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Nonlinear Flutter Characteristic Analysis of the Hypersonic Wings

LUO Qing;LI Dong-xu;NIE Hai-tao;ZHOU Yi;ZHANG Yi-ming

2012, 32 (3): 29-33. DOI: 10.3969/j.issn.1006-1355.2012.03.007

Abstract （1838）

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The dynamic equation of a 2-dimentional hypersonic wing was derived by using the modified third order nonlinear piston theory. Both linear and nonlinear flutter boundary conditions were obtained through Hopf-bifurcation theory and directive numerical method respectively. The simulation results show that the effects of nonlinearities can delay or precede the appearance of limit cycles oscillations according to the system parameters.

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LI Dong-xu;LIU Wang;JIANG Jian-ping

2011, 31 (4): 46-50. DOI: 10.3969/j.issn.1006-1355-2011.04.011

Abstract （1608）

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For the special physical environment of the space, the vibration control of space truss structure (STS) of spacecrafts is an important problem in aerospace technology. Passive damping control technology provides a good way for solving this vibration control problem. In this paper, a double layer cylindrical viscoelastic damper (VED) is designed on the base of theoretical analysis of the damping mechanism of viscoelastic material (VEM). Then the optimal placement of the viscoelastic damping rod is determined, and the dynamic equation of STS is derived. Furthermore, the dynamic quality of the truss structure is analyzed with the consideration of the damping characteristics of VEM. Taking a truss with a straight configuration as an example, the control effect of VED passive damping control is simulated. Numerical result shows that the amplitude of vibration in the resonance region is attenuated by 35 %, and this VED has a good control effect.