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    題名: 後緣襟翼在非線性複材葉片之分析
    其他題名: On the trailing edge flap effects of the nonlinear composite rotor blade
    作者: 張穎巽;Chang, Ying-hsun
    貢獻者: 淡江大學航空太空工程學系碩士班
    王怡仁;Wang, Yi-ren
    關鍵詞: 直昇機;複材葉片;動態失速;後緣機翼;誘導流;Helicopter;composite rotor blade;ONERA dynamic stall;trailing edge flap;induced flow
    日期: 2005
    上傳時間: 2010-01-11 06:52:45 (UTC+8)
    摘要: 直昇機之減振設計已是國內外的研究課題之一,在諸多減振法之中,最讓人感興趣的為高階諧模控制法。這些控制輸出端賴於針對某一葉片做轉距角的調整,因此有獨立葉片控制法產生。然而這種利用葉片根部的連桿來改變轉距角的傳統方法已漸漸不被採用了,取而代之的為機翼後緣的伺服襟翼。近代的直昇機學界朝著複合材料之後緣機翼及智慧型結構的應用來發展,而這其中又以分析懸停滯空時之穩定性最具實用價值 (共面運動的緣故),然而相關後緣襟翼的研究仍停留在實驗的階段,在理論方面,卻是極為缺乏且幾乎為不完整的耦合模式。
    因此,本研究將建立一套整合直昇機主旋翼之非線性複合材料結構葉片、線性ONERA動態失速的空氣動力模式、尾流造成之誘導流及允許旋翼葉片後緣襟翼做任意角度調整之空氣動力流場的耦合模式。並進而分析這一套耦合系統在直昇機懸停時,隨著後緣襟翼角度的改變對於整個主旋翼氣體彈性系統之影響。
    相較於以往之研究,本論文使用完全非線性複材葉片除了能模擬更大的形變量外,亦能從中得到更完整的振動行為,從中也將可以觀察到,在線性結構方程不易被觀察到的現象。
    吾人之耦合系統所使用的比較函數是線性複材葉片方程式之理論解,並假設其邊界條件與非線性複材葉片的邊界條件一致。再利用Galerkin法來求解此耦合系統。本研究將著眼於系統之特徵值及動態響應分析,尤其是升力及扭力矩,亦即求取在不同的後緣襟翼角度之下,整個耦合系統的響應,其結果將可提供做為日後直昇機後緣襟翼設計的資訊及高階諧模控制減振技巧參考之數據。
    The dynamic behavior of a long slender beam is of interest in connection with helicopter rotor blades, wind-turbine blades, and other systems that perform large and/or complex motions. When the vibration amplitude is large, various nonlinear effects come into play. Owing to the participation of these nonlinear characteristics, many nonlinear phenomena deserve detailed exam.
    For the past years, the concept of trailing edge flap (TEF) has been applied on the helicopter rotor blade system. Although experimental analyses have made a successfully progress, the theoretical models are still on the way. It is proved that the TEF has great advantages on the vibration reduction and control of the helicopter rotor system, especially for the higher harmonic control (HHC) and individual blade control (IBC).
    In this research, the fully nonlinear composite rotor blade of a helicopter rotor system is considered. This structural model is further coupled with a linearized ONERA dynamic stall aerodynamic model and the wake induced flow effects are also included. Peters’ generalized deformable blade unsteady aerodynamic theory is used for the formulation of the TEF model on the composite rotor blade.
    The comparison functions of this aeroelastic system are obtained analytically by a linearized composite blade equation, assuming the boundary conditions is consisting with nonlinear blade. The Galerkin’s method is employed to solve the coupled system. The nonlinear coefficients of these aeroelastic equations are determined by Powell hybrid algorithm and a finite-difference approximation to the Jacobian via IMSL solver. The system eigenvalues and dynamic response due to various TEF locations on the blade and different TEF index angles (pitch angles of TEF) will be studied in this research. Hopefully, several nonlinear dynamics on the composite blade associating with the TEF effects will be discovered in this research.
    顯示於類別:[航空太空工程學系暨研究所] 學位論文

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