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Numerical and Experimental Investigation of the Design of a Piezoelectric De-Icing System for Small Rotorcraft Part 3/3: Numerical Model and Experimental Validation of Vibration-Based De-Icing of a Flat Plate Structure

1
Anti-Icing Materials International Laboratory (AMIL), Université du Québec à Chicoutimi (UQAC), Chicoutimi, QC G7H 2B1, Canada
2
National Research Council Canada, Flight Research Laboratory, Ottawa, ON K1A 0R6, Canada
*
Author to whom correspondence should be addressed.
Aerospace 2020, 7(5), 54; https://doi.org/10.3390/aerospace7050054
Received: 31 March 2020 / Revised: 26 April 2020 / Accepted: 29 April 2020 / Published: 2 May 2020
(This article belongs to the Special Issue Deicing and Anti-Icing of Aircraft)
The objective of this research project is divided in four parts: (1) to design a piezoelectric actuator-based de-icing system integrated to a flat plate experimental setup and develop a numerical model of the system with experimental validation, (2) use the experimental setup to investigate actuator activation with frequency sweeps and transient vibration analysis, (3) add an ice layer to the numerical model and predict numerically stresses at ice breaking with experimental validation, and (4) bring the concept to a blade structure for wind tunnel testing. This paper presents the third part of the investigation in which an ice layer is added to the numerical model. Five accelerometers are installed on the flat plate to measure acceleration. Validation of the vibration amplitude predicted by the model is performed experimentally and the stresses calculated by the numerical model at cracking and delamination of the ice layer are determined. A stress limit criteria is then defined from those values for both normal stress at cracking and shear stress at delamination. As a proof of concept, the numerical model is then used to find resonant modes susceptible to generating cracking or delamination of the ice layer within the voltage limit of the piezoelectric actuators. The model also predicts a voltage range within which the ice breaking occurs. The experimental setup is used to validate positively the prediction of the numerical model. View Full-Text
Keywords: icing; rotorcraft; ice protection system; piezoelectric actuator; vibration; numerical model; experimental testing icing; rotorcraft; ice protection system; piezoelectric actuator; vibration; numerical model; experimental testing
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Villeneuve, E.; Volat, C.; Ghinet, S. Numerical and Experimental Investigation of the Design of a Piezoelectric De-Icing System for Small Rotorcraft Part 3/3: Numerical Model and Experimental Validation of Vibration-Based De-Icing of a Flat Plate Structure. Aerospace 2020, 7, 54.

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