Piezoelectric deicing device

• US 4,545,553 A
• Filed: 08/07/1984
• Issued: 10/08/1985
• Est. Priority Date: 02/25/1983
• Status: Expired due to Fees

• Current Assignee: United States Administrator of National Aeronautics and Space Administration
• Original Assignee: United States Administrator of National Aeronautics and Space Administration
• Inventors: Banks, Bruce A., Finke, Robert C.
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US06/638,541
• Time in Patent Office: 427 Days
• Field of Search: 244/134 R, 244/134 A, 244/134 D, 244/134 C, 310/324, 310/328, 310/340, 310/800, 114/22 L, 60/39.093, 29/25.35, 134/1, 134/17, 252/62.9, 367/157, 427/100, 428/422
• US Class Current: 244/134.00D
• CPC Class Codes: B64D 15/163 using electro-impulsive devices
• CPC Class Codes: H10N 30/204 using bending displacement, e.g. unimorph, bimorph or multimorph cantilever or membrane benders
• CPC Class Codes: H10N 30/50 having a stacked or multilayer structure
• CPC Class Codes: Y10S 310/80 Piezoelectric polymers, e.g. PVDF
• CPC Class Codes: Y10T 29/42 Piezoelectric device making

Abstract

A fast voltage pulse is applied to a transducer which comprises a composite of multiple layers of alternately polarized piezoelectric material. These layers are bonded together and positioned over the curved leading edge of an aircraft wing structure. Each layer is relatively thin and metallized on both sides. The strain produced in the transducer causes the composite to push forward resulting in detachment and breakup of ice on the leading edge of the aircraft wing.

Claims

1. Apparatus for removing ice from an aircraft wing comprising

a transducer for covering the leading edge of said aircraft wing, said transducer comprising

multiple sheets of alternately polarized piezoelectric polymeric material bonded together to form a composite, each of said sheets being metallized on both surfaces, and

a pair of spaced metallized terminals, one of said terminals being in electrical contact with one of said metallized surfaces of each of said sheets and the other of said terminals being in electrical contact with the other of said metallized surfaces on each of said sheets,

means for restraining oppositely disposed edges of said composite from movement while providing freedom of movement of the central portion thereof,

a direct current electrical power supply,

means for selectively connecting said electrical power supply to said spaced terminals for applying a fast voltage pulse thereto so that a positive electrical charge is placed on said one of said terminals and a negative electrical charge is placed on said other of said terminals thereby producing a sheet lengthening piezoelectric strain in said sheets to cause the unrestrained central portion of said composite to move forward away from said aircraft wing so long as said fast voltage pulse is maintained, and

a cover of a polymeric material bonded to said composite for protecting the exposed surface thereof from particle damage.

2. Apparatus for removing ice from an aircraft wing as claimed in claim 1 wherein said sheets have thicknesses between about 0.003 inch and about 0.010 inch.

3. Apparatus for removing ice from an aircraft wing as claimed in claim 1 wherein said polymeric material comprises polyvinylidene fluoride.