• Title, Summary, Keyword: Fixed wing

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Rotor Performance Optimization of the Canard Rotor Wing Aircraft (Canard Rotor Wing 항공기의 로터 성능 최적화 연구)

  • Jeon, Kwon-Su;Lee, Jae-Woo;Byun, Yung-Hwan;Yu, Yung H.
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.36 no.2
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    • pp.105-114
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    • 2008
  • In this study, the sizing and performance analysis program is developed for the canard rotor wing(CRW) aircraft which operates in dual modes (fixed wing mode and rotary wing mode). The developed program is verified for both fixed wing and rotary wing modes using the existing aircraft data and the design optimization formulation is made to perform the reconnaissance mission. For the canard rotor wing aircraft optimization , multi-objective function is constructed to consider both the fixed wing mode and rotary wing mode the weighting factor. For six design cases with different weighting factors and different design constraints, the optimization is performed and improved rotor design results are derived.

The study on safety measures and the trend of helicopter accidents (헬리콥터의 사고 추세와 안전대책에 관한 연구)

  • Kim, C.Y.;Choi, Y.C.
    • Journal of the Korean Society for Aviation and Aeronautics
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    • v.12 no.2
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    • pp.59-70
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    • 2004
  • Most of studies on aircraft accidents have been conducted mainly for fixed-wing aircraft, while the studies on helicopter accidents have been done less even though the helicopter accidents occurred quite more than those of the fixed-wing. There are lots of differences between helicopter and fixed-wing accidents, in aspect of causes and occurrence of accidents as well as aerodynamics and operation. In Korea, helicopter accidents have occurred 2 or 3 times annually since 2000, while the number of fixed-wing aircraft accidents has been reduced considerably. The goal of this study is to solve the present safety problems in helicopter accidents by reviewing the characteristics of past accidents and comparing differences between two types of aircraft.

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Design optimization of a fixed wing aircraft

  • Yayli, Ugur C.;Kimet, Cihan;Duru, Anday;Cetir, Ozgur;Torun, Ugur;Aydogan, Ahmet C.;Padmanaban, Sanjeevikumar;Ertas, Ahmet H.
    • Advances in aircraft and spacecraft science
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    • v.4 no.1
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    • pp.65-80
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    • 2017
  • Small aircrafts, Unmanned Aerial Vehicles (UAVs), are used especially for military purposes. Because landing fields are limited in rural and hilly places, take-off or landing distances are very important. In order to achieve a short landing or take-off distance many parameters have to be considered, for instance the design of aircrafts. Hence this paper represents a better design to enlarge the use of fixed wing aircrafts. The document is based on a live and simulated experiments. The various components of designed aircraft are enhanced to create short take-off distance, greater lift and airflow without the need for proper runway area. Therefore, created aerodynamics of the remotely piloted aircraft made it possible to use fixed wing aircrafts in rural areas.

Fixed-wing Aircraft Course Control in Significant Wind (강한 바람조건에서의 고정익 항공기 코스제어 기법)

  • Lee, Hongju
    • Journal of the Korea Institute of Military Science and Technology
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    • v.22 no.3
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    • pp.408-415
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    • 2019
  • Basically the dynamics of the fixed-wing aircraft is based on the airspeed which is relative to the wind, but when it comes to the track guidance and control, ground speed is the factor to be considered. Especially in the case of low-speed fixed-wing unmanned aerial vehicles the difference between the airspeed and the ground speed is significant depending on wind conditions, so that the heading control and the course control have to be designed separately. This paper represents the course control method using the pre-designed heading control gains which meet the desired characteristics. Also, waypoint guidance and control algorithms are suggested applying this control method. Finally the robustness of the proposed method is confirmed by 6-DoF nonlinear simulation.

