De-icing systems and methods
AssigneeIntertechnique
InventorJULIEN DELRIEU
Life of this patent
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Abstract
An de-icing system comprising a shield that is configured to deform in a pre-determined way that de-bonds accreted ice. In some embodiments, the shield has a variable (non-uniform) stiffness across its width and/or length such that it undergoes a twist-like or other suitable deformation when subjected to a force. In some embodiments, the system includes a plurality of electro-mechanical actuators configured to generate the force applied to the shield.
Claims23
An aircraft de-icing system comprising:
- a shield having an inner surface and an outer surface;
- one or more actuators positioned adjacent the inner surface of the shield, wherein each of the one or more actuators is configured to generate an actuator force against the inner surface of the shield;
- and
- a plurality of stiffeners and a plurality of reduced thickness areas along a width of the shield that create a variable thickness across the width of the shield such that the shield undergoes a twist-like deformation when subjected to the actuator forces.
A system for de-icing a wing comprising:
- a shield having an inner surface and an outer surface and having a stiffness that varies along a width of the shield;
- and
- a plurality of actuators each configured to apply a force to the shield,
- wherein the variable stiffness of the shield causes a twist-like deformation along the shield when the shield is subjected to the forces.
A method comprising:
- providing a shield, wherein the shield has a variable stiffness along its width such that the shield deforms in a twist-like fashion when a force is applied to the shield.
The method of 14, wherein the step of providing the shield further comprises providing a shield that has a variable stiffness along its width.
A system for de-icing a wing comprising:
- a shield formed of a fiber composite material, wherein the shield has an outer surface and an inner surface and wherein a stiffness of the shield varies along a width of the shield;
- and
- a plurality of actuators each configured to apply a force to the shield, wherein an arrangement of the fiber composites a layers causes a twist-like deformation along the width of the shield when the shield is subjected to the forces.
A system for de-icing a wing comprising:
- a laminate shield formed of a composite material and having a stiffness that varies along a width of the shield;
- and
- a plurality of actuators each configured to apply a force to the shield,
- wherein layers of the shield cause a twist-like deformation along the width of the shield when the shield is subjected to the forces.
Dependencies are inferred from the claim text.