GB2533785A

GB2533785A - A device for removing debris from an aerodynamic structure

Info

Publication number: GB2533785A
Application number: GB1423307.6A
Authority: GB
Inventors: Korya Chetan; Mcvey Andrew
Original assignee: Airbus Operations Ltd
Current assignee: Airbus Operations Ltd
Priority date: 2014-12-29
Filing date: 2014-12-29
Publication date: 2016-07-06
Anticipated expiration: 2034-12-29
Also published as: US20160185457A1; GB2533785B; GB201423307D0

Abstract

A device for removing debris, such as insects and ice, from an aerodynamic structure of an aircraft (such as a wing) and in which the aerodynamic structure has upper (14, figure 5) and lower (15) surfaces separated by a leading edge (12) extending along the length of the aerodynamic structure. The device comprises a spine 20 positionable so as to extend between the surfaces and over the leading edge of the aerodynamic structure, a scraping edge 22a, 23a, carried by the spine facing a direction that extends along the length, and a drive mechanism (36) configured to move the spine so that the scraping edge scrapes debris from along the length of the aerodynamic structure. The spine is configured to bias the scraping edge against the aerodynamic structure. Preferably the spine includes an elongate body 24 and flanges 25, on which the scraping edges are formed and which may be biased by springs 33. A heating element 35 may be included.

Description

TITLE

A DEVICE FOR REMOVING DEBRIS FROM AN AERODYNAMIC STRUCTURE

TECHNICAL FIELD

[0001] The present invention relates to a device for removing debris from an aerodynamic structure and to an aerodynamic structure incorporating the device of the invention.

BACKGROUND

[0002] In the field of aeronautics it is known that laminar flow wing designs require an uninterrupted and undisturbed air flow over them in order to function properly. However, during certain phase of flight the surfaces of aerodynamic structures such as wings, can become contaminated with debris.

[0003] During landing and take-off insects may accumulate on a leading edge of lifting surfaces and, during cruise, ice can form on or behind the leading edge. Organic build up and ice formation reduces the efficiency of an aircraft. It is therefore desirable to ensure that aerodynamic surfaces of an aircraft are kept free of such debris.

[0004] It is known to provide large transport passenger aircraft with ice protection systems to prevent ice build up by making use of heating elements. However, such ice protection systems arc located within the wing structure or arc integral with the wing structure, such as heating pads embedded in the leading edge or hot air bleeds from an engine. Failure of a single component in these ice protection systems can he complicated and time consuming to fix.

[0005] Furthermore, it is known to provide sailplanes, and the like, with a simple scraper to remove insects and debris from the leading edge of the aerodynamic surface. Scrapers of this kind are operated by pulley systems and require a pilot to manually position, operate, and remove them during flight. Scrapers of this type do not have the ability to deal with ice build up and are not suitable for use on commercial transport aircraft.

SUMMARY

[0006] According to the invention, there is provided a device for removing debris, such as insects and ice, from an aerodynamic structure of an aircraft, the aerodynamic structure having upper and lower surfaces separated by a leading edge extending along a length of said aerodynamic structure, the device comprising a spine positionable so as to extend between said upper and lower surfaces over the leading edge of the aerodynamic structure, a scraping edge carried by said spine facing a direction that extends along said length, and a drive mechanism configured to move said spine in said direction so that the scraping edge scrapes debris from said aerodynamic structure, wherein the spine is configured to bias the scraping edge against said aerodynamic structure.

I0007J The spine is preferably configured to bias the scraping edge against said aerodynamic structure along the length of said spine.

[0008] The spine may be flexible and preferably includes an elongate main body and a flange extending from a longitudinal edge of said main body. The scraping edge can then be formed at an end of said flange remote from said main body.

[0009] In a preferred embodiment, a biasing element is mounted to the main body to bias the flange, and the scraping edge formed at an end of said flange, in a direction towards the aerodynamic surface on which the spine is positioned.

I0010J Preferably, the main body comprises a base wall positionable against said aerodynamic structure and a wall extending upwardly from said base in a direction away from said aerodynamic structure to define a recess along the length of the spine, said biasing element being received in said recess.

