| 摘要 |
Embodiments of the present disclosure relate generally to systems and methods for de-icing an aircraft surface (14). The systems create a shock pulse to create a shock activation. The shock pressure is designed to deform the surface of an erosion shield (16) on the surface in order to expulse ice from the wing. The deformation may be between a negative to a positive shape. In one example, the de-icing occurs from a pulse delivered by pressurized fluid injected into and quickly removed from a recess (12) between the aircraft surface and an erosion shield. A pulse of pressurized air or fluid may be injected into one or more cells (32) formed in the recess, together or alternately, according to the desired effect on the erosion shield surface. |
