淡江大學機構典藏:Item 987654321/18475
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    Please use this identifier to cite or link to this item: https://tkuir.lib.tku.edu.tw/dspace/handle/987654321/18475


    Title: 直昇機旋翼葉片扭角之最佳化設計
    Other Titles: Optimum design twist angle for helicopter rotor blade
    Authors: 張永康;Chang, Y. K.;王怡仁;Wang, Y. R.;謝鳴軒’;Hsieh, M. S.
    Contributors: 淡江大學航空太空工程學系
    Keywords: 旋翼力學;尾流動力學;最佳化設計;Rotary Wing Dynamics;Rotor Blade;Wake Dynamics;Optimal Design;Twist Angle
    Date: 1997-12
    Issue Date: 2009-09-01 13:37:26 (UTC+8)
    Publisher: 臺南市 : 成功大學
    Abstract: 本研究將利用最佳準則法在考慮非穩態空氣動力環境下, 以期設計出直昇機旋翼葉片最佳的扭角分佈值。此法必須滿足庫恩塔克必要條件, 並能在固定的推力限制下獲得最低輸出功率。以往葉片的設計甚少考慮尾流振動的影響, 本研究結合了旋翼的空氣動力及尾流動力之耦合系統, 並選用Peters的尾流動力理論作為非穩態空氣動力環境的模擬, 且利用自動操控的調適平衡法取得葉片在此一振動系統下之升力及扭角的最終穩態平衡值。二種不同飛行狀態的範例將在本文中探討。
    This study presents an application of optimality criteria method for a helicopter rotor blade twist angle design through an unsteady aerodynamic consideration. The method used in blade optimization is the concept of Khun- Tucker necessary condition, which to minimize the power output and also maitain the lift force with the optimum configuration of the blade. The unsteady aerodynamic environment used for the blade design contains the coupling of wake dynamics and aerodynamics. The Peters' finite state inflow theory is chosen for a wake modeling. The auto pilot trim approach ia applied to find the blade twist angle distribution around the rotor disk subject to a lift equilibrium condition in such a wake vibration system. Two different flight condition example will be discussed in this study.
    Relation: 中國航空太空學會八十六年年會暨第三十九屆學術研討會論文集›†=Proceedings of the 39th Conference on Aeronautics and Astronautics, R.O.C.，頁651-658
    Appears in Collections:[Graduate Institute & Department of Aerospace Engineering] Proceeding

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