Aircraft icing detection system

• US 5,301,905 A
• Filed: 12/23/1992
• Issued: 04/12/1994
• Est. Priority Date: 12/23/1992
• Status: Expired due to Fees

• Current Assignee: David A. Blaha
• Original Assignee: David A. Blaha
• Inventors: Blaha, David A.
• Primary Examiner(s): Huppert, Michael S.
• Assistant Examiner(s): MARQUIS, LISSI MOJICA
• Application Number:
  US07/995,446
• Time in Patent Office: 475 Days
• Field of Search: 244/134 R, 244/134 F, 244/134 D, 340/580, 340/582, 73/178 R, 60/39.093
• US Class Current: 244/134.00F
• CPC Class Codes: B64D 15/20 Means for detecting icing or initiating de-icing

Abstract

An aircraft icing detection system detects accumulation of ice on an upper surface (12) of a wing (10) of an aircraft. The system includes an air pump (18) that delivers air through first and second conduits (24, 26). The first conduit delivers air through a first air knife (32) to openings (34) in the upper surface of the wing. The second conduit delivers air through a lower wing surface (14) through openings in a second air knife (42). When ice accumulates on the upper surface, flow from the first air knife is restricted. A differential pressure sensor (46) senses a pressure difference between the conduits and warns the pilot of possible ice accumulation by illuminating a warning light (50).

Claims

1. A system for detecting accumulation of ice on a surface of an aircraft, comprising:

air pump means for pumping air;

a first generally horizontal extending exterior surface of an aircraft, said first surface being on an upper side of said aircraft and exposed to precipitation falling from above;

at least one first opening in said first horizontally extending surface;

a second surface of said aircraft, said second surface not exposed to precipitation;

at least one second opening in said second surface;

first conducting means for conducting air from said air pump means to said first opening;

second conducting means for conducting air from said air pump means to said second opening;

differential pressure sensing means for sensing a difference in pressure between said first and second conducting means; and

indicating means in connection with said sensing means for indicting said pressure difference to an operator of said aircraft.

3. The system according to claim 1 wherein said first surface is an upper surface of a wing and said second surface is a lower surface of the wing.

4. The system according to claim 3 and further comprising a first air knife adjacent said first opening and in fluid communication with said first conducting means;

and a second air knife adjacent said second opening and in fluid communication with said second conducting means.

5. The system according to claim 4 wherein said first opening includes a plurality of adjacent first holes.

6. The system according to claim 5 wherein said second opening includes a plurality of adjacent second holes.

7. The system according to claim 6 and further comprising a recess in said upper surface of said wing, said first holes extending in said recess.

8. The system according to claim 7 wherein said indicating means includes warning means for providing a warning when said pressure in said first conducting means exceeds pressure in said second conducting means by an amount.

9. The system according to claim 8 and further comprising first valve means in said first conducting means for regulating flow therethrough;

and second valve means in said second conducting means for regulating flow therethrough; and

wherein said first and second valve means are set to minimize differential pressure sensed by said differential pressure sensing means when said first holes and said second holes are unobstructed.

10. The system according to claim 9 wherein said differential pressure sensing means is adapted to indicate the alarm at a differential pressure generally above 0.001 psi.

11. The system according to claim 10 wherein said first holes comprise 16 first holes generally one millimeter in diameter, said first holes aligned linearly along a first axis, said first axis parallel of a longitudinal axis of said wing;

said second holes comprise 16 second holes generally one millimeter in diameter, said second holes aligned linearly along a second axis, said second axis parallel of said longitudinal axis; and

said air pump means delivers air at generally 2,000 cubic centimeters per minute at 0.02 psig.

2. A system for detecting accumulation of ice on an aircraft, comprising:

an air pump;

a first generally horizontally extending exterior surface of an aircraft, said first surface being on an upper side of said aircraft and exposed to precipitation falling from above;

at least one first opening in said first horizontally extending surface;

a second surface of said aircraft, said second surface not exposed to precipitation;

at least one opening in said second surface;

a first conduit in fluid communication with said air pump and said first opening;

a second conduit in fluid communication with said air pump and said second opening;

a differential pressure sensor in fluid communication with said first and second fluid conduits;

an operator indicator in connection with said differential pressure sensor, whereby a differential pressure is indicated to an operator of said aircraft.

12. A method for detecting accumulation of ice on a surface of an aircraft, comprising the steps of:

pumping air with pumping means;

conducting air from said pumping means in first conducting means;

passing air from said first conducting means to atmosphere through at least one first opening, said first opening in a first generally horizontally extending exterior surface of an aircraft, said first surface on an upper side of said exterior surface and exposed to precipitation falling from above;

conducting air from said pumping means in second conducting means;

passing air from said second conducting means to atmosphere through at least one second opening;

said second opening in a second surface of said aircraft not exposed to precipitation falling from above;

sensing pressure differential between said first and second conducting means with pressure sensing means; and

indicating to an operator of said aircraft when said pressure differential sensed by said sensing means exceeds an amount.

13. The method according to claim 12 wherein said method further comprises the step of indicating a warning when said differential pressure exceeds an amount.

14. The method according to claim 13 and further comprising the steps of:

controlling flow through said first conducting means with first valve means; and

controlling flow through said second conducting means with second valve means, wherein there is generally no pressure differential between said first and second conducting means when said first openings are unobstructed by ice.

15. The method according to claim 14 wherein said flow through said first openings is of sufficient velocity to displace rain droplets and dry snow therefrom.