• Journal of the Korean Society for Aviation and Aeronautics
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• v.27 no.4
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• pp.83-95
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• 2019

In order to promote the domestic aircraft manufacturing industry, this study analyzed the limitations of the preceding study on the WTO dispute concerning civil aircraft by summarizing the latest developments and issues in the mid-range aircraft dispute between Brazil and Canada and the large civil aircraft dispute between the United States and the EU. Based on the results of the study, we should look closely at WTO regulations and existing cases of disputes to find maximum support measures, and we believe that in order to stimulate the domestic aircraft manufacturing industry, we should refrain from publicly specifying support measures in the data, such as laws and policies, utilize the WTO SCM Agreement exceptions, and strengthen links with international cooperation and other industries.

• Journal of Aerospace System Engineering
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• v.15 no.6
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• pp.26-32
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• 2021

The global aircraft-manufacturing industry ecosystem is characterized by the international division of labor through the worldwide supply chain and by the concentration of value added at the top of the supply chain. As a result, the competition for entry into the top supply chain and for order expansion is becoming increasingly intensive. To increase their orders, domestic aircraft manufacturing enterprises need to enhance their competitiveness by evaluating and analyzing it. However, most domestic aircraft manufacturing companies are unaware of the need to quantitatively evaluate their competitiveness. It is challenging to perform such an evaluation, and there are few research cases. In this study, we quantitatively evaluated and analyzed the competitiveness of domestic aircraft manufacturers by using data mining techniques. Thereby, implications for enhancing their competitiveness could be identified.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.23 no.1
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• pp.96-102
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• 2015

Composite materials are widely used as structural materials for manufacturing an aircraft, due to their : low weight, low thermal expansion coefficient, production efficiency, anisotropy, corrosion resistance and long fatigue life. The range of using composite materials has been extended from the fuselage and the wings to the entire aircraft structure. In this paper, by analyzing the problems which were generated while designing and fabricating aircraft structures using composite materials, the differences between metallic structures and composite structures are described. In addition, the methodological improvement directions on design and fabricating are described.

• International Journal of Aeronautical and Space Sciences
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• v.16 no.3
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• pp.451-462
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• 2015

Safety is the first priority in civil aviation, and so the International Civil Aviation Organization (ICAO) has introduced and mandated the use of Safety Management Systems (SMS) by airlines, airports, air traffic services, aircraft maintenance organizations, and training organizations. The aircraft manufacturing industry is the last for which ICAO has mandated the implementation of SMS. Since SMS is a somewhat newer approach for most manufacturers in the aviation industry, they hardly believe in the value of implementing SMS. The management of safety risk characteristics that occur during early aircraft development stages and the systematic linkage that the safety risk has to do with an aircraft in service could have a significant influence on the safe operation and life cycle of the aircraft. This paper conducts a case analysis of the McDonnell Douglas MD-11 accident/incident to identify the root causes and safety risk levels, and also verified why aircraft manufacturing industry should begin to adopt SMS in order to prevent aircraft accident.

• Journal of Aerospace System Engineering
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• v.2 no.4
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• pp.38-43
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• 2008

Since UAV has been developed, the demand of uav is increasing because of the advantage which are no injury people and less cost. Also, it has easy maintenance and adaptation because it will carry out each mission by only change payload. So, in this study, we performed aircraft design and manufacturing which it could have maximum payload weight when consider each mission has different weight of payload

• Journal of the Korean Society of Manufacturing Process Engineers
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• v.19 no.2
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• pp.103-110
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• 2020

Riveting is mainly used to assemble the aircraft fuselage. An average of 2~3 workers is needed to assemble an aircraft fuselage consisting of various size frames by riveting. In this study, a riveting process that enables one-person operation using an automated C-frame riveting machine was proposed for improving the efficiency of productivity. The proposed process was verified stability through structural analysis. In the range that can maintain structural stability, panel thickness of the riveting machine and shape were modified to optimizing the shape for reducing the weight of the riveting process. The structural analysis was performed by software ANSYS workbench 19.2. The optimized riveting machine was reduced by 257kg compared to the existing model.

• Journal of the Korean Society of Manufacturing Process Engineers
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• v.15 no.6
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• pp.115-121
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• 2016

The aircraft flight control system controls an aircraft's direction and flying attitude, and actuators are key components of control systems. Actuators can be classified as Geared Rotary Actuator (GRA) and Ball Screw Actuator (BSA). GRA is used in mid-sized aircraft, and BSA is used in larger aircraft. A two-stage differential GRA model was suggested in this paper, and structural analysis and performance tests were performed. According to the analysis and experiment, the stiffness of the two-stage differential GRA was 17.57% higher than that of the conventional GRA, and the structural safety was improved.

• Journal of the Korean Society of Manufacturing Process Engineers
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• v.19 no.9
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• pp.85-92
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• 2020

In this study, the automatic processing of the wing ribs of large aircraft was simulated. Specifically, in the simulation for the automatic processing of the fly ribs, the process of the automated loading device with a robot was examined, along with the wing rib processing and manufacturing automation processes. Moreover, the process time, corresponding to all the stages in the wing rib processing, was calculated. The results pertaining to the machining and manufacturing times of 34 wing ribs (Nos. 1-17), as obtained through the proposed simulation approach, indicated that the total machining time for the left and right wing ribs and rib guns was 537.7 h. The production time was calculated as 1,117.4 h. It is considered that the processing of the wing ribs of large aircraft can be automated in a factory, based on the results of the proposed simulation process.

• Journal of the Korea Institute of Military Science and Technology
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• v.2 no.2
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• pp.83-91
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• 1999

Dynamic characteristic of manufacturing stage is understood and the utilization of each machine is maximized by developing on-line dynamic CAPP system to consider the overloads in the aircraft part manufacturing line. In this paper, a scheme of production planning and scheduling system was proposed through inspection about some predeveloped CAPP system. Developed production planning and scheduling system included process planning module. After precise inspection of some FMS line schema at domestic heavy industry, optimized FMS line was applied to aircraft part manufacturing and repairing factory. By virtue of considering overloads of factory and machine through on-line dynamic CAPP system, the utilization of resources is maximized and manufacturing lead time is minimized.

• Journal of the Korean Society of Manufacturing Technology Engineers
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• v.22 no.1
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• pp.162-167
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• 2013

The most important factor in an aircraft manufacturing is stability and weight reduction. Most of aircraft components are designed with thin plate type to satisfy weight reduction needs. The thin plate is difficult to be machined because it is apt to be vibrated by dynamic force generated in milling process. The most critical factor in machining of aluminum thin plate is width and thickness between stiffeners. So we tested many cases to find out the machinable minimum thickness at different width between stiffeners. And with the data obtained from many tests, this papers suggested the standard width thickness relation that is machinable without vacuum fixture. Machinist will be able to reduce the cost of aircraft thin plate parts by reducing the number of vacuum fixture used by the help of this standard.