• Asia-pacific Journal of Multimedia Services Convergent with Art, Humanities, and Sociology
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• v.6 no.8
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• pp.577-584
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• 2016

UAV(Unmaned Aerial Vehicle), which is autonomous flight without pilots. Recently, UAV is being applied to various fields such as video recording, aerial photogrammetry. In particular, UAV is getting a lot of attention in the field of space-related information because of it's data acquisition speed and economic feasibility. But analytical study of an unmanned air-side technologies are lacking. In this study, the research of equipment for the unmanned aerial surveys and UAV technologies and trend analysis for generation of terrain model and ortho image effectively were performed. As a result, the ways to improve the utilization field of unmanned aerial surveying and processing of fixed-wing and rotary-wing unmanned aircraft. were suggested. If analytical research on generation of terrain models and ortho image will be performed, production efficiency of the geospatial information industry is expected to be significantly increased.

• Current Industrial and Technological Trends in Aerospace
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• v.4 no.1
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• pp.55-60
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• 2006

헬리콥터와 같은 전통적인 수직이착륙항공기는 이착륙시 활주로가 필요로 하지 않는 장점이 있으나 고 속비행 및 고고도 성능에 있어서는 고정익기에 뒤떨어진다. 고효율의 엔진개발에 따라 고정익 항공기가 최 대속도 및 성능이 비약적으로 발전한대 비해, 헬리콥터의 최대속도는 160 ~170 kts (300~315 km/h) 수 준으로 제한되어왔고 장거리 운항에서 필수적인 고고도 운항능력에 있어서도 4km 이상의 고도에서 효율 적인 비행을 수행하는 데에는 한계가 있다. 이를 극복하기 위해 지난 반세기 동안 다양한 신개념 비행체 연 구가 수행되었다. 스마트무인기기술개발사업단에서는 항공선진국의 이러한 연구개발동향 및 그 결과를 종 합하여 미래적 신개념 비행체 대안을 모색하였고, 그 결과 틸트로터 개념을 선정하여 상세설계를 종료한 상태이다. 이러한 경과에 대한 요약과 현재 활발히 진행중인 항공선진국의 미래형 수직이착륙 항공기 개발 기종의 현황, 성능비교를 통해 고속, 고고도 수직이착륙 항공기 개발에 관한 세계적 추세와 본 사업의 연관 성을 고찰해 보았다.

• Journal of Aerospace System Engineering
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• v.14 no.spc
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• pp.39-48
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• 2020

This paper deals with the process of estimating the environmental noise generated from the actual flying aircraft using the noise measurement results obtained through the wind tunnel test and verifying it through flight tests. In order to evaluate the environmental noise of an aircraft, noise tests and evaluations are generally conducted according to the procedures prescribed by the International Civil Aviation Organization (ICAO). In this paper, we introduced environmental noise evaluation method that can be applied to composite both fixed-wing aircraft and multi-copter, and introduced the evaluation method by experiment. This paper introduces the process of simulating the noise test results measured in the wind tunnel test using real flight test results. In addition, in consideration of flight operating conditions and noise measurement methods proposed by the ICAO, the effective perceived noise level (EPNL) was predicted by performing both the wind tunnel test and the aircraft flight test.

• 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.

• KSCE Journal of Civil and Environmental Engineering Research
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• v.33 no.6
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• pp.2593-2600
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• 2013

The main purpose of this study is to carry out the performance evaluation of Ultra-light Fixed Wing UAV(Unmanned Aerial Vehicle) photogrammetry which is being, currently, applied for various fields such as cultural assets, accident survey, military reconnaissance work, and disaster management at home and abroad. Firstly, RMSE estimation of Aerial Triangulation (AT) are within approximately 0.10 cm in position (X, Y). And through the comparison of parcel's boundary points coordinates by terrestrial surveying and by UAV photogrammetry, the analysis shows that RMSE are shifted approximately 0.174~0.205 m in X-direction, 0.294~0.298 m in Y-direction respectively. Lastly, parcel's area by orthophoto of UAV photogrammetry and by that of cadastre register has been shown the difference by 0.118 m2. The results presented in this study is just one case study of orthophoto accuracy assessment of Ultra-light fixed wing UAV photogrammetry, hereafter various researches such as AT, direct-georeferencing, flight planning, practical applications, etc. should be necessary continuously.

