航空学报 > 1999, Vol. 20 Issue (6): 527-532

跨音速操纵面嗡鸣Hopf分叉分析及结构参数对嗡鸣特性影响的研究

刘千刚1, 代捷2, 白俊强1   

  1. 1. 西北工业大学飞机工程系, 陕西西安 710072;2. 北京航空航天大学飞机设计所, 北京 100083
  • 收稿日期:1997-12-15 修回日期:1999-03-01 出版日期:1999-12-25 发布日期:1999-12-25

HOPF BIFURCATION ANALYSIS OF TRANSONIC CONTROL SURFACE BUZZ AND INVESTIGATION OF THE INFLUENCE OF STRUCTURAL PARAMETERS ON BUZZ CHARACTERISTICS

LIU Qian-gang1, DAI Jie2, BAI Jun-qiang1   

  1. 1. Deparment of Aircraft Engineering, Northwestern Polytechnical University, Xi'an 710072,China;2. Institute of Flight Vehicle Design, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
  • Received:1997-12-15 Revised:1999-03-01 Online:1999-12-25 Published:1999-12-25

摘要: 采用Hopf分叉分析方法,对跨音速操纵面嗡鸣问题进行了研究。用二维守恒型非定常Navier-Stokes 方程计算了舵面振动时的非定常气动力,计算了出现Hopf分叉的Ma 数,研究了一些参数对嗡鸣的影响。将Hopf分叉的计算结果与嗡鸣的时间历程计算做了对比,两者相当吻合,与飞行试验结果相比,也比较接近。

关键词: Hopf分叉, 操纵面嗡鸣, 非定常纳维-斯托克斯方程

Abstract: Hopf bifurcation analysis is employed to investigate the problems of the control surface buzz. The unsteady aerodynamic loads acting on the control surface are calculated by the two dimensional Navier Stokes equations. The critical Mach number of the control surface buzz is calculated and the influence of the structural parameters on the buzz characteristics is also investigated. The results of the Hopf bifurcation analysis are consistent with the results of the time integration calculations, and the calculated results both are in good agreement with the flight test data.

Key words: Hopf-bifurcat ion, control sur face buzz, unsteady Navier -Stokes equat ions

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