English  |  正體中文  |  简体中文  |  Items with full text/Total items : 62805/95882 (66%)
Visitors : 3967252      Online Users : 294
RC Version 7.0 © Powered By DSPACE, MIT. Enhanced by NTU Library & TKU Library IR team.
Scope Tips:
  • please add "double quotation mark" for query phrases to get precise results
  • please goto advance search for comprehansive author search
  • Adv. Search
    HomeLoginUploadHelpAboutAdminister Goto mobile version
    Please use this identifier to cite or link to this item: https://tkuir.lib.tku.edu.tw/dspace/handle/987654321/77075

    Title: Wing Stiffness on Light Flapping Micro Aerial Vehicles
    Authors: Yang, Lung-Jieh;Kuo, A-Fu;Hsu, Cheng-Kuei
    Contributors: 淡江大學機械與機電工程學系
    Date: 2012-03
    Issue Date: 2012-05-29 11:26:02 (UTC+8)
    Publisher: Reston: American Institute of Aeronautics and Astronautics, Inc.
    Abstract: In an effort to develop micro-aerial-vehicles (MAVs) of 20 cm-span with a successful flight record, this present study aims to investigate the influences of wing configuration and foil stiffness on the aerodynamic forces via wind tunnel testing. These wings with the same wing skeleton structures are made of polyethylene (PE), polyethyleneterephthalate (PET), and polyxylylene (parylene). The foil thickness ranges from 17 to 43 um which corresponds to the variating stiffness of the membrane. The tests showed that the lift coefficients of the stiffened wings have been improved, while the net thrust coefficients have little importance with the wing foil thickness. Inspection on the relations between power consumption and the flexural stiffness of tested flapping wings reveals that the larger lift force and greater power consumption is associated with the 35 and 43 um thick parylene. Therefore, The present study demonstrated that the flight test of a MAV with the best wing foil of 24 um thick PET resulted in the longest endurance time of 8 min. Several innovative aspects of developing this work are also summarized.
    Relation: Journal of Aircraft 49(2), p.423-431
    DOI: 10.2514/1.C031320
    Appears in Collections:[Graduate Institute & Department of Mechanical and Electro-Mechanical Engineering] Journal Article

    Files in This Item:

    File Description SizeFormat
    Wing Stiffness on Light Flapping Micro Aerial Vehicles.pdf3329KbAdobe PDF1View/Open

    All items in 機構典藏 are protected by copyright, with all rights reserved.

    DSpace Software Copyright © 2002-2004  MIT &  Hewlett-Packard  /   Enhanced by   NTU Library & TKU Library IR teams. Copyright ©   - Feedback