Experimental Feedback Control of Flow Induced Cavity Tones

Cabell, Randolph H.; Kegerise, Michael A.; Cox, D. E.; Gibbs, Gary P.

doi:10.2514/6.2002-2497

Cited by 32 publications

(25 citation statements)

References 10 publications

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“…For example, suppression of resonant tones is often accompanied by either peak splitting, i.e. creation of a pair of lower-magnitude tones on either side of the suppressed one (Rowley et al 2002), or peaking, where additional lower magnitude tones appear away from the original tone(s) (Cabell et al 2002). Therefore many opportunities remain for further advancement of the technology (Gad-el-Hak 2000).…”

Section: Introductionmentioning

confidence: 99%

An Experimental Study of the Cavity Flow for Closed-Loop Flow Control

Debiasi

Samimy

2003

33rd AIAA Fluid Dynamics Conference and Exhibit

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We present the results of an experimental investigation conducted as part of a multidisciplinary effort intended to address systematically the problem of closed-loop flow control by assembling expertise from numerical and experimental flow analysis, flow modeling, and control design disciplines. Experiments were conducted using a shallow-cavity flow in a small-scale wind tunnel that can operate continuously in the subsonic regime. We restricted our attention to cavity flow in the Mach number range 0.25-0.5. The flow exhibits the characteristic staging behavior predicted by the semi-empirical Rossiter formula with multiple modes in the Mach number range 0.32-0.38 and a single strong mode in the other flow conditions. A preliminary survey of the velocity at the exit of the compression-driver actuator used for control reveals that this actuator has a non-linear behavior and was little influenced by the local effect of Mach 0.3 main flow. Forcing the Mach 0.3 flow with the actuator indicates that this has good authority over a large range of frequencies, with elimination of the resonant peak observed at some frequencies. We took advantage of this phenomenon to develop a preliminary, logic-based controller that searches the frequency space and maintains the optimal forcing frequency for peak reduction at each Mach number. Optimal frequencies and the corresponding reduced resonance have been obtained for all the flow conditions explored.

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Section: Introductionmentioning

confidence: 99%

An Experimental Study of the Cavity Flow for Closed-Loop Flow Control

Debiasi

Samimy

2003

33rd AIAA Fluid Dynamics Conference and Exhibit

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“…In this case, the effective effort penalty at each frequency will be the sum of the frequency dependent and independent terms [5].…”

Section: Linear Quadratic Gaussian (Lqg) Controlmentioning

confidence: 99%

Decentralized control of sound radiation from an aircraft-style panel using iterative loop recovery

Schiller

Cabell

Fuller

2008

The Journal of the Acoustical Society of America

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A decentralized LQG-based control strategy is designed to reduce low-frequency sound transmission through periodically stiffened panels. While modern control strategies have been used to reduce sound radiation from relatively simple structural acoustic systems, significant implementation issues have to be addressed before these control strategies can be extended to large systems such as the fuselage of an aircraft. For instance, centralized approaches typically require a high level of connectivity and are computationally intensive, while decentralized strategies face stability problems caused by the unmodeled interaction between neighboring control units. Since accurate uncertainty bounds are not known a priori, it is difficult to ensure the decentralized control system will be robust without making the controller overly conservative. Therefore an iterative approach is suggested, which utilizes frequency-shaped loop recovery. The approach accounts for modeling error introduced by neighboring control loops, requires no communication between subsystems, and is relatively simple. The control strategy is validated using real-time control experiments performed on a built-up aluminum test structure representative of the fuselage of an aircraft. Experiments demonstrate that the iterative approach is capable of achieving 12 dB peak reductions and a 3.6 dB integrated reduction in radiated sound power from the stiffened panel.

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“…Cabell et al (2) used a piezo-driven synthetic jet. Their actuators were activated by signals from a pair of pressure sensors located in the midplane of the floor and the rear cavity wall.…”

Section: Introductionmentioning

confidence: 99%

Sound Suppression of Laminar Separating Flow over Cavity

Izawa

Maita

Terashima

et al. 2006

JSME international journal. Ser. B, Fluids and thermal engineer

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A passive control of aerodynamic noise generated by a laminar separating flow over a cavity is carried out in a wind tunnel test and by numerical simulation, using a thin plate inserted into the cavity as a passive flow-controlling device. In the experiment, a noise suppression effect up to 14 dB is achieved by placing a plate in a proper location. It is shown that a plate of smaller vertical size is more effective. In the numerical simulation, it is shown that the location where the shear layer rolls up and the path of vortices are both very sensitive to plate position.

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Experimental Feedback Control of Flow Induced Cavity Tones

Cited by 32 publications

References 10 publications

An Experimental Study of the Cavity Flow for Closed-Loop Flow Control

An Experimental Study of the Cavity Flow for Closed-Loop Flow Control

Decentralized control of sound radiation from an aircraft-style panel using iterative loop recovery

Sound Suppression of Laminar Separating Flow over Cavity

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