• Journal of the Korean Society of Surveying, Geodesy, Photogrammetry and Cartography
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• v.35 no.6
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• pp.535-544
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• 2017

UAVs (Unmanned Aerial Vehicle) are generally classified into fixed-wing and rotary-wing type, and both have very different flight characteristics each other during photographing. These can greatly effect on the quality of images and their productions. In this paper, the change of the camera rotation angle at the moment of photographing was compared and analyzed by calculating orientation angles of each image taken by both types of payload. Study materials were acquired at an altitude of 130m and 260m with fixed-wing, and at an altitude of 130m with rotary-wing UAV over an agricultural land. In addition, an accuracy comparison of boundary surveying methods between UAV photogrammetry and terrestrial cadastral surveying was conducted in two parcels of the study area. The study results are summarized as follows. The differences at rotation angles of images acquired with between two types of UAVs at the same flight height of 130m were significantly very large. On the other hand, the distance errors of parcel boundary surveying were not significant between them, but almost the same, about within ${\pm}0.075m$ in RMSE (Root Mean Square Error). The accuracy of boundary surveying with a fixed-wing UAV at 260m altitude was quite variable, $0.099{\sim}0.136m$ in RMSE. In addition, the error of area extracted from UAV-orthoimages was less than 0.2% compared with the results of the cadastral survey in the same two parcels used for the boundary surveying, In conclusion, UAV photogrammetry can be highly utilized in the field of cadastral surveying.

• Proceedings of the Korea Water Resources Association Conference
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• 2016.05a
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• pp.249-249
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• 2016

무인항공기(UAV)는 군사적 목적으로 개발되었지만, 최근 다양한 분야에서 활용되고 있다. 수자원 관리를 위해서도 시대적 흐름에 따라 드론과 관련된 많은 연구가 진행되고 있다. 이수임 등(2015)은 UAV영상을 활용한 수변구조물의 DSM 생성 및 정확도 연구를 통해 지상 LIDAR와 같은 수준의 DSM 및 더욱 정확한 GCP 취득의 필요성을 제시했다. 이용창(2015)은 회전익 UAS 영상기반 고밀도 측점자료의 위치 정확도를 평가하였다. 이인수 등(2013)은 초경량 고정익무인항공기 사진측량기법의 정사영상 정확도 평가를 수행하였다. 또한 김민규 등(2010)은 풍수해 모니터링을 위한 UAV 적용성 분석을 실시하였고, 김홍래 등(2014)은 UAV를 활용한 감시정보정찰 임무분석 및 설계도구 개발을 위한 연구를 수행하였다. 상기와 같이 수자원 분야 활용을 위한 많은 연구가 보고 되고 있으나, 아직까지 드론 활용의 대부분은 항공영상 취득 및 분석기술 개발에 집중되어 있다. 본 연구에서는 무인항공기를 수재해 감시 및 관리 기술에 적용하기 위해 수행되었다. 수재해 감시 및 관리를 위한 방법으로 NIR(Near Infrared) 센서를 부착한 '재해관리용 드론'을 개발하고 현장실험을 수행하였다. 실험결과 NIR센서를 탑재한 드론은 수재해 관리에 매우 유용하게 활용될 수 있을 것으로 판단되었다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.1
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• pp.31-39
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• 2013

A Quad Tilt Wing UAV is a new concept hybrid UAV having the advantages of both fixed-wing and rotary-wing aircraft. This paper presents longitudinal flight dynamic characteristics of a Quad Tilt Wing UAV. The designed Quad Tilt Wing UAV is a configuration of a tandem wing type aircraft with an actuating motor and propeller mounted at each wing. Momentum theory is used to calculate the thrust, and nonlinear modeling is performed considering lift and drag generated by slip stream effect of propellers. Also, Force and moment variation at each tilting angle is considered. Static trim on longitudinal axis is analyzed via numerical simulation. Componentwise force contribution was analyzed at each trim mode. Dynamic characteristics were evaluated through eigenvalue analysis for a linear model at each flight mode. It is verified that longitudinal dynamic characteristics are changing from unstable to stable state by continuous transition of dominant poles.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.12
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• pp.1097-1107
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• 2015

General VTOL aircraft uses gas turbine engine which has high power to weight ratio. However, in the VTOL UAV in small sector, the gas turbine as a prime mover is not adequate because of the limitation of the high fuel consumption ratio of the gas turbine. In this research, The Series Hybrid-Electric Propulsion System(SHEPS) has been proposed and technology survey & comparison analysis has conducted to constitute propulsion system for engine, electric motor and battery. To achieve this object a 65kg-class P-UAV from "Company I" was used. And to estimate the validity of power control algorithm and developed power management control, Matlab/simulink$^{(R)}$ has been used for the simulation. As a result, the developed algorithm worked comparatively well and the research has predicted that SHEPS was satisfied enough for 7 hour of endurance for mission profile.

• Journal of Advanced Navigation Technology
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• v.16 no.6
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• pp.910-919
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• 2012

In this paper, we described development of on-board image processing system and its process and verified its performance through flight experiment. The image processing board has single ARM(Advanced Risk Machine) processor. We performed Embedded Linux Porting. Algorithm to be applied for object tracking is color-based image processing algorithm, it can be designed to track the object that has specific color on ground in real-time. To verify performance of the on-board image processing system, we performed flight test using the PNUAV, UAV developed by LAB. Also, we performed optimization of the image processing algorithm and kernel to improve real-time performance. Finally we confirmed that proposed system can track the blue-color object within four pixels error range consistently in the experiment.