HEATED LEADING EDGE STRUCTURE FOR AN AIRCRAFT

Abstract

A heated leading edge structure for an aircraft, including a leading edge panel having an outer surface configured to be contacted by an ambient flow, and an inner surface opposite the outer surface, and including a heater device mounted to the inner surface of the leading edge panel for heating of the leading edge panel. The heater device is mounted to the inner surface of the leading edge panel in a detachable manner to provide a simple, lightweight and cost-efficient leading edge structure that enables a simple, quick and efficient maintenance.

Claims

1. A heated leading edge structure for an aircraft, comprising a leading edge panel having an outer surface configured to be contacted by an ambient flow, and an inner surface opposite the outer surface, and a heater device mounted to the inner surface of the leading edge panel for heating of the leading edge panel, wherein the heater device is detachably mounted to the inner surface of the leading edge panel.

2. The leading edge structure according to claim 1, wherein the heater device is formed as a heater mat.

3. The leading edge structure according to claim 1, wherein the heater device is mounted to the inner surface of the leading edge panel by a fastener arrangement comprising at least one discrete releasable fastener.

4. The leading edge structure according to claim 3, wherein the at least one discrete releasable fastener comprises a plurality of discrete releasable fasteners spaced from one another along the inner surface of the leading edge panel.

5. The leading edge structure according to claim 3, wherein the at least one fastener is attached to the inner surface of the leading edge panel and engages the heater device.

6. The leading edge structure according to claim 5, wherein the at least one fastener is formed as a snap connector that can be engaged to and disengaged from the heater device by elastic deformation of the fastener or the heater device.

7. The leading edge structure according to claim 5, wherein the at least one fastener comprises a pin extending away from the inner surface of the leading edge panel and engaging a hole in the heater device.

8. The leading edge structure according to claim 7, wherein the hole is formed as a through hole, wherein the pin is provided with a retainer device at its free end, and wherein, in an engaged state, the pin extends through the hole such that its free end with the retainer device projects out of the hole and the retainer device secures the pin in the hole.

9. The leading edge structure according to claim 8, wherein the retainer device comprises an extended-diameter head formed at the free end of the pin.

10. The leading edge structure according to claim 9, wherein the retainer device further comprises a removable retainer element arrangeable around the pin between the heater device and the head.

11. The leading edge structure according to claim 7, wherein the at least one fastener comprises a base member attached to the inner surface of the leading edge panel by adhesive and holding the pin.

12. The leading edge structure according to claim 1, wherein the heater device is additionally attached to the inner surface of the leading edge panel by an adhesive layer.

13. The leading edge structure according to claim 1, further comprising a lower panel opposite from the leading edge panel and from the heater device attached thereto, wherein the lower panel has an access opening closed by a removable cover for access to an inside of the leading edge structure.

14. A slat for a wing of an aircraft, comprising the leading edge structure according to claim 1.

15. A wing for an aircraft, comprising the leading edge structure according to claim 1.

16. A wing for an aircraft, comprising the slat according to claim 14.

17. An aircraft comprising a leading edge structure according to claim 1.

18. An aircraft comprising a slat according to claim 14.

19. An aircraft comprising a wing according to claim 15.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Hereinafter, preferred embodiments of the present invention are described in more detail by means of a drawing.

[0023] FIG. 1 shows a perspective view of an aircraft according to the invention,

[0024] FIG. 2 shows a schematic cross sectional view of a leading edge structure according to a first embodiment of the invention as part of a slat,

[0025] FIG. 3 shows a detailed cross sectional view of a fastener of the leading edge structure shown in FIG. 2,

[0026] FIG. 4 shows a perspective, isolated view of the heater device from FIG. 2 with a view of the inner side, and

[0027] FIG. 5 shows a schematic cross sectional view of a leading edge structure according to a second embodiment of the invention with an access opening in the lower panel.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0028] In FIG. 1 an aircraft 1 according to an embodiment of the invention is illustrated. The aircraft 1 comprises a fuselage 3, wings 9, a vertical tail plane 5 and a horizontal tail plane 7. The wing 9 comprises a main wing 11 and a slat 13 mounted to the main wing 11 movably between a retracted position and an extended position. The slat 13 is shown in FIG. 2 in an isolated form and comprises a leading edge structure 15 according to the invention.

[0029] The leading edge structure 15 comprises a leading edge panel 17 and a heater device 19. The leading edge panel 17 extends along a span direction 21 and in a chord direction 23 extends in a way curved about the span direction 21 and including a leading edge point 25. The leading edge panel 17 has an outer surface 27 configured for contact with an ambient flow 28, and an inner surface 29 opposite the outer surface 27 and facing an inside 30 of the leading edge structure 15. The leading edge panel 17 is made of a metal material, in the present embodiment of aluminum, steel or titanium. The heater device 19, in the present embodiment in the form of an electrothermal heater mat, is mounted to the inner surface 29 of the leading edge panel 17 in a way that it covers the inner surface 29 for controlled heating of the leading edge panel 17 to protect the leading edge panel 17 from icing. The heater device 19 is mounted to the inner surface 29 of the leading edge panel 17 in a detachable and replaceable manner by a non-destructively detachable connection.

