Ice protection system

• US 10,232,949 B2
• Filed: 02/28/2014
• Issued: 03/19/2019
• Est. Priority Date: 02/28/2013
• Status: Active Grant

• Current Assignee: GKN Aerospace Services Limited (Melrose Industries Plc)
• Original Assignee: GKN Aerospace Services Limited (Melrose Industries Plc)
• Inventors: English, Peter, Richards, Thomas Stephen Rowe, Armstrong, David John
• Primary Examiner(s): Bonzell, Philip J
• Assistant Examiner(s): Giczy, Alexander V.
• Application Number:
  US14/770,837
• Publication Number:
  US 20160009400A1
• Time in Patent Office: 1,845 Days
• Field of Search: 7317026, 7317002
• CPC Class Codes: B64D 15/20 Means for detecting icing or initiating de-icing
• CPC Class Codes: B64D 15/22 Automatic initiation by icing detector

Abstract

An ice-protection system has first and second zones of a leading edge of an aerodynamic or streamlined aerodynamic component, each zone having a de-icing apparatus and an ice-detection sensor positioned behind an elongated convex window as to be aero-conformal with the leading edge. The ice-detection sensor is in the form of a module and has a sensor head having a front face and abutments at ends of the window. The ice-detection sensors may have a central light emitter and a plurality of sensor elements peripheral to the light emitter. The ice-protection system also has a control system responsive to the ice-detection sensors to control the respective de-icing apparatus, and may activate automatically a sequence of operation.

Claims

1. An ice-protection system comprising:

first and second zones, wherein each of the zones is a zone of a leading edge of an aerodynamic or streamlined airframe component, each zone including a window;

a first de-icing apparatus operable to de-ice the first zone;

a first ice-detection sensor positioned in the first zone and configured to detect ice accreted on the first zone;

a control system responsive to the first ice-detection sensor and configured to control the operation of the first de-icing apparatus;

a second de-icing apparatus operable to de-ice the second zone; and

a second ice-detection sensor positioned in the second zone and configured to detect ice accreted on the second zone;

wherein the control system is responsive to the second ice-detection sensor and is configured to control the operation of the second de-icing apparatus;

wherein a sensor head of each respective ice-detection sensor is positioned behind the window in each respective zone,

each respective ice-detection sensor is in a form of a sensor module including the respective sensor head,

each window is elongated, having longitudinal ends in a longitudinal direction,

each window is elongated, having longitudinal ends in a longitudinal direction,

each respective sensor head having a front face and a first abutment and a second abutment, each abutment positioned at a respective one of the longitudinal ends of the window and terminating prior to a front face of the window,

each sensor module positioned behind the respective window of the respective zone such that the respective sensor head front face is covered by the respective window, and

the window front face in each respective zone is convex so as to be aero-conformal with an adjacent part of the leading edge of the airframe component.

2. The ice-protection system of claim 1, wherein the airframe component is one of a forward portion of an aerofoil and a wing slat.

3. The ice-protection system of claim 1, wherein the respective sensor head of each ice-detection sensor comprises a central light emitter and a plurality of sensor elements positioned peripherally of the central light emitter.

4. The ice-protection system of claim 3, wherein the sensor head is elongate and has a longitudinal axis which is aligned along or is parallel to a longitudinal axis of a leading edge of the airframe component.

5. The ice-protection system of claim 1, wherein each ice-detection sensor is positioned in a central portion of the respective zone.

6. The ice-protection system of claim 1, wherein:

each of the ice-detection sensors is further configured to detect a rate of accretion of ice and a type of accreted ice, and the control system is configured to store a library of sequences of operation of the de-icing apparatuses and is configured to select a sequence from the library of sequences based on at least one of a thickness of accreted ice, a rate of accretion of ice, and a type of accreted ice-detected on the zones.

7. The ice-protection system of claim 1, wherein:

the control system is configured to do one of select a sequence of operation which starts with the zone with the first detected accretion of ice and select a sequence of operation which starts with the zone with the thickest detected accretion of ice.

