• 한국운동역학회지
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• 제29권3호
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• pp.173-183
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• 2019

Objective: The aim of this study was to investigate the correlation coefficients between anthropometric parameters of the foot and kinetic variables during running. Method: This study was conducted on 21 healthy young adults (age: $24.8{\pm}2.1yes$, height: $177.2{\pm}5.8cm$, body mass: $73.3{\pm}7.3kg$, foot length: $256.5{\pm}12.3mm$) with normal foot type and heel strike running. To measure the anthropometric parameters, radiographs were taken on the frontal and sagittal planes, and determined the length and width of each segment and the navicular height. Barefoot running was performed at a preferred velocity ($3.0{\pm}0.2m/s$) and a fixed velocity (4.0 m/s) on treadmill (Bertec, USA) in order to measure the kinetic variables. The vertical impact peak force, the vertical active peak force, the braking peak force, the propulsion peak force, the vertical force at mid-stance (vertical ground reaction when the foot is fully landed in mid-stance or at the point where the weight was uniformly distributed on the foot) and the impact loading rate were calculated. Pearson's correlation coefficient was used to investigate the relationship between anthropometric variables and kinetical variables. The significance level was set to ${\alpha}=.05$. Results: At the preferred velocity running, the runner with longer forefoot had lower active force (r=-.448, p=.041) than the runner with short forefoot. At the fixed velocity, as the navicular height increases, the vertical force at full landing moment increases (r= .671, p= .001) and as the rearfoot length increases, the impact loading rate decreases (r=- .469, p= .032). Conclusion: There was a statistically significant difference in the length of fore-foot and rearfoot, and navicular height. Therefore it was conclude that anthropometric properties need to be considered in the foot study. It was expected that the relationship between anthropometric parameters and kinetical variables of foot during running can be used as scientific criteria and data in various fields including performance, injury and equipment development.

• 한국소음진동공학회논문집
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• 제15권6호
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• pp.718-723
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• 2005

The purpose of this study is to present a fundamental data for evaluating aircraft noise of building site development. By the field experiments and the predicted equal noise level contours using the INM program, actual condition in the building site development arranged district was investigated. In order to get the results, Analysis of factors effected on noise level, sound level on the rate of increase to aircraft demand and difference on the aircraft noise levels according to floor level in apartment house was carried out. As a result the influence of the take-off and landing direction were appeared greatly. The influences of the height at receiving point, movement number of aircraft and increase to aircraft demand were appeared small And the influence of 1 day average WECPNL must be considered.

• 제어로봇시스템학회논문지
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• 제13권2호
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• pp.101-107
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• 2007

A coaxial rotor flying robot is developed for surveying and reconnoitering various circumstances under calamity environment. The robot has two contrarotating rotors on a common axis, an embedded microcontroller, an IMU(Inertial Measurement Unit), an IR sensor for height control, a micro camera for surveillance, ultrasonic position sensors and wireless communication devices. A bell-bar mounted on the top of the upper rotor hub increases stability and improves flight performance. In this paper, we present a dynamic model of a coaxial rotor flying robot and design an embedded controller far the robot, and implement them to control the developed flying robot. Experimental results show that the proposed controller is valid for autonomous hovering and position control.

• International Journal of Naval Architecture and Ocean Engineering
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• 제7권2호
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• pp.259-269
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• 2015

The issue of the longitudinal stability of a WIG vehicle has been a very critical design factor since the first experimental WIG vehicle has been built. A series of studies had been performed and focused on the longitudinal stability analysis. However, most studies focused on the longitudinal stability of WIG vehicle in cruise phase, and less is available on the longitudinal static stability requirement of WIG vehicle when hydrodynamics are considered: WIG vehicle usually take off from water. The present work focuses on stability requirement for longitudinal motion from taking off to landing. The model of dynamics for a WIG vehicle was developed taking into account the aerodynamic, hydrostatic and hydrodynamic forces, and then was analyzed. Following with the longitudinal static stability analysis, effect of hydrofoil was discussed. Locations of CG, aerodynamic center in pitch, aerodynamic center in height and hydrodynamic center in heave were illustrated for a stabilized WIG vehicle. The present work will further improve the longitudinal static stability theory for WIG vehicle.

• 한국항공운항학회지
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• 제17권4호
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• pp.32-41
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• 2009

This paper presents the work being carried out in order to reduce the ground turbulence by the fence in the vicinity of airport runway. In preliminary study, we knows that cross-wind effect in the vicinity of runway is highly dependent on the shape of the buildings and have predicted results confirmed reduction of wind-effect by doing that set up the building with a fence, terraced shape or gap. This study is to figure out effect of ground turbulence by the building with fence, which is changing fence height, in using two-dimensional computational fluid dynamics analysis.

• 한국항공우주학회지
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• 제33권5호
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• pp.50-56
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• 2005

본 연구에서는 착륙 접근시 단일엔진 고장 분석 및 비행전이 해석을 통하여 수직이착륙기에서 요구하는 최적의 엔진추력과 날개하중비를 구하고자 한다. 항공기 해석 모듈들은 기존의 항공기 통합 사이징 프로그램을 기반으로 하고 있으며, 항공기 설계 및 해석을 하나로 묶는 컴퓨팅 체계 구축은 사용자 용도에 맞게 주문 제작이 용이한 반 완성 프로그램인 EMDIOS를 설계프레임웍으로 사용하였다. 시뮬레이션 결과, 고도 40 ft 근처가 단일엔진고장시 가장 위험한 영역임을 확인할 수 있었으며, 비행전이 영역에 대한 파라메타 연구를 통하여 엔진 추력은 클수록, 반면에 엔진틸트각 회전속도와 날개 하중비는 작을수록 비행전이시의 고도 상실이 작아짐을 알 수 있었다.

