• International Journal of Aerospace System Engineering
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• v.3 no.2
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• pp.1-8
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• 2016

The improvements in high performance and agility of modern fighter aircraft have led to improvements in survivability as well. Related to these performance increases are rapid response and adequate deflection of the control surfaces. Most control surface failures result from the failure of the actuator. Therefore, the failure and behavior of the actuators are essential to both combat aircraft survivability and maneuverability. In this study, we investigate the effects of flaperon actuator failure on flight maneuvers of a supersonic aircraft. The flight maneuvers were analyzed using six degrees of freedom (6DOF) simulations. This research will contribute to improvements in the reconfiguration of control surfaces and control allocation in flight control algorithms. This paper compares the results of these 6DOF simulations with the horizontal tail actuator failures analyzed previously.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.8
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• pp.711-717
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• 2012

During the conceptual design phase of a light sport aircraft, the wind tunnel tests were conducted to investigate the static stability of newly-designed configuration. The 1/5 scale-down wind tunnel model consisted of fuselage, main wing, vertical tail and horizontal tail. The main wing and tails were able to be attached or detached from the fuselage. The aerodynamic forces and moments acting on the 6 different configurations compounding each component were measured by using the internal balance system and their static stability derivatives were derived. With these experimental data, the baseline lift and drag characteristics as well as the effects of each component to the longitudinal, directional and lateral static stability were quantitatively analyzed.

• Wind and Structures
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• v.20 no.4
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• pp.549-564
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• 2015

The three-dimensional unsteady incompressible Reynolds-averaged Navier-Stokes equations and k-${\varepsilon}$ double equations turbulent model were used to investigate the effect on the measurements of anemometers due to a passing high-speed train. Sliding mesh technology in Fluent was utilized to treat the moving boundary problem. The high-speed train considered in this paper was with bogies and inter-carriage gaps. Combined with the results of the wind tunnel test in a published paper, the accuracy of the present numerical method was validated to be used for further study. In addition, the difference of slipstream between three-car and eight-car grouping models was analyzed, and a series of numerical simulations were carried out to study the influences of the anemometer heights, the train speeds, the crosswind speeds and the directions of the induced slipstream on the measurements of the anemometers. The results show that the influence factors of the train-induced slipstream are the passing head car and tail car. Using the three-car grouping model to analyze the train-induced flow is reasonable. The maxima of horizontal slipstream velocity tend to reduce as the height of the anemometer increases. With the train speed increasing, the relationship between $V_{train}$ and $V_{induced\;slipstream}$ can be expressed with linear increment. In the absence of natural wind conditions, from the head car arriving to the tail car leaving, the induced wind direction changes about $330^{\circ}$, while under the crosswind condition the wind direction fluctuates around $-90^{\circ}$. With the crosswind speed increasing, the peaks of $V_X,{\mid}V_{XY}-V_{wind}{\mid}$ of the head car and that of $V_X$ of the tail car tend to enlarge. Thus, when anemometers are installed along high-speed railways, it is important to study the effect on the measurements of anemometers due to the train-induced slipstream.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.7
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• pp.655-663
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• 2010

DUP (direct underside pressurization) is a device that can considerably increase lift, reduce take-off speed and minimize hump drag when a WIG effect vehicle takes off on the water surface. A 3-dimensional numerical investigation of a WIG effect vehicle with DUP is performed to analyze aerodynamic characteristics and the static height stability. The model vehicle, named Aircat, consists of a propeller in the middle of a fuselage, an air chamber under the fuselage, Lippisch-type wings and a large horizontal T-tail. The lift is mainly increased by the stagnation of the accelerated air coming into the air chamber through the channel in the middle of the fuselage. However, the accelerated air increases drag as well as reduces static height stability.

• Journal of Veterinary Clinics
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• v.16 no.2
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• pp.409-412
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• 1999

To establish the electroacupuncture anesthesia for pigs, 6 piglets (Landrace mixed, 1 month old, 3.7~5.3 kg, female: 3 heads and male: 3 heads) were examined. The acupoints used for porcine electroacupuncture anesthesia were An-shen, and Tian-ping and Bai-hui. After horizontal insertion of needle to left and right An-shen, and perpendicular insertion to Tian-ping and Bai-hui, respectively, positive electrode was connected at right An-shen and Tian-ping, and negative electrode was connected at left An-shen and Bai-hui using veterinary electroacupuncture anesthesia apparatus, respectively. Electric condition was 3 V and 30 Hz. To examine the effect of electroacupuncture anesthesia, laparotomy (4 heads) and castration (2 heads)were applied. The induction time of electroacupuncture anesthesia was very rapid and about 1 minute, and pain of the body surface including the extremities was not detected. As for the reactions with electroacupuncture anesthesia, the head was directed to backward, nasal part was curved to one side, and blepharum was closed in part of changed nasal part. In addition, consciousness was vivid, and muscle tension and lift of the tail were observed in early stage but was relaxated afterwards. The pain was not found during incision and suture, bleeding was comparatively small volume and the class of anesthesia effect was excellent.

