• Journal of Advanced Navigation Technology
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• v.28 no.1
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• pp.15-20
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• 2024

The utilization of small unmanned aerial vehicles (UAVs) has expanded into both military and civilian domains, increasing the necessity for research to ensure operational safety and the efficient utilization of airspace. In this study, the calculation of minimum separation distances for the safe operation of small UAVs at low altitudes was conducted. The determination of minimum separation distances requires a comprehensive analysis of the total system errors associated with small UAVs, necessitating sensitivity analysis to identify key factors contributing to flight technology errors. Flight data for small UAVs were acquired by integrating the control system of an actual small UAV with a flight simulation program. Based on this data, operational scenarios for small UAVs were established, and the minimum separation distances for each scenario were calculated. This research contributes to proposing methods for utilizing calculated minimum separation distances as crucial parameters for ensuring the safe operation of small unmanned aerial vehicles in real-world scenarios.

• Journal of KIISE
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• v.44 no.6
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• pp.559-565
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• 2017

A UAV(unmanned aerial vehicle) requires higher reliability for external effects such as electromagnetic interference because a UAV is operated by pre-designed programs that are not under human control. The design of a small UAV with a complete resistance against the external effects, however, is difficult because of its weight and size limitation. In this circumstance, a conventional small UAV dropped to the ground when an external effect caused the rebooting of the flight-control computer(FCC); therefore, this paper presents a novel algorithm for the improvement of the flight safety of a small UAV. The proposed algorithm consists of three steps. The first step comprises the calibration of the navigation equipment and validation of the calibrated data. The second step is the storage of the calibration data from the UAV take-off. The third step is the restoration of the calibration data when the UAV is in flight and FCC has been rebooted. The experiment results show that the flight-control system can be safely operated upon the rebooting of the FCC.

• 한국항공운항학회:학술대회논문집
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• 2016.05a
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• pp.228-232
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• 2016

유/무인기가 통합되어 운용되는 환경을 고려한 시뮬레이션 시스템 설계 방안을 제시하였다. 기존의 관제 공역 내의 유인기를 대상으로 하는 항공 교통 시뮬레이션 시스템의 기능과 무인기 시스템의 기본적인 기능을 고려하였으며, 이를 기반으로 유/무인기 복합 운용의 새로운 개념을 적용하여 모의할 수 있는 시뮬레이션 환경을 구성하였다. 모의 환경의 확장성을 고려하여, 무인기는 관제 공역에 진입하여 유인기와 복합 운용되는 무인항공기 시스템과 비관제 영역에서 운용되는 소형 무인비행장치로 구분하여 구성하였다. 시뮬레이션 시스템을 구현하기 위한 운용 개념에 대해 서술하였으며, 이를 기반으로 필요로 하는 주요 기능 요소들을 구성하고 각 요소에서 고려되어야 하는 주요 요구 사항을 제시하였다.

• Korea Information Processing Society Review
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• v.24 no.4
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• pp.31-40
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• 2017

• 한국항공운항학회:학술대회논문집
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• 2007.12a
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• pp.130-133
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• 2007

• Journal of Aerospace System Engineering
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• v.18 no.3
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• pp.76-85
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• 2024

Recently, from a global perspective, the use of small unmanned aerial vehicles in terrorism and warfare is increasing, and the need for anti-drone shooting training targeting small UAVs is increasing. However, in reality, there are many cases in Korea where anti-drone shooting training is restricted, due to complaints such as noise. In this paper, we describe the development and testing of an electric-powered direct strike type high-speed, low-noise small aerial target drone. To achieve the flight speed and endurance required for shooting training, target drone sizing was performed, and aerodynamic performance analysis was conducted using a CFD program. Based on the performance analysis, the motor propulsion system was selected and a variable pitch propeller system was designed, and performance tests were performed on a ground test rig. Finally, the target flight speed, flight time, and flight noise level were confirmed through flight tests.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.251-256
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• 2008

The experimental analysis on a ducted fan for the propulsion system of a small UAV were performed. To investigate the aerodynamic characteristics of the ducted fan, flow fields at inlet and outlet were measured using a hot-wire anemometry. Thrusts were measured with the six-component balance with due regard to the cross wind. To reproduce the cross wind effect, the ducted fan was aligned to $90^{\circ}$ rotated direction against flow direction in the wind tunnel. In this paper, the variation of the flow fields and thrust according to the cross wind were analyzed.

• Proceedings of the Korean Society of Disaster Information Conference
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• 2015.11a
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• pp.232-234
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• 2015

본 연구에서는 무인기(UAV)를 활용하여 재난현장을 분석하고 uGIS기법에 의한 처리방안에 대하여 제시한다. 무인기는 군사적인 용도로 개발되면서부터 급속한 민간의 활용으로 확산되면서 소형에서 대형까지 매우 다양한 시스템으로 수 많은 분야에 적용되고 있다. 특히 무인기는 재난재해의 현장에 어떠한 수단보다도 원활하고 신속 정확한 분석과 모니터링을 동시에 수행할 수 있으며, 그 과정을 uGIS기법에 의한 실시간 현장영상의 제공과 현장의 변화관리를 지속가능하게 공중을 나르는 로봇형 공간정보의 한 기술로서 자료의 전송, 보존 및 관리와 운영을 할 수 있다는 새로운 uIT분야의 하일라이트로서 크게 부각되어, 향후에도 무한한 영향력을 발휘할 수 있는 잠재력을 견지할 수 있는 수단으로 기여될 것이다.

• 한국항공운항학회:학술대회논문집
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• 2015.11a
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• pp.50-54
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• 2015

구형무인비행체는 다중 모터를 이용한 무인항공기에 비행 소형화, 경량화, 경제화 등의 장점을 가지고 있다. 본 논문에서는 구형무인비행체의 경로 추종을 위한 제어기 설계 및 성능에 대한 내용을 다루고 있다. 먼저 구형무인비행체의 운동방정식이 제어기 설계를 위해 유도되었고, 유도된 운동방정식을 이용해 경로 추종 제어기를 설계하였다. 구형무인비행체의 자세제어는 무게중심을 변화하는 방법을 사용하였다. 요구 경로를 설정하여 설계된 제어기의 경로 추종 성능을 MATLAB 시뮬레이션을 통해 확인하였다. 시뮬레이션 결과, 제시된 제어기가 설정된 경로를 추종하고 있음을 확인하였다.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.28 no.10
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• pp.779-787
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• 2017

In this paper, we designed a RF transceiver for small unmanned aerial vehicle(UAV) using power switching method. To apply for the UAV, several characteristics such as size, weight, and power consumption are very important. To reduce power consumption, we propose a new power switching method. Using the proposed method, we fabricated the RF transceiver needed to establish the data link for a small UAV. The fabricated RF transceiver shows an output power of +25 dBm, a noise figure of 4.56 dB and a received signal strength of -100 dBm. By performing power measurement of proposed switching method, 25 % of power could be reduced. The size of the fabricated RF transceiver is $100{\times}60{\times}5.7mm^3$ and the weight is as small as 38 g.