• 한국운동역학회지
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• 제15권2호
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• pp.119-127
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• 2005

The purpose of this research helps to make full use for perfect performance by grasping the defects of Ropez motion performed by athlete CSM who was under the training for the 28th 2004 Athene Olympic Garnes, and by presenting complementary methods. For the better Ropez motion which had been performed by CSM for the 1st dispatch selection test and the final for the 28th Athene Olympic Game was analyzed with 3-dimensional cinematographic method. Here are the conclusions: 1. During the board contact phase, powerful kicking and rapid forward flexion motion of upper body make increasing vertical velocity of C. O. G and enlarging body angle. 2. It was indicated that rapid forward flexion motion of upper body during the board contact phase get a large body angle in horse take-off. 3. rapid forward flexion motion of upper body during the board contact phase makes a longer time at horse contacting phase. It showed that this result increased velocity of horse take-off causing by powerful blocking motion. 4. Increasing of air-borne height during pre- flight phase, makes a higher C. O. G; and larger angle of hip, angle of knee and body angle in the landing phase. And it revealed that these results have a stable landing.

• 항공우주기술
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• 제12권2호
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• pp.99-107
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• 2013

화성은 국지적인 강한 바람과 그 바람에 의해 표면의 먼지들이 솟아오르는 현상들을 가지고 있다. 대기 순환과 먼지 상승은 서로 관계가 있다고는 알려져 있지만, 먼지 상승의 역학적 원인은 명확하게 밝혀진 것은 없다. 먼지 폭풍은 히말라야 산 높이까지 상승하는 매우 강한 상승 기류인데 이런 기류들은 탐사선이 착륙할 때 또는 로버가 탐사를 수행할 때 피해야 할 위험 요소이다. 본 연구에서는 대기 순환과 관련된 먼저 폭풍의 발생 시기와 발생 지역 분포에 대해 조사하였다. 대기 순환의 원천적인 에너지는 태양이기 때문에 먼지 폭풍의 발생 시기와 화성의 계절에 대해 분석하였고, 최종적으로는 발생 시기와 발생 지역의 공간 분포의 관계를 지도로 작성하였다. 이 자료를 토대로 화성 먼지 폭풍의 발생이 빈번하지 않은 지역과 시기를 예측할 수 있다. 향후 이 자료는 국내 자력으로 화성 착륙선을 보낼 때 착륙시기와 관계하여 발사시점 및 착륙지점을 선정하는데 있어서 결정적인 역할을 할 것이라고 기대한다.

• 한국운동역학회지
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• 제14권1호
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• pp.51-63
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• 2004

The purpose of this study was to investigate a three dimensional kinematic variables about the last stride and the release phase of the throwing technique for female javelin throwers. For the motion analysis, Six female javelin throwers were used as subjects. Three-dimensional coordinates were collected using the Kwon3D Motion Analysis Package Version 2.1 Program. Two S-VHS Video Cameras were used to record the locations and orientations of control object and the performances of the subjects at a frequency of 6.0 HZ. After the kinematic variables such as the time, the distance, the velocity, and the angle were analyzed about the last stride and release phase, the followings were achieved; 1. For the effectively javelin throwing, the subjects appeared to do long the approach time in the phasel of landing phase, and short the delivery time in release phase 2. In the release event, the other subjects except for subject A appeared to throwing in the lower condition than the height of themselves. This result showed to slow the projecion velocity. 3. For increase the projection vcelocity of the upper extremity joint in the release event, it appeared to do extend rather the shoulder angle than increase the extension of elbow joint. 4. The body of COG angle showed to gradually increase nearly at the vertical axis in the release event. But the front lean angle of trunk showed a small angle compare to increase of the body of COG angle. Therefore for the effectively momentum transmission of the whole body in the javelin, the front and back lean angle of trunk appeared to do fastly transfer the angle displacement in the arch posture or the crescent condition during the deliverly motion of the release phase.

• 항공우주시스템공학회지
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• 제18권3호
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• pp.56-64
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• 2024

본 연구에서는 항공우주구조물의 낙하 충격 특성 및 기초 시험, 학술적 연구를 종합적으로 수행하기 위하여 낙하충격시험기를 개발하였다. 낙하충격시험기는 항공기가 지면과의 충돌 시 발생하는 동적인 응력과 변형에 대한 정확한 평가를 가능하게 하며, 안전성 및 기구 강도와 같은 중요한 설계 요소들을 확인할 수 있도록 한다. 낙하충격시험기는 전자석을 이용하여 시험체를 부착 및 낙하하며, 크레인을 이용하여 시험체 낙하 높이 조절이 가능하도록 구성하였다. 또한, 수직 낙하를 위한 낙하보조장치를 제작하였다. 시험을 위한 낙하 시험체의 수치해석을 수행하고 낙하충격시험기를 활용하여 기초 시험을 수행하였다. 해석 및 시험 결과를 통해 착륙장치 낙하 상황에서의 구조적 형상을 분석하고 각 부분의 거동을 종합적으로 평가하였다.