• Proceedings of the KIEE Conference
• /
• 2005.07d
• /
• pp.2849-2851
• /
• 2005

본 논문에서는 소형 카오스 무인 비행체에서의 장애물 회피 기법과 목표물 탐지 기법을 제안하였다. 장애물은 불안정한 VDP(van der Pol) 방정식을 이용하였으며 목표물은 안정한 VDP 방정식을 이용하였다. UAV가 장애물과 목표물에 접근하게 되면 불안정 또는 안정한 VDP 방정식이 UAV를 밀어내거나 끌어들임으로서 장애물을 피해가거나 목표물 탐색할 수 있는 알고리즘을 제시하고 컴퓨터 시뮬레이션으로 그 결과를 검증하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.40 no.5
• /
• pp.413-422
• /
• 2012

The ducted fan for a small UAV propulsion can reconnoiter and observe in a town and a small area, it has better thrust efficiency and a long endurance than propeller. Thrust characteristics of hover and for ward flight condition for the ducted fan UAV is important issue to improve a endurance. The unsteady 3-dimensional flow fields of the ducted fan UAV is essential to stable flight. In this paper, to verify the design results of the ducted fan and to investigate a stable aeronautical characteristic, the thrust performance and the unsteady 3-dimensional flow fields are measured. Thrust characteristics for the hovering and the forward flight conditions are measured by the 6-components balance system in the subsonic wind tunnel. The unsteady 3-dimensional flow fields are analyzed by using a stationary $45^{\circ}$ slanted hot-wire technique. The swirl velocity is almost removed behind the stator blades. Therefore, the thrust performance of the ducted fan is improved and the flight stability is maintained.

• Journal of Advanced Marine Engineering and Technology
• /
• v.40 no.7
• /
• pp.622-628
• /
• 2016

The prosperity of IT technologies and the removal of restrictions regarding Unmanned Aerial Vehicles (UAVs), also known as drones, have driven growth in their popularity. However, without a proper solution to the problem of accident avoidance for UAVs, this popularity increases the potential for collisions between UAVs and between UAV and terrain features. These collisions can occur because UAVs to date have flown using radio control or image recognition based autonomous navigation. Therefore, we propose efficient UAV routing schemes to tackle the collision problem using vehicular communication systems. Performance evaluation by computer simulation shows that the proposed methods effectively reduce the collision probability and improve the routing efficiency of the UAV. Furthermore, the proposed algorithms are compatible and can be directly applied with small overhead to the commercial vehicular communication system implementation.

• Proceedings of the Korean Society of Computer Information Conference
• /
• 2012.07a
• /
• pp.63-64
• /
• 2012

본 논문에서는 소형 무인 비행체 (Unmanned Aerial Vehicle, UAV)를 스마트폰을 이용하여 제어하기 위한 방법을 제안하고. UAV에 Wi-Fi 통신 모듈 설계 및 개발 과정을 설명한다. 스마트폰과 UAV는 Wi-Fi를 통해 통신하며, 이것의 instruction set은 MCU에서 C언어로 다운로드 된 로직으로 수행하게 된다. 데이터의 송수신은 Serial 포트를 이용하여 흐름을 제어하며 확인할 수 있다. 또한 관련 모듈들을 통합하기 위해 PCB(Printed Circuit Board)과정을 진행, 소형화하여 개발하였다.

• Proceedings of the Korea Water Resources Association Conference
• /
• 2016.05a
• /
• pp.449-453
• /
• 2016

하천 구역에 존재하는 인력 및 장비의 접근이 물리적으로 불가능한 공간에 대한 지형정보 취득의 한계를 극복하기 위한 대안으로 소형 UAV(Unmanned Aerial Vehicle)의 활용성을 살펴보고자, 낙동강 달성보와 강정고령보 사이에 위치하는 습지구간에 대한 영상촬영 및 분석을 통한 지형측량을 실시하였다. 홍수터 지형측량에 있어 소형 UAV를 이용한 사진측량의 신뢰성과 정확성을 평가하기 위하여, Network RTK를 이용한 육상측량결과와 정사영상 분석결과를 비교하여 '항공레이저측량 작업규정'의 '수치표고모델 규격 및 정확도'에 제시된 기준에 의거하여 수직위치 정확도를 검토하였다. 검토 결과 과대오차를 배제할 경우 지표면 상태에 따라 1/1,000~1/5,000의 정사영상 및 수치표고모델 제작이 가능함을 확인할 수 있었다.

• 제어로봇시스템학회:학술대회논문집
• /
• 2002.10a
• /
• pp.47.4-47
• /
• 2002

$\textbullet$ Introduction of UAV Helicopter $\textbullet$ System Specification $\textbullet$ Dynamics of Small EP Helicopter $\textbullet$ Construction of Electrical System $\textbullet$ LQG Control Law $\textbullet$ Simulations $\textbullet$ Results and Analysis

• Aerospace Engineering and Technology
• /
• v.4 no.1
• /
• pp.260-267
• /
• 2005

An electronic spark ignition unit has been developed for gasoline for small UAV. The unit is programmable to adjust the optimal ignition advance angle in accordance with rpm and intake pressure. Initial advance angle and the position of Hall sensor on the engine can be set from PC via serial interface. The results are expected to be valuable core technology of powerplants in developing small UAV's.

• 제어로봇시스템학회:학술대회논문집
• /
• 2005.06a
• /
• pp.1005-1007
• /
• 2005

A Nonlinear approach to control of Small Scale Rotary Wing Unmanned Aerial Vehicle (R-UAV) is presented. Using Backstepping, a globally stabilizing control law is derived. We derive backstepping control law for angle of attack and sideslip control. The inherent nonlinear nature of the system are considered here which helps in naturally stabilizing without extensive external effort. Thus, the resulting control law is much simpler than if the feedback linearization had been used.

• International Journal of Aeronautical and Space Sciences
• /
• v.18 no.3
• /
• pp.588-600
• /
• 2017

We develop a wireless, contact free power transfer mechanism that is safer than the direct metallic contact and robust to imperfect alignment on landing at the base station. A magnetic field is created using inductors on both the transmitting and receiving sides. We use the inductive wireless recharging to increase autonomy and decrease the sensor interference by reducing the inductor loop size. By locating four independent small receiver loops and corresponding four circuits around the quadrotor UAV, we can increase safety from circuit malfunctions in comparison to the use of just one loop. On the base station, four folding robotic bars are used to realign the receiver loops over the transmitter loops. After adequate recharging as measured by battery voltages or power consumption at the bae station, the UAV sends a signal to the base station to open the robotic bars and takes off once freed from the robotic bars.

• Journal of the Korea Institute of Military Science and Technology
• /
• v.21 no.6
• /
• pp.790-798
• /
• 2018

Discrete noise signals from a small scale tactical unmanned aerial vehicle(UAV) propeller were predicted numerically using time domain approach. Two-bladed 29 inch propeller in diameter and 150 kgf in gross weight were used for main parameters of the UAV based on the actual size of the similar scale vehicle. Panel method and Farassat formula A1 were adopted for aerodynamic and aeroacoustic analysis respectively. Time domain signals of both thickness and loading noises were transformed into frequency domain to analyze the discrete noise characteristics. Directivity pattern in a plane perpendicular to the rotating disc plane and attenuation of noise intensity according to double distance were also presented.