• Korean Journal of Applied Biomechanics
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• v.14 no.1
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• pp.83-98
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• 2004

The purpose of this study was to determine the kinematic variables of the hurdling for a korea record holder (A) and a national hurdle representative (B). after the kinematic variables such the distance and the distance and height of C.G, the velocity and the angle were analyzed about the hurdling. The results were summarized as follows; 1. In terms of the distance and the height of C.G, subject A showed long in horizontal distance from C.G to the take-off phase, but showed short in the landing phase. Subject B showed short in horizontal distance from C.G to the take-off phase, and showed long in the landing phase. 2. In terms of the velocity of C.G, Subject A showed fast C.G velocity in horizontal direction to the braking phase, Subject A and B showed slower C.G velority in the landing phase, but Subject A showed height C.G velocity in vertical direction to the to the take-off, the landing, and propulsion phase 3. In terms of the angle of C.G and lean of C.G to front at the braking and the take-off phase. Subject A kept the less angle in the maximum trunk lean to front at the flight phase as comparison with Subject B. 4. In terms of the velocity of the knee and the ankle joint. Subject A showed fast in the resultant velocity of the left ankle joint the take-off phase, but showed slow in the left knee joint. Subject B showed fast in the resultant velocity of the left knee joint the take-off phase, but showed slow in the right knee and the right ankle joint.

• The Korean Journal of Air & Space Law and Policy
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• v.18
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• pp.363-384
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• 2003

The Military Airbase Law has designated imaginary surface, restricting the height of structure above the imaginary surface. The purpose of establishment of imaginary surface is to promote safety of aircraft operation. However, given the fact that the land is limited, the Military Airbase Law does not set up outer horizontal surface such that the reduced imaginary surface would undermine the safety of aircraft operations with respect to IFR (Instrument Flight Rules) procedures. The fact that some areas which IFR procedures require are not designated as imaginary surface results in no imposition of height restriction on such area. With regard to aviation safety, this article deals with issue of height restriction on area which is beyond the imaginary surface area. This article also examines the establishment of the imaginary surface in the Military Airbase Law, and conducts case study of imaginary surface systems in other country. Based upon this discussion, the current problems posed in the Military Airbase Law will be discussed. To resolve these problems, it is necessary to establish height restriction zone beyond the current imaginary surface area. The provisions of ICAO, FAA and other counties in relation with this issue are referred as well. As a result, many different proposals are suggested, and it is concluded as the most effective proposal that, in certain zone beyond the imaginary surface area, an aeronautic study should be required for the purpose of ensuring aviation safety before a permit of construction higher than prescribed height is issued.

• Aerospace Engineering and Technology
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• v.2 no.2
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• pp.179-185
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• 2003

In this study, considerations for establishing RVSM airspace and requirements for RVSM operating aircraft are verified. The purpose of RVSM is to reduce vertical separation minimum for aircraft which operate between FL290~FL410 inclusive in regional airspace, and to increase airspace capacity by providing additional flight levels. To introduce RVSM, it is necessary to estimate quantatively airborne collision risk due to the reduction in vertical separation minimum. Aircraft operating through RVSM airspace is required to verify that height keeping performance is above specific standards.

• 한국전산유체공학회:학술대회논문집
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• 2005.10a
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• pp.245-248
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• 2005

SCRamjet is the key technology for hypersonic flight over mach number 6. It is characterized by very short residence time in combustor because its internal flow is supersonic. In this short time, the whole process of combustion must be done. Especially numerical study of combustor is important because air-fuel mixing rate influences the performance of combustor. Various methods of air-fuel mixing enhancement are proposed. Among these, cavity injection method is selected to study in this paper. The numerical study is conducted with the variation of the cavity length at the fixed height of unit and jet injection on the downstream of cavity.

