• 한국항공운항학회:학술대회논문집
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• 2016.05a
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• pp.1-4
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• 2016

항공기 사이징은 항공기 설계에서 설계 및 임무 요구조건을 만족하기 위한 항공기의 무게를 계산하는 과정이다. 사이징 프로그램은 엔지니어가 기본적인 파라미터만 입력하면 내장된 코드에 의하여 자동적으로 사이징 과정을 수행하여 주는 프로그램을 말한다. 본 연구에서는 개발된 프로그램의 프로세스, 프로그램 구성을 설명하고 실행 예를 통하여 사용자가 편리하고 직관적으로 활용할 수 있는 사이징 프로그램을 개발하였다. 개발 된 프로그램은 사이징 과정에서 편리한 임무작성, 입력된 임무에 따른 임무형상 도시, 그리고 사이징 및 임무해석결과를 한눈에 확인할 수 있는 것이 특징이다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.2
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• pp.22-31
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• 2005

A design study was conducted for a new concept aircraft(Canard Rotor/Wing: CRW) that has the capability of dual mode flight, a rotorcraft and a fixed wing mode. The CRW can show a vertical take off/landing and a high speed/efficiency cruise performance simultaneously. It is not surprising to develop a new sizing code for this class of aircraft because conventional sizing codes developed solely for either the rotary wing or the fixed wing aircraft are not adequate to design a dual mode aircraft operated both by the rotary wing through tip jet effux and the fixed wing lift. Thus, a new design code was developed based on the conventional sizing code by adding some features including rotor performance, duct flow, and engine flow analysis, hence could eventually predict the performance of reaction driven rotor, the flight performance and the flight characteristics. The various design parameters were investigated to find their influences on the flight performance then, a small UAV(Unmanned Aircraft Vehicle) of 1500 lbs class was optimally designed to have minimum weight using the developed sizing code.

• Aerospace Engineering and Technology
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• v.8 no.1
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• pp.117-131
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• 2009

In this study, a detail design was conducted for KSLV-1 1st stage Rear Fuselage Upper Compartment assembly. A basic structural sizing was done by the aircraft fuselage sizing in-house program. The frame structural design and the interface check were conducted by the FE and the CAD program. The structural margin of safety was conformed by FE analysis for the normal section model and duct cut-out section models which are the weakest parts of the rear fuselage. The shear stress analysis was performed for a fastener design of the skin-stringer which is most affected by the shear stress induced by the shear load.

• 한국항공운항학회:학술대회논문집
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• 2007.12a
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• pp.88-92
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• 2007

• Journal of the Korea Fashion and Costume Design Association
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• v.18 no.1
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• pp.191-203
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• 2016

The 3D virtual fitting system is a new and very efficient system replacing real fitting in apparel industry and on-line shopping. It is a win-win system for both of consumer and manufacturer which not only reduces design and production time but also resolves consumer's complaints by checking the wearing image beforehand. It is a must-have item in the future. The purpose of this study is to analyze sizing menu, terms, and current status and to figure out problems of avatar sizing programs which substitute human bodies in virtual fitting. We chose three existing outstanding programs in domestic and global market, compared and analyzed the program, manual, and terms that are used in avatar sizing, and investigated the strengths, weaknesses, problems of options and terms and finally suggested an alternative terms. The revealed problems are as follows: each program supports various avatars ranging from male to female, from child to adult, and from oriental style to western style. The image of the avatar could be changed through the options for hair style, shoes and accessories. But we found out some problems. The avatar body types are far from actual human body types, avatar sizing menus and item terms are different from program to program, and terms not yet standardized. Cooperative efforts of industry and academy on standardization of sizing menus and terms should be emphasized for the virtual fitting system to be widely used like the other computer graphic programs or word editors.

• Culinary science and hospitality research
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• v.19 no.3
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• pp.1-17
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• 2013

This research was to examine the effects of downsizing kitchen employees in a hotel on their job efficiency and to verify differences in the individuals' behavior characteristics according to DISC behavior types in this causal relationship. Through SPSS 17.0 program, factor analysis, reliability analysis, correlation analysis, and multiple regression analysis were conducted on 200 samples secured for an empirical research. Two factors for the downsizing items and two factors for the items related to job attitude were extracted. Hypothesis 1 was that the downsizing within a hotel has significant negative (-) effects on job attitude. As a result of the verification, it was found that downsizing had significantly negative effects on the job attitude of cooking employees as factors for organizational commitment in employment circumstances (${\beta}$=-.256), and employment anxiety (${\beta}$=-.258), and as factors for job satisfaction in employment circumstances (${\beta}$=-.319), and employment anxiety (${\beta}$=-.174). Hypothesis 2 was that the downsizing according to DISC behavior types has significant negative (-) effects on job attitude. As a result of the verification, it was found that in the organizational commitment factors, the dominance type (D) was more influenced by employment anxiety (${\beta}$=-.435) than by any other types, and the conscientiousness type (C) was not influenced by organizational commitment. In the job satisfaction factors, the steadiness type (S) was more influenced by the changes in employment circumstances (${\beta}$=-.414) than by other types, and the dominance type (D) was not influenced. Based on the results of this research, it can be said that hotel's downsizing strategies influence job attitude such as organizational commitment and job satisfaction of cooking employees, and that there are differences in the influences according to the individuals' behavior types of kitchen employees.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.18 no.3
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• pp.1-8
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• 2010

A design study has been performed to obtain configuration and weight of a compound gyroplane. A study of research trends and characteristics was performed to develop the compound gyroplane sizing program. Based on these results, the sizing program has been developed and its suitability has been validated using existing compound gyroplane data. The subject air vehicles was a Challis Heliplane UAV, Carter Coptet, FB-1 Gyrodyne, and Jet Gyrodyne. As results, the program was suitable to size a compound gyroplane at conceptual design phase, because the greatest error rate was less than 10% and the conceptual design allowance error rate is less than 15%.

• Journal of Astronomy and Space Sciences
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• v.24 no.2
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• pp.179-194
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• 2007

The design and analysis of satellite power subsystem is an important driver for the mass, size, and capability of the satellite. Every other satellite subsystem is affected by the power subsystem, and in particular, important issues such as launch vehicle selection, thermal design, and structural design are largely influenced by the capabilities and limitations of the power system. This paper introduces a new electrical power subsystem design program for the rapid development of LEO satellite and shows an example of design results using other LEO satellite design data. The results shows that the proposed design program can be used the optimum sizing and the analytical prediction of the on-orbit performance of satellite electrical power subsystem.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.9
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• pp.850-857
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• 2007

The design and analysis of satellite electrical power subsystem is an important driver for the mass, size, and capability of the satellite. In particular, satellite energy balance analysis is critical in determining the capabilities and limitations of the power subsystem and the success of satellite operations. This paper introduces a new energy balance analysis program for LEO satellite development and shows an example of test results using other LEO satellite design data. The test results show that the proposed energy balance program can be used the optimal sizing of satellite electrical power subsystem and the analytical prediction of the on-orbit energy balance during satellite mission operations.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.2
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• pp.105-114
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• 2008

In this study, the sizing and performance analysis program is developed for the canard rotor wing(CRW) aircraft which operates in dual modes (fixed wing mode and rotary wing mode). The developed program is verified for both fixed wing and rotary wing modes using the existing aircraft data and the design optimization formulation is made to perform the reconnaissance mission. For the canard rotor wing aircraft optimization , multi-objective function is constructed to consider both the fixed wing mode and rotary wing mode the weighting factor. For six design cases with different weighting factors and different design constraints, the optimization is performed and improved rotor design results are derived.