• Journal of the Korean Society for Aviation and Aeronautics
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• v.5 no.1
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• pp.65-79
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• 1997

In this study, we deviced side warning system that is necessary to the ground operation of aircraft. The system consist of obstacle detection part, transmission part, receive part, and warning part. We used TOF(Time Of Flight) method using 40kHz ultrasonic wave as the obstacle detection part. The 447MHz RF module was applied to the transmission and receive part. The warning part is activated by the computer using received distance data. The detection system attach to the left/right side edge of main wing and horizontal stabilizer. We have decided 10m obstacle detection range. The result of experiment was satisfactory.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1995.11a
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• pp.159-167
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• 1995

본 연구는 유도탄 비행시험시에 연소관의 스커트와 날개 장착용 브라켓에 작용하는 공력하중과 연소관에 내압이 동시에 작용하는 추진기관에 대하여 구조 해석하였다. 추진기관의 스커트부 및 브라켓부의 공력하중은 3차원적으로 작용하기 때문에 대칭성을 이용한 $180^{\circ}C$3차원 구조 해석을 수행하여 비행시험, 수압시험, 지상시험 모드에 대하여 응력 수준을 비교하였다. 해석 결과 3가지 모드의 최대 등가응력은 거의 같으며, 비행시험시 공력하중이 앞마개부에 미치는 영향은 최대 등 가응력의 6%이내로 상당히 작았다. 수압시험 모드와 지상시험 모드의 실험치와 해석치를 비교한 결과 정확한 해석을 위해서는 점화기를 모델링과 점화기와 연소관, 브라켓과 연소관에 접촉요소의 적용, 3차원 비선형 해석등 보다 상세한 해석이 필요함을 알 수 있었다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.9
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• pp.708-713
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• 2013

KARI is developing a solar-electric powered HALE UAV(EAV-3). For demonstrating the technology, EAV-2H, a down-scaled version of EAV-3, is developed and after EAV-2H's initial flight test, the directional stability and control need to be improved. Thus, the vertical tail and rudder of EAV-2H are redesigned with Advanced Aircraft Analysis(AAA). Size of the rudder is increased from mean chord ratio of rudder to vertical tail, $C_r/C_v(%)=30$ to $C_r/C_v(%)=60$ and size of the vertical tail is reduced 15%. As a result, the directional control to side wind($v_1$) is improved to sideslip angle, ${\beta}(deg)=25^{\circ}$ and $v_1(m/sec)=3.54$. Also, variation of airplane side force coefficient with sideslip angle ($C_{y_{\beta}}$) and variation of airplane side force coefficient with dimensionless rate of change of yaw rate ($C_{y_r}$) are reduced 15% and 22%, respectively to minimize the effect of side wind. The empennage design of EAV-2H is verified with flight tests and applied to design of KARI's solar-electric-powered EAV-3.

• Ocean and Polar Research
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• v.26 no.3
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• pp.425-431
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• 2004

The study focuses on the morphology of larval and juvenile codlets, Bregmaceros atlanticus, collected from the East China Sea in May 2001 and September 2002. A total of 47 individuals were collected by using an IKMT, and the range of their body lengths was $2.41{\sim}17.18$ mm. Specimens can be categorized into two groups: larvae and juvenile. The first group, in which the yolk is completely absorbed, had a body length of 2.41m. They had big heads, and large and thick melanophores were sparsely scattered about the head, bottom of the pectoral fins, rear parts of the trunk and ends of the notochords. The specimens had a body length of 2.54mm and over, and thin and elongated body trunks. Their heads were significantly smaller, including the body depth, and melanophores were coarsely developed all over their bodies. Occipital rays, the first and unique-ray dorsal fin, were observed on individuals of body length greater than 4.01 m, and the rays grew proportionally with body length, but didn't reach the root of the second dorsal fin. The second group, juveniles, had an body length of 9.82mm and over, and their fin rays satisfied the completed numbers of rays and vertebrae for adults. Melanophores were densely scattered all over the body, where thick colors were observed on the rear parts of the dorsal and anal fins and front part of the caudal fin.

• Journal of the Korean Society of Food Science and Nutrition
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• v.44 no.7
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• pp.1028-1034
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• 2015

General composition and cholesterol contents of chicken 4 parts (breasts, thighs, legs without skin, and wings with skin) were analyzed. Fatty acids, amino acids, and mineral contents of breasts and thighs were also analyzed and compared with sirloin parts of beef and pork. Lipid contents of chicken parts (1.2% in breasts, 2.8% in thighs, and 14.9% in wings) were lower than those of beef and pork. Protein contents of chicken parts (22.9% in breasts, 19.7% in thighs, and 17.6% in wings) were higher than those of beef and pork. Cholesterol contents of chicken parts (99.0 mg% in wings, 80.8 mg% in thighs, and 56.7 mg% in breasts) were higher than those of beef and pork. However, saturated fatty acid contents of chicken (31.6~32.9%) was lower than those of beef (40.8%) and pork (42.7%). In the meanwhile, unsaturated fatty acid contents of chicken (67.1~68.4%) was higher than those of beef (59.2%) and pork (57.3%). Essential fatty acid contents of chicken (16.6~16.9%) were 1.6 times as high as that of pork (10.4%) and 5 times as high as that of beef (3.9%). Major amino acids composition were glutamic acid, aspartic acid, lysine, and leucine. Ten essential amino acid contents were 11,860 mg% in breasts and 10,454 mg% in thighs, and the ratio of essential amino acids (41.7~44.1%) was similar to those of pork and beef. Mineral contents of chicken were similar to those of pork and beef despites of slight different mineral contents in thighs and breasts.

