De-icer

• US 4,836,474 A
• Filed: 07/16/1987
• Issued: 06/06/1989
• Est. Priority Date: 07/16/1987
• Status: Expired due to Term

• Current Assignee: Goodrich Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Goodrich Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Putt, James C., Phillips, Ronald W. II, Leffel, Kevin L., Briscoe, James A.
• Primary Examiner(s): Barefoot, Galen
• Application Number:
  US07/074,107
• Time in Patent Office: 691 Days
• Field of Search: 244/134 R, 244/134 A, 244/134 B
• US Class Current: 244/134.00A
• CPC Class Codes: B64D 15/16 by mechanical means

Abstract

A de-icer for de-icing those ice accreting surfaces of a skin formed of a material having a substantially elevated modulus, wherein the de-icer is positioned between a support surface and a surface of the skin obverse to the ice accreting surface and inflated to produce a deformation in the skin sufficient to detach and dislodge accumulations of ice on the ice accreting surface but insufficient to exceed an endurance limit for the material from which the skin is formed. The invention finds use in de-icing aircraft surfaces such as wings, tail surfaces, propellers, rotors such as rotating wings, tail rotors and nose cones.

Claims

1. In an object having a sheet-like skin formed of a material having a modulus of elasticity of at least 40,000 kPa and including an ice accreting surface, a de-icer comprising;

a support surface positioned obversely to the ice accreting surface;

at least one principal inflation tube between the support surface and the skin; and

means for introducing a fluid under pressure into the principal inflation tube at a rate and in a quantity sufficient to slowly inflate in a period of 0.5 to 5 seconds the inflation tube to a desired extent at which a desired deformation occurs to the skin to a degree sufficient to detach ice accumulations thereon and dislodge the ice accumulations into a stream of fluid flowing over the ice accreting surface without exceeding a stress level characterizing an endurance limit associated with the material forming the skin and for subsequently deflating the principal inflation tube.

2. The de-icer of claim 1, further including a plurality of additional inflation tubes positioned between the support surface and the skin and configured for inflation to an extent sufficient to deform the skin immediately thereover to a degree sufficient to detach and dislodge ice accumulations upon the ice accreting surface thereof without exceeding the stress endurance limit for the material from which skin is formed.

3. The de-icer of claim 1, the principal inflation tube being formed from at least one ply of fabric coated on at least one surface with a rubberizing compound and vulcanizingly cured to form the principal inflation tube.

4. The de-icer of claim 3, the principal inflation tube being affixed to the support surface.

5. The de-icer of claim 2, the principal inflation tube being formed from at least one ply of fabric coated on at least one surface with a rubberizing compound and vulcanizingly cured to form the principal inflation tube.

6. The de-icer of claim 2, the principal inflation tube and additional inflation tubes being affixed to the support surface.

7. The de-icer of any one of claims 2, 5, or 6 further including an intermediate ply positioned intermediate the skin and the support surface to lie between the principal inflation tube and the skin, the additional inflation tubes being attached to the intermediate layer and configured to lie between the intermediate layer and the skin.

8. The de-icer of claim 7, including means for inflating the principal inflation tube in a cyclical manner.

9. In an aerofoil having an outer skin formed of a material having a modulus of elasticity of at least 40,000 kPa, the aerofoil having a leading edge and trailing surfaces therefrom defined by the skin, the skin having a surface upon which ice accretes and an obverse surface, a de-icer comprising;

a rigid support surface positioned in spaced relationship away from the obverse surface of the skin;

at least one principal inflation tube positioned between the obverse surface of the skin and the support surface and affixed to the support surface;

means for slowly inflating the principal inflation tube in a period of 0.5 to 5 seconds by the introduction of fluid under pressure thereinto to a desired extent sufficient to cause deformation of the skin to a degree sufficient to detach and dislodge ice accretions thereon into a stream of fluid flowing over the aerofoil, but not to a degree exceeding a stress level characterizing an endurance limit for the material from which the skin is formed.

10. The de-icer of claim 9, including a plurality of additional inflation tubes positioned between the obverse surface of the skin and the support surface and further including a means for inflating the additional inflatable tubes to an extent sufficient to deform portions of the skin thereover to a degree sufficient to detach and dislodge ice accumulations thereon into a fluid stream flowing over the aerofoil but insufficient to exceed the endurance limit for the material from which the skin is formed.