8. The ice-protection system of claim 1, wherein:

the control system is configured, when one or more zones have no detected accreted ice or accreted ice which is below a predetermined thickness, to select a sequence of operation which omits said one or more zones or de-ices said one or more zones at the end of the sequence of operation.

9. The ice-protection system of claim 1, wherein each de-icing apparatus comprises an electro-thermal heater mat.

10. The ice-protection system of claim 9, wherein each heater mat has a plurality of independently-operable heater areas each corresponding to a respective sub-zone of the zone of de-icing operation of the heater mat.

11. The ice-protection system of claim 10, wherein each heater area includes a respective ice-detection sensor that is one of the first ice-detection sensor, the second ice-detection sensor, or a third ice detection sensor.

12. The ice-protection system of claim 10, wherein each of the heater areas comprises one or more respective heater elements.

13. The ice-protection system of claim 9, wherein:

each heater mat is elongate in a longitudinal direction and is curved transversely of the longitudinal direction to define a convex forward face of the heater mat and a concave rearward face of the heater mat; and

each heater mat includes one or more sensor apertures each containing a sensor head of an ice-detection sensor that is one of the first ice-detection sensor, the second ice-detection sensor, or a third ice detection sensor and that is associated with the heater mat.

14. The ice-protection system of claim 13, wherein:

the one or more sensor apertures of each heater mat are positioned on a leading edge of the heater mat.

15. The ice-protection system of claim 13, wherein:

the one or more sensor apertures of each heater mat are positioned on trailing portions of the respective heater mat behind a leading edge of the respective heater mat.

16. The ice-protection system of claim 13, wherein:

the one or more sensor apertures of each heater mat are positioned in a row along a leading edge of the respective heater mat and are also positioned above or below the leading edge of the respective heater mat.

17. The ice-protection system of claim 1, wherein:

each ice-detection sensor is configured to detect a thickness of the ice accreted on the respective zone;

the control system is configured, when the detected thickness of the accreted ice on a zone has built up to a predetermined thickness, to operate the respective de-icing apparatus.

18. The ice-protection system of claim 17, wherein:

each ice-detection sensor is also configured to detect a type of ice that is accreted on the respective zone; and

the control system is responsive to the detected ice type to vary the predetermined thickness needed to trigger operation of the respective de-icing apparatus.

19. An aircraft comprising an ice-protection system, the ice protection system comprising:

first and second zones, wherein each of the zones is a zone of a leading edge of an airframe component that is at least one of aerodynamic and streamlined, each zone including a window;

a first de-icing apparatus operable to de-ice the first zone;

a first ice-detection sensor positioned in the first zone and configured to detect ice accreted on the first zone;

a control system responsive to the first ice-detection sensor and configured to control the operation of the first de-icing apparatus;

a second de-icing apparatus operable to de-ice the second zone; and

a second ice-detection sensor positioned in the second zone and configured to detect ice accreted on the second zone;

wherein the control system is responsive to the second ice-detection sensor and is configured to control the operation of the second de-icing apparatus;

wherein a sensor head of each respective ice-detection sensor is positioned behind the window in each respective zone,

each respective ice-detection sensor is in a form of a sensor module including the respective sensor head,

each window is elongated, having longitudinal ends in a longitudinal direction,

each window is elongated, having longitudinal ends in a longitudinal direction,

each respective sensor head having a front face and a first abutment and a second abutment, each abutment positioned at a respective one of the longitudinal ends of the window and terminating prior to a front face of the window,

each sensor module positioned behind the respective window of the respective zone such that the respective sensor head front face is covered by the respective window, and

the window front face in each respective zone is convex so as to be aero-conformal with an adjacent part of the leading edge of the airframe component.

20. The aircraft of claim 19, wherein the control system of the ice-protection system is configured to activate automatically a sequence of operation of the de-icing apparatuses in response to the ice-detection sensors without requiring manual activation.