本研究係利用混合法在考慮非穩態空氣動力環境下, 尋求直昇機於全程飛行中含有不同飛行狀態之最低總輸出功率並滿足各飛行狀態的最大升力要求。本研究將探討以線性規劃法和最佳準則法為基礎之混合法, 並配合以Bezier Curve為技巧之移動限制以期設計出直昇機旋翼葉片最佳且平滑的弦長分佈值。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, 且利用葉片元素理論及升力線理論推導出升力函數。本文之目的即希望設計出一套系統程式, 應用所發展的混合法以提高葉片設計的效率及準確性。 This study presents an application of hybrid method for a helicopter rotor blade design through an unsteady aerodynamic consideration. The objective of this study is to find the best strategy for the optimum design algorithm, which based on linear programming and optimality criteria. The move limit is improved by the Bezier curve technique. The Peters finite state inflow theory is chosen for a wake modeling. The blade element theory and lifting-line theory are used to formulate the aerodynamic force (lift) for a blade. The best configuration design of the rotor blade can be obtained when the design variables are solved.
