• 한국생산제조학회지
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• 제23권3호
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• pp.284-290
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• 2014

Aluminum alloy is a core material for structural parts of aircraft and automobiles to reduce the weight and maintain high specific strength. This study evaluates the machinability and investigates the optimal cutting conditions considering the surface integrity and productivity for Al7050-T7451 milling. The machining variables considered are the feed per tooth, spindle speed, axial depth of the cut, and radial depth of the cut. The machinability evaluation of Al7050-T7451 is conducted by analyzing the cutting force signals, acceleration signals, AE signals, and machined surface conditions. The optimal cutting conditions are determined by analyzing the experimental results using response surface methodology for stable machining considering the productivity and surface integrity.

• 한국생산제조학회지
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• 제25권3호
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• pp.211-216
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• 2016

Al alloys are useful materials having high specific strength and are used in machining of parts having thin-walled structures for weight reduction in aircraft, automobiles, and portable devices. In machining of thin-walled structures, it is difficult to maintain dimensional accuracy because machining deformation occurs because of cutting forces and heat in the cutting zone. Thus, cutting conditions and methods need to be investigated and cutting signals need to be analyzed to diagnose and minimize machining deformation and thereby enhance machining quality. In this study, an investigation on cutting conditions to minimize machining deformation and an analysis on characteristics of cutting signals when machining deformation occurs are conducted. Cutting signals for the process are acquired by using an accelerometer and acoustic emission (AE) sensor. Signal characteristics according to the cutting conditions and the relation between machining deformation and cutting signals are analyzed.

• 한국기계가공학회지
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• 제13권4호
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• pp.99-105
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• 2014

The domestic airline industry undertakes the production of finished products by assembling existing self-described components via a design process which involves assembly and production steps, after which many of the finished products are exported. However, high reliability and stability must be guaranteed, because customers require high-precision components at the time of manufacturing. In the aircraft parts industry, the mass production of high-value-added parts is limited. Therefore, a small production scale depending on the part is used, as many types of conventional CNC lathe machines with X-axis and Z-axis as well as Z-axis and C-axis CNC milling are used. The parts also rely on high-pressure air to increase production. The most important factors are good stability during processing, as high-precision parts are required, as noted above. It was found that as the C-axis rotation speed increased, the diameter of the cutting tool decreased with a decrease in the surface roughness, while the workpiece rotation speed increased with an increase in the surface roughness.

• 한국기계가공학회지
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• 제17권5호
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• pp.1-7
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• 2018

Flexible track drilling machines are credited with important applications in the area of aircraft manufacturing because of their portability, quick installation capabilities, and high efficiency. However, their structures are special and the constitution principles and motion characteristics are difficult to control, increasing the development costs and research cycle in the context of the technology blockade of foreign companies. The simulation analysis of flexible track drilling machines can be conducted by applying virtual prototypes, shortening the development cycle and reducing the cost. In this paper, a model of a machine is established by using the SolidWorks software and imported into ADAMS to conduct kinematic and dynamic simulation analysis. During the analysis, the feasibility of the configuration is checked, a reasonable driving motion is chosen, potential deficiencies are found, and improvement actions are raised.

• 한국군사과학기술학회지
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• 제12권6호
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• pp.808-814
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• 2009

Numerical flow-filed computations have been conducted around a projectile with a triangular ballute at Mach numbers of 0.3 ~ 0.9 and angles of attack of $0^{\circ}\;{\sim}\;30^{\circ}$. The expansion shape of a triangular ballute has been determined from both the manufacturing dimensions and the wind tunnel test results. It has been assumed that the shape does not alter after the ballute has been expanded completely. The computed results showed a good agreement with the wind tunnel test results. A sensitivity analysis on the aerodynamic coefficients has been performed to evaluate the quantitative effects on the flight performance. Trajectory simulation results were also in good agreement with the flight test results.

• 대한산업공학회지
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• 제43권3호
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• pp.229-237
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• 2017

Presented in this paper is a case study of constructing a smart factory for aircraft parts. The construction procedure involves four phases. First of all, its management goals are set, and layout design and simulation are carried out in the conceptual design phase. In the detail design phase, operating scenarios for each module are written out, and probable risks are analyzed by expert groups, and then requirements for developing equipments and subsystems are determined with consideration for element technologies and their integration schemes into the smart factory. In the fabrication and installation phase, system development, equipment fabrication and installation are proceeded in a separate manner, and then integrated together subsequently. In the operation and improvement phase, the factory is stabilized, sophisticated and improved constantly during real operation.

