• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 1997년도 춘계학술대회논문집; 경주코오롱호텔; 22-23 May 1997
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• pp.539-544
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• 1997

Although the identification of a moving noise source is important in reducing the source power of the transport systems such as airplane or high speed train, the direct measurement of the frequency characteristics is usually difficult due to wind noise when using a microphone running with that noise source. On the other hand the motion of a source causes the frequency characteristics of the pass-by sound measured at a fixed point to be distorted that it is quite difficult to identify the original source characteristics. In this study the relationship between the spectra of the source and the pass-by sound signal is analyzed for a source moving at a constant velocity. The effects of the speed and the frequency characteristics of the source on the pass-by noise spectrum are investigated through numerical simulations.

• 한국항공운항학회지
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• 제17권1호
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• pp.64-70
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• 2009

Because of globalization, flight trips are generalizing, however in proportion to this, it is increasing that people who afraid of riding an airplane because of flight phobia. ‘Flight Phobia’ is individual problem; however it can be factors to suspend of flight schedules. This research is experimental analyzed the recognition degree of flight attendants and cabin attendants about flight phobia and suggested the direction of management about related problems. This research examines meanwhile overlooked importance of flight phobia and the actual condition and if problems are happened, this research will be used valuable to manage quickly and safely.

• 한국항공운항학회지
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• 제15권3호
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• pp.70-76
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• 2007

The benefits for using reduced takeoff thrust are many, ranging from lower maintenance and operating costs to improved engine and dispatch reliabilities. Some pilots, however, are apprehensive about using reduced thrust. They are particularly reluctant to use the maximum permissible level of reduced thrust. Two common arguments are (1)If reduced thrust is used, then the airplane will not be able to clear the obstacles if an engine fails during takeoff, and (2)If the maximum allowable assumed temperature is used, then there will be no stopping margin left if the takeoff is aborted. There is the notion that using reduced thrust sacrifices safety. The intent of this discussion is to: (1)Show that reduced thrust performance meets all regulatory requirements (2)Show that the Assumed Temperature method includes inherent extra performance margins (3)Show how to maximize performance margins while maximizing thrust reduction.

• International Journal of Aeronautical and Space Sciences
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• 제6권2호
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• pp.17-22
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• 2005

As one of validation tool for attitude determination system, we have used various constraints using priori information which is known through base vector set up. However these conventional constraints cannot guarantee validity in terms of final solutions such as Euler angle. So we suggest attitude boundary concept to verify the final attitude solution on the flying airplane, it is based on the combination of velocity based attitude estimation technique and ambiguity resolution. we can say it can check invalid solution effectively at just one epoch without repeatability test of resolved cycle ambiguity. In this paper we show that the suggested constraint can effectively reject incorrectly resolved cycle ambiguity the conventional constraints have missed.

• EDISON SW 활용 경진대회 논문집
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• 제4회(2015년)
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• pp.274-278
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• 2015

There are different kinds of aircrafts, such as conventional airplane, rotorcraft, fighter, and unmanned aerial vehicle. Their shape and feature are dependent upon their assigned mission. One of the fundamental analyses during the design of the aircraft is the structural analysis. The structural analysis becomes more complicated and needs more computations because of the on-going complex aircrafts' structure. In order for efficiency in the structural analysis, a simplified approach, such as equivalent beam or plate model, is preferred. However, it is not clear which analysis will be appropriate to analyze the realistic configuration, i.e., an equivalent beam or plate analysis for an aircraft wing. It is necessary to assess the boundary between the one-dimensional beam analysis and the two-dimensional plate theory for an accurate structural analysis. Thus, in this paper, the static structural analysis results obtained by EDISON solvers were compared with the three-dimesional results obtained from MSC NASTRAN. Before that, EDISON program was verified by comparing the results with those from MSC NASTRAN program and analytic solution.

• 한국항공운항학회:학술대회논문집
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• 한국항공운항학회 2015년도 추계학술대회
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• pp.35-38
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• 2015

본 연구에서는 스포츠급 경항공기 모형의 공력 특성을 공군사관학교 아음속 풍동에서 측정하였다. 풍동시험은 유속 40m/s에서 이전 모델과 최근 공력성능 향상을 위해 보완된 모델에 대해 비교 실험 수행하였으며, 정확한 데이터를 얻기 위하여 흐름각 효과, 벽면효과, 지지대 간섭효과를 보정하여 공력계수를 산출하였다. 실험 결과, 두 모델의 항력계수와 양력계수가 전체적으로 유사한 경향성을 보이나 고받음각에서의 양력특성의 차이가 발생하였다. 또한 실제 비행 시의 레이놀즈 수 유동을 모사하기 위하여 Trip strip의 영향에 대하여 실험하였다. 그 결과 Trip strip을 부착하였을 경우 항력계수가 증가하고 최소항력받음각이 낮아지는 결과를 획득하였다.

• 한국통신학회논문지
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• 제10권2호
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• pp.93-103
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• 1985

대역폭 압축에 의한 디지털 신호처리 기술은 최근 몇 년동안 집적회로 기술의 발달에 따라 급성장해왔다. 본 연구에서는 화면의 중앙에 시야가 돋보이며 눈의 감각과 일치하는 Hadamard Matrix의 중앙에 Weight를 준 Nonorthogonal 변환인 Weighted Handamard Matrix를 구하여 실시간처리를 위한 고속계산방법과 Hardware system을 연구하였다. 따라서 본 연구는 항공사진, X-Ray, CATV, 인공위성통신 등 디지탈영상신호처리에 사용할 수 있을 것이다.

• 한국항공운항학회지
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• 제14권2호
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• pp.71-78
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• 2006

In this paper, it is described on the exportation trend and future development paradigm of the localized small aircraft which was recently developed four seated canard type aircraft for exportation purpose. Presently, even though the development of small aircraft is recessed, if we start development of the proper airplane models by integrating domestic power of industry-university-institute on the base of research experience from now on, we can go into the global market and take up the level of world top 10 makers without doubt. For successful operation of exportation system of small aircraft, it is needed to set up development strategy paradigm by forming consortium centering around the medium and small enterprises.

• 대한조선학회지
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• 제20권2호
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• pp.43-49
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• 1983

Stiffened plates, mostly used in the major part of ship and airplane structures, have been studied by various way-theoretical and experimental. In case of the fore and aft parts of the parallel middle body of ship structure, the stiffeners are not right-angled to the plate but acute angled. This paper presents the analysis of plates having included stiffeners by Finite Strip Method. The results of calculation show the influence of inclined angle which is less than $10^{\circ}$is ignorable. It is recommended that, when the inclined angle is over $20^{\circ}$, the section modulus of stiffener should be increased.

• 대한조선학회논문집
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• 제40권6호
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• pp.88-95
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• 2003

Liquid storage rectangular tank structures are used in many fields of airplane and marine engineering. Fatigue damages are sometimes observed in these tanks which seem to be caused by resonance. Therefore it is essentially important to estimate vibration characteristics of tank structures. Many Investigators studied the vibration of cylindrical and rectangular tank structures containing still fluid. In general, the eigenbehavior of interior liquid is characterized by the sloshing mode while that of the structure by the bulging mode. However, the structure deformation to the sloshing mode and the liquid free-surface fluctuation to the bulging mode have been neglected in the classical added-mass computation. in the present paper, we study the vibration characteristics with sloshing mode effect.