Feasibility Study of Ultrasonic De-Icing Technique for Aircraft Wing Ice Protection
- 10.2991/aviaent-19.2019.15How to use a DOI?
- aircraft wing de-icing; ultrasonic de-icing; ice protection system; piezoelectric transducer
Flight in icing conditions brings significant safety risks due to aircraft aerodynamic performance reduction, stability and controllability deterioration, failures, mechanical damages. For reliable operation in icing conditions active anti-icing/de-icing systems are needed, which entail at the present time considerable on-board power consumption, additional weight, installation or maintenance difficulties and other drawbacks. Moreover, a lot of incidents still appear due to in-flight icing. Nowadays, it is a high demand for efficient and reliable de-icing techniques. Recent studies presented hybrid and non-thermal in-flight ice protection methods with potentials to be more advantageous, including ultrasonic de-icing technique. In this paper, the feasibility study with semi-hard lead zirconate titanate (PZT) ultrasonic Langevin-type transducer was carried out. The theoretical model explaining ice detaching mechanism with applied ultrasonic guided wave propagation theory was described. The verifying experiment was conducted to prove feasibility of de-icing. Prospects for further research were given.
- © 2019, the Authors. Published by Atlantis Press.
- Open Access
- This is an open access article distributed under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/).
Cite this article
TY - CONF AU - Vladislav Daniliuk AU - Evgeny Pamfilov AU - Aleksey Daniliuk AU - Yuanming Xu PY - 2019/11 DA - 2019/11 TI - Feasibility Study of Ultrasonic De-Icing Technique for Aircraft Wing Ice Protection BT - Proceedings of the International Conference on Aviamechanical Engineering and Transport (AviaENT 2019) PB - Atlantis Press SP - 77 EP - 82 SN - 2352-5401 UR - https://doi.org/10.2991/aviaent-19.2019.15 DO - 10.2991/aviaent-19.2019.15 ID - Daniliuk2019/11 ER -