• Journal of the Korean Home Economics Association
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• v.39 no.9
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• pp.153-174
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• 2001

The objectives of this study were to examine the propensity and to analyze some determinants of complaining behavior about the educational services of private institutes. The survey was conducted by means of self-administered questionnaire with 546 university students Living in Seoul and Cheongjoo. They had an experience of studying in the educational services of private institutes in recent two years. Major findings were as following: (1) The propensity of private complaining behavior about the educational services of private institutes averages 3.36 points out of 5. This score is beyond the middle slightly. Whereas the propensity of pubic complaining behavior is very low. (2) According to the discriminant analysis, tuition fee, information supplied for solving the dissatisfaction, and altitude about the complaining behavior are the determinants to distinguish between complaining/non complains behavior group of private complaining behavior. (3) Information supplied for solving the dissatisfaction, kindness of the stars, the establishment, the way of making tuition fees, the degree of awareness of cost, the attitude about complaining behavior, the confidence of success for complaining behavior are the determinants to distinguish between complaining/non complains behavior group of public complaining behavior.

• The Bulletin of The Korean Astronomical Society
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• v.40 no.2
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• pp.56.4-57
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• 2015

We present the optical design and a sensitivity analysis for a wide field of view (FOV) instrument operating at UV and IR wavelengths. The ongoing investigation is performed in collaboration with Omnisys Instruments (Sweden) and focuses on a telluric-limb-viewing instrument that will fly in a low Earth orbit to study mesospheric wave structures over a wide range of horizontal scales in the altitude range 80 - 100 km. The instrument has six wavelength channels which consist of 4 channels of IR and 2 of UV. We are proposing an optical design based on three mirror aplanatic off-axis reflective system. The entrance pupil diameter and effective focal length are 45 mm and 270 mm, respectively. The FOV is $5.5^{\circ}{\times}1^{\circ}$ and the secondary mirror is set for stop. The optical specification is required to have an encircled energy of at least 80 % within a diameter of 21 um. We performed sensitivity analysis for the longest wavelength of 772 nm in consideration of the diffraction limit of system. The results show that tolerance limits for positions and angles of the mirrors are not very sensitive compared with typical error budgets of manufacturing and assembling process. The secondary mirror has the most sensitive tolerance for surface figure of 250 nm in root-mean-square.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.26 no.10
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• pp.924-931
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• 2015

When a target locates at low altitude over a curved earth surface and far away from a radar, we examine the accuracy of the conventional formulations to compute the radar echo signal. The 4-ray model is used to calculate the scattering by the target to consider the ground plane effect. In this paper, the diffracted wave is not included. Based on the required parameters able to be calculated by known equations for the estimation of the wave propagation phenomena, the radar echo signal is computed and verified by comparing with measured data sets.

• International Journal of Aeronautical and Space Sciences
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• v.17 no.1
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• pp.132-138
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• 2016

Korea Aerospace Research Institute (KARI) is developing an electric-driven HALE UAV in order to secure system and operational technologies since 2010. Based on the flight tests and design experiences of the previously developed electric-driven UAVs, KARI has designed EAV-3, a solar-powered HALE UAV. EAV-3 weighs 53kg, the structure weight is 22kg, and features a flexible wing of 19.5m in span with the aspect ratio of 17.4. Designing the main wing and empennage of the EAV-3 the amount of the bending due to the flexible wing, 404mm at 1-G flight condition based on T-800 composite material, and side wind effects due to low cruise speed, $V_{cr}=6m/sec$, are carefully considered. Also, unlike the general aircraft there is no center of gravity shift during the flight because of the EAV-3 is the solar-electric driven UAV. Thus, static margin cuts down to 28.4% and center of gravity moves back to 31% of the Mean Aerodynamic Chord (MAC) comparing with the previously designed the EAV-2 and EAV-2H/2H+ to upgrade the flight performance of the EAV-3.