11. The de-icer of claim 9, further including an intermediate member positioned between the skin and the support surface and encapsulating by partition the principal inflation tube between the intermediate member and the support surface, the additional inflation tubes being affixed to the intermediate member and positioned between the intermediate member and the skin.

12. The de-icer of any one of claims 9-11, the principal inflation tube and any additional inflation tubes being formed from a fabric coated on at least one surface thereof with a rubberizing compound and formed and vulcanizably cured to define a tube.

13. The de-icer of claim 12, the tubes including a partitioning means configured to divide at least the principal inflation tube into at least a pair of tubular compartments, the means being configured to define the tubular compartments in a spaced apart relationship sufficient whereby, upon inflation of the tubular structures, bending stress in the skin induced by the inflation of parallel, spaced apart tubes does not exceed a bending microstrain in the material forming the skin characterizing a service life for the skin and capable of accommodating at least a million cycles of inflation/deflation of the tubular structures.

14. The de-icer of claim 12, the skin being formed from one of titanium, aluminum, steel, including stainless steel, a plastic, and a polymeric composite.

15. The device of claim 13, the partitioning means being one of stitching and adhesive.

16. A method for de-icing an object having a shell-like skin including an ice accreting surface, the skin being possessed of a modulus of elasticity of at least 40,000 kPa, comprising the steps of:

employing a fluid under pressure periodically slowly inflating in a period of 0.5 to 5 seconds at least one principal inflatable tubular structure in a cavity between the skin and a support surface to a pressure sufficient to detach and dislodge accreted ice but insufficiently elevated whereby stresses placed upon the skin do not exceed an endurance limit for the material from which the skin is formed.

17. In the method of claim 16, the step of inflating a pair of principal inflatable tubular structure spaced apart one from the next to an extent sufficient to assure that, upon inflation, bending distortion of the skin by reason of inflation does not exceed a micro strain characterizing a substantial likelihood of fatigue failure of the skin within a million inflation/deflation cycles of the tubes.

18. The method of claim 16, including the step of inflating between the skin and the support surface a plurality of additional tubes to produce a distortion of the skin sufficient to detach and dislodge accumulations of ice thereon.

19. The method of claim 17, including the step of inflating between the skin and the support surface a plurality of additional inflatable tubes to produce a distortion of the skin sufficient to detach and dislodge accumulations of ice thereon.

20. A method for de-icing an airfoil having a leading edge defined by a skin having an outer, ice accreting surface, the skin being formed from a material having a modulus of elasticity of at 40,000 kPa comprising the steps of:

slowly inflating in 0.5 to 5 seconds, employing a fluid under pressure, a tube configured to lie generally spanwise with respect to the leading edge and positioned between a support for the tube and the skin, to a pressure sufficient to deform the skin to an extent effecting a detachment and dislodgment of ice accumulations on the ice accreting surface into an airstream flowing over the airfoil.

21. The method of claim 20 including the step of:

inflating a plurality of additional inflation tubes positioned between the support and skin to a pressure sufficient to effect a distortion in the skin sufficient to detach and dislodge ice accumulations upon the ice accreting surface.

22. A method for de-icing an airfoil having a leading edge associated therewith, the airfoil including a skin having an ice accreting surface formed of a material having a modulus of elasticity of at least 40,000 kPa, comprising the steps of employing a fluid under pressure slowly inflating in 0.5 to 5 seconds an inflatable tube positioned between the skin and a support surface and extending spanwise along the leading edge;

subsequently inflating employing the fluid under pressure utilized in inflating the spanwise inflation tube, a plurality of additional inflation tubes positioned in one of a chordwise and spanwise relationship to the leading edge and positioned between the support surface and the skin;

the inflation tube and the additional inflation tubes being inflated to an extent sufficient to produce a desired deformation in the skin sufficient to detach and dislodge ice accumulations on the ice accreting surface thereof into an airstream flowing over the airfoil but to an extent insufficient to exceed a stress level associated with an endurance limit for the material forming the skin.

23. In an object having a sheet-like skin formed of a material having a modulus elasticity of at least 40,000 kPa and including an ice accreting surface, a de-icer comprising;

a support surface positioned obversely to the ice accreting surface;

at least one principal inflation tube between the support surface and the skin; and

means for introducing a fluid under pressure in a rapid series of pulses into the principal inflation tube in a quantity sufficient to inflate the inflation tube to a desired extent at which a desired deformation occurs to the skin to a degree sufficient to detach ice accumulations thereon and dislodge the ice accumulations into a stream of fluid flowing over the ice accreting surface without exceeding a stress level characterizing an endurance limit associated with the material forming the skin and for subsequently deflating the principal inflation tube.

