A de-icing system for an airfoil includes a flexible skin having one or more stiffening elements embedded therein and one or more actuators positioned within the airfoil and configured to engage an impact area of the flexible skin with a displacement force. The stiffening elements extend substantially parallel to the leading edge of an airfoil and are placed in a chordwise succession proceeding away from the leading edge of the airfoil. The one or more stiffening elements are configured to transmit the displacement force to a non-impact area of the flexible skin adjacent to or near the one or more stiffening elements. The displacement force causes an outer surface of the flexible skin adjacent to the impact area to be distorted and an outer surface of the flexible skin of the non-impact area to be distorted.
Mechanical De-Icing System
2024-06-20
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
Aircraft Icing and Thermo-Mechanical Explusion De-Icing
British Library Conference Proceedings | 2012
|European Patent Office | 2021
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