Effect of angle of attack on flutter characteristics of a control surface with free play nonlinearity

Weiwei Zhang, Zhongbo Wang, Zhengyin Ye, Yongnian Yang

科研成果: 期刊稿件文章同行评审

3 引用 (Scopus)

摘要

Limit cycle flutter of a 3D supersonic control surface with preload free play is studied. CFD (computational fluid dynamics) based local piston theory is use to compute unsteady aerodynamic loads, and equivalent linearization method is use to analysis the limit cycle flutter of the control surface. The effects of angle of attack and free play on the characteristic of the limit cycle flutter are studied. The results show that aerodynamic preloads and reduction of the free play can improve the stability of the aeroelastic system. For this supersonic control surface, if the linear flutter speed and free play of the rudder satisfies the national military standard, acute flutter won't appeal in the flight state, only small amplitude limit cycle oscillation will appeal at 0 angle attack flight.

源语言英语
页(从-至)296-301
页数6
期刊Jixie Qiangdu/Journal of Mechanical Strength
33
2
出版状态已出版 - 4月 2011

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