24. The de-icer of claim 23, further including a plurality of additional inflation tubes positioned between the support surface and the skin and configured for inflation to an extent sufficient to deform the skin immediately thereover to a degree sufficient to detach and dislodge ice accumulations upon the ice accreting surface thereof without exceeding the stress endurance limit for the material from which the skin is formed.

25. In an aerofoil having an outer skin formed of a material having a modulus of elasticity of at least 40,000 kPa, the aerofoil having a leading edge and trailing surfaces therefrom defined by the skin, the skin having a surface upon which ice accretes and an obverse surface, a de-icer comprising;

a rigid support surface positioned in spaced relationship away from the obverse surface of the skin;

at least one principal inflation tube positioned between the obverse surface of the skin and the support surface and affixed to the support surface;

means for inflating the principal inflation tube by the introduction in a rapid series of pulses of fluid under pressure thereinto to a desired extent sufficient to cause deformation of the skin to a degree sufficient to detach and dislodge ice accretions thereon into a stream of fluid flowing over the aerofoil, but not to a degree exceeding a stress level characterizing an endurance limit for the material from which the skin is formed.

26. The de-icer of claim 25, including a plurality of additional inflation tubes positioned between the obverse surface of the skin and the support surface and further including a means for inflating the additional inflatable tubes to an extent sufficient to deform portions of the skin immediately thereover to a degree sufficient to detach and dislodge ice accumulation thereon into a fluid stream flowing over the aerofoil but insufficient to exceed the endurance limit for the material from which the skin is formed.

27. The de-icer of claim 25, further including an intermediate member positioned between the skin and the support surface and encapsulating by partition the principal inflation tube between the intermediate member and the support surface, the additional inflation tubes being affixed to the intermediate member and positioned between the intermediate member and the skin.

28. The de-icer of claim 26, further including partitioning means configured to divide at least the principal inflation tube into at least a pair of tubular compartments, the means being configured to define the tubular compartments in a spaced apart relationship sufficient whereby, upon inflation of the tubular structures, bending stress in the skin induced by the inflation of parallel, spaced apart tubes does not exceed a bending microstrain in the material forming the skin characterizing a service life for the skin and capable of accommodating at least a million cycles of inflation/deflation of the tubular structures.

29. The de-icer of claims 25, 26 or 27, the skin being formed from one of titanium, aluminum, steel, including stainless steel, a plastic, and a polymeric composite.

30. A method for de-icing an object having a shell-like skin including an ice accreting surface, the skin being possessed of a modulus of elasticity of at least 40,000 kPa, comprising the steps of:

employing a fluid under pressure periodically inflating using a rapid series of pulses at least one principal inflatable tubular structure in a cavity between the skin and a support surface to a pressure sufficient to detach and dislodge accreted ice but insufficiently elevated whereby stresses placed upon the skin do not exceed an endurance limit for the material from which the skin is formed.

31. In the method of claim 30, the step of inflating a plurality of principal inflatable tubular structures spaced apart one from the next to an extent sufficient to assure that, upon inflation, bending distortion of the skin by reason of inflation does not exceed a micro strain characterizing a substantial likelihood of fatigue failure of the skin within a million inflation/deflation cycles of the tubes.

32. The method of any one of claims 30 or 31 including the step of inflating the principal inflatable tubular structure within not more than about 0.10 seconds.

33. A method for de-icing an airfoil having a leading edge defined by a skin having an outer, ice accreting surface, the skin being formed from a material having a modulus of elasticity of at least 40,000 kPa comprising the steps of:

inflating employing a fluid under pressure in a rapid series of pulses, a tube configured to lie generally spanwise with respect to the leading edge and positioned between a support for the tube and the skin, to a pressure sufficient to deform the skin to an extent effecting a detachment and a dislodgment of ice accumulations on the ice accreting surface into an airstream flowing over the airfoil.

34. The method of claim 33 including the step of:

inflating a plurality of additional inflation tubes positioned between the support and skin to a pressure sufficient to effect a distortion in the skin sufficient to detach and dislodge ice accumulations upon the ice accreting surface.

35. The method of claim 33, including the step of inflating the spanwise tube in not more than 0.10 seconds.

36. The method of claim 33 including the step of inflating the spanwise inflation tube in a rapid series of pulses producing a series of near instantaneous distortions of the skin overlying the spanwise inflation tube.