[0011] The flange preferably extends from said wall and the biasing element is configured to act on said wall to deflect said flange and bias the scraping edge against said aerodynamic surface.

[0012] In some embodiments, the wall may be divided into sections by slots in said main body.

[0013] In preferred embodiments, a heating element is received in the flange adjacent to said scraping edge and extends along the length of the spine.

[0014] The flange may comprise a plurality of spaced connecting arms extending between said wall and the scraping dement. The heating element may he received in a space in the flange beneath said spaced connecting arms.

[0015] In some embodiments, a flange extends from opposing longitudinal edges of said main body, each flange having a scraping element that faces in opposite directions extending along the length of the aerodynamic surface, wherein the biasing element is configured to bias each scraping element against said aerodynamic surface.

[0016] In any of the preferred embodiments, the biasing element may comprise a plurality of springs spaced from each other along the length of the spine and positioned so as to apply a biasing force to the flange to urge the scraping edge in a direction towards said aerodynamic surface.

[0017] The drive mechanism is preferably positionable within said aerodynamic structure for connection to the spine extending between said upper and lower surfaces and over the leading edge of the aerodynamic structure.

[0018] Preferably, the spine is formed from heat resistant polycarbonate.

[0019] According to another aspect of the invention, there is provided an aerodynamic structure incorporating the device for removing debris according to the invention.

BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Embodiments of the invention will now be described, by way of example only, with reference to Figures 3 to 6 of the accompanying drawings, in which: Fig. 1 shows a schematic perspective/front view of a known aircraft; Fig. 2 shows a schematic cross-sectional view of an aerodynamic structure of the aircraft in Fig. 1; Fig. 3 shows a schematic perspective view of an embodiment of a device according to the invention for removing debris positioned over a leading edge of the aerodynamic structure shown in Fig. 1 and Fig. 2; Fig. 4 shows a schematic cross-sectional view of a a portion of the device shown in Fig. 3; Fig. 5 shows a schematic cross-sectional view of the device for removing debris positioned over the leading edge of the aerodynamic structure shown in Fig. I; and, Fig. 6 shows a schematic cross-sectional view of another embodiment of the device for removing debris positioned over the leading edge of the aerodynamic structure shown in Fig. 1.

DETAILED DESCRIPTION

[0021] Referring to Fig. 1, a commercial aircraft 1 of known configuration is shown. The aircraft 1 comprises aerodynamic structures 2 that extend from a fuselage 3. The aerodynamic structures include the main wings 4, tailplanes 5 and vertical tail 6.

[0022] The main wings 4 provide the majority of the lift. Ailerons 8 on the main wing 4 are used to control the roll of the aircraft 1 about its longitudinal axis. The tailplane 5 also contributes to the lift force. Elevators 9 on the tailplane 5 are used to control the pitch of the aircraft 1 about its lateral axis. The vertical tail 6 comprises a rudder 10 which helps to control the yaw of the aircraft 1 about its vertical axis.

[0023] The aerodynamic structures 2 on modern aircraft I are tapered in an outboard direction away from the fuselage 3, as shown in Fig. 1. Therefore, the chord of the aerodynamic structure 2 at its root, where the aerodynamic structure 2 joins the fuselage, is greater than at its tip. The thickness of the aerodynamic structures 2 also vary along its span and therefore, the profile, or cross-section, of the aerodynamic structures 2 also vary.

[0024] Referring to Fig. 2, a cross-sectional profile through a main wing 4 is shown. The aerodynamic structure 2 comprises a body 11. The body 11 comprises a leading edge 12. The leading edge 12 is the first component of the main wing 4 which the airflow encounters during flight. Therefore, especially during take-off and landing, insects or debris may accumulate on the leading edge 12.

[0025] Furthermore, during cruise atmospheric icing can occur on and/or just behind the leading edge 12. This can lead to flow separation from the aerodynamic structure 2 and reduce the ability to control the aircraft 1.

