• Proceedings of the Korean Society of Disaster Information Conference
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• 2022.10a
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• pp.373-374
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• 2022

본 연구는 민간 시큐리티 분야의 드론 도입 시 교육과목 중 드론의 기능을 적용할 수 있는 과목을 기준으로 절차 및 내용에 관하여 연구를 실시하였다. 연구 결과 경계감시, 순찰, 경보, 촬영 및 영상기록, 장비점검, 장비 운송, 사격등의 과목에 드론운영에 대한 교육 내용을 포함시켜야 할 것이다. 이처럼 드론 시큐리티 분야를 민간 시큐리티 산업에 적용하기 위해서는 드론의 기능과 더불어 각 업무분야에 고유한 특성을 반영하여 과목을 구성하여야 할 필요가 있다. 또한 현재의 기술로는 드론에 부착되는 장비에 따라 사용 용도가 다를 수 밖에 없으며, 비행시기와 장소에 따라 실내비행이나 야간비행이 필요한 추가적인 조종교육 및 운용교육이 요구된다고 할 것이다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.8
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• pp.673-679
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• 2013

Photogrammetric techniques were used to analyze separation characteristics of store in safe separation flight test. In this analysis, we used single camera method to analyze 6 degrees of freedom of separated store. We established instrumentation requirements based on theoretical background of photogrammetry and guidelines of MIL-HDBK-1763. We applied the photogrammetry to flight test and extracted separation trajectory. We empirically estimated the input variables uncertainties of photogrammetry and its effects on separation trajectory. Using this trajectory which includes the photogrammetric error, we analyzed the safety of separation.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.93-96
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• 2009

Advances in high speed flight technologies and engine efficiencies increase heat load on the aircraft. As the temperature of air flow is too high to cool the structure at hypersonic flight speeds, it is necessary to utilize the aircraft fuel as the primary coolant. By undergoing endothermic reaction, such as thermal decomposition or catalytic decomposition, aircraft fuels have heat sink potential. These fuels are called endothermic fuels. The endothermic reaction can be improved by catalysts, but limited by coke deposition. In this study the essential technologies of endothermic fuels are described, and intended to be used for basic research.

• Aerospace Engineering and Technology
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• v.3 no.2
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• pp.197-207
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• 2004

The developing Smart UAV in KARI supposes high speed flight as like a conventional plane, as well as vertical takeoff and landing as like a helicopter. Therefore, the air intake system should be designed to provide the sufficient air flow to the engine and the maximum possible total pressure recovery at the engine intake screen over a wide range of flight conditions. For this purpose, we designed the intake system using a pitor type intake model and plenum chamber. In this paper, we designed the intake model and analyzed the performance of designed intake system using the general-purpose commercial CFD code, CFD-ACE+. The analysis results of the total pressure variation and the velocity distribution were illustrated in this paper. The pressure recovery and distortion coefficient at a plane coincident with the compressor inlet were calculated and streamline variation through the intake system was investigated at the worst flight condition as well as the standard flight condition.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.6
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• pp.63-69
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• 2011

The Smart UAV must have the control characteristics of propulsion system necessary for both rotary aircraft and fixed wing aircraft though it equips turbo-shaft engine. To develop an electronic engine controller in the future, it is necessary to accumulate the experience of engine operation and data of tilt rotor aircraft. For this purpose, the computer programs which predict engine performance in the steady state and transient state can be utilized for the supplementation of flight test data. In this work, we developed a dynamic analysis program using engine performance data gathered during the flight tests. In addition the accuracy of the program was verified through comparison with flight test data and the results of steady-state performance analysis program.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.23 no.4
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• pp.57-65
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• 2015

In this study, MBTI(Myers-Briggs Type Indicator) test was carried out targeting flight instructors and student pilots in charge of introductory flight training course. The results was analyzed in accordance with the personality type, the preferred indicator, and the combination of preferred indicators in order to see how these characteristics affect the flight training results. Most of personality types of the instructor, regardless of the attitude category such as E or I, were -STJ(70.6%), however the student pilot showed a variety of personality types, rather than professors. Sensing-type(S) students showed higher academic achievement scores than Intuition-type(N), and Judging-type(J) students showed higher academic achievement scores and pilot qualification scores than Perceiving-type(P). The success rate of Extraversion-type(E) student pilots was higher than that of Introversion-type(I) student pilots. As the personality combinations of instructor and student pilot, the academic achievement scores of Judging-Judging(J-J) type were higher than those of Perceiving-Perceiving(P-P) type. The combination of Extraversion-Extraversion(E-E) type showed higher success rate than Extraversion-Introversion(E-I). This result suggests that if both instructor and student pilot have same attitude of Extroversion(E), good training results can be expected.

• Journal of the Korean Society of Propulsion Engineers
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• v.4 no.3
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• pp.74-82
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• 2000

The concept and characteristics of the propulsion systems for the next generation flight vehicles are described in this paper, where Hey are grouped into air breathing engine, rocket engine and combined cycle engine according to the feeding system of oxidizer. Air breathing engine has its good reusability and superior performance at low altitude, but its usage is limited at high altitude due to the decreased air density. Rocket engine can be used over the wide range of altitude, but it has disadvantages in low specific impulse and high cost. The several types of combined cycle engine, which are being developed by the leading countries in the aerospace, are highlighted as a remarkable candidate for the next generation propulsion system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.647-650
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• 2017

As the necessity of development of supersonic vehicle increases, securing an aerodynamic data from low to high altitude is requested for flying vehicles crusing in various high-tech environment. Therefore our research team built equipment by improving heating device of Model Aerodynamic Facility(MAF) of Konkuk University to simualte a real gas environment. Guided weapon system and temperature and velocity distribution according to the flow that is produced from the pier of supersonic vehicle is planned to be researched by using this equipment.

• Journal of the Korean Vacuum Society
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• v.17 no.6
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• pp.501-510
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• 2008

The stealth technology to conceal an aircraft from the vision of a radar have been accomplished by coating the surface with special paints absorbing the electromagnetic wave. Nowadays, researches to utilize characteristics of the plasma-wave interaction for realizing the stealth technology are actively progressed. In this paper, to investigate the physical feasibility of the plasma stealth, calculation results for the required conditions of the plasma cloaking on the aircraft flying in the air for showing the stealth function, using a flat non-magnetized non-uniform plasma model, are reported and discussed.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.5
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• pp.437-446
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• 2017

An integrated flight simulation program for multicopter drones is presented. The program includes rigid body dynamics, propeller thrust, battery energy, control, and air. Using this program, users can monitor and analyze the states of drones along flight trajectories. As a programming language, Modelica has been chosen, that specializes in simulation program development. Modelica enables users to develop simulation programs efficiently due to acausal and object oriented properties. For missions including horizontal and vertical maneuvers, many dynamical states of drones have been analyzed with simulation results.