The flutter study of a two - dimensional airfoil with asymmetry freeplay 具有不對稱間隙的二元機翼顫振研究
This dissertation presents how to use the ultrasonic motor as an actuator to suppress the flutter of a two - dimensional airfoil section with a control surface . the ultrasonic motor , which features simple structure , high torque at low speed , small size , low weight and no electromagnetic contamination , is a promising actuator for the flutter suppression of small aircraft 超聲電機以其結構簡單緊湊、轉矩/質量比大、低速大扭矩、直接驅動,動態(tài)響應快、斷電自鎖和不產生磁場且不受外界磁場干擾等優(yōu)點,有望成為一種非常有前途的作動器,用于小型飛機的機翼顫振主動抑制。
The dissertation presents the combined theoretical , numerical and experimental studies on the experimental modeling of the actuator , the design of test rig and control system , the modeling of two - dimensional airfoil aeroelastic system , the control design of active flutter suppression , and the effect of group delay in the digital filter on the stability of aeroelastic closed - loop system 本文通過理論分析、數(shù)值仿真與風洞實驗相結合的方法,研究了超聲電機作動器建模、翼段顫振實驗裝置和控制系統(tǒng)設計、二維翼段氣動彈性系統(tǒng)建模、顫振抑制控制律設計以及數(shù)字濾波器群時延對顫振抑制閉環(huán)系統(tǒng)穩(wěn)定性影響等問題。