• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2000년도 제14회 학술강연논문집
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• pp.8-8
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• 2000

In this paper are presented main power and gasdynamic characteristics of C-l6VK hypersonic test cell of Research Test Center of CIAM. Gasdynamic adjustment of the C-l6VK test cell was carried out with the working section constructed on scheme of Ramjet/scramjet test in free stream. Gasdynamic adjustment was conducted stage by stage in tile following sequence. First, check and preparation of all technical systems and checking measuring system. Than determination of the characteristics of test cell on cold (without the heating of air at entrance) regime and determination of the characteristics of test cell on regimes with the heating of air. Finally determination of tile characteristics of test cell with the loading of the working part by object. On tile final stage of gasdynamic adjustment two experiments with tile axisymmetric Scramjet model loaded into the working part of test cell were conducted. The first experiment was conducted with the purpose of determination of flow parameters with the object leaded into the working part and verification of experiment cyclogram. The second experiment was conducted with injection of hydrogen into the combustion chamber of object, that is tile conditions on test cell simulated Scramjet flight Mach number M = 6. Such methodology of gasdynamic adjustment allows to determine influence of experimental object on flow parameters in the working part at different conditions of experiment (with the burning in combustion chamber of object and without the homing), and also to compare flow characteristics in the object duct.

• 한국항공우주학회지
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• 제30권8호
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• pp.30-36
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• 2002

풍동시험 모형은 모형 지지부 삽입 등으로 실제 비행체와 다른 형상을 갖게 된다. 이러한 형상의 차이는 비행시험과 다른 힘과 모멘트를 발생시키게 되므로 이에 대한 보정은 필수적이다. 이러한 보정에는 cavity 압력 보정, 모형 지지부 간섭 보정 등이 있다. 본 시험에 사용된 모형은 내장밸런스와 함께 벨리 스팅 지지부를 사용하였으며 보정을 위하여 모형지지부 두께변화 방법과 더미 스팅 방법, wire support 방법의 시험결과를 비교하였다. 모형 지지부 두께 변화 방법은 간섭이 거의 없는 것으로 알려진 wire support 방법과 시험결과가 잘 일치하였다.

• 한국항공우주학회지
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• 제32권6호
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• pp.72-80
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• 2004

본 논문에서는 추력중단 후 무유도방식 유도탄의 추력비행단계 유도알고리듬의 설계과정을 다룬다. 유도의 목적은 추력중단 시점에서 요구속도벡터를 성취하기 위한 것이다. 구현 가능한 피치평면 비행궤적을 조사하기 위해 네 가지 성능지수에 대한 비행궤적 최적화를 수행하였다. 궤적최적화 결과로부터 구속조건들을 만족시키기 위해서는 비행초기에 고앙각 기동이 필요함을 알 수 있다. 제안된 유도알고리듬은 개루프 피치자세각 명령 산출기인 피치프로그램과 증가요구속도벡터를 0으로 만들기 위한 요자세각 명령 산출기로 구성된다. 피치프로그램은 궤적최적화 결과 얻어진 피치자세각 선도를 이용하여 구성되었다.

• 한국항공운항학회지
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• 제21권4호
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• pp.112-118
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• 2013

Air travel demand has recently been growing and establishment and operation of low-cost carriers have been increased. Against this backdrop, low-cost carriers need to figure out diversified customer demand for low-cost carriers and ways to maximize marketing efficiency before applying it to the field so that they can attain superiority to large carriers in increased intensified competition. Low-cost carriers need to be differentiated from other carriers for the purpose of improving profits. Toward this end, this study conducted analysis on importance and satisfaction with carrier choice using IPA with regard to low-cost carrier customers. In conclusion, the paper accurately examined advantages and disadvantages of low-cost carriers compared to general carriers based on results of IPA analysis and suggested managerial strategies to enhance competitiveness based on division into four parts including maintenance and enforcement (1st quadrant, Delay compensation, Booking rapidity, Check rapidity, Crew service, refund service, baggage service, punctuality, transit services, airlines images), concentrated improvement (2nd quadrant, price, Convenience of seat), passive administration (3rd quadrant, Boarding service, cabin cleanliness, flight schedule, whether local crew on board, meal service, in-flight entertainment service), and enhanced satisfaction (4th quadrant, duty-free service, Variety of routes), so that practical suggestions could be presented to employees working in the field.

• 항공우주기술
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• 제12권1호
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• pp.54-63
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• 2013

항공기의 자세제어를 담당하는 각각의 비행 조종면에 중복안정성 등의 이유로 여러 개의 작동기를 연결하여 사용하고 있다. 다중 작동기들이 동시에 정확하게 같은 위치로 이동하지 않으면 비행조종면에 변형이 발생한다. 그 결과 변형된 조종면이 원래 상태로 복원하려는 힘에 의해 작동기들 간에 force fighting이 발생한다. 게다가 force fighting은 각 장치들의 초기 허용 오차 등에 의해서도 발생한다. 다중 작동기간의 force fighting 현상은 제어정밀도에 영향을 미치고 피로파괴의 원인이 되어 작동기와 비행조종면의 수명을 단축할 수도 있다. 본 논문에서는 두 개의 서보작동기를 사용하는 시스템의 force fighting을 감소하기 위하여 힘되먹임제어를 사용하는 제어기를 설계하였다.

