• 한국항공우주학회지
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• 제38권6호
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• pp.530-536
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• 2010

비행 중 대기조건에 의한 결빙은 항공기 안전성과 직결되며, 특히 항공기 표면 발생 결빙은 공력 특성 변화를 야기하여 제어면 성능을 저해하는 요소가 된다. KC-100 항공기의 결빙에 의한 공력 영향성 조사를 위해 결빙 전문 CFD 코드인 FENSAP-ICE를 이용하였다. 항공기의 공력 특성을 대표하는 주날개 단면 익형을 먼저 고려하고 다음으로 전기체형상에 대해 결빙 해석을 수행하였다. 또한 Anti-Icing 및 De-Icing 장치 설계를 위해 항공기 부품별 결빙 영역 및 결빙 증식 크기를 조사하였다. 결빙 영역은 주날개 및 수평 꼬리날개의 앞전에서 단면 코드길이 기준 약 7.07%, 11.2% 범위를 나타냈고, Wind Shield의 경우 약 16.7%에서 결빙이 발생하였다. 결빙에 의한 공력특성 변화의 경우, 받음각 0도에서 KC-100 항공기의 양력은 64.3% 감소한 반면 항력은 55.2% 증가하였다.

• 한국전산유체공학회지
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• 제19권3호
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• pp.20-23
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• 2014

The flow pattern inside the inlet chamber of the tube side is one of the key parameters influencing on the performances of the shell-and-tube type of heat exchangers(STHE). In order to improve the flow distribution, the baffle shaped as the porous plate is installed in the inlet chambers. In the present study, numerical simulation has been performed to investigate the flow features of the tube side of the STHE in sense of the hydraulic performances. The flow fields have been analysed by the three-dimensional Navier-Stokes solvers with the proper turbulent models. Computational domain is ranged in the whole of the tube side of the STHE. The numerical results showed that the presence of the baffles improves the redistribution of the flow injecting to the tube bundels. The good agreements of the numerical results with the experimental results of PIV measurements have been shown for the validation of the numerical methods adopted in the present papers.

• 전기학회논문지
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• 제66권9호
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• pp.1341-1350
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• 2017

In this paper, a high reliability 30W DC-DC converter is designed considering military standard (MIL-STD) for military applications such as guided weapon and aircraft. The performances and specifications of conventional military grade DC-DC converter are practically analyzed. The requirements for military grade DC-DC converter are established in consideration of MIL-STD and analysis results of conventional product. Two isolated DC-DC converter, forward and fly-back converter, are designed and compared to determine topology. From experimental results under various operating conditions, the forward topology satisfied performances and specifications of MIL-STD for military DC-DC converter.

• 한국항공우주학회지
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• 제43권8호
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• pp.739-747
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• 2015

무인항공기시스템 수요의 증가와 기술의 급격한 발전에 따라, 많은 국가들에서 기존의 공역 시스템에 무인항공기를 통합하려는 시도가 이루어지고 있다. 통합 운용을 위한 규정을 제정하기 위해서는 비행성능의 차이, 통제와 통신의 특징, 항공기간 분리 방법, 인간과 기계의 상호작용과 같은 무인항공기의 통합이 전체 시스템에 끼치는 영향에 대한 이해가 중요하다. 인하대학교에서는 공역 내에서의 무인항공기의 영향을 실제 운용 인력이 참여하는 Human-in-The-Loop(HiTL) 시뮬레이션을 통하여 연구할 수 있는 항공관제시뮬레이션 시스템을 개발하였다. 본 논문에서는 이를 이용하여 무인항공기와 유인기가 조우하는 3가지의 시나리오를 설정하고, 관제사의 관제명령을 통하여 위험 상황을 해결하는 시험을 진행하여 조종사와 관제사의 반응 속도와 각 기동에 대한 위험도를 분석한 과정과 결과를 제시한다.

