• 한국정보통신학회:학술대회논문집
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• 한국정보통신학회 2016년도 춘계학술대회
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• pp.407-408
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• 2016

드론은 최근 가까운 공원에서도 볼 수 있을 정도로 대중화가 되었다. 드론이란 조종사 없이 무선전파로 비행 조종이 가능한 무인 항공기(UVA)를 말하며, 주로 비행기나 헬리콥터 모양을 하고 있다. 드론은 군사용으로 시작 되었지만, 최근 방송촬영, 농약살포, 현장탐사, 취미용 등 민간으로 용도가 확대 되었다. 하지만 시중에서 많이 볼 수 있는 드론은 가격도 비싸고 고장이 났을 경우 수리하기가 어려우며, 비행시간이 짧은 불편함이 있다. 본 논문에서는 위에서 말한 불편한 점을 해결하고자 가격이 저렴한 ATmega128을 이용한 드론(쿼드콥터)를 구현했다. 6축 자이로, 가속도 센서와 MCU간의 TWI통신과, PID제어를 통한 드론의 자세제어를, 수신기의 신호를 입력받아 송신기로 드론을 제어하는 동작을 C프로그래밍언어를 기반으로 구현하였다.

• 한국항행학회논문지
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• 제23권2호
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• pp.114-124
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• 2019

2016년 1월 다보스포럼에서 발표된 4차 산업혁명에 대한 다양한 기술 적용 분야의 하나로서 무인비행장치인 드론 시장은 미래의 교통체계의 커다란 변화와 관련된 중요한 분야로 급속하게 확대 발전되고 있다. 한국의 경우 드론에 대한 관심은 국가자격증의 폭발적인 수요로 연계되고 있으며 드론조종자 수도 2015년 400여명에서 2018년 기준 17,000여명을 초과하면서 교육환경과 안전의 중요성이 강조되고 있다. 따라서 본 연구에서는 드론교육 현황과 함께 교육환경 평가를 위해 설계된 DREEM(Dundee ready educational environment measure) 모형에 근거하여 조종자의 안전의식을 분석하였다. 연구결과 교육 환경에 대한 만족도가 절차 준수를 포함한 전반적인 안전의식에 영향을 주므로 이에 대한 개선이 요구된다는 결론을 도출하였다.

• 예술인문사회 융합 멀티미디어 논문지
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• 제6권9호
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• pp.81-90
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• 2016

최근 드론은 하나의 취미 생활이 될 정도로 대중화가 되었다. 드론이란 조종사 없이 무선 전파로 비행·조종이 가능한 무인 항공기를 말하며, 주로 비행기나 헬리콥터 모양을 하고 있다. 드론은 군사용으로 시작 되었지만, 건설 현장, 농약 살포용, 현장 탐사, 화물 배송 그리고 수험생에게 답을 알려주는 부정행위를 방지하기 위한 드론 등 민간으로 용도가 크게 확대 되었다. 하지만 시중에서 볼 수 있는 드론은 굉장히 고가이고, 고장이 났을 경우 수리하기가 어려우며, 비행시간이 짧은 불편함이 있다. 본 논문에서는 위에서 말한 불편한 점을 해결하고자 보다 적은 비용으로 8비트 마이크로컨트롤러인 ATmega128을 이용한 드론를 구현했다. 6축 자이로, 가속도 센서와 MCU간의 TWI통신과, PID 제어를 통한 드론의 자세 제어를, 수신기의 신호를 입력받아 송신기로 드론을 제어하는 동작을 C프로그래밍언어를 기반으로 구현하였다. ATmega128을 이용한 드론은 호버링이 가능하고, 제어에 필요하지 않은 핀을 활용하여 다양한 용도의 드론으로 사용 할 수 있다.

• Journal of Biosystems Engineering
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• 제33권2호
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• pp.94-100
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• 2008

Present chemical application method using a power sprayer has been labor intensive, costly and ineffective. Therefore, a small agricultural unmanned helicopter was suggested to replace the conventional spray system. In this study, conceptual design for developing the helicopter and a consequential prototype were reported. The overall conceptual design was initiated by deciding the type of agricultural helicopter, as the single rotor helicopter with a tail system. As the first step of the designing, an air-cooled, 2-stroke engine was selected and a prototype transmission was designed by determining the rotating speed of main rotor shaft. A 'pusher' type tail rotor system was adapted to balance the reaction torque and reduce the power use. The tail boom length was designed to avoid the rotating trajectory of the main rotor. The RF console consisted of the engine control, attitude control, and emergency control modules. Assembling the prototype concluded the mechanical development of the agricultural helicopter.

• 한국항공운항학회지
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• 제20권4호
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• pp.50-56
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• 2012

Rotor system is a very important part which produce lift, thrust and control force in helicopter. Component of rotor system must have structural integrity for applied load. The estimation of structural integrity is regarded greatly as important in aerospace field. In this study, the process of structural analysis performed for bearingless main rotor system of helicopter. The composite flexbeam and torque tube of bearingless main rotor are very thick, so 3D layered soild elements of MSC.PATRAN were used to get the finite element analysis results. To estimate structural integrity, non-linear static analysis considering geometric non-linearity is performed. In addition, detailed finete element analysis and non-linear static analysis are performed to consider the stress concentration for fitting effect and contact surface. The estimation process of structural integrity for bearingless main rotor system of helicopter may help the design.