• 공원문화
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• s.84
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• pp.12-13
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• 2009

바람은 지리산 자락으로 숨어들다 바위틈에 몸을 놓고 살을 부비며 친한 척 너스레다. 그렇지만 천년을 한결 같은 지리산 아니던가. 그 웅장한 자태를 짐짓 바꿔 바람을 맞을 리 없다. 지친 날개를 달래듯 한 숨 돌린 바람은 칭얼대듯 몇 번 더 휘돌다 짐짓 앵돌아진 계집아이처럼 등성이로 꼭대기로 휘휘 날아 논다. 무턱 없이 부는 바람을 따라 가노라니 어느덧 지리산 국립공원 사무소에 닿았다. 나공주 소장님의 반가운 웃음과 소승호 분소장님 등의 인사와 함께 궁금증을 참지 못한 박종규 기자의 문답이 이어졌다.

• Proceedings of the KIPE Conference
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• 2010.11a
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• pp.250-251
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• 2010

본 연구는 수평축(horizontal axis) 풍력 터빈에 의해서 수직축 발전기를 운전하는 구조 및 그 운전 방식에 관한 것으로서 바람에 의해 수평축 터빈 로터로 입력된 회전력을 기계적으로 두 개의 수직축 회전 성분으로 변환하여 이들로부터 전기 에너지를 얻어내고 필요에 따라 터빈 날개가 바람이 부는 방향을 향하도록 yaw-axis 제어를 하는 기술에 관한 것이다.

• Journal of Aerospace System Engineering
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• v.18 no.4
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• pp.10-17
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• 2024

Solar-powered unmanned aerial vehicles(SPUAV), which are being actively developed domestically and internationally, generally feature high aspect ratio(AR) wings. These high AR wings necessitate a lightweight design as their weight increases, rendering them susceptible to flutter. Consequently, flutter analysis is critical from the initial design phase. Typically, flutter analysis is conducted using a standard section wing or more precisely through a 3D model. However, due to the extended analysis time required by 3D models, this study opts for a 2D aircraft model. The 2D model computes faster than the 3D model and intuitively secures the flutter boundary. In this study, a structural/aerodynamic force model of the 2D aircraft was established, and the findings were compared with those from a 3D half model. The results showed that the flutter analysis between the 2D model and the 3D half model was similar, within about a 3% margin, thus validating the proposed 2D model's effectiveness.

• Journal of Power System Engineering
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• v.16 no.1
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• pp.44-50
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• 2012

팁 간격의 크기가 냉각탑용 축류팬의 성능과 누설 유동에 미치는 영향을 조사하기 위해서 서로 다른 2가지 팁 간격을 가진 경우에 대해서 점성유동을 해석하였다. 케이싱 내에서 작동하는 축류팬 주위의 유동을 연속방정식, Navier-Stokes 방정식 등을 지배방정식으로 사용하여 수치해석 하였다. 난류유동에 나타나는 레이놀즈 응력은 ${\kappa}-{\epsilon}$ 난류모델을 사용하여 계산하였다. 전체적으로 H형 격자계를 사용하였으며, 팁 주위의 유동을 해석하기 위해서 팁 영역 주위에 부분적으로 조밀한 격자를 두었다. 팁 간격이 증가하면 누설 유동의 증가로 인한 유동 손실의 증가로 전압상승과 수력효율이 감소하였다. 팬 직경에 대한 팁 간격이 0.4%에서 1.0%로 증가하면 전압상승 값이 약 10% 정도 감소하였으며, 수력효율은 약 3% 정도 감소하였다. 팁 간격이 팁 근처 날개 주위의 압력에 미치는 영향을 보면, 팁 간격이 증가하여 누설 유동이 증가하면 흡입면과 압력면의 압력차가 전연 부근에서 감소함을 알 수 있었다. 누설 와류의 중심은 코드를 따라서 흡입면으로 부터 떨어져 나가면서 형성됨을 알 수 있었다. 누설 와류의 위치를 보면 팁 간격이 증가하면 와류 중심의 위치가 흡입면 쪽으로 이동하고, 흡입면에서 떨어진 거리도 날개 후반부에서 증가 폭이 커지는 포물선 형태로 증가함을 알 수 있었다.

• Journal of the Korean Society of Propulsion Engineers
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• v.13 no.2
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• pp.26-34
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• 2009

Secondary flow losses can be as high as 30~50% of the total aerodynamic losses for a turbo-machinery blade or stator row. These are important part for improving a turbine efficiency. Therefore, many studies have been performed to decrease the secondary flow losses. The present study deals with the chamfered leading-edge at a generic wing-body junction to decrease the horseshoe vortex, one of factors to generate the secondary flow losses, and investigates the vortex generation and the characteristics of the horseshoe vortex with the chamfered height, and depth of the chamfer by using $FLUENT^{TM}$. It was found that the total pressure loss for the best case can be decreased about 1.55% compare to the baseline case.