• 패션비즈니스
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• 제17권6호
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• pp.111-124
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• 2013

The purpose of this research was to conduct a comparison analysis of color in the characteristics and image of Korea/China/Japan airline uniforms. Research subjects for this research included 19 Korean, Chinese and Japanese airlines servicing the Incheon International Airport in South Korea. The analysis methods are based on the Munsell Color Order System and PCCS (Practical Color Coordinate System) tone classification in order to examine the color characteristics. For the color image analysis, the present research performed a positioning on Shigenobu Kobayashi's color images scale with adjectives in order to compare the resulting differences. As a result of the analysis, this research discovered the following; First, achromatic colors were found to be used most frequently in flight attendant uniforms of Korea/China/Japan. In Korean flight attendant uniforms, YR/Y, GY and B/PB/P; in Chinese, R/PB, RP, YR/Y/GY and BG/P; in Japanese, RP, R/P/PB and Y/BG were found in order. As for the main uniform colors, Korean flight attendant uniforms were found to be in the colors YR, and R/GY/B/P; Chinese flight attendant uniforms, R, PB, and P/B; and Japanese flight attendant uniforms, R, BG, B, RP and N. Second, Korean flight attendant uniforms used W and It most frequently; China flight attendant uniforms, W; and Japanese flight attendant uniforms, W and v. Regarding the main colors, Korean flight atteddant uniforms used lt/g and v/p; Chinese flight attendant uniforms, v, dp and s/d/dkg; and Japanese flight attendant uniforms, v/dkg and Bk. Third, after positioning each country's uniform color combination bars on the Kobayashi image scale, Korean flight attendant uniforms showed classic images along with casual/pretty/elegant/chic images; Chinese flight attendant uniforms displayed, casual images as well as, dynamic/gorgeous/chic/cool casual/dandy images; and finally, Japanese flight attendant uniforms converyed dandy images along with casual/gorgeous images. This research findings indicate that Korea/China/Japan airlines' flight attendant uniforms seek for differentiated image establishment by reflecting their own CIs and unique national cultures in the uniform color marketing.

• 항공우주시스템공학회지
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• 제8권3호
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• pp.47-54
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• 2014

This is a research on the method of how to improve stall characteristics for the small general aviation airplanes to meet the FAR part 23 requirements. This research is based on the experience of certification flight tests of KC-100 airplane for Korea type certification. KAS/FAR Part 23.201/203 are the stall characteristics requirements. 23.201 requires to show the stable stalling tendency of the wings level stall and 23.203 requires to show the stable stalling tendency of stall characteristics during turning flight. In this paper, the stall characteristics requirements, improvement methods and flight test experience of KC-100 airplane for type certification.

• 시스템엔지니어링학술지
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• 제16권2호
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• pp.131-140
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• 2020

The characteristics of ballistic missiles are changing rapidly but studies have mostly focused on fragmentary flight trajectory analysis estimating the changing characteristics of some types, while there is a lack of research on comprehensive and efficient ballistic search, detection and prediction for missiles including the new types that have been gaining attention lately. This paper analyzes the flight trajectory characteristics of ballistic missiles at various ranges considering flight path angle adjustment, specific impulse and drag force with altitude based on the optimized equations of motion reflecting the parameters of North Korea's general and new types of ballistic missiles. The flight trajectory characteristics of representative ranges for each ballistic missile were analyzed by adjusting the flight path angle in the minimum energy method, lofted method, and depressed method. In addition, High value target can attacked by ballistic missiles considering flight path angle adjustment at various points. It's expected to be used to Threat Evaluation and Weapon Allocation, and deployment of defense systems by interpreting the analysis of the latest Iskander-class ballistic missiles and the new multiple rocket launcher.

• 한국군사과학기술학회지
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• 제23권4호
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• pp.355-362
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• 2020

EFP composed of explosive, charge and liner generally penetrates standoff a target by Monroe effect. Its performance highly depends on penetrator characteristics and flight stability. Penetration ability can be dramatically reduced when the penetrator reaches the target with AOA, even if the penetrator has high kinetic energy and L/D ratio. Therefore, it is important to research not only penetrator characteristics and but also flight stability. In this work, the effect of liner shape on penetrator characteristics was examined using free flight test and numerical tools. It was found that tip velocity of penetrator was increased with decreasing liner thickness. It was also found that thicker liner had higher static margin leading to better flight status.

• 한국윤활학회:학술대회논문집
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• 한국윤활학회 2002년도 제35회 춘계학술대회
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• pp.285-290
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• 2002

Screw in injection molding machine is affected by heat flux, pressure on inside barrel, geometry of screw including flight number, pitch and flight angle. Volumetric efficiency increases as the flight number increases, but it didn't show steady tendency according to helix angle of flight. Heat flux from heating pad and injection pressure play a very important role on the thermal behavior characteristics. The increased number of multi-flight is merits and demerits for a screw efficiency. So, we have to optimize flight number of the screw considering temperature, displacement, distortion and stress of the screw.