• International Journal of Aeronautical and Space Sciences
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• v.14 no.2
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• pp.193-199
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• 2013

This work investigates the orbital perturbations of the cubesats that lie on LEO due to Earth albedo. The motivation for this paper originated in the investigation of the orbital perturbations for closed- Earth pico-satellites due to the sunlight reflected by the Earth (the albedo). Having assumed that the Sun lies on the equator, the albedo irradiance is calculated using a numerical model in which irradiance depends on the geographical latitude, longitude and altitude of the satellite. However, in the present work the longitude dependency is disregarded. Albedo force and acceleration components are formulated using a detailed model in a geocentric equatorial system in which the Earth is an oblate spheroid. Lagrange planetary equations in its Gaussian form are used to analyze the orbital changes when $e{\neq}0$ and $i{\neq}0$. Based on the Earth's reflectivity data measured by NASA Total Ozone Mapping Spectrometer (TOMS project), the orbital perturbations are calculated for some cubesats. The outcome of the numerical test shows that the albedo force has a significant contribution on the orbital perturbations of the pico-satellite which can affect the satellite life time.

• Journal of the Korea Furniture Society
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• v.19 no.3
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• pp.193-202
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• 2008

In order to occupy educational furniture market that grows by the day and to meet demands for alternative product for the current market, this study took business features and productivity of Sinil Furniture Co into consideration, and developed computer desk for education by group, which is new among educational furniture. The scope of the study ranges from data research based on design process into creation of prototype. By improving the condition where, despite that electrically-powered computer desk for anti-theft system is high priced, it sees frequent malfunction, the study suggested low-priced, non- electrically-powered anti-theft system which has more solid structure. Furthermore, in order for the user to be more free and comfortable while studying on it, it differentiates from other products by locating PC main body to the back of the monitor and lowering it below the altitude of monitor to prevent it from interfering with studies. We've made the higher board of the desk in a soft curved-shape in order to lessen the stress from studying. And as space for the monitor's lower mount was decreased, we've put the lower mount below the higher board; so that lacking space can be recovered while functioning as anti-theft system. Moreover, we've covered the PC main body with steel cover so that it would add color and formal luxuriousness to the appearance of the desk. Considering ease of mobility and productivity, knock-down system was introduced.

• Journal of Astronomy and Space Sciences
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• v.8 no.1
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• pp.85-98
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• 1991

Geomagnetism was used to control the attitude of the small scientific satellite at low altitude in sun-synchronous orbit. First, we analyzed the telemetry data. The rotation state of the satellite, can be known from the magnitude and variations of the magnetic field which is measured from the 3 axis magnetometer. In axisymmetric case, it is possible to control the attitude of the satellite by changing the rotation velocity of each 3 axis. The algorithm and the program were developed to calculate the supply time of the current operating the magnetorquer. This attitude control can be applied when the satellite is in tumbling motion and after passive control is attained by the Gravity gradient boom.

• Journal of the Korea Institute of Military Science and Technology
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• v.19 no.4
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• pp.443-452
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• 2016

Current low-altitude radar system often fails to detect small unmanned aerial vehicles (UAV) because of their small radar cross section (RCS) compared with larger targets. As a potential alternative, a passive bistatic radar system has been considered. We study an optimal deployment problem for the passive bistatic radar system. We model this problem as a covering problem, and develop an integer programming model. The objective of the model is to maximize coverage of a passive bistatic radar system. Our model takes into account factors specific to a bistatic radar system, including bistatic RCS and transmitter-receiver pair coverage. Considering bistatic RCS instead of constant RCS is important because the slight difference of RCS value for small UAVs could significantly influence the detection probability. The paired radar coverage is defined by using the concept of gradual coverage and cooperative coverage to represent a realistic environment.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.7
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• pp.576-585
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• 2014

In this paper, we survey the Moving Target Indication(MTI) techniques for small UAVs. MTI consists of image alignment phase and frame differencing correction phase, and image alignment has two ways of parametric approach which is mainly focused in this paper and non-parametric approach. Since small UAVs are operated in the low altitude, the parallax is considerable and the epipolar geometry is applied to compensate the parallax. The related works and future works are presented.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.23 no.1
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• pp.24-29
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• 2015

In order to increase endurance flight efficiency of long endurance electric powered UAV, main wing of UAV should have high aspect ratio and low structural weight. Since a spar which consists of thin and slender structure for weight reduction can cause catastrophic failure during the flight, it is important to develop verification method of structural integrity of the spar with the light weight design. In this paper, process of structural analysis using non-linear finite element method was introduced for the verification of structural integrity of the spar. The static strength test of the spar was conducted to identify structural characteristic under the static load. Then, the experimental result of the spar was compared to the analytical result from the non-linear finite element analysis. It was found that the developed process of structural analysis could predict well the non-linear structural behavior of the spar under ultimate load.