Method for de-icing an aerodynamic wall using at least two different de-icing systems, aircraft equipped with a de-icing device making it possible to implement said method
AssigneeAirbus Operations GmbH
InventorFlorent Crebassol
Life of this patent
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Abstract
A method for de-icing an aerodynamic wall of an aircraft, the method comprising activation of a thermal de-icing system configured to generate at least a localized heating on the outer face of the aerodynamic wall and activation of another de-icing system by elastic deformation configured to deform the aerodynamic wall. Also an aircraft equipped with a de-icing device.
Claims14
A method for de-icing an aerodynamic wall of an aircraft, said aerodynamic wall having an outer face against which an air stream flows in a longitudinal direction and an inner face opposite the outer face, wherein the method comprises:
- providing at least one first de-icing system configured to be in an activated state in which the at least one first de-icing system generates at least one elastic deformation of the aerodynamic wall and at least one second de-icing system, different from the at least one first de-icing system, configured to be in an activated state in which the at least one second de-icing system generates at least a localized heating on the outer face of the aerodynamic wall;
- activating the at least one second de-icing system;
- and,
- activating the at least one first de-icing system,
- wherein the at least one first de-icing system is positioned between and spaced from slender heating elements of the at least one second de-icing system such that the at least one second de-icing system completely surrounds the at least one first de-icing system,
- wherein activating the at least one second de-icing system embrittles a cluster of ice adhered to said aerodynamic wall in line with the slender heating elements and the cluster of ice comprises zones of reduced thickness in line with the slender heating elements.
An aircraft comprising:
- an aerodynamic wall and
- a de-icing device for treating said aerodynamic wall,
- the aerodynamic wall having an outer face against which an air stream flows in a longitudinal direction and an inner face opposite the outer face, the de-icing device comprising at least one first de-icing system configured to generate at least one elastic deformation of said aerodynamic wall, wherein the de-icing device further comprises at least one second de-icing system, different from the at least one first de-icing system, configured to generate a localized heating on the outer face of the aerodynamic wall,
- wherein the at least one first de-icing system is positioned between and spaced from slender heating elements of the at least one second de-icing system such that the at least one second de-icing system completely surrounds the at least one first de-icing system,
- wherein activating the at least one second de-icing system embrittles a cluster of ice adhered to said aerodynamic wall in line with the slender heating elements and the cluster of ice comprises zones of reduced thickness in line with the slender heating elements.
Dependencies are inferred from the claim text.