Abstract
An active rotor with trailing-edge flaps is an effective approach to alleviate vibrations and noise in helicopters. In this study, a compact piezoelectric actuator is proposed to drive trailing-edge flaps. The two groups of piezoelectric stacks accommodated in the actuator operate in opposition, and double-acting output can be realized through the differential motion of these stacks. A theoretical model and a finite element model are established to predict the output capability of this actuator, and structural optimization is performed using the finite element model. A prototype is built and tested on a benchtop to assess its performance. Test results demonstrate that the actuator stiffness reaches 801 N/mm, and its output stroke is up to ±0.27 mm when subjected to actuation voltage of 120 V. Agreement between measurements and simulations validates the accuracy of the established models. In addition, actuator outputs in failure modes are measured by canceling the supply voltage of one group of piezoelectric stacks. In this condition, the actuator can still generate acceptable outputs, and the initial position of the output end remains unchanged. Simulations and test results reveal that the proposed actuator achieves promising performance, and it is capable to be applied to a helicopter active rotor.
Highlights
Simulations and test results reveal that the proposed actuator achieves promising performance, and it is capable to be applied to a helicopter active rotor
Actuators of trailing-edge flaps (TEFs) are installed inside rotor blades, meaning that the actuators should be compact enough to fit the limited volume of these blades
Test results demonstrate that the established models are reliable to predict the actuator performance, and this actuator has the potential to be applied to to predict active the actuator helicopter rotors. performance, and this actuator has the potential to be applied to helicopter active rotors
Summary
Publisher’s Note: MDPI stays neutral with regard to jurisdictional claims in published maps and institutional affiliations. [10] Myasnikov et al present a prototype electro-mechanical actuator designed to drive TEFs of a medium-class helicopter Benchtop tests of this prototype with a model TEF demonstrated that the maximum deflection angle of the TEF reached 5 degrees at 19.2 Hz. the relatively low operating bandwidth of this type of actuator restricts its application in small-scaled rotors of high rotation speed. Piezoelectric actuators are applicable to active helicopter rotors Since this type of actuator operates based on the converse piezoelectric effect, and the induced strain of piezoelectric materials is usually too low to drive a TEF directly, an amplification mechanism should be used to convert the small strain into usable output. Test results demonstrate that the established models are reliable to predict the actuator performance, and this actuator has the potential to be applied to to predict active the actuator helicopter rotors. performance, and this actuator has the potential to be applied to helicopter active rotors
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