• Journal of Environmental Health Sciences
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• v.44 no.6
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• pp.591-598
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• 2018

Objectives: Radiologists are the service worker with emotional labor who works within a relatively small space of the hospital, dealing with multiple patients. The purposes of this study were to search the turnover intention and job satisfaction through the work of emotional labor of radiologists. Methods: A questionnaire survey was conducted on 109 radiologists working at university hospitals, general hospitals, clinics and other facilities across the domestic. The regions were aggregated according to Quality Function Deployment (QFD) method, which was applied in proportion to the population distribution. A questionnaire was composed of 26 questions which were used in Korean Emotional Laboratory Scale (K-ELS). Results: The overall emotional labor score was $48.3{\pm}15.8$. The most pressing requirement of radiologists to improve emotional labor was the topic about the exchange of colleagues ($75.8{\pm}15.6$ score, ${\beta}=0.78$, p<0.001). Conclusions: In order to resolve the emotional labor of radiologists, it could be necessary to have a meeting through training and workshops where the exchange of colleagues can take place.

• KSII Transactions on Internet and Information Systems (TIIS)
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• v.15 no.11
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• pp.4043-4064
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• 2021

Night-time image quality evaluation is an urgent requirement in visual inspection. The lighting environment of night-time results in low brightness, low contrast, loss of detailed information, and colour dissonance of image, which remains a daunting task of delicately evaluating the image quality at night. A new blind quality assessment metric is presented for realistic night-time scenario through a comprehensive consideration of contrast, texture, and colour in this article. To be specific, image blocks' color-gray-difference (CGD) histogram that represents contrast features is computed at first. Next, texture features that are measured by the mean subtracted contrast normalized (MSCN)-weighted local binary pattern (LBP) histogram are calculated. Then statistical features in Lαβ colour space are detected. Finally, the quality prediction model is conducted by the support vector regression (SVR) based on extracted contrast, texture, and colour features. Experiments conducted on NNID, CCRIQ, LIVE-CH, and CID2013 databases indicate that the proposed metric is superior to the compared BIQA metrics.

• The Journal of the Acoustical Society of Korea
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• v.27 no.2
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• pp.92-101
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• 2008

To dissolve the multi-layered model problems, and to complement 2-layered model's simplicity, assumed fluid-fluid-solid 3-layered model. Generally it is known that if the sediment thickness is more than 10 wavelength, the half space's influence to the in-water acoustic field could be disregarded. By tracking the maximum correlation coefficient of calculated results and experimental ones we confirmed that the requirement could be more realized. To calculate the maximum correlation coefficient we used single sensor transmission loss. On the assumption that the sediment sound velocity was 1813 m/s and frequency range 50 kHz to 120 kHz, the conversion condition was from 2.5 to 7.7 wavelength.

• The Korean Journal of Air & Space Law and Policy
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• v.7
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• pp.101-134
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• 1995

Article 3 Paragraph 1 of the Warsaw Convention regulates the requirements of passenger tickets, Article 4 Paragraph 3, the requirements of baggage tickets, Article 8, the requirements of airway bills. In this article the writer has discussed the legal nature of the documents of air carriage, such as air waybills, passenger tickets and baggage checks. Further, the writer has also discussed several issues relating to the use of the documents of air carriage under the Warsaw Convention. Article 3 Paragraph 2, as well as Article 4 Paragraph 4 and 9 provides that the carrier shall not be entitled to avail himself of the provisions of the Convention which evade or limit his liability. In particular, the Montreal Agreement of 1966 provides that the notification on the carrier's liability in passenger ticket should be printed in more than 10 point type size with contrasting ink colors. However, another question is whether the carrier shall not be entitled to avail himself of the liability limit under the Convention in case the type size is below 10 points. The Convention does not specify the type size of certain parts in passenger tickets and only provides that the carrier shall not be entitled to avail himself of liability limit, when a carrier fails to deliver the ticket to passenger. However, since the delivery of passenger tickets is to provide an opportunity for passengers to recognize the liability limit under the Convention and to map out a subsequent measures, the carrier who fails to give this opportunity shall not be entitled to avail himself of the liability limit under the Convention. But some decisions argue that when the notice on the carrier's liability limit is presented in a fine print in a hardly noticeable place, the carrier shall not be entitled to avail himself under the Convention. Meanwhile, most decisions declare that regardless of the type size, the carrier is entitled to avail himself of liability limit of the provisions of the Convention. The reason is that neither the Warsaw Convention nor the Montreal Agreement stipulate that the carrier is deprived from the right to avail himself of liability limit of the provisions of the Convention when violating the notice requirement. In particular, the main objective of the Montreal Agreement is not on the notice of liability limit but on the increase of it. The latest decisons also maintain the same view. This issue seems to have beeen settled on the occasion of Elisa Chan, et al. vs. Korean Airlines Ltd. The U.S. Supreme Court held that the type size of passenger ticket can not be a target of controversy since it is not required by law, after a cautious interpretation of the Warsaw Convention and the Montreal Agreement highlighting the fact that no grounds for that are found both in the Warsaw Convention and the Montreal Agreement. Now the issue of type size can hardly become any grounds for the carrier not to exclude himself from the liability limit. In this regard, any challenge to raise issue on type size seems to be defeated. The same issue can be raised in both airway bills and baggage tickets. But this argument can be raised only to the tranportation where the original Convention is applied. This creates no problem under the Convention revised by the Hague Protocol, because the Hague Protocol does not require any information on weight, bulk, size, and number of cargo or baggage. The problem here is whether the carrier is entitled to avail himself of the liability limit of the provisions of the Convention when no information on number or weight of the consigned packages is available in accordance with Article 4 of the Convention. Currently the majority of decisions show positive stance on this. The carrier is entitled to avail himself of the liability limit of the provisions of the Convention when the requirement of information on number and weight of consigned packages is skipped, because these requirements are too technical and insubstancial. However some decisions declare just the opposite. They hold that the provisions of the Convention Article 4 is clear, and their meaning and effect should be imposed on it literally and that it is neither unjust nor too technical for a carrier to meet the minimum requirement prescribed in the Convention. Up to now, no decisions by the U.S. Supreme Court on this issue is available.

