English  |  正體中文  |  简体中文  |  全文筆數/總筆數 : 49433/84388 (59%)
造訪人次 : 7446263      線上人數 : 95
RC Version 7.0 © Powered By DSPACE, MIT. Enhanced by NTU Library & TKU Library IR team.
搜尋範圍 查詢小技巧:
  • 您可在西文檢索詞彙前後加上"雙引號",以獲取較精準的檢索結果
  • 若欲以作者姓名搜尋,建議至進階搜尋限定作者欄位,可獲得較完整資料
  • 進階搜尋
    請使用永久網址來引用或連結此文件: http://tkuir.lib.tku.edu.tw:8080/dspace/handle/987654321/46444

    題名: The lifting rotor inflow mode shapes and blade flapping vibration system eigen-analysis
    作者: Wang, Yi-Ren;Peters, David A.
    貢獻者: 淡江大學航空太空工程學系
    關鍵詞: Dynamics;Eigenvalues and eigenfunctions;Helicopter rotors;Lift;Mathematical models;Mathematical transformations;Matrix algebra;Three dimensional;Turbomachine blades;Unsteady flow;Velocity;Wakes;Axial flight flapping modes;Blade flapping vibration system;Eigenanalysis;Lifting rotor inflow mode;Peters generalized dynamic inflow theory;Unsteady wake model;Vibrations (mechanical)
    日期: 1996-07
    上傳時間: 2013-03-20 16:24:44 (UTC+8)
    出版者: Amsterdam: Elsevier BV
    摘要: The three-dimensional helicopter rotor inflow vibrating modes and rigid blade flapping motion coupled with unsteady wake system have been studied through eigen-analysis. The Peters' generalized dynamic inflow theory has been chosen as the unsteady wake model. The three-dimensional inflow velocity vibrating mode shapes for node lines have been plotted in various skew angles. The continuous motions of these mode shapes provide important information and insight into the physical phenomenon of a helicopter rotor-wake aeroelastic system. The damping of axial flight flapping modes and the flapping divergent boundary in forward flight have been compared with Su's and Lowis' rsults, respectively, to show the accuracy of our model. The results of this work give us stability information about a rotor aeroelastic system and also reveal that the induced flow has a profound effect on blade dynamics even at high advance ratios. The effect may cause an earlier unstable condition for a helicopter rotor system.
    關聯: Computer Methods in Applied Mechanics and Engineering 134(1-2), pp.91-105
    DOI: 10.1016/0045-7825(96)01027-4
    顯示於類別:[航空太空工程學系暨研究所] 期刊論文


    檔案 大小格式瀏覽次數



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