• Journal of Biosystems Engineering
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• 제35권1호
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• pp.31-36
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• 2010

A small unmanned helicopter was suggested to replace the conventional spray system. Aerial application using an agricultural helicopter helps precise and timely spraying, and reduces labor intensity and environmental pollution. In this research, a rotor system (SW05) was developed and its lift capability was evaluated. Lift force for the dead weight of the helicopter was obtained at the grip pitch angle of $12^{\circ}$. As the pitch angle increased to $14^{\circ}$ and $16^{\circ}$, the payload increased to 176 N and 216 N, respectively. Compared with SW04 airfoil performance in the total lift, the SW05 airfoil showed nearly the same capacity, but the payload of the SW05 was reduced because of the increased dead weight. A rated flight condition was defined as lifting mean payload of 294 N with the grip pitch angles of $16{\sim}17^{\circ}$ at the rotor rotating speed of 850~950 rpm for the adjusted engine power. The fuel consumption would be 4.8~6.0 L/hr, and the air temperature of cooling fan should be kept below $160^{\circ}C$.

• Journal of Biosystems Engineering
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• 제35권5호
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• pp.302-309
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• 2010

Aerial application using an unmanned agricultural helicopter would allow precise and timely spraying. The attitude of a helicopter depends on a number of dynamic variables for roll-balanced flight. Laterally tilting behavior of a helicopter is a physically intrinsic phenomenon while hovering and forwarding. In order to balance the fuselage, the rotor should be counter-tilted, resulting in the biased down-wash. The biased spraying toward right side causes uneven spray pattern. In this study, a raised tail rotor system for the roll-balanced helicopter was studied. Thrust of the tail rotor system was measured and theoretically estimated for the fundamental database of the roll-balanced helicopter design. The estimated tail thrust and roll-moment would be used to design the raising height of tail rotor and roll balancing dynamics. The unmanned agricultural helicopter required the tail rotor thrust of about 39.2 N (4.0 kgf) during hovering with a payload of 235.4 N (24 kgf). A raised tail rotor system would compensate for the physical tilt phenomena. A further attitude control system of helicopter would assist roll-balanced aerial spray application.

• Journal of Biosystems Engineering
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• 제33권5호
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• pp.289-295
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• 2008

The task of chemical spraying has been seriously considered as an irritating and annoying job for Korean rice farmers. An agricultural unmanned helicopter was suggested to solve this problem so as the farmers to have more decent farming condition. The objectives of this study were to analyze the adoptability of an experimental rotor blade (SW05) using the CFD simulation and also to compare the simulation results with experimental results. The simulation results showed that the induced power of this rotor reached to $57{\sim}63%$ of total power and the profile power was about $37{\sim}43%$ of total power. Therefore it can be concluded that this rotor's performance characteristics were not so efficient for the size of unmanned helicopter due to the low induced power and high profile power relatively compared with ones of conventional rotors. The comparison with experimental results showed that the tested lifts were less than 70% of simulated ones at the grip pitch of $12^{\circ}$ and decreased to 40% at the $18^{\circ}$ grip pitch. Therefore, it can be concluded that the rotor was too oversized to be used for a 15.4 kW (21 PS) engine.

• Journal of Biosystems Engineering
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• 제33권1호
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• pp.14-20
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• 2008

An agricultural unmanned helicopter was suggested for an alternative to current pesticide application methods to solve such problems as high cost, low efficiency, shirking task and unsafe work. To pursuit this trend, researches on the development of unmanned helicopters have been accelerated in Korea as well. In this research, a guide type centrifugal clutch that plays an important role in the unmanned helicopter was studied. Theoretical analyses and experimental tests were conducted for designing an optimal clutches. Main design factors of the guide type centrifugal clutch were found to be spring constant, free length of spring, mass of friction sector, contact area, allowable pressure, number of friction sector, friction coefficient, radius of drum, and clutch arrangement. And these design factors could be the functions of engaging engine speed and desired power transfer capacity. The result of the single clutch test showed the power transfer capacity of 14.1 PS at 5,800 rpm and the result of the dual clutch test showed that the capacity of 17.7 PS at 5,600 rpm. These experimental results agreed well the theoretical simulations.

• 한국항공우주학회지
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• 제39권12호
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• pp.1160-1165
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• 2011

본 연구는 무인항공기 및 헬리콥터 등에 장착되어 운용되는 고정밀 관측 다축 구동 EO/IR 카메라의 진동해석에 관한 것이며, 카메라에 적용된 볼 베어링을 모델링 하는데 있어서 3축 스프링요소를 적용하는 방법을 제시하였고, 이것에 의한 유한요소모델의 진동 응답 결과를 얻었다. 볼 베어링을 3축 스프링 요소로 모델링한 진동해석결과는 시험결과와 비교 되었으며, 잘 일치함을 알 수 있었다. 또한, 랜덤진동 시간이력해석을 통하여 다축 구동 EO/IR 카메라의 진동 응답 특성을 해석하고 분석하였다. 이의 연구결과는 우주용 카메라들에 사용되는 볼 베어링의 유한요소모델링 기법에 응용될 수 있다.