Aircraft Interior Noise Reduction Through a Piezo Tunable Vibration Absorber System (original) (raw)
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Application of Piezoelectric Materials for Aircraft Propeller Blades Vibration Damping
International Journal of Scientific and Engineering Research
Abs tr act-Vibrations of turbomachinery blades are critical to jet engine durability and performance. Active vibration control using piezoelectri c sensors and actuators have recently been emerged as a practi cal and promising technology. This paper deal s w ith a new vibration damping technique for an Unmanned Aerial Vehicle (UAV) propeller (BIELA 24 in diameter and 12 in pitch) utilizing piezoelectri c transducers (sensors and actuators). The propeller blades are one of the main sources of turboprop engine vibration. The damping performance depends on the type and location of the piezoelectri c transducers with respect to the mode shape of the blade mechanical strain. Numerical simulations are carried out for the propeller blades. A finite element modal analysis of non-rotating propeller w ithout piezoelectri c transducers is built in ANSYS-Workbench 15.0, where the numerical results are compared to the experimental measured modal data for veri fication. The numerical results are in very good agreement w ith the experimental measured data. A numerical model of the propeller w ithout and w ith piezoelectri c transducers is built in ANSYS. The results indicate the feasibility of using piezoelectri c transducers as a smart material for vibration suppression in turboprop engines by applying these transducers to propeller blades at the first mode high modal strain areas.
Piezoceramic Materials and Devices, NOVA Science publ., 2009
In the presented chapter some theoretical and real-world approaches to design and implementation of aircraft structures smart vibration control on the basis of controlled by feedback and shunted by external circuits power PZT patches are presented. First we consider a problem of vibration reduction in the helicopter rotor blades, more particularly, the features of rotor blade dynamics and approach to ensuring a dynamic similarity between full scale and scaled rotor blade. On the basis of this analysis we deduce the principal requirements to smart vibration control of rotor blades. One of the greatest technical difficulties of rotor blade active vibration damping is the necessity to transmit to a blade the number of high-voltage command signals through the rotated hub. The purpose of our investigation was decreasing a number of control channels at saving good vibration damping efficiency. In the presented study we try to find the optimum type (bimorph or unimorph), places, and sizes of plate-like actuators and sensors attached to a composite spar undergoes the bend and twist load. We also perform a comparative investigation of active and passive (shunted by electric circuit) PZT actuators working modes. On basis of numerical simulation it is shown that passive damping mode is efficient in the high frequency range only. On other hand, at active control the stability of control loop can be lost at some vibrations and feedback parameters. We propose an approach according to which all active controlled PZT patches are driven at narrow frequency band filtering preferentially on a first eigenfrequencies. And all installed shunted passive PZT patches will damp high vibration frequencies, simultaneously rising stability of the control loop. Finally we present some experimental results obtained on the scaled (1/7) rotor.
Vibration damping of aircraft propeller blades using shunted piezoelectrictransducers
Vibration damping of aircraft propeller blades using shunted piezoelectrictransducers, 2021
Gas turbine engine blades experience vibrations due to the flow disturbances, these vibrations are critical to the engine durability and performance. Piezoelectric transducers (sensors and actuators) have been used for engine blade vibrations damping either through a passive or active vibration control. The propeller blades are part of turboprop engine and considered as one of the main source of turboprop engine vibrations. Piezoelectric blade damping ideas have been studied by other researchers for fan blades and compressor blades. In this research a vibration damping procedure using piezoelectric transducers applied to an unmanned aerial vehicle (UAV) composite propeller. Experimental investigation introduces an approach for the propeller vibration damping using piezoelectric transducers in conjunction with appropriate shunt circuit. Three thin piezoelectric transducers macro fiber composite (MFC) type PZT-5A are surface-mounted on the propeller, one at each blade. These transducers are placed at locations of high modal strain areas for the propeller first mode at each blade, where these locations are identified by finite element numerical simulation. Electronic resonance shunt circuit, resistor-inductor-capacitor type, for the piezoelectric transducers is designed and experimentally developed such that effective vibration suppression of the propeller is achieved. The experimental and numerical investigations in this research illustrate that piezoelectric transducers with appropriate shunt circuit reduces the aircraft propeller vibrations.