• 한국국방경영분석학회지
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• 제32권1호
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• pp.176-187
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• 2006

탄도미사일은 비행속도가 매우 빠르고 불안정한 하강운동에 기인하는 나선형과 같은 고유의 특이한 비행운동으로 인해 정확한 비행궤적의 추정이 어렵다. 이 논문은 탄도미사일의 비행궤적 특성에 대한 종합적인 해석을 기술한다. 최대사거리를 포함 다양한 미사일 비행사거리에 따른 비행궤적특성이 해석적 방법에 의해 도출되었다. 최대사거리를 줄여 발사했을 때 비행특성에 따른 위협이 급격히 증가됨을 해석적으로 나타냈다. 이 연구는 하층미사일방어체계 구축의 운용개념 설정에 대한 기반연구이다.

• 한국항공운항학회지
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• 제19권1호
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• pp.1-6
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• 2011

The free-wing tilt-body aircraft is researched in the flight performance characteristics such as short take-off and landing capability, and reduced sensitivity to gust and center of gravity (CG) change. Due to the main wing separating from the fuselage, the high tiltable empennage, and the stub-wing strongly influencing from the propeller wake, the resulting vehicle aerodynamics and flight dynamics are quite different from those of a conventional fixed-wing aircraft. Using the governing flight dynamics model was studied previously, all of speed and body tilt angle is simulated to determine the flight envelope by a non-linear 3-DOF flight simulation analysis. Though flight performance and trimmability are studied, the flight model of free-wing tilt-body aircraft is to reduce the hidden risk and to achieve the successful flight test. It is analyzed the flight characteristics that distinguishes free-wing tilt-body aircraft from the conventional aircraft.

• 한국정보통신학회:학술대회논문집
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• 한국정보통신학회 2021년도 춘계학술대회
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• pp.189-192
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• 2021

항적추적 기술에 딥러닝 기반 LSTM(Long Short-Term Memory) 모델을 적용하는 연구로서 기존의 항적추적기술의 경우, 항공기의 등속, 등가속, 급기동, 선회(3D) 비행 등 비행 특성에 따른 칼만 필터 기반의 LMIPDA를 활용한 실시간 항적 추적 시 등속, 등가속, 급기동, 선회(3D) 비행 가중치가 자동으로 변경된다. 이러한 과정에서 등속 비행 중 급기동 비행과 같이 비행 특성이 변경될 때, 항적 손실 및 항적 추적 성능이 하락하여 비행 특성 가중치 변경성능을 향상시킬 필요성이 있다. 본 연구는 레이더의 오차 모델이 적용된 시뮬레이터의 Plot과 표적을 딥러닝 기반 LSTM(Long Short-Term Memory) 모델을 적용하여 학습시키고, 칼만 필터를 활용한 항적추적 결과와 딥러닝 기반 LSTM(Long Short-Term Memory) 모델을 적용한 항적추적결과를 비교함으로써 미리 비행 특성의 변경과정을 예측하여 등속, 등가속, 급기동, 선회(3D) 비행 가중치변경을 신속하게 함으로써 항적추적성능을 향상하기 위한 연구이다.

• 한국항공운항학회지
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• 제24권4호
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• pp.81-86
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• 2016

Unmanned aerial vehicles(UAVs) are increasingly used in civilian areas as well as in military areas due to the technological advancement of UAVs. In response to the increasing demand in UAVs, many studies are under way to integrate the airspace between manned aircraft and UAV. The development of flight test can secure the performance and flight characteristics of the designed aircraft. And the capability of research and development can be expanded through the accumulation of technical data. It is also essential to verify the correct performance and characteristics of development aircraft themselves. In this paper, we propose development flight test procedures and items for civilian UAVs.

• 한국항공운항학회지
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• 제19권4호
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• pp.1-5
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• 2011

The free-wing tilt-body aircraft is researched in the flight performance characteristics for center of gravity (CG) change. All of speed, body tilt angle and center of gravity change are simulated to determine the flight envelope by a non-linear 3-DOF mathematical model. In flight, this aircraft configuration changes by the tiltable empennage. Then, flight dynamics distinguishes from those of a conventional fixed-wing aircraft. Though flight performance and trimmability are studied by CG change, the flight model of free-wing tilt-body aircraft is to reduce the hidden risk and to achieve the successful flight test. It is analyzed the flight characteristics by CG change that distinguishes free-wing tilt-body aircraft from the conventional aircraft.