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US 9,067,685 B2Granted
De-icing systems and methods
AssigneeZodiac Aerotechnics
InventorJulien Delrieu
Life of this patent
Estimating the term…
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.
Claims21
An aircraft de-icing system comprising:
- a shield having an inner surface and an outer surface,
- wherein the shield is fixed to an aircraft wing or slat structure at a plurality of fixation points;
- one or more actuators positioned adjacent the inner surface of the shield and spaced apart from each of the plurality of fixation points,
- 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 arranged along a width of the shield
- so that a thickness between the inner surface and the outer surface of the shield varies across the width of the shield
- and causes the shield to undergo a non-uniform flexion when subjected to the actuator forces,
- wherein a stiffness of the shield is greater at a portion of the shield having one of the plurality of stiffeners than at one of the plurality of reduced thickness areas,
- and wherein a location of each of the plurality of reduced thickness areas along the width of the shield generally aligns with a location of one of the plurality of fixation points.
6 more elements
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 due to a plurality of high stiffness areas and a plurality of low stiffness areas;
- a plurality of fixation points that fix the inner surface of the shield to the wing or a slat structure;
- and a plurality of actuators spaced apart from each of the plurality of fixation points and each configured to apply a force to the shield,
- wherein the variable stiffness of the shield causes non-uniform deformation along the shield when the shield is subjected to the forces,
- and wherein a location of each of the plurality of low stiffness areas along the width of the shield generally aligns with a location of one of the plurality of fixation points.
2 more elements
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;
- a plurality of fixation points at which an inner surface of the shield is coupled with the wing or a slat structure;
- a plurality of actuators spaced apart from each of the plurality of fixation points and each configured to apply a force to the shield;
- a plurality of high stiffness areas and a plurality of low stiffness areas;
- wherein each of the plurality of low stiffness areas aligns generally along the width of the shield with one of the plurality of fixation points to cause a non-uniform deformation along the width of the shield when the shield is subjected to the forces.
3 more elements
A system for de-icing a wing comprising:
- a laminate shield formed of a composite material comprising layers,
- wherein the layers are configured such that the shield includes a plurality of high stiffness areas and a plurality of low stiffness areas to vary a stiffness of the shield along a width and a length of the shield;
- a plurality of fixation points at which an inner surface of the laminate shield is coupled with the wing or a slat structure;
- and a plurality of actuators separated from each of the plurality of fixation points and each configured to apply a force to the shield,
- wherein each of the plurality of low stiffness areas is positioned to align generally with one of the plurality of fixation points,
- and wherein the configuration of the layers of the shield causes a non-uniform deformation along the width and the length of the shield when the shield is subjected to the forces.
3 more elements
Dependencies are inferred from the claim text.