Experimental feedback control of flow-induced cavity tones

被引：17

作者：

Cabell, Randolph H. ^{[1
]}

Kegerise, Michael A. ^{[1
]}

Cox, David E. ^{[1
]}

Gibbs, Gary P. ^{[1
]}

机构：

[1] NASA, Langley Res Ctr, Hampton, VA 23681 USA

来源：

AIAA JOURNAL | 2006年 / 44卷 / 08期

关键词：

D O I：

10.2514/1.19608

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Discrete-time, linear quadratic methods were used to design feedback controllers for reducing tones generated by flow over a cavity. The dynamics of a sypthetic-jet actuator mounted at the leading edge of the cavity as observed by two microphones in the cavity were modeled over a broad frequency range using state space models computed from experimental data. Variations in closed loop performance as a function of model order, control order, control bandwidth, and state estimator design were studied using a cavity in the Probe Calibration Tunnel at NASA Langley Research Center. The controller successfully reduced the levels of multiple cavity tones at the tested flow speeds of Mach 0.275, 0.35, and 0.45. In some cases, the closed loop results were limited by excitation of sidebands of the cavity tones, or the creation of new tones at frequencies away from the cavity tones. The models were not able to account for nonlinear dynamics, such as interactions between tones at different frequencies. Nonetheless, the results validate the combination of optimal control and experimentally generated state space models for the cavity tone problem.

引用

页码：1807 / 1815

页数：9

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