Induced-Shear Piezoelectric Actuators for Active Twist Rotor Blades

Centolanza, Louis; Smith, Edward C.

doi:10.2514/6.2002-1446

Cited by 8 publications

(5 citation statements)

References 26 publications

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“…Smith [56] analytically evaluated an induced shear piezoelectric tube as an active blade twist actuator. This induced shear actuator had already been investigated for trailing edge flap models; an effort for developing an active twist rotor was being pursued in this study.…”

Section: Induced Shear Mechanismsmentioning

confidence: 99%

See 1 more Smart Citation

Active Twist Control of Smart Helicopter Rotor - A Survey

Thakkar,

Ganguli

2023

joast

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Helicopter vibration and blade-vortex interaction (BVI) noise are major problems restricting the wider use of helicopters in civil and military applications. Traditional methods based on vibration isolators and absorbers and passive designs of the rotor blade to reduce BVI noise have reached the point of diminishing returns and are increasingly unable to meet the stringent requirements of next generation helicopters. The advent of smart materials such as piezoceramics, has opened the possibility of actively twisting the rotor blade using control algorithms in a manner such that new higher harmonic forcing is developed which cancels the existing unsteady higher harmonic aerodynamic forces that are the main sources of vibration and noise on the rotor. Since the main rotor of a helicopter is the principal source of vehicle vibration, active twist control offers possibility of a low vibration helicopter. This paper reviews the literature in active twist rotor control using smart materials.

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Section: Induced Shear Mechanismsmentioning

confidence: 99%

“…The studies [56][57][58] show the possible use of induced shear actuation for the active twist rotor. The piezoelectric coefficient d 15 is larger than d 31 and d 33 and increases in a strongly nonlinear manner with increasing electric field leading to high induced strains.…”

Section: Induced Shear Mechanismsmentioning

confidence: 99%

Active Twist Control of Smart Helicopter Rotor - A Survey

Thakkar,

Ganguli

2023

joast

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“…Smith [26] analytically evaluated an induced shear piezoelectric tube as an active blade twist actuator. A finite element model of the induced shear actuator and rotor blade was used to guide the designs of the tube actuator for both small-scale and full-scale rotor blade applications.…”

Section: Induced Shear Actuation and Nonlinearitymentioning

confidence: 99%

Helicopter vibration reduction in forward flight with induced-shear based piezoceramic actuation

Thakkar¹,

Ganguli

2004

Smart Mater. Struct.

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Governing equations are obtained for helicopter rotor blades with surface bonded piezoceramic actuators using Hamilton’s principle. The equations are then solved for dynamic response using finite element discretization in the spatial and time domains. A time domain unsteady aerodynamic model is used to obtain the airloads. The nonlinear relationship between the piezoelectric shear coefficient and applied ac field is represented as a polynomial curve fit. The nonlinear effects are investigated by applying a sinusoidal voltage to the helicopter rotor blade. The rotor blade is modeled as a two-cell box section with piezoelectric layers surface bonded to the top and bottom of the box beam. Comparison of results with linear and nonlinear shear coefficients is presented. Use of a nonlinear relationship (compared to linear) to achieve targeted reductions in strains or displacements results in a reduction in the requirement of applied amplitude of the sinusoidal field. A rate feedback control law is implemented which feeds back the higher harmonics of the time rate of change of strain in the azimuthal direction. The sensed voltage is then applied to the rotor blade, resulting in a vibration reduction of approximately 43% for a four-bladed, soft-in-plane hingeless rotor in forward flight.

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“…The tube actuator functioned well under torque load and demonstrated superior characteristics compared with the previously reported torsional actuators. Centolanza and Smith [5] applied this torsional actuator to actively twist rotor blades.…”

Section: Introductionmentioning

confidence: 99%

Optimal excitation of a rectangular plate resting on an elastic foundation by a piezoelectric actuator

Yang¹,

Zhang

2006

Smart Mater. Struct.

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In this paper, a simply supported rectangular plate subject to in-plane forces, resting on an elastic foundation and excited by a PZT actuator, is studied. A closed-form solution has been obtained to describe the plate vibration. Based on this solution, the optimal placement of the PZT actuator in terms of maximizing the plate deflection is calculated and discussed. It is observed that the pattern of the optimal locations of the PZT actuator can be represented by a simple function, namely, the combined position mode function (CPMF). A simple yet general procedure to determine the optimal excitation locations is thus proposed based on the above observation. This procedure only requires the calculation of natural frequencies of the plate and the CPMF, thus alleviating the computational effort in searching for the optimal PZT locations.

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Induced-Shear Piezoelectric Actuators for Active Twist Rotor Blades

Cited by 8 publications

References 26 publications

Active Twist Control of Smart Helicopter Rotor - A Survey

Active Twist Control of Smart Helicopter Rotor - A Survey

Helicopter vibration reduction in forward flight with induced-shear based piezoceramic actuation

Optimal excitation of a rectangular plate resting on an elastic foundation by a piezoelectric actuator

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