Patent ID: 7673832

Claim:
An aircraft component being exposed to streaming surrounding air, comprising an inner wall; an outer wall, the outer wall being displaced a distance from the inner wall, the distance defining a space between the inner wall and the outer wall; a plurality of partition walls being inserted within the space between the inner wall and the outer wall, the plurality of partition walls are formed by an integral sheet with trapezoidal corrugations having a plurality of base areas, the base areas alternately in contact with the outer wall and the inner wall and having openings in fluid communication with a plurality of perforations through the outer wall such that a plurality of sections form a plurality of pressure channels, each adjacent to a respective one of a plurality of suction channels, the plurality of sections extending from the inner wall to the outer wall, such that: the plurality of suction channels are adapted for sucking surrounding air from a plurality of first regions of the outer wall; the plurality of pressure channels are adapted for feeding hot pressurized air to a plurality of second regions of the outer wall; the plurality of first regions of the outer wall have a significantly larger area than the plurality of second regions of the outer wall; and a control device controllably coupling the plurality of pressure channels to a hot air reservoir and the plurality of suction channels to a vacuum reservoir.