• 소음진동
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• 제7권5호
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• pp.819-826
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• 1997

The finite element analyses of a composite hingeless rotor blade in forward flight have been performed to investigate the influence of blade design parameters on the blade stability. The blade structure is represented by a single cell composite box-beam and its nonclassical effects such as transverse shear and torsion-related warping are considered. The nonlinear periodic differential equations of motion are obtained by moderate deflection beam theory and finite element method based on Hamilton principle. Aerodynamic forces are calculated using the quasi-steady strip theiry with compressibility and reverse flow effects. The coupling effects between the rotor blade and the fuselage are included in a free flight propulsive trim analysis. Damping values are calculated by using the Floquet transition matrix theory from the linearized equations perturbed at equilibrium position of the blade. The aeroelastic results were compared with an alternative analytic approch, and they showed good correlation with each other. Some parametric investigations for the helicopter design variables, such as pretwist and precone angles are carried out to know the aeroelastic behavior of the rotor.

• 한국항공운항학회지
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• 제20권1호
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• pp.55-65
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• 2012

An airman licensing system is central to the establishment and management of a state's airman licensing which gives official privileges to a person to perform specific activities by evaluating applicant's knowledge and proficiency. In recent decades, the level of the domestic aviation industry continues to leap forward and state's airman licensing system has also been advanced. However, accidents caused by pilot human errors are still occurring. In particular, the pilot occupations require a lot of experience and knowledge and the student pilots receiving the initial flight training have formed their own flight habits based on knowledge, skill, training methods, procedures, etc learned from the flight instructor. This paper discusses possible ways on the improvement for the domestic flight instructor rating by analyzing domestic and international rules and procedures for a flight instructor rating.

• 한국항공우주학회지
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• 제35권1호
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• pp.18-26
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• 2007

날개들이 편대를 이루면서 비행하는 경우의 정상상태 공력특성에 대하여 와류격자법을 이용하여 해석하였다. 2개의 날개가 편대 비행 상태에 있을 때, 선도 날개에 의하여 후방 날개의 부분 양력계수가 높아짐을 알 수 있었다. 3개 이상의 날개를 일렬 및 V자편대 배치하여 양항비에 대하여 해석하였는데, 날개가 편대의 후방에 위치할수록 커지고, 가로 간격이 벌어질수록 작아짐을 알 수 있었다. 가로세로비가 증가할수록 전방 날개와 후방 날개의 양항비 차이가 커짐을 알 수 있었다. 후방 날개의 높이를 변화시켰을 경우, 같은 높이에서 최대 양항비를 나타내었다. 3개, 9개, 15개의 날개를 편대 비행했을 경우 날개 수가 많아질수록 편대 비행의 이득이 증가함을 알 수 있었다.

• 한국항공우주학회지
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• 제38권6호
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• pp.519-529
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• 2010

본 연구에서는 주로터, 동체, 그리고 꼬리로터를 포함한 UH-60A 전기체 형상에 대한 비정상 유동 해석을 수행하였다. 개발된 로터해석용 유동 해석코드를 이용하여 고속 전진 비행 및 저속 전진비행 조건에 대한 해석을 수행하였으며, 해석코드의 검증을 위해 주로터에서의 비정상 공력 하중을 비행시험 및 타 연구자들의 해석 결과와 비교하였다. 주로터만 존재하는 형상, 주로터와 동체만 존재하는 형상, 그리고 꼬리로터만 존재하는 형상에 대한 해석 결과를 전기체 형상에 대한 해석 결과와 비교함으로써 헬리콥터 각 컴포넌트 간의 공기력 간섭현상을 분석하였다. 동체는 주로터에서 발생하는 내리흐름 분포를 변화시킴으로써 주로터의 수직력 분포를 변화시키는 요인이 됨을 확인하였으며, 주로터 끝단으로부터 발생한 와류와 꼬리로터 블레이드가 충돌함에 따라 강한 간섭현상이 발생함을 확인하였다

• 한국운동역학회지
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• 제13권3호
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• pp.47-65
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• 2003