Flying-wing Type Compound Drone Design and Mission Accuracy Analysis (전익기형 복합드론의 설계 및 임무 정확도 연구)

  • Sung, Dong-gyu;Koh, Eun-hak;Kim, Ju-chan;Nam, Yong-hyeon;Lee, Jeong-ho;Lee, Jae-seung;Lee, Chan-bin;Jeon, Yeong-bae;Choi, Cheol-kyun;Lee, Jae woo
    • Journal of the Korean Society for Aviation and Aeronautics
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    • v.26 no.4
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    • pp.122-128
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    • 2018
  • A compound drone that combines a fixed wing and a rotary wing is an aircraft that can take off and landing vertically, and can increase flight time and fly faster with fixed wings. The compound drones are divided into many types depending on the method of adding the thrust vectoring or the lift fan and the position of the rotor. In this study, we designed and fabricated a composite drone with four V-TOL motors in a fixed-wing, and assigned missions to the aviation body, hence judged mission accuracy using the actual flight test. The design process and the mission evaluation process employed in this study can be utilized on the development of various unmanned aerial vehicle.

Guidance Law for Vision-Based Automatic Landing of UAV

  • Min, Byoung-Mun;Tahk, Min-Jea;Shim, Hyun-Chul David;Bang, Hyo-Choong
    • International Journal of Aeronautical and Space Sciences
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    • v.8 no.1
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    • pp.46-53
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    • 2007
  • In this paper, a guidance law for vision-based automatic landing of unmanned aerial vehicles (UAVs) is proposed. Automatic landing is a challenging but crucial capability for UAVs to achieve a fully autonomous flight. In an autonomous landing maneuver of UAVs, the decision of where to landing and the generation of guidance command to achieve a successful landing are very significant problem. This paper is focused on the design of guidance law applicable to automatic landing problem of fixed-wing UAV and rotary-wing UAV, simultaneously. The proposed guidance law generates acceleration command as a control input which derived from a specified time-to-go ($t_go$) polynomial function. The coefficient of $t_go$-polynomial function are determined to satisfy some terminal constraints. Nonlinear simulation results using a fixed-wing and rotary-wing UAV models are presented.

Steady State Operational Characteristic Analysis of the Propulsion System for the Canard Rotor Wing UAV in three different Flight Modes (비행 모드에 따른 CRW UAV 추진시스템의 정상상태 운전특성 해석)

  • 공창덕;강명철;기자영;박종하;양수석;전용민
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.215-218
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    • 2003
  • In this study, a performance model of the Smart UAV propulsion system with ducts, tip jets and variable main nozzle, which has flight capability of the rotary wing mode for the take-off/landing and low speed forward flight as well as the fixed wing mode for high speed forward flight, has been newly developed. With the proposed model, steady-state performance analysis was performed at various flight modes and conditions, such as rotary wing mode, fixed wing mode, compound wing, mode altitude and flight speed.

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Accuracy Assessment of Parcel Boundary Surveying with a Fixed-wing UAV versus Rotary-wing UAV (고정익 UAV와 회전익 UAV에 의한 농경지 필지경계 측량의 정확도 평가)

  • Sung, Sang Min;Lee, Jae One
    • 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.

Availability Evaluation for Generation of Geospatial Information using Fixed Wing UAV (고정익 무인항공기를 이용한 공간정보 구축의 활용성 평가)

  • Park, Young Jin;Jung, Kap Yong
    • Journal of Korean Society for Geospatial Information Science
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    • v.22 no.4
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    • pp.159-164
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    • 2014
  • These days, inexpensive and high efficiency UAV of disaster prevention and spatial information has been given more attention. But studies about test of accuracy of UAV were not enough despite high interest. This research produced DSM and ortho photo and estimated accuracy by comparing coordinates with GNSS survey to evaluate outcome of fixed wing UAV. The ortho photo was found to make use of it to update 1/1,000 map. This research investigated spatial information construction using existing terrestrial LiDAR to suggest effectiveness of fixed wing UAV.

Electric power Small fixed wing UAV Aerodynamic performance Analysis (전기 동력 소형 고정익 무인항공기 공력성능 연구)

  • Jeong, Seongrok
    • Journal of Aerospace System Engineering
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    • v.13 no.1
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    • pp.11-17
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    • 2019
  • In this paper, the performance of a small fixed wing unmanned aerial vehicle is predicted theoretically with the minimum specifications and a low Reynolds number. Based on the results, it was compared with the results of an actual flight test and simple electric motor wind tunnel test. As a result of the validity of the analysis, a 3.5 kilograms class fixed wing small UAV can predict aerodynamic performance by general theory analysis. However, the required thrust was analyzed as a possible design error. Based on the results of this study, this paper proposed a method to minimize the design error when developing small fixed wing UAV flying in a low Reynolds number.