Experimental Study of a Piezoelectric De-Icing System Implemented to Rotorcraft Blades

A four-year project investigating the use of piezoelectric actuators as a vibration-based low power de-icing system has been initiated at the Anti-Icing Materials Laboratory. The work done preceding this investigation consisted of studying, numerically and experimentally, the system integration to a...

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Autores principales:	Eric Villeneuve, Sebastian Ghinet, Christophe Volat
Formato:	article
Lenguaje:	EN
Publicado:	MDPI AG 2021
Materias:	icing wind tunnel experimental testing numerical modeling aerospace ice protection system Technology T Engineering (General). Civil engineering (General) TA1-2040 Biology (General) QH301-705.5 Physics QC1-999 Chemistry QD1-999
Acceso en línea:	https://doaj.org/article/5e8591c7d627406796d9b344187c0278
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spelling	oai:doaj.org-article:5e8591c7d627406796d9b344187c02782021-11-11T14:59:29ZExperimental Study of a Piezoelectric De-Icing System Implemented to Rotorcraft Blades10.3390/app112198692076-3417https://doaj.org/article/5e8591c7d627406796d9b344187c02782021-10-01T00:00:00Zhttps://www.mdpi.com/2076-3417/11/21/9869https://doaj.org/toc/2076-3417A four-year project investigating the use of piezoelectric actuators as a vibration-based low power de-icing system has been initiated at the Anti-Icing Materials Laboratory. The work done preceding this investigation consisted of studying, numerically and experimentally, the system integration to a flat plate structure, the optimal excitation of the system, the resonant structural modes and the shear stress amplitudes to achieve de-icing for that structure. In this new investigation, the concepts and conclusions obtained on the flat plate structure were used to design and integrate the system into a rotating blade structure. An experimental setup was built for de-icing tests in rotation within an icing wind tunnel, and a finite-element numerical model adapted to the new geometry of the blade was developed based on the expertise accumulated using previous flat plate structure analysis. Complete de-icing of the structure was obtained in the wind tunnel using the developed de-icing system, and its power consumption was estimated. The power consumption was observed to be lower than the currently used electrothermal systems. The finite-elements numerical model was therefore used to study the case of a full-scale tail rotor blade and showed that the power reduction of the system could be significantly higher for a longer blade, confirming, therefore, the relevance of further de-icing investigations on a full-scale tail rotor.Eric VilleneuveSebastian GhinetChristophe VolatMDPI AGarticleicingwind tunnelexperimental testingnumerical modelingaerospaceice protection systemTechnologyTEngineering (General). Civil engineering (General)TA1-2040Biology (General)QH301-705.5PhysicsQC1-999ChemistryQD1-999ENApplied Sciences, Vol 11, Iss 9869, p 9869 (2021)
institution	DOAJ
collection	DOAJ
language	EN
topic	icing wind tunnel experimental testing numerical modeling aerospace ice protection system Technology T Engineering (General). Civil engineering (General) TA1-2040 Biology (General) QH301-705.5 Physics QC1-999 Chemistry QD1-999
spellingShingle	icing wind tunnel experimental testing numerical modeling aerospace ice protection system Technology T Engineering (General). Civil engineering (General) TA1-2040 Biology (General) QH301-705.5 Physics QC1-999 Chemistry QD1-999 Eric Villeneuve Sebastian Ghinet Christophe Volat Experimental Study of a Piezoelectric De-Icing System Implemented to Rotorcraft Blades
description	A four-year project investigating the use of piezoelectric actuators as a vibration-based low power de-icing system has been initiated at the Anti-Icing Materials Laboratory. The work done preceding this investigation consisted of studying, numerically and experimentally, the system integration to a flat plate structure, the optimal excitation of the system, the resonant structural modes and the shear stress amplitudes to achieve de-icing for that structure. In this new investigation, the concepts and conclusions obtained on the flat plate structure were used to design and integrate the system into a rotating blade structure. An experimental setup was built for de-icing tests in rotation within an icing wind tunnel, and a finite-element numerical model adapted to the new geometry of the blade was developed based on the expertise accumulated using previous flat plate structure analysis. Complete de-icing of the structure was obtained in the wind tunnel using the developed de-icing system, and its power consumption was estimated. The power consumption was observed to be lower than the currently used electrothermal systems. The finite-elements numerical model was therefore used to study the case of a full-scale tail rotor blade and showed that the power reduction of the system could be significantly higher for a longer blade, confirming, therefore, the relevance of further de-icing investigations on a full-scale tail rotor.
format	article
author	Eric Villeneuve Sebastian Ghinet Christophe Volat
author_facet	Eric Villeneuve Sebastian Ghinet Christophe Volat
author_sort	Eric Villeneuve
title	Experimental Study of a Piezoelectric De-Icing System Implemented to Rotorcraft Blades
title_short	Experimental Study of a Piezoelectric De-Icing System Implemented to Rotorcraft Blades
title_full	Experimental Study of a Piezoelectric De-Icing System Implemented to Rotorcraft Blades
title_fullStr	Experimental Study of a Piezoelectric De-Icing System Implemented to Rotorcraft Blades
title_full_unstemmed	Experimental Study of a Piezoelectric De-Icing System Implemented to Rotorcraft Blades
title_sort	experimental study of a piezoelectric de-icing system implemented to rotorcraft blades
publisher	MDPI AG
publishDate	2021
url	https://doaj.org/article/5e8591c7d627406796d9b344187c0278
work_keys_str_mv	AT ericvilleneuve experimentalstudyofapiezoelectricdeicingsystemimplementedtorotorcraftblades AT sebastianghinet experimentalstudyofapiezoelectricdeicingsystemimplementedtorotorcraftblades AT christophevolat experimentalstudyofapiezoelectricdeicingsystemimplementedtorotorcraftblades
_version_	1718437889775239168

Experimental Study of a Piezoelectric De-Icing System Implemented to Rotorcraft Blades

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