本文利用升力線法和葉片元素理論模擬具扭角的旋翼葉片的空氣動力特性並和動力尾流理論相耦合而模擬旋翼之非穩態空氣動力環境。此外，本文利用自動操控的調適平衡法(auto pilot trim approach)取得葉片在此一振動系統下之升力及扭角在整個旋翼圓盤的最終穩態平衡值；本文所考慮的系統是一尾流、升力、及葉片外形扭角三者相互影響的閉迴路系統，其中任一項的改變都會導致其他二者的改變。本系統所發展的模式可成功預測旋翼在不同的飛行姿態且達到平衡時旋翼圓盤的升力及攻角分佈。 In this work, the lifting line method and blade element theory are used to formulate a twisted rotor blade lift distribution and coupled with dynamic wake model to simulate the unsteady aerodynamic environment of a lifting rotor. The auto pilot trim approach is applied to the rotor system subject to a lift equilibrium condition in such a wake vibrating system. Results show that our model successfully predicts the lift and angle of attack distribution on the trimmed rotor disk.
Relation:
中國航空太空學會學刊=Transactions of the Aeronautical and Astronautical Society of the Republic of China 29(3)，頁217-226