10026] The body 11 of the aerodynamic structure 2 further comprises a trailing edge 13. The trailing edge 13 is the last component of the aerodynamic structure 2 which the airflow encounters during flight and is where the control surfaces, such as the ailerons 8, elevators, 9 and rudder 10, shown in Fig. 1, are located.

[0027] The body 11 further comprises an upper surface 14 and a lower surface 15. Both the upper and lower surfaces 14, 15 extend from the leading edge 12 back to the trailing edge 13 and are profiled to generate lift during flight.

[0028] Other systems, such as fuel tanks (not shown) and actuators (not shown) for the control surfaces 8, 9, 10 may be disposed internally of the body 11.

10029] Referring now to Fig. 3, a device according to an embodiment of the invention, for removing debris, such as insects and ice, from an aerodynamic structure 2 is shown mounted to a wing 4 of Figure 2. The device comprises an elongate flexible spine 20 that is positioned on the wing 4 so that it extends between upper and lower surfaces 14, 15 and wraps around its leading edge 12.

[0030] The spine 20 carries a scraping edge 22. In the illustrated embodiment, the spine 20 carries two scraping edges 22a, 22b which are supported by the spine 20 and which extend along opposing longitudinal -5 -edges. One scraping edge 22h faces in an inboard direction towards the fuselage 3 and, the other scraping edge 22a faces in an outboard direction away from the fuselage 3. In another, unillustrated embodiment, there is only one scraping edge 22 extending along one longitudinal edge of the spine 20. [0031] The spine 20 comprises a main body 24 and a flange 25 on either side of the main body 24 that extends outwardly from each longitudinal edge of the main body 24 for the length of the spine 20. The scraping edge 22a, 22h is formed on or is mounted to, an end of the flange 25 remote from the main body 24. Each flange 25 may flex upwardly and downwardly relative to the main body 24, in the direction indicated by arrow 'F' in Figure 3, in order to enable the scraping edge 22a, 22b to be biased downwardly, towards and against the surface of the wing 4 upon which the spine 20 is positioned.

10032] The spine 20 is mounted to the wing 4 via a coupling 26 (see Figures 5 and 6) which allows the spine to slide in a direction along the length of the wing 4 in an inboard or outboard direction (i.e. direction 'A' or 'B', as shown in Figure 3), and in response to operation of a drive mechanism 36, such as a motor, mounted within the wing 4. The coupling 26 may take the form of one or more bearings 27 received within a slide member 28 which is of conventional design and will not be described here in detail.

[0033] As the spine 20 is driven in an inboard or outboard direction along the length of the aerodynamic structure in the direction of arrows 'A' or 'B', one of the outboard scraping edges 22a, 22b, which are biased against the surface of the wing 4, removes insects and ice from the surface, depending on the direction of travel of the spine 20. When the spine 20 is driven in an outboard direction 'B', scraping edge 22a removes insects and ice from the wing 4, and when the spine 20 is driven in the inboard direction 'A', scraping edge 22h removes insects and ice from the surface of the wing 4. [0034] The main body 24 of the spine 21 comprises a base wall 29 that is placed on the surface of the aerodynamic structure 2. Side walls upstand from opposing edges of the base wall 29 and extend along the length of the main body 24. Slots 31 are formed in the main body 24 to divide the side -6 -walls into individual wall sections 30. The base wall 29 and wall sections 30 together define a recess 32 to receive a biasing element 33. The biasing element 33 may comprise a plurality springs or spring-like elements that are parallel to and spaced from each other and have their axis extending at right angles to the longitudinal edge of the spine 20. Each spring 33 may extend between corresponding facing walls or wall sections 30 and they act to bias the walls or wall sections 30 in opposite directions away from each other in inboard and outboard directions extending along the length of the wing 4, i.e. in the directions indicated by arrows 'A' and 'B' in Figure 3. The action of the springs 33 against the wall sections 30 causes the wall sections 30 to bow outwardly. As each flange 25 extends from the walls or wall sections 30, they are urged, together with their scraping edges 22a, 22h formed at the remote end of each flange 25, in a downward direction towards and into contact with the aerodynamic surface 2 upon which the spine 20 is positioned. This means that, as the spine 20 is driven in an inboard or outboard direction along the length of the wing 4, the scraping edge 22a, 22b is biased against the wing 4 and effectively scrapes the surface to remove any build up of ice or bugs.