• Journal of the Society of Naval Architects of Korea
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• v.55 no.1
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• pp.75-82
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• 2018

Wedge-shaped fins are generally used to provide sufficient forces and moments to control and maneuver a supercavitating vehicle. There are four fins placed along the girth of the vehicle, near he tail: two of the fins are horizontal and the other two fins are vertical. In a fully developed supercavitating flow condition, a part of the fin is in a cavity pocket and the other is exposed to water. In this paper, experimental investigations of hydrodynamic characteristics of the wedge-shaped fin models are presented. Experiments were conducted at a cavitation tunnel of the Chungnam National University. We first closely observed the typical formation of wake cavitation and measured lift and drag forces acting on two different test models. Next, using a special device for generating natural and artificial supercavities, we investigated hydrodynamic forces at different cavitation number conditions. This work provides a basis for interpreting the cavity stability and hydrodynamic characteristics of the wedge-shaped control fin for a supercavitating vehicle.

• Journal of Institute of Control, Robotics and Systems
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• v.14 no.9
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• pp.916-924
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• 2008

In this paper dynamic modeling parameters were estimated using a frequency domain estimation method. A systematic flight test method was employed using preprogrammed multistep excitation of the swashplate control input. In addition when one axis is excited, the autopilot is engaged in the other axis, thereby obtaining high-quality flight data. A dynamic model was derived for a small scale unmanned helicopter (CNUHELI-020, developed by Chungnam National University) equipped with a Bell-Hiller stabilizer bar. Six degree of freedom equations of motion were derived using the total forces and moments acting on the small scale helicopter. The dynamics of the main rotor is simplified by the first order tip-path plane, and the aerodynamic effects of fuselage, tail rotor, engine, and horizontal/vertical stabilizer were considered. Trim analysis and linearized model were used as a basic model for the parameter estimation. Doublet and multistep inputs are used to excite dynamic motions of the helicopter. The system and input matrices were estimated in the frequency domain using the equation error method in order to match the data of flight test with those of the dynamic modeling. The dynamic modeling and the flight test show similar time responses, which validates the consequence of analytic modeling and the procedures of parameter estimation.

• Aerospace Engineering and Technology
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• v.12 no.2
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• pp.180-185
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• 2013

In this study, preliminary design of human powered aircraft was performed by considering the aerodynamic performance. For this, overall weight including the aircraft and pilot was determined. Then, the main wing and horizontal/vertical tail were designed with appropriate selection of the airfoils and planform shapes. Based on these, three dimensional flow was calculated to obtain lift and drag coefficients and the position of center of gravity (CG). Consequently, it was shown that the lift and power of the aircraft satisfied the constraints of the minimum required lift and the pilot's available power. Also, the CG of the aircraft was located at aerodynamic center (AC) of the main wing, which guaranteed 26% of the static margin.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.11 no.1
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• pp.5-16
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• 2003

The present study was carried out to develop highly efficient RC ornithopter 'Songgolmae' powered by motor and battery. Designed electric ornithopter, which has the dimension of O.88m(W)${\times}$0.56m(L)${\times}$0.15m(H), is smaller than a conventional ornithopter. This ornithopter weighs 277 grams and has 3 channels radio control. It runs on an electric motor by a lithium polymer battery and has a gear ratio of about 75${\sim}$95 to 1 to flap its 88 cm wingspan. The aerodynamic performance of the ornithopter, applied to a flapping motion only, was validated by flight tests. Flight times have exceeded 23 minutes until the battery was used up. The flight test results indicate that the ornithopter developed here has sufficient thrust to propel itself in a forward flight. From the economical point of view and the handling of the RC ornithopter, it can be said that the developed robot ornithopter is an effective RC ornithopter. This robot ornithopter flies its way high into the sky just like a real bird flies. The robot ornithopter is used for a wide range of missions.

• The Korean Journal of Zoology
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• v.35 no.4
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• pp.518-525
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• 1992

본 연구에서는 horizontal clinostat과 원심분리 방법의 이용으로 각각 저중력 상태($\mu$G)와 고중력 상태(3G)를 유도하여, 중력장의 변화가 양서류 수정란의 초기 형태 형성에 미치는 영향을 북방산개구리(Rano dybows비름를 대상으로 조사하였다. 중력장의 변화는 첫번째 수평 분열인 제3분열면의 위치에 영향을 미쳤다. 즉 저중력 상태에서는 분열면이 적도면 근처에서, 또 고중력 상태에서는 분열면이 동물극 근처에서 형성되었다. 이와 같은 변화는 포배기로 이어져 할강의 위치와 동물극 정단 세포층 수에 영향을 미쳤다. 즉 저중력에 노출된 포배는 정상배(1G)에 비해 할강이 중앙에 위치했으며 동물극 정단의 세포층 수가 증가하는 반면 고중력에 노출된 포배는 할강이 보다 동물극 폭에 위치했으며 동물극 정단의 세포층 수도 감소하였다. 그러나 낭배기에 도달하면 동물극 정단 세포층 수의 차이는 정상 상태로 조절되었다. 한편 중력장의 변화는 낭배기에 이르는 발생 속도와 원구상순부의 위치를 변경시켰다. 낭배기 이후의 발생 단계에서 중력에 의한 변화로는 tail fin circulation(stage 22)시기의 머리크기의 변화를 들 수 있다. 이상의 결과로 무미 양서류의 초기 형태 형성은 중력장에 의해 변형될 수 있으며 이러한 변화는 발생이 진행됨에 따라 조절되는 것으로 보인다.