本文對於直昇機轉子的氣體彈性系統於前飛的狀況下，其頻率響應以一個三維尾流的模式及一剛性葉片組成的轉子做拍撲運動而探討之。此三維尾流乃是以Peters的有限狀態引入流理論模擬其運動，而葉片的拍撲解及誘導流係數則以傅利葉函數展開於頻域內。此耦合系統之升力及控制導數的頻率響應則與二維模擬結果相比較，其結果顯示在每一共振區間的升力，前飛時將比垂直飛行時還低，此外也發覺尾流層在前飛時，並末如想像中的隨著消失。其影響力仍存在著，就如同其之對於盤旋飛行時一般。 The frequency response of a helicopter rotor aeroelastic system in forward flight is studied by a three-dimensional unsteady wake model coupled with a rigid-bladed flapping rotor. This three-dimensional wake model is extracted from Peters' finite-state inflow theory. Fourier series are applied to the blades flapping angles and rotor inflow state coefficients to extend the coupled equations to frequency domain. The frequency response of these coupled system lifts and control derivatives are compared with two-dimensional results and show that in forward fight, the lifts in each resonant area are lower than the vertical flight condition, and reveal that the wake layering is not diminished in forward flight. The wake effect still plays an important role as it does in hover.
中國航空太空學會學刊=Transactions of the Aeronautical and Astronautical Society of the Republic of China 26(4)，頁299-309