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실내감시정찰용 동축반전 헬리콥터형 미세비행체 설계 및 제작
변영섭(Youngseop Byun),신동환(Donghwan Shin),안진웅(Jinung An),송우진(Woojin Song),김정(Jeong Kim),강범수(Beomsoo Kang) Korean Society for Precision Engineering 2011 한국정밀공학회지 Vol.28 No.12
This paper is focused on the procedure of the development of a micro air vehicle which has vertical take-off and landing capability for indoor reconnaissance mission. Trade studies on mission feasibility led to the proposal of a coaxial rotorcraft configuration as the platform. The survey to provide a guide for preliminary design were conducted based on commercial off-theshelf platform, and the rotor performance was estimated by the simple momentum theory. To determine the initial size of the micro air vehicle, the modified conventional fuel balance method was applied to adopt for electric powered vehicle, and the sizing problem was optimized with the sequential quadratic programming method using MATLAB. The designed rotor blades were fabricated with high strength carbon composite material and integrated with the platform. The developed coaxial rotorcraft micro air vehicle shows stable handling quality with manual flight test in indoor situation.
무인 헬리콥터용 길이가변 로터 블레이드 개발을 위한 선행연구
천주홍(Juhong Chun),변영섭(Youngseop Byun),이병언(Byoungeon Lee),송우진(Woojin Song),김정(Jeong Kim),강범수(Beomsoo Kang) Korean Society for Precision Engineering 2010 한국정밀공학회지 Vol.27 No.3
A preliminary study on a length-variable rotor blade for a small unmanned helicopter has been conducted. After surveys on previous researches, and examining requirements for application to a small unmanned helicopter, a length-variable rotor blade was designed and manufactured to be driven by centrifugal force from rotor revolution with no mechanical actuator. The rotor blade was divided into a fixed inboard section and an outboard section sliding in span-wise direction. In order to determine the operating conditions of the length-variable rotor during revolution, and to derive the design variables of extension spring and rotor weight, a series of analyses from multibody dynamics solution were conducted. The manufactured prototype was verified of its lengthvarying mechanism from a rotor stand, the results and required future improvements are discussed.
Study on Performance Prediction of Electric Propulsion System for Multirotor UAVs
정진석(Jinseok Jeong),변영섭(Youngseop Byun),송우진(Woojin Song),강범수(Beomsoo Kang) Korean Society for Precision Engineering 2016 한국정밀공학회지 Vol.33 No.6
This paper describes a study of performance prediction of an electric propulsion system for multirotor UAVs. The electric propulsion system consists of motors, propellers, batteries and speed controllers, and significantly affects performance characteristics of the platform. The performance of the electric propulsion system for multirotor UAVs was predicted using an analytical model derived from the characteristics of each component, operation experiments and statistical analyses. Ground performance tests and endurance flights were performed to verify the reliability of the proposed performance prediction method. A quadrotor platform was designed to demonstrate the parcel delivery service used in the endurance flight. From the result of verification tests, it was confirmed that the proposed method has a good agreement.
Study on Analysis of Vibration Characteristics and Modal Test for a Quad-Rotor Drone
김민송(Minsong Kim),김재남(Jaenam Kim),변영섭(Youngseop Byun),김정(Jeong Kim),강범수(Beomsoo Kang) Korean Society for Precision Engineering 2016 한국정밀공학회지 Vol.33 No.9
This paper describes analysis results of vibration characteristics and modal test for a small-scale quad-rotor drone. The rotor arm has a slender body with a propeller and motor at its tip. Rotor system generates excitation for an unbalanced mass. Therefore, the drone platform is involved in the possibility of resonance. For advance identification of the possibility of resonance, confirmation of eigen-mode being closest to the propeller operation range is necessary. Material properties of CFRP tubes used for the rotor arm were acquired by finding the natural frequency based on Rayleigh method. A simplified quad-rotor FE model consisting of rotor arm assembly with tip mass was built to perform numerical analysis, and a free-free boundary condition was applied to provide flight status. Modal tests for the actual platform with impact hammer instrument were performed to verify analysis results. Separation margin from hazardous eigen-mode was checked on the propeller operation range.