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    Please use this identifier to cite or link to this item: http://tkuir.lib.tku.edu.tw:8080/dspace/handle/987654321/84715


    Title: 直昇機旋翼於空氣動力和尾流動力耦合系統之穩健化研究
    Authors: 張永康;林昉瑾;劉偉斌Chang, Y. K.;Lin, F. J.;Liu;W. B.
    Contributors: 淡江大學航空太空工程學系
    Keywords: 旋翼力學;尾流動力學;穩健設計Rotary Wing Dynamics;Wake Dynamics;Robust Design
    Date: 1999
    Issue Date: 2013-03-22 19:32:34 (UTC+8)
    Abstract: 本研究係利用穩健設計之觀念,考量製造與使用環境變異的影響,使研發設計的葉片能有穩定的品質輸出,以達到穩健最佳化的目標。吾人將採用最佳化指標的觀念配合統計學的方法以期能夠設計出直昇機旋翼葉片的最佳外形。穩健最佳化設計即是希望所得到的設計儘可能的趨近公稱最佳值而且移動限制也保持在合理區間內,因此本研究採用新的可變式移動限制技術應用於複雜的直昇機非線性系統內。
    The purpose of this study is to use the robust design concept which considering the effect of manufacturing and variability on a design through an unsteady aerodynamic system and obtain the steady output for the optimum design of the rotor blade. In this research we develop a new approach for helicopter rotor blade optimum configuration design by optimality index concept and statistical method. Therefore, a new variable move limit technique was developed and applied to the helicopter complex nonlinear systems.
    Relation: 一九九九中華民國「航太學會/燃燒學會/民航學會」航太學術聯合會議論文集=Proceedings of the 1999 AASRC/ CIROC/ CSCA Aerospace Joint Conference,頁463-469
    Appears in Collections:[航空太空工程學系暨研究所] 會議論文

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    直昇機旋翼於空氣動力和尾流動力耦合系統之穩健化研究_西文摘要.docx摘要13KbMicrosoft Word68View/Open

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