The purpose of this study was to investigate the differences of the kinematical and the kinetical factors that calculated from preflight to postflight of salto forward straight 3/2 turn motion between skitters and less-skitters. four S-VHS video cameras operating at 60Hz were used to record the performances. five elite male gymnasts were participated in this study as subjects. three-dimensional coordinates of 20 body landmarks during each trial were collected using a Direct Linear Transformation method. The digitized body landmarks were smoothed using a Butterworth second order with low pass digital filter and a cutoff frequency of 10Hz. 1. A skitter, got a high score for performance, showed shorter time and faster horizontal velocity than a less-skitter at the board contact. also, a skitter extended quickly his knee and hip joint after contacting board for preflight phase. 2. A skitter revealed faster time and horizontal velocity the vault from taking off board than a less-skiller. A skitter took a long time and high distance to get the vertical peak compared with a less-skiller. 3. For the second phase, a skitter, who executes the most optimal motions among the subjects, displayed a long flight time, a high height, and a far flight distance as well as maintaining consistent horizontal speed even at the peak of post flight. On the other side, a less-scorer displayed a slow vertical velocity, distance and a short time at the point of take-off from vault as well as low height at the peak of post flight.

• Design & Manufacturing
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• 제11권3호
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• pp.41-45
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• 2017

Drones can be manipulated in a variety of ways. One of the most common controller is joystick method. But joystick controller uses both hands and takes a long time to learn. Particularly, in the case of 8-character flight, it is necessary to use both front and rear flight (pitch), left and right flight (Roll), and body rotation (Yaw). Joystick controller has limitations to intuitively control it. In particular, when the main body rotates, the viewpoint of the forward direction is changed between the drones and the user, thereby causing a mental rotation problem in which the user must control the rotating state of the drones. Therefore, we developed a motion matching controller that matches the motion of the drones and the controller. That is, the movement of the drone and the movement of the controller are the same. In this study, we used a gyro sensor and an acceleration sensor to map the controller's forward / backward, left / right and body rotation movements to drone's forward / backward, left / right, and rotational flight motion. The motor output is controlled by the throttle dial at the center of the controller. As the motions coincide with each other, it is expected that the first drone operator will be able to control more intuitively than the joystick manipulator with less learning.

• 한국항공운항학회지
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• 제16권3호
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• pp.1-6
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• 2008

The stalling speed flight test of light airplane, ChangGong-91, was performed to acquire the certification. With power-off engine condition, the wings level stall flight tests were conducted at the aircraft configuration of various flap angle - clean, 20degree, and full flap, respectively. They were performed considering with the combination of the maximum and minimum test weight, and forward and afterward center of gravity. The stalling speeds and the minimum speeds of light airplane were determined from the results of flight test. Also, the appropriateness of stall warning speeds are evaluated through the flight test measures. The airplane is recoverable only with pitch control and engine throttle from stall state without exceptional operation.

• 한국항공우주학회지
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• 제43권11호
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• pp.971-977
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• 2015

복합 자이로플레인의 전진 비행 성능해석을 수행하였다. 자동회전하는 로터의 성능을 해석하기 위하여 과도모사법(Transient Simulation Method)을 이용하였으며 비행 속도 증가에 따른 동체의 공력 성능 변화를 확인하기 위해 동체에 대한 수치해석을 수행하였다. 주어진 속도와 샤프트각, 그리고 콜렉티브 피치 조건에서 준 정상 자동회전 상태를 판정하고 로터의 성능 변화를 관찰하였다. 성능해석 결과 속도가 증가함에 따라 동체의 형상에 따른 공력특성이 미치는 영향이 커지는 것으로 나타났으며 고속으로 비행하기 위해서는 유선형의 동체가 필수적이고 전진 속도 한계는 로터의 자동회전 성능에 종속적이었다.

• International Journal of Aeronautical and Space Sciences
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• 제10권1호
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• pp.104-111
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• 2009

An unstructured overset mesh method has been developed for the simulation of unsteady flow fields around isolated rotors and rotor-fuselage configurations. The flow solver was parallelized for the efficient calculation of complicated flows requiring a large number of cells. A quasi-unsteady mesh adaptation technique was adopted to enhance the spatial accuracy of the solution and to better resolve the rotor wake. The method has been applied to calculate the flow fields around rotor-alone and rotor-fuselage configurations in forward flight. Validations were made by comparing the predicted results with those of measurements. It was demonstrated that the present method is efficient and robust for the prediction of unsteady time-accurate flow fields involving multiple bodies in relative motion.

• 한국전산유체공학회지
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• 제16권4호
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• pp.21-27
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• 2011

In this paper, the diagonal implicit harmonic balance method is applied to analyze helicopter rotor blade flow. The periodic boundary condition for Fourier coefficients is also applied in hover and forward flight conditions. It is available enough to simulate the forward flight problem with only one rotor blade using the periodic boundary condition in the frequency domain. In order to demonstrate the present method, Caradonna & Tung's rotor blades were used and the results were compared to the time-accurate method and experimental data.