• Journal of Astronomy and Space Sciences
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• v.22 no.3
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• pp.329-352
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• 2005

Long term observations of full-disk Lyman-o irradiance have been made by the instruments on various satellites. In addition, several sounding rockets dating back to the 1950s and up through the present have measured the $Lyman-{\alpha}$ irradiance. Previous full disk $Lyman-{\alpha}$ images of the sun have been very interesting and useful scientifically, but have been only five-minute 'snapshots' obtained on sounding rocket flights. All of these observations to date have been snapshots, with no time resolution to observe changes in the chromospheric structure as a result of the evolving magnetic field, and its effect on the Lyman-o intensity. The $Lyman-{\alpha}$ Imaging Solar Telescope(LIST) can provide a unique opportunity for the study of the sun in the $Lyman-{\alpha}$ region with the high time and spatial resolution for the first time. Up to the 2nd year development, the preliminary design of the optics, mechanical structure and electronics system has been completed. Also the mechanical structure analysis, thermal analysis were performed and the material for the structure was chosen as a result of these analyses. And the test plan and the verification matrix were decided. The operation systems, technical and scientific operation, were studied and finally decided. Those are the technical operation, mechanical working modes for the observation and safety, the scientific operation and the process of the acquired data. The basic techniques acquired through the development of satellite based solar telescope are essential for the construction of space environment forecast system in the future. The techniques which we developed through this study, like mechanical, optical and data processing techniques, could be applied extensively not only to the process of the future production of flight models of this kind, but also to the related industries. Also, we can utilize the scientific achievements which are obtained throughout the project And these can be utilized to build a high resolution photometric detectors for military and commercial purposes. It is also believed that we will be able to apply several acquired techniques for the development of the Korean satellite projects in the future.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.48 no.6
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• pp.455-466
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• 2020

In this study, we built a thermal model for SNIPE 6U nano-satellite which has scientific mission for measuring science data in near Earth space environment and described thermal design based on the thermal model. And the validity of the thermal design was verified through the on-orbit thermal analysis. The thermal design was carried out mainly on the passive thermal control techniques such as surface finishes, insulators, and thermal conductors in consideration of the characteristics of the nano-satellite. However, the components with narrow operating temperature range and directly exposed to the orbital thermal environments, such as a battery and thrusters, are accomodated with heaters to satisfy the temperature requirements. On-orbit thermal analysis conditions are based on the basic orbital conditions of the satellite, and thermal analysis was performed for Normal mode, Launch & Early Orbit Phase (LEOP), Safehold mode, and Maneuver mode which are classified by the power consumption and the attitude of the satellite according to the mission scenario. The analysis results for each mode confirmed that every component satisfies the temperature requirement. In addition, the heater capacity and duty cycle of the battery and thruster were calculated through the analysis results of the Safehold mode.

• Archives of design research
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• v.19 no.4 s.66
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• pp.155-162
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• 2006

Today, according to population decrease and aging of the old due to the decline of birthrate in our society in $21^{st}$ century, there is a stiff increase of the aged group. Complying with the request of epic needs, as there was a full scale amendment of law of the aged welfare in 1997, the centers appeared differently based on the regional dimension, the difference of the number of persons to be accommodated, and the social and economic characteristics. Coping with these problems occurring, along with the necessity of welfare facilities for the leisure of the aged, the government prepared and carried out a number of plans for the service of the aged and securing of facilities. This practice of the government, however, centered on the crease of service in quantity other than the quality, resulting in a situation of lacking the welfare facilities for the aged meeting the requirement of the aged in their aspect of consumer. On the contrary, building the welfare centers in Japan started in 1960 with a rapid increase of the number of centers in 1970s, and there were 2,214 welfare centers in operation in Japan in 1995, keeping a high level of service in quality and quantity. Thus, this study aims to present basic materials necessary for the criteria of space designing plans for the aged welfare centers in Korea through case analysis of the facility criterion, area constitution and space constitution by the floor that play an important role in regional welfare facilities for the aged in Japan.

• Journal of KIISE:Computing Practices and Letters
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• v.13 no.4
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• pp.231-239
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• 2007

This paper presents the trade-off relationship between area and performance in the hardware design space exploration for the Korean national standard 128-bit block cipher algorithm SEED. In this paper, we compare the following four hardware design types of SEED algorithm : (1) Design 1 that is 16 round fully pipelining approach, (2) Design 2 that is a one round looping approach, (3) Design 3 that is a G function sharing and looping approach, and (4) Design 4 that is one round with internal 3 stage pipelining approach. The Design 1, Design 2, and Design 3 are the existing design approaches while the Design 4 is the newly proposed design in this paper. Our new design employs the pipeline between three G-functions and adders consisting of a F function, which results in the less area requirement than Design 2 and achieves the higher performance than Design 2 and Design 3 due to pipelining and module sharing techniques. We design and implement all the comparing four approaches with real hardware targeting FPGA for the purpose of exact performance and area analysis. The experimental results show that Design 4 has the highest performance except Design 1 which pursues very aggressive parallelism at the expanse of area. Our proposed design (Design 4) shows the best throughput/area ratio among all the alternatives by 2.8 times. Therefore, our new design for SEED is the most efficient design comparing with the existing designs.

• Korean Journal of Remote Sensing
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• v.26 no.2
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• pp.277-285
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• 2010

Geostationary Ocean Color Imager(GOCI-I), the world's first space-borne ocean color observation geostationary satellite, will be launched on June 2010. Development of GOCI-I took about 6 years, and its expected lifetime is about 7 years. The mission and user requirements of GOCI-II are required to be defined at this moment. Because baseline of the main mission of GOCI-II must be defined during the development time and early operational period of GOCI-I. The main difference between these missions is the global-monitoring capability of GOCI-II, which will meet the necessity of the monitoring and research on climate change in the long-term. The user requirements of GOCI-II will have higher spatial resolution, $250m{\times}250m$, and 12 spectral bands to fulfill GOCI-I's user request, which could not be implemented on GOCI-I for technical reasons. A dedicated panchromatic band will be added for the nighttime observation to obtain fishery information. GOCI-II will have a new capability, supporting user-definable observation requests such as clear sky area without clouds and special-event areas, etc. This will enable higher applicability of GOCI-II products. GOCI-II will perform observations 8 times daily, the same as GOCI-I's. Additionally, daily global observation once or twice daily is planned for GOCI-II. In this paper, we present an improved development and organization structure to solve the problems that have emerged so far. The hardware design of the GOCI-II will proceed in conjunction with domestic or foreign space agencies.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.3
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• pp.243-249
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• 2021

The star tracker detects microscopic star light in space and compares it with a stored list of stars to calculate the satellite's position in the inertial coordinate system. If other light, such as the sun or the earth, enters the optical head, the star cannot be recognized and the star tracker cannot be operated. In particular, strong light such as the sun affects not only operation but also the performance of the star tracker. The sun exclusion angle of the star tracker is one of the important factors determining the performance of the star tracker. This paper performs the verification of the star tracker's sun exclusion angle. In order to verify the sun exclusion angle, we predict the sun exclusion time of the star tracker and compare it to the actual sun exclusion time of the GEO-KOMPSAT-2A star tracker. In addition, the performance of the star tracker is analyzed for normal operations against the sun exclusion in the optical head. It shows that the actual sun exclusion is maintained under the range of 26 degrees, the performance requirement of the star tracker, and the star tracker operates normally in spite of the sun exclusion.