• 한국항공운항학회지
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• 제22권4호
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• pp.15-24
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• 2014

Low Cost Carrier(LCC)s in Asia Pacific market are expected to record high growth due to the expansion of Open Sky Policy among Korea, Japan, China and South East Asia. As everybody is aware of, LCC is not only saving flight cost but also creates differentiating business model by reducing unnecessary services such as F&B and in-flight duty free sales services. Booming LCCs in Asian market will cause not only Incheon airport but also other local airports in Korea to compete heavily to attract LCCs. For example, Air Asia Group with more than 200 fleet has expanded its alliance network throughout Asia. Therefore this paper has researched a new business model operating a LCC terminal for the hub airport competitiveness. According to analysis result of case study, it was found out, considering increasing airline demand next decade, Incheon airport and other domestic airports in Korea had better change an existing terminal into a LCC Terminal(LCCT) to differentiate airport services and expand its hub network. That is because of economic feasibility, first of all, of securing hub and spoke networking capabilities with airlines and finally of developing commercial facilities customizing LCC passengers' demand.

• Advances in aircraft and spacecraft science
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• 제6권1호
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• pp.31-49
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• 2019

Flutter is a dangerous phenomenon encountered in flexible structures subjected to aerodynamic forces. This includes aircraft, helicopter blades, engine rotors, buildings and bridges. Flutter occurs as a result of interactions between aerodynamic, stiffness and inertia forces on a structure. The conventional method for designing a rotor blade to be free from flutter instability throughout the helicopter's flight regime is to design the blade so that the aerodynamic center (AC), elastic axis (EA) and center of gravity (CG) are coincident and located at the quarter-chord. While this assures freedom from flutter, it adds constraints on rotor blade design which are not usually followed in fixed wing design. Periodic Structures have been in the focus of research for their useful characteristics and ability to attenuate vibration in frequency bands called "stop-bands". A periodic structure consists of cells which differ in material or geometry. As vibration waves travel along the structure and face the cell boundaries, some waves pass and some are reflected back, which may cause destructive interference with the succeeding waves. In this work, we analyze the flutter characteristics of a helicopter blades with a periodic change in their sandwich material using a finite element structural model. Results shows great improvements in the flutter forward speed of the rotating blade obtained by using periodic design and increasing the number of periodic cells.

• 한국환경과학회지
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• 제26권6호
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• pp.779-788
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• 2017

In this study, we analyzed the changes in the echolocation and prey-capture behavior of the horseshoe bat Rhinolophus ferrumequinum from search phase to capture time. The experiment was conducted in an indoor free-flight room fitted with an ultra-high-speed camera. We found that the bats searched for food while hanging from a structure, and capturing was carried out using the flight membrane. In addition, it was confirmed that the mouth and uropatagium were continuously used in tandem during the capturing process. Furthermore, using Constant Frequency (CF), we confirmed that the prey catching method reflected the wing morphology and echolocation pattern of R. ferrumequinum. The echolocation analysis revealed that the pulse duration, pulse interval, peak frequency, start-FM-bandwidth, and CF duration decreased as the search phase approached the terminal phase. Detailed analysis of echolocation pulse showed that the end-FM bandwidth, which increases as it gets nearer to the capture time of prey, was closely related to the accurate grasp of the location of an insect. At the final moment of prey capture, the passive listening that stopped the divergence of the echolocation was identified; this was determined to be the process of minimizing the interruption from the echo of the echolocation call emitted from the bat itself and sound waves emitted from the prey.

• 한국항행학회논문지
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• 제23권6호
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• pp.522-525
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• 2019

기존 항행안전시설 지상점검의 한계점을 극복하기 위해서 한국공항공사는 항행안전시설 점검용 드론시스템을 개발하였다. 드론시스템을 이용한 항행안전시설 점검은 사용자(항공기) 입장에서 공중 전파신호를 점검할 수 있다 장점이 있다. 또한 드론은 항공기와 비교하여 비행경로가 자유롭고 비행속도의 제어가 용이하기 때문에 공중 전파신호를 보다 면밀히 점검할 수 있다. 최근 공항주변개발의 가속화에 따라 항행안전시설 전파신호의 품질저하에 대한 우려가 고조되고 있다. 이에 따라, 항행안전시설 전파왜곡현상을 분석하기 위해 드론을 활용한 전파환경조사를 진행하였다. 드론의 비행경로별 신호수신 시 항행전파신호가 왜곡되는 구간을 측정·분석하여 반사파가 발생되는 원점을 특정화하였다.

• 한국항공우주학회지
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• 제43권6호
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• pp.516-525
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• 2015

본 연구에서는 정지 비행과 저속 하강 비행하는 회전익기 로터에 대한 소음을 예측하고 실험값과 비교하여 검증하였다. Ffowcs Williams-Hawkings 방정식을 이용한 소음압 예측 프로그램을 개발하였다. 해석 결과의 검증을 위해서 2가지 풍동 시험 결과를 이용하였다. Boeing 360 모델 로터를 이용하여 정지 비행 조건에서의 저차 주파수 대역의 소음압을 검증하였고, HART II 로터를 이용하여 저속 하강 비행 조건의 중간 주파수 대역의 BVI 소음을 검증하였다. 하중 소음을 예측하기 위해서 정지비행 조건에서는 자유후류기법을 통한 공력계수를 이용하였고, 저속 하강 비행 조건에서는 CFD/CSD 연계해석 결과를 이용하였다. 소음해석 결과 저차 주파수 대역의 소음압과 중간 주파수 대역의 BVI 소음압을 비교적 잘 예측하는 것을 확인하였다. BVI 소음압은 FFT 해석을 통하여 소음 방사 지도를 그려 실험결과와 비교하였다. 비교 결과 시험결과와 비교적 유사하게 예측하는 것을 확인하였다.