[0030] The heater device 19 is mounted to the inner surface 29 of the leading edge panel 17 by a fastener arrangement 31 comprising a plurality of discrete releasable fasteners 33 spaced from one another along the inner surface 29 of the leading edge panel 17, as shown in FIGS. 2 and 4. An exemplary fastener 33 is shown in detail in FIG. 3.

[0031] As visible in FIG. 3, the fastener 33 is attached by adhesive to the inner surface 29 of the leading edge panel 17 and engages the heater device 19. The fastener 33 comprises a pin 35 extending away from the inner surface 29 of the leading edge panel 17 and engaging a hole 37 in the heater device 19. The hole 37 is formed as a through hole extending through the heater device 19 from an outer side 39 facing the inner surface 29 of the leading edge panel 17 to an opposite inner side 41. The pin 35 is provided with a retainer device 43 at its free end 44 for retaining and securing the pin 35 in the hole 37. The retainer device 43 comprises an extended-diameter head 45 formed at the free end 44 of the pin. The head 45 is formed integrally with the pin 35. In the engaged state the pin 35 extends through the hole 37 such that its free end 44 with the retainer device 43 projects out of the hole 37 at the inner side 41 of the heater device 19, and the retainer device 43 secures the pin 35 in the hole 37.

[0032] The retainer device 43 further comprises a removable retainer element 47 arrangeable around the pin 35 between the inner side 41 of the heater device 19 and the head 45, such that the retainer element 47 forms a counter bearing to the inner side 41 of the heater device 19 and the head 45 forms a counter bearing to the retainer element 47. The retainer element 47 is formed as an elastic ring that can be pulled over the head 45 by stretching the ring and thus extending the diameter of the ring.

[0033] The at least one fastener 33 comprises a base member 51 in the form of a base plate attached to the inner surface 41 of the leading edge panel 17 by adhesive and holding the pin 35, in the present embodiment being formed integrally with the pin 35. The base member 51 is preferably formed of a metal material having a high thermal conductivity between, so that the heat from the heater device 19 can be transferred to the leading edge panel 17 as unhindered as possible in the area of the base member 51.

[0034] The heater device 19 is additionally attached to the inner surface 29 of the leading edge panel 17 by an adhesive layer 53 formed between the inner surface 29 of the leading edge panel 17 and the outer side 39 of the heater device 19. The adhesive layer 53 is flexible to avoid delamination upon smaller impacts. Further, the adhesive layer 53 has a high thermal conductivity above 0.5 W/m*K, and has a relatively low adhesive strength of below 0.4 N/mm The chemical composition of the adhesive layer 53 is adapted to have mechanical properties such that it allows a peel of the heater device 19 from the leading edge panel 17 at low forces, preferably ranging below 0.4 N/mm As shown in FIG. 4, to enable gripping of the heater device 19 by hand or by a simple tool a plurality of tabs 55 are distributed along the edges of the heater device 19. Further, the adhesive layer 53 is formed with a temperature dependency, wherein it sustains the loading spectrum of the normal aircraft operation, but at higher temperatures above the operating temperature window of the aircraft 1, e.g., above 100° C., which might be applied during maintenance when the heater device 19 is to be removed, the adhesive layer 53 becomes weak enough so that the heater device 19 can be peeled off by hand or by tool from the leading edge panel 17 at peel forces lower that 0.4 N/mm

[0035] FIG. 5 shows a further embodiment of the leading edge structure 15 where a lower panel 57 opposite from the leading edge panel 17 and the heater device 19 attached thereto has an access opening 59 closed by a removable cover 61. Removing the cover 61 allows access through the access opening 59 into the inside 30 of the leading edge structure 15 and, thus, to the inner surface 29 of the leading edge panel 17 with the attached heater device 19, so that the heater device 19 can be easily removed and replaced during maintenance without dismounting the entire leading edge panel 17 or lower panel 57.

[0036] By the leading edge structure 15 according to the invention as described above, the heater device 19 can be removed and replaced in a very quick and simple manner during maintenance without the need to replace the entire leading edge panel 17. Merely, it might be required to dismount the leading edge panel 17 or some other structure, such as the lower panel 57 or the cover 61, to make the heater device 19 accessible for detachment. This largely simplifies maintenance and reduces costs. At the same time, the heater device 19 does not need to be designed for high impact loads, e.g., due to bird strike, since the heater device 19 is arranged at the inner surface 29 of the leading edge panel 17, which makes the leading edge structure 15 lightweight and cost-efficient.

[0037] While at least one exemplary embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms “comprise” or “comprising” do not exclude other elements or steps, the terms “a” or “one” do not exclude a plural number, and the term “or” means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.