Research of an Active Tunable Vibration Absorber for Helicopter Vibration Control
Chinese Journal of Aeronautics, 2003
Sig nificant structural vibratio n is an undesir able characteristic in helico pter flight that leads to st ructural fatig ue, poor ride quality for passenger s and hig h acoustic sig nature. P revio us Individual Blade Control ( I BC ) t echniques to r educe these effects hav e been hinder ed by electromechanical limitatio ns of piezoelect ric actuators. T he Smart Spr ing is an active tunable v ibr ation absorber using I BC approach to adaptively alter the "struct ur al impedance" at the blade r oot. In this paper, a mathematical model w as developed t o pr edict the r espo nse under harmo nic ex citatio ns. An adaptiv e notch alg orithm was designed and implement ed on a T M S320c40 DSP platfo rm. Reference sig nal synthesis techniques w er e used to automat ically tr ack the shifts in the fundamental v ibrator y frequency due to v ariations in flight conditio ns. Clo sed-loop tests per formed on the proof -of-concept hardwar e achieved sig nificant vibr ation suppr essio n at har monic peaks as w ell as t he br oadband reduction in vibrat ion. T he investigation ver ified the capability of the Smart Spr ing to suppress multiple harmonic compo nents in blade vibratio n thr oug h act ive impedance contro l. Key words: helicopter vibr ation cont rol; active tunable v ibr ation absorber; smar t str uctur e . , David G . Z imcik, V ir esh K . Wickramasinghe, F red N it zsche. ( ) , 2003, 16( 4) : 203-211. : , , , , ; , DSP ; , : ; ; : 1000-9361( 2003) 04-0203-09 : V 214. 3 + 3 : A Helicopter rotors operat e in a highly complex , unsteady aerodynam ic environm ent caused by cyclic v ariat ion of centrifugal and aerodynamic loads on the blades. Sig nificant structural vibrat ion due to unst eady aerody namics caused by blade vortex int eract ion ( BVI) and dynamic blade stall is a not able and undesirable charact eristic of helicopt er flight [ 1] .
52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, 2011
Piezoelectric-based vibration reduction can alleviate the unwanted vibration levels of turbomachinery, thus reducing the dangers of high-cycle fatigue while also decreasing the blade weight, drag, and jet noise. Most passive approaches provide limited benefit in turbomachinery due to the changing blade dynamics and excitation conditions that make optimally tuning a shunt circuit difficult. Active control typically provides large vibration reduction but requires a power source in the rotating frame. Semi-active approaches seek to balance the advantages of passive and active systems, outperforming the passive approaches while significantly reducing the power required. This research presents a semiactive approach that applies to excitations with swept frequencies. It involves detuning the structural resonance frequency from the excitation frequency by altering the structural stiffness (here by switching the electrical boundary conditions of a piezoelectric element), thus limiting the structural dynamic response. Including a switch back to the original stiffness state, detuning requires two switches per resonance / excitation frequency crossing, orders of magnitude fewer than other state switching approaches that require four switches per cycle of vibration. The detuning method applies to any mode of vibration with a positive electromechanical coupling coefficient and provides the greatest normalized vibration reduction for slow sweeps, low damping, and high coupling coefficient. Yet even for a moderate sweep rate α = 10 −4 and modal damping ζ = 0.1%, detuning a structure with a coupling coefficient k 2 = 10% provides the same vibration reduction as increasing either the sweep rate or modal damping by an order of magnitude.
Tuning of a vibration absorber with shunted piezoelectric transducers
Archive of Applied Mechanics, 2014
In order to reduce structural vibrations in narrow frequency bands, tuned mass absorbers can be an appropriate measure. A quite similar approach which makes use of applied piezoelectric elements, instead of additional oscillating masses, are the well-known resonant shunts, consisting of resistances, inductances, and possibly negative capacitances connected to the piezoelectric element. This paper presents a combined approach, which is based on a conventional tuned mass absorber, but whose characteristics can be strongly influenced by applying shunted piezoceramics. Simulations and experimental analyses are shown to be very effective in predicting the behavior of such electromechanical systems. The vibration level of the absorber can be strongly attenuated by applying different combinations of resistant, resonant, and negative capacitance shunt circuits. The damping characteristics of the absorber can be changed by applying a purely resistive or resonant resistant shunt. Additionally, the tuning frequency of the absorber can be adapted to the excitation frequency, using a negative capacitance shunt circuit, which requires only the energy to supply the electric components.
A new adaptive resonance frequency of piezoelectric components used for vibration damping
The Journal of the Acoustical Society of America, 2010
This paper describes two methods for vibration damping in a broad band frequency range using a piezoelectric patch. The first method, applied to an adaptive device, uses a bias (static voltage control), which applies stresses or releases stresses in a piezoelectric component to modify its mechanical characteristics and thereby its resonance frequency. The second method is based on a semipassive approach [synchronized switch damping (SSD)], developed to control structural vibration damping using a piezoelectric component. Attenuations of 10 and 4.8 dB in vibration velocity have been obtained using the adaptive frequency and SSD methods.