• Proceedings of the KOSOMBE Conference
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• v.1997 no.05
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• pp.131-135
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• 1997

We implementated an ultrasonic wave cane for the blind. The cane detect walking obstacle and provide a walking direction. The cane used time of flight method of ultrasonic-wave for a measurement of obstacle distance and fluxgate geomagnetic sensor for guidance of walking direction. This system can detect an obstacle of upward, forward, downward and that warn to the blind with vibration, pitch sound. And the blind can know walking direction to voice output. As a result, the blind could efficiently avoid a exposed obstacle, obstacles beyond knee, an exposed street obstacle, a branch of tree person's height and it is usable search for surrounding land mark.

• Proceedings of the KSRS Conference
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• v.1
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• pp.504-507
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• 2006

Airborn Lidar technology has been applied to diverse applications with the advantages of accurate 3D information. Further, Lidar intensity, backscattered signal power, can provid us additional information regarding target's characteristics. Lidar intensity varies by the target reflectance, moisture condition, range, and viewing geometry. This study purposes to generate normalized airborne LiDAR intensity image considering those influential factors such as reflectance, range and geometric/topographic factors (scan angle, ground height, aspect, slope, local incidence angle: LIA). Laser points from one flight line were extracted to simplify the geometric conditions. Laser intensities of sample plots, selected by using a set of reference data and ground survey, werethen statistically analyzed with independent variables. Target reflectance, range between sensor and target, and surface slope were main factors to influence the laser intensity. Intensity of laser points was initially normalized by removing range effect only. However, microsite topographic factor, such as slope angle, was not normalized due to difficulty of automatic calculation.

• Proceedings of the IEEK Conference
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• 1998.06a
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• pp.565-568
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• 1998

In this paper, we implemented the electornic moving aid system for safe walking of the blind. An obstacle detecting of each sector used ultrasound and a distance measurement used time of flight. The alarm is designed to have a sound and a tactile function that can be selected on an user's convenience. This system can detect and obstacle of upward, forward, downward and optimally warn to the blind with vibration, beep sound by appling warning algorithm on object detection. Experimental testing and performance evaluation have been successfully carried out with a prototype cane, and the experiment shows the capability of the function to detect unknown objects within an assigned distance, under knees, over head height, and crushed puddles.

• Atmosphere
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• v.23 no.4
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• pp.513-517
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• 2013

In this study, it is first intended to simulate the vertical profile of atmospheric flow in a short wind tunnel. In order to accomplish it, proper devices are designed properly to reduce freestream flow momentum and it is confirmed from the measured velocity profile using hot-wire anemometer that momentum flux of the tunnel free stream can be reduced and desired atmospheric boundary can be created. Second, experiments are performed to identify influences of a surrounding structure measuring correct wind velocity by an anemometer, which are located nearby due to area limitation in actual airport and correction factors are proposed from experimental results. One of findings is that in order to limit the velocity attenuation due to a nearby structure under 10%, wind velocity measuring equipment should be installed at least 6 times of the structure height away from the structure of concern.

• Aerospace Engineering and Technology
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• v.6 no.2
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• pp.1-7
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• 2007

The control design for attitude and yaw rate of 40 % scaled SMART UA Vhas been performed. Analytic selection method for a control gain is proposed to meet the design specification of desired time response considering stability margin. The sliding mode attitude controller is also proposed and compared with the simulation results of a linear controller. Additionally, a velocity and height tracking controller is devised to prepar for the flight test.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.21 no.12
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• pp.1615-1623
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• 1997

Numerical study on the chaotic stirring of the screw extruder model proposed has been performed. The velocity field was used in obtaining the trajectories of passive particles for studying the stirring effect of the screw extruder. Two nonlinear dynamical tools, that are Poincare sections and Lyapunov exponents, were used in analysing the stirring effect. The Poincare sections and the Lyapunov exponents show that the stirring effect is most satisfactory, when n(the number of flights in a section) is 1, for the case a (aspect ratio ; flight height divided by the spacing between flights) being O.1. It is also required to set n=3, or 5 at a= 0.2, 0.3 for a uniform stirring.