• 산업경영시스템학회지
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• 제41권4호
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• pp.59-69
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• 2018

This study deals with the case study on the pallet quantity determination problem for the flexible manufacturing system producing 32 different types of aircraft wing ribs which are major structures of an aircraft wings. A Korean company has constructed the WFMS (wing rib flexible manufacturing system) that is composed of several automated equipments such as the 5-axis machining centers, the RGV (rail guided vehicles)s, the AS/RS (automated storage and retrieval system), the loading/unloading stations, and so on. Pallets play a critical role in the WFMS to maintain high system utilization and continuous work flow between 5-axis machining machines and automated material handling devices. The discrete event simulation method is used to evaluate the performance of the WFMS under various pallet mix alternatives for wing rib manufacturing processes. Four performance measures including system utilization, throughput, lead-time and work in process inventory level are investigated to determine the best pallet mix alternative. The best pallet mix identified by the simulation study is adopted in setting up and operating a real Korean aircraft parts manufacturing shop. By comparing the real WFMS's performances with those of the simulation study, we discussed the cause of performance difference observed and the necessity of developing the CPS (cyber physical system).

• 융복합기술연구소 논문집
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• 제5권2호
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• pp.27-32
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• 2015

Air intakes are an essential component of aircraft engines. They are mainly used to offer uniform airflows to engine faces. Fighter aircraft have to mask the engine face inside the fuselage in order to reduce the Radar Cross Section(RCS). Therefore, offset intakes like a S-Duct are one of promising components for this purpose. During a fight, it is unavoidable that the flow will enter the intakes at some face angles other than zero. In this case, the performance of the aircraft engine will be influenced to the angle of incidence. In this study, the CFD analysis of the semi-circular S-Duct with AR(0.5,0) is performed to investigate the influence of the angle of incidence on the performance of the S-Duct using a distortion coefficient. To consider the adverse pressure gradient, a $k-{\omega}$ SST turbulence model is employed. The secondary flow and flow separation are observed for all computational cases. It is found that the positive incidence angle produces the best performances.

• 한국항공운항학회지
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• 제22권2호
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• pp.1-8
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• 2014

This paper introduces a new framework of predicting the arrival time of an aircraft by incorporating the probabilistic information of what type of trajectory pattern will be applied by human air traffic controllers. The proposed method is based on identifying the major patterns of vectored trajectories and finding the statistical relationship of those patterns with various traffic complexity factors. The proposed method is applied to the traffic scenarios in real operations to demonstrate its performances.

• 한국시뮬레이션학회:학술대회논문집
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• 한국시뮬레이션학회 2003년도 춘계학술대회논문집
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• pp.3-8
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• 2003

A Simulation S/W is developed to evaluate performances of MLS (Microwave Landing System) and IBLS(Integrated Beacon Landing System) in precision auto-landing. For this study classical PID and optimal LQG controllers are developed as well as mathematical models of MLS and IBLS. Ship-landing condition is also considered by assuming sinusoidal movement of the ship in the pitch direction. The simulated aircraft is F-16 in the study of precision auto-landing. For the integrated simulation environment GUI windows are designed for input of parameter values necessary for simulation, such as vehicle performance and environmental data. For validation and verification of models various comparison graphs of simulation outputs are comprised in the GUI design as well as 3D visual simulation of vehicle dynamics.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2004년도 추계 학술대회논문집
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• pp.165-171
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• 2004

Smart UAV, which adopting tiltrotor aircraft concept, requires long endurance and high speed capability simultaneously These two contradictable flight performances are hard to meet with single wing concept and inevitably require the operation of flap system which should reveal optimal performance for each flight mode. In order to design SUAV flaperon satisfying the performance requirement, various configurations are generated and their aerodynamic performances are analyzed using numerical flow computations around flaps. Considering aerodynamic performance and manufacturing simplicity, a final flap configuration is selected.

• Advances in aircraft and spacecraft science
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• 제2권4호
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• pp.469-482
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• 2015

This study has the aim to develop a numerical design regarding the position and the inner performances of a heat exchanger in a light helicopter. the problem was to find first of all the best position of the heat exchanger inside the engine vane in order to maximize the air flow rate capable to pass through the heat exchanger section. It is to be said that the only air contribution in the vane comes from the opening present in the roof under the main rotor. The design has been performed by means of the commercial code Fluent and using the well known grid generator ICEM CFD. Different positions are first investigated so to establish the best one. Subsequently, different areas of the opening on the roof have been considered in order to maximize even more the flow rate in the heat exchanger that was not sufficient based on the first guess of velocity, as aforementioned. At the end interesting design results are presented and discussed by contours of fields and values.