• 복식문화연구
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• 제19권5호
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• pp.1019-1030
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• 2011

The aim of this study was to develop a pattern of flight attendant uniform shirts to provide better comfort for their work postures. Flight attendants' work postures were evaluated to determine the problems of clothing and mobility during their work. The pattern of the flight attendants' uniform shirt was altered by applying dynamic wearing ease(DWE). DWE was calculated from four standardized dynamic postures and a static posture. An experimental garment was made with the altered postures. The researcher redesigned the pattern of the uniform shirts, which minimizes physical limitations in movements. The fit and mobility of the shirts were evaluated. Results of this study are as follows. First, the five representative work postures were selected by "clothing stress" and "repetitiveness." These postures included raised arms, twisting midriff and shoulder postures. Five representative postures were selected by using the ergonomic posture assessment device index(OWAS). Second, the experimental garment was developed by applying DWE across the back and at armhole depth, back length, and side length. Third, the fit and mobility of the experimental garments and the original uniform shirts were compared at the flight working environment set and 5 dynamic body postures of raising arms. The experimental garments made with an altered pattern provided better fit and mobility than the original sample shirts.

• 한국항공운항학회지
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• 제19권4호
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• pp.67-73
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• 2011

For loads analysis of airplane, applicable regulation should be determined. Then, loads conditions are prepared from the regulation. Modeling for aerodynamic, mass, and structure are performed. Panel method is usually adopted for aircraft loads analysis to obtain air loads. The ARGON which is a multidisciplinary fixed wing aircraft design software co-developed by the KARI and TsAGI are used for loads analysis. The ARGON can be utilized for flutter and stress analysis as well as for flight and ground loads analysis. In this paper, flight loads analysis for wing structural design of the regional aircraft at the conceptual design phase are performed with the ARGON. FAR 25 is used for the regulation for the load analysis. Shear force, bending moment and torsion diagrams for the wing and shear force and hinge moment for the aileron are presented.

• 한국윤활학회:학술대회논문집
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• 한국윤활학회 2001년도 제33회 춘계학술대회 개최
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• pp.248-256
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• 2001

Capacities of screw are pumping, steady flow of polymer melts, volumetric efficiency, steady volumetric throughout etc. they are affected by geometry of screw, heat flux, pressure on inside barrel, rotating velocity, friction coefficient at screw surface etc. Also the temperature of polymer melts by heating pad and injection pressure play a very important role in the injection molding machine. by computation volumetric efficiency increases as rotating velocity increases, flight number increses, and decreases as friction coefficient increases. but volumetric throughout is different :s flight number increases with helix angle variability. so in this paper we analyze thermal distortion and stress of screw includes pressure and temperature distributions by finite element analysis to understand what design factors influence on thermo-mechanical characteristics of screw.

• 융합정보논문지
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• 제9권10호
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• pp.203-212
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• 2019

본 연구는 학생조종사의 스트레스 요인이 정신건강에 미치는 영향을 파악하며, 스트레스 대처방식과 사회적 지지의 심리적 완충 역할의 확인을 통해 안전하고 효율적인 비행교육과 심리적 부조화를 감소시키고자 하였다. 연구목적을 달성하기 위해 선행연구를 근거로 하여 연구모형과 가설을 제시하였으며, 202명의 학생조종사를 대상으로 한 설문을 통해 회귀분석과 매개효과 검증을 실시하였다. 분석결과, 비행 스트레스, 가치관 스트레스, 교수관계 스트레스, 친구관계 스트레스의 요인이 정서상태 혹은 심리적 안녕감에 영향이 있는 것으로 나타났으며, 매개변수인 비관여 대처, 가족/지인 지지, 학교조직 지지가 학생조종사 스트레스와 심리적 건강의 요인에 매개효과가 있음을 파악하였다. 따라서, 학생조종사의 비행훈련, 가치관 혼란, 교수관계, 친구관계로 발생될 수 있는 문제와 부정적 감정을 잘 관리해야 할 필요성이 있으며, 가족과 지인의 감정적 지원과 비행과 관련된 훈련, 안전에 관한 학교의 지원이 주요한 사항임을 제안하였다.

• 한국항공운항학회지
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• 제20권2호
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• pp.58-63
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• 2012

An altitude chamber, also known as a hypobaric chamber, is a device used during aerospace or high terrestrial altitude research or training to simulate the effects of high altitude on the human body. Although data from altitude chamber researches using experimental animals have been accumulated, studies in the humans exposed to hypobaric conditions are seldomly reported. Despite the importance of altitude chamber flight training in the field of aviation physiology, the hematological analysis of post-flight physiological changes has rarely been performed. The aims of the present study were to investigate the alterations in blood components during altitude chamber flight and to determine whether the differences between pre- and post-flight values are significant. Sixty experienced pilots in the Republic of Korea Air Force were enrolled in the altitude chamber flight training. Venous blood samples were obtained before and immediately after the flight. Compared with the pre-flight values($6.32{\times}10^3/mm^3$, $5.02{\times}10^6/mm^3$, 15.61 g/dL, respectively), white blood cell count, red blood cell count and hemoglobin level were significantly increased after the flight($6.77{\times}10^3/mm^3$, $5.44{\times}10^6/mm^3$, 16.26 g/dL; p=0.006, p=0.012, p<0.001, respectively). These alterations may be attributable to the exposure to hypobaric hypoxia, 100% oxygen supply for denitrogenation, considerable rise and fall in altitude and psychophysical stress due to these factors. In further studies, experimental groups and methods should be individualized to ensure objectivity and diversification. In addition, multiple time-frame analyses regarding the changing pattern of each blood component are also required to elucidate the physiological process for adapting to the high terrestrial altitude exposure.