[0035] The scraping edge 22a, 22b may be connected to the wall sections 30 by spaced connecting arms 34. A connecting arm 34 may extend from an upper region of each wall section 30 at a downward angle to a location dose to an associated scraping edge 22a, 22b. A space is formed beneath or between the connecting arms 34, which may receive a flexible healing element 35 positioned adjacent to the scraping edge 22a, 22h and to which power may be supplied to heat the scraping edge 22a, 22h and thereby assist in ice removal.

10036] The spine 20 and flange 25 may be integrally formed from, for example, heat resistant polycarhonate.

[0037] Referring to Fig. 4, a partial cross-section through a flange 25 of the spine 20 of Figure 3 is shown and from which it is apparent that the scraping edge 22a may take the form of a blade 35. The blade 35 may be formed from a metallic material and can he embedded in the flange 25.

10038] Referring now to Fig. 5 and Fig. 6, schematic cross-sectional views of two different arrangements for mounting the spine 20 to the wing 4 are shown. As described above, the spine 20 is attached to the wing 4 by a coupling 26 that enables the spine 20 to slide in inboard and outboard directions. For example, bearings 27 may be rotatably mounted to the spine 20 and received in a slide member 28 attached to the wing 4. A drive mechanism 36, such as a motor, is located within the wing 4 and is operable to slide the spine 20 along the slide member 28 in each direction.

[0039] In the embodiment shown in Fig. 5, the coupling 26 comprises a single slide track 28 situated in front of a kreuger flap 37. In the embodiment shown in Fig. 6, the coupling 26 comprises double tracks 28 located behind the kreuger flap 45. Therefore, operation of the kreuger flap 37 is not prevented due to the presence of the device 20. When the kreuger flap 37 is deployed, operation of the device 20 is reduced to a section of the wing 4 where the kreuger flap 45 is not deployed. Alternatively, the device 20 may return to a "home" position when not in use so that it does not obstruct control surfaces, such as the kreuger flap 37.

[0040] It will be appreciated that the spine 20 may be driven from the motor 36 by a pulley. Alternatively, the motor may be external, a drive shaft and screw, or an internal gear may he employed.

[0041] It will he appreciated that the foregoing description is given by way of example only and that modifications may be made to the present invention without departing from the scope of the appended claims. -8 -

Claims

CLAIMS1. A device for removing debris, such as insects and ice, from an aerodynamic structure of an aircraft, the aerodynamic structure having upper and lower surfaces separated by a leading edge extending along a length of said aerodynamic structure, the device comprising a spine positionable so as to extend between said upper and lower surfaces over the leading edge of the aerodynamic structure, a scraping edge carried by said spine facing a direction that extends along said length, and a drive mechanism configured to move said spine in said direction so that the scraping edge scrapes debris from along said length of the aerodynamic structure, wherein the spine is configured to bias the scraping edge against said aerodynamic structure.
2. A device according to claim 1, wherein the spine is configured to bias the scraping edge against said aerodynamic structure along the length of said spine.
3. A device according to claim 1 or claim 2, wherein the spine is flexible and includes an elongate main body and a flange extending from a longitudinal edge of said main body, the scraping edge being formed at an end of said flange remote from said main body.
4. A device according to claim 3, wherein a biasing clement is mounted to the main body to bias the flange, and the scraping edge formed at an end of said flange, in a direction towards the aerodynamic surface on which the spine is positioned.
5. A device according to claim 4, wherein the main body comprises a base wall positionable against said aerodynamic structure and a wall extending upwardly from said base in a direction away from said aerodynamic structure to define a recess along the length of the spine, said biasing element being received in said recess.
6. A device according to claim 5, wherein said flange extends from said wall and the biasing element is configured to act on said wall to deflect said flange and bias the scraping edge against said aerodynamic surface.
7. A device according to claim 6, wherein said wall is divided into sections by slots in said main body.
8. A device according to any of claims 3 to 7, wherein a heating element is received in the flange adjacent to said scraping edge and extends along the length of the spine.
9. A device according to claim 8, wherein the flange comprises a plurality of spaced connecting arms extending between said wall and the scraping element.
10. A device according to claim 9, wherein the heating element is received in a space in the flange beneath said spaced connecting arms.
11. A device according to any of claims 3 to 10, wherein a flange extends from opposing longitudinal edges of said main body, each flange having a scraping element that faces in opposite directions extending along the length of the aerodynamic surface, wherein the biasing element is configured to bias each scraping clement against said aerodynamic surface.
12. A device according to any of claims 3 to 11, wherein the biasing dement comprises a a plurality of springs spaced from each other along the length of the spine and positioned so as to apply a biasing force to the flange to urge the scraping edge in a direction towards said aerodynamic surface.
13. A device according to any one of the preceding claims, wherein said drive mechanism is positionable within said aerodynamic structure for connection to the spine extending between said upper and lower surfaces and over the leading edge of the aerodynamic structure.

