Aerodynamic Profile for Aircraft and Wind Power Stations and Method of Measuring the Thickness of Ice on an Aerodynamic Profile

• US 20090189020A1
• Filed: 02/26/2007
• Published: 07/30/2009
• Est. Priority Date: 02/27/2006
• Status: Active Grant

• Current Assignee: Airbus Operations GmbH (Airbus SE)
• Original Assignee: EADS Deutschland GmbH (Airbus SE)
• Inventors: Bilgram, Rudolf, Friedberger, Alois, Gradolph, Christian, Kloeppel, Valentin
• Granted Patent: US 8,434,365 B2
• Time in Patent Office: Days
• US Class Current: 244/134.F
• CPC Class Codes: B64D 15/20 Means for detecting icing or initiating de-icing
• CPC Class Codes: F03D 80/40 Ice detection; De-icing means
• CPC Class Codes: G01B 17/025 for measuring thickness of coating
• CPC Class Codes: Y02E 10/72 Wind turbines with rotation axis in wind direction

Abstract

An aerodynamically shaped profile member for aircraft and wind power stations includes, for example, phased-array ultrasonic generator arrangement is arranged therein. During operation of the profile member, the ultrasonic generator emits ultrasonic waves in a targeted manner in multiple directions to determine a profile of the thickness of an ice layer on the surface of the aerodynamic profile. The structure may be, for example, a composite fiber material arranged around a foam core, with the ultrasonic generator arrangement being laminated into the composite fiber material. For measurement of the ice thickness, ultrasonic waves are transmitted in a targeted manner to different positions of the surface of the aerodynamic profile, and the ultrasonic waves reflected on the interfaces of the ice layer are detected. At least one region of the surface is scanned by means of the targeted ultrasonic waves, to determine an ice thickness profile.

Claims

1-15. -15. (canceled)

16. An aerodynamically shaped profile member for aircraft and wind power stations, said profile member having an ultrasonic generator arrangement arranged in an interior space thereof;

wherein;

during operation, the ultrasonic generator arrangement emits ultrasonic waves in a targeted manner in multiple directions to determine the profile of the thickness of an ice layer on the surface of the aerodynamic profile; and

the ultrasonic generator arrangement comprises a plurality of piezo transducer elements which are arranged underneath an erosion protector of the profile member.

17. The aerodynamically shaped profile member according to claim 16, wherein the ultrasonic generator arrangement performs a scan of the thickness of the ice layer.

18. The aerodynamically shaped profile member according to claim 16, wherein:

the profile member comprises a fiber composite material; and

the ultrasonic generator arrangement is laminated into the fiber composite material.

19. The aerodynamically shaped profile member according to claim 16, wherein:

the profile member comprises a region which is produced of a fiber composite material; and

the ultrasonic generator arrangement is arranged outside the region made of fiber composite material.

20. The aerodynamically shaped profile member according to claim 16, wherein the ultrasonic generator arrangement is a phased-array arrangement.

21. The aerodynamically shaped profile member according to claim 16, wherein the ultrasonic generator arrangement comprises an array of ultrasonic generators.

22. The aerodynamically shaped profile member according to claim 16, wherein the ultrasonic generator arrangement comprises a one-dimensional array that has a series of successively arranged ultrasonic generator elements.

23. The aerodynamically shaped profile member according to claim 16, wherein the ultrasonic generator arrangement comprises an at least two-dimensional array that has a plurality of ultrasonic generator elements.

24. The aerodynamically shaped profile member according to claim 16, wherein the piezo transducer elements are provided in the form of a PVDF foil.

25. The aerodynamically shaped profile member according to claim 16, wherein the profile member is one of a rotor blade for a helicopter or wind power station, and a wing of an airplane.

26. A method of measuring the thickness of ice on an aerodynamic profile, said method comprising:

emitting ultrasonic waves to a surface of the aerodynamic profile;

receiving ultrasonic waves reflected at the interfaces of an ice layer; and

determining the thickness of the ice layer by one of i) analyzing transit times of the reflected ultrasonic waves within the ice layer, and ii) analyzing interferences;

wherein,

the ultrasonic waves are transmitted in a targeted manner to different positions of the surface of the aerodynamic profile; and

at least one region of the surface is scanned by the targeted ultrasonic waves to determine an ice thickness profile.

27. The method according to claim 26, wherein the ice thickness profile is determined based on transit times of the ultrasonic waves reflected at interfaces of the ice layer.

28. The method according to claim 26, wherein the ice thickness profile is determined by analyzing interferences of the ultrasonic waves reflected and superimposed on at least two interfaces of the ice layer.

29. The method according to claim 26, wherein:

a reference measurement is first made in the absence of ice;

a temporal course of the sensor signal is stored; and

during the operation of the aerodynamic profile in the presence of ice, the difference between the two signals is analyzed to minimize the influence of interfering reflections.

30. The method according to claim 26, wherein the wave fronts of the ultrasonic waves impinge substantially perpendicularly on the surface of the aerodynamic profile.