The flutter study of a two - dimensional airfoil with asymmetry freeplay 具有不對(duì)稱間隙的二元機(jī)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(jī)以其結(jié)構(gòu)簡(jiǎn)單緊湊、轉(zhuǎn)矩/質(zhì)量比大、低速大扭矩、直接驅(qū)動(dòng),動(dòng)態(tài)響應(yīng)快、斷電自鎖和不產(chǎn)生磁場(chǎng)且不受外界磁場(chǎng)干擾等優(yōu)點(diǎn),有望成為一種非常有前途的作動(dòng)器,用于小型飛機(jī)的機(jī)翼顫振主動(dòng)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(guò)理論分析、數(shù)值仿真與風(fēng)洞實(shí)驗(yàn)相結(jié)合的方法,研究了超聲電機(jī)作動(dòng)器建模、翼段顫振實(shí)驗(yàn)裝置和控制系統(tǒng)設(shè)計(jì)、二維翼段氣動(dòng)彈性系統(tǒng)建模、顫振抑制控制律設(shè)計(jì)以及數(shù)字濾波器群時(shí)延對(duì)顫振抑制閉環(huán)系統(tǒng)穩(wěn)定性影響等問(wèn)題。