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14. A device according to any preceding claim, wherein the spine is formed from heat resistant polycarbonate.
15. An aerodynamic structure incorporating the device for removing debris according to any of the preceding claims.Amendments to the claims have been filed as followsCLAIMS1. A device for removing debris, such as insects and ice, from an aerodynamic structure of an aircraft, the aerodynamic structure having upper and lower surfaces separated by a leading edge extending along a length of said aerodynamic structure, the device comprising a spine positionable so as to extend between said upper and lower surfaces over the leading edge of the aerodynamic structure, a scraping edge carried by said spine facing a direction that extends along said length, and a drive mechanism configured to move said spine in said direction so that the scraping edge scrapes debris from along said length of the aerodynamic structure, wherein the spine is flexible and includes an elongate main body and a flange extending from a longitudinal edge of said main body, the scraping edge being formed at an end of said flange remote from said main body, the device further comprising a biasing element mounted to the main body to bias the scraping edge against said aerodynamic structure.2. A device according to claim I. wherein the spine is configured to bias the scraping edge against said aerodynamic structure along the length of said spine.3. A device according to claim 1 or 2, wherein the main body comprises a base wall positionable against said aerodynamic structure and a wall extending upwardly from said base in a direction away from said aerodynamic structure to define a recess along the length of the spine, said biasing element, being received in said recess.4. A device according to claim 3, wherein said flange extends from said wall and the biasing element is configured to act on said wall to deflect said flange and bias the scraping edge against said aerodynamic surface.5. A device according to claim 4, wherein said wall is divided into sections by slots in said main body.O6. A device according to any of claims 3 to 5, wherein a heating element is received in the flange adjacent to said scraping edge and extends along the length of the spine.7. A device according to claim 6, wherein the flange comprises a plurality of spaced connecting arms extending between said wall and the scraping element.8. A device according to claim 7, wherein the heating element is received in a space in the flange beneath said spaced connecting arms.9. A device according to any of claims 3 to 8, wherein a flange extends from opposing longitudinal edges of said main body, each flange having a scraping element that faces in opposite directions extending along the length of the aerodynamic surface, wherein the biasing element is configured to bias each scraping element against said aerodynamic surface. C\IID. A device according to any of claims 3 to 9, wherein the biasing clement comprises a plurality of springs spaced from each other along the length of the spine and positioned so as to apply a biasing force to the flange to urge the scraping edge in a direction towards said aerodynamic surface.11. A device according to any one of the preceding claims, wherein said drive mechanism is positionable within said aerodynamic structure for connection to the spine extending between said upper and lower surfaces and over the leading edge of the aerodynamic structure.12. A device according to any preceding claim, wherein the spine is formed from heat resistant polycarhonate.13. An aerodynamic structure incorporating the device for removing debris according to any of the preceding claims.