A method for forming an aircraft component includes forming an inner portion of the aircraft component. The method further includes forming an outer layer of the aircraft component using extrusion of an elastomeric material. The method further includes coupling the outer layer of the aircraft component to the inner portion of the aircraft component.

Ice may form along the leading edge of an aircraft wing or horizontal and vertical stabilizers. A pneumatic deicer system may be configured to inflate and dislodge ice along the leading edge of lift and control surfaces. The pneumatic deicer system may comprise a laser welded deicing boot attached to the leading edge. The compressed air can be directed to the deicing boot, inflating the deicing boot along inflatable tubes formed by laser welds, which can crack and dislodge the ice. A method of manufacturing a laser welded pneumatic deicer boot is also disclosed.

A blade for a rotor of a hover-capable aircraft is described comprising: a main body with a first outer surface; and a de-icing system for removing ice; the de-icing system, in turn, comprises: a first layer formed by a shape-memory material activatable so as to alter its shape according to a temperature-associable quantity, which is arranged on at least one outer surface of the main body; the de-icing system is characterized in that it comprises a second covering layer, which defines at least a portion of a second outer surface of the blade on which ice deposits; the second layer laid on top of the first layer on the opposite side of the main body is selectively movable under the action of the first layer so as to exert a mechanical action on the ice and remove it from the blade, and is adapted to protect the first layer from external agents.

A flow body for an aircraft with an integrated de-icing system. The flow body includes a front skin, an internal structural component, a lever having first and second ends, with an attachment point in-between, and an actuator. The actuator is spaced inside the front skin. The lever extends from the actuator to a front skin inner surface, the first end coupling with the front skin, and the second end coupling with the actuator. The attachment point is swivably supported on the internal structural component. The attachment joint is closer to the first end than the second end. The lever and the actuator apply an impulsive force in a transverse direction to the lever, such that the lever rotates around the attachment point, and such the first end urges the front skin to locally elastically deform for removing ice accretion from an outer side of the front skin.

The nacelle can have an inlet portion having a duct wall and an outer skin, the duct wall being annular around an axis and having a surface forming a radially-outer delimitation to a gas path upstream of a fan area, the duct wall extending from a rounded inlet edge of the nacelle to the fan area, a cavity located inside the inlet portion, a compressed air inlet leading into the cavity, and an outlet fluidly connecting the cavity to the gas path, the outlet having a plurality of apertures disposed circumferentially around the duct wall, the apertures sloping circumferentially.

A de-icing element having a skin with a surface to be de-iced, at least one excitation actuator attached to the skin, the excitation actuator configured to excite the skin according to at least one predetermined vibration mode generating a deformation of the skin, the deformation of the skin comprising at least one antinode and one node. The skin having a characteristic thickness generally constant with, locally, at least one thickness variation that is localized according to the predetermined vibration mode or modes.

A de-icing element having a skin with a surface to be de-iced, at least one excitation actuator attached to the skin, the excitation actuator configured to excite the skin according to at least one predetermined vibration mode generating a deformation of the skin, the deformation of the skin comprising at least one antinode and one node. The skin having a characteristic thickness generally constant with, locally, at least one thickness variation that is localized according to the predetermined vibration mode or modes.

An anti-icing system may comprise a deicing boot of an elastomeric material comprising a plurality of tubes, wherein the deicing boot comprises a first set of tubes and a second set of tubes, wherein each of the first set of tubes and the second set of tubes have a corresponding end, and wherein the corresponding end is coupled to a continuous dual wrap end closure.

A method for forming an aircraft component includes forming an inner portion of the aircraft component. The method further includes forming an outer layer of the aircraft component using extrusion of an elastomeric material. The method further includes coupling the outer layer of the aircraft component to the inner portion of the aircraft component.

A de-icer is provided and includes first and second structural layers that each include centerline and a non-inflatable edge angled with respect to the centerline, edge sealing material disposed to adhere the first and second structural layers together to form a non-inflatable edge area extending along at least the non-inflatable edge and surrounding a central area and stitching. The stitching is disposed to stitch the first and second structural layers together in the central area to form tubes. The tubes include an outermost tube which is closest to and parallel with the non-inflatable edge.