• 한국정보전자통신기술학회논문지
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• 제15권6호
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• pp.457-462
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• 2022

최근 드론을 엔터테인먼트 도구로 이용하는 문화생활이 다양하게 만들어지고 있고, 이를 실현하기 위해 비행 금지 구역을 침범할 정도로 성능이 좋은 드론을 이용하는 사용자가 많아지고 있다. 만족도가 높은 엔터테인먼트 활동을 위한 드론은 체공 시간도 길어야 하고 장거리 비행도 가능해야 하는데, 이것이 종종 비행 금지구역을 침범하거나 또는 원하지 않는 비행 충돌 문제가 발생하여 큰 피해가 날 수 있다. 본 연구에서는 이러한 문제를 해결하기 위하여 GCS(Ground Control System)로 비행 금지구역을 설정하고, 임계속도 10km/h 이하로 비행할 경우 비행 금지구역으로부터 10m 떨어진 임계거리 안으로 들어오지 않게 하여 안전하게 드론을 조종하게 하고, 임계속도 이상으로 비행해서 임계거리 안으로 진입할 경우 드론이 GCS 제어에 의해 self-drop 하도록 하여 비행 금지구역 안으로 들가지 못하도록 하는 방법을 제안하였다. 제안한 방법으로 특정 실험 지역에서 총 44번의 반복실험을 한 결과 한두번 제한구역을 넘어간 경우를 제외하고는 드론이 안전하게 self-drop한 결과를 얻었으며 제안한 방법으로 드론을 제어할 경우 비행 금지구역으로 넘어가는 것을 막을 수 있는 적절한 방법임을 확인할 수 있었다.

• 융복합기술연구소 논문집
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• 제10권1호
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• pp.1-5
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• 2020

The wake shapes behind wings in formation flight are very important to the aerodynamics and performances of aircrafts. In the present study, a discrete vortex methood is extended to handle the wake rollups behind multiple wings. It was found that the relative distance between the wings and the rotational direction of the wingtip vortices have significant effect on the movement of the wingtip vortices. When the wings are close to each other, the wingtip vortices moved faster than the wings of large relative distances. The vortex pair of opposite signs generated from each wingtip has an effect of moving the wingtip vortices upward. The relative height between the wings has an effect of moving the wingtips along the centerline of each vortex. The wakeshape behind multiple wings is a function of the relative distances and thus is dependent on the configuration of the formation flight. In the futhre, a study on the vortex movement pattern will be studied.

• 한국정보전자통신기술학회논문지
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• 제6권2호
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• pp.101-104
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• 2013

실제 항공기에 탑승하여 교육을 수행 할 수 있으나 초등 비행 시 숙련도가 떨어지는 조종사를 교육하기 위한 비용과 위험이 만만치 않다. 또한 상당한 기술을 필요로 하는 고등 비행 훈련 시 따르는 위험도 마찬가지이다. 이러한 것들을 모의 소프트웨어를 통해 훈련에 따르는 위험과 비용을 줄일 수 있으며 예상되는 위험 상황을 가상으로 하여 실제 상황처럼 전개해 볼 수 있는 장점이 있다. 본 논문은 실제 항공기의 비행 역학 특성 및 무장 탄도학이 고려된 게임 개발을 위한 소프트웨어 플랫폼 기반을 설계함으로써 조종사가 되고 싶은 학생들의 항공기에 대한 이해를 돕기 위함이다.

• 한국군사과학기술학회지
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• 제12권4호
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• pp.460-468
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• 2009

The purpose of this study is propose an alternative for flight attendants to acquire equipment that could enhance the ability to adapt in flying conditions. Introducing and acquiring weapon system, such equipments should be deeply considered in multilateral aspects; reinforcements in the overall strategic status in the army, the ramifications that can contribute to military resources, and economic situations in the country. To do this, we first induced several criteria that can be used for evaluating alternatives. After that, we applied the analytic hierarchy process(AHP) approach to putting all factors into considerations in decision making for equipment acquirement. The results of this study are expected to have usefulness in formulating strategies and policies in selecting equipment acquisition alternatives for flight attendants.

• Journal of Welding and Joining
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• 제28권2호
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• pp.74-78
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• 2010

In this paper, a non-contact method of evaluating the thickness reduction in an aluminum sheet caused by corrosion and friction using SH-EMAT (shear horizontal, electromagnetic acoustic transducer) is described. Since this method is based on the measurement of the time-of-flight and amplitude change of guided waves caused from the thickness reduction, it provides information on the thinning defects. Information was obtained on the changes of the various wave features, such as their time-of-flight and amplitude, and their correlations with the thickness reduction were investigated. The interesting features in the dispersive behavior of selected guided modes were used for the detection of thinning defects. The measurements of these features using SH waves were performed on aluminum specimens with regions thinned by 7.2% to 29.5% of the total thickness. It is shown that the time-of-flight measurement provides an estimation of the thickness reduction and length of the thinning defects.

