某战斗机高速全模颤振风洞试验研究

Abstract

Abstract: In order to validate the flutter testing technology for high-speed wind tunnel and obtain the flutter safety limit of a fighter plane, the full-model flutter characteristics of the fighter plane are investigated based on wind tunnel test. The key points of investigation focus on the stability and safety of the model and support system, and the typical flutter characteristics of the full-model. The results reveal that the freedom degrees of the model motion are not restricted by the support system except for axis direction and the system is stable and safe during testing. The flutter characteristics are influenced to a great extent by the non-linear aerodynamic forces at the transonic regime and the non-linear elastic forces at higher dynamic pressures, and the non-linear relationship between stability parameters and dynamic pressure also resulted from them. The plot of vibration time history show that the flutter type of the full-model is a tempered flutter and validated the calculation results when the model is designed.

Key words: full-model flutter, aeroelasticity, floating suspension system, wind tunnel test, fighter plane

CLC Number:

V215.3⁺4

GUO Hongtao, LU Bo, YU Li, YANG Xinghua, LUO Jianguo, LU Binbin. Investigation on Full-model Flutter of a Certain Fighter Plane in High-speed Wind Tunnel Test[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012, 33(10): 1765-1771.

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Investigation on Full-model Flutter of a Certain Fighter Plane in High-speed Wind Tunnel Test

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