Mechanisms of active control in cylindrical fuselage structures

Silcox, R. J.; Lester, H. C.; Fuller, C

doi:10.2514/6.1987-2703

Cited by 5 publications

(3 citation statements)

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“…For instance, this control approach has been successfully applied on the SAAB 2000 aircraft, using 72 control microphones and 48 loudspeakers (Emborg 1998). An alternative efficient control method is represented by the active structural acoustic control (ASAC) approach that uses structurally-based actuators to exert control forces on the cavity bounding shell to minimize wall vibrations and, in turn, sound radiated in the cavity (Jones and Fuller 1990;Silcox et al 1990Silcox et al , 1992.…”

Section: Introductionmentioning

confidence: 99%

Optimal design of tonal noise control inside smart-stiffened cylindrical shells

Bernardini

Testa

Gennaretti

2011

Journal of Vibration and Control

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This paper deals with the abatement of noise inside cylindrical cavities bounded by stiffened shells that are impinged by external tonal sound waves. The problem is analysed in a multidisciplinary context, involving interactions among exterior noise field, elastic shell dynamics, interior acoustics and control system. The actuation in the noise control process is performed through piezoelectric patches embedded in the stiffened shell, driven by a control law obtained from an optimal LQR cyclic control formulation, coupled with a genetic optimization algorithm (GA). A modal approach is applied to describe the smart shell dynamics and the interior acoustics that are coupled in the acoustoelastic plant model, while the exterior acoustic scattering is predicted through a boundary element method formulation. Numerical results deal with an aeronautical problem concerning a general aviation aircraft cabin impinged by the pressure disturbances emitted by a pair of propellers; in particular, the effectiveness and robustness of the active control law synthesized through the GA is investigated.

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Section: Introductionmentioning

confidence: 99%

Optimal design of tonal noise control inside smart-stiffened cylindrical shells

Bernardini

Testa

Gennaretti

2011

Journal of Vibration and Control

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“…Some of the early efforts for active noise control of cylindrical shells were initiated in the 1980s by NASA, since the traditional methods dictated a mass law for low-frequency control, while for aerospace vehicles maximum noise reduction is desired with minimum additional weight [8][9][10]. Further work was done modeling and taking experimental data for active control of aircraft fuselages by Bullmore and others [11][12][13][14][15][16][17]. In the following years, some advancements were achieved in better understanding the relation between the vibration of the structure and the radiated sound.…”

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confidence: 99%

Active control of cylindrical shells using the weighted sum of spatial gradients control metric

Aslani

Sommerfeldt

Blotter

2015

Journal of the Acoustical Society of America

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Active Control of Cylindrical Shells Using theWeighted Sum of Spatial Gradients (WSSG) Control Metric Pegah Aslani Department of Physics and Astronomy, BYU Doctor of Philosophy Cylindrical shells are common structures that are often used in industry, such as pipes, ducts, aircraft fuselages, rockets, submarine pressure hulls, electric motors and generators. In many applications it is desired to attenuate the sound radiated from the vibrating structure. There are both active and passive methods to achieve this purpose. However, at low frequencies passive methods are less effective and often an excessive amount of material is needed to achieve acceptable results. There have been a number of works regarding active control methods for this type of structure. In most cases a considerable number of error sensors and secondary sources are needed. However, in practice it is much preferred to have the fewest number of error sensors and control forces possible. Most methods presented have shown considerable dependence on the error sensor location. The goal of this dissertation is to develop an active noise control method that is able to attenuate the radiated sound effectively at low frequencies using only a small number of error sensors and secondary sources, and with minimal dependence on error sensor location. The Weighted Sum of Spatial Gradients control metric has been developed both theoretically and experimentally for simply supported cylindrical shells. The method has proven to be robust with respect to error sensor location. In order to quantify the performance of the control method, the radiated sound power has been chosen. In order to calculate the radiated sound power theoretically, the radiation modes have been developed for cylindrical shells. Experimentally, the radiated sound power without and with control has been measured using the ISO 3741 standard. The results show comparable, or in some cases better, performance in comparison with other known methods. Some agreement has been observed between model and experimental results. However, there are some discrepancies due to the fact that the actual cylinder does not appear to behave as an ideal simply supported cylindrical shell.

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“…This is consistent with the well-accepted rule that treating noise at or close to its source yields superior performance compared to treating the problem further down the transmission path. The resulting system is generally simpler with fewer actuators and sensors since they are required only in the propeller footprint area (Silcox et al, 1990;Rossetti et al, 1993). The use of piezoelectric elements as structural actuators has a number of benefits due to their high bandwidth, low weight and distributed nature.…”

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confidence: 99%

Active Cabin Noise and Vibration Control for Turboprop Aircraft Using Multiple Piezoelectric Actuators

Grewal

Zimcik

Hurtubise

et al. 2000

Journal of Intelligent Material Systems and Structures

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The Active Structural Acoustic Control (ASAC) technique was applied to reduce propeller-induced noise and vibration in the passenger cabin of the deHavilland Dash-8 turboprop aircraft. Piezoceramic elements were used for structural actuation while velocity feedback of the fuselage was achieved through the use of accelerometers. Three actuators comprised of segmented piezoelectric elements were designed with the objective of reducing the noise and vibration levels at the propeller Blade Passage Frequency (BPF). Twelve accelerometers were grouped to effectively form three sensors. Second order classical compensators were designed for each of the three dominant control loops in order to achieve high gain at the BPF, rendering the closed-loop system insensitive to disturbances at the control frequency. The propeller acoustic field on the port side of the aircraft was simulated in a laboratory using a speaker-ring consisting of four loudspeakers. The control system was tested using this acoustic field, producing noise attenuation as high as 28 dB in the interior, and fuselage vibration reduction as high as 16 dB.

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Mechanisms of active control in cylindrical fuselage structures

Cited by 5 publications

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Optimal design of tonal noise control inside smart-stiffened cylindrical shells

Optimal design of tonal noise control inside smart-stiffened cylindrical shells

Active control of cylindrical shells using the weighted sum of spatial gradients control metric

Active Cabin Noise and Vibration Control for Turboprop Aircraft Using Multiple Piezoelectric Actuators

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