• 한국군사과학기술학회지
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• 제8권1호
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• pp.39-48
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• 2005

After the development of the Firefly, flight tests have been performed to verify the performance and get the parameters for the mathematical model of the aircraft. The flight test data is used to get parameters for the mathematical model of the aircraft through the parameter identification process. An arbitrary control input is applied to the test flight which is a part of parameter identification process. A square wave has been used a control input which is called Doublet signal. The aspect of the signal is same length and magnitude in both (+) and (-) directions such as sine wave. The Doublet signal is composed of a dominant frequency and many high frequencies, so that it is appropriate signal to excite the motion of an aircraft. In this paper, the control input of the flight test data has been analyzed to check the efficiency of the control input using DFT(Discrete Fourier Transform). From the result of analysis, an alternative input was extracted.

• 한국군사과학기술학회지
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• 제19권5호
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• pp.638-644
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• 2016

In this research, theoretical study on empirical analysis method to estimate waterdrop's deformation by shock wave is presented. Flow field is calculated using theoretical and empirical relations. Waterdrop's deformation including movement, size, mass, and orientation is modeled using empirical relations derived from existing experimental data. Developed method is applied to specific flight examples with arbitrary flight speed and vehicle's configuration. The flight speed is assumed to Mach number of 2 and 4. The diameter of waterdrop is varied from 1 to 5 mm. Waterdrops along the stagnation line in front of hemispherical nose with the radius of 50 mm and around a cone-shaped side wall with the half angle of 20 degree are considered. It is found that the maximum diameter of the waterdrop is increased up to 2.77 times the initial diameter. The mass is conserved more than 66.7 %. In the case of a cone-shaped side wall, waterdrop's orientation angles defined from the flight direction when the Mach number is 2 and 4 are calculated as 33.0 and 25.6 degree, respectively.

• 항공우주기술
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• 제12권1호
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• pp.189-199
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• 2013

본 논문에서는 나로호 3차 비행시험에서의 2단 자세제어 결과를 정리하였다. 나로호 2단 추력기시스템에 의한 무추력 비행구간 3축 자세제어 및 추력벡터제어에 의한 킥모터 연소구간 피치/요 자세제어가 정상적으로 수행되었음을 보였다. 무게중심 오프셋, 킥모터 슬래그 영향, 킥모터 잔류추력 영향으로 인한 외란에도 불구하고 2단 자세제어기가 모든 비행구간에서 성공적으로 작동하였음을 보였다. 이러한 결과들은 국내의 발사체 자세제어 기술을 향상시키는 데 있어서 중요한 토대를 마련할 것이다.

• Journal of Astronomy and Space Sciences
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• 제30권4호
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• pp.291-298
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• 2013

The concept of the satellite formation flight is area where it is actively study with expandability and safety compare to existing satellite. For execution of duty with more safety issue, it needs to consider hot topic of space debris for operation of formation flight. In this paper, it suggests heuristic algorithm to have avoidance maneuver for space debris towards operating flight formation. Indeed it covers, using common software, operating simulation to nearest space environment and not only to have goal of avoidance but also minimizing the usage of fuel and finding optimization for maximizing cycle of formation flight. For improvement on convergence speed of existing heuristic algorithm, it substitute to hybrid heuristic algorithm, PSOGSA, and the result of simulation, it represents the satisfaction of minimum range for successful avoidance maneuver and compare to not using avoidance maneuver, it keeps more than three times of formation maintenance performance. From these, it is meaningful results of showing several success goals like simple avoidance collision and fuel usage and decreasing number of times of maintaining formation maneuver.

• 한국군사과학기술학회지
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• 제14권6호
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• pp.1009-1017
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• 2011

A Ballistic Missile(BM) is a missile that follows a sub-orbital ballistic flightpath with the objective of delivering one or more wardheads to a predetermined target and An Anti-Ballistic Missile(ABM) is a missile designed to destroy a ballistic missile before reaching its target. The main objective of this study is to assess the requirement of ABM by considering both flight characteristic of the SCUD-B/C, Nodong missiles and intercept performance of ABM in the Lower tier Ballistic Missile Defense(BMD). The Ballistic Missile's flight characteristics, such as trajectory, velocity etc., are estimated by simulation using the physical motion equations. The requirement of ABM is calculated by evaluating whether the BMD forces can defend those when the ballistic missiles attack prime facilities.