• International Journal of Aeronautical and Space Sciences
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• 제18권1호
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• pp.82-90
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• 2017

The aim of this work is to develop a new computational program to determine the effect of using the gas of propulsion of combustion chamber at high temperature on the shape of the two-dimensional Minimum Length Nozzle giving a uniform and parallel flow at the exit section using the method of characteristics. The selected gases are $H_2$, $O_2$, $N_2$, CO, $CO_2$, $H_2O$, $NH_3$, $CH_4$ and air. All design parameters depend on the stagnation temperature, the exit Mach number and the used gas. The specific heat at constant pressure varies with the temperature and the selected gas. The gas is still considered as perfect. It is calorically imperfect and thermally perfect below the threshold of dissociation of molecules. A error calculation between the parameters of different gases with air is done in this case for purposes of comparison. Endless forms of nozzles may be found based on the choise of $T_0$, $M_E$ and the selected gas. For nozzles delivering same exit Mach number with the same stagnation temperature, we can choose the right gas for aerospace manufacturing rockets, missiles and supersonic aircraft and for supersonic blowers as needed in settings conception.

• 항공우주정책ㆍ법학회지
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• 제5권
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• pp.321-384
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• 1993

The paper is to study and analyze the civil aviation industry of China and to present some cooperative and developing models between Korea and China in the fields of civil aviation on the basis of mutul benefit. In this study, civil aviation includes both the air transport industry and aircraft manufacturing industry. As it is not easy and realistic for us to conduct field survey on the civil aviation of China so far, this study has havily depended upon the literature data gathered from the ICAO and other published materials. This study includes the following major contents. 1. The historical development of China civil aviation 2. The present status and future prospect of Civil Aviation Adminstration of China(CAAC) 3. The present status of Chinese aircraft industry 4. Administration of airport and airspace of China 5. Air transport industry of China 6. The design of Korea-China civil aviation cooperation

• 한국항공우주학회지
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• 제37권8호
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• pp.751-758
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• 2009

본 논문에서는 항공기 구조용 탄소 복합재 단일겹침 접착 체결부에서, 파손하중에 영향을 미치는 주요인자들의 효과를 실험으로 연구하였다. 실험을 위해 제작공정 4가지, 겹침 길이 5가지, 모재 두께 4가지에 대한 시편 총 335개를 제작하였다. 예상대로 겹침길이가 감소할수록, 모재두께가 증가할수록 파손강도가 높아지는 것을 확인하였다. 그러나 제작공정의 측면에서는, 접착제가 없는 일체성형 시편과 이차접착 시편의 강도가 동시접착이나 접착제를 사용한 일체성형 시편에서보다 높은 파손강도를 보이는 흥미로운 사실을 발견하였다. 특히 이차접착 시편의 강도가 일체성형 시편의 강도와 유사하거나 더 높은 현상을 발견하였는데, 이는 접착제의 강도가 모재의 층간강도보다 높거나 최소한 비슷한 수준임을 의미하는 것으로 볼 수 있다.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2005년도 춘계학술대회논문집
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• pp.692-697
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• 2005

좋은 날개 실속특성 및 실속/스핀의 특성이 입증된 선미익형 항공기를 현재 개발중에 있다. 전에 개발된 1호기 및 2호기 시제기는 코어 샌드위치 형식으로 날개 전체가 채워지고 고정식 착륙장치로 제작되었다. 새로이 개발될 반디호는 접개식 착륙장치와 날개와 동체에 일반적인 폼 코아 샌드위치층이 장착될 예정이다. 제작을 위해 시편 시험을 포함한 복합 소재 제작 공정이 연구되었고 적층 몰드를 이용하여 유리 섬유 천으로 폼 코어 위로 상온 적충하는 방식이 채택되었으며, 복합소재 부품들은 실온과 대기압하에 경화시킨다. 일반적으로, 몰드부품들은 양산에 적합한 매끄러운 표면 조도와 표준 품질을 보여주었다. 본 연구에서는 소형 항공기 반디호 몰드 기술과 개발 상황을 기술하였다.