,고범용,이충호,Cho, Young-Tae,Ko, Boum-Yong,Lee, Choong-Ho 한국생산제조학회 2010 한국생산제조학회지 Vol.26 No.1
It was attempted to develop an auto part by over molding injection mold that produces precision products in high productivity with use of an eco-friendly TPE substitute material for NBR. NBR is currently used in motor gear cover, one of the key parts in motor module for auto doors. Gear cover is composed of plastics and rubber mostly today, which requires a two (2) step process for production using two presses of different types. A hot press is used at this time for forming the rubber, which has drawback of requiring a rather long forming time of 400 seconds for one forming process. Even though this difficulty is overcome by reducing production time through employment of multi-cavity molds, time for forming process must be shortened for improvement of the productivity eventually, and the existing method of insert injection for products that have been formed with plastic material must be outgrown. In this point of view, over molding injection using TPE has a big advantage. Forming time is shortened to 54 seconds, and working the two (2) processes in series by one (1) press could solve the durability problem caused by deflection of the plastics, not to mention shortening the process time. Enhancement of productivity by almost 80% and improvement in the accuracy of the product could thus be achieved.
Flush Air Data System Modeling Using DOE-Based Wind-Tunnel Test
이명섭,김상진,고범용,안재명 한국항공우주학회 2023 International Journal of Aeronautical and Space Sc Vol.24 No.2
This paper proposes a procedure to design a flush air data system (FADS) for a stealth aircraft using wind tunnel testing based on the design of experiments (DoE) technique. The FADS of an aircraft reduces its radar cross-section (RCS) by preventing protrusion to its outer mold line (OML). The system acquires air data (e.g., altitude, airspeed, aerodynamic angles) by pressure measurements at multiple static holes. The wind tunnel testing is composed of two steps: the screening test for selecting influential factors and the database test for model construction. The 5-hole probe algorithm is used to predict the aerodynamic data out of pressure measurements. The FADS configuration design/optimization case study (pressure hole selection) is conducted.