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Design for Flapping Wing Micro Vehicle Using 6-Bar Linkage Mechanism
6절 링크를 이용한 날갯짓 초소형 비행체 설계

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Authors
전재혁
Advisor
신상준
Major
공과대학 기계항공공학부
Issue Date
2016-02
Publisher
서울대학교 대학원
Keywords
Flapping wingMulti-body dynamic analysisSix-bar linkage
Description
학위논문 (석사)-- 서울대학교 대학원 : 기계항공공학부, 2016. 2. 신상준.
Abstract
Recently, there occurs rise and growth of the research on the flapping wing vehicles
by mimicking the biological motion. Its result is so-called the Flapping Micro Aerial
Vehicle (FWMAV). In this thesis, design requirements for FWMAV were established
by using an analytical tool and unsteady blade element theory (UBET). Based on the
present FWMAV design requirements, flapping wing mechanism using a six-bar
linkage was devised. Moreover, the present mechanisms were analyzed by using the
flexible multi-body dynamic analysis to ensure its structural robustness. By
completing such procedure, behavior of the present mechanism was estimated. Then,
detail design was conducted. Currently, structural analysis regarding the present
mechanism was conducted under the flapping operation in vacuum. And the
resulting von-Misses stresses in the linkage were designed to be smaller than the
yield stress of the chosen material. After that, detail design and experiment of the
present FWMAV were conducted for validating the performance, such as
aerodynamic force, flapping frequency and flapping amplitude.
Language
English
URI
https://hdl.handle.net/10371/123893
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College of Engineering/Engineering Practice School (공과대학/대학원)Dept. of Mechanical Aerospace Engineering (기계항공공학부)Theses (Master's Degree_기계항공공학부)
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