• 한국항공운항학회지
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• 제25권3호
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• pp.74-80
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• 2017

As for A rotary wing aircraft, the configuration change about split yaw swaged rod was executed to improve hit treat capability for dealing with a long rod. The purpose of this study was to analyze if or not the quality of the split yaw swaged rod was obtained, and so the flight safety was ensured or not. Buckling analysis, Coupling Thread Strength Analysis, Thermal Stress analysis and Rod Natural Frequency Analysis were executed for structural analysis. The results of the analysis were presented that the split rod had the sufficient margin of safety and so there were no anomalies in the limit load and no failures in the ultimate load. And there were no resonances in result of natural frequency analysis. In conclusion, this study showed that the split yaw swaged rod had structural safety, so flight safety of rotary wing aircraft was secured and there was no problem in aircraft operation. It is certain that the technology of splitting the yaw swage rod will contribute to the operational Safety of the rotary wing aircraft in the future.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2003년도 추계학술대회
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• pp.1045-1050
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• 2003

In this study, to investigate the effects of omitting low-amplitude cycles from a flight-simulation loading, crack growth tests are conducted on 2124-T851 aluminum alloy specimens. Three test spectra are generated by omitting small load ranges as counted by the rain-flow count method. The crack growth test results are compared with the data obtained from the flight-simulation loading. The experimental results show that omission of the load ranges below 5% of the maximum load does not significantly affect crack growth behavior, because these are below the initial stress intensity factor range. However, in the case of omitting the load ranges below 15% of the maximum load, crack growth rates decrease, and therefore crack growth curve deviates from the crack growth data under the flight-simulation loading. To optimize the load range that can be omitted, crack growth curves are simulated by the stochastic crack growth model. The prediction shows that the omission level can be extended to 8% of the maximum load and test time can be reduced by 59%.

• 동력기계공학회지
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• 제8권4호
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• pp.11-16
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• 2004

In this study, to investigate the effects of omitting low-amplitude cycles from a flight-simulation loading, crack growth tests were conducted on 2124-T851 aluminum alloy specimens. Three test spectra were generated by omitting small load ranges as counted by the rain-flow count method. The crack growth test results were compared with the data obtained from the flight-simulation loading. The experimental results show that the ranges equal to or smaller than 5% of the maximum load do not contribute to crack growth behavior because these are below the initial stress intensity factor range. Omitting these from the flight-simulation loading, test time can be reduced by 54%. However, in the case of omitting the load ranges below 15% of the maximum load, crack growth rates decreased, and crack growth curve deviated from the crack growth data under the flight-simulation loading because loading cycles above fatigue fracture toughness were omitted.

• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2005년도 추계학술발표대회 논문집
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• pp.179-184
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• 2005

In the present study, conceptual design of the main wing for 20 seats WIG{wing in Ground Effect) flight vehicle, which will be a high speed maritime transportation system for the next generation, was performed. The high stiffness and strength Carbon-Epoxy material was used for the major structure and the skin-spar with a foam sandwich structural type was adopted for improvement of lightness and structural stability. As a design procedure for this study, firstly the design load was estimated with maximum flight load, and then flanges of the front and the rear spar from major bending load and the skin structure and the webs of the spars were preliminarily sized using the netting rules and the rule of mixture. In order to investigate the structural safety and stability, stress analysis was performed by Finite Element Codes such as NASTRAN/PA TRAN[6] and NISA II [7]. From the stress analysis results, it was confirmed that the upper skin structure between the front spar and rear spar was very unstable for the buckling. Therefore in order to solve this problem, a middle spar and the foam sandwich structure at the upper skin and the web were added. After design modification, even thought the designed wing weight was a little bit heavier than the target wing weight, the structural safety and stability of the final design feature was confirmed. Moreover, in order to fix the wing structure at the fuselage, the insert bolt type structure with six high strength bolts was adopted for easy assembly and removal.

• 한국직업건강간호학회지
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• 제27권1호
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• pp.25-35
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• 2018

Purpose: The purpose of this study was to figure out emotional labor, healthy lifestyle, needs for health services of flight attendants and the relationships among needs for health services according to various characteristics of flight attendants. Methods: The participants of this study were 140 flight attendants who work on major and low cost airlines. Data were collected through a questionnaire from 2017 .Jan.~2017. Feb. Data were subsequently analyzed using the SPSS 21 Program. Results: The score of emotional labor was 3.76 surface acting was 3.75 and deep acting was 3.77. The average of healthy lifestyle was 2.41, and the highest was 3.13 of personal relationship and the lowest was 1.91 of eating habits. There is a positive correlation between emotional labor-deep acting and healthy lifestyle. Flight attendants demand health services for physical exercise, stress and emotional labor management, healthy eating habits, emergency treatment, prevention of fatigue, cancer screening, sexual harassment prevention, sex education and etc. Conclusion: These results show that flight attendants need to various interventions for improving healthy lifestyle and reducing emotional labor. It is necessary to develop customized health